An example coolant nozzle includes a cylindrical shank having a first axial end and a second axial end; a nozzle head extending from the second axial end of the cylindrical shank; a central coolant channel extending from a central axis of the first axial end of the cylindrical shank to partially through a central axis of the nozzle head; and at least one first coolant delivery channel extending radially outward from the central coolant channel to an outer wall of the nozzle head.
B24B 55/03 - Equipment for cooling the grinding surfaces, e.g. devices for feeding coolant designed as a complete equipment for feeding or clarifying coolant
B05B 1/14 - Nozzles, spray heads or other outlets, with or without auxiliary devices such as valves, heating means with multiple outlet openingsNozzles, spray heads or other outlets, with or without auxiliary devices such as valves, heating means with strainers in or outside the outlet opening
2.
TURBINE SHROUD ASSEMBLIES WITH RETAINER FEATURES FOR BLOCKING SEAL MIGRATION
A turbine shroud assembly includes a carrier segment, a blade track segment, and a buffer air seal assembly. The carrier segment includes a cantilevered wall extending radially inwardly within a recess so as to form a groove between the cantilevered wall and the inner wall of the recess. The buffer air seal assembly includes first, second, and third seal members arranged in the groove. The second and third seal members are aligned with each other and arranged radially outward of the first seal member. The cantilevered wall a barrier portion wider than a main portion of the wall such that the barrier portion extends at least partially into the groove. The second and third seal members are arranged on opposing circumferential sides of the barrier portion such that the barrier portion blocks circumferential movement of the second and third seal members.
A turbine shroud assembly adapted for use with a gas turbine engine includes a carrier segment, a blade track segment, and a seal system. The carrier segment arranged circumferentially at least partway around an axis. The blade track segment is coupled to the carrier segment and defines a portion of a gas path of the gas turbine engine. The seal system includes seals arranged radially between the carrier segment and the blade track segment to block gases from flowing between the carrier segment and the blade track segment.
A turbine shroud assembly adapted for use with a gas turbine engine includes a carrier segment, a blade track segment, and a seal system. The carrier segment arranged circumferentially at least partway around an axis. The blade track segment is coupled to the carrier segment and defines a portion of a gas path of the gas turbine engine. The seal system includes seals arranged radially between the carrier segment and the blade track segment to block gases from flowing between the carrier segment and the blade track segment.
A turbine shroud assembly adapted for use with a gas turbine engine includes a carrier segment, a blade track segment, and a seal system. The carrier segment arranged circumferentially at least partway around an axis. The blade track segment is coupled to the carrier segment and defines a portion of a gas path of the gas turbine engine. The seal system is arranged radially between the carrier segment and the blade track segment to block gases from flowing between the carrier segment and the blade track segment.
A turbine shroud assembly for use with a gas turbine engine includes a first shroud segment, a second shroud segment, and a damping strip seal assembly. The first shroud segment has a first carrier segment arranged circumferentially at least partway around a central axis and a first blade track segment supported by the first carrier segment. The second shroud segment is arranged circumferentially adjacent the first shroud segment. The damping strip seal assembly includes a body segment and a damping segment that extends along a curvilinear path.
Rolls-Royce North American Technologies, Inc. (USA)
Rolls-Royce Corporation (USA)
Inventor
Heeter, Robert W.
Molnar, Jr., Daniel E.
Thralls, Jordan
Abstract
A turbine engine includes at least one turbine, combustion equipment, and at least one compressor. The at least one compressor includes a compressor stage. The compressor stage includes a plurality of compressor blades configured to input work into a core airflow flowing through the turbine engine. The turbine engine includes an electrical generator. The electrical generator includes a rotor carried on an outer diameter of the plurality of compressor blades of the compressor stage and mechanically rotated by the plurality of compressor blades of the compressor stage and configured to rotate about a longitudinal axis of the turbine engine. The electrical generator further includes a stator.
A dual-walled component of a gas turbine engine includes a cold section part, such as a spar, and a hot section part, such as a coversheet. The cold section part includes a single crystal or directionally solidified metal alloy and defines an outer surface, a hot section part comprising a polycrystalline metal alloy formed using additive manufacturing. The hot section part includes a plurality of support structures forming a plurality of cooling channels and defining an inner surface. The outer surface of the cold section part and the inner surface of the plurality of support structures are diffusion bonded.
An assembly adapted for use in a gas turbine engine includes a blade track segment, a carrier segment, and a pin. The blade track segment defines a portion of a gas path of the gas turbine engine. The carrier segment supports the blade track segment to locate the blade track segment radially outward of the axis. The pin couples the blade track segment to the carrier segment. The carrier segment may include cooling passageways to conduct cooling air to preselected cooling areas located on the blade track segment.
A turbine shroud assembly includes a carrier segment, a blade track segment, and a buffer air seal assembly. The carrier segment includes a cantilevered wall extending radially inwardly within a recess so as to form a groove between the cantilevered wall and the inner wall of the recess. The carrier segment includes a second recess located at an end of the groove that opens deeper into the segment than the groove. The buffer air seal assembly includes first and second seal members arranged in the groove, the second seal member being arranged radially outward of the first seal member. A first end of the second seal member extends circumferentially beyond the first circumferential end of the first groove, and the first end of the second seal member extends radially outwardly into the second recess so as to block circumferential movement of the second seal member.
Rolls-Royce North American Technologies, Inc. (USA)
Inventor
Krishnamoorthi, Sidharth
Gold, Matthew R.
Golden, Robert
Abstract
A method includes receiving, by a computing device, a raw image indicative of a cross-section of a thermally-sprayed layer. The image includes a matrix of pixels, and each respective pixel in the matrix of pixels defines a luminance value. The method may further include determining, based on the luminance values, at least one pixel that corresponds to an oxide component in the layer and removing the at least one pixel that corresponds to the oxide component in the layer to generate a modified matrix of pixels. The method may further include generating an oxide-filtered image based on the modified matrix of pixels. The method may further include converting, by the computing device and based on the luminance values, the oxide-filtered image into a binary image and determining, by the computing device and based at least partially on the binary image, a porosity of the coating layer.
Rolls-Royce North American Technologies, Inc. (USA)
Inventor
Krishnamoorthi, Sidharth
Gold, Matthew R.
Golden, Robert
Abstract
A method includes receiving, by a computing device, an image indicative of a cross-section of a thermally-sprayed layer. The thermally-sprayed layer includes a microstructure. The image comprises a matrix of pixels, each pixel in the matrix of pixels defining a respective luminance value. The method includes determining, by the computing device and based on the luminance values of the matrix of pixels, a quantification of a layering of the microstructure of the thermally-sprayed layer.
G06V 10/24 - Aligning, centring, orientation detection or correction of the image
G06V 10/77 - Processing image or video features in feature spacesArrangements for image or video recognition or understanding using pattern recognition or machine learning using data integration or data reduction, e.g. principal component analysis [PCA] or independent component analysis [ICA] or self-organising maps [SOM]Blind source separation
13.
POROSITY CHARACTERISTICS OF THERMAL SPRAY COATINGS TECHNICAL FIELD
Rolls-Royce North American Technologies, Inc. (USA)
Inventor
Krishnamoorthi, Sidharth
Gold, Matthew R.
Golden, Robert
Abstract
A method includes receiving, by a computing device, an image indicative of a cross-section of a thermally-sprayed layer. The thermally-sprayed layer defines a porosity comprising a void volume of the thermally-sprayed layer. The image comprises a matrix of pixels, each pixel in the matrix of pixels defining a respective luminance value of a plurality of luminance values. The method includes identifying, based on the luminance values, at least one pixel that is indicative of a void volume in the thermally-sprayed layer. The method includes calculating, based on the at least one pixel that is indicative of the void volume in the thermally-sprayed layer, a total porosity of the thermally-sprayed layer. The method includes determining, by the computing device and based on the at least one pixel that corresponds to a void volume in the thermally-sprayed layer, a quantification of a spatial homogeneity of the porosity of the thermally-sprayed layer.
An example aircraft includes a parallel propulsion unit, the parallel propulsion unit comprising: a propulsor configured to provide forward propulsion of the aircraft; a gas turbine engine configured to drive the propulsor; an electrical machine configured to generate, for output via one or more electrical busses, electrical energy using mechanical energy derived from the gas turbine engine; and a power sharing module configured to control a ratio of the mechanical energy used to drive the propulsor and used to generate electrical energy; and a plurality of series propulsion units, each series propulsion unit comprising a respective propulsor of a plurality of propulsors that are configured to provide vertical propulsion of the aircraft and a respective electrical machine of 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 one or more electrical busses.
B64D 35/024 - Transmitting power from power plants to propellers or rotorsArrangements of transmissions specially adapted for specific power plants for electric power plants of hybrid-electric type of series type
B64D 35/023 - Transmitting power from power plants to propellers or rotorsArrangements of transmissions specially adapted for specific power plants for electric power plants of hybrid-electric type of series-parallel type
F02C 6/00 - Plural gas-turbine plantsCombinations of gas-turbine plants with other apparatusAdaptations of gas-turbine plants for special use
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 7/00 - Arrangements for handling mechanical energy structurally associated with dynamo-electric machines, e.g. structural association with mechanical driving motors or auxiliary dynamo-electric machines
H02K 7/102 - Structural association with clutches, brakes, gears, pulleys or mechanical starters with friction brakes
H02K 7/116 - Structural association with clutches, brakes, gears, pulleys or mechanical starters with gears
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 11/00 - Structural association of dynamo-electric machines with electric components or with devices for shielding, monitoring or protection
H02P 1/54 - Arrangements for starting electric motors or dynamo-electric converters for starting dynamo-electric motors or dynamo-electric converters for starting two or more dynamo-electric motors
H02P 3/04 - Means for stopping or slowing by a separate brake, e.g. friction brake or eddy-current brake
An aircraft includes a first propulsion unit, a second propulsion, and a controller configured to increase thrust output in one of the first propulsion unit or the second propulsion unit in response to a detected thrust reduction from the other of the first propulsion unit. Each of the first propulsion unit and the second propulsion unit include a rotor driven by a gas turbine engine with a drive shaft, an output shaft coupled between the drive shaft and the driven rotor and a mechanical coupler for decoupling the output shaft from the drive shaft.
An assembly adapted for use in a gas turbine engine includes a blade track segment, a carrier segment, and a pin. The blade track segment defines a portion of a gas path of the gas turbine engine. The carrier segment supports the blade track segment to locate the blade track segment radially outward of the axis. The pin couples the blade track segment to the carrier segment. The carrier segment may include cooling passageways to conduct cooling air to preselected cooling areas located on the blade track segment.
Rolls-Royce North American Technologies, Inc. (USA)
Rolls-Royce Corporation (USA)
Inventor
Thralls, Jordan
Baninajar, Hossein
Abstract
An example electric machine of a gas-turbine engine having a longitudinal axis includes a stator; a rotor configured to rotate around the stator and about the longitudinal axis of the gas-turbine engine, the rotor comprising: a rotor body having an inner surface and an outer surface; and magnets on the inner surface of the rotor body, wherein axial edges of the magnets perpendicular to the longitudinal axis are profiled to include a shoulder that corresponds to a geometry of a radial retention structure of the rotor.
F01D 15/10 - Adaptations for driving, or combinations with, electric generators
H02K 1/28 - Means for mounting or fastening rotating magnetic parts on to, or to, the rotor structures
H02K 7/18 - Structural association of electric generators with mechanical driving motors, e.g.with turbines
H02K 21/22 - Synchronous motors having permanent magnetsSynchronous generators having permanent magnets with stationary armatures and rotating magnets with magnets rotating around the armatures, e.g. flywheel magnetos
A turbine shroud assembly comprising a first shroud segment, a second shroud segment, and a plurality of seals. The first shroud segment includes a first carrier segment and a first blade track segment having a first shroud wall that is formed to include a first recess that extends circumferentially into the first shroud wall. The second shroud segment includes a second carrier segment and a second blade track having a second shroud wall that is formed to include a second recess that extends circumferentially into the second shroud wall. The plurality of seals extend circumferentially into the first shroud segment and the second shroud segment to block gases from escaping the gas path radially between the first shroud segment and the second shroud segment.
An example method includes measuring, by at least one of a polarized light device, a spatially resolved acoustic spectroscopy device, or an eddy current device, an alpha phase data set indicative of an alpha phase of a crystalline structure of a material. The method includes receiving, by processing circuitry, the alpha phase data set, wherein the alpha phase data set comprises a plurality of pixels, wherein each pixel of the plurality of pixels includes a position, a first Euler angle, a second Euler angle, and a third Euler angle, wherein the third Euler angle is missing or erroneous. The method also includes adjusting, by the processing circuitry, the third Euler angle of a pixel of the plurality of pixels and storing, by the processing circuitry and based on adjusting the third Euler angle of the pixel reducing a total beta phase misorientation, the alpha phase data set.
G01N 23/207 - Diffractometry, e.g. using a probe in a central position and one or more displaceable detectors in circumferential positions
G01N 23/20058 - Measuring diffraction of electrons, e.g. low energy electron diffraction [LEED] method or reflection high energy electron diffraction [RHEED] method
A turbine shroud assembly for use with a gas turbine engine includes a carrier segment, a blade track segment, and a seal system. The carrier segment arranged circumferentially at least partway around an axis. The blade track segment is coupled to the carrier segment and defines a portion of a gas path of the gas turbine engine. The seal system is arranged radially between the carrier segment and the blade track segment to block gases from flowing between the carrier segment and the blade track segment.
An additive manufacturing system includes an energy delivery device configured to deliver energy to a build surface of a component to form a melt pool in the build surface of the component, a powder delivery device configured to direct a powder stream toward the melt pool, a gas delivery device configured to direct a gas stream toward or adjacent to the melt pool, at least one Schlieren imaging sensor configured to generate image data representative of a gas flow of one or more gas streams from the gas delivery device, and a computing device configured to receive the image data from the at least one Schlieren imaging sensor. The computing device is configured to determine a gas flow profile of the gas flow based on the image data and control the energy delivery device, gas delivery device and/or the powder delivery device based on the gas flow profile.
An additive manufacturing system includes an energy delivery device configured to deliver energy to a build surface of a component to form a melt pool in the build surface of the component, a powder delivery device configured to direct a powder stream toward the melt pool, a microstructural monitoring device configured to capture data representative of a microstructure of at least a portion of the component; and a computing device. The computing device is configured to receive data from the microstructural monitoring device, and control at least one of the powder delivery device or the energy delivery device based at least partially on the data received from the microstructural monitoring device.
An additive manufacturing system includes an energy delivery device configured to deliver energy to a build surface of a component to form a melt pool in the build surface of the component, a powder delivery device configured to direct a powder stream toward the melt pool, at least one sensor configured to generate sensor data, and a computing device. The computing device may be configured to receive the sensor data from the at least one sensor, determine, based on the sensor data, at least one powder flow characteristic, and generate a signal indicative of the at least one powder flow characteristic. The computing device may be further configured to control, based on the at least one powder flow characteristic, the energy delivery device and the powder delivery device to deposit a plurality of layers based on a set of deposition parameters.
An additive manufacturing system includes an energy delivery device configured to deliver energy to a build surface of a component to form a melt pool in the build surface of the component, a powder delivery device configured to direct a powder stream toward the melt pool, at least one sensor configured to generate powder data, and a computing device. The computing device may be configured to receive the powder data from the at least one sensor, determine, based on the powder data, at least one particle characteristic, and generate a signal indicative of the at least one particle characteristic. The computing device may be further configured to control, based on the at least one particle characteristic, the energy delivery device and the powder delivery device to deposit a plurality of layers based on a set of deposition parameters.
An additive manufacturing system includes an energy delivery device configured to deliver, a powder delivery device, and one or more thermal sensors configured to measure a temperature of a first portion of the additively-manufactured component and a second portion of the additively manufactured component. The additive manufacturing system includes a computing device configured to receive data indicative of the temperature of the first portion and of the second portion, determine a residual stress of the additively-manufactured component based at least partially on the received thermal sensor data from the first portion of the additively-manufactured component and the received data from the second portion of the additively-manufactured component; and predict final dimensions of the additively-manufactured component based at least partially on the determined residual stress of the additively-manufactured component.
An additive manufacturing system includes an energy delivery device configured to deliver energy to a build surface of a component to form a melt pool in the build surface of the component, a powder delivery device configured to direct a powder stream toward the melt pool, a spatter monitoring system, and a computing device configured to receive image data from the spatter monitoring system. The spatter monitoring system is configured to capture image data indicative of spatter, wherein spatter is material ejected from the melt pool. The computing device is configured to identify a spatter event based on the received image data and control at least one of the energy delivery device or the powder delivery device based on the determined spatter event.
An additive manufacturing system includes an energy delivery device configured to deliver energy to a build surface of a component to form a melt pool in the build surface of the component, a powder delivery device configured to direct a powder stream toward the melt pool, at least one sensor configured to generate sensor data representative of at least one process characteristic, and a computing device. The computing device is configured to receive the sensor data from the at least one sensor, determine, based on the sensor data and a predictive model data, at least one powder control parameter configured to achieve a predetermined powder feed rate of the powder stream, and control, based on the at least one powder control parameter, the energy delivery device and the powder delivery device to deposit a plurality of layers.
B29C 64/393 - Data acquisition or data processing for additive manufacturing for controlling or regulating additive manufacturing processes
B29C 64/153 - Processes of additive manufacturing using only solid materials using layers of powder being selectively joined, e.g. by selective laser sintering or melting
An additive manufacturing system includes a first energy delivery device configured to deliver energy to a build surface of an additively-manufactured component to form a melt pool in the build surface of the component and a second energy delivery energy delivery device. The system also includes a powder delivery device and a heat sensor configured to measure a temperature of a portion of an additively-manufactured component. The system includes a computing device configured to receive data from the heat sensor captured at a first point in time and captured at a second point in time, determine a thermal history of the component based at least partially on the received data captured at the first point in time and the received data received data captured at the second point in time, and control the first energy delivery device or the second energy delivery device based on the determined thermal history.
An additive manufacturing system includes an energy delivery device configured to deliver energy to a build surface of an additively-manufactured component to form a melt pool and a powder delivery device configured to direct a powder stream toward the melt pool. The system further includes a powder flow monitoring system configured to observe the powder stream and an optical system configured to observe the melt pool. A computing device configured to receive data indicative of a position of the powder stream, and receive data indicative of a position of the melt pool. The computing device is configured to determine a relative position of the powder stream to the melt pool and control, based on the determined relative position of the powder stream to the melt pool, one or both of the powder delivery device and the energy delivery device.
An additive manufacturing system includes an energy delivery device configured to deliver energy to a build surface of an additively-manufactured component being manufactured to form a melt pool in the build surface of the component. The system further includes a powder delivery device, a melt pool monitor configured to observe the melt pool, and a computing device. The computing device is configured to receive, from the melt pool monitor, data indicative of one or more parameters of the melt pool and determine, based on the received data, a current position of the melt pool. The computing device is configured to determine a desired size of the melt pool based on the current position of the melt pool and control, based on the desired size of the melt pool, the energy delivery device to form the melt pool of the desired size in the build surface of the component.
A method for additive manufacturing includes controlling, by a computing device, a powder delivery device to deliver a metal powder to a build surface of an abrasive coating and controlling, by the computing device, an energy delivery device to deliver energy to a melt pool of the build surface to form a metal matrix composite via an in situ reaction. The metal matrix composite includes a ceramic phase in a metal matrix.
B22F 10/34 - Process control of powder characteristics, e.g. density, oxidation or flowability
B22F 7/04 - Manufacture of composite layers, workpieces, or articles, comprising metallic powder, by sintering the powder, with or without compacting of composite layers with one or more layers not made from powder, e.g. made from solid metal
B22F 10/368 - Temperature or temperature gradient, e.g. temperature of the melt pool
B24D 18/00 - Manufacture of grinding tools, e.g. wheels, not otherwise provided for
B33Y 50/02 - Data acquisition or data processing for additive manufacturing for controlling or regulating additive manufacturing processes
B33Y 70/10 - Composites of different types of material, e.g. mixtures of ceramics and polymers or mixtures of metals and biomaterials
B33Y 80/00 - Products made by additive manufacturing
32.
ADAPTIVE MACHINING USING BUILD SURFACE TOPOLOGY FOR ADDITIVE MANUFACTURING SYSTEMS
An additive manufacturing system includes an energy delivery device configured to deliver energy to a build surface of a component to form a melt pool in the build surface of the component, a powder delivery device configured to direct a powder stream toward the melt pool, a machining device configured to machine the build surface, at least one topology sensor configured to generate topological data representative of a topology of the build surface, and a computing device configured to receive the topological data from the at least one topology sensor for a plurality of layers, identify differences between the topological data and specification data representative of a set of tolerances of the build surface, control the energy delivery device and the powder delivery device based on a set of deposition parameters, and control the machining device to machine the build surface based on the identified differences.
An additive manufacturing system includes an energy delivery device to deliver energy to a build surface of a deposit overlying a substrate to form a melt pool in the build surface, a powder delivery device to direct a powder stream toward the melt pool, and a computing device to determine a first set of deposition parameters for an innermost layer of the deposit overlying the substrate, determine a second set of deposition parameters for an inner plurality of layers of the deposit overlying the innermost layer, determine a third set of deposition parameters for an outer plurality of layers of the deposit overlying the inner plurality of layers, and control the energy delivery device and the powder delivery device to deposit the innermost layer, the inner plurality of layers, and the outer plurality of layers based on the respective first, second, and third sets of deposition parameters.
An additive manufacturing system includes an energy delivery device and a powder delivery device configured to form an as-deposited layer on a build surface of the component. The system includes a topology monitoring system configured to capture data indicative of a position of a surface of the as-deposited layer, and also includes a computing device. The computing device is configured to receive the data and determine an actual position of the surface of the as-deposited. The computing device is configured to compare the actual position to a modeled position of the surface of the as-deposited layer. The computing device is further configured to determine a difference between the actual position and the modeled position of the as-deposited layer and control at least one of the energy delivery device or the powder delivery device based on the difference between the actual position and the modeled position of the as-deposited layer.
An additive manufacturing system includes a first energy delivery device configured to deliver energy to a build surface of a component to form a melt pool in the build surface of the component, a second energy delivery device configured to deliver energy to the build surface of the component; a stage configured to support an additively-manufactured component, at least one heat sensor configured to capture data indicative of a temperature of a portion of a component, and a computing device. The computing device is configured to receive data from the at least one heat sensor; and control the first or the second energy device based at least partially on the received data from the at least one heat sensor to provide functionally-graded characteristics to the additively-manufactured component, in-situ, through modification of an amount of thermal energy delivered by the first energy delivery device or the second energy delivery device.
B22F 10/28 - Powder bed fusion, e.g. selective laser melting [SLM] or electron beam melting [EBM]
B22F 10/36 - Process control of energy beam parameters
B22F 10/85 - Data acquisition or data processing for controlling or regulating additive manufacturing processes
B22F 12/90 - Means for process control, e.g. cameras or sensors
B23K 26/03 - Observing, e.g. monitoring, the workpiece
B23K 26/144 - Working by laser beam, e.g. welding, cutting or boring using a fluid stream, e.g. a jet of gas, in conjunction with the laser beamNozzles therefor the fluid stream containing particles, e.g. powder
An additive manufacturing system may include an energy delivery device configured to deliver energy to a build surface of a component to form a melt pool in the build surface of the component; a powder delivery device configured to direct a powder stream toward the melt pool; a plurality of mass sensors, each mass sensor associated with a portion of the additive manufacturing system; a plurality of heat sensors; and one or more computing devices. The computing device(s) are configured to receive data from the plurality of mass sensors; determine an overall mass flux based on the data from the mass sensors; control the powder delivery device based on the overall mass flux; receive data from the plurality of heat sensors; determine an overall heat flux based on the data from the heat sensors; and control the energy delivery device based on the overall heat flux.
An additive manufacturing system includes an energy delivery device configured to deliver energy to a build surface of a component to form a melt pool, a powder delivery device configured to direct a powder stream toward the melt pool, a topology sensor configured to generate topographical data representative of a topology of the build surface, and a computing device configured to receive the topological data from the topology sensor for a first layer deposited according to an initial set of deposition conditions and determine a build height of the first layer based on the topological data, identify a difference between the build height and a target build height, determine an adjusted set of deposition parameters of a second layer based on the identified difference, and control the energy and powder delivery devices to deposit the second layer based on the adjusted set of deposition parameters.
Rolls-Royce North American Technologies, Inc. (USA)
Inventor
Gold, Matthew R.
Lagow, Benjamin W.
Blair, Taylor K.
Abstract
An example system includes at least one acoustic sensor configured to generate at least one time-dependent acoustic data signal indicative of an acoustic signal generated by an atomization system performing a process possessing a plurality of process attributes, and a computing device including an acoustic data signal processing module configured to receive the at least one time-dependent acoustic data signal, and transform the at least one time-dependent acoustic data signal to a frequency-domain spectrum, wherein each process attribute of the plurality of process attributes is associated with at least one respective frequency band, and a correlation module configured to determine a process attribute of the plurality of process attributes by identifying at least one characteristic of the frequency-domain spectrum.
B22F 9/08 - Making metallic powder or suspensions thereofApparatus or devices specially adapted therefor using physical processes starting from liquid material by casting, e.g. through sieves or in water, by atomising or spraying
Rolls-Royce North American Technologies, Inc. (USA)
Inventor
Gold, Matthew R.
Lagow, Benjamin W.
Blair, Taylor K.
Abstract
An example system includes at least one acoustic sensor configured to generate at least one time-dependent acoustic data signal indicative of an acoustic signal generated by a cold spray system performing a process possessing a plurality of process attributes, and a computing device including an acoustic data signal processing module configured to receive the at least one time-dependent acoustic data signal, and transform the at least one time-dependent acoustic data signal to a frequency-domain spectrum, wherein each process attribute of the plurality of process attributes is associated with at least one respective frequency band, and a correlation module configured to determine a process attribute of the plurality of process attributes by identifying at least one characteristic of the frequency-domain spectrum.
Rolls-Royce North American Technologies, Inc. (USA)
Inventor
Lagow, Benjamin W.
Gold, Matthew R.
Blair, Taylor K.
Abstract
An example system includes at least one acoustic sensor configured to generate at least one time-dependent acoustic data signal indicative of an acoustic signal generated by a system performing a fluid transport process possessing a plurality of process attributes. The fluid transport process may include a flow of a fluid along at least one path. The system may further include a computing device including an acoustic data signal processing module configured to receive the at least one time-dependent acoustic data signal, and transform the at least one time-dependent acoustic data signal to a frequency-domain spectrum. Each process attribute of the plurality of process attributes may be associated with at least one respective frequency band. The computing device may include a correlation module configured to determine a process attribute of the plurality of process attributes by identifying at least one characteristic of the frequency-domain spectrum.
Rolls-Royce North American Technologies, Inc. (USA)
Inventor
Blair, Taylor K.
Nelson, Scott
Lagow, Benjamin W.
Gold, Matthew R.
Abstract
An example system includes at least one acoustic sensor configured to generate at least one time-dependent acoustic data signal indicative of an acoustic signal generated by an additive manufacturing system performing a process possessing a plurality of process attributes. The process includes depositing material by interaction of an energy beam and a material stream on a build target to form a structure. The system includes a computing device including an acoustic data signal processing module configured to receive the at least one time-dependent acoustic data signal, and transform the at least one time-dependent acoustic data signal to a frequency-domain spectrum. Each process attribute of the plurality of process attributes may be associated with at least one respective frequency band. The computing device may further include a correlation module configured to determine a process attribute of the plurality of process attributes by identifying at least one characteristic of the frequency-domain spectrum.
Rolls-Royce North American Technologies, Inc. (USA)
Inventor
Blair, Taylor K.
Nelson, Scott
Lagow, Benjamin W.
Gold, Matthew R.
Abstract
An example system includes at least one acoustic sensor configured to generate at least one time-dependent acoustic data signal indicative of an acoustic signal generated by a system performing a powder transport process possessing a plurality of process attributes. The powder transport process may include a flow of a powder stream along at least one path. The system may further include a computing device including an acoustic data signal processing module configured to receive the at least one time-dependent acoustic data signal, and transform the at least one time-dependent acoustic data signal to a frequency-domain spectrum. Each process attribute of the plurality of process attributes may be associated with at least one respective frequency band. The computing device may include a correlation module configured to determine a process attribute of the plurality of process attributes by identifying at least one characteristic of the frequency-domain spectrum.
Rolls-Royce North American Technologies, Inc. (USA)
Inventor
Lagow, Benjamin W.
Gold, Matthew R.
Blair, Taylor K.
Nelson, Scott
Abstract
An example system includes at least one acoustic sensor configured to generate at least one time-dependent acoustic data signal indicative of an acoustic signal generated by an engine performing a process possessing a plurality of process attributes, and a computing device including an acoustic data signal processing module configured to receive the at least one time-dependent acoustic data signal, and transform the at least one time-dependent acoustic data signal to a frequency-domain spectrum, wherein each process attribute of the plurality of process attributes is associated with at least one respective frequency band, and a correlation module configured to determine a process attribute of the plurality of process attributes by identifying at least one characteristic of the frequency-domain spectrum.
Rolls-Royce North American Technologies, Inc. (USA)
Inventor
Nelson, Scott
Lagow, Benjamin W.
Gold, Matthew R.
Blair, Taylor K.
Abstract
An example system includes at least one acoustic sensor configured to generate at least one time-dependent acoustic data signal indicative of an acoustic signal generated by an nuclear power plant performing a process possessing a plurality of process attributes, and a computing device including an acoustic data signal processing module configured to receive the at least one time-dependent acoustic data signal, and transform the at least one time-dependent acoustic data signal to a frequency-domain spectrum, wherein each process attribute of the plurality of process attributes is associated with at least one respective frequency band, and a correlation module configured to determine a process attribute of the plurality of process attributes by identifying at least one characteristic of the frequency-domain spectrum.
G01N 29/14 - Investigating or analysing materials by the use of ultrasonic, sonic or infrasonic wavesVisualisation of the interior of objects by transmitting ultrasonic or sonic waves through the object using acoustic emission techniques
G01N 29/34 - Generating the ultrasonic, sonic or infrasonic waves
G01N 29/44 - Processing the detected response signal
G01N 29/46 - Processing the detected response signal by spectral analysis, e.g. Fourier analysis
45.
Turbine shroud assemblies with channels for buffer cavity seal thermal management
A turbine shroud assembly adapted for use with a gas turbine engine includes a carrier segment, a blade track segment, and a seal system. The carrier segment arranged circumferentially at least partway around an axis. The blade track segment is coupled to the carrier segment and defines a portion of a gas path of the gas turbine engine. The seal system includes seals arranged radially between the carrier segment and the blade track segment to block gases from flowing between the carrier segment and the blade track segment.
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 11/00 - Preventing or minimising internal leakage of working fluid, e.g. between stages
F01D 11/04 - Preventing or minimising internal leakage of working fluid, e.g. between stages by non-contact sealings, e.g. of labyrinth type using sealing fluid, e.g. steam
46.
TURBINE-POWERED SYSTEM WITH THERMOELECTRIC COOLING
Rolls-Royce North American Technologies Inc. (USA)
Inventor
Rivers, Jonathan M.
Heeter, Robert W.
Molnar, Jr., Daniel E.
Abstract
The present disclosure teaches a turbine-powered system with a thermoelectric cooler configured to selectively cool powered electronics in the system. In examples provided, the thermoelectric cooler including a cooling plate coupled to the powered electronics and a heat sink integrated into aero surfaces of a gas turbine engine.
An assembly adapted for use in a gas turbine engine includes a blade track segment, a carrier segment, and a retainer. The blade track segment defines a portion of a gas path of the gas turbine engine. The carrier segment supports the blade track segment to locate the blade track segment radially outward of the axis. The retainer couples the blade track segment to the carrier segment. The carrier segment may include a plurality of impingement passageways to conduct cooling air to the blade track segment.
A turbine assembly adapted for use with a gas turbine engine includes a turbine shroud assembly and a turbine vane. The turbine shroud assembly includes a blade track segment arranged circumferentially at least partway around an axis of the gas turbine engine, a carrier segment arranged circumferentially at least partway around the axis, and a mount assembly configured to couple the blade track segment to the carrier segment. The turbine vane is located axially aft of the turbine shroud assembly and helps retain the mount assembly in place.
Rolls-Royce High Temperature Composites Inc. (USA)
Inventor
Thomas, David J.
Downie, Christopher
Sippel, Aaron D.
Freeman, Ted J.
Snyder, Clark
Abstract
A turbine shroud assembly adapted for use with a gas turbine engine includes a shroud segment. The shroud segment includes a heat shield, an attachment flange, and a multi-layer coating. The heat shield extends circumferentially partway around the axis to define a portion of gas path for the gas turbine engine. The attachment feature extends radially outward from the heat shield. The multi-layer coating is applied to different surfaces of the heat shield and the attachment feature of the shroud segment.
F01D 25/24 - CasingsCasing parts, e.g. diaphragms, casing fastenings
F01D 5/28 - Selecting particular materialsMeasures against erosion or corrosion
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 25/00 - Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
50.
Adjustable position impeller shroud for centrifugal compressors
A compressor assembly for a gas turbine engine includes a shroud assembly, an outer case assembly, and a plurality of locating bolt assemblies. The shroud assembly extends circumferentially around the engine axis. The outer case assembly includes an outer case that extends circumferentially around the axis and a plurality of fasteners that couple the shroud assembly with the outer case. The plurality of locating bolt assemblies extend into the outer case and abut the shroud assembly at a predetermined axial location to axially locate the shroud assembly.
F04D 29/42 - CasingsConnections for working fluid for radial or helico-centrifugal pumps
F01D 11/16 - Adjusting or regulating tip-clearance, i.e. distance between rotor-blade tips and stator casing by self-adjusting means
F01D 11/22 - Actively adjusting tip-clearance by mechanically actuating the stator or rotor components, e.g. moving shroud sections relative to the rotor
F01D 17/12 - Final actuators arranged in stator parts
F04D 29/46 - Fluid-guiding means, e.g. diffusers adjustable
A compressor assembly for a gas turbine engine comprising an outer case, a shroud arranged circumferentially around the axis to direct compressed air through an impeller, and an actuator coupled with the outer case and the shroud to vary the position of the shroud axially relative to the outer case. The actuator includes a mount arm, an actuator body, and a travel stop. The mount arm is coupled with the outer case. The actuator body is coupled with the mount arm and the shroud to control axial movement of the shroud relative to the outer case. The travel stop is coupled to the mount arm and extends away from the mound arm and is configured to limit a forward most axial position of the shroud relative to the outer case.
F01D 11/22 - Actively adjusting tip-clearance by mechanically actuating the stator or rotor components, e.g. moving shroud sections relative to the rotor
52.
Turbine shroud assemblies with rod seal and strip seals
A turbine shroud assembly includes a first shroud segment, a second shroud segment, and a plurality of seals. The first shroud segment includes a first carrier segment arranged circumferentially at least partway around a central axis and a first blade track segment supported by the first carrier segment. The second shroud segment is arranged circumferentially adjacent the first shroud segment about the central axis. The plurality of seals extend circumferentially into the first shroud segment and the second shroud segment to block gases from escaping the gas path radially between the first shroud segment and the second shroud segment.
A turbine assembly adapted for use with a gas turbine engine includes a turbine shroud assembly and a turbine vane. The turbine shroud assembly includes a carrier segment arranged circumferentially at least partway around an axis and a blade track segment supported by the carrier segment to locate the blade track segment radially outward of the axis. The turbine vane is located axially forward of the turbine shroud assembly and cooperates with the turbine shroud assembly to form a tortuous flow path therebetween.
A turbine assembly includes a turbine case, a vane assembly, and a locating plate. The vane assembly includes a first vane and an outer platform arranged on a radially outer end of the first vane, the outer platform including a first anti-rotation protrusion extending radially outwardly away from a radially outwardly-facing surface of the outer platform. The locating plate is radially outside of the vane assembly and includes a main wall and two anti-rotation extensions extending radially inwardly. The first anti-rotation protrusion of the vane assembly is arranged to engage with one of the anti-rotation extensions so as to block circumferential movement of the vane assembly relative to the locating plate.
Rolls-Royce North American Technologies Inc. (USA)
Rolls-Royce Corporation (USA)
Inventor
Heeter, Robert W.
Rivers, Jonathan M.
Molnar, Jr., Daniel E.
Abstract
A fan case assembly adapted for use with a gas turbine engine includes a fan casing and a bleed air flow control system. The fan casing includes an annular case and a fan track liner coupled with the annular case. The bleed air flow control system is configured to bleed selectively a portion of air flowing through a gas path of the fan case assembly for use as a cooling source in the fan case assembly.
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
F04D 29/52 - CasingsConnections for working fluid for axial pumps
F04D 29/58 - CoolingHeatingDiminishing heat transfer
56.
Adjustable fan track liner with groove array active fan tip treatment for distortion tolerance
Rolls-Royce North American Technologies Inc. (USA)
Rolls-Royce Corporation (USA)
Inventor
Molnar, Jr., Daniel E.
Heeter, Robert W.
Rivers, Jonathan M.
Abstract
A gas turbine engine includes a fan and a fan case assembly. The fan includes a fan rotor configured to rotate about an axis of the gas turbine engine and a plurality of fan blades coupled to the fan rotor for rotation therewith. The fan case assembly extends circumferentially around the plurality of fan blades radially outward of the plurality of the fan blades.
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 11/22 - Actively adjusting tip-clearance by mechanically actuating the stator or rotor components, e.g. moving shroud sections relative to the rotor
F04D 29/52 - CasingsConnections for working fluid for axial pumps
Computer implementations for managing contract data requirements list (CDRL) deliverables are disclosed. In some implementations, a controller identifies a CDRL deliverable associated with a program. The controller determines whether the CDRL deliverable is associated with a milestone of a plurality of milestones associated with the program and whether the CDRL is associated with a recurrence. In addition, the controller determines a delivery date for the CDRL deliverable based on whether the CDRL is associated with the milestone and whether the CDRL deliverable is associated with the recurrence. The controller displays, via a display, a CDRL deliverable name of the CDRL deliverable and at least one of: the delivery date, a delivery status corresponding to the delivery date, and a delivery evaluation corresponding to the delivery date.
Rolls-Royce North American Technologies Inc. (USA)
Rolls-Royce Corporation (USA)
Inventor
Lighty, Kerry J.
Acker, Jonathan P.
Kremer, Douglas J.
Mazur, Steven
Whitlock, Mark E.
Abstract
A bleed valve assembly includes a manifold coupled to a case of a compressor of a gas turbine engine to control a flow of bleed air exiting the compressor, a valve housing coupled with the manifold, a piston configured to move selectively relative to the valve housing and the manifold, and one or more shims located between the valve housing and the piston.
Rolls-Royce North American Technologies Inc. (USA)
Rolls-Royce Corporation (USA)
Inventor
Molnar, Jr., Daniel E.
Heeter, Robert W.
Rivers, Jonathan M.
Abstract
A gas turbine engine includes a fan and a fan case assembly. The fan includes a fan rotor configured to rotate about an axis of the gas turbine engine and a plurality of fan blades coupled to the fan rotor for rotation therewith. The fan case assembly extends circumferentially around the plurality of fan blades radially outward of the plurality of the fan blades.
F04D 29/68 - Combating cavitation, whirls, noise, vibration, or the likeBalancing by influencing boundary layers
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 17/12 - Final actuators arranged in stator parts
F04D 29/52 - CasingsConnections for working fluid for axial pumps
F01D 11/22 - Actively adjusting tip-clearance by mechanically actuating the stator or rotor components, e.g. moving shroud sections relative to the rotor
60.
Turbine shroud assemblies with inter-segment strip seal
A turbine shroud assembly comprising a first shroud segment, a second shroud segment, and a plurality of seals. The first shroud segment includes a first carrier segment and a first blade track segment having a first shroud wall that is formed to include a first recess that extends circumferentially into the first shroud wall. The second shroud segment includes a second carrier segment and a second blade track having a second shroud wall that is formed to include a second recess that extends circumferentially into the second shroud wall. The plurality of seals extend circumferentially into the first shroud segment and the second shroud segment to block gases from escaping the gas path radially between the first shroud segment and the second shroud segment.
An example machine-gear system that connects to a prime mover in which the prime mover may operate at a first rotational speed and the machine may operate at a different rotational speed. The gear system, of the machine-gear system, may be configured to connect the prime mover and the machine such that the prime mover operates at the first rotational speed and the machine may operate at the different speed. The gear system may be located within the housing of the machine, which may result in a more compact machine-gear system, than for other arrangements. In some examples, the gear system may include two or more stages. In some examples, the multiple stage gear systems may be configured to engage or disengage from one, or more, stages, which may result in a machine-gear system that operates at two or more different rotational speeds as the operational modes change.
Rolls-Royce North American Technologies, Inc. (USA)
Inventor
Hodgson, Benedict N.
Heeter, Robert W.
Smith, Alan W.
Baninajar, Hossein
Abstract
A stator housing assembly includes a stator housing and a stator sleeve. The stator sleeve including a combination of composite layers with different high strength fibers. The stator housing includes a first end section and a second end section that define a stator cavity configured to contain a pressurized cooling fluid. The stator sleeve defines a longitudinal axis and includes a plurality of layers of composite materials that include more than one high strength fiber material. High strength fibers may include carbon and glass fibers. Portions of the stator sleeve may have different combinations of high strength fiber materials and fiber orientations to optimize sleeve properties.
H02K 1/18 - Means for mounting or fastening magnetic stationary parts on to, or to, the stator structures
H02K 1/04 - Details of the magnetic circuit characterised by the material used for insulating the magnetic circuit or parts thereof
H02K 1/20 - Stationary parts of the magnetic circuit with channels or ducts for flow of cooling medium
H02K 7/18 - Structural association of electric generators with mechanical driving motors, e.g.with turbines
H02K 15/12 - Impregnating, moulding insulation, heating or drying of windings, stators, rotors or machines
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 power reduction system for an energy storage system of an aircraft includes a controller configured to control power reduction of power supplied from the energy storage system to an aircraft engine supply bus; and an override switch configurable in an override state and a non-override state. The override switch is configured to: in the non-override state, permit the controller to control the power reduction according to a default configuration comprising one or more parameters that trigger the power reduction; and in the override state, control the power reduction to be performed according to a relaxed configuration that at least one of relaxes and omits the one or more parameters in the default configuration.
B64D 31/00 - Power plant control systemsArrangement of power plant control systems in aircraft
B60L 58/10 - Methods or circuit arrangements for monitoring or controlling batteries or fuel cells, specially adapted for electric vehicles for monitoring or controlling batteries
B64D 27/24 - Aircraft characterised by the type or position of power plants using steam or spring force
64.
METHOD OF MANUFACTURING A COMPONENT TO REDUCE RISK OF COLD DWELL FATIGUE FAILURE
A method of manufacturing a component including a metal alloy comprises measuring crystallographic texture of a volume of a component, determining a risk factor of the component for cold dwell fatigue failure, and adjusting metallurgical processing of the component based on the risk factor. Such risk analysis and mitigation may aid in improving the usage and operation of components including materials that are susceptible to cold dwell fatigue failure.
A turbine assembly includes a turbine case, a turbine shroud assembly including a carrier segment, and a locating plate. The locating plate is coupled with the turbine case axially forward of the carrier segment to block axially forward movement of the carrier segment and prevent separation of the carrier segment from the turbine case. The locating plate includes a main wall, a raised portion extending upwardly a first radial distance, and two circumferentially spaced apart extensions extending upwardly a second radial distance. The second radial distance is greater than the first radial distance such that, in a first arrangement, only the extensions contact the turbine case and such that, in a second arrangement, the raised portion is pulled toward the turbine case via a fastener so as to contact the turbine case in addition to the extensions.
An article includes a silicon-containing ceramic substrate and a coating system overlying the silicon-containing ceramic substrate. The coating system includes an intermediate coating overlying the silicon-containing ceramic substrate and a barrier coating overlying the intermediate coating. The intermediate coating includes silicon and hafnium disilicide. A coefficient of thermal expansion of the intermediate coat is less than about 7 parts per million (ppm) per degree Kelvin (K).
Rolls-Royce North American Technologies, Inc. (USA)
Inventor
Lee, Andrew
Desai, Mihir
Kalyanasamy, Govindaraj
Collett, Mark
Abstract
A method of monitoring a fuel system in a gas turbine engine. The method may comprise pumping fuel to a combustor from a fuel tank with a pump. The method may comprise controlling a flow of the fuel to the combustor with a metering valve disposed downstream of the pump and closing a spill valve disposed downstream of the pump, wherein the spill valve is closed in fixed increments and closing the spill valve increases a pressure in the fuel system. The method may comprise opening a pressure valve in response to the pressure in the fuel system being equal to or greater than a predetermined value, and capturing a degree of closing of the spill valve when the pressure valve opens.
Rolls-Royce North American Technologies, Inc. (USA)
Rolls-Royce Corporation (USA)
Inventor
Kalyanasamy, Govindaraj
Desai, Mihir
Lee, Andrew
Collett, Mark
Abstract
A method of mitigating uncommanded or uncontrollable high thrust in a gas turbine engine is provided. The method may comprise pumping fuel to a combustor from a fuel tank, controlling a flow rate of the fuel to the combustor with a metering valve, spilling a portion of the fuel pumped by the pump with a primary spill valve, controlling a pressure of the fuel flowing to the combustor via a pressure valve, detecting a pressure differential across the pressure valve with a pressure transducer, determining the flow rate of the fuel based on the detected pressure differential and the positional feedback of the pressure valve opening, comparing the determined flow rate with a demand flow rate, and opening a secondary spill valve when the determined flow rate exceeds the demand flow rate.
Rolls-Royce North American Technologies Inc. (USA)
Rolls-Royce Corporation (USA)
Inventor
Oechsle, Victor L.
Pesyna, Kenneth M.
Lerg, Bryan H.
Monzella, Michael C.
Rauch, Zachary A.
Moser, Michael
Abstract
A gas turbine engine includes a bypass duct, a rotating detonation augmentor, and a flow valve. The bypass duct is configured to conduct air through a flow path arranged around an engine core of the gas turbine engine. The rotating detonation augmentor is located in the bypass duct and configured to be selectively operated to detonate fuel and a portion of the air to increase thrust for propelling the gas turbine engine. The flow valve is configured to vary selectively the portion of the air flowing into the rotating detonation augmentor to control a magnitude of the thrust increase provided by the rotating detonation augmentor during operation of the rotating detonation augmentor.
F02K 3/02 - 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
70.
Turbine shroud system with ceramic matrix composite segments and dual inter-segment seals
A turbine shroud assembly includes a first shroud segment, a second shroud segment, and a plurality of seals. The first shroud segment includes a first carrier segment and a first blade track segment having a first shroud wall. The second shroud segment includes a second carrier segment and a second blade track. The plurality of seals extend circumferentially into the first shroud segment and the second shroud segment to block gases from escaping the gas path radially between the first shroud segment and the second shroud segment.
Rolls-Royce North American Technologies Inc. (USA)
Inventor
Costello, John
Dalley, Robert C.
Schetzel, Douglas
Abstract
A method of monitoring a health of a temperature system may comprise selecting a temperature sensor of a plurality of temperature sensors arranged in an array, where each temperature sensor corresponds to an address within the array. The method may comprise identifying the address corresponding to the single temperature sensor, sending the address to a multiplexer, and selecting the single temperature sensor using the identified address. The method may comprise testing the selected single temperature sensor calculating an average temperature detected by the plurality of temperatures sensors.
G01J 5/90 - Testing, inspecting or checking operation of radiation pyrometers
F01D 21/00 - Shutting-down of machines or engines, e.g. in emergencyRegulating, controlling, or safety means not otherwise provided for
F01D 21/12 - Shutting-down of machines or engines, e.g. in emergencyRegulating, controlling, or safety means not otherwise provided for responsive to temperature
G01J 5/00 - Radiation pyrometry, e.g. infrared or optical thermometry
Rolls-Royce North American Technologies Inc. (USA)
Inventor
Costello, John
Dalley, Robert C.
Schetzel, Douglas
Abstract
A system for detecting a failure in a thermocouple array may comprise the thermocouple array. The thermocouple array may comprise a plurality of thermocouples. The system may comprise an impedance determination circuit. The impedance determination circuit may include a capacitor that has a capacitance equal to an expected capacitance of one of the plurality of thermocouples. The one of the plurality of thermocouples may be connected to test nodes of the impedance determination circuit. The system may comprise a comparator circuit connected to the impedance determination circuit, where the comparator circuit includes an amplifier and a comparator. The system may comprise an excitation circuit connected to the impedance determination circuit, where the excitation circuit includes a waveform generator and an amplifier.
G01K 15/00 - Testing or calibrating of thermometers
G01K 7/02 - Measuring temperature based on the use of electric or magnetic elements directly sensitive to heat using thermoelectric elements, e.g. thermocouples
73.
Turbine shroud assembly with inter-segment damping
A turbine shroud assembly includes a first shroud segment, a second shroud segment, and a seal assembly. The first shroud segment includes a first carrier segment arranged circumferentially at least partway around a central axis and a first blade track segment supported by the first carrier segment. The second shroud segment is arranged circumferentially adjacent the first shroud segment about the central axis. The seal assembly is configured to block gases from escaping the gas path radially between the first shroud segment and the second shroud segment.
Rolls-Royce North American Technologies Inc. (USA)
Rolls-Royce Corporation (USA)
Inventor
Molnar, Jr., Daniel E.
Heeter, Robert W.
Rivers, Jonathan M.
Abstract
A gas turbine engine includes a fan and a fan case assembly. The fan includes a fan rotor configured to rotate about an axis of the gas turbine engine and a plurality of fan blades coupled to the fan rotor for rotation therewith. The fan case assembly extends circumferentially around the plurality of fan blades radially outward of the plurality of the fan blades.
Rolls-Royce North American Technologies, Inc. (USA)
Inventor
Schenk, Peter
Hill, Mathew
Harral, Jacob Ward
Kabbes, Michael Joseph
Abstract
A system includes a gas turbine engine configured to provide propulsion to an aircraft and a starter system configured to start the gas turbine engine. The starter system comprises a motor controller and a closed-loop cooling system configured to cool the motor controller during an emergency in-flight restart operation of the gas turbine engine. The closed-loop cooling system includes a cooling fluid reservoir containing cooling fluid. The cooling fluid is configured to receive thermal energy from the motor controller during the emergency in-flight restart operation of the gas turbine engine.
An example system includes a first gas-turbine engine (GTE) of a plurality of GTEs that are configured to propel an aircraft, the first GTE comprising: a first electric starter of a plurality of electric starters, the first electric starter configured to rotate a spool of the first GTE, wherein the first electric starter is rotationally connected to the spool of the first GTE without a clutch; a second GTE of the plurality of GTEs, the second GTE comprising: a second electric starter of the plurality of electric starters, the second electric starter configured to rotate a spool of the second GTE, wherein the second electric starter is rotationally connected to the spool of the second GTE without a clutch; one or more controllers configured to control the plurality of GTEs; and a common electric starter controller configured to control the plurality of electric starters.
An example system includes a first gas-turbine engine (GTE) of a plurality of GTEs that are configured to propel an aircraft, the first GTE comprising: a first air-turbine starter (ATS) of a plurality of ATSs, the first ATS configured to rotate a spool of the first GTE; and a first electric starter of a plurality of electric starters, the first electric starter configured to rotate the spool of the first GTE; a second GTE of the plurality of GTEs, the second gas-turbine engine comprising: a second ATS of the plurality of ATSs, the second ATS configured to rotate a spool of the GTE; and a second electric starter of the plurality of electric starters, the second electric starter configured to rotate the spool of the GTE; and one or more controllers configured to control the plurality of GTEs.
Rolls-Royce North American Technologies, Inc. (USA)
Inventor
Lawrence, Jeffrey
Schenk, Peter
Harral, Jacob Ward
Huber, Brian Joseph
Abstract
An example system includes a first gas-turbine engine configured to propel an aircraft, the first gas-turbine engine comprising: a first air-turbine starter, the first air-turbine starter configured to rotate a spool of the first gas-turbine engine; and a first electric starter, the first electric starter configured to rotate the spool of the first gas-turbine engine; and one or more controllers collectively configured to: cause, during a time period, the first-air turbine starter and the first electric starter to start the first gas-turbine engine while the aircraft is on the ground; measure, during the time period, values of one or more parameters of the first gas-turbine engine; and determine, based on the values of the one or more parameters, whether the first electric starter is available for use in performing mid-air restart of the first gas-turbine engine.
An example system includes a plurality of transient voltage suppressors (TVSs) that are connected in series across an electrical bus of an aircraft, the electrical bus having a high side and a low side; a plurality of switches, each switch of the plurality of switches configured to selectively shunt a corresponding TVS of the plurality of TVSs to the low side of the electrical bus; and a controller configured to: determine a desired voltage suppression level; and control operation of the plurality of switches such that the plurality of TVSs provides the desired voltage suppression level.
Rolls-Royce North American Technologies, Inc. (USA)
Rolls-Royce Corporation (USA)
Inventor
Badger, Bradon
Steffen, Philip J.
Schenk, Peter
Abstract
A starting apparatus for a gas turbine engine of a plurality of gas turbine engines of an aircraft. The apparatus includes a fuel supply system, a combustor, and a controller. The controller is configured to cause fuel to be introduced to the combustor of the gas turbine engine at a first threshold rotational speed of the gas-turbine engine during a normal starting operation in which the aircraft is on the ground. The controller is configured to cause fuel to be introduced to the combustor at a second threshold rotational speed of the gas-turbine engine during an emergency in-flight restarting operation in which the aircraft is in-flight. The second threshold rotational speed is lower than the first threshold rotational speed. Introducing fuel at the second threshold rotational speed results in a higher temperature in a turbine of the gas turbine engine than introducing fuel at the first threshold rotational speed.
Rolls-Royce North American Technologies, Inc. (USA)
Inventor
Lawrence, Jeffrey
Schenk, Peter
Schetzel, Ii, Douglas Keith
Harral, Jacob Ward
Huber, Brian Joseph
Abstract
A starting apparatus for a first gas turbine engine of a plurality of gas turbine engines of an aircraft. The apparatus includes an air turbine starter, an electric machine, and a controller. The controller is configured to receive an emergency restart command for the first gas turbine engine while the aircraft is in-flight, determine whether the first gas turbine engine is in operation, determine whether at least a second gas turbine engine of the plurality of gas turbine engines is in operation, and, responsive to receiving the emergency restart command and determining that at least the second gas turbine engine of the plurality of gas turbine engines is in operation and that the first gas turbine engine is not in operation, perform an emergency restart of the first gas turbine engine.
A hands-free smoking device is disclosed, which is a marijuana, cigarette, and/or cigar holder for use while gaming and other tasks device. The device is worn over the head like a headset and allows the user to smoke hands free. The hands-free smoking device comprises a headset component with a flexible arm component. The flexible arm component retains a smoking implement holder. The smoking implement holder is available in multiple shapes and sizes to hold any size cigarette, blunt, cigar, etc. The flexible arm component is bendable and can be bent in any position near a user's mouth or in any direction needed. Further, the headset component can comprise a cushioning component positioned near a user's head or neck when worn. Thus, the device enables users to maintain a comfortable and hands-free position while smoking.
Rolls-Royce North American Technologies Inc. (USA)
Rolls-Royce Corporation (USA)
Inventor
Molnar, Jr., Daniel E.
Heeter, Robert W.
Rivers, Jonathan M.
Abstract
A gas turbine engine includes a fan and a fan case assembly. The fan includes a fan rotor configured to rotate about an axis of the gas turbine engine and a plurality of fan blades coupled to the fan rotor for rotation therewith. The fan case assembly extends circumferentially around the plurality of fan blades radially outward of the plurality of the fan blades.
Rolls-Royce North American Technologies Inc. (USA)
Rolls-Royce Corporation (USA)
Inventor
Heeter, Robert W.
Molnar, Jr., Daniel E.
Rivers, Jonathan M.
Abstract
A gas turbine engine includes a fan and a fan case assembly. The fan includes a fan rotor configured to rotate about an axis of the gas turbine engine and a plurality of fan blades coupled to the fan rotor for rotation therewith. The fan case assembly extends circumferentially around the plurality of fan blades radially outward of the plurality of the fan blades.
F04D 29/68 - Combating cavitation, whirls, noise, vibration, or the likeBalancing by influencing boundary layers
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 11/22 - Actively adjusting tip-clearance by mechanically actuating the stator or rotor components, e.g. moving shroud sections relative to the rotor
F04D 29/52 - CasingsConnections for working fluid for axial pumps
85.
Method and apparatus for ceramic matrix composite turbine shroud assembly
Rolls-Royce High Temperature Composites Inc. (USA)
Inventor
Thomas, David J.
Downie, Christopher
Sippel, Aaron D.
Freeman, Ted J.
Snyder, Clark
Abstract
A turbine shroud assembly adapted for use with a gas turbine engine includes a shroud segment. The shroud segment includes a heat shield, an attachment flange, and a multi-layer coating. The heat shield extends circumferentially partway around the axis to define a portion of gas path for the gas turbine engine. The attachment feature extends radially outward from the heat shield. The multi-layer coating is applied to different surfaces of the heat shield and the attachment feature of the shroud segment.
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 25/00 - Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
F01D 25/24 - CasingsCasing parts, e.g. diaphragms, casing fastenings
F01D 5/28 - Selecting particular materialsMeasures against erosion or corrosion
86.
Electric starter verification during gas-turbine engine barring
Rolls-Royce North American Technologies, Inc. (USA)
Inventor
Lawrence, Jeffrey
Huber, Brian Joseph
Munevar, Erik A.
Schetzel, Ii, Douglas Keith
Abstract
An example system includes a first gas-turbine engine configured to propel an aircraft, the first gas-turbine engine comprising a first electric starter, the first electric starter configured to rotate a spool of the first gas-turbine engine; and one or more controllers collectively configured to: cause, following operation of the first gas-turbine engine, the first electric starter to perform barring of the first gas-turbine engine; measure, during the barring of the first gas-turbine engine, values of one or more parameters of the first gas-turbine engine; and determine, based on the values of the one or more parameters, whether the first electric starter is available for use in performing mid-air restart of the first gas-turbine engine.
A ceramic matrix composite (CMC) component is provided that includes: a CMC body in which an environmental protection layer is completely embedded within a CMC material of the CMC body, the environmental protection layer comprising a ceramic that has a higher impact and/or environmental resistance than the CMC material. Methods for manufacturing the CMC component are also provided.
B32B 3/08 - 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 features of form at particular places, e.g. in edge regions characterised by added members at particular parts
B32B 5/06 - Layered products characterised by the non-homogeneity or physical structure of a layer characterised by structural features of a layer comprising fibres or filaments characterised by a fibrous layer needled to another layer, e.g. of fibres, of paper
Rolls-Royce North American Technologies Inc. (USA)
Rolls-Royce Corporation (USA)
Inventor
Heeter, Robert W.
Molnar, Jr., Daniel E.
Rivers, Jonathan M.
Abstract
A gas turbine engine includes a fan and a fan case assembly. The fan includes a fan rotor configured to rotate about an axis of the gas turbine engine and a plurality of fan blades coupled to the fan rotor for rotation therewith. The fan case assembly extends circumferentially around the plurality of fan blades radially outward of the plurality of the fan blades.
F04D 29/52 - CasingsConnections for working fluid for axial pumps
F01D 11/22 - Actively adjusting tip-clearance by mechanically actuating the stator or rotor components, e.g. moving shroud sections relative to the rotor
A turbine shroud assembly includes a first shroud segment, a second shroud segment, and a damping strip seal. The first shroud segment has a first carrier segment arranged circumferentially at least partway around a central axis and a first blade track segment supported by the first carrier segment. The second shroud segment is arranged circumferentially adjacent the first shroud segment about the central axis. The damping strip seal extends circumferentially into the first shroud segment and the second shroud segment to block gases from passing between the first shroud segment and the second shroud segment.
A turbine shroud assembly for use with a gas turbine engine includes a first shroud segment, a second shroud segment, and a damping strip seal assembly. The first shroud segment has a first carrier segment arranged circumferentially at least partway around a central axis and a first blade track segment supported by the first carrier segment. The second shroud segment is arranged circumferentially adjacent the first shroud segment. The damping strip seal assembly includes an axial seal member, a forward seal, and an aft seal member.
An example electrical machine is described that includes active segments for variable voltage generation. The electrical machine includes a drive shaft, a fixed rotor segment, an active rotor segment, and an actuator mechanism. The fixed rotor segment is coupled to the drive shaft, where the fixed rotor segment has affixed thereon first permanent magnets of alternating polarity. The active rotor segment axially is adjacent to the fixed rotor segment along the drive shaft. The active rotor segment also has affixed thereon second permanent magnets of alternating polarity. The actuator mechanism is configured to articulate the active rotor segment relative to the fixed rotor segment and thereby alter a phase of the second permanent magnets relative to the first permanent magnets in order to change a first voltage generated by the electrical machine to a second voltage generated by the electrical machine.
H02K 21/16 - Synchronous motors having permanent magnetsSynchronous generators having permanent magnets with stationary armatures and rotating magnets with magnets rotating within the armatures having annular armature cores with salient poles
H02K 1/2789 - Outer rotors the magnetisation axis of the magnets being perpendicular to the rotor axis the rotor consisting of two or more circumferentially positioned magnets
H02K 7/12 - Structural association with clutches, brakes, gears, pulleys or mechanical starters with auxiliary limited movement of stators, rotors or core parts, e.g. rotors axially movable for the purpose of clutching or braking
H02K 7/18 - Structural association of electric generators with mechanical driving motors, e.g.with turbines
H02K 7/20 - Structural association with auxiliary dynamo-electric machines, e.g. with electric starter motors or exciters
92.
Rotor with magnet retention band for use with electric machines
Rolls-Royce North American Technologies Inc. (USA)
Inventor
Hill, Mathew
Schenk, Peter
Coffee, Jeffrey
Abstract
A rotor assembly for an electric machine includes a rotor segment configured to rotate about an axis and having a rotor body, a side wall and an outer band that cooperate to form a cavity, a plurality of magnets located in the cavity, and an end plate configured to block the plurality of magnets within the cavity.
A turbine vane assembly includes a flow path ring, an airfoil heat shield, and a seal. The flow path ring is made of ceramic matrix composite materials. The airfoil heat shield is made of ceramic matrix composite materials. The seal resists passage of gases through a gap formed between the flow path ring and the airfoil heat shield along an interface at the airfoil aperture.
A method of assembling a wire harness adapted for use with a piece of electrical equipment includes several steps. The wire harness includes a plurality of wires, a plurality of connector pins, and an electrical connector. The electrical connector is configured to be coupled to the piece of electrical equipment.
Rolls-Royce North American Technologies, Inc. (USA)
Rolls-Royce Corporation (USA)
Inventor
Kalyanasamy, Govindaraj
Schenk, Peter
Abstract
An example system includes a thermal energy system configured to transport thermal energy harvested from a first portion of a gas turbine engine to a second portion of the gas turbine engine after the gas turbine engine was in operation, wherein the transported thermal energy minimizes or prevents undesired contact or seizing of a rotor with another component of the gas turbine engine due to warping of the rotor due to uneven cooling of the gas turbine engine after the operation. The thermal energy system includes a cavity configured to flow a fluid, wherein the fluid is configured to transport thermal energy from the first portion to the second portion.
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
96.
Thermal energy system to minimize or eliminate rotor bow
Rolls-Royce North American Technologies, Inc. (USA)
Rolls-Royce Corporation (USA)
Inventor
Kalyanasamy, Govindaraj
Schenk, Peter
Abstract
An example system includes one or more heaters configured and positioned to add thermal energy to one or more portions of a gas turbine engine after the gas turbine engine was in operation, wherein the thermal energy minimizes or prevents undesired contact or seizing of a rotor of the gas turbine engine with another component of the gas turbine engine due to warping of the rotor due to uneven cooling of the gas turbine engine after the operation. The system further includes a controller configured to control operation of the one or more heaters.
F01D 25/10 - Heating, e.g. warming-up before starting
F01D 5/18 - Hollow bladesHeating, heat-insulating, or cooling means on blades
F01D 19/02 - Starting of machines or enginesRegulating, controlling, or safety means in connection therewith dependent on temperature of component parts, e.g. of turbine casing
In one example, a method for forming an environmental barrier coating (EBC), thermal barrier coating (TBC), and/or abradable coating on a substrate. The method may include depositing a coating on a substrate to form an as-deposited coating, wherein the coating includes at least one of a TBC layer, an EBC layer, or an abradable coating layer; and heat treating the as-deposited coating at or above a first temperature for a first period of time following the deposition of the as-deposited coating on the substrate, wherein heat treating the as-deposited coating includes heating the as-deposited coating to or above the first temperature at a controlled heating rate, and wherein the controlled heating rate is selected such that the heat treated coating exhibits a compressive residual stress state upon cooling.
Rolls-Royce North American Technologies, Inc. (USA)
Rolls-Royce Corporation (USA)
Inventor
Gold, Matthew R.
Glucklich, Andrew
Abstract
In some examples, a method of forming an article for a gas turbine engine, the method comprising depositing a powder to form a protective coating on a leading edge of an airfoil substrate. The deposited powder includes carbide particles in a metal matrix and the carbide particles in the powder have an average particle size of about 1 micron or less. The protective coating on the leading edge of the airfoil substrate includes the carbide particles in the metal matrix.
A turbine section of a gas turbine engine includes a case, a plurality of flow path components, and a mounting system. The case extends circumferentially around a central axis of the gas turbine engine. The plurality of flow path components includes a turbine vane, a turbine blade, and a flow path ring. The mounting system is configured to couple the flow path ring to the case.
An example system includes a common electric starter controller configured to control electric starters of a plurality of gas-turbine engines that are configured to propel an aircraft, wherein the common electric starter comprises: a driver configured to generate, using electrical energy sourced from a battery of the aircraft, power signals that control the electric starters; and a plurality of bus bars configured to directly connect the common electric starter controller to the battery and transport the electrical energy from the battery to the common electric starter controller.
