公开(公告)号：US12188128B2

公开(公告)日：2025-01-07

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

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：US12055295B2

公开(公告)日：2024-08-06

申请号：US17687769

申请日：2022-03-07

Applicant: General Electric Company

Inventor： Michael Anthony Benjamin ,  Joshua Tyler Mook ,  Sean James Henderson ,  Ramon Martinez

IPC: F23R3/28 ,  F23D11/38 ,  F23R3/14 ,  F23R3/34

CPC classification number: F23R3/283 ,  F23D11/386 ,  F23R3/286 ,  F23D2209/30 ,  F23R3/14 ,  F23R3/34 ,  F23R3/346 ,  F23R2900/00004

Abstract: A fuel nozzle apparatus includes: an outer body having an exterior surface and a plurality of openings in the exterior surface. An inner body is disposed inside the outer body, cooperating with the outer body to define an annular space. A main injection ring is disposed in the annular space and includes an array of fuel posts extending outward therefrom, each fuel post including a perimeter wall defining a lateral surface and a recessed floor. Each fuel post is aligned with one of the openings and separated from the opening by a perimeter gap defined between the opening and the lateral surface. A main fuel gallery extends within the main injection ring. The main injection ring includes plurality of main fuel orifices, each main fuel orifice communicating with the main fuel gallery and extending through one of the fuel posts.

公开(公告)号：US11859820B1

公开(公告)日：2024-01-02

申请号：US17984669

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 ,  Andrew Wickersham ,  Narendra Digamber Joshi

IPC: F23R3/00 ,  H01M8/04089 ,  H01M8/2457 ,  F23R3/28 ,  H01M8/04007

CPC classification number: F23R3/002 ,  F23R3/28 ,  H01M8/04074 ,  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 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 outlet end of the plurality of fuel cells extends through the combustion liner and partially defines the combustion chamber.

公开(公告)号：US11802693B2

公开(公告)日：2023-10-31

申请号：US17232653

申请日：2021-04-16

Applicant: General Electric Company

Inventor： Allen M. Danis ,  Nicholas R. Overman ,  Steven Clayton Vise ,  Michael Anthony Benjamin ,  James Matthew Rogers

IPC: F23R3/14 ,  F23D14/62 ,  F23R3/28

CPC classification number: F23R3/14 ,  F23D14/62 ,  F23R3/286 ,  F23D2206/10 ,  F23D2900/14021 ,  F23D2900/14701

Abstract: A swirler apparatus for a combustor, including: primary and secondary swirlers disposed axially adjacent to each other along a swirler centerline; the primary swirler including a plurality of primary swirl vanes arrayed around the swirler centerline, each primary swirl vane including opposed sides bounded between opposed forward and aft edges and opposed leading and trailing edges; wherein the forward edge is oriented at a first vane angle with respect to a radial direction; wherein the aft edge is oriented at a second vane angle with respect to the radial direction; wherein the second vane angle is different from the first vane angle; and the secondary swirler including a plurality of secondary swirl vanes arrayed around the swirler centerline.

公开(公告)号：US20230211887A1

公开(公告)日：2023-07-06

申请号：US17567990

申请日：2022-01-04

Applicant: General Electric Company

Inventor： Honggang Wang ,  Michael Anthony Benjamin ,  Koji Asari

IPC: B64D31/00 ,  H01M8/04694 ,  B64D27/24 ,  B64D27/10 ,  B64D37/00 ,  B60L58/30 ,  H01M8/04298 ,  B64D27/02

CPC classification number: B64D31/00 ,  H01M8/04694 ,  B64D27/24 ,  B64D27/10 ,  B64D37/00 ,  B60L58/30 ,  H01M8/04305 ,  H01M2250/20 ,  B60L2200/10 ,  B64D2027/026

Abstract: A propulsion system including: a fuel cell assembly comprising a fuel cell, the fuel cell defining an outlet positioned to remove output products from the fuel cell and a fuel cell assembly operating condition; a combustion section that includes a combustor configured to receive a flow of aviation fuel from the aircraft fuel supply and further configured to receive the output products from the fuel cell; and a controller comprising memory and one or more processors, the memory storing instructions that when executed by the one or more processors cause the propulsion system to perform operations including: determining data indicative of at least one of an enthalpy or a composition of the output products from the fuel cell; and modifying the flow of aviation fuel from the aircraft fuel supply to the combustor based on the at least one of the enthalpy or the composition of the output products.

公开(公告)号：US20230211884A1

公开(公告)日：2023-07-06

申请号：US17568254

申请日：2022-01-04

Applicant: General Electric Company

Inventor： Honggang Wang ,  Michael Anthony Benjamin

IPC: B64D27/10 ,  H01M8/04111 ,  H01M8/04746 ,  H01M8/04701 ,  H01M8/04992

CPC classification number: B64D27/10 ,  H01M8/04111 ,  H01M8/04776 ,  H01M8/04738 ,  H01M8/04992 ,  H01M2250/20 ,  B64D2027/026

Abstract: A gas turbine engine includes a fuel cell assembly including a fuel cell stack and defining a fuel cell assembly operating parameter, a fuel source, and a turbomachine. The turbomachine includes a compressor section, a combustor, and a turbine section arranged in serial flow order. The combustor is configured to receive a flow of fuel from the fuel source and further configured to receive output products from the fuel cell stack. A controller is configured to perform operations including receiving data indicative of system operation conditions, determining a set of fuel cell operating conditions to move the system emission output into or maintain the system emission output within an emissions range, and controlling the fuel cell assembly operating parameter according to the determined set of fuel cell operating conditions.

公开(公告)号：US11603799B2

公开(公告)日：2023-03-14

申请号：US17130040

申请日：2020-12-22

Applicant: General Electric Company

Inventor： Ravindra Shankar Ganiger ,  Hiranya Kumar Nath ,  Michael Anthony Benjamin ,  Rajendra Mahadeorao Wankhade ,  Gurunath Gandikota

IPC: F23R3/28 ,  F02C7/24 ,  F02C7/22

Abstract: A combustor for a gas turbine engine includes an inner liner and an outer liner positioned outward of the inner liner along the radial direction such that a combustion chamber is defined between the inner and outer liners. Furthermore, the combustor includes a fuel nozzle configured to supply fuel to the combustion chamber. Moreover, the combustor includes a bristle pack having a base plate and a plurality of bristles extending outward from the base plate such that the bristle pack forms at least a portion of at least one of a heat shield coupled to the fuel nozzle, a deflector of the combustor, or a flare of the combustor.

公开(公告)号：US20230003382A1

公开(公告)日：2023-01-05

申请号：US17363088

申请日：2021-06-30

Applicant: General Electric Company

Inventor： Ravindra Shankar Ganiger ,  Hiranya Kumar Nath ,  Rajendra Mahadeorao Wankhade ,  Daniel J. Kirtley ,  Michael Anthony Benjamin

IPC: F23R3/00 ,  F02C7/28

Abstract: A gas turbine engine and combustor assembly are provided, the combustor assembly including a first liner and a second liner together defining at least in part a combustion chamber, wherein the first liner and the second liner are separated by a gap along the longitudinal direction, and wherein the first liner is forward of the second liner relative to a flow of fluid through the combustion chamber along the longitudinal direction, and wherein the gap is extended along the circumferential direction.

公开(公告)号：US20220390112A1

公开(公告)日：2022-12-08

申请号：US17340703

申请日：2021-06-07

Applicant: General Electric Company

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

IPC: F23R3/00 ,  F02C3/14

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 liner at least partially defining a combustion chamber, the liner including a dilution slot in fluid communication with the combustion chamber; and one or more guides configured to redirect cooling medium into the dilution slot.

公开(公告)号：US11300295B2

公开(公告)日：2022-04-12

申请号：US16586016

申请日：2019-09-27

Applicant: General Electric Company

Inventor： Michael Anthony Benjamin ,  Joshua Tyler Mook ,  Sean James Henderson ,  Ramon Martinez

IPC: F23R3/28 ,  F23R3/14 ,  F23R3/34 ,  F23D11/38

Abstract: A fuel nozzle apparatus includes: an outer body having an exterior surface and a plurality of openings in the exterior surface. An inner body is disposed inside the outer body, cooperating with the outer body to define an annular space. A main injection ring is disposed in the annular space and includes an array of fuel posts extending outward therefrom, each fuel post including a perimeter wall defining a lateral surface and a recessed floor. Each fuel post is aligned with one of the openings and separated from the opening by a perimeter gap defined between the opening and the lateral surface. A main fuel gallery extends within the main injection ring. The main injection ring includes plurality of main fuel orifices, each main fuel orifice communicating with the main fuel gallery and extending through one of the fuel posts.