公开(公告)号：US20240291008A1

公开(公告)日：2024-08-29

申请号：US18404083

申请日：2024-01-04

Applicant: General Electric Company

Inventor： Honggang Wang ,  Brandon Wayne Miller ,  Michael Anthony Benjamin ,  Richard L. Hart ,  Randy M. Vondrell ,  Ryan St. Pierre

IPC: H01M8/0612 ,  F02C7/22

CPC classification number: H01M8/0618 ,  F02C7/22 ,  H01M8/0625 ,  H01M2250/20

Abstract: A gas turbine engine is provided. The gas turbine engine includes a turbomachine having a compressor section, a combustor, and a turbine section arranged in serial flow order, the turbomachine further including an outer casing; a fuel cell assembly positioned within the outer casing of the turbomachine, the fuel cell assembly including a fuel cell and an output products line in fluid communication with an outlet of the fuel cell for receiving output products from the fuel cell; a fuel delivery assembly including a fuel line; and a reformer in communication with the fuel line and the output products from the fuel cell during operation of the gas turbine engine to convert a fuel flow through the fuel line to a hydrogen rich gas.

公开(公告)号：US12037952B2

公开(公告)日：2024-07-16

申请号：US17568359

申请日：2022-01-04

Applicant: General Electric Company

Inventor： Honggang Wang ,  Michael Anthony Benjamin

IPC: F02C9/00 ,  F02C7/22 ,  F02C9/40 ,  F23R3/36

CPC classification number: F02C9/40 ,  F02C7/22 ,  F23R3/36 ,  F05D2220/32 ,  F05D2240/35

Abstract: Systems and methods including a plurality of reformer stacks extended around the combustion chamber. The reformer stacks are distributed along a length of the combustion chamber in the axial direction and configured to provide output products to the combustion chamber.

公开(公告)号：US20240159397A1

公开(公告)日：2024-05-16

申请号：US17984641

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: F23R3/00 ,  F23R3/28 ,  H01M8/04089 ,  H01M8/2457

CPC classification number: F23R3/002 ,  F23R3/28 ,  H01M8/04089 ,  H01M8/2457 ,  H01M2250/20

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 that extends 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 extends at an angle between the inlet end and the outlet end relative to a radial projection line.

公开(公告)号：US11970282B2

公开(公告)日：2024-04-30

申请号：US17568892

申请日：2022-01-05

Applicant: General Electric Company

Inventor： Honggang Wang ,  Kum Kang Huh ,  Michael Anthony Benjamin ,  Koji Asari

IPC: B64D27/24 ,  B64D27/10 ,  B64D31/12 ,  B64D27/02 ,  B64D41/00

CPC classification number: B64D31/12 ,  B64D27/10 ,  B64D27/24 ,  B64D2027/026 ,  B64D2041/005 ,  B64D2221/00

Abstract: Systems and methods of aircraft thrust management are provided. For example, a propulsion system for an aircraft comprises a fuel cell assembly comprising a fuel cell, a turbomachine, and a controller comprising memory and one or more processors. The memory stores instructions that, when executed by the one or more processors, cause the propulsion system to perform operations including receiving data indicative of a propulsion system thrust discrepancy and modifying an output of the fuel cell in response to receiving data indicative of the propulsion system thrust discrepancy. Modifying the fuel cell output may include modifying output products, an electrical power output, or both of the fuel cell to balance the thrust provided by the propulsion system.

公开(公告)号：US11846026B2

公开(公告)日：2023-12-19

申请号：US17150613

申请日：2021-01-15

Applicant: General Electric Company

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

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

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：US20230282848A1

公开(公告)日：2023-09-07

申请号：US17676488

申请日：2022-02-21

Applicant: General Electric Company

Inventor： Honggang Wang ,  Radislav A. Potyrailo ,  Michael Anthony Benjamin

IPC: H01M8/0444 ,  H01M8/04858 ,  H01M8/0662 ,  H01M8/249 ,  F02C7/00 ,  B64D27/10 ,  B64D27/24 ,  B60L50/70 ,  B60L58/30

CPC classification number: H01M8/0444 ,  B60L50/70 ,  B60L58/30 ,  B64D27/10 ,  B64D27/24 ,  F02C7/00 ,  H01M8/0494 ,  H01M8/0662 ,  H01M8/249 ,  B60L2200/10 ,  F05D2220/323 ,  F05D2240/35 ,  F05D2270/053 ,  H01M2250/20

Abstract: A propulsion system is provided including: a gas turbine engine including a combustion section having a combustor; and a modular fuel cell assembly. The modular fuel cell assembly includes: a first fuel cell string comprising a first processing unit and a first fuel cell stack, the first fuel cell stack comprising a first fuel cell defining an outlet configured to provide output products from the first fuel cell to the combustor; and a second fuel cell string comprising a second processing unit and a second fuel cell stack, the second fuel cell stack comprising a second fuel cell defining an outlet configured to provide output products from the second fuel cell to the combustor.

公开(公告)号：US20230282847A1

公开(公告)日：2023-09-07

申请号：US17676478

申请日：2022-02-21

Applicant: General Electric Company

Inventor： Honggang Wang ,  Radislav A. Potyrailo ,  Michael Anthony Benjamin

IPC: H01M8/04111 ,  B64D27/10 ,  B64D27/24 ,  H01M8/04992 ,  H01M8/04746

CPC classification number: H01M8/04111 ,  B64D27/10 ,  B64D27/24 ,  H01M8/04753 ,  H01M8/04992 ,  B64D2027/026 ,  H01M2250/20

Abstract: A method is provided for operating a propulsion system having a gas turbine engine and a fuel cell assembly. The fuel cell assembly includes a fuel cell. The method includes: receiving gas composition data of output products from the fuel cell; and controlling operation of the fuel cell assembly, the gas turbine engine, or both in response to the received gas composition data of the output products from the fuel cell.

公开(公告)号：US20230265792A1

公开(公告)日：2023-08-24

申请号：US17676465

申请日：2022-02-21

Applicant: General Electric Company

Inventor： Honggang Wang ,  Radislav A. Potyrailo ,  Michael Anthony Benjamin

IPC: F02C6/00 ,  F02C3/20

CPC classification number: F02C6/00 ,  F02C3/20 ,  F05D2220/323

Abstract: A propulsion system is provided including: a propulsor; a turbomachine operable to drive the propulsor to generate thrust during operation; a fuel cell assembly configured to add power to the propulsor, the turbomachine, or both; and a multi-gas sensor operable with the turbomachine, the fuel cell assembly, or both for sensing gas composition data of a fluid flow in or to the turbomachine, the fuel cell assembly, or both, the gas composition data comprising data indicative of at least two gases and their concentrations.

公开(公告)号：US20230234716A1

公开(公告)日：2023-07-27

申请号：US17581135

申请日：2022-01-21

Applicant: General Electric Company

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

IPC: B64D31/00 ,  H01M8/04225 ,  H01M8/04223 ,  H01M8/04302 ,  H01M8/04701 ,  B64D27/10 ,  B64D27/24

CPC classification number: B64D31/00 ,  H01M8/04225 ,  H01M8/04231 ,  H01M8/04302 ,  H01M8/04701 ,  B64D27/10 ,  B64D27/24 ,  H01M2250/20 ,  B64D2027/026

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 fuel cell defining an outlet positioned to remove output products from the fuel cell during operation, the method including: executing a startup sequence for the fuel cell assembly, wherein executing the startup sequence for the fuel cell assembly includes initiating the startup sequence for the fuel cell assembly; executing a startup sequence for the gas turbine engine, wherein executing the startup sequence for the gas turbine engine comprises initiating the startup sequence for the gas turbine engine subsequent to initiating the startup sequence for the fuel cell assembly; and operating the fuel cell assembly to provide output products to a combustion section of the gas turbine engine.

公开(公告)号：US20230234714A1

公开(公告)日：2023-07-27

申请号：US17581098

申请日：2022-01-21

Applicant: General Electric Company

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

IPC: B64D27/24 ,  H01M8/04701 ,  H01M8/04223 ,  B64D27/10 ,  H01M8/04225 ,  H01M8/04111 ,  B64D27/02 ,  B64D41/00

CPC classification number: B64D27/24 ,  H01M8/04738 ,  H01M8/04708 ,  H01M8/04231 ,  B64D27/10 ,  H01M8/04225 ,  H01M8/04111 ,  B64D2027/026 ,  B64D2041/005 ,  H01M2250/20

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 comprising a fuel cell stack having a fuel cell defining an outlet positioned to remove output products from the fuel cell during operation, the method including: executing a startup sequence for the gas turbine engine, wherein executing the startup sequence comprises initiating the startup sequence for the gas turbine engine; executing a startup sequence for the fuel cell assembly concurrently with, or subsequent to, initiating the startup sequence for the gas turbine engine; and operating the fuel cell assembly to provide output products to a combustion section of the gas turbine engine.