A control system for a hybrid electric powerplant of an aircraft can include a master controller configured to receive one or more power settings and to output a heat engine setting and an electric motor setting and a heat engine controller operatively connected to the master controller. The heat engine controller can be configured to receive the heat engine setting and to control a heat engine system as a function of the heat engine setting to control torque output by a heat engine. The system can include an electric motor controller operatively connected to the master controller. The electric motor controller configured to receive the electric motor engine setting and to control an electric motor system as a function of the electric motor setting to control torque output by an electric motor. The master controller can include a protection control module configured to provide one or more protection commands to directly control one or more heat engine protection systems and one or more electric motor protection systems.
A turbine blade has an attachment root and an airfoil. A cooling passageway system has a plurality of trunks extending from respective inlets along the root inner diameter end from a leading trunk near a first axial end to a trailing trunk near a second axial end; and a plurality of outlets along the airfoil including trailing edge outlets fed by the trailing trunk. Viewed normal to a root end-to-end centerplane: the trailing trunk has a turn passing forward and then rearward; an outside of the turn protrudes forward; and the outside of the turn has a tighter curvature than an inside of the turn.
An investment casting core system includes first and second investment casting cores. The first investment casting core has a pin and the second investment casting core has a hole and an access slot that opens to the hole. The pin is disposed in the hole such as to space the first investment casting core in a fixed position relative to the second investment casting core. A bonding agent is disposed in the access slot and around the pin in the hole.
A method (400) for applying a coating to a substrate (124) includes spraying (414) an aluminum-based coating layer (120) on the substrate. The coating layer is then infiltrated (420) with an aqueous solution (610). The solution comprises: a source of chromium; and potassium hexafluorozirconate.
C23F 11/00 - Inhibiting corrosion of metallic material by applying inhibitors to the surface in danger of corrosion or adding them to the corrosive agent
C25D 3/02 - ElectroplatingBaths therefor from solutions
C25D 3/04 - ElectroplatingBaths therefor from solutions of chromium
C25D 3/06 - ElectroplatingBaths therefor from solutions of chromium from solutions of trivalent chromium
C23C 4/00 - Coating by spraying the coating material in the molten state, e.g. by flame, plasma or electric discharge
C23C 4/04 - Coating by spraying the coating material in the molten state, e.g. by flame, plasma or electric discharge characterised by the coating material
C23C 4/137 - Spraying in vacuum or in an inert atmosphere
C23C 10/18 - Solid state diffusion of only metal elements or silicon into metallic material surfaces using liquids, e.g. salt baths, liquid suspensions
C23C 22/05 - Chemical surface treatment of metallic material by reaction of the surface with a reactive liquid, leaving reaction products of surface material in the coating, e.g. conversion coatings, passivation of metals using aqueous solutions
C23C 22/30 - Chemical surface treatment of metallic material by reaction of the surface with a reactive liquid, leaving reaction products of surface material in the coating, e.g. conversion coatings, passivation of metals using aqueous solutions using aqueous acidic solutions with pH < 6 containing hexavalent chromium compounds containing also trivalent chromium
C23C 22/56 - Treatment of aluminium or alloys based thereon
5.
COATING REPAIR FOR CERAMIC MATRIX COMPOSITE (CMC) SUBSTRATES
In a method for repairing a coated article, the article has: a ceramic matrix composite (CMC) substrate; and a coating system having a plurality of layers. A damage site at least partially penetrates at least one of the layers. The method includes: applying a slurry of a repair material to the damage site for repairing a first of the penetrated layers; and after the applying, heating the repair material with a plasma torch.
C04B 35/565 - Shaped ceramic products characterised by their compositionCeramic compositionsProcessing powders of inorganic compounds preparatory to the manufacturing of ceramic products based on non-oxides based on carbides based on silicon carbide
C04B 35/571 - Fine ceramics obtained from polymer precursors
A system for automated adaptive manufacturing of airfoil castings is disclosed. The system may receive a three dimensional scan of a work piece. The system may compare the three dimensional scan to a digital model of the work piece. The system may identify an area of dimensional abnormality on the work piece based on the comparison. The system may alter the area of dimensional abnormality on the work piece.
A metal-supported electrolyzer includes an electrolysis cell that has, in stacked order, an electrode unit having a first solid oxide electrode layer, a solid oxide electrolyte layer that is proton-conductive in a temperature range of 650°C or lower, and a second solid oxide electrode layer. A porous metal sheet in contact with the second solid oxide electrode layer supports the electrode unit, a metal separator sheet bonded to the porous metal sheet, and a metal interconnect backing the metal separator sheet.
C25B 1/04 - Hydrogen or oxygen by electrolysis of water
C25B 9/10 - Cells comprising dimensionally-stable non-movable electrodes; Assemblies of constructional parts thereof with diaphragms including an ion-exchange membrane in or on which electrode material is embedded
Aerospace components that are exposed to foreign particles during operation are described. The aerospace components include a substrate surface and a coating and/or means for repelling a foreign particle from the substrate surface.
An apparatus for countergravity casting a metallic material, comprises: a crucible for holding melted metallic material; a casting chamber for containing a mold; a fill tube capable of extending into the crucible to communicate melted metallic material to the casting chamber; a gas source coupled a headspace of the melting vessel to allow the gas source to pressurize said headspace to establish a pressure differential to force the melted metallic material upwardly through said fill tube into said mold; and means for gettering sulfur.
A combustor assembly (56) for a turbine engine includes a liner panel (64) defining a portion of an inner surface (68) of a combustor chamber (55), liner panel including an end face (70) transverse the inner surface, and at least one diffuser (84) through the end face. A liner panel and a method are also disclosed.
A method of manufacturing a composite vessel assembly (20) includes the step of placing the composite vessel assembly (20) in a pliable containment (94) prior to curing of a resin of the composite vessel assembly (20). With the composite vessel assembly (20) in the pliable containment (94), a vacuum is applied through an orifice (96) in the pliable containment (94) to evacuate air and compact the composite vessel assembly (20).
B29C 70/44 - Shaping or impregnating by compression for producing articles of definite length, i.e. discrete articles using isostatic pressure, e.g. pressure difference-moulding, vacuum bag-moulding, autoclave-moulding or expanding rubber-moulding
An aircraft has a gas turbine engine including a compressor section that includes at least one compressor bleed. An environmental control system has an air input configured to receive pressurized cabin air. An intercooler has an input and an output. A selection valve is configured to selectively connect the bleeds to an intercooler input. At least one auxiliary compressor is connected to the intercooler output. An output of at least one auxiliary compressors is connected to an ECS air input. A controller is configured to receive contemporaneous operational data, calculate minimum configuration requirements to satisfy environmental demands, and transmit calculated configuration requirements to at least the selection valve to achieve a desired pressure and temperature for the air downstream of the auxiliary compressor. A method for supplying engine air to an environmental control system and a system for use on a turbine engine powered aircraft are also disclosed.
B64D 13/06 - Arrangements or adaptations of air-treatment apparatus for aircraft crew or passengers, or freight space the air being conditioned
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
B64D 27/10 - Aircraft characterised by the type or position of power plants of gas-turbine type
14.
INTERCOOLED COOLED COOLING INTEGRATED AIR CYCLE MACHINE
A first cooling stage is fluidly coupled to a bleed port of a compressor to receive and cool bleed air with the air stream to produce a cool bleed air. A cooling pump receives and increase a pressure of the cool bleed air to produce a pressurized cool bleed air. A second cooling stage is fluidly coupled to the pump to receive and cool the pressurized cool bleed air to produce an intercooled cooling air. A is valve downstream of the first cooling stage, the valve selectively delivering air into a mixing chamber where it is mixed with air from a tap that is compressed to a higher pressure than the air from the bleed port, and the valve also selectively supplying air from the first cooling stage to a use on an aircraft associated with the gas turbine engine. A method is also disclosed.
F02C 7/18 - Cooling of plants characterised by cooling medium the medium being gaseous, e.g. air
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
A pyroelectric system (10) is disclosed that includes a plurality of pyroelectric modules (44, 46, 48, 50). The pyroelectric modules individually include a pyroelectric element, a first port (44a, 46a, 48a, 50a), a second port (44b, 46b, 48b, 50b), and an internal module fluid flow path (26) between the first port and the second port in thermal communication with the pyroelectric element. The pyroelectric modules are arranged along a cascade fluid flow path (51) connecting the first ports of the pyroelectric modules. A hot side inlet (28) to the cascade fluid flow path receives fluid at a first temperature from a heat source in fluid communication with the cascade fluid flow path, and the fluid is discharged from the cascade fluid flow path to a hot side outlet (34). A sink fluid flow path (53) comprises fluid at a second temperature lower than the first temperature, and is in fluid communication with the second ports of each of the plurality of pyroelectric modules.
H01L 37/02 - Thermoelectric devices without a junction of dissimilar materials; Thermomagnetic devices, e.g. using Nernst-Ettinghausen effect; Processes or apparatus specially adapted for the manufacture or treatment thereof or of parts thereof using thermal change of dielectric constant, e.g. working above and below the Curie point
A rotor blade deflection sensing system including a rotor blade having a first surface, a second surface, a third surface and a fourth surface. At least two fiber optic sensor arrays are mounted to the rotor blade. At least one of the at least two fiber optic sensor arrays is mounted to one of the first surface, the second surface, the third surface and the fourth surface and another of the at least two fiber optic sensor arrays being mounted to another of the first surface, a second surface, a third surface and a fourth surface. A controller is operatively connected to the at least two fiber optic sensor arrays. The controller determines one or more of a flapwise and an edgewise displacement based on inputs from the at least two fiber optic sensor arrays.
An electrocaloric element for a heat transfer system includes an electrocaloric material of a copolymer of (i) vinylidene fluoride, (ii) an addition polymerization monomer selected from tetrafluoroethylene, trifluoroethylene, vinyl fluoride, or combinations thereof, and (iii) a halogenated addition polymerization monomer larger than vinylidene fluoride. It is also provided that: (a) the monomer (ii) includes an addition polymerization monomer smaller than trifluoroethylene, (b) at least one of the addition polymerization monomers (ii) or (iii) is a chiral monomer, and the copolymer includes syndiotactic ordered segments of chiral monomer units, and/or (c) at least one of the addition polymerization monomers (ii) or (iii) comprises chlorine, and the copolymer includes an ordered distribution of monomer units comprising chlorine along the copolymer polymer backbone.
A heat transfer system is disclosed in which, an electrocaloric material includes a copolymer of a monomer mixture including (i) vinylidene fluoride, (ii) an addition polymerization monomer selected from tetrafluoroethylene, trifluoroethylene, or a monomer smaller than trifluoroethylene, and (iii) a halogenated addition polymerization monomer different than (ii) that is larger than vinylidene fluoride. The electrocaloric material also includes an additive selected from a nucleating agent having a polar surface charge, electrocalorically active solid particles, or a combination thereof. Electrodes are disposed on opposite surfaces of the electrocaloric material, and an electric power source is configured to provide voltage to the electrodes. The system also includes a first thermal flow path between the electrocaloric material and a heat sink, and a second thermal flow path between the electrocaloric material and a heat source.
A method of making an energy storage article having a metal nitride electrode is disclosed where metal nitride is made by nitriding particles of a metal or oxide of a metal selected from vanadium molybdenum, titanium, niobium, tungsten, or combinations including any of the foregoing by contacting the particles with a gas of nitrogen and hydrogen, or ammonia, in a fluidized bed reactor to form particles of metal nitride for the electrode.
H01G 11/30 - Electrodes characterised by their material
H01G 11/24 - Electrodes characterised by structural features of the materials making up or comprised in the electrodes, e.g. form, surface area or porosityElectrodes characterised by the structural features of powders or particles used therefor
H01G 11/86 - Processes for the manufacture of hybrid or EDL capacitors, or components thereof specially adapted for electrodes
20.
DEEP CONVOLUTIONAL NEURAL NETWORKS FOR CRACK DETECTION FROM IMAGE DATA
A method includes detecting at least one region of interest in a frame of image data. One or more patches of interest are detected in the frame of image data based on detecting the at least one region of interest. A model including a deep convolutional neural network is applied to the one or more patches of interest. Post-processing of a result of applying the model is performed to produce a post-processing result for the one or more patches of interest. A visual indication of a classification of defects in a structure is output based on the result of the post-processing.
A pressure vessel assembly includes a vessel having a wall defining a chamber and a circumferentially continuous lip projecting into the chamber from the wall. The lip defines a through-bore that is in fluid communication with the chamber. A nozzle assembly of the pressure vessel assembly includes a tube projecting at least in-part into the through-bore, and an o-ring disposed between, and in sealing contact with, the tube and the lip.
A method of manufacturing a composite vessel assembly (20) includes the steps of filling a first chamber defined by a first liner (28,30,32) with a first granulated material (96) through a first orifice (98) in the first liner. A vacuum is then applied to the first chamber, and the first orifice is plugged. The first liner may then be enveloped with a first layer (84) for structural rigidity followed by relief of the vacuum.
B29C 33/54 - Moulds or coresDetails thereof or accessories therefor with means for, or specially constructed to facilitate, the removal of articles, e.g. of undercut articles made of powdered or granular material
B29C 33/52 - Moulds or coresDetails thereof or accessories therefor with means for, or specially constructed to facilitate, the removal of articles, e.g. of undercut articles soluble or fusible
B29C 70/42 - Shaping or impregnating by compression for producing articles of definite length, i.e. discrete articles
F17C 1/16 - Pressure vessels, e.g. gas cylinder, gas tank, replaceable cartridge constructed of plastics materials
B29C 70/32 - Shaping by lay-up, i.e. applying fibres, tape or broadsheet on a mould, former or coreShaping by spray-up, i.e. spraying of fibres on a mould, former or core on a rotating mould, former or core
23.
COMPOSITE PRESSURE VESSEL ASSEMBLY AND METHOD OF MANUFACTURING
A composite pressure vessel assembly includes a first vessel having a first inner layer and a second vessel having a second inner layer. An outer layer of the assembly is in contact with and substantially envelopes the first and second inner layers. A junction of the assembly has outer boundaries defined by segments of the first inner layer, the second inner layer and the outer layer. A cross-layered component of the assembly is disposed in the junction, the first and second inner layers and the outer layer for adding strength to the junction and restricting delamination.
F17C 1/14 - Pressure vessels, e.g. gas cylinder, gas tank, replaceable cartridge constructed of aluminiumPressure vessels, e.g. gas cylinder, gas tank, replaceable cartridge constructed of non-magnetic steel
F17C 1/16 - Pressure vessels, e.g. gas cylinder, gas tank, replaceable cartridge constructed of plastics materials
24.
SYSTEMS AND METHODS FOR DETECTING ENGINE VIBRATION
Systems and methods of monitoring health of rotating engine components are provided. The systems and methods may receive a measurement from a speed sensor (44), detect the measurement from the speed sensor (44) indicates a vibration of an engine, determine the vibration of the engine persisted for a predetermined duration, and signal the vibration of the engine is detected.
A turbomachine sealing component has: a substrate having circumferential surface; and a coating on the circumferential surface. The coating or a layer thereof is patterned to form circumferential sealing ridges.
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 11/00 - Preventing or minimising internal leakage of working fluid, e.g. between stages
F01D 11/08 - Preventing or minimising internal leakage of working fluid, e.g. between stages for sealing space between rotor blade tips and stator
F02C 7/00 - Features, component parts, details or accessories, not provided for in, or of interest apart from, groups Air intakes for jet-propulsion plants
A heat transfer system is disclosed that includes a plurality of electrocaloric elements (12) including an electrocaloric film (14), a first electrode (16) on a first side of the electrocaloric film, and a second electrode (18) on a second side of the electrocaloric film. A fluid flow path (20) is disposed along the plurality of electrocaloric elements, formed by corrugated fluid flow guide elements (19).
A heat transfer system includes an electrocaloric element comprising an electrocaloric film (12). A first electrical conductor is disposed on a first side of the electrocaloric film, and a second electrical conductor is disposed on a second side of the electrocaloric film. At least one of the first and second electrical conductors is an electrically conductive liquid. An electric power source (20) is in electrical contact with the first and second electrical conductors, and is configured to provide an electrical field across the electrocaloric film. A liquid flow path (28) is disposed along the plurality of electrocaloric elements for the electrically conductive liquid.
A heat transfer system is disclosed including a plurality of modules arranged in a stack. The stack modules include electrocaloric element and electrodes on each side of the film. A fluid flow path is disposed between two or more electrocaloric elements. A first electrical bus element (18) in electrical contact with the first electrode (14), and a second electrical bus element (20) in electrical contact with second electrode (16). The first electrical bus element is electrically connected to at least one other electrical bus of another electrocaloric element in the stack at the same polarity as said first electrical bus, or the second electrical bus element is electrically connected to at least one other electrical bus of another electrocaloric element in the stack at the same polarity as said second electrical bus.
A method of making an electrocaloric element includes forming conductive layers on opposing surfaces of a film comprising an electrocaloric material to form an electrocaloric element, wherein the forming of the conductive layers includes one or more of: vapor deposition of the conductive layers under reduced pressure for a duration of time, wherein the duration of time under reduced pressure is less than 240 minutes; vapor deposition of the conductive layers under reduced pressure for a duration of time, wherein the duration of time of exposure to conductive material deposition is less than 240 minutes; vapor deposition of the conductive layers under reduced pressure, wherein the reduced pressure is 10 -8 torr to 500 torr; or maintaining the film at a temperature of less than or equal to 200 °C during forming of the conductive layers.
H01L 37/02 - Thermoelectric devices without a junction of dissimilar materials; Thermomagnetic devices, e.g. using Nernst-Ettinghausen effect; Processes or apparatus specially adapted for the manufacture or treatment thereof or of parts thereof using thermal change of dielectric constant, e.g. working above and below the Curie point
A method of making an electrocaloric element includes dissolving or dispersing an electrocaloric polymer in an organic solvent having a boiling point of less than 100°C at 1 atmosphere to form a liquid composition comprising the electrocaloric polymer. A film of the liquid composition is cast on a substrate, and the organic solvent is evaporated to form a film of the electrocaloric polymer. The film is removed from the substrate and disposed between electrical conductors to form an electrocaloric element.
B29C 41/12 - Spreading-out the material on a substrate
F25B 21/00 - Machines, plants or systems, using electric or magnetic effects
F25B 21/04 - Machines, plants or systems, using electric or magnetic effects using Peltier effectMachines, plants or systems, using electric or magnetic effects using Nernst-Ettinghausen effect reversible
H01L 37/02 - Thermoelectric devices without a junction of dissimilar materials; Thermomagnetic devices, e.g. using Nernst-Ettinghausen effect; Processes or apparatus specially adapted for the manufacture or treatment thereof or of parts thereof using thermal change of dielectric constant, e.g. working above and below the Curie point
31.
COMPOSITE PRESSURE VESSEL ASSEMBLY AND METHOD OF MANUFACTURING
A composite pressure vessel assembly includes at least one liner defining a chamber. The liner is perforated such that an applied composite layer envelops the liner and at least partially extrudes into the perforations during manufacture and when the chamber is placed under a vacuum.
A composite pressure vessel assembly includes a first and second vessels aligned side-by-side. Each vessel has a liner defining respective chambers. First and second mid-layers of the assembly cover the respective liners with portions of the respective mid-layers being in contact with one-another. An outer layer of the vessel assembly is in contact with and substantially envelops both mid-layers except for the mid-layer portions.
A pressure vessel assembly includes a composite layer surrounding at least one chamber. A heating element is embedded in the composite layer for extracting gas from the chamber.
A pressure vessel assembly includes a vessel including a wall defining a chamber and a circumferentially continuous lip projecting into the chamber from the wall. The lip defines a through-bore in fluid communication with the chamber. A nozzle assembly including a tube and a flange projecting radially outward from the tube. The tube includes a first portion projecting from the flange and through the through-bore and an opposite second portion projecting outward from the flange. The flange is in contact with the wall and the first portion includes an outer surface having a contour configured to produce sealing friction between the lip and the outer surface.
An illustrative example embodiment of a grid-forming inverter system includes an inverter including a plurality of switches, the inverter being configured to be selectively connected to a power grid; and an electronic controller including a voltage magnitude module that is configured to determine a voltage magnitude reference based on a voltage of the power grid when the inverter is in an inactive mode wherein the inverter is not operating to provide power, a phase locked loop module that is configured to determine a reference angle based on a phase angle of the voltage of the power grid when the inverter is in the inactive mode, and wherein the controller uses the voltage magnitude reference and the reference angle to set an initial voltage of the inverter to be approximately synchronized with the voltage of the power grid when the inverter switches from the inactive mode into a power providing mode.
An additive fabrication process includes rotating a core member about a central axis. While the core member is rotating, a first material is selectively deposited onto the core member with respect to computerized design data representing an article to form a first radial layer of the article. While the core member with the first radial layer is rotating, a second material is selectively depositing onto the first radial layer with respect to the computerized design data to form a second radial layer of the article.
A method of configuring a power conversion cell for a distributed power system according to an example of the present disclosure includes: importing one or more software modules onto a controller of a conversion device configured to control power conversion with one or more of the modules selected based on one or more of a load or source device, and the results of a software simulation.
H02M 7/5387 - Conversion of DC power input into AC power output without possibility of reversal by static converters using discharge tubes with control electrode or semiconductor devices with control electrode using devices of a triode or transistor type requiring continuous application of a control signal using semiconductor devices only, e.g. single switched pulse inverters in a bridge configuration
H02J 1/00 - Circuit arrangements for dc mains or dc distribution networks
A power factor correction system according to the present disclosure includes an inverter connected in parallel with at least one load and a controller configured to command an output voltage of the inverter to provide reactive power to the at least one load when a voltage source is available to the load and real power and reactive power to the at least one load when the voltage source is unavailable to the load.
G05F 1/565 - Regulating voltage or current wherein the variable actually regulated by the final control device is DC using semiconductor devices in series with the load as final control devices sensing a condition of the system or its load in addition to means responsive to deviations in the output of the system, e.g. current, voltage, power factor
G05F 1/70 - Regulating power factorRegulating reactive current or power
H02M 1/42 - Circuits or arrangements for compensating for or adjusting power factor in converters or inverters
A cooling system includes an electrocaloric element (12) having a liquid crystal elastomer or a liquid form liquid crystal retained in an elastomeric polymer matrix. A pair of electrodes (14,16) is disposed on opposite surfaces of the electrocaloric element. A first thermal flow path (18) is disposed between the electrocaloric element and a heat sink (17). A second thermal flow path (22) is disposed between the electrocaloric element and a heat source (20). The system also includes a controller (24) configured to control electrical current to the electrodes and to selectively direct transfer of heat energy from the electrocaloric element to the heat sink along the first thermal flow path or from the heat source to the electrocaloric element along the second thermal flow path.
An energy storage assembly includes an energy storage unit. A supervisor is operable to determine a power reference set point based upon a cost function. A storage unit controller is configured to control the energy storage unit to provide electric energy to at least one load based upon a power reference input that is based upon the power reference set point and at least one dynamically changing power profile from the at least one load.
A microgrid according to an exemplary aspect of the present disclosure includes, among other things, a plurality of intelligent electronic devices configured to communicate directly with one another in a first language. Each of the intelligent electronic devices includes a controller and a gateway. The gateway is configured to convert incoming messages from the first language to a second language native to the controller. The first language is different than the second language. A method is also disclosed.
An image processing system configured to process perceived images of an environment includes a central processing unit (CPU) including a memory storage device having stored thereon a computer model of the environment, at least one sensor configured and disposed to capture a perceived environment including at least one of visual images of the environment and range data to objects in the environment, and a rendering unit (RU) configured and disposed to render the computer model of the environment forming a rendered model of the environment. The image processing system compares the rendered model of the environment to the perceived environment to update the computer model of the environment.
A microgrid controller includes a database in communication with a processor. The processor is operable to receive at least one microgrid input, to determine a first plurality of optimal power characteristic levels at a corresponding one of a plurality of first time intervals for a first time period, and to determine a second plurality of optimal power characteristic levels of a device determined at a corresponding one of a plurality of second time intervals for a second time period. The first time intervals are found at a first frequency different than a second frequency of the second time intervals. One of the second plurality of optimal power characteristic level corresponds to one of the first plurality of optimal power characteristic levels at each first time interval. The processor is configured to control a device optimal power characteristic level in response to the second plurality of optimal power characteristic levels.
G05B 13/02 - Adaptive control systems, i.e. systems automatically adjusting themselves to have a performance which is optimum according to some preassigned criterion electric
G06F 1/30 - Means for acting in the event of power-supply failure or interruption, e.g. power-supply fluctuations
H02J 3/06 - Controlling transfer of power between connected networksControlling sharing of load between connected networks
Disclosed is an ion-exchange membrane that includes a molecular barrier for influencing permeation selectivity through the membrane. The membrane includes fluorinated carbon backbone chains and fluorinated side chains that extend off of the fluorinated carbon backbone chains. The fluorinated side chains include acid groups for ionic conductivity. The acid groups surround and define permeable domains that are free of the fluorinated carbon backbone chains. Molecular barriers are located in the permeable domains and influence permeability through the domains.
An electrochemical device includes first and second spaced-apart electrodes. The first electrode is configured for redox reactions with a liquid electrolyte solution and the second electrode is configured for redox reactions with each of a gaseous reductant and a gaseous oxidant. An electrolyte separator is arranged between the electrodes.
A method of treating a carbon electrode includes heat treating a carbon-based electrode in an environment that is above approximately 325°C and that includes an oxidizing gas, and prior to use of the carbon-based electrode in an electro-chemical battery device, soaking the carbon-based electrode in an oxidizer solution.
A method for treating a liquid redox electrolyte solution for use in a flow battery includes feeding a liquid redox electrolyte solution into a first half-cell of an electrochemical cell and feeding a gaseous reductant into a second half-cell of the electrochemical cell, and electrochemically reducing at least a portion of the liquid redox electrolyte solution in the electrochemical cell using the gaseous reductant.
A power balancing assembly according to an exemplary aspect of the present disclosure includes, among other things, at least one sensor operable to detect a first electrical parameter and a second electrical parameter relating to a first portion of a power grid. An energy storage device is coupled to a second portion of the power grid. A controller determines that the second portion should be disconnected from the first portion based upon determining an electrical variation in the first electrical parameter, and causes the energy storage device to operate at a power level based on an instantaneous value of the second electrical parameter prior to the second portion being disconnected from the first portion of the power grid.
A method includes converting time-series data from a plurality of prognostic and health monitoring (PHM) sensors into frequency domain data. One or more portions of the frequency domain data are labeled as indicative of one or more target modes to form labeled target data. A model including a deep neural network is applied to the labeled target data. A result of applying the model is classified as one or more discretized PHM training indicators associated with the one or more target modes. The one or more discretized PHM training indicators are output.
An assembly for detecting a grid condition according to an exemplary aspect of the present disclosure includes, among other things, a controller that determines an electrical variation of an electrical parameter, the electrical variation relating to a mechanical torque oscillation of a power generation device, and determines that the power generation device should be disconnected from the power grid if the electrical variation meets a preselected criterion. A method of detecting a grid event is also disclosed.
H02J 9/06 - Circuit arrangements for emergency or stand-by power supply, e.g. for emergency lighting in which the distribution system is disconnected from the normal source and connected to a standby source with automatic change-over
51.
MULTI-MODAL SENSOR DATA FUSION FOR PERCEPTION SYSTEMS
A method includes fusing multi-modal sensor data from a plurality of sensors having different modalities. At least one region of interest is detected in the multi-modal sensor data. One or more patches of interest are detected in the multi-modal sensor data based on detecting the at least one region of interest. A model that uses a deep convolutional neural network is applied to the one or more patches of interest. Post-processing of a result of applying the model is performed to produce a post-processing result for the one or more patches of interest. A perception indication of the post-processing result is output.
Heat pump cycle provided with a fluidic loop connecting two heat exchangers. The fluidic loop is filled with an electro-caloric liquid as a heat transfer medium. Applying electric filed in one of the heat exchangers the temperature of the electro-caloric liquid is changed.
An electrolytic capacitor comprising an anode; a cathode; a Kraft paper separator that is either coated with a polymer coating or where some of the hemicellulose and cellulose of the Kraft paper has been removed and replaced by the polymer coating, said polymer having a Tg of less than 160 degrees C, a degradation temperature of greater than 200 degree C and a conductivity of 10 to 1000 Siemens per centimeter at 20 degrees C; and a non-aqueous liquid electrolyte, said electrolyte having a vapor pressure of less than 2 mm at 20 degrees C, a boiling point equal to or greater than 200 degrees C, and a melting point equal to or less than -30 degrees C.
A composite pressure vessel assembly includes a plurality of lobes, each of the lobes having at least one interior wall and at least one curved wall, the plurality of lobes being positioned in a side by side arrangement and extending in a longitudinal direction from a first end to a second end. Also included is a plurality of end caps disposed at the ends of the lobes, wherein the plurality of lobes and end caps are formed of at least one fiber-reinforced polymer. A method of manufacturing a composite pressure vessel assembly is provided. The method includes forming a plurality of lobes consisting of at least one fiber-reinforced polymer. The method also includes forming a main body with the plurality of lobes, the lobes disposed in a side by side arrangement.
F17C 1/14 - Pressure vessels, e.g. gas cylinder, gas tank, replaceable cartridge constructed of aluminiumPressure vessels, e.g. gas cylinder, gas tank, replaceable cartridge constructed of non-magnetic steel
F17C 1/16 - Pressure vessels, e.g. gas cylinder, gas tank, replaceable cartridge constructed of plastics materials
A method is disclosed for regenerating an electrode of a flow battery. The method can be executed during shutdown of the flow battery from an active charge/discharge mode to an inactive, shut-down mode in which neither a negative electrolyte nor a positive electrolyte are circulated through at least one cell of the flow battery. The method includes driving voltage of the least one cell of the flow battery toward zero by converting, in-situ, the negative electrolyte in the at least one cell to a higher oxidation state. The negative electrolyte is in contact with an electrode of the at least one cell. The higher oxidation state negative electrolyte is used to regenerate, in-situ, catalytically active surfaces of the electrode of the at least one cell.
An article with controllable wettability includes a substrate and a layer of a composite material supported on the substrate. The layer has an exposed surface and the composite material includes particles that have controllable polarization embedded fully or partially in a matrix. A controller is operable to selectively apply a controlled variable activation energy to the layer. The controllable polarization of the particles varies responsive to the controlled variable activation energy such that a wettability of the exposed surface also varies responsive to the controlled variable activation energy.
B01J 19/08 - Processes employing the direct application of electric or wave energy, or particle radiationApparatus therefor
B05D 7/00 - 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
B82B 1/00 - Nanostructures formed by manipulation of individual atoms or molecules, or limited collections of atoms or molecules as discrete units
B82Y 30/00 - Nanotechnology for materials or surface science, e.g. nanocomposites
A drainage assembly (68) includes a first segment (70A) with a first inner tube (76A) defining a first inner tube passage (78A), a first outer tube (72A) concentrically disposed around the first inner tube (76A) and defining a first outer tube passage (74A), and a first fitting (80A) disposed on an end of the first segment (70A). The first fitting (80A) has a first inner passage (82A) in fluid communication with the first inner tube passage (78A) and a first outer passage (84A) in fluid communication with the first outer tube passage (74A). A plate (88) is positioned adjacent the first fitting (80A). The plate (88) has a second inner passage (90) in fluid communication with the first inner passage (82A) on one side, and a second outer passage (92) in fluid communication with the first outer passage (84A) on the one side. Also included is a drainage line (104) in fluid communication with the first outer tube passage (74A).
F16L 55/07 - Arrangement or mounting of devices, e.g. valves, for venting or aerating or draining
F02C 7/00 - Features, component parts, details or accessories, not provided for in, or of interest apart from, groups Air intakes for jet-propulsion plants
A method for preparing an alloy nanocellular foam includes at least partially coating a nanocellular precursor into a multiple composition nanoparticle precursor and converting the multiple composition nanoparticle precursor into an alloy via a diffusion process.
An airfoil of a turbine engine includes pressure and suction sides and extends in a radial direction from a 0% span position to a 100% span position. The airfoil has a relationship between a stagger angle and span position that defines a curve with a stagger angle that is greater than 32° from 90% span to 100% span.
A blade outer air seal according to an exemplary aspect of the present disclosure includes, among other things, a body to be distributed circumferentially about a blade array. The body has a plurality of grooves, which can, for example, improve the aerodynamic efficiency of a turbine. A fin is between a first groove and a second groove of the plurality of grooves. The fin extends radially from the body and terminates at a radially inner fin face that provides one or more cooling outlets.
An airfoil of a turbine engine includes pressure and suction sides that extend in a radial direction from a 0% span position to a 100% span position. The airfoil has a relationship between a leading edge angle and span position that defines a curve with at least one of a decreasingly negative slope or a positive slope from 80% span to 100% span.
An airfoil of a turbine engine includes pressure and suction sides and extends in a radial direction from a 0% span position to a 100% span position. The airfoil has a relationship between a leading edge angle and span position that defines a curve with a leading edge angle of less than 40° at 100% span.
A gas turbine engine includes a fan section, a compressor section and a turbine section, one of which includes an airfoil. The airfoil includes pressure and suction sides extending in a radial direction from a 0% span position at an inner flow path location to a 100% span position at an airfoil tip. The airfoil has a maximum chord length projection that is not in an axial view.
An airfoil of a turbine engine includes pressure and suction sides and extends in a radial direction from a 0% span position to a 100% span position. The airfoil has a relationship between a camber angle and span position that defines a curve with the camber angle having a positive slope from 0% span to 100% span.
A compressor airfoil of a turbine engine having a geared architecture includes pressure and suction sides that extend in a radial direction from a 0% span position to a 100% span position. The airfoil has a relationship between an axial stacking offset and span position that includes a curve with a negative slope from 90% span to 100% span. The negative slope leans forward relative to an engine axis.
A compressor airfoil of a turbine engine having a geared architecture includes pressure and suction sides that extend in a radial direction from a 0% span position to a 100% span position. The airfoil has a relationship between a tangential stacking offset and span position that defines a curve that is non-linear.
A compressor airfoil of a turbine engine having a geared architecture includes pressure and suction sides extending in a radial direction from a 0% span position to a 100% span position. The airfoil has a relationship between leading edge sweep angle and span position defined by a curve in which the leading edge sweep angle is positive at 0% span and crosses to a negative leading edge sweep angle at a span position less than 80% span. A negative sweep angle is in the forward direction, and a positive sweep angle is in the rearward direction.
A compressor airfoil of a turbine engine having a geared architecture includes pressure and suction sides and extends in a radial direction from a 0% span position to a 100% span position. The airfoil has a relationship between a trailing edge angle and span position that defines a curve with a non-negative slope from 0% span to 20% span corresponding to a non-decreasing trailing edge angle.
F01D 25/24 - CasingsCasing parts, e.g. diaphragms, casing fastenings
F02C 7/00 - Features, component parts, details or accessories, not provided for in, or of interest apart from, groups Air intakes for jet-propulsion plants
A gas turbine engine component comprises an airfoil with a suction side and pressure side extending from a leading edge to a trailing edge. There are a plurality of cooling holes adjacent the leading edge, with the cooling holes having a non-circular shape, with a longer dimension and a smaller dimension. The airfoil defines a radial direction from a radially outer end to a radially inner end, and radially outer of the cooling holes spaced toward the radially outer end, which have the longer dimension extending closer to parallel to the radial direction. Radially inner cooling holes closer to the radially inner end having the longer dimension extend to be closer to perpendicular relative to the radial direction compared to the radially outer cooling holes.
Embodiments are directed to obtaining a specification comprising at least one requirement associated with a heating, ventilation, and air-conditioning (HVAC) system, and based on the specification, configuring a control system to control a movement of fluid back and forth across at least one regenerator device of the HVAC system and a mixing of the fluid with ambient air.
A gas turbine engine comprises a compressor, a combustor and a turbine. A housing for the gas turbine engine includes a mount member to define a vertically upper location. Sides of the engine are defined on opposed sides of the mount, with a fuel filter, a fuel pump and a fuel flow meter being positioned on a first side and an oil pump, an oil filter and an oil tank positioned on a second of the sides.
A septum-tied tube pack is provided that includes a first outer wall formed by a multiple of first connected radiuses. A second outer wall is formed by a multiple of second connected radiuses. A first end radius connects the first outer wall and the second outer wall. A second end radius connects the first outer wall and the second outer wall. A multiple of septum elements extend between the first outer wall and the second outer wall. A gas turbine engine is also provided that includes an engine case structure and a fluid conduit mounted to the engine case structure. The fluid conduit includes a septum-tied tube pack section.
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
74.
CONTAINER HAVING AN INTERNAL STRUCTURE WITH MINIMUM SURFACES
An illustrative example container includes a plurality of internal support members having a surface contour that at least approximates a minimum surface. The plurality of internal support members collectively provide structural support for carrying loads on the container. The plurality of internal support members collectively establish a plurality of cavities for at least temporarily containing fluid. An outer shell is connected with at least some of the internal support members. The outer shell includes a plurality of curved surfaces. The outer shell encloses the cavities.
B32B 3/12 - Layered products comprising a layer with external or internal discontinuities or unevennesses, or a layer of non-planar shapeLayered products comprising a layer having particular features of form characterised by a discontinuous layer, i.e. apertured or formed of separate pieces of material characterised by a layer of regularly-arranged cells whether integral or formed individually or by conjunction of separate strips, e.g. honeycomb structure
75.
GAS TURBINE ENGINE COMPONENT WITH SEPARATION RIB FOR COOLING PASSAGES
A gas turbine engine component comprises a body extending between two ends and having at least two cooling passages. The body has a first wall and second wall. At least two cooling passages include a first passage that is closer to the first wall than is a second of the passages at upstream locations along a flow path. The second passage has upstream locations that are closer to the second wall than are upstream portions of the first passage. The first and second passages cross along a length of the flow path such that downstream portions of the second passage are closer to the first wall than are downstream portions of the first passage, and downstream portions of the first passage are closer to the second wall than are downstream portions of the second passage.
An aircraft jet propulsion system may comprise a thermoelectric cooler array coupled to a portion thereof, wherein the TEC array converts electrical energy to heat energy to create a temperature gradient and cools a turbine case using the temperature difference of the TEC array. The system may include a controller configured to control an input power provided to each TEC of the array of TECs, such that the array of TECs facilitates controlled cooling of the aircraft jet propulsion system in response to the input power provided to each TEC of the array of TECs. The TEC array may be powered by an alternator or by a thermoelectric generator.
F25B 21/02 - Machines, plants or systems, using electric or magnetic effects using Peltier effectMachines, plants or systems, using electric or magnetic effects using Nernst-Ettinghausen effect
A mid-turbine frame for use in a gas turbine engine comprises at least one vane extending between a vane inner platform and a vane outer platform, and an inner case radially inward of the inner platform. A plurality of tie rods extend from a platform radially inward of the inner case to a radially outer location which is secured by a mount member. The tie rods are secured in the inner case by a forward bolt, and at least one rear bolt, with the forward bolt extending along an axis which is non-parallel to a center axis of the inner case. A gas turbine engine and a method for assembling a mid-turbine frame are also disclosed.
A gas turbine engine includes a fan shaft and a support which supports at least a portion of the fan shaft. The support defines at least one of a support transverse and a support lateral stiffness. A gear system drives the fan shaft. A flexible support at least partially supports the gear system, and defines at least one of a flexible support transverse and a flexible support lateral stiffness with respect to at least one of the support transverse and the support lateral stiffness. An input to the gear system defines at least one of an input transverse and an input lateral stiffness with respect to at least one of the support transverse and the support lateral stiffness. A method of designing a gas turbine engine is also disclosed.
A mid-turbine frame (MTF") for a jet engine is disclosed and comprises a duct that extends between a high pressure turbine ("HPT") and a low pressure turbine ("LPT"), the duct comprising a plurality of segments that together form an outer annular structure and an inner annular structure, the inner annular structure situated radially inward of the outer annular structure, and/or a plurality of vanes that extend radially outward from the inner annular structure toward the outer annular structure, each vane comprising a channel. Each segment may be coupled to an adjacent segment by a seal.
A method of additive manufacturing comprises determining a first resonant frequency of an unflawed reference workpiece at a first partial stage of completion, fabricating a production workpiece to the first partial stage of completion via additive manufacture, sensing a second resonant frequency of the production workpiece in-situ at the first partial stage of completion, during the fabrication, analyzing the workpiece for flaws based on comparison of the first and second resonant frequencies, and providing an output indicative of production workpiece condition, based on the analysis. An additive manufacturing system comprises an additive manufacturing tool, a sensor, and a controller. The additive manufacturing tool is disposed to construct a workpiece via iterative layer deposition. The sensor is disposed to determine a resonant frequency of the workpiece in-situ at the additive manufacturing tool, during fabrication. The controller is configured to terminate manufacture of the workpiece if the resonant frequency differs substantially from a reference frequency.
G01N 24/08 - Investigating or analysing materials by the use of nuclear magnetic resonance, electron paramagnetic resonance or other spin effects by using nuclear magnetic resonance
A gas turbine engine includes a conduit that is configured to direct a fluid to at least one manifold that is adjacent to a turbine section. A first intake is in fluid communication with the conduit. A second intake is in fluid communication with the conduit. A valve is configured to selectively direct a fluid from at least one of the first intake and the second intake.
In one exemplary embodiment, an airfoil for a turbine engine includes an airfoil that has pressure and suction sides and extends in a radial direction from a 0% span position at an inner flow path location to a 100% span position at an airfoil tip. The airfoil has a curve that corresponds to a relationship between a leading edge dihedral and a span position. The leading edge dihedral has a portion of the curve with a change in dihedral in the range of 90% to 100% span position of greater than 10°. A positive dihedral corresponds to suction side-leaning. A negative dihedral corresponds to pressure side-leaning.
An airfoil assembly has at least one cooling hole in an aft edge of at least one platform for cooling at least one of an axially downstream airfoil root and/or tip region. The airfoil assembly may be a high pressure turbine first stage vane coupled with a combustor operating at a low Pattern Factor.
A liner panel is provided for use in a combustor of a gas turbine engine. The liner panel includes a major dilution passage having a lip and a first seal boss. The liner panel also includes a minor dilution passage having a second seal boss adjacent the first seal boss.
A combustor wall assembly has a heat shield and a supporting shell with a cooling cavity defined therebetween. A grommet generally includes a wall defining a dilution hole isolated from the cooling cavity, and a flange projecting radially outward from the wall and into the cooling cavity. The flange is space from the heat shield and a cooling channel is defined between the wall and the heat shield that communicates with the cavity for cooling the wall proximate to a combustion chamber.
F23R 3/42 - Continuous combustion chambers using liquid or gaseous fuel characterised by the arrangement or form of the flame tubes or combustion chambers
F02C 3/14 - Gas-turbine plants characterised by the use of combustion products as the working fluid characterised by the arrangement of the combustion chamber in the plant
86.
AUXILIARY OIL SYSTEM FOR GEARED GAS TURBINE ENGINE
A gas turbine engine comprises a fan drive turbine, a fan rotor, and a gear reduction driven by the fan drive turbine to, in turn, drive the gear architecture. A main oil supply system supplies oil to components within the gear reduction, and an auxiliary oil supply system. The auxiliary oil system operates to ensure that the gear reduction will be adequately supplied with lubricant for at least 30 seconds at power should the main oil supply system fail.
The present disclosure relates generally to a hydrostatic advanced low leakage seal having a shoe supported by at least one beam. An anti-vibration seal is disposed in contact with beam and operative to mitigate an externally induced vibratory response of the beam.
An assembly is provided for a turbine engine. This turbine engine assembly includes a combustor wall, which includes a shell, a heat shield and an annular body. The body at least partially defines a first aperture through the shell and the heat shield. The body also defines one or more second apertures through which air is directed into the first aperture and provides non-uniform cooling to the body.
F23R 3/42 - Continuous combustion chambers using liquid or gaseous fuel characterised by the arrangement or form of the flame tubes or combustion chambers
F02C 7/16 - Cooling of plants characterised by cooling medium
89.
GEARED GAS TURBINE ENGINE WITH REDUCED OIL TANK SIZE
A gas turbine engine comprises a fan drive turbine for driving a gear reduction, which drives a fan rotor. A lubrication system supplies oil to the gear reduction. An oil tank is relatively small. The lubrication system operates to allow oil to remain in the oil tank for a dwell time of less than or equal to five seconds. A method of designing a gas turbine engine is also disclosed.
A combustor for a gas turbine engine comprises a combustion chamber having a pilot injector at one end and at least one main injector spaced radially from the pilot injector. The main injector includes a fluid flow path with a plug that restricts flow at least at an interior portion of the flow path. A gas turbine engine is also disclosed.
An article includes a ceramic-based substrate and a barrier layer on the ceramic-based substrate. The barrier layer includes a matrix of barium-magnesium alumino-silicate or SiO2, a dispersion of silicon oxycarbide particles in the matrix, and a dispersion of particles, of the other of barium-magnesium alumino-silicate or SiO2, in the matrix.
B32B 9/00 - Layered products essentially comprising a particular substance not covered by groups
B32B 15/04 - Layered products essentially comprising metal comprising metal as the main or only constituent of a layer, next to another layer of a specific substance
92.
TURBINE AIRFOIL WITH ADDITIVE MANUFACTURED REINFORCEMENT OF THERMOPLASTIC BODY
A component for a gas turbine engine comprises an airfoil body formed of a plastic. A reinforcement portion has webs formed of a metallic material and extend into the airfoil. A gas turbine engine, and a method of forming a component for use in a gas turbine engine are also disclosed.
A testing apparatus may include a stand having an aperture and a platform adjacent to the aperture, a clamp adjacent to the platform and configured to hold a coupon, and an actuator within the aperture. The actuator is configured to impart a first force on the platform and the coupon at a specified frequency. The testing apparatus may also include a displacement sensor adjacent to the stand and configured to measure a displacement of the coupon and circuitry connected to the actuator and the displacement sensor with the circuitry configured to collect data from the actuator and the displacement sensor.
G01N 3/00 - Investigating strength properties of solid materials by application of mechanical stress
G01N 3/24 - Investigating strength properties of solid materials by application of mechanical stress by applying steady shearing forces
G01N 3/38 - Investigating strength properties of solid materials by application of mechanical stress by applying repeated or pulsating forces generated by electromagnetic means
B06B 1/06 - Processes or apparatus for generating mechanical vibrations of infrasonic, sonic or ultrasonic frequency making use of electrical energy operating with piezoelectric effect or with electrostriction
G01L 1/20 - Measuring force or stress, in general by measuring variations in ohmic resistance of solid materials or of electrically-conductive fluidsMeasuring force or stress, in general by making use of electrokinetic cells, i.e. liquid-containing cells wherein an electrical potential is produced or varied upon the application of stress
G01B 21/32 - Measuring arrangements or details thereof, where the measuring technique is not covered by the other groups of this subclass, unspecified or not relevant for measuring the deformation in a solid
G01J 5/48 - ThermographyTechniques using wholly visual means
94.
COMPRESSED CHOPPED FIBER COMPOSITE FAN BLADE PLATFORM
The present disclosure relates generally to the field of fan blade platforms for gas turbine engines. More specifically, the present disclosure relates to a compressed chopped fiber fan blade platform for a gas turbine engine.
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
An article such as a heat shield panel includes a substrate and a multi-layered coating supported on the substrate. The multi-layered coating can include alternating layers of different ceramic material compositions having individual thicknesses of less than 25 micrometers.
F23R 3/42 - Continuous combustion chambers using liquid or gaseous fuel characterised by the arrangement or form of the flame tubes or combustion chambers
F23R 3/46 - Combustion chambers comprising an annular arrangement of flame tubes within a common annular casing or within individual casings
A flow system for use in a gas turbine engine includes a diffuser case strut defining a first opening at a first radial end, a second opening at a second radial end, and a strut passage radially therethrough between the first and second openings. A first chamber wall and a second chamber wall define a first mixing chamber disposed radially inward of the diffuser case strut in fluid communication with the strut passage. A third chamber wall extends between the second flowpath wall and the second chamber wall to define a second mixing chamber disposed between the diffuser case strut and the first mixing chamber. The second flowpath wall and the second chamber wall are shaped to form a venturi in the second mixing chamber.
One exemplary embodiment according to this disclosure relates to a system includes a blade outer air seal (BOAS), and a meter plate. A portion of the meter plate is provided radially outward of a radially outermost surface of the BOAS.
A gas turbine engine according to an example of the present disclosure includes a drive turbine configured to drive a fan section, a speed change mechanism connected to the drive turbine and located aft of the drive turbine and aft of the fan. An output of the speed change mechanism connects to the fan.
An inlet manifold for a multi-tube pulse detonation engine includes a vaneless diffuser disposed in a first zone to collect an air discharged from a compressor; a vaned diffuser including a plurality of guide vanes disposed in a second zone to slow the air from the compressor; a plenum disposed in a third zone located next to second zone to provide the air from the compressor to chambers; and a splitter disposed in a fourth zone to split the air from the compressor into an airflow required by each pulse detonation tube for detonation.
F02K 7/067 - Plants in which the working-fluid is used in a jet only, i.e. the plants not having a turbine or other engine driving a compressor or a ducted fanControl thereof the jet being intermittent, i.e. pulse jet with combustion chambers having valves having aerodynamic valves
patents
