公开(公告)号：US20240209793A1

公开(公告)日：2024-06-27

申请号：US18088122

申请日：2022-12-23

Applicant: RTX Corporation

Inventor： Jon Erik Sobanski ,  Andrew E. Breault

IPC: F02C7/36 ,  F02C3/06 ,  F02K3/04

CPC classification number: F02C7/36 ,  F02C3/06 ,  F02K3/04 ,  F05D2220/323 ,  F05D2240/62

Abstract: A fan drive turbine drives a drive shaft. A compressor section and a turbine section rotate about a rotational axis, with the turbine section positioned in a downstream direction. A fan has fan blades and a fan hub positioned radially within a fan case, with the fan case defining a bypass duct. A fan inlet guide vane case is upstream of the fan blades and a fan exit guide vane case is mounted downstream. The drive shaft is mounted on at least one input drive shaft bearing inwardly of the fan inlet guide vane case. The drive shaft drives a flexible coupling to in turn drive a gear reduction. The gear reduction drives a fan drive shaft to in turn drive the fan hub. At least two fan drive shaft bearings support the fan drive shaft within the fan exit guide vane case. An aircraft is also disclosed.

公开(公告)号：US20240132221A1

公开(公告)日：2024-04-25

申请号：US18493186

申请日：2023-10-23

Applicant: Boom Technology, Inc.

Inventor： Nathaniel Blake Scholl

IPC: B64D27/16 ,  B64C15/14 ,  B64C30/00 ,  F02C7/32 ,  F02K3/04

CPC classification number: B64D27/16 ,  B64C15/14 ,  B64C30/00 ,  F02C7/32 ,  F02K3/04

Abstract: An aircraft propulsion system having a variable airflow capture area is provided. The propulsion system includes a main propulsion source and an auxiliary propulsion source. In a first mode, the auxiliary propulsion source is stowed within an aerodynamic profile of the aircraft, and the main propulsion source provides all of the propulsion force for powering flight of the aircraft. In a second mode, the auxiliary propulsion source is deployed to augment the airflow capture area of the main propulsion source and increase an overall airflow capture area of the propulsion system. In the second mode, the auxiliary power source is operated by power extracted from the main propulsion source. The main propulsion source may include one or more low bypass ratio engines. The auxiliary power source may include one or more auxiliary thrust fans coupled at a plurality of locations on the aircraft.

公开(公告)号：US11918943B2

公开(公告)日：2024-03-05

申请号：US17993082

申请日：2022-11-23

Applicant: General Electric Company

Inventor： Timothy Deryck Stone ,  Gregory Michael Laskowski ,  Robert Proctor ,  Curtis Stover ,  Robert Francis Manning ,  Victor Hugo Silva Correia ,  Jared Peter Buhler ,  Robert Carl Murray ,  Corey Bourassa ,  Byron Andrew Pritchard, Jr. ,  Jonathan Russell Ratzlaff

IPC: B01D45/16 ,  B04C3/00 ,  B04C3/06 ,  F01D5/18 ,  F01D9/06 ,  F02C6/08 ,  F02C7/052 ,  F02C7/18 ,  F02K3/04

CPC classification number: B01D45/16 ,  B04C3/06 ,  F01D5/189 ,  F01D9/065 ,  F02C6/08 ,  F02C7/052 ,  F02C7/18 ,  B04C2003/003 ,  B04C2003/006 ,  F02K3/04 ,  F05D2260/607 ,  Y02T50/60

Abstract: A turbine engine having a compressor section, a combustor section, a turbine section, and a rotatable drive shaft that couples a portion of the turbine section and a portion of the compressor section. A bypass conduit couples the compressor section to the turbine section while bypassing at least the combustion section. At least one particle separator is located in the turbine engine having a separator inlet that receives a bypass stream, a separator outlet that receives a reduced-particle stream flows, and a particle outlet that receives a concentrated-particle stream comprising separated particles. A conduit, fluidly coupled to the particle outlet, extends through an interior of at least one stationary vane.

公开(公告)号：US20230383709A1

公开(公告)日：2023-11-30

申请号：US18202709

申请日：2023-05-26

Applicant: Raytheon Technologies Corporation

Inventor： Paul R. Hanrahan ,  Roxanne M. Bochar

IPC: F02K1/00 ,  F02K3/04

CPC classification number: F02K1/002 ,  F02K3/04 ,  F05D2220/323 ,  F05D2240/128

Abstract: An assembly is provided for an aircraft propulsion system. This assembly includes a bladed rotor and a thrust vectoring exhaust nozzle. The bladed rotor is rotatable about an axis. The thrust vectoring exhaust nozzle is configured to direct gas propelled by the bladed rotor out of the aircraft propulsion system along a first direction during a first mode and along a second direction during a second mode. The first direction is parallel with the axis or angularly offset from the axis by no more than five degrees. The second direction is angularly offset from the axis by at least seventy-five degrees. The thrust vectoring exhaust nozzle has a first exit area during the first mode and a second exit area during the second mode that is greater than the first exit area.

公开(公告)号：US11802515B2

公开(公告)日：2023-10-31

申请号：US17783073

申请日：2020-12-11

Applicant: SAFRAN AIRCRAFT ENGINES ,  SAFRAN TRANSMISSION SYSTEMS

Inventor： Caroline Marie Frantz ,  Gilles Alain Marie Charier ,  Maeva Daphné Gros-Borot ,  Matthieu Bruno François Foglia ,  Adrien Louis Simon

IPC: F01D25/18 ,  F02C7/36 ,  F02K3/04

CPC classification number: F02C7/36 ,  F02K3/04 ,  F05D2260/40311

Abstract: A propulsion system includes a drive shaft, a fan, a fan shaft, and a reduction device coupling the drive and fan shafts. The reduction device includes a first reduction stage and a second reduction state, and include a sun gear, centered on an axis of rotation of the drive and fan shafts and driven in rotation by the drive shaft, a ring gear, coaxial with the sun gear and that drives the fan shaft in rotation about the axis, and planet gears distributed circumferentially about the axis between the sun and ring gears, each planet gear including a first portion which is meshed with the sun gear and a second portion which is meshed with the ring gear, a diameter of the first portion being different from a diameter of the second portion, and an oil transfer bearing positioned between the fan and the reduction device.

公开(公告)号：US11674453B2

公开(公告)日：2023-06-13

申请号：US17745532

申请日：2022-05-16

Applicant: Rolls-Royce Deutschland Ltd & Co KG

Inventor： Moritz Wirth

IPC: F02C9/18 ,  F02K3/04 ,  B64D15/04 ,  F02C6/08 ,  F02C7/047 ,  F02K3/06

CPC classification number: F02C9/18 ,  B64D15/04 ,  F02C6/08 ,  F02C7/047 ,  F02K3/04 ,  F02K3/06

Abstract: A gas turbine engine has an engine core, a fan arranged upstream of the engine core, and a hollow low-pressure shaft. The low-pressure shaft includes axially front and rear ends, wherein hot compressor air is applied to the axially rear end during operation. A valve is integrated into the interior of the low-pressure shaft, configured to open or close in accordance with the rotational speed of the low-pressure shaft, wherein the valve is closed from a predefined rotational speed and is open below this rotational speed, and wherein the valve, in the open state, allows hot compressor air to flow from the axially rear end of the low-pressure shaft to the axially front end of the low-pressure shaft and, in the closed state, prevents hot compressor air from flowing through the low-pressure shaft. A mechanism, when the valve is open, feeds hot compressor air outside of the fan disk.

公开(公告)号：US20180305036A1

公开(公告)日：2018-10-25

申请号：US15493623

申请日：2017-04-21

Applicant: General Electric Company

Inventor： Randy M. Vondrell ,  Anthony Austin Bouvette ,  Robert Charles Hon

IPC: B64D33/08 ,  B64D27/18 ,  B64D27/24 ,  B64C21/06 ,  B60L11/14 ,  F02K3/04 ,  H02G5/10 ,  H02K9/19 ,  H02K7/18

CPC classification number: B64D33/08 ,  B60L50/16 ,  B60L2200/10 ,  B64C21/06 ,  B64D27/18 ,  B64D27/24 ,  B64D2027/026 ,  B64D2221/00 ,  F02K3/04 ,  H02G5/10 ,  H02K7/1823 ,  H02K9/19 ,  Y02T50/64

Abstract: A propulsion system for an aircraft includes an electric power source, an electric propulsor assembly having an electric motor and a propulsor configured to generate thrust for the aircraft, and a power bus electrically connecting the electric power source to the electric propulsor assembly such that the electric power source powers the electric propulsor assembly. The power bus includes an electric line and a fluid cooling system, the fluid cooling system extending along at least a portion of a length of the electric line. The fluid cooling system is in thermal communication with the electric line for cooling the electric line during operation and is further in thermal communication with the electric motor of the electric propulsor assembly for cooling the electric motor of the electric propulsor assembly.

公开(公告)号：US20180298845A1

公开(公告)日：2018-10-18

申请号：US16016295

申请日：2018-06-22

Applicant: Rohr, Inc.

Inventor： Stephen Michael Roberts

IPC: F02K3/04 ,  F02K1/09 ,  F15B21/00 ,  F15B7/06 ,  F02K1/72 ,  B64C9/36 ,  H02G11/00 ,  E05D11/00 ,  F02K1/80 ,  F02K1/76

CPC classification number: F02K3/04 ,  B64C9/36 ,  E05D11/0081 ,  F02K1/09 ,  F02K1/72 ,  F02K1/763 ,  F02K1/80 ,  F05D2260/50 ,  F15B7/06 ,  F15B21/00 ,  H02G11/006

Abstract: A variable area fan nozzle actuation (“VAFN”) system is disclosed. The VAFN system may include an electrohydrostatic actuator (“EHA”) arranged to translate a VAFN panel relative to a translating sleeve. An electrical coupling may extend between a translating sleeve associated with the VAFN system and the fixed structure. The electrical coupling may be movable so that as the translating sleeve and fixed structure move relative to each other, power may be provided to the EHA by a wiring harness extending across the space between the translating sleeve and the fixed structure and connecting the EHA to an EHA power source.

公开(公告)号：US10072507B2

公开(公告)日：2018-09-11

申请号：US13660455

申请日：2012-10-25

Applicant: United Technologies Corporation

Inventor： David P. Houston

IPC: F01D5/30 ,  F01D21/04 ,  F02K3/04

CPC classification number: F01D5/3007 ,  F01D21/045 ,  F02K3/04 ,  F05D2220/36 ,  Y10T29/49321

Abstract: An airfoil attachment according to one example of this disclosure includes an airfoil and a disk supporting the airfoil. Further, there are primary contact surfaces and secondary contact surfaces between the airfoil and the disk. The secondary contact surfaces are not engaged during a normal operating condition.

公开(公告)号：US09982630B2

公开(公告)日：2018-05-29

申请号：US14721412

申请日：2015-05-26

Applicant: PRATT & WHITNEY CANADA CORP.

Inventor： Remo Marini ,  Roberto Marrano ,  Adam Trumpour

IPC: F02K3/115 ,  F02K3/105 ,  B64D33/10 ,  F02C7/12 ,  F02C7/141 ,  B64D33/08 ,  F02C7/18 ,  F02C7/14 ,  F02K3/075 ,  F02K3/06 ,  B64D33/02 ,  F02K3/068 ,  F28D21/00 ,  F02C7/32 ,  F02K3/077 ,  F02K3/02 ,  F02K3/04 ,  F02K3/00 ,  F02K1/82 ,  F02K3/065 ,  F02C7/143 ,  F02K3/062

CPC classification number: F02K3/115 ,  B64D33/08 ,  B64D33/10 ,  B64D2033/024 ,  B64D2033/0286 ,  F02C7/12 ,  F02C7/14 ,  F02C7/141 ,  F02C7/143 ,  F02C7/18 ,  F02C7/185 ,  F02C7/32 ,  F02K1/822 ,  F02K3/00 ,  F02K3/025 ,  F02K3/04 ,  F02K3/06 ,  F02K3/062 ,  F02K3/065 ,  F02K3/068 ,  F02K3/075 ,  F02K3/077 ,  F02K3/105 ,  F05D2250/13 ,  F05D2250/50 ,  F05D2250/51 ,  F05D2250/52 ,  F05D2250/712 ,  F05D2260/20 ,  F05D2260/213 ,  F28D2021/0021 ,  F28D2021/0026 ,  F28D2021/0049 ,  Y02T50/671 ,  Y02T50/675

Abstract: A cooler assembly disposed in and cooled by an air stream according to one embodiment includes a cooler matrix and a fairing. The fairing assembly is disposed generally around the cooler matrix and includes side fairing-housings, first and second side fairing-housings being joined to one another at respective leading and trailing edges, the leading edges partially defining a cooler inlet and the trailing edges partially defining a cooler outlet, the first and second side fairing-housing trailing edges angled transversely toward each other to define a trapezoidal shape for the outlet.