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    COMBUSTOR FOR GAS TURBINES
    1.
    发明公开
    COMBUSTOR FOR GAS TURBINES 审中-公开

    公开(公告)号：EP4459189A1

    公开(公告)日：2024-11-06

    申请号：EP22915941.3

    申请日：2022-12-23

    申请人： KAWASAKI JUKOGYO KABUSHIKI KAISHA

    发明人： OZAKI, Yoshihiko

    IPC分类号： F23R3/42 ,  F01D25/12 ,  F02C7/18 ,  F02C7/28 ,  F23R3/60

    摘要： A combustor of a gas turbine includes: a shell made of metal; a liner located inside the shell and made of a ceramic matrix composite, the liner including an inner surface defining a combustion chamber, an outer surface facing a side opposite to a side where the combustion chamber is located, and at least one cooling hole that is open toward the combustion chamber; and a cooling chamber defined between the shell and the liner. The shell includes a tubular shell main body and a seal wall structure projecting from an inner surface of the shell main body toward the liner.

    EXTRACTION IMPELLER FOR AXIAL COMPRESSOR
    2.
    发明公开
    EXTRACTION IMPELLER FOR AXIAL COMPRESSOR 审中-公开

    公开(公告)号：EP4455487A1

    公开(公告)日：2024-10-30

    申请号：EP24168471.1

    申请日：2024-04-04

    申请人： General Electric Technology GmbH

    发明人： SUBRAMANIYAN, Moorthi ,  KISHAN T R, Navaneeth

    IPC分类号： F04D17/02 ,  F01D25/12 ,  F04D19/02 ,  F04D29/30 ,  F04D29/32 ,  F01D5/08 ,  F02C6/08 ,  F02C7/18

    摘要： An extraction impeller (200) for an axial compressor (102) includes first vanes (210) having an elongated S-shape arranged on the surface (204) of an impeller body (202). The first vanes (210) extend radially from an outer flow inlet edge (220) of the body (202) to a flow outlet hub (222) centered on the surface (204) at the rotation axis (A). A radially inner end (224) of each of the first vanes (210) connects at the flow outlet hub (222) in a direction perpendicular to a rotation axis (A). Second vane(s) (230) are arranged between adjacent first vanes (210), and third vanes (240) are arranged between second vanes (230) and between first vanes (210) and second vanes (230). Second vanes (230) are radially longer than third vanes (240). The impeller (200) extracts air from the axial compressor (102) and forms an axial flow with reduced vortex whistle. When used in an axial compressor (102) of a gas turbine system (100), the impeller (200) reduces flow unsteadiness.

    AUGMENTED COOLING FOR BLADE TIP CLEARANCE OPTIMIZATION
    9.
    发明公开
    AUGMENTED COOLING FOR BLADE TIP CLEARANCE OPTIMIZATION 审中-公开

    公开(公告)号：EP4296473A1

    公开(公告)日：2023-12-27

    申请号：EP23181053.2

    申请日：2023-06-22

    申请人： PRATT & WHITNEY CANADA CORP.

    发明人： GOVER, Christopher ,  SYNNOTT, Remy

    IPC分类号： F01D11/24 ,  F01D25/14 ,  F01D25/26 ,  F02C7/18

    摘要： A turbine assembly (70) of an aircraft engine (10) includes a cooling system (50) for optimizing a tip clearance gap (27) defined between an inner surface (28) of a turbine housing (30) and blade tips (26) of the turbine blades (24). The cooling system (50) includes a cooling airflow passage (34) located radially outward from the turbine housing (30) and being in heat-transfer communication with the turbine housing (30). The cooling airflow passage (34) receives a flow of cooling air therethrough for cooling the turbine housing (34). A heat sink (80) is disposed on the outer surface (39) of the turbine housing (30) within the cooling airflow passage (34), the heat sink (80) including heat transfer elements projecting into the cooling airflow passage (34) away from the outer surface (29) of the turbine housing (30). The heat transfer elements are in convective heat transfer relationship with the flow of cooling air in the cooling airflow passage (34).