公开(公告)号：US12074350B2

公开(公告)日：2024-08-27

申请号：US17581155

申请日：2022-01-21

Applicant: General Electric Company

Inventor： Honggang Wang ,  Michael Anthony Benjamin ,  Seung-Hyuck Hong ,  Richard L. Hart

IPC: H01M8/04111 ,  H01M4/86 ,  H01M8/12

CPC classification number: H01M8/04111 ,  H01M4/8652 ,  H01M2004/8684 ,  H01M2008/1293 ,  H01M2250/20

Abstract: A propulsion system for an aircraft, the aircraft including an aircraft fuel supply, the propulsion system including: a turbomachine including a compressor section, a combustion section, and a turbine section arranged in serial flow order, the combustion section configured to receive a flow of aviation fuel from the aircraft fuel supply; and a fuel cell assembly including a fuel cell stack having a solid oxide fuel cell, the solid oxide fuel cell defining an outlet positioned to remove output products from the solid oxide fuel cell and provide the output products to the combustion section, the solid oxide fuel cell including a cathode; an electrolyte layer; and an anode positioned opposite the electrolyte layer from the cathode, the anode including a cermet, the cermet including less than 25% by volume nickel.

公开(公告)号：US20240247807A1

公开(公告)日：2024-07-25

申请号：US18585509

申请日：2024-02-23

Applicant: General Electric Company

Inventor： Karthikeyan Sampath ,  Pradeep Naik ,  Veeraraju Vanapalli ,  Perumallu Vukanti ,  Shai Birmaher ,  Daniel J. Kirtley ,  Deepak Ghiya ,  Rample Rakeshkumar Rangrej ,  Saket Singh ,  Ravindra Shankar Ganiger ,  Hiranya Kumar Nath ,  Michael Anthony Benjamin ,  Rajendra Mahadeorao Wankhade

IPC: F23R3/60 ,  B33Y80/00 ,  F23R3/06

CPC classification number: F23R3/60 ,  F23R3/06 ,  B33Y80/00 ,  F23R2900/00012 ,  F23R2900/00017 ,  F23R2900/00018

Abstract: A combustor for a gas turbine engine, the gas turbine engine defining a longitudinal centerline extending in a longitudinal direction, a radial direction extending orthogonally outward from the longitudinal centerline, and a circumferential direction extending concentrically around the longitudinal centerline, the combustor including: a forward liner segment; an aft liner segment disposed downstream from the forward liner segment relative to a direction of flow through the combustor, the forward and aft liner segments at least partially defining a combustion chamber; and an intermediate member disposed at least partially between the forward and aft liner segments and extending in the circumferential direction.

公开(公告)号：US12025061B2

公开(公告)日：2024-07-02

申请号：US17712747

申请日：2022-04-04

Applicant: General Electric Company

Inventor： Honggang Wang ,  Michael Anthony Benjamin ,  Stefan Joseph Cafaro

IPC: F02C9/40 ,  F02C7/32 ,  F02C9/48 ,  F23R3/36

CPC classification number: F02C9/40 ,  F02C7/32 ,  F02C9/48 ,  F23R3/36 ,  F05D2220/323 ,  F05D2220/76 ,  F05D2270/304 ,  F05D2270/31

Abstract: A method of operating a gas turbine engine is provided. The method includes: providing a flow of a primary fuel to a combustor of a turbomachine, the turbomachine including a compressor, a turbine, and a spool rotatable with the compressor and the turbine; receiving data indicative of a spool parameter of the spool; and modifying a flow of a secondary fuel to the combustor in response to the received data indicative of the spool parameter of the spool.

公开(公告)号：US20240162459A1

公开(公告)日：2024-05-16

申请号：US17984699

申请日：2022-11-10

Applicant: General Electric Company

Inventor： Seung-Hyuck Hong ,  Richard L. Hart ,  Honggang Wang ,  Anil Raj Duggal ,  Michael Anthony Benjamin

IPC: H01M8/04111

CPC classification number: H01M8/04111 ,  B64D2027/026

Abstract: A combustion section defines an axial direction, a radial direction, and a circumferential direction. The combustion section includes a casing that defines a diffusion chamber. A combustion liner is disposed within the diffusion chamber and defines a combustion chamber the combustion liner is spaced apart from the casing such that a passageway is defined between the combustion liner and the casing. A fuel cell assembly is disposed in the passageway. The fuel cell assembly includes a fuel cell stack that has a plurality of fuel cells each extending between an inlet end and an outlet end. The inlet end receives a flow of air and fuel and the outlet end provides output products to the combustion chamber. The fuel cell assembly further includes an electrical circuit that is electrically coupled to the plurality of fuel cells and that extends through the casing.

公开(公告)号：US20240159193A1

公开(公告)日：2024-05-16

申请号：US17988302

申请日：2022-11-16

Applicant: General Electric Company

Inventor： Arthur William Sibbach ,  Michael Anthony Benjamin ,  Sibtosh Pal ,  Erich Alois Krammer ,  Douglas Scott Jacobs ,  Jacques Paul

IPC: F02C9/40 ,  F02C7/22 ,  F02C7/266 ,  F02C9/26

CPC classification number: F02C9/40 ,  F02C7/22 ,  F02C7/266 ,  F02C9/263 ,  F05D2220/323 ,  F05D2270/44 ,  F05D2270/54

Abstract: A combustion system for a vehicle having an engine includes a hydrogen fuel system having a fuel source providing a hydrogen fuel, a combustor operable to combust the hydrogen fuel to generate combustion gases, and a fuel delivery assembly operable to deliver the hydrogen fuel from the fuel source to the combustor. A first control system has a first update rate and is operable to control one or more operational aspects of the turbine engine. A second control system is in communication with the first control system and the hydrogen fuel system and has a second update rate faster than the first update rate. The second control system is operable to monitor at least one parameter associated with the hydrogen fuel system and output at least one control signal to the hydrogen fuel system to control the delivery or the combustion of the hydrogen fuel.

公开(公告)号：US20240117479A1

公开(公告)日：2024-04-11

申请号：US18364875

申请日：2023-08-03

Applicant: General Electric Company

Inventor： Lawrence Bernard Kool ,  Bangalore Aswatha Nagaraj ,  Thomas George Holland ,  Alfred Albert Mancini ,  Michael Anthony Benjamin

IPC: C23C2/04 ,  B05D1/12 ,  B05D1/18 ,  B05D5/00 ,  B32B15/04 ,  B32B15/18 ,  C09D1/00 ,  C23C2/26 ,  C23C4/04 ,  C23C4/06 ,  C23C4/10 ,  C23C4/18 ,  C23C14/08 ,  C23C20/00 ,  C23C20/06 ,  C23C20/08 ,  C23C24/00 ,  C23C26/00 ,  F01D5/28 ,  F02C7/30

CPC classification number: C23C2/04 ,  B05D1/12 ,  B05D1/18 ,  B05D5/00 ,  B32B15/04 ,  B32B15/043 ,  B32B15/18 ,  C09D1/00 ,  C23C2/26 ,  C23C4/04 ,  C23C4/06 ,  C23C4/10 ,  C23C4/18 ,  C23C14/087 ,  C23C20/00 ,  C23C20/06 ,  C23C20/08 ,  C23C24/00 ,  C23C26/00 ,  F01D5/28 ,  F01D5/286 ,  F01D5/288 ,  F02C7/30 ,  F05D2220/323 ,  F05D2230/30 ,  F05D2230/31 ,  F05D2230/90 ,  Y02T50/60 ,  Y10T428/12847 ,  Y10T428/12944 ,  Y10T428/12951 ,  Y10T428/12979 ,  Y10T428/2495 ,  Y10T428/24967 ,  Y10T428/26 ,  Y10T428/265

Abstract: A hydrocarbon fluid containment article having a wall with a surface that is wetted by hydrocarbon fluid. The surface includes an anti-coking coating. The anti-coking coating includes a copper salt, a silver salt, or a combination thereof. A gas turbine engine component including a wall having a first surface and an anti-coking coating on the first surface of the wall that is wetted by hydrocarbon fluid. The anti-coking coating including a copper salt, a silver salt, or a combination thereof that prevents the formation of gum or coke on a surface thereon. Methods for reducing the deposition of thermal decomposition products on a wall of an article are also provided.

公开(公告)号：US11933216B2

公开(公告)日：2024-03-19

申请号：US17568286

申请日：2022-01-04

Applicant: General Electric Company

Inventor： Honggang Wang ,  Michael Anthony Benjamin

IPC: F02C3/30 ,  F02C7/232 ,  F02C9/28 ,  F23R3/28

CPC classification number: F02C3/30 ,  F02C7/232 ,  F02C9/28 ,  F23R3/286

Abstract: Systems and methods include a plurality of fuel cell stacks extended around a combustion chamber. The plurality of fuel cell stacks are distributed along a length of the combustion chamber in the axial direction. The fuel cell stacks are configured to provide output products to the combustion chamber to achieve at least one of late lean injection and a desired combustor gas concentration distribution.

公开(公告)号：US20230290967A1

公开(公告)日：2023-09-14

申请号：US17581155

申请日：2022-01-21

Applicant: General Electric Company

Inventor： Honggang Wang ,  Michael Anthony Benjamin ,  Seung-Hyuck Hong ,  Richard L. Hart

IPC: H01M8/04111 ,  H01M4/86 ,  F02C7/22

CPC classification number: H01M8/04111 ,  F02C7/22 ,  H01M4/8652 ,  H01M2008/1293 ,  H01M2250/20

Abstract: A propulsion system for an aircraft, the aircraft including an aircraft fuel supply, the propulsion system including: a turbomachine including a compressor section, a combustion section, and a turbine section arranged in serial flow order, the combustion section configured to receive a flow of aviation fuel from the aircraft fuel supply; and a fuel cell assembly including a fuel cell stack having a solid oxide fuel cell, the solid oxide fuel cell defining an outlet positioned to remove output products from the solid oxide fuel cell and provide the output products to the combustion section, the solid oxide fuel cell including a cathode; an electrolyte layer; and an anode positioned opposite the electrolyte layer from the cathode, the anode including a cermet, the cermet including less than 25% by volume nickel.

公开(公告)号：US20230238548A1

公开(公告)日：2023-07-27

申请号：US17581229

申请日：2022-01-21

Applicant: General Electric Company

Inventor： Honggang Wang ,  Michael Anthony Benjamin ,  Seung-Hyuck Hong ,  Richard L. Hart

IPC: H01M8/04007 ,  H01M8/04303 ,  H01M8/04746 ,  B64D31/00 ,  B64D27/10 ,  B64D27/24

CPC classification number: H01M8/04007 ,  H01M8/04303 ,  H01M8/04753 ,  B64D31/00 ,  B64D27/10 ,  B64D27/24 ,  H01M8/10

Abstract: A method for operating a propulsion system for an aircraft, the propulsion system including a gas turbine engine and a fuel cell assembly, the fuel cell assembly including a fuel cell stack having a solid oxide fuel cell defining an outlet positioned to remove output products from the solid oxide fuel cell during operation, the method including: operating the fuel cell assembly to provide output products to a combustor of a combustion section of the gas turbine engine; and operating the fuel cell assembly, the gas turbine engine, or both such that a pressure within an anode of the solid oxide fuel cell is less than a pressure within a cathode of the solid oxide fuel cell, is less than a pressure within a combustion chamber of the gas turbine engine, or both while operating the gas turbine engine.

公开(公告)号：US20230216071A1

公开(公告)日：2023-07-06

申请号：US17568269

申请日：2022-01-04

Applicant: General Electric Company

Inventor： Honggang Wang ,  Michael Anthony Benjamin

IPC: H01M8/04298 ,  G06F30/27 ,  F01D15/10

CPC classification number: H01M8/04305 ,  G06F30/27 ,  F01D15/10 ,  H01M2250/20 ,  F05D2220/76 ,  F05D2240/35

Abstract: Systems and methods configured to receive a set of real-time flight conditions and a user-selected objective function. The user-selected objective function is one of a plurality of objective functions. The systems and methods determine, with an emissions tuning model, one of a plurality of sets of fuel cell operating conditions based on the set of real-time flight conditions and the user-selected objective function. The systems and methods are configured to control a fuel cell assembly operating parameter according to the determined one of the plurality of sets of fuel cell operating conditions.