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    Fuel nozzle structure for air assist injection
    3.
    发明授权
    Fuel nozzle structure for air assist injection 有权

    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.

    Fuel nozzle structure for air assist injection
    5.
    发明授权
    Fuel nozzle structure for air assist injection 有权

    公开(公告)号：US10451282B2

    公开(公告)日：2019-10-22

    申请号：US15107282

    申请日：2014-12-23

    Applicant: GENERAL ELECTRIC COMPANY

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

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

    Abstract: A fuel nozzle includes an outer body extending parallel to a centerline axis, having a generally cylindrical exterior surface, forward and aft ends, and a plurality of openings through the exterior surface. The fuel nozzle further includes an inner body inside the outer body, cooperating with the outer body to define an annular space, and a main injection ring inside the annular space, the main injection ring including fuel posts extending therefrom. Each fuel post is aligned with one of the openings and separated from the opening by a perimeter gap which communicates with the annular space. There is a circumferential main fuel gallery in the main injection ring, and a plurality of main fuel orifices, wherein each orifice communicates with the main fuel gallery and extends through one of the fuel posts.

    Heat exchanger having curved fluid passages for a gas turbine engine
    6.
    发明授权
    Heat exchanger having curved fluid passages for a gas turbine engine 有权

    公开(公告)号：US12196502B2

    公开(公告)日：2025-01-14

    申请号：US18136594

    申请日：2023-04-19

    Applicant: General Electric Company

    Inventor： Ramon Martinez ,  Raymond Floyd Martell ,  Donald Lee Gardner

    IPC: F28D7/00 ,  F28F9/02

    Abstract: A heat exchanger for a gas turbine engine includes a heat exchanger body having a first surface and a second surface oriented at least partially at an oblique angle relative to the first surface. The heat exchanger body defines a plenum extending between the first and second surfaces. Furthermore, the heat exchanger body defines a fluid passage extending through the second surface such that the fluid passage is in fluid communication with the plenum. The fluid passage, in turn, includes first and second portions. The first portion intersects the plenum at an intersection and defines a line of projection extending normal to the second surface. The second portion defines a line of projection extending normal to the first surface. The fluid passage further includes a curved portion extending from the first portion to the second portion.

    HEAT EXCHANGER FOR AN AIRCRAFT
    8.
    发明公开
    HEAT EXCHANGER FOR AN AIRCRAFT 审中-公开

    公开(公告)号：US20240287934A1

    公开(公告)日：2024-08-29

    申请号：US18659339

    申请日：2024-05-09

    Applicant: General Electric Company

    Inventor： Matthew Ryan Johns ,  Alex William Ariapad ,  Nicolas Kristopher Sabo ,  Jeffrey Douglas Rambo ,  Ramon Martinez ,  Jared Wolfe

    IPC: F02C7/14

    CPC classification number: F02C7/14 ,  F05D2220/323 ,  F05D2260/213 ,  F05D2260/606

    Abstract: A heat exchanger for an aircraft includes an inlet plenum housing defining an inlet plenum configured to receive a fluid and an outlet plenum housing defining an outlet plenum configured to discharge the fluid. Furthermore, the heat exchanger includes a core configured to heat or cool a first portion of the fluid, with the core defining a plurality of fluid passages extending from the inlet plenum to the outlet plenum. Moreover, the heat exchanger includes a passive bypass defining a passive bypass flow path fluidly coupled to and extending between the inlet plenum and the outlet plenum. As such, the passive bypass flow path is in parallel with at least a portion of the core such that a second portion of the fluid bypasses at least a portion of the core and flows continuously and unobstructed through the passive bypass flow path to the outlet plenum.

    HEAT EXCHANGER HAVING CURVED FLUID PASSAGES FOR A GAS TURBINE ENGINE
    9.
    发明公开
    HEAT EXCHANGER HAVING CURVED FLUID PASSAGES FOR A GAS TURBINE ENGINE 审中-公开

    公开(公告)号：US20230258407A1

    公开(公告)日：2023-08-17

    申请号：US18136594

    申请日：2023-04-19

    Applicant: General Electric Company

    Inventor： Ramon Martinez ,  Raymond Floyd Martell ,  Donald Lee Gardner

    IPC: F28D7/00

    CPC classification number: F28D7/0016 ,  F28F2210/10 ,  F28F2009/0287

    Abstract: A heat exchanger for a gas turbine engine includes a heat exchanger body having a first surface and a second surface oriented at least partially at an oblique angle relative to the first surface. The heat exchanger body defines a plenum extending between the first and second surfaces. Furthermore, the heat exchanger body defines a fluid passage extending through the second surface such that the fluid passage is in fluid communication with the plenum. The fluid passage, in turn, includes first and second portions. The first portion intersects the plenum at an intersection and defines a line of projection extending normal to the second surface. The second portion defines a line of projection extending normal to the first surface. The fluid passage further includes a curved portion extending from the first portion to the second portion.

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