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    GAS TURBINE ENGINE WITH FRONT SUPPORT ARRANGEMENT
    1.
    发明申请
    GAS TURBINE ENGINE WITH FRONT SUPPORT ARRANGEMENT 有权

    公开(公告)号：US20250052204A1

    公开(公告)日：2025-02-13

    申请号：US18929956

    申请日：2024-10-29

    Applicant: RTX CORPORATION

    Inventor： William G. Sheridan

    IPC: F02C7/36 ,  F01D5/02 ,  F01D15/12 ,  F01D25/16 ,  F02C3/04 ,  F02C3/107 ,  F02C7/06

    Abstract: A gas turbine engine includes a propulsor section including a propulsor having blades extending from a propulsor hub, and a propulsor shaft that drives the propulsor hub. A compressor section includes a first compressor having a rotatable compressor hub. A speed reduction device drives the compressor hub and the propulsor through a connection established axially forward of the epicyclic gear system relative to an engine longitudinal axis. The epicyclic gear system is straddled by forward and aft bearings that engage a carrier of the speed reduction device.

    MANIFOLD MIXING FEATURE
    3.
    发明申请
    MANIFOLD MIXING FEATURE 有权

    公开(公告)号：US20250027430A1

    公开(公告)日：2025-01-23

    申请号：US18356650

    申请日：2023-07-21

    Applicant: RAYTHEON TECHNOLOGIES CORPORATION

    Inventor： JEFFREY J. LIENAU ,  COURTNEY LANA PRUETTE ,  KEVIN M. BROWN ,  RICHARD YU ,  PAUL K. SANCHEZ

    IPC: F02C7/12 ,  F01D25/24 ,  F02C3/04

    Abstract: A gas turbine engine is provided. The gas turbine engine includes a case having a wall that provides a manifold cavity, the wall including an aperture and a bore; a tube assembly with a flange that provides a fluid passage aligned with the aperture; a mixing feature arranged in the manifold cavity and including a plate with a hole; and an insert having a body and a head, the body received in the hole and sealed in the bore, the head capturing the plate against the wall. The mixing feature is configured to divert a flow of cooling fluid in at least a counterclockwise direction improving jet mixing and placement of the cooling fluid.

    Combustor cylinder, combustor, and gas turbine
    4.
    发明授权
    Combustor cylinder, combustor, and gas turbine 有权

    公开(公告)号：US12203659B2

    公开(公告)日：2025-01-21

    申请号：US18229968

    申请日：2023-08-03

    Applicant: MITSUBISHI HEAVY INDUSTRIES, LTD.

    Inventor： Geoffrey D. Myers ,  Kenji Miyamoto

    IPC: F23R3/28 ,  F02C3/04

    Abstract: A combustor cylinder includes a cylinder, and a fuel nozzle capable of injecting fuel into a combustion space of the cylinder. The cylinder has a plurality of cooling passages allowing cooling air to circulate therethrough, and a nozzle attachment penetration hole penetrating the cylinder from an outer circumferential surface of the cylinder to an inner circumferential surface of the cylinder. The fuel nozzle has a mixing passage, a fuel passage communicating with the mixing passage and capable of supplying the fuel to the inside of the mixing passage, and a connection passage communicating with the mixing passage and capable of supplying cooling air from a part of the plurality of cooling passages to the inside of the mixing passage. A position in the mixing passage communicating with the connection passage is on a side where a spout port of the mixing passage is present from a position where the mixing passage communicates with the fuel passage.

    Bearing configuration for a rotational equipment assembly
    5.
    发明授权
    Bearing configuration for a rotational equipment assembly 有权

    公开(公告)号：US12203413B1

    公开(公告)日：2025-01-21

    申请号：US18215957

    申请日：2023-06-29

    Applicant: Raytheon Technologies Corporation

    Inventor： Paul R. Hanrahan

    IPC: F02C7/06 ,  F01D25/16 ,  F01D25/22 ,  F02C3/04 ,  F16C17/02

    Abstract: An assembly for rotational equipment includes a shaft, a first rolling-element bearing, a second rolling-element bearing, and a mid-shaft foil bearing. The shaft extends along a rotational axis between and to a first axial end and a second axial end. The shaft is configured for rotation about the rotational axis. The first rolling-element bearing is disposed at the first axial end. The second rolling-element bearing is disposed at the second axial end. The mid-shaft foil bearing is disposed axially between the first rolling-element bearing and the second rolling-element bearing.

    Engine controller for a gas turbine engine
    6.
    发明授权
    Engine controller for a gas turbine engine 有权

    公开(公告)号：US12203411B2

    公开(公告)日：2025-01-21

    申请号：US18343954

    申请日：2023-06-29

    Applicant: General Electric Company

    Inventor： Harry Kirk Mathews, Jr. ,  William Morton ,  Constantinos Minas

    IPC: F01D25/24 ,  F02C3/04 ,  F02C7/00

    Abstract: A gas turbine engine is provided having: a turbomachine; a fan section having a fan rotatable by the turbomachine; a nacelle enclosing the fan; and an engine controller positioned within the nacelle. The nacelle defines an inner surface radius (r) along the radial direction inward of the engine controller, wherein the engine controller defines a radial height (Δr) along the radial direction, a total volume (V), and a normalized radius (r′). The normalized radius (r′) is a ratio of the inner surface radius (r) to the total volume (V) to cube root, and wherein these parameters are related by the following equation: 0.1(r′)−1

    GAS TURBINE ENGINE COMPRESSOR ARRANGEMENT
    8.
    发明申请
    GAS TURBINE ENGINE COMPRESSOR ARRANGEMENT 有权

    公开(公告)号：US20240410320A1

    公开(公告)日：2024-12-12

    申请号：US18808243

    申请日：2024-08-19

    Applicant: RTX CORPORATION

    Inventor： Karl L. Hasel ,  Joseph B. Staubach ,  Brian D. Merry ,  Gabriel L. Suciu ,  Christopher M. Dye

    IPC: F02C7/36 ,  F02C3/04 ,  F02C3/06 ,  F02C3/107 ,  F02K3/02 ,  F02K3/06

    Abstract: A gas turbine engine includes, among other things, a propulsor section including a propulsor, a core engine, a gear arrangement that drives the propulsor. A compressor section includes a low pressure compressor and a high pressure compressor. A turbine section includes a high pressure turbine and a low pressure turbine. An overall pressure ratio is provided by the combination of a pressure ratio across the low pressure compressor and a pressure ratio across the high pressure compressor, and greater than 40. The pressure ratio across the high pressure compressor is between 7 and 15, and the pressure ratio across the low pressure compressor is between 4 and 8.

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