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    Turbine vane in gas turbine engine
    1.
    发明授权
    Turbine vane in gas turbine engine 有权

    公开(公告)号：US12116906B2

    公开(公告)日：2024-10-15

    申请号：US18269037

    申请日：2021-01-06

    Applicant: SIEMENS ENERGY GLOBAL GMBH & CO. KG

    Inventor： Daniel Joo ,  Ching-Pang Lee ,  Gm Salam Azad ,  Sin Chien Siw

    IPC: F01D9/06 ,  F01D25/12

    CPC classification number: F01D9/06 ,  F01D25/12 ,  F05D2220/32 ,  F05D2240/12 ,  F05D2260/20

    Abstract: A turbine vane in a gas turbine engine includes an inner platform, an outer platform, and a vane airfoil positioned therebetween. The vane airfoil includes a first cooling passage extending between the outer platform and the inner platform, and a second cooling passage extending between the outer platform and the inner platform. The second cooling passage is arranged downstream of the first cooling passage with respect to a flow direction. The turbine vane includes a jumper tube disposed between the second cooling passage and the inner platform. The jumper tube includes an inlet, an outlet, and a tube wall enclosing a hollow interior. The inlet is positioned a distance within the second cooling passage. The outlet is positioned at least partially through an aperture of the inner platform.

    Turbine shroud segment and its manufacture
    2.
    发明授权
    Turbine shroud segment and its manufacture 有权

    公开(公告)号：US12110801B2

    公开(公告)日：2024-10-08

    申请号：US18447740

    申请日：2023-08-10

    Applicant: Rolls-Royce plc

    Inventor： Rupert J. Taylor ,  Ngungunyana Mhlanga ,  Grant Mathieson ,  Ryan R. Allen ,  James Revell ,  Dinesh Perumalsamy ,  Carlos Javier Diaz Rodriguez

    IPC: F01D25/24 ,  F01D25/12

    CPC classification number: F01D25/24 ,  F01D25/12 ,  F05D2260/201

    Abstract: A turbine shroud segment, e.g. for a gas turbine engine, which is coolable by a supply of cooling air, e.g. from a gas turbine engine compressor. The turbine shroud segment has a segment casing that has a radially outer surface and a radially inner surface. The segment casing houses a main plenum, a first layer of impingement chambers, a second layer of impingement chambers, and a plurality of effusion passages. The first layer of impingement chambers fluidly communicates with the main plenum via transfer passages that are formed in the segment casing. The second layer of impingement chambers fluidly communicates with the first layer of impingement chambers via impingement passages that are formed in the segment casing. The effusion passages run between impingement chamber core surface, which is a radially inner surface of an impingement chamber, and the radially inner surface of the segment casing.

    Compact turbine-compressor assembly
    9.
    发明授权
    Compact turbine-compressor assembly 有权

    公开(公告)号：US11994037B2

    公开(公告)日：2024-05-28

    申请号：US17800843

    申请日：2021-02-19

    Applicant: Nathan Geoffrey Andrews

    Inventor： Nathan Geoffrey Andrews

    IPC: F01D25/12 ,  F02B39/08

    CPC classification number: F01D25/12 ,  F02B39/08 ,  F05D2220/40 ,  F05D2260/213

    Abstract: There is provided a compact turbine-compressor assembly 25. The turbine-compressor assembly 25 includes a turbine wheel 39 with one or more turbine blades 41 and a compressor wheel 47 that includes one or more compressor blades 49. The compressor wheel 47 is concentric with the turbine wheel 39. Furthermore, the compressor wheel 47 and the turbine wheel 39 are not located at opposite ends of a common axle with a medial portion of the axle distancing them apart, as is the case with prior art turbine-compressor assemblies that are known. In contrast, the turbine wheel 39 and the compressor wheel 47 are located adjacent to each other and in one embodiment they axially overlap each other so that one nests within the other to thereby provide a compact arrangement. The turbine-compressor assembly 25 includes a first fluid path 67 which is configured to convey fluid, which will typically be air, through the turbine blades 41. The turbine-compressor assembly 25 also includes a second fluid path 77 which is configured to convey fluid, which will typically be air, through the compressor blades. The turbine-compressor assembly 25 is arranged so that the first fluid path 67 is distinct from the second fluid path 77 and vice-versa.

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