Abstract

An example method includes obtaining a representation of a change in rotational speed of an electric machine; obtaining a representation of an expected change in rotational speed of the electric machine; and determining, based on the obtained representation of the change in rotational speed of the electric machine and the representation of an expected change in rotational speed of the electric machine, whether a disconnect device has failed, wherein, when operating in an engaged state, the disconnect device is configured to couple rotational mechanical energy between the electric machine and a rotating device, and wherein, when operating in a disengaged state, the disconnect device is not configured to couple rotational mechanical energy between the electric machine and the rotating device.

IPC Classes  ?

• G01M 13/022 - Power-transmitting couplings or clutches
• H02K 7/10 - Structural association with clutches, brakes, gears, pulleys or mechanical starters
• H02K 7/18 - Structural association of electric generators with mechanical driving motors, e.g.with turbines

Abstract

An exhaust assembly for use with a gas turbine engine includes an exhaust duct and a damper system coupled to the exhaust duct. The exhaust duct is configured for fluid communication with the gas turbine engine to receive hot exhaust gases produced by the gas turbine engine. The exhaust duct includes a plurality of panels that define an exhaust passageway. The damper system is coupled to one of the plurality of panels and is configured to dampen vibration of the exhaust duct during use of the gas turbine engine.

IPC Classes  ?

• F01D 15/10 - Adaptations for driving, or combinations with, electric generators
• F01D 25/30 - Exhaust heads, chambers, or the like
• F02C 7/24 - Heat or noise insulation
• F02K 1/82 - Jet pipe walls, e.g. liners

Abstract

A two-phase pump loop (TPPL) for dissipating a thermal load during operation of an apparatus includes a coolant, a vapor/liquid receiver, a pump, an evaporator, a condenser, a valve (V1) configured to regulate a pressure at an outlet of the condenser; a valve (V2) having a control set point set equivalent to a low pressure (P L) measured in the vapor/liquid receiver; and a controller configured to control the set points of V1 and V2. The TPPL is configured to cool the thermal load with tight control of the temperature of the coolant that is cooling the apparatus. The TPPL may be combined with a vapor cycle system (VCS) to provide a thermal management system with the VCS being configured to use the same or different coolant than the TPPL.

IPC Classes  ?

• F01P 3/22 - Liquid cooling characterised by evaporation and condensation of coolant in closed cyclesLiquid cooling characterised by the coolant reaching higher temperatures than normal atmospheric boiling-point
• F25B 7/00 - Compression machines, plants or systems, with cascade operation, i.e. with two or more circuits, the heat from the condenser of one circuit being absorbed by the evaporator of the next circuit
• F28D 15/02 - Heat-exchange apparatus with the intermediate heat-transfer medium in closed tubes passing into or through the conduit walls in which the medium condenses and evaporates, e.g. heat-pipes
• F28D 21/00 - Heat-exchange apparatus not covered by any of the groups
• F28F 27/00 - Control arrangements or safety devices specially adapted for heat-exchange or heat-transfer apparatus

Abstract

A turbine vane comprising ceramic matrix composite materials. Theturbine vane includes an vane support core, an airfoil, and a pair of end walls that are spaced apart from one another to define a gas path. The turbine vane is formed from a plurality of ceramic plies or preforms that are infiltrated with ceramic matrix material to form a one-piece ceramic matrix composite turbine vane.

IPC Classes  ?

• C04B 35/80 - Fibres, filaments, whiskers, platelets, or the like
• F01D 9/02 - NozzlesNozzle boxesStator bladesGuide conduits

Abstract

A turbofan engine has a fan portion in fluid communication with a core stream and a bypass stream of air separated by splitters disposed both upstream and downstream of the fan portion. A blade splitter (shroud) on the fan partially spans the fan blade thus separating the core and bypass streams downstream while leaving a gap upstream for communication between the flows. The communication gap expands the operational range of the fan over fans without the communication gap.

IPC Classes  ?

• F01D 11/02 - Preventing or minimising internal leakage of working fluid, e.g. between stages by non-contact sealings, e.g. of labyrinth type
• F02K 3/06 - Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber the plant including ducted fans, i.e. fans with high volume, low-pressure outputs, for augmenting jet thrust, e.g. of double-flow type with front fan
• F02K 3/075 - Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber the plant including ducted fans, i.e. fans with high volume, low-pressure outputs, for augmenting jet thrust, e.g. of double-flow type controlling flow ratio between flows

Abstract

A heat transfer system for high transient heat loads includes a fluid, a heat exchanger; a compressor downstream of the heat exchanger outlet; a condenser downstream of the compressor outlet, and a thermal energy storage (TES) section downstream of the condenser outlet and upstream of the heat exchanger. The TES section may include a first pressure regulating valve downstream of a TES unit; and a second pressure regulating valve upstream of the first pressure regulating valve.

IPC Classes  ?

• F25B 1/00 - Compression machines, plants or systems with non-reversible cycle
• F25B 40/00 - Subcoolers, desuperheaters or superheaters

Abstract

A heat transfer system for high transient heat loads includes a fluid, a heat exchanger; a compressor downstream of the heat exchanger outlet; a condenser downstream of the compressor outlet, and a thermal energy storage (TES) section downstream of the condenser outlet and upstream of the heat exchanger. The TES section may include a first pressure regulating valve downstream of a TES unit; and a second pressure regulating valve upstream of the first pressure regulating valve.

IPC Classes  ?

• F25B 1/00 - Compression machines, plants or systems with non-reversible cycle
• F25B 40/00 - Subcoolers, desuperheaters or superheaters

Abstract

In some examples, an electrical power system includes a differential bus including a high-side rail and a low-side rail, a power source configured to generate power, and a bulk capacitor coupled between the high-side rail and the low-side rail, the bulk capacitor configured to filter the power generated by the power source. The electrical power system also includes a converter configured to convert the power filtered by the bulk capacitor and a pre-charging circuit comprising one or more switches and a middle capacitor, the pre-charging circuit configured to pre-charge the bulk capacitor.

IPC Classes  ?

• H02M 1/08 - Circuits specially adapted for the generation of control voltages for semiconductor devices incorporated in static converters
• H02M 1/36 - Means for starting or stopping converters

Abstract

A bearing system includes bearing unit and a lubrication system. The bearing unit includes an outer race, a plurality of internal rotating components, and an inner race. The lubrication system includes an injector for delivering a stream of lubrication to the plurality of rotating components to withdraw heat generated and lubricate the bearing unit during operation of the bearing system.

IPC Classes  ?

• F01D 25/16 - Arrangement of bearingsSupporting or mounting bearings in casings
• F01D 25/18 - Lubricating arrangements
• F02C 7/06 - Arrangement of bearingsLubricating
• F16C 33/66 - Special parts or details in view of lubrication

Abstract

A bearing system includes bearing unit and a side-jet injector. The bearing unit includes an outer race, a plurality of internal rotating components, and an inner race. The side-jet injector includes an injector for delivering a lubrication source to the plurality of rotating components to withdraw heat generated and lubricate the bearing unit during operation of the bearing system.

IPC Classes  ?

• F01D 25/16 - Arrangement of bearingsSupporting or mounting bearings in casings
• F01D 25/18 - Lubricating arrangements
• F02C 7/06 - Arrangement of bearingsLubricating
• F16C 33/66 - Special parts or details in view of lubrication
• F16C 35/04 - Rigid support of bearing unitsHousings, e.g. caps, covers in the case of ball or roller bearings
• F16N 1/00 - Constructional modifications of parts of machines or apparatus for the purpose of lubrication
• F16N 7/32 - Mist lubrication

Abstract

A member may have a primary major surface and a secondary major surface. The member may form an array of apertures extending from the primary major surface to the secondary major surface. The array of apertures includes at least one aperture comprising two or more conduits. The axis of each conduit intersects the axis of each other conduit in the aperture. The cross-section of at least one of the conduits perpendicular to its axis may be circular. In some embodiments, an aperture may comprise two or three conduits.

IPC Classes  ?

• F01D 5/08 - Heating, heat-insulating, or cooling means
• F01D 5/18 - Hollow bladesHeating, heat-insulating, or cooling means on blades
• F01D 25/12 - Cooling
• F02C 7/12 - Cooling of plants

Abstract

A receiver in a communication system may include a buffer and hardware. The buffer may be configured to store a communication signal comprising one or more pulses representative of data. The hardware may be configured to determine whether a data authentication pulse has been superimposed over at least one of the one or more pulses, and authenticate, based on the determination of whether the data authentication pulse has been superimposed over at least one of the one or more pulses, the one or more pulses as a valid representation of the data.

IPC Classes  ?

• H04B 10/11 - Arrangements specific to free-space transmission, i.e. transmission through air or vacuum
• H04B 10/25 - Arrangements specific to fibre transmission
• H04B 10/85 - Protection from unauthorised access, e.g. eavesdrop protection
• H04L 9/32 - Arrangements for secret or secure communicationsNetwork security protocols including means for verifying the identity or authority of a user of the system

Abstract

The present disclosure relates to a gas turbine engine including a turbine wheel mounted for rotation about a central axis and a turbine shroud ring mounted radially outward from the turbine wheel. The turbine wheel includes a plurality of blades that are spaced apart radially from the turbine shroud ring to establish a blade tip clearance gap. The gas turbine engine further includes a blade tip clearance control system that passively controls the size of the clearance gap based on engine operation.

IPC Classes  ?

• F01D 9/04 - NozzlesNozzle boxesStator bladesGuide conduits forming ring or sector
• F01D 11/14 - Adjusting or regulating tip-clearance, i.e. distance between rotor-blade tips and stator casing
• F01D 11/18 - Adjusting or regulating tip-clearance, i.e. distance between rotor-blade tips and stator casing by self-adjusting means using stator or rotor components with predetermined thermal response, e.g. selective insulation, thermal inertia, differential expansion

Abstract

Systems and methods are provided that use a tip clearance control apparatus comprising a mechanical iris, where the tip clearance control apparatus controls a distance between a tip of a blade and a ring of abradable material positioned in an adjustable opening of the mechanical iris.

IPC Classes  ?

• F01D 11/12 - Preventing or minimising internal leakage of working fluid, e.g. between stages for sealing space between rotor blade tips and stator using a rubstrip, e.g. erodible, deformable or resiliently biased part
• F01D 11/22 - Actively adjusting tip-clearance by mechanically actuating the stator or rotor components, e.g. moving shroud sections relative to the rotor

Abstract

A system is described that includes a controllable component of an engine configured to regulate fuel flow to the engine, a digital control unit configured to control the engine by at least communicating with the controllable component of the engine, and a protection component configured to disable communication between the digital control unit and the controllable component of the engine. The system further includes an analog control unit configured to control the engine by at least communicating with the controllable component of the engine in response to the protection component disabling communication between the digital control unit and the controllable component of the engine.

IPC Classes  ?

• B64D 31/00 - Power plant control systemsArrangement of power plant control systems in aircraft
• F02C 9/26 - Control of fuel supply
• F02C 9/46 - Emergency fuel control

Abstract

A system may include a receiver configured to receive a communications signal from a transmitter and processing circuitry configured to: determine at least one frequency characteristic of the communications signal and compare the at least one frequency characteristic to at least one verified frequency characteristic stored by a memory associated with the processing circuitry to determine whether the transmitter is a verified transmitter. In some examples, the transmitter, receiver and communications signal are an optical transmitter, and optical receiver, and an optical signal, respectively.

IPC Classes  ?

• H04B 10/11 - Arrangements specific to free-space transmission, i.e. transmission through air or vacuum
• H04B 10/548 - Phase or frequency modulation
• H04B 10/80 - Optical aspects relating to the use of optical transmission for specific applications, not provided for in groups , e.g. optical power feeding or optical transmission through water

Abstract

An example hybrid aircraft propulsion system includes one or more parallel propulsion units, each of the parallel propulsion units comprising: a first propulsor; a gas turbine engine configured to drive the first propulsor; and an electrical machine selectively configurable to: generate, for output via one or more electrical busses, electrical energy using mechanical energy derived from the first propulsor or the gas turbine engine; and drive the first propulsor using electrical energy received via the one or more electrical busses; and one or more series propulsion units, each of the series propulsion units comprising: a second propulsor; and an electrical machine selectively configurable to: generate, for output via the one or more electrical busses, electrical energy using mechanical energy derived from the second propulsor or the gas turbine engine; and drive the second propulsor using electrical energy received from one or more electrical busses.

IPC Classes  ?

• B60K 6/20 - Arrangement or mounting of plural diverse prime-movers for mutual or common propulsion, e.g. hybrid propulsion systems comprising electric motors and internal combustion engines the prime-movers consisting of electric motors and internal combustion engines, e.g. HEVs
• B64D 35/00 - Transmitting power from power plants to propellers or rotorsArrangements of transmissions
• B64D 41/00 - Power installations for auxiliary purposes

Abstract

An example hybrid aircraft propulsion system includes a plurality of electrical busses comprising a propulsion bus, a critical bus, and a non-critical bus; an electrical energy storage system coupled to each of the plurality of electrical busses; one or more power units configured to generate and output electrical energy via the propulsion bus; one or more electrical machines configured to drive respective propulsors using electrical energy received via the propulsion bus; one or more hotel loads configured to receive energy via the non-critical bus; and one or more critical loads configured to receive energy via the critical bus.

IPC Classes  ?

• B60K 6/20 - Arrangement or mounting of plural diverse prime-movers for mutual or common propulsion, e.g. hybrid propulsion systems comprising electric motors and internal combustion engines the prime-movers consisting of electric motors and internal combustion engines, e.g. HEVs
• B64D 35/00 - Transmitting power from power plants to propellers or rotorsArrangements of transmissions
• B64D 41/00 - Power installations for auxiliary purposes

Abstract

An example hybrid aircraft propulsion system includes a plurality of power units configured to output electrical energy onto one or more electrical busses; one or more propulsors; and one or more electrical machines, each respective electrical machine configured to drive a respective propulsor of the one or more propulsors using electrical energy received from at least one of the one or more electrical busses.

IPC Classes  ?

• B60K 6/20 - Arrangement or mounting of plural diverse prime-movers for mutual or common propulsion, e.g. hybrid propulsion systems comprising electric motors and internal combustion engines the prime-movers consisting of electric motors and internal combustion engines, e.g. HEVs
• B64D 35/00 - Transmitting power from power plants to propellers or rotorsArrangements of transmissions
• B64D 41/00 - Power installations for auxiliary purposes

Abstract

An example hybrid aircraft propulsion system includes one or more power units configured to output electrical energy onto one or more electrical busses; a plurality of propulsors; and a plurality of electrical machines, each respective electrical machine configured to drive a respective propulsor of the plurality of propulsors using electrical energy received from at least one of the one or more electrical busses.

IPC Classes  ?

• B60K 6/20 - Arrangement or mounting of plural diverse prime-movers for mutual or common propulsion, e.g. hybrid propulsion systems comprising electric motors and internal combustion engines the prime-movers consisting of electric motors and internal combustion engines, e.g. HEVs
• B64D 35/00 - Transmitting power from power plants to propellers or rotorsArrangements of transmissions
• B64D 41/00 - Power installations for auxiliary purposes

Abstract

Energy storage systems for aircraft and methods of operating the same are provided. The energy storage system may include a main battery, a propulsion power bus, a non-critical bus, a critical bus, and an engine starter bus. The propulsion power bus may be configured to convey electricity, which is supplied by the main battery, to an electric propulsion machine configured to provide propulsion for the aircraft. The non-critical bus may be configured to convey electricity to a hotel load on the aircraft. The critical bus may be configured to convey electricity, which is supplied by the main battery, to a critical load on the aircraft. The engine starter bus may be configured to convey electricity, which is supplied by the main battery, to an electric starter for a gas turbine engine, where the gas turbine engine is configured to power the electric propulsion machine.

IPC Classes  ?

• B64D 27/00 - Arrangement or mounting of power plants in aircraftAircraft characterised by the type or position of power plants
• B64D 41/00 - Power installations for auxiliary purposes

Abstract

A combustor dome may be formed by way of additive layer manufacturing. The combustor dome may further include a raised outer surface and a recessed outer surface on a hot side of the combustor dome. The recessed outer surfaces may be closer to the cold side than the raised outer surfaces. The combustor dome may include a shadow surface defined between the raised outer surface and recessed outer surface. The shadow surface may define a corresponding cooling outlet in fluid communication with an internal cooling channel defined inside of the combustor dome. The cooling outlet may release air from the internal cooling channel to the hot axial side of the combustor dome.

IPC Classes  ?

• F23R 3/04 - Air inlet arrangements

Abstract

In some examples, an electrical power system includes a differential bus, a power converter coupled to the differential bus, and a controller configured to control the power converter based on a first target value for the differential bus. The controller is also configured to sense that a ground fault has occurred in the electrical power system while controlling the power converter based on the first target value. The controller is further configured to, responsive to sensing that the ground fault has occurred, control the power converter based on a second target value for the differential bus, the second target value being different than the first target value.

IPC Classes  ?

• H02H 3/16 - Emergency protective circuit arrangements for automatic disconnection directly responsive to an undesired change from normal electric working condition, with or without subsequent reconnection responsive to fault current to earth, frame or mass
• H02M 1/32 - Means for protecting converters other than by automatic disconnection

Abstract

A redundant, load-sharing system and method for distributing electrical power to components in a vehicle. The system including a source of power, multiple power distribution buses, a plurality of switching devices and at least two channel controllers. The system being configured to isolate the components and power sources that are determined to be electrically noisy from the components and the power sources that are sensitive to electric noise. Each of the components may be assigned a priority based on the criticality of the component to the operation of the vehicle. In the event of at least a partial loss of power in one or more of the power distribution buses, the switching devices disconnect the components from the effected power distribution buses in reverse order of the assigned priority.

IPC Classes  ?

• B60R 16/03 - Electric or fluid circuits specially adapted for vehicles and not otherwise provided forArrangement of elements of electric or fluid circuits specially adapted for vehicles and not otherwise provided for electric for supply of electrical power to vehicle subsystems
• B64D 41/00 - Power installations for auxiliary purposes
• H02J 13/00 - Circuit arrangements for providing remote indication of network conditions, e.g. an instantaneous record of the open or closed condition of each circuitbreaker in the networkCircuit arrangements for providing remote control of switching means in a power distribution network, e.g. switching in and out of current consumers by using a pulse code signal carried by the network

Abstract

Methods and systems are provided for controlling a component of an aircraft engine by communicating data over an inner control loop portion of a distributed engine control network for an aircraft; and controlling an operation of the aircraft engine by communicating encrypted data over an outer control loop portion of the distributed engine control network, wherein the data communicated over the inner control loop portion is unencrypted or encrypted with weaker encryption than the data communicated over the outer control loop portion.

IPC Classes  ?

• H04L 9/18 - Encryption by serially and continuously modifying data stream elements, e.g. stream cipher systems
• H04L 12/28 - Data switching networks characterised by path configuration, e.g. LAN [Local Area Networks] or WAN [Wide Area Networks]

Abstract

An electronics enclosure may include a fibrous thermoelectric material; a thermally and electrically conductive mesh; and a matrix material in which the fibrous thermoelectric material and the thermally and electrically conductive mesh are embedded.

IPC Classes  ?

• B32B 7/025 - Electric or magnetic properties
• B32B 7/027 - Thermal properties
• B32B 27/04 - Layered products essentially comprising synthetic resin as impregnant, bonding, or embedding substance
• H01B 1/02 - Conductors or conductive bodies characterised by the conductive materialsSelection of materials as conductors mainly consisting of metals or alloys
• H05K 5/02 - Casings, cabinets or drawers for electric apparatus Details
• H05K 7/20 - Modifications to facilitate cooling, ventilating, or heating

Abstract

In some examples, a method includes determining, by a controller in a system, a result of a first control loop based on a first sensed signal in a first instance and determining, by the controller, a result of a second control loop based on a second sensed signal in a second instance. The method also includes clamping, by the controller, the result of the second control loop to be equal to the result of the first control loop in the first instance and clamping, by the controller, the result of the first control loop to be equal to the result of the second control loop in the second instance. The method further includes outputting, by the controller and to a component of the system, a control signal based on the result of the first control loop.

IPC Classes  ?

• F02D 41/04 - Introducing corrections for particular operating conditions
• G05B 11/00 - Automatic controllers
• G05B 11/06 - Automatic controllers electric in which the output signal represents a continuous function of the deviation from the desired value, i.e. continuous controllers
• G05B 19/042 - Programme control other than numerical control, i.e. in sequence controllers or logic controllers using digital processors

Abstract

An oil supply system includes an oil supply assembly in a turbine engine. The assembly includes scavenge cavity and an oil supply tube located in and protected by a strut in the turbine engine to supply oil to a bearing chamber.

IPC Classes  ?

• F01D 25/16 - Arrangement of bearingsSupporting or mounting bearings in casings
• F01D 25/18 - Lubricating arrangements
• F02C 7/06 - Arrangement of bearingsLubricating

Abstract

A seal assembly can accommodate deflection between two components through a cartridge that is slidingly engaged with a slide plate.

IPC Classes  ?

• B64D 7/00 - Arrangement of military equipment, e.g. armaments, armament accessories or military shielding, in aircraftAdaptations of armament mountings for aircraft
• B64D 33/04 - Arrangement in aircraft of power plant parts or auxiliaries not otherwise provided for of exhaust outlets or jet pipes
• F02C 7/28 - Arrangement of seals
• F16J 15/52 - Sealings between relatively-movable members, by means of a sealing without relatively-moving surfaces, e.g. fluid-tight sealings for transmitting motion through a wall by means of sealing bellows or diaphragms

Abstract

An article may include a substrate including a metal or alloy; a bond coat directly on the substrate; an intermediate ceramic layer on the bond coat; and an abradable ceramic layer directly on the intermediate ceramic layer. The intermediate ceramic layer includes a stabilized tetragonal prime phase constitution and defines a first porosity. The abradable ceramic layer includes zirconia or hafnia stabilized in the tetragonal prime phase by a second mixture including between about 5 wt. % and about 10 wt. % ytterbia, between about 0.5 wt. % and about 2.5 wt. % samaria, and between about 1 wt. % and about 4 wt. % of at least one of lutetia, scandia, ceria, neodymia, europia, or gadolinia, and a balance zirconia or hafnia. The abradable ceramic layer defines a second porosity, and the second porosity is higher than the first porosity.

IPC Classes  ?

• C23C 4/02 - Pretreatment of the material to be coated, e.g. for coating on selected surface areas
• C23C 4/073 - Metallic material containing MCrAl or MCrAlY alloys, where M is nickel, cobalt or iron, with or without non-metal elements
• C23C 4/11 - Oxides
• C23C 28/00 - Coating for obtaining at least two superposed coatings either by methods not provided for in a single one of main groups , or by combinations of methods provided for in subclasses and

Abstract

A variable pitch blade holder for use with a gas turbine engine. The variable pitch blade holder is configured to retain a blade and to rotate about a center axis with the blade during operation of the gas turbine engine. The blade holder is adapted to rotate about a pitch change axis to vary a pitch of the blade.

IPC Classes  ?

• B64C 11/06 - Blade mountings for variable-pitch blades
• F01D 7/00 - Rotors with blades adjustable in operationControl thereof
• F02K 3/06 - Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber the plant including ducted fans, i.e. fans with high volume, low-pressure outputs, for augmenting jet thrust, e.g. of double-flow type with front fan

Abstract

A blade retainer adapted for use in a gas turbine engine is configured to block axial movement of a blade. The blade retainer includes a first brace, a second brace, and a web that extends between the first brace and the second brace.

IPC Classes  ?

• F01D 5/14 - Form or construction
• F01D 5/30 - Fixing blades to rotorsBlade roots
• F01D 5/32 - Locking, e.g. by final locking-blades or keys
• F02K 3/06 - Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber the plant including ducted fans, i.e. fans with high volume, low-pressure outputs, for augmenting jet thrust, e.g. of double-flow type with front fan

Abstract

A propulsor includes an electric motor, a fan unit, and a thrust system positioned downstream of and coupled to the fan unit. The electric motor converts electrical power to mechanical rotation to rotationally drive the fan unit and create an air stream directed towards the thrust control system

IPC Classes  ?

• B64C 15/02 - Attitude, flight direction or altitude control by jet reaction the jets being propulsion jets
• B64D 33/00 - Arrangement in aircraft of power plant parts or auxiliaries not otherwise provided for

Abstract

Control systems and methods to secure communications within the control system. The control system includes a control node operably coupled to a concentrator node via a first data link. The control node can communicate with the concentrator node over the first data link at a first communication frequency and first communication rate. The control node can also change the first communication frequency in response to an event, such as a cyber-security threat. The concentrator node can communicate with the control node at the changed first communication frequency in response to receiving a frequency change indication. In some examples, the control node is also operably coupled to the concentrator node via a second data link. The second data link may operate at a second communication rate that is different from the first communication rate. The control node may send redundant data on the first data link and the second data link.

IPC Classes  ?

• B64D 47/00 - Equipment not otherwise provided for
• H04B 10/278 - Bus-type networks
• H04L 12/22 - Arrangements for preventing the taking of data from a data transmission channel without authorisation
• H04L 12/40 - Bus networks

Abstract

Control systems and methods for securing software images to be executed by the control system. In some examples the control system includes a control node, a concentrator node, and a security module. The security module may include a secured memory area that can hold software images. The security module may load a first executable image from the secured memory area to the control node. The security module may also load a second executable image from the secured memory area to the concentrator node. In some examples, rather than having a security module load the software images, the control node and concentrator node each include a secured area of memory where their respective software images reside. Each of the control node and concentrator node may load the software images from their respective secured areas of memory.

IPC Classes  ?

• B64D 45/00 - Aircraft indicators or protectors not otherwise provided for
• G06F 21/57 - Certifying or maintaining trusted computer platforms, e.g. secure boots or power-downs, version controls, system software checks, secure updates or assessing vulnerabilities
• G06F 21/74 - Protecting specific internal or peripheral components, in which the protection of a component leads to protection of the entire computer to assure secure computing or processing of information operating in dual or compartmented mode, i.e. at least one secure mode

Abstract

Structural rod supports are provided in vanes in a gas turbine assembly in order to provide support to the vanes and an annular seal. Structural rods couple to the turbine case at one end and the annular seal at an opposite end.

IPC Classes  ?

• F01D 9/02 - NozzlesNozzle boxesStator bladesGuide conduits
• F01D 9/04 - NozzlesNozzle boxesStator bladesGuide conduits forming ring or sector
• F01D 11/08 - Preventing or minimising internal leakage of working fluid, e.g. between stages for sealing space between rotor blade tips and stator
• F01D 25/24 - CasingsCasing parts, e.g. diaphragms, casing fastenings
• F01D 25/28 - Supporting or mounting arrangements, e.g. for turbine casing
• F02C 7/28 - Arrangement of seals

Abstract

An apparatus and a method of cooling a heat shield are provided. The apparatus comprises a heat shield of a combustor, the heat shield comprising a first surface and a second surface, wherein the first surface is configured to face a combustion chamber and the second surface is opposite the first surface; a plurality of channels located on the second surface of the heat shield; and a turbulator included in a channel, the channel being included in the plurality of channels. The heat shield may be cooled by directing airflow over the heat shield through channels towards an opening of the heat shield and past turbulators located in the plurality of channels.

IPC Classes  ?

• F02C 7/22 - Fuel supply systems
• F02C 7/24 - Heat or noise insulation
• F23R 3/00 - Continuous combustion chambers using liquid or gaseous fuel

Abstract

In some examples, a method including applying a wet bond coat slurry to a damaged area of a coating system on a metal substrate, wherein the bond coat slurry comprises a liquid binder, at least one of glass particles or glass-ceramic particles, and ceramic oxide particles; depositing a plurality of fibers onto the wet bond coat slurry at least one of during or after the wet bond coat slurry is applied to the damaged area, wherein the plurality of fibers includes at least one of metallic fibers or ceramic fibers; applying a ceramic composite slurry on the bond coat to form a ceramic composite layer, wherein, during the application of the ceramic composite slurry on the bond coat, the bond coat is wet or at least partially dried, wherein the wet or at least partially dried bond coat includes a plurality of partially exposed fibers, wherein, following the application of the ceramic composite slurry, a first portion of individual fibers of the plurality of fibers are embedded in the wet or at least partially dried bond coat and a second portion of the individual fibers of the plurality of fibers extend into the layer of the ceramic composite slurry; and heating the wet or at least partially dried bond coat and the ceramic composite layer to form a repaired portion of the coating system on the metal substrate, wherein heating the bond coat melts at least a portion of the at least one of the glass particles or the glass-ceramic particles to form a fully amorphous glass phase or a mixture of amorphous and crystalline glass phases which bond with the metal substrate.

IPC Classes  ?

• B05D 3/00 - Pretreatment of surfaces to which liquids or other fluent materials are to be appliedAfter-treatment of applied coatings, e.g. intermediate treating of an applied coating preparatory to subsequent applications of liquids or other fluent materials
• B05D 7/14 - Processes, other than flocking, specially adapted for applying liquids or other fluent materials to particular surfaces or for applying particular liquids or other fluent materials to metal, e.g. car bodies

Abstract

A thermal management system for regulating dissipation of multiple thermal loads during operation of an apparatus includes a two-phase pump loop (TPPL), a vapor cycle system (VCS), and a liquid thermal energy storage (TES) system integrated together to maintain the apparatus at a constant temperature. The TPPL is configured to remove heat from the apparatus; the TES system is configured to provide thermal energy storage and temperature regulation; and the VCS is configured to transfer heat to the environment. The multiple thermal loads include a primary thermal load in the form of heat from the apparatus and a secondary thermal load in the form of at least one of a housekeeping thermal load or a power electronics thermal load. The primary and secondary loads are at different temperatures with each being independently selected to be transient or steady state.

IPC Classes  ?

• F01P 3/22 - Liquid cooling characterised by evaporation and condensation of coolant in closed cyclesLiquid cooling characterised by the coolant reaching higher temperatures than normal atmospheric boiling-point
• F25B 7/00 - Compression machines, plants or systems, with cascade operation, i.e. with two or more circuits, the heat from the condenser of one circuit being absorbed by the evaporator of the next circuit
• F28D 15/02 - Heat-exchange apparatus with the intermediate heat-transfer medium in closed tubes passing into or through the conduit walls in which the medium condenses and evaporates, e.g. heat-pipes
• F28D 21/00 - Heat-exchange apparatus not covered by any of the groups

Abstract

A thermal system may comprise a reservoir, a first fluid flowpath, and a second fluid flowpath. The first fluid flowpath may start at the reservoir and return to the reservoir. The first fluid flowpath may comprise, in a direction of the fluid flow, a first side of a sub-cooler, a liquid pump, a first side of a pre-heater, and a first side of an evaporator. The second fluid flowpath may start at the reservoir and return to the reservoir. The second fluid flowpath may comprise, in a direction of a fluid flow, a pressure regulator, a vapor compressor, a first side of a condenser, and an expansion value.

IPC Classes  ?

• F01P 3/22 - Liquid cooling characterised by evaporation and condensation of coolant in closed cyclesLiquid cooling characterised by the coolant reaching higher temperatures than normal atmospheric boiling-point
• F25B 7/00 - Compression machines, plants or systems, with cascade operation, i.e. with two or more circuits, the heat from the condenser of one circuit being absorbed by the evaporator of the next circuit
• F28D 15/02 - Heat-exchange apparatus with the intermediate heat-transfer medium in closed tubes passing into or through the conduit walls in which the medium condenses and evaporates, e.g. heat-pipes
• F28D 21/00 - Heat-exchange apparatus not covered by any of the groups

Abstract

The disclosure is directed to delivering power to and communication with optical devices, such as sensors and effectors using only optical fibers. The device may receive optical energy from a fiber optic cable simultaneously with receiving communication in the form of inverse signaling. Inverse signaling means the light is on for longer than the light is off which may allow the device may receive more optical energy than when using normal signaling. Normal signaling means the light is off for longer than the light is on. The device may perform sensing or other functions using the received optical energy. The device may send communications through at least one optical fiber that may be separate from the one or more optical fibers from which the device receives communication and optical energy. The device may send communication using normal signaling, which uses less energy than inverse signaling.

IPC Classes  ?

• H02J 50/30 - Circuit arrangements or systems for wireless supply or distribution of electric power using light, e.g. lasers
• H04B 10/80 - Optical aspects relating to the use of optical transmission for specific applications, not provided for in groups , e.g. optical power feeding or optical transmission through water
• H04J 14/00 - Optical multiplex systems

Abstract

A method may include introducing a suspension including a coating material and a carrier into a heated plume of a thermal spray device. The coating material may include silicon or a silicon alloy. The method may further include directing the coating material toward a substrate using the heated plume, in which the substrate includes a ceramic or a ceramic matrix composite. The method may include depositing the coating material in a bond coat directly on the substrate, where the bond coat has a porosity of less than about 3 volume percent.

IPC Classes  ?

• C04B 41/85 - Coating or impregnating with inorganic materials
• C23C 4/12 - Coating by spraying the coating material in the molten state, e.g. by flame, plasma or electric discharge characterised by the method of spraying

Abstract

A distributed propulsion system is described that includes at least one turbine engine including an engine shaft and at least one mechanically driven propulsor, wherein a propulsor shaft of the at least one mechanically driven propulsor is not co-axial with the engine shaft of the at least one turbine engine and is driven by the engine shaft of the at least one turbine engine. The distributed propulsion system further includes at least one generator driven by rotation of at least one of the engine shaft of the at least one turbine engine or the propulsor shaft of the at least one mechanically driven propulsor. The distributed propulsion system also includes at least one electrically driven propulsor, wherein a propulsor motor of the at least one electrically driven propulsor drives a propulsor fan of the at least one electrically driven propulsor based on electricity produced by the at least one generator.

IPC Classes  ?

• B60K 6/20 - Arrangement or mounting of plural diverse prime-movers for mutual or common propulsion, e.g. hybrid propulsion systems comprising electric motors and internal combustion engines the prime-movers consisting of electric motors and internal combustion engines, e.g. HEVs
• B64D 27/00 - Arrangement or mounting of power plants in aircraftAircraft characterised by the type or position of power plants
• B64D 35/00 - Transmitting power from power plants to propellers or rotorsArrangements of transmissions

Abstract

A micro grid power control system may control a plurality of different sources of electrical energy, such as generators, renewable energy sources, and stored energy sources. The micro grid power control system may include hierarchical levels of control. At a system level, the micro grid power control system may include a system controller configured to selectively allocate the sources and centrally control electrical distribution of electric power within the micro grid based on system conditions to optimize system operation. Optimization of system operation may be dynamically varied by the system controller based on priorities and modeling of system operation. At a source level, each of the sources may include a source controller configured to optimize generation of electrical energy of the respective source. Optimization of a source with a respective source controller may be based on a source objective independently associated with each of the sources and source modeling.

IPC Classes  ?

• G05B 17/02 - Systems involving the use of models or simulators of said systems electric
• H02J 4/00 - Circuit arrangements for mains or distribution networks not specified as ac or dc
• H02J 13/00 - Circuit arrangements for providing remote indication of network conditions, e.g. an instantaneous record of the open or closed condition of each circuitbreaker in the networkCircuit arrangements for providing remote control of switching means in a power distribution network, e.g. switching in and out of current consumers by using a pulse code signal carried by the network

Abstract

A propulsion system that includes a plurality of power units, a plurality of propulsors, where respective power units of the plurality of power units are controllably coupled to the plurality of propulsors, and a controller configured to receive a desired throttle value corresponding to a desired propulsive force, determine a number of power units of the plurality of power units to be coupled to the plurality of propulsors to achieve the desired propulsive force based on a respective power value associated with each respective power unit of the plurality of power units, and cause the number of power units of the plurality of power units to be coupled to the plurality of propulsors.

IPC Classes  ?

• B60W 20/10 - Controlling the power contribution of each of the prime movers to meet required power demand
• B63H 21/17 - Use of propulsion power plant or units on vessels the vessels being motor-driven by electric motor
• B63H 21/21 - Control means for engine or transmission, specially adapted for use on marine vessels
• B63H 23/00 - Transmitting power from propulsion power plant to propulsive elements
• B64D 31/12 - Initiating means actuated automatically for equalising or synchronising power plants
• B64D 35/00 - Transmitting power from power plants to propellers or rotorsArrangements of transmissions

Abstract

A ceramic brush seal for a gas turbine engine, and a process for manufacturing the seal are provided. In one example, the process includes deinfiltrating an edge of a plurality of plies having a preimpregnated configuration. The edge is defined by a plurality of ceramic fibers extending away from a portion edge of a matrix infiltrated portion of each of the plies. In another example, the process includes masking an edge of a plurality of plies, the edge being defined by a plurality of ceramic fibers extending away from a portion edge of a body portion of each of the plies, and infiltrating the body portion of the plurality of plies with a ceramic matrix slurry. The plies are stacked, formed into a green body and then fired to form the component. The plies may include oxide/oxide woven ceramic fiber plies.

IPC Classes  ?

• C04B 35/80 - Fibres, filaments, whiskers, platelets, or the like
• C09K 3/10 - Materials not provided for elsewhere for sealing or packing joints or covers

Abstract

Systems and methods thermal management of a directed energy weapon are provided. The system may include a controller module executable by a processor to determine a planned energy emission from a light-emitting diode (LED) of the directed energy weapon. The controller module may generate a cooling instruction to influence a temperature of the LED with a cooling fluid in response to the planned energy emission. The controller module may cause the cooling fluid to be applied to the LED in accordance with the cooling instruction prior to a start of the planned energy emission of the LED.

IPC Classes  ?

• F41H 13/00 - Means of attack or defence not otherwise provided for
• H01S 5/024 - Arrangements for thermal management

Abstract

A propulsion system includes a gas turbine engine, an inlet particle separator, an infrared suppression system, and an engine controller. The engine controller may be configured to determine an activation state of the inlet particle separator, adjust one or more engine operating parameters based on the activation state, and control the gas turbine engine based on the adjusted engine operating parameters. The engine operating parameters may be adjusted based on inlet flow, which is determined based on the activation state. The engine controller may be further configured to determine an activation state of the infrared suppression system, adjust one or more engine operating parameters based on the activation state, and control the gas turbine engine based on the adjusted engine operating parameters. The engine operating parameters may be adjusted based on backpressure, which is determined based on the activation state.

IPC Classes  ?

• F02C 7/05 - Air intakes for gas-turbine plants or jet-propulsion plants having provisions for obviating the penetration of damaging objects or particles
• F02C 7/052 - Air intakes for gas-turbine plants or jet-propulsion plants having provisions for obviating the penetration of damaging objects or particles with dust-separation devices
• F02C 9/00 - Controlling gas-turbine plantsControlling fuel supply in air-breathing jet-propulsion plants
• F02C 9/16 - Control of working fluid flow

Abstract

A propulsion system is described that includes an AC generator configured to produce AC current, and a plurality of propulsors configured to receive the AC current from the AC generator and provide thrust based on the AC current from the AC generator. The propulsion system further includes an AC distribution system configured to deliver a first portion of the AC current to a first group of propulsors from the plurality of propulsors, and a second subsystem configured to deliver a second portion of the AC current to a second group of propulsors from the plurality of propulsors.

IPC Classes  ?

• B64C 15/02 - Attitude, flight direction or altitude control by jet reaction the jets being propulsion jets
• B64D 27/30 - Aircraft characterised by electric power plants
• B64D 27/35 - Arrangements for on-board electric energy production, distribution, recovery or storage
• H02P 5/74 - Arrangements specially adapted for regulating or controlling the speed or torque of two or more electric motors controlling two or more AC dynamo-electric motors
• H02P 9/00 - Arrangements for controlling electric generators for the purpose of obtaining a desired output

Abstract

A turbine engine is described that includes a drive shaft and an electric generator comprising a first rotating element comprising a magnet array, wherein the first rotating element is configured to rotate in a first direction based on a rotation of the drive shaft. The turbine engine further includes a second rotating element comprising a coil array, wherein the second rotating element is configured to rotate in a second direction based on the rotation of the drive shaft, wherein the second direction is opposite to the first direction.

IPC Classes  ?

• B64D 35/00 - Transmitting power from power plants to propellers or rotorsArrangements of transmissions
• F01D 15/10 - Adaptations for driving, or combinations with, electric generators
• F02C 7/32 - Arrangement, mounting, or driving, of auxiliaries
• F02C 7/36 - Power transmission between the different shafts of the gas-turbine plant, or between the gas-turbine plant and the power user
• H02K 7/18 - Structural association of electric generators with mechanical driving motors, e.g.with turbines
• H02K 21/02 - Synchronous motors having permanent magnetsSynchronous generators having permanent magnets Details

Abstract

A turbine engine is described that includes a drive shaft and an electric generator, wherein the electric generator includes a first rotating element comprising a first magnet array and mechanically coupled to the drive shaft. The electric generator further includes a second rotating element comprising a second magnet array and mechanically coupled to the drive shaft and an armature comprising a first coil array and a second coil array, wherein the first rotating element is configured to rotate at a particular velocity relative to the first coil array, and the second rotating element is configured to rotate at the particular velocity relative to the second coil array.

IPC Classes  ?

• B64D 35/00 - Transmitting power from power plants to propellers or rotorsArrangements of transmissions
• F01D 15/10 - Adaptations for driving, or combinations with, electric generators
• F02C 7/32 - Arrangement, mounting, or driving, of auxiliaries
• F02C 7/36 - Power transmission between the different shafts of the gas-turbine plant, or between the gas-turbine plant and the power user
• H02K 7/18 - Structural association of electric generators with mechanical driving motors, e.g.with turbines
• H02K 16/00 - Machines with more than one rotor or stator
• H02K 21/24 - Synchronous motors having permanent magnetsSynchronous generators having permanent magnets with stationary armatures and rotating magnets with magnets axially facing the armatures, e.g. hub-type cycle dynamos

Abstract

A gas turbine engine includes devices, systems, and methods for providing bleed air from the compressor impeller to the turbine for cooling and/or other use. The bleed air may include compressor cooling air that is routed through the diffuser and external to an outer bypass duct and/or internally to a forward wheel cavity of the turbine.

IPC Classes  ?

• F02C 3/13 - Gas-turbine plants characterised by the use of combustion products as the working fluid having a turbine driving a compressor having variable working fluid interconnections between turbines or compressors or stages of different rotors
• F02C 9/18 - Control of working fluid flow by bleeding, by-passing or acting on variable working fluid interconnections between turbines or compressors or their stages

Abstract

A turbine engine is described that includes an intake, an inlet duct configured to receive fluid from the intake, and an outer bypass duct configured to receive fluid from the intake. The turbine engine further includes a drive shaft, a tower shaft mechanically coupled to the drive shaft, and an electric generator mechanically coupled to the tower shaft. The electric generator is located between the inlet duct and the outer bypass duct.

IPC Classes  ?

• B64D 33/00 - Arrangement in aircraft of power plant parts or auxiliaries not otherwise provided for
• B64D 35/00 - Transmitting power from power plants to propellers or rotorsArrangements of transmissions
• F02C 7/32 - Arrangement, mounting, or driving, of auxiliaries
• F02C 7/36 - Power transmission between the different shafts of the gas-turbine plant, or between the gas-turbine plant and the power user
• H02K 1/06 - Details of the magnetic circuit characterised by the shape, form or construction

Abstract

A system platform includes a gas turbine engine coupled to a generator. The generator, driven by the gas turbine engine, supplies power to subsystems of the platform.

IPC Classes  ?

• B64D 35/00 - Transmitting power from power plants to propellers or rotorsArrangements of transmissions
• B64D 41/00 - Power installations for auxiliary purposes
• F02C 7/268 - Starting drives for the rotor
• F02C 7/32 - Arrangement, mounting, or driving, of auxiliaries
• F02C 7/36 - Power transmission between the different shafts of the gas-turbine plant, or between the gas-turbine plant and the power user

Abstract

Methods and systems are provided to damp oscillations in a synchronous alternating current (AC) grid. Current may be received from the synchronous AC grid through a phase of an n-phase supply line. The current received from the synchronous AC grid is supplied to a phase of the synchronous motor. A sub-harmonic oscillation may be detected in the current received from the synchronous AC grid. The sub- harmonic oscillation may be damped by: shunting a portion of the current away from the phase of the synchronous motor during a first time period in an upper-half of the sub-harmonic oscillation, and/or supplying compensation current from a partial power converter to the phase of the synchronous motor during a second time period in a lower-half of the sub-harmonic oscillation.

IPC Classes  ?

• H02J 3/34 - Arrangements for transfer of electric power between networks of substantially different frequency
• H02P 21/00 - Arrangements or methods for the control of electric machines by vector control, e.g. by control of field orientation
• H02P 25/022 - Synchronous motors

Abstract

Methods and systems for load alignment assistance are provided. An alignment current may be provided with a partial power converter through an n-phase supply line to a synchronous alternating current (AC) motor during a startup of a synchronous AC grid. The synchronous AC motor may receive polyphase AC power through the n-phase supply line from the synchronous AC grid during the startup. The partial power converter may be powered by a power source isolated from the synchronous AC grid. The alignment current may be controlled such that the alignment current causes a rotor of the synchronous AC motor to align with a rotor of a generator that powers the synchronous AC grid.

IPC Classes  ?

• H02P 1/46 - Arrangements for starting electric motors or dynamo-electric converters for starting dynamo-electric motors or dynamo-electric converters for starting an individual synchronous motor
• H02P 21/00 - Arrangements or methods for the control of electric machines by vector control, e.g. by control of field orientation
• H02P 25/026 - Synchronous motors controlled by supply frequency thereby detecting the rotor position

Abstract

Systems and methods for pre-aligning rotors of synchronous motors on a synchronous AC grid prior to startup of the motors are provided. A partial power converter may provide an alignment current through an n-phase supply line to a synchronous AC motor. The synchronous AC motor may be configured to receive polyphase AC power through the n-phase supply line from the synchronous AC grid, whereas the partial power converter is powered by a power source isolated from the synchronous AC grid. The alignment current may cause a rotor of the synchronous AC motor to move to and stop at a target angular position.

IPC Classes  ?

• H02P 1/46 - Arrangements for starting electric motors or dynamo-electric converters for starting dynamo-electric motors or dynamo-electric converters for starting an individual synchronous motor
• H02P 21/00 - Arrangements or methods for the control of electric machines by vector control, e.g. by control of field orientation
• H02P 25/026 - Synchronous motors controlled by supply frequency thereby detecting the rotor position

Abstract

Systems and methods for controlling stators of a compressor of a gas turbine engine are provided. The stators and rotatable blades may be included in a stage of the compressor. The rotatable blades may be configured to rotate about an axial axis of the compressor, and each of the stators is rotatable about a corresponding vane axis that extends radially outward from the axial axis of the compressor. Electric motors may be coupled to the stators, where each of the electric motors is configured to individually rotate a corresponding one of the stators in the compressor. A motor controller may be configured to cause the electric motors to rotate the stators in unison or individually.

IPC Classes  ?

• F01D 9/02 - NozzlesNozzle boxesStator bladesGuide conduits
• F01D 17/16 - Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits by means of nozzle vanes
• F04D 29/56 - Fluid-guiding means, e.g. diffusers adjustable

Abstract

A system and method of non-intrusive thrust measurement of a gas turbine engine. The system comprises a transmitter disposed at a boundary of fluid flow and at least one receiver adapted to receive transmissions from the transmitter. A processor is coupled to the receivers to determine a parameter from a characteristic of the transmission at the receiver suite and adapted to determine a thrust parameter from the parameter. A method for non-intrusively measuring engine thrust includes transmitting a wave across the exhaust plume, receiving the transmitted wave and determining a measurement parameter of the exhaust plume based on a characteristic of the received wave, and comparing the measurement parameter to a reference parameter and determining the thrust based on the comparison.

IPC Classes  ?

• B64F 5/60 - Testing or inspecting aircraft components or systems
• G01L 5/12 - Apparatus for, or methods of, measuring force, work, mechanical power, or torque, specially adapted for specific purposes for measuring axial thrust in a rotary shaft, e.g. of propulsion plants
• G01P 5/24 - Measuring speed of fluids, e.g. of air streamMeasuring speed of bodies relative to fluids, e.g. of ship, of aircraft by measuring the direct influence of the streaming fluid on the properties of a detecting acoustical wave

Abstract

A gas turbine engine and methods of operation include a low pressure electric motor-generator having an electrical assembly for electrical connection.

IPC Classes  ?

• B64D 33/00 - Arrangement in aircraft of power plant parts or auxiliaries not otherwise provided for
• F01D 15/10 - Adaptations for driving, or combinations with, electric generators
• F02C 7/32 - Arrangement, mounting, or driving, of auxiliaries
• H02K 7/18 - Structural association of electric generators with mechanical driving motors, e.g.with turbines

Abstract

A gas turbine engine and methods of operation include a low pressure electric motor-generator arranged for selective operation in a generator mode to generate electrical power or a drive mode to assist rotation of a low pressure drive shaft of the engine.

IPC Classes  ?

• F01D 15/10 - Adaptations for driving, or combinations with, electric generators
• F02C 7/32 - Arrangement, mounting, or driving, of auxiliaries
• F02C 7/36 - Power transmission between the different shafts of the gas-turbine plant, or between the gas-turbine plant and the power user
• H02K 7/18 - Structural association of electric generators with mechanical driving motors, e.g.with turbines

Abstract

A turbofan gas turbine engine includes low pressure (LP) motor-generator operable in either a generation mode or a drive mode, an high pressure (HP) motor-generator operable in a either a generation mode or a drive mode, and a power control module for selectively operating the LP and HP motor-generators according to operational conditions of the engine.

IPC Classes  ?

• F01D 15/10 - Adaptations for driving, or combinations with, electric generators
• F02C 7/32 - Arrangement, mounting, or driving, of auxiliaries
• F02C 9/00 - Controlling gas-turbine plantsControlling fuel supply in air-breathing jet-propulsion plants
• H02K 7/18 - Structural association of electric generators with mechanical driving motors, e.g.with turbines

Abstract

A gas turbine engine and methods of operation are disclosed including a low pressure motor-generator and flutter control system.

IPC Classes  ?

• F01D 15/10 - Adaptations for driving, or combinations with, electric generators
• F01D 25/04 - Antivibration arrangements
• F02C 7/32 - Arrangement, mounting, or driving, of auxiliaries
• F02C 9/00 - Controlling gas-turbine plantsControlling fuel supply in air-breathing jet-propulsion plants
• H02K 7/18 - Structural association of electric generators with mechanical driving motors, e.g.with turbines

Abstract

The disclosure is directed to an "optionally hybrid power system" that may operate either as a traditional power system, deriving power from a single power source, or as a hybrid power system, deriving power from multiple types of power sources. An example optionally hybrid power system may include a gas turbine engine and one or more electric motors. When configured as a traditional power system the optionally hybrid power system may derive all power from the gas turbine engine. However, when configured as a hybrid power system, the one or more motors may be coupled to the optionally hybrid power system to supplement the power produced by the gas turbine engine. Additionally, an operator interface that may control the optionally hybrid power system may select from a plurality of operating modes that depend on the configuration of the optionally hybrid power system.

IPC Classes  ?

• B60W 20/40 - Controlling the engagement or disengagement of prime movers, e.g. for transition between prime movers
• B64D 27/10 - Aircraft characterised by the type or position of power plants of gas-turbine type

Abstract

A lubricant scavenging system for a turbine engine having a pair of concentric, counter-rotating shafts. The system comprises a lubricant sump housing having a radially inner surface, a pair of pedestal mounts each adapted to receive a bearing assembly from a respective shaft, a lubricant collection point axially disposed between the pedestal mounts, and a pair of axial channels adapted to guide lubricant toward the lubricant collection point.

IPC Classes  ?

• F01D 25/18 - Lubricating arrangements
• F01D 25/32 - Collecting of condensation waterDrainage
• F02C 7/06 - Arrangement of bearingsLubricating

Abstract

A propulsion system is described that includes an electrical bus, a generator configured to provide electrical power to the electrical bus, a propulsor configured to provide thrust by simultaneously being driven by the electrical power at the electrical bus, and a controller. The controller is configured to synchronize a rotational speed of an individual propulsor from the plurality of propulsors with a rotational speed of the generator after the propulsor has become unsynchronized with the rotational speed of the generator by controlling at least one of the rotational speed of the generator, nozzle area of the individual propulsor, or a pitch angle of the individual propulsor. The controller is also configured to disengage the propulsor from the electrical bus prior to controlling the rotational speed of the generator, the nozzle area of the propulsor, or the pitch angle of the propulsor.

IPC Classes  ?

• B63H 3/10 - Propeller-blade pitch changing characterised by having pitch control conjoint with propulsion-plant control
• B63H 21/17 - Use of propulsion power plant or units on vessels the vessels being motor-driven by electric motor
• B64C 11/30 - Blade pitch-changing mechanisms
• B64D 35/00 - Transmitting power from power plants to propellers or rotorsArrangements of transmissions
• H02P 25/024 - Synchronous motors controlled by supply frequency

Abstract

An airfoil may include a spar comprising a passageway inside of the spar for a cooling fluid, a pedestal on an outer surface of the spar, and an inlet configured to direct the cooling fluid from the passageway to the outer surface of the spar. The airfoil may further include a coversheet, wherein an inner surface of the coversheet is positioned on the pedestal of the spar and an edge of the coversheet is positioned along an end of the spar. The inner surface of the coversheet, the pedestal, and the outer surface of the spar may define a cooling path from the inlet to an outlet at the edge of the coversheet. The outlet at the edge of the coversheet may be configured to direct cooling fluid onto the end of the spar, onto a footing, and/or onto a fillet positioned along an intersection of the footing and the spar.

IPC Classes  ?

• F01D 5/14 - Form or construction
• F01D 5/18 - Hollow bladesHeating, heat-insulating, or cooling means on blades
• F01D 9/02 - NozzlesNozzle boxesStator bladesGuide conduits
• F01D 25/12 - Cooling

Abstract

A power system includes a bus, a first controller and one or more second controllers. The first controller is configured to excite a first generator to generate electric power on the bus in response to initiation of rotation of the first generator. The one or more second controllers are configured to excite one or more respective second generators with a constant excitation in response to initiation of rotation of the first generator. The second generator(s) are electrically coupled with the bus and configured to operate as a motor to commence synchronous rotation with the first generator in response to electric power being present on the bus. The second controller(s) are further configured to initiate dynamic adjustment of the excitation of the second generator(s) to generate electric power on the bus with the second generator(s) in response to the first generator and the second generator(s) synchronously reaching a predetermined rotational speed.

IPC Classes  ?

• H02J 3/40 - Synchronising a generator for connection to a network or to another generator
• H02K 19/38 - Structural association of synchronous generators with exciting machines
• H02P 1/46 - Arrangements for starting electric motors or dynamo-electric converters for starting dynamo-electric motors or dynamo-electric converters for starting an individual synchronous motor
• H02P 9/10 - Control effected upon generator excitation circuit to reduce harmful effects of overloads or transients, e.g. sudden application of load, sudden removal of load, sudden change of load
• H02P 25/022 - Synchronous motors

Abstract

A system includes an exciter configured to operate with a synchronous generator. The exciter may be mechanically coupled and rotatable with the synchronous generator, or the exciter may be independently rotatable. The exciter is configured to output a field current for exciting the synchronous generator to produce a voltage and a current at an output of the synchronous generator. The synchronous generator may be synchronized with loads during a time when the synchronous generator is at substantially zero speed and the loads, such as motors, are at zero speed. A controller included in the system is configured to control output of the field current by the exciter with an exciter voltage. The controller may control the exciter voltage to selective include an AC component and DC component in accordance with a rotational speed of the exciter.

IPC Classes  ?

• H02K 19/38 - Structural association of synchronous generators with exciting machines
• H02P 25/022 - Synchronous motors

Abstract

A shaft balancing assembly comprising a nose cone and a plurality of balance weights. The nose cone is mounted to a rotatable shaft of a turbine machine via a plurality of elongated fasteners such that a central axis of the nose cone is alighted with the rotatable shaft. The nose cone comprises a flange extending axially from a leading tip to a trailing edge and a plurality of apertures each adapted to receive a balancing weight and an elongated fastener. The nose cone flange is formed from a filament wound composite material and has a uniform thickness.

IPC Classes  ?

• B64C 11/14 - Spinners
• F01D 5/10 - Antivibration means
• F16F 15/28 - CounterweightsAttaching or mounting same

Abstract

A magnetic squeeze film damper system comprises a bearing assembly having an outer race with a first outer surface and a first inner surface and a bearing located along the first inner surface. The system further comprises a squeeze film damper housing having a second outer surface and a second inner surface that is contiguous with the first outer surface. A channel having a forward end and an aft end is defined within the housing along the second inner surface, the channel bordered by the first outer surface. The system further includes a first seal gland located along the forward end of the channel and a second seal gland located along the aft end of the channel. Both seal glands comprise a reservoir for holding a magneto- rheological fluid, the reservoir encased in an elastomer. At least one electromagnet is arranged in close proximity to each of the seal glands.

IPC Classes  ?

• F01D 25/16 - Arrangement of bearingsSupporting or mounting bearings in casings
• F01D 25/18 - Lubricating arrangements
• F02C 7/06 - Arrangement of bearingsLubricating

Abstract

A gas turbine engine exhaust component is disclosed herein. The gas turbine engine exhaust component includes an annular mixer that extends around a central axis and is formed to include inner lobes that define radially- outwardly opening channels and outer lobes that define radially-inwardly opening channels. A constraint band is added to connect the outer lobes and reduce vibration, deflections, and stresses.

IPC Classes  ?

• F01D 9/02 - NozzlesNozzle boxesStator bladesGuide conduits
• F02K 1/28 - Plants characterised by the form or arrangement of the jet pipe or nozzleJet pipes or nozzles peculiar thereto using fluid jets to influence the jet flow
• F02K 1/46 - Nozzles having means for adding air to the jet or for augmenting the mixing region between the jet and the ambient air, e.g. for silencing

Abstract

A propulsion system including a gas turbine engine is disclosed herein. The propulsion system further includes a heat exchanger arranged outside the gas turbine engine and adapted to cool fluid from the gas turbine engine.

IPC Classes  ?

• B64D 29/00 - Power-plant nacelles, fairings or cowlings
• B64D 33/08 - Arrangement in aircraft of power plant parts or auxiliaries not otherwise provided for of power plant cooling systems
• B64D 33/10 - Radiator arrangement
• F02C 7/12 - Cooling of plants

Abstract

A method for use in a turbine control system includes controlling fuel supply to a gas turbine engine at least in part using a fuel supply limit determined as a first function of a rotational speed of a shaft of the gas turbine engine. The method also includes obtaining a first value representative of a rotational speed of the shaft, and differentiating the first value within a processing unit. The processing unit determines an adjusted fuel supply limit as an adjusted function of the first value. The adjusted function is based on the first function and the differentiated first value. The method further includes controlling the fuel supply to the gas turbine engine at least in part using the adjusted fuel supply limit.

IPC Classes  ?

• F01D 21/02 - Shutting-down responsive to overspeed
• F01D 21/14 - Shutting-down of machines or engines, e.g. in emergencyRegulating, controlling, or safety means not otherwise provided for responsive to other specific conditions
• F02C 9/28 - Regulating systems responsive to plant or ambient parameters, e.g. temperature, pressure, rotor speed

Abstract

An expendable bearing and a method for making the same including an inner race defining an inner bearing diameter, an outer race defining an outer bearing diameter, a seal attached to the outer race and positioned adjacent and in contact with the inner race, where the inner race, the outer race, and the seal define a bearing cavity, a plurality of rolling elements positioned adjacent to the inner and outer races in the bearing cavity, a dry film lubricant on a surface of at least one of the inner race, the outer race, or the plurality of rolling elements, and a powder lubricant comprising carbon nanotubes disposed in the bearing cavity.

IPC Classes  ?

• F16C 19/00 - Bearings with rolling contact, for exclusively rotary movement
• F16C 33/66 - Special parts or details in view of lubrication

Abstract

ABSTRACTIn general, techniques and circuits relate to an example AC-type TeDP system that enables an aircraft to operate propulsor motors, and propulsor fans, at different speeds without requiring DC distribution. An alternating current type electric propulsion system is described that includes an AC generator and a plurality of propulsors electrically coupled to the AC generator. A first propulsor from the plurality of propulsors includes a first motor that drives a first fan of the first propulsor at a first speed and has a first quantity of motor pole pairs. A second propulsor from the plurality of propulsors comprises a second motor that drives a second fan of the second propulsor at a second speed that is different than the first speed and has a second quantity of motor pole pairs that is different than the first quantity of motor pole pairs.Date Recue/Date Received 2023-01-18

IPC Classes  ?

• B60L 50/10 - Electric propulsion with power supplied within the vehicle using propulsion power supplied by engine-driven generators, e.g. generators driven by combustion engines
• B64C 11/00 - Propellers, e.g. of ducted typeFeatures common to propellers and rotors for rotorcraft
• B64D 27/34 - All-electric aircraft
• B64D 31/16 - Power plant control systemsArrangement of power plant control systems in aircraft for electric power plants

Abstract

An electric propulsion system is described that includes an AC drive circuit, a synchronization circuit, and a control unit. The AC drive circuit includes a plurality of propulsor motors, an AC power bus, and an AC generator that delivers AC electrical power to the AC power bus for simultaneously driving the plurality of propulsor motors. The synchronization circuit is configured to synchronize, with the AC generator, single propulsor motor from the plurality of propulsor motors, at a time. The control unit is configured to maintain synchronicity between the single propulsor motor and the AC generator by engaging the synchronization circuit with the single propulsor motor in response to determining that the single propulsor motor is not synchronized with the AC generator.

IPC Classes  ?

• B60L 15/32 - Control or regulation of multiple-unit electrically-propelled vehicles
• B60L 15/38 - Control or regulation of multiple-unit electrically-propelled vehicles with automatic control
• B60R 16/03 - Electric or fluid circuits specially adapted for vehicles and not otherwise provided forArrangement of elements of electric or fluid circuits specially adapted for vehicles and not otherwise provided for electric for supply of electrical power to vehicle subsystems
• B63H 21/17 - Use of propulsion power plant or units on vessels the vessels being motor-driven by electric motor
• B63H 21/21 - Control means for engine or transmission, specially adapted for use on marine vessels

Abstract

An electric propulsion system is described that includes at least one branch for distributing electrical power, provided by a power source, to one or more loads. The at least one branch is partitioned into one or more zones and comprises a plurality of branch isolation devices that are configured to isolate the at least one branch from the power source in response to a fault current at the at least one branch. In addition, the at least one branch comprises a respective pair of zone isolation devices for each respective zone from the one or more zones. The respective pair of zone isolation devices for each respective zone is configured to isolate the respective zone from the at least one branch, during a test of the at least one branch for identifying which of the one or more zones is a source of the fault current.

IPC Classes  ?

• B63H 21/17 - Use of propulsion power plant or units on vessels the vessels being motor-driven by electric motor
• B64D 45/00 - Aircraft indicators or protectors not otherwise provided for
• H02H 3/02 - Emergency protective circuit arrangements for automatic disconnection directly responsive to an undesired change from normal electric working condition, with or without subsequent reconnection Details
• H02H 7/26 - Sectionalised protection of cable or line systems, e.g. for disconnecting a section on which a short-circuit, earth fault, or arc discharge has occurred

Abstract

The present disclosure provides an apparatus with a prime mover coupled to a generator that is directly electrically coupled to an electric motor. A propeller or fan may be coupled to and driven by the electric motor. A bi-directional power converter may be coupled to the generator and further coupled to an energy storage device. The energy storage device may be selectively coupled to the electric motor. Methods of using the apparatus are also provided.

IPC Classes  ?

• B60L 50/15 - Electric propulsion with power supplied within the vehicle using propulsion power supplied by engine-driven generators, e.g. generators driven by combustion engines with additional electric power supply
• B64D 27/34 - All-electric aircraft
• H02J 15/00 - Systems for storing electric energy
• H02K 7/14 - Structural association with mechanical loads, e.g. with hand-held machine tools or fans
• H02K 7/18 - Structural association of electric generators with mechanical driving motors, e.g.with turbines
• H02K 19/02 - Synchronous motors
• H02K 19/16 - Synchronous generators
• H02K 21/00 - Synchronous motors having permanent magnetsSynchronous generators having permanent magnets
• H02M 7/66 - Conversion of AC power input into DC power outputConversion of DC power input into AC power output with possibility of reversal

Abstract

An air-inlet duct includes an outer wall, an inner wall, and a splitter. The splitter cooperates with the outer wall to establish a particle separator which separates particles entrained in an inlet flow moving through the air-inlet duct to provide a clean flow of air to a compressor section of a gas turbine engine.

IPC Classes  ?

• F02C 7/05 - Air intakes for gas-turbine plants or jet-propulsion plants having provisions for obviating the penetration of damaging objects or particles
• F02C 7/052 - Air intakes for gas-turbine plants or jet-propulsion plants having provisions for obviating the penetration of damaging objects or particles with dust-separation devices

Abstract

A control for a hybrid turbo electric aero-propulsion system prioritizes and optimizes the operating parameters, according to a desired optimization objective, for and across a number of different control optimization subsystems of the hybrid turbo electric aero-propulsion system. The control subsystems may include, for example, a propulsion control optimization subsystem and a power plant control optimization subsystem. The optimizations may be based on a system model, which is developed and updated during the operation of the hybrid turbo electric aero-propulsion system.

IPC Classes  ?

• B60K 6/20 - Arrangement or mounting of plural diverse prime-movers for mutual or common propulsion, e.g. hybrid propulsion systems comprising electric motors and internal combustion engines the prime-movers consisting of electric motors and internal combustion engines, e.g. HEVs
• B60W 20/10 - Controlling the power contribution of each of the prime movers to meet required power demand
• B64D 35/00 - Transmitting power from power plants to propellers or rotorsArrangements of transmissions
• F01D 7/02 - Rotors with blades adjustable in operationControl thereof having adjustment responsive to speed
• F01D 21/00 - Shutting-down of machines or engines, e.g. in emergencyRegulating, controlling, or safety means not otherwise provided for
• F02C 7/32 - Arrangement, mounting, or driving, of auxiliaries
• F02C 9/20 - Control of working fluid flow by throttlingControl of working fluid flow by adjusting vanes
• F02K 1/18 - Control or regulation automatic

Abstract

A gas turbine engine is disclosed which is capable of being reconfigured for one operating mode to another. A display is provided that permits a pilot or other operator to select between engine modes. One aspect is the ability to provide variable cooling that can be controlled by various devices. The variable cooling features can be used with devices such as cooled turbine components like vanes and/or blades. Devices can be used to reconfigure the performance and/or operability of a gas turbine engine.

IPC Classes  ?

• B64D 31/04 - Initiating means actuated personally
• F02K 1/17 - Control or regulation conjointly with another control with control of fuel supply

Abstract

A method of operating a gas turbine engine may include operating a starter motor to rotate a spool of the gas turbine engine; determining a torque of the starter motor during rotation of the spool; and controlling the rotation of the spool based on the torque.

IPC Classes  ?

• F01D 19/00 - Starting of machines or enginesRegulating, controlling, or safety means in connection therewith
• F01D 25/00 - Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
• F02C 3/30 - Adding water, steam or other fluids to the combustible ingredients or to the working fluid before discharge from the turbine

Abstract

An aircraft 1 is provided with a gas turbine engine 20 having a plurality of shafts. A first output shaft 32 provides power to an electrical machine 40 and a propeller 50, while a second output shaft 33 provides power to a refrigerant compressor 70. The refrigeration system may be integrated to the propeller, like a ducted fan, or on the outer skin of the aircraft.

IPC Classes  ?

• B64D 13/06 - Arrangements or adaptations of air-treatment apparatus for aircraft crew or passengers, or freight space the air being conditioned
• B64D 27/02 - Aircraft characterised by the type or position of power plants
• B64D 35/00 - Transmitting power from power plants to propellers or rotorsArrangements of transmissions
• B64D 41/00 - Power installations for auxiliary purposes

Abstract

A real-time engine management system having a controller system configured to control demand on a first component of an engine. The controller system is also configured to access a first set of prognostic data about the first component, where the first set of prognostic data includes a remaining lifespan approximation of the first component operating at a present operating condition. The controller system is also configured to identify a temporal length of an engine procedure operating at the present operating condition, alter a current limit constant associated with the first component to increase the remaining lifespan approximation of the first component beyond the temporal length, and implement the current limit constant associated with the first component so that the first component does not fault during the engine procedure.

IPC Classes  ?

• G05B 23/02 - Electric testing or monitoring

Abstract

An aircraft, comprising: a wing; a fuselage coupled to the wing; an engine (34) coupled to at least one of the fuselage and the wing; an electrical load (20) associated with the aircraft during flight operations; a generator (32) coupled to the engine and configured to generate electrical power for the electrical load; a conductor (38) electrically disposed between the electrical load and the generator; a conduit (46) configured to house the conductor; and a dielectric gas (44) disposed in the conduit; wherein the conduit (46) is configured to envelop the conductor (38) in the dielectric gas (44).

IPC Classes  ?

• B64D 41/00 - Power installations for auxiliary purposes
• H02J 4/00 - Circuit arrangements for mains or distribution networks not specified as ac or dc

Abstract

A turbomachinery component of a gas turbine engine is disclosed having a number of techniques of reducing the effects of a gap flow between an airfoil member of the gas turbine engine and a wall of the gas turbine engine. The airfoil member can be a variable and in one form is a variable turbine vane. In one embodiment a brush seal is included between the vane and the wall. In another form a wear surface is disposed between the vane and the wall. In yet another form a moveable member capable of being actuated to change position can be disposed between the vane and the wall to alter the size of a gap between the two.

IPC Classes  ?

• F01D 11/12 - Preventing or minimising internal leakage of working fluid, e.g. between stages for sealing space between rotor blade tips and stator using a rubstrip, e.g. erodible, deformable or resiliently biased part
• F01D 17/16 - Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits by means of nozzle vanes
• F04D 27/00 - Control, e.g. regulation, of pumps, pumping installations or pumping systems specially adapted for elastic fluids
• F04D 27/02 - Surge control
• F04D 29/56 - Fluid-guiding means, e.g. diffusers adjustable
• F16J 15/3288 - Filamentary structures, e.g. brush seals

Abstract

One embodiment of the present invention is a unique platform. Another embodiment is a unique engine system. Another embodiment is a unique wiring harness system. Other embodiments include apparatuses, systems, devices, hardware, methods, and combinations for one or more of various types of platforms, such as aircraft, ground vehicles, water-borne vessels and stationary platforms; engine systems; and wiring harness systems. Further embodiments, forms, features, aspects, benefits, and advantages of the present application will become apparent from the description and figures provided herewith.

IPC Classes  ?

• B64D 47/00 - Equipment not otherwise provided for
• H01B 7/00 - Insulated conductors or cables characterised by their form
• H01R 13/658 - High frequency shielding arrangements, e.g. against EMI [Electro-Magnetic Interference] or EMP [Electro-Magnetic Pulse]
• H02G 3/08 - Distribution boxesConnection or junction boxes
• H02G 13/00 - Installations of lightning conductorsFastening thereof to supporting structure
• H05K 9/00 - Screening of apparatus or components against electric or magnetic fields

Abstract

An electric machine is disclosed integrated to rotate with a shaft of a gas turbine engine. In one form the electric machine is integrated with a fan of the gas turbine engine. A rotor of the electric machine can be disposed at the end of the fan blades and the stator integrated into a flow path forming surface of the gas turbine engine. In one form the windings of the electric machine can change configuration permitting some windings to be placed in parallel with one or more other windings, and then connected together in series with remaining windings, if any. The voltage of the electric machine can change as a result of a change in configuration of the windings.

IPC Classes  ?

• F01D 15/10 - Adaptations for driving, or combinations with, electric generators
• F02C 6/00 - Plural gas-turbine plantsCombinations of gas-turbine plants with other apparatusAdaptations of gas-turbine plants for special use
• H02K 1/00 - Details of the magnetic circuit
• H02K 3/00 - Details of windings
• H02K 7/18 - Structural association of electric generators with mechanical driving motors, e.g.with turbines

Abstract

A unique variable camber vane system for a gas turbine engine is provided. The variable camber vane system allows for increasing the efficiency of as gas turbine engine in a simple and reliable manner. In particular, the seal strip can be manufactured relatively easily, and additional means for fastening the seal strip to the airfoil portion are not required due to the interference fit. Furthermore, the seal can be firmly pressed with its rubbing surface onto the crown, to reduce the risk of leakage through the gap between the two airfoil portions. Accordingly, a leakage flow from the pressure side of the airfoil to the suction side of the airfoil is reduced or even prevented, so that the flow through the vane system can be controlled more accurately.

IPC Classes  ?

• F01D 17/16 - Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits by means of nozzle vanes
• F02C 9/22 - Control of working fluid flow by throttlingControl of working fluid flow by adjusting vanes by adjusting turbine vanes

Abstract

Gas turbine engines with a secondary air flow circuit are disclosed. The secondary flow circuit is operative to deliver secondary air flow to the impeller for controlling a temperature of a portion of the impeller. The secondary air flow is delivered to the impeller from across a flowpath through a first opening; and one or more walls defining a cavity separate from the flowpath. The one or more walls further have an opening therein configured to supply a secondary air flow from the cavity to at least one diffuser vane, wherein the impeller includes a plurality of blades and a back face opposite the plurality of blades. A static structure is spaced apart from the back face and configured to direct the secondary air flow from a radially outer tip portion of the impeller radially inward along the back face of the impeller.

IPC Classes  ?

• F02C 3/04 - Gas-turbine plants characterised by the use of combustion products as the working fluid having a turbine driving a compressor
• F02C 7/18 - Cooling of plants characterised by cooling medium the medium being gaseous, e.g. air

Abstract

Turbine engine flowpath components of a unique gas turbine engine are described. Existing gas turbine engine systems have disadvantages relative to certain applications. The engine flowpath components of the present invention effectively use cooling fluids to cool gas turbine engines. The present invention describes apparatuses, systems, devices, hardware, methods, and combinations for gas turbines and cooled gas turbine engine flowpath components. One embodiment of a gas turbine engine comprises a unique cooled gas turbine engine flowpath component. The gas turbine engine flowpath component may comprise pedestals, cooling air passages, and/or hollow pins to transmit the cooling fluid

IPC Classes  ?

• F01D 5/18 - Hollow bladesHeating, heat-insulating, or cooling means on blades
• F01D 25/12 - Cooling

Abstract

Embodiments of the present invention includes an airfoil configured to mitigate and/or prevent the migration of cooling air due to centrifugal loading. Embodiments of the present invention include an airfoil for a turbine engine, comprising: an outer wall having a plurality cooling air exit openings; an inner wall having a plurality of cooling air inlet openings; a cooling air supply passage that is operative to supply cooling air to the cooling air inlet openings, and means for cooling the outer wall without allowing flow migration in a radially outward direction. One embodiment of the present invention is a unique airfoil for a turbomachine. Another embodiment is a unique gas turbine engine. Yet another embodiment is a method for manufacturing an airfoil for a turbomachine. Other embodiments include apparatuses, systems, devices, hardware, methods, and combinations for airfoils and turbomachinery.

IPC Classes  ?

• F01D 5/18 - Hollow bladesHeating, heat-insulating, or cooling means on blades
• F01D 9/02 - NozzlesNozzle boxesStator bladesGuide conduits
• F01D 25/12 - Cooling
• F02C 7/18 - Cooling of plants characterised by cooling medium the medium being gaseous, e.g. air

Abstract

A fluid cooled airfoil member is disclosed as disposed in a flow path and having a plurality of walls extending along a span of the member and enclosing an open interior, the walls forming a cooling passage therebetween, an inner wall of the plurality of walls extending into the flow path beyond a portion of an outer wall of the plurality of walls; a plurality of apertures in the airfoil member having an upstream inlet and a downstream exit and operable to pass a fluid therethrough oriented to cool the inner wall that extends beyond the portion of the outer wall, wherein the downstream exits of the apertures are non-circular.

IPC Classes  ?

• F01D 5/18 - Hollow bladesHeating, heat-insulating, or cooling means on blades
• F01D 5/20 - Specially-shaped blade tips to seal space between tips and stator
• F01D 11/12 - Preventing or minimising internal leakage of working fluid, e.g. between stages for sealing space between rotor blade tips and stator using a rubstrip, e.g. erodible, deformable or resiliently biased part
• F01D 11/24 - Actively adjusting tip-clearance by selectively cooling or heating stator or rotor components
• F01D 25/12 - Cooling
• F02C 7/18 - Cooling of plants characterised by cooling medium the medium being gaseous, e.g. air

Abstract

A cooling system for use with a gas turbine engine is disclosed wherein the cooling system provides cooling to the object of cooling in the gas turbine. The gas turbine engine comprises a heat exchanger to cool air of a first working fluid stream, a cooling medium inlet for the heat exchanger to receive a second working fluid stream in one bypass duct, and a cooling medium outlet for the heat exchanger to discharge the cooling medium into a third working fluid stream in another bypass duct. The cooling system is structured to transfer heat from the air of the first working fluid stream to the cooling medium and discharge it into the third working fluid stream.

IPC Classes  ?

• F01D 25/12 - Cooling
• F02C 7/14 - Cooling of plants of fluids in the plant
• F02C 7/141 - Cooling of plants of fluids in the plant of working fluid
• F02C 7/143 - Cooling of plants of fluids in the plant of working fluid before or between the compressor stages

Abstract

A gas turbine engine and with a heat exchange system is disclosed wherein the heat exchange system provides adaptive cooling to the object of cooling in the gas turbine. The gas turbine engine comprises an engine core, a first fan operable to generate a first air stream at a first pressure, a second fan operable to receive a portion of the first air stream and generate a second air stream at a second pressure, a fan bypass duct to receive a portion of the second air stream, and another fan bypass duct to receive a portion of the first air stream. The heat exchange system is configurable to cool the object of cooling using one of or both of the first and the second air stream to provide adaptive cooling.

IPC Classes  ?

• F01D 25/12 - Cooling
• F02C 6/08 - Gas-turbine plants providing heated or pressurised working fluid for other apparatus, e.g. without mechanical power output providing compressed gas the gas being bled from the gas-turbine compressor
• F02C 7/12 - Cooling of plants
• F02C 7/14 - Cooling of plants of fluids in the plant
• F02C 7/18 - Cooling of plants characterised by cooling medium the medium being gaseous, e.g. air

Abstract

A turbofan gas turbine engine is provided having a unique power off-take shaft and gear system. Other gas turbine engine types are also contemplated herein. Two power off- takes are provided, one each for the low pressure spool and high pressure spool. The power off-takes extend across a core flow path of the turbofan engine between the low and high pressure shafts to a fan frame of the turbofan. A drive gear is provided near the front end of the high pressure shaft, and another drive gear is provided on the low pressure shaft near the drive gear for the high pressure shaft. Both gears are located in a sump of the gas turbine engine. The power off-take shafts are coupled to the drive gears. Two power devices are coupled to the power off-take shafts and are located in the fan frame. The power devices can be electric generators or motors.

IPC Classes  ?

• F01D 15/10 - Adaptations for driving, or combinations with, electric generators
• F02C 7/275 - Mechanical drives
• F02C 7/32 - Arrangement, mounting, or driving, of auxiliaries
• F02C 7/36 - Power transmission between the different shafts of the gas-turbine plant, or between the gas-turbine plant and the power user