Raytheon Technologies Corporation patent applications on September 19th, 2024
Patent Applications by Raytheon Technologies Corporation on September 19th, 2024
Raytheon Technologies Corporation: 23 patent applications
Raytheon Technologies Corporation has applied for patents in the areas of F02C3/30 (6), F01D5/18 (2), C04B35/628 (2), C04B35/80 (2), B22F10/34 (1) F02C3/30 (5), C04B35/80 (2), F01D5/18 (2), F02C7/141 (1), G02B6/50 (1)
With keywords such as: steam, combustor, turbine, fuel, chamber, assembly, injector, cavity, combustion, and end in patent application abstracts.
Patent Applications by Raytheon Technologies Corporation
Inventor(s): Henry H. Thayer of Wethersfield CT (US) for raytheon technologies corporation, Lawrence A. Binek of Glastonbury CT (US) for raytheon technologies corporation
IPC Code(s): B22F10/34, B22F12/58
CPC Code(s): B22F10/34
Abstract: a process for forming an overhang feature without downward facing surface defects in the overhang feature on a part; the process includes laying down a first layer with a first powder material on a build plate; fusing the first powder material with a first power laser beam; laying down a second layer on top of the first layer, the second layer comprising a second powder material having an additive which lowers the melting point temperature of the second powder material; forming an overhang feature from the second layer; and fusing the second powder material with a second power laser beam in the absence of forming the downward facing surface defects in the overhang feature of the part.
Inventor(s): Jeffrey L. Rosebaugh of Topeka KS (US) for raytheon technologies corporation, Stephen Kapp of Columbus GA (US) for raytheon technologies corporation
IPC Code(s): B23B25/00
CPC Code(s): B23B25/00
Abstract: a turning fixture including a fixture insert attached to the turning fixture, the fixture insert comprising an upper portion having an upper portion body, the upper portion body includes a central span with a first arm and second arm opposite the first arm, a cavity is defined between the first arm and the second arm along the central span on an inner side of the upper portion body; the fixture insert including a lower portion having a lower portion body that includes a chamber located centrally between a first end and a second end; and a rod is insertable through the lower portion through the chamber, the rod being configured to apply a force to a compressor spindle vane inserted between the upper portion and the lower portion.
Inventor(s): Zhigang Wang of South Windsor CT (US) for raytheon technologies corporation, Andrzej E. Kuczek of Bristol CT (US) for raytheon technologies corporation, Robin H. Fernandez of East Haddam CT (US) for raytheon technologies corporation, John D. Riehl of Hebron CT (US) for raytheon technologies corporation, Alan C. Barron of Jupiter FL (US) for raytheon technologies corporation, Ahmed Abdillahi Abdi of Oceanside CA (US) for raytheon technologies corporation, Jason Nelson of Puyallup WA (US) for raytheon technologies corporation, Andrew Joseph Lazur of La Jolla CA (US) for raytheon technologies corporation
IPC Code(s): B24B1/04, B24B57/02, B25J9/00, B25J9/02, B25J9/16, B25J11/00
CPC Code(s): B24B1/04
Abstract: an ultrasonic impact grinding assembly includes a base with a mount for connecting a workpiece to the base and a first tool arm. the ultrasonic impact grinding assembly also includes a second tool arm. the first tool arm and the second tool arm each include a base end, a distal end, at least one joint between the base end and the distal end, and at least one actuator configured to move the at least one joint. a first ultrasonic impact grinding tool head is connected to the distal end of the first tool arm. a second ultrasonic impact grinding tool head is connected to the distal end of the second tool arm.
Inventor(s): Gregory Boardman of Owens Cross Roads AL (US) for raytheon technologies corporation, Stephen K. Kramer of Cromwell CT (US) for raytheon technologies corporation
IPC Code(s): B64D37/16, B64D37/06, B64D37/30, F02M37/00
CPC Code(s): B64D37/16
Abstract: during a method, an aircraft powerplant is provided. the aircraft powerplant includes an injector and a fuel system configured to deliver fuel to the injector. the fuel system includes a first tank, a first circuit and a second circuit arranged in parallel with the first circuit between the first tank and the injector. the second circuit includes a second tank. the fuel is directed from the first tank to the injector during a first mode through the first circuit and independent of the second circuit. the fuel is directed from the second tank to the injector during a second mode through the second circuit and independent of the first circuit.
Inventor(s): Brendan Lenz of Wethersfield CT (US) for raytheon technologies corporation, Molly Kole of Hartford CT (US) for raytheon technologies corporation
IPC Code(s): C04B35/80, C04B35/628, C04B35/64
CPC Code(s): C04B35/80
Abstract: a needle array suitable for perforating a fibrous preform includes a backplate, a plurality of needles removably attached to and extending away from the backplate, and a collar disposed around each of the plurality of needles. each of the plurality of needles includes a metallic body, and a polymer sheath covering the metallic body.
Inventor(s): Molly Kole of Hartford CT (US) for raytheon technologies corporation, Olivier H. Sudre of Glastonbury CT (US) for raytheon technologies corporation
IPC Code(s): C04B35/80, C04B35/628, C04B35/634, D04H18/02
CPC Code(s): C04B35/80
Abstract: a needle array suitable for perforating a fibrous preform includes a backplate and a plurality of needles individually removably attached to and extending away from the backplate. each of the plurality of needles includes a bundle of ceramic filaments, a metallic sheath surrounding a first end of the bundle abutting the backplate, and a sharpened point on the second end of the bundle, the second end being oppositely disposed from the first end.
Inventor(s): Brendan Lenz of Wethersfield CT (US) for raytheon technologies corporation, Olivier H. Sudre of Glastonbury CT (US) for raytheon technologies corporation
IPC Code(s): C04B41/53, C04B41/45, C04B41/50, D03D15/242, D03D25/00
CPC Code(s): C04B41/5392
Abstract: a method of forming a ceramic matrix composite includes three-dimensionally weaving a fibrous preform, the preform including a plurality of warp tows, a plurality of weft tows, and a plurality of z-fibers passing orthogonally between the plurality of warp and the plurality of weft tows. the method further includes debulking the preform, decomposing the plurality of z-fibers to form a respective plurality of z-channels in the preform, and densifying the preform with a ceramic matrix.
Inventor(s): David E. Bitter of Chester CT (US) for raytheon technologies corporation, William John Oldach of West Hartford CT (US) for raytheon technologies corporation, William C. Sheridan of East Haddam CT (US) for raytheon technologies corporation, Matthew Michael Massaro of Wilmington DE (US) for raytheon technologies corporation
IPC Code(s): F01D5/18
CPC Code(s): F01D5/18
Abstract: a hollow vane assembly including an open body including an interior; at least one cover support structure formed in said open body proximate the interior; a cover brazed to the open body to form at least one flow passage; and at least one surface feature on the cover.
Inventor(s): David E. Bitter of Chester CT (US) for raytheon technologies corporation, S. Bret Bonarrigo of Wallingford CT (US) for raytheon technologies corporation, William John Oldach of West Hartford CT (US) for raytheon technologies corporation, William C. Sheridan of East Haddam CT (US) for raytheon technologies corporation, Matthew Michael Massaro of Wilmington DE (US) for raytheon technologies corporation
IPC Code(s): F01D5/18
CPC Code(s): F01D5/18
Abstract: a hollow vane assembly including an open body including an interior; at least one cover support structure formed in said open body proximate the interior; a cover brazed to the open body to form at least one flow passage; and at least one ply formed in the cover.
Inventor(s): Bernard W. Pudvah of Portland CT (US) for raytheon technologies corporation
IPC Code(s): F01D25/14, F01D9/04, F01D25/12, F01D25/24
CPC Code(s): F01D25/14
Abstract: manufacturing a compressor case by casting a member having: forward and aft annular portions; a cavity forward wall extending from the forward annular portion to a first inner end; a cavity aft wall extending from the aft annular portion to a second inner end; a cavity outer wall extending between the forward and aft annular portions and defining an outer aperture; casting a cavity inner wall and welding the cavity inner wall between the cavity forward and aft walls such that the cavity inner wall is offset from the first and second inner ends of the cavity forward and aft walls to form a u-shaped end channel, the compressor case is capable of receiving a vane so that a trunnion bearing extends from a vane root to a trunnion bearing outer end, through the inner aperture in the cavity inner wall and the outer aperture in the cavity outer wall.
Inventor(s): Gregory Boardman of Owens Cross Roads AL (US) for raytheon technologies corporation
IPC Code(s): F02C3/30
CPC Code(s): F02C3/30
Abstract: an assembly is provided for a turbine engine. this assembly includes a combustor and an injection system. the combustor includes a combustion chamber. the injection system includes an injector. the injection system is configured to direct fluid and steam into the combustion chamber through the injector. the injection system is configured to modulate a flow of the fluid into the combustion chamber through the injector by regulating a flow of the steam into the combustion chamber through the injector.
Inventor(s): Gregory Boardman of Owens Cross Roads AL (US) for raytheon technologies corporation
IPC Code(s): F02C3/30
CPC Code(s): F02C3/30
Abstract: a method is provided for operating a turbine engine. during this method, fuel is injected into a combustion chamber of a combustor of the turbine engine. the combustion chamber extends circumferentially around a centerline. the fuel is combusted within the combustion chamber. steam is introduced into the combustion chamber in an asymmetric pattern around the centerline.
Inventor(s): Stephen K. Kramer of Cromwell CT (US) for raytheon technologies corporation, Lance L. Smith of West Hartford CT (US) for raytheon technologies corporation, Gregory Boardman of Owens Cross Roads AL (US) for raytheon technologies corporation, Zhongtao Dai of West Hartford CT (US) for raytheon technologies corporation
IPC Code(s): F02C3/30
CPC Code(s): F02C3/30
Abstract: an assembly is provided for a turbine engine. this assembly includes a housing, a combustor and a steam injector. the housing includes an air plenum. the combustor is disposed within the air plenum. the combustor includes a combustor wall and a combustion chamber. the combustor wall is disposed between the combustion chamber and the air plenum. the combustor wall includes a quench aperture that extends through the combustor wall from the air plenum to the combustion chamber. the steam injector projects partially into or through the quench aperture.
Inventor(s): Stephen K. Kramer of Cromwell CT (US) for raytheon technologies corporation, Zhongtao Dai of West Hartford CT (US) for raytheon technologies corporation, Lance L. Smith of West Hartford CT (US) for raytheon technologies corporation, Gregory Boardman of Owens Cross Roads AL (US) for raytheon technologies corporation
IPC Code(s): F02C3/30
CPC Code(s): F02C3/30
Abstract: an assembly is provided for a turbine engine. this assembly includes a housing, a combustor and a fuel injector assembly. the housing includes a case and a diffuser plenum radially within the case. the case extends axially along and circumferentially about a centerline. the combustor is disposed within the diffuser plenum. the combustor includes a bulkhead, a hood, a combustion chamber and a hood cavity. the bulkhead is axially between the combustion chamber and the hood cavity. the hood is between the hood cavity and the diffuser plenum. the fuel injector assembly projects radially into the diffuser plenum from the case. the fuel injector assembly includes a fuel nozzle and a steam nozzle. the fuel nozzle is configured to inject fuel into the combustion chamber. the steam nozzle is configured to inject steam into the hood cavity.
Inventor(s): Stephen K. Kramer of Cromwell CT (US) for raytheon technologies corporation, Lance L. Smith of West Hartford CT (US) for raytheon technologies corporation, Zhongtao Dai of West Hartford CT (US) for raytheon technologies corporation
IPC Code(s): F02C3/30
CPC Code(s): F02C3/30
Abstract: an aircraft propulsion system is provided that include a propulsor rotor, a turbine engine core and a steam system. the turbine engine core is configured to power the propulsor rotor. the turbine engine core includes a core flowpath, a compressor section, a combustor section and a turbine section. the core flowpath extends through the compressor section, the combustor section and the turbine section from a flowpath inlet to a flowpath exhaust. the combustor section includes a diffuser plenum and a combustor disposed within the diffuser plenum. the steam system is configured to introduce steam into the core flowpath upstream of the diffuser plenum.
Inventor(s): Stephen K. Kramer of Cromwell CT (US) for raytheon technologies corporation, Lance L. Smith of West Hartford CT (US) for raytheon technologies corporation, Zhongtao Dai of West Hartford CT (US) for raytheon technologies corporation, Gregory Boardman of Owens Cross Roads AL (US) for raytheon technologies corporation
IPC Code(s): F02C3/30, F23R3/10
CPC Code(s): F02C3/305
Abstract: an assembly is provided for a turbine engine. this assembly includes a housing, a combustor and a steam system. the housing includes an air plenum. the combustor is disposed within the air plenum. the combustor includes a combustion chamber and a combustor wall between the combustion chamber and the air plenum. the steam system includes a steam injector arranged within the air plenum next to the combustor wall. the steam system is configured to inject steam out of the steam injector and into the air plenum to impinge against the combustor wall.
Inventor(s): Stephen K. Kramer of Cromwell CT (US) for raytheon technologies corporation, Lance L. Smith of West Hartford CT (US) for raytheon technologies corporation, Gregory Boardman of Owens Cross Roads AL (US) for raytheon technologies corporation, Zhongtao Dai of West Hartford CT (US) for raytheon technologies corporation
IPC Code(s): F02C7/141, F02C7/16
CPC Code(s): F02C7/141
Abstract: an assembly is provided for a turbine engine. this assembly includes a turbine vane array and a cooling system. the turbine vane array includes an inner platform, an outer platform and a plurality of turbine vanes extending between and connected to the inner platform and the outer platform. the turbine vanes include a first turbine vane, and the first turbine vane includes a first passage and a second passage. the cooling system is configured to direct a first fluid into the first passage and a second fluid into the second passage. the first fluid includes air and steam during a first mode. the second fluid includes the air without the steam during the first mode.
Inventor(s): Gregory Boardman of Owens Cross Roads AL (US) for raytheon technologies corporation
IPC Code(s): F02C7/18, F02C9/18
CPC Code(s): F02C7/18
Abstract: a control method is provided during which a turbine engine is operated. the turbine engine includes a plurality of steam cooled zones along a flowpath within the turbine engine. steam is distributed between the steam cooled zones based on a first distribution while the turbine engine is operating in a first mode. the steam is distributed between the steam cooled zones based on a second distribution while the turbine engine is operating in a second mode. the second distribution is different than the first distribution.
Inventor(s): Hamidreza Mohseni of Avon CT (US) for raytheon technologies corporation, Lesley Dawag of West Hartford CT (US) for raytheon technologies corporation
IPC Code(s): F02C7/28, F16J15/324
CPC Code(s): F02C7/28
Abstract: a sealing system includes a shaft, a rotor configured to rotate with respect to the shaft, and a carbon-carbon composite seal ring arranged around the shaft such that it seals against the rotor. the carbon-carbon composite seal ring includes a monoaluminum phosphate binder layer disposed on at least one surface of the carbon-carbon composite seal ring and a ceramic layer disposed over the monoaluminum phosphate binder layer on the least one surface of the carbon-carbon composite seal ring. a method of manufacturing a seal is also disclosed.
Inventor(s): Lance L. Smith of West Hartford CT (US) for raytheon technologies corporation
IPC Code(s): F23L7/00, F23R3/30
CPC Code(s): F23L7/005
Abstract: an assembly is provided for a turbine engine. this assembly includes a combustor, a fuel injector nozzle and a fuel system. the combustor includes a combustion chamber. the fuel injector nozzle is configured to inject a fuel-steam mixture into the combustion chamber for combustion. the fuel system includes a fuel source, a steam source and a manifold. the manifold is configured to mix fuel received from the fuel source with steam received from the steam source to provide the fuel-steam mixture. the fuel system is configured to deliver the fuel-steam mixture to the fuel injector nozzle.
Inventor(s): Eli Warren of Wethersfield CT (US) for raytheon technologies corporation, Bryan J. Hackett of Berlin CT (US) for raytheon technologies corporation
IPC Code(s): G01M15/14
CPC Code(s): G01M15/14
Abstract: a measurement system is provided that includes a probe housing, a field probe and an optical probe. the probe housing includes a sidewall, a cavity and a channel. the sidewall extends circumferentially around and axially along the cavity. the channel is radially outboard of the cavity and extends axially in the sidewall. the field probe includes a field sensor disposed in the cavity. the field sensor forms a sensor face. the optical probe is configured with an optical line of sight through the channel into a volume adjacent the sensor face.
Inventor(s): Bryan J. Hackett of Berlin CT (US) for raytheon technologies corporation, Eli Warren of Wethersfield CT (US) for raytheon technologies corporation
IPC Code(s): G02B6/44, F16L25/01
CPC Code(s): G02B6/50
Abstract: an optical system is provided that includes a first conduit, a second conduit and a conduit coupler. the first conduit includes a first optics line and a first fluid passage extending longitudinally along the first optics line. the second conduit includes a second optics line and a second fluid passage extending longitudinally along the second optics line. the conduit coupler removably connects the first conduit to the second conduit at an interface within the conduit coupler. the first optics line is optically coupled to the second optics line at the interface. the first fluid passage is fluidly coupled with the second fluid passage at the interface.
Inventor(s): William Richard Shaw of Westbrook CT (US) for raytheon technologies corporation, Joseph V. Mantese of Ellington CT (US) for raytheon technologies corporation, Gurkan Gok of Milford CT (US) for raytheon technologies corporation, Joseph Zacchio of Wethersfield CT (US) for raytheon technologies corporation, Sharbel Elias Azzi of Palm Beach Gardens FL (US) for raytheon technologies corporation, Jonathan J. Gilson of West Hartford CT (US) for raytheon technologies corporation, Coy B. Wood of Ellington CT (US) for raytheon technologies corporation, Andre M. Ajami of Henderson NV (US) for raytheon technologies corporation
IPC Code(s): H04B1/03, H01Q1/28, H04B1/04, H04B1/08
CPC Code(s): H04B1/03
Abstract: an aircraft includes a communication system having a node and includes a method of operating the aircraft with the communication system. the communication system includes a waveguide and the node. the node is located in a high temperature environment. the node includes a high temperature logic circuit, a power supply, wherein the high temperature logic circuit and the power supply are disposed on a first side of the node in a high temperature environment, and a transponder disposed on a second side of the node. a sensor and/or an actuator can be operated via communication with the node via the waveguide.
Raytheon Technologies Corporation patent applications on September 19th, 2024
- Raytheon Technologies Corporation
- B22F10/34
- B22F12/58
- CPC B22F10/34
- Raytheon technologies corporation
- B23B25/00
- CPC B23B25/00
- B24B1/04
- B24B57/02
- B25J9/00
- B25J9/02
- B25J9/16
- B25J11/00
- CPC B24B1/04
- B64D37/16
- B64D37/06
- B64D37/30
- F02M37/00
- CPC B64D37/16
- C04B35/80
- C04B35/628
- C04B35/64
- CPC C04B35/80
- C04B35/634
- D04H18/02
- C04B41/53
- C04B41/45
- C04B41/50
- D03D15/242
- D03D25/00
- CPC C04B41/5392
- F01D5/18
- CPC F01D5/18
- F01D25/14
- F01D9/04
- F01D25/12
- F01D25/24
- CPC F01D25/14
- F02C3/30
- CPC F02C3/30
- F23R3/10
- CPC F02C3/305
- F02C7/141
- F02C7/16
- CPC F02C7/141
- F02C7/18
- F02C9/18
- CPC F02C7/18
- F02C7/28
- F16J15/324
- CPC F02C7/28
- F23L7/00
- F23R3/30
- CPC F23L7/005
- G01M15/14
- CPC G01M15/14
- G02B6/44
- F16L25/01
- CPC G02B6/50
- H04B1/03
- H01Q1/28
- H04B1/04
- H04B1/08
- CPC H04B1/03
