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    Gas turbine engine component having an airfoil with internal cross-ribs
    1.
    发明授权
    Gas turbine engine component having an airfoil with internal cross-ribs 有权

    公开(公告)号：US12196095B2

    公开(公告)日：2025-01-14

    申请号：US18071121

    申请日：2022-11-29

    Applicant: Raytheon Technologies Corporation

    Inventor： James T. Roach ,  Jonas Banhos ,  Russell Kim

    IPC: F01D25/12 ,  F01D5/18 ,  F01D9/02

    Abstract: A gas turbine engine component includes an airfoil body extending between a leading edge and a trailing edge and having a suction wall and a pressure wall. An outer surface of the airfoil body is formed by an outer coat defining around the pressure and suction sides, a leading edge and a trailing edge. An internal cross-rib is formed within a cavity in the airfoil body. The internal cross-rib extends to be secured to the outer coat adjacent the leading edge and the trailing edge, and extending across the internal cavity to form a junction such that the cross-rib is x-shaped. The outer coat and the cross-rib are formed of ceramic matrix composites. A gas turbine engine is also disclosed.

    TURBINE ENGINE WITH COMPOSITE AIRFOILS
    3.
    发明申请
    TURBINE ENGINE WITH COMPOSITE AIRFOILS 有权

    公开(公告)号：US20240392689A1

    公开(公告)日：2024-11-28

    申请号：US18792961

    申请日：2024-08-02

    Applicant: General Electric Company

    Inventor： Nicholas Joseph Kray ,  Arthur William Sibbach

    IPC: F01D5/28 ,  F01D9/02 ,  F01D25/00

    Abstract: A turbine engine includes a fan and a turbomachine defining an engine centerline. The turbomachine includes a compressor section, a combustion section, and a turbine section in serial flow order. The turbine engine also includes a set of composite airfoils circumferentially arranged about the engine centerline. An airfoil in the set of composite airfoils including a composite portion extending chordwise between a composite leading edge and a trailing edge and a leading edge protector coupled to the composite portion.

    Cylinder head with integrated turbocharger
    5.
    发明授权
    Cylinder head with integrated turbocharger 有权

    公开(公告)号：US12078078B2

    公开(公告)日：2024-09-03

    申请号：US17953514

    申请日：2022-09-27

    Applicant: FCA US LLC

    Inventor： Douglas Trudeau ,  Michael P Schmidt ,  Philip J Insalaco ,  Brian Jacobs ,  Phillip Bunker ,  Matthew T Barker

    IPC: F01D25/24 ,  F01D9/02 ,  F02F1/24

    CPC classification number: F01D25/243 ,  F01D9/026 ,  F02F1/24 ,  F05D2220/40 ,  F05D2230/21 ,  F05D2240/14 ,  F05D2240/15 ,  F05D2250/14 ,  F05D2260/98

    Abstract: A cylinder head assembly for an internal combustion engine includes a cast cylinder head, a turbocharger housing including a compressor housing and turbine housing integrally cast with the cylinder head, and a turbocharger cartridge assembly configured to be inserted into the turbocharger housing and including a shaft coupled between a compressor wheel and a turbine wheel. A compressor cover is configured to couple to the compressor housing and define a compressor inlet and at least partially define a compressor diffuser passage. The cartridge assembly includes a housing having a diffuser flange extending outwardly therefrom, the diffuser flange including a front surface and an opposite contoured volute surface. The compressor diffuser passage is at least partially defined by the compressor cover and the diffuser flange front surface. A compressor volute is at least partially defined by the diffuser flange contoured volute surface and a contoured inner surface of the compressor housing.

    Turbocharger turbine housing
    7.
    发明授权
    Turbocharger turbine housing 有权

    公开(公告)号：US12060804B2

    公开(公告)日：2024-08-13

    申请号：US17485463

    申请日：2021-09-26

    Applicant: Garrett Transportation I Inc.

    Inventor： Karel Mizerovsky ,  Pavel Stepanek ,  Jan Klement ,  Adam Ohnút

    IPC: F01D25/24 ,  F01D9/02

    CPC classification number: F01D25/24 ,  F01D9/02 ,  F05D2220/40 ,  F05D2230/21 ,  F05D2250/38

    Abstract: A turbine housing can include a bearing housing end and a treatment unit end; a volute wall that defines a volute; a wall that defines at least a portion of a turbine wheel space that defines a turbine wheel space axis and a turbine wheel space diameter, where the wall extends to an axial peak to define an extended space with an extended space outlet having an extended space outlet dimension; and an outlet wall that defines an outlet space with a treatment unit end outlet having an outlet dimension, where the extended space is disposed at least in part axially between the turbine wheel space and the outlet space to increase axial velocity uniformity at the treatment unit end outlet.

    Scroll structure of centrifugal compressor and centrifugal compressor
    9.
    发明授权
    Scroll structure of centrifugal compressor and centrifugal compressor 有权

    公开(公告)号：US12031548B2

    公开(公告)日：2024-07-09

    申请号：US17623054

    申请日：2019-07-16

    Applicant: MITSUBISHI HEAVY INDUSTRIES ENGINE & TURBOCHARGER, LTD.

    Inventor： Kenichiro Iwakiri

    IPC: F04D29/44 ,  F01D9/02 ,  F02B39/00 ,  F04D29/42

    CPC classification number: F04D29/441 ,  F01D9/026 ,  F02B39/00 ,  F04D29/4206 ,  F05D2220/40 ,  F05D2240/14 ,  F05D2250/52

    Abstract: A scroll structure of a centrifugal compressor includes, of a flow passage connection section where a scroll start portion and a scroll end portion of a scroll flow passage intersect, a connection region where a first inner circumferential surface of the scroll end portion in the centrifugal compressor and a second inner circumferential surface of the scroll start portion in the centrifugal compressor are connected. The connection region includes a turning start point where a direction starts to change from the first inner circumferential surface toward the second inner circumferential surface, and a turning end point where the change in direction from the first inner circumferential surface toward the second inner circumferential surface comes to an end. Where a cross-section orthogonal to an extension direction of a center line of the scroll flow passage in the connection region is a first cross-section, the turning start point on the first cross-section is a first turning start point, a turning end point on the first cross-section is a first turning end point, and a tangent line to the first inner circumferential surface passing through the first turning start point on the first cross-section is a first direction, the first turning start point exists at a position away from the first turning end point along the first direction by a distance not less than 30% of a height dimension along an axial direction of the centrifugal compressor at a minimum cross-sectional area position of the scroll flow passage.

    FLUID DUCTS INCLUDING A RIB
    10.
    发明公开
    FLUID DUCTS INCLUDING A RIB 审中-公开

    公开(公告)号：US20240191630A1

    公开(公告)日：2024-06-13

    申请号：US18105393

    申请日：2023-02-03

    Applicant: General Electric Company

    Inventor： Nishita Deshmukh ,  Deepak Ghiya ,  Reddi Hari Prasad Reddy Mylapalli

    IPC: F01D9/02 ,  F01D25/12

    CPC classification number: F01D9/023 ,  F01D25/12 ,  F05D2260/22141

    Abstract: A fluid duct includes a body and an elongate rib. The body extends along a central axis and defines a lumen configured to receive a first fluid extending therethrough. The body has an inner surface and an outer surface. The central axis defines an axial direction along the central axis, a radial direction perpendicular to the central axis, and a circumferential direction oriented rotationally about the central axis. The elongate rib is positioned on the inner surface of the body and extends radially inward from the inner surface of the body. The elongate rib defines a channel extending through the elongate rib in a primary direction. The channel is configured to receive a second fluid and isolate the second fluid from the first fluid.

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