公开(公告)号：US20240133318A1

公开(公告)日：2024-04-25

申请号：US17972734

申请日：2022-10-24

Applicant: General Electric Company

Inventor： Brian Lewis Devendorf ,  Arthur William Sibbach

IPC: F01D25/26

CPC classification number: F01D25/265 ,  F05D2240/14 ,  F05D2260/36

Abstract: A gas turbine engine, comprising a turbomachine and a housing at least partially encasing a portion of the turbomachine, the housing having an inner surface and defining in part a void between the inner surface and the portion of the turbomachine, the housing moveable relative to the portion of the turbomachine; and an engine component selectively coupled to the portion of the turbomachine or to the housing.

公开(公告)号：US11795964B2

公开(公告)日：2023-10-24

申请号：US17377668

申请日：2021-07-16

Applicant: General Electric Company

Inventor： Nicholas M. Daggett ,  Gert Johannes van der Merwe ,  Daniel Alan Niergarth ,  Brian Lewis Devendorf

IPC: B64C11/34 ,  F04D29/34 ,  F02C3/06 ,  B64C11/32 ,  F04D29/32 ,  F04D29/36

CPC classification number: F04D29/34 ,  F02C3/06 ,  B64C11/325 ,  B64C11/346 ,  F04D29/323 ,  F04D29/366 ,  F05D2220/32 ,  F05D2240/24

Abstract: A fan assembly for a gas turbine engine includes a fan disk, a trunnion, a fan blade, and a counterweight assembly. The fan disk is configured to rotate about an axial centerline of the gas turbine engine when installed in the gas turbine engine. The trunnion is mounted to the fan disk and defines a slot extending through a portion of the trunnion. The fan blade defines a pitch axis and is rotatably attached to the fan disk about its pitch axis through the trunnion. The counterweight assembly includes a link arm extending to the trunnion and an engagement device mounted to the link arm that is disposed to move through the slot of the trunnion.

公开(公告)号：US20210222628A1

公开(公告)日：2021-07-22

申请号：US16904035

申请日：2020-06-17

Applicant: General Electric Company

Inventor： Brian Lewis Devendorf

IPC: F02C7/36 ,  F02C7/32 ,  F01D15/10

Abstract: A gas turbine engine is provided. The gas turbine engine includes a turbomachine having a low speed spool and a high speed spool; a rotor assembly coupled to the low speed spool; an electric machine rotatable with the low speed spool for extracting power from the low speed spool, for adding power to the low speed spool, or both; and an inter-spool clutch positioned between the low speed spool and the high speed spool for selectively coupling the low speed spool to the high speed spool.

公开(公告)号：US11761344B1

公开(公告)日：2023-09-19

申请号：US17724074

申请日：2022-04-19

Applicant: General Electric Company

Inventor： Brandon Wayne Miller ,  Brian Lewis Devendorf ,  Jeffrey Douglas Rambo ,  Brian Gene Brzek ,  Kevin Edward Hinderliter ,  Erich Alois Krammer ,  Arthur William Sibbach

IPC: F01D19/02 ,  F01D25/10 ,  F01D25/18

CPC classification number: F01D19/02 ,  F01D25/10 ,  F01D25/18 ,  F05D2260/213 ,  F05D2260/232 ,  F05D2260/607 ,  F05D2260/85 ,  F05D2260/98

Abstract: A method is provided for operating a thermal management system of a gas turbine engine. The method includes: operating the gas turbine engine to start-up the gas turbine engine; receiving data indicative of a state of a thermal transport bus of the thermal management system using a sensor, the state of the thermal transport bus including a phase of a thermal fluid within the thermal transport bus; and starting a pump of a pump assembly in response to receiving data indicative of the state of the thermal transport bus of the thermal management system, the pump in fluid communication with the thermal transport bus.

公开(公告)号：US20220412254A1

公开(公告)日：2022-12-29

申请号：US17361804

申请日：2021-06-29

Applicant: General Electric Company

Inventor： Nicholas M. Daggett ,  Gert Johannes van der Merwe ,  Daniel Alan Niergarth ,  Brian Lewis Devendorf

IPC: F02C3/06 ,  F04D3/00 ,  F04D29/32

Abstract: A fan assembly for a gas turbine engine includes a fan disk, a trunnion, an actuation device, a fan blade, and a counterweight assembly. The trunnion is mounted to the fan disk. The actuation device is operably coupled to the trunnion. The fan blade is rotatably attached to the fan disk. The counterweight assembly includes a link arm, a lever arm, a hinge, and a counterweight. The link arm is connected to the trunnion, to the actuation device, or to both. The link arm is configured to drive rotation of the trunnion relative to the fan disk. The hinge is pivotably connected to the lever arm. The lever arm is connected to the link arm and is disposed to rotate about a connection point of the lever arm and the hinge. The counterweight is mounted to the lever arm at a location spaced from the hinge.

公开(公告)号：US11506067B2

公开(公告)日：2022-11-22

申请号：US16904035

申请日：2020-06-17

Applicant: General Electric Company

Inventor： Brian Lewis Devendorf

IPC: F01D7/00 ,  F02C7/36 ,  F02C7/32 ,  F01D15/12 ,  F01D15/10 ,  F02C9/00 ,  F02C9/22 ,  F02K1/76 ,  F01D5/18 ,  F01D5/30 ,  F02C7/264 ,  F01D9/04 ,  F01D17/16 ,  B64D27/12 ,  F01D25/12 ,  B32B7/022 ,  B64C1/12 ,  B64D7/00 ,  B64C1/38 ,  F01D5/14 ,  F02K1/66 ,  F02C9/48 ,  F02C9/20 ,  B64D45/00 ,  F02C6/20 ,  B64C1/00 ,  F02C3/113

Abstract: A gas turbine engine is provided. The gas turbine engine includes a turbomachine having a low speed spool and a high speed spool; a rotor assembly coupled to the low speed spool; an electric machine rotatable with the low speed spool for extracting power from the low speed spool, for adding power to the low speed spool, or both; and an inter-spool clutch positioned between the low speed spool and the high speed spool for selectively coupling the low speed spool to the high speed spool.

公开(公告)号：US10830141B2

公开(公告)日：2020-11-10

申请号：US15843260

申请日：2017-12-15

Applicant: General Electric Company

Inventor： William Dwight Gerstler ,  Daniel Jason Erno ,  Brian Lewis Devendorf ,  Kevin Kenneth Pruzinsky

IPC: F02C7/10 ,  F02C7/08 ,  F02C3/04 ,  F28D21/00

Abstract: A recuperator includes a monolithic heat exchanger core having a first side proximal to a combustor inlet and a turbine outlet, and a second side that includes an exhaust outlet. A compressed air inlet is located on the second side, and a compressed air outlet is located on the first side. The compressed air outlet supplies air to a combustor. A first plurality of passageways connects the compressed air inlet to the compressed air outlet. A turbine exhaust inlet is located on the first side, and a turbine exhaust outlet is located on the second side. A second plurality of passageways connects the turbine exhaust inlet to the turbine exhaust outlet. The first and second plurality of passageways are defined by parting plates that extend radially outward in a spiral pattern that maintains a substantially equal distance between adjacent parting plates.

公开(公告)号：US20240417101A1

公开(公告)日：2024-12-19

申请号：US18817394

申请日：2024-08-28

Applicant: General Electric Company

Inventor： Brian Lewis Devendorf

IPC: B64D45/00 ,  B32B7/022 ,  B64C1/00 ,  B64C1/12 ,  B64C1/38 ,  B64D27/12 ,  F01D5/14 ,  F01D5/18 ,  F01D5/30 ,  F01D7/00 ,  F01D9/04 ,  F01D15/10 ,  F01D15/12 ,  F01D17/16 ,  F01D25/12 ,  F02C3/113 ,  F02C6/20 ,  F02C7/264 ,  F02C7/32 ,  F02C7/36 ,  F02C9/00 ,  F02C9/22 ,  F02K1/66 ,  F02K1/76

Abstract: A gas turbine engine is provided. The gas turbine engine includes a turbomachine comprising a low speed spool; a rotor assembly coupled to the low speed spool; an electric machine mechanically coupled to the low speed spool at a connection point of the low speed spool; and a clutch positioned in the torque path of the low speed spool between the connection point and the rotor assembly

公开(公告)号：US20240229679A9

公开(公告)日：2024-07-11

申请号：US17972734

申请日：2022-10-25

Applicant: General Electric Company

Inventor： Brian Lewis Devendorf ,  Arthur William Sibbach

IPC: F01D25/26

CPC classification number: F01D25/265 ,  F05D2240/14 ,  F05D2260/36

Abstract: A gas turbine engine, comprising a turbomachine and a housing at least partially encasing a portion of the turbomachine, the housing having an inner surface and defining in part a void between the inner surface and the portion of the turbomachine, the housing moveable relative to the portion of the turbomachine; and an engine component selectively coupled to the portion of the turbomachine or to the housing.

公开(公告)号：US20240003294A1

公开(公告)日：2024-01-04

申请号：US18353472

申请日：2023-07-17

Applicant: General Electric Company

Inventor： Arthur William Sibbach ,  Allan George van de Wall ,  Sean Christopher Binion ,  Brian Lewis Devendorf ,  Brandon Wayne Miller

IPC: F02C7/047 ,  F02K3/06 ,  B64D33/02

CPC classification number: F02C7/047 ,  F02K3/06 ,  B64D33/02 ,  B64D2033/0233

Abstract: A turbofan engine is provided. The turbofan engine includes a fan comprising a plurality of fan blades; a turbomachine operably coupled to the fan for driving the fan, the turbomachine comprising a compressor section, a combustion section, and a turbine section in serial flow order and together defining a core air flowpath; a nacelle surrounding and at least partially enclosing the fan; an inlet pre-swirl feature located upstream of the plurality of fan blades, the inlet pre-swirl feature attached to or integrated into the nacelle; and a means for reducing ice buildup or ice formation on the inlet pre-swirl feature, the means in communication with the inlet pre-swirl feature.