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    GAS TURBINE ENGINE WITH AXIAL COMPRESSOR WITH INTERNAL COOLING PATHWAYS
    1.
    发明申请
    GAS TURBINE ENGINE WITH AXIAL COMPRESSOR WITH INTERNAL COOLING PATHWAYS 有权
    具有内部冷却路径的轴向压缩机的气体涡轮发动机

    公开(公告)号：US20160032767A1

    公开(公告)日：2016-02-04

    申请号：US14788089

    申请日：2015-06-30

    Applicant: United Technologies Corporation

    Inventor： James Hill ,  Brian Merry ,  Gabriel Suciu

    IPC: F01D25/14 ,  F02C7/18

    CPC classification number: F01D25/14 ,  F01D5/084 ,  F02C7/12 ,  F02C7/18 ,  F04D29/321 ,  F04D29/584 ,  Y02T50/673 ,  Y02T50/676

    Abstract: A gas turbine engine may include an axial high pressure compressor having an air flow pathway positioned between the inner and outer rim of the rotor section. The air flow pathway includes an inlet port, a transition segment, an axial segment, and an outlet port. The pathway may be a tube having an ovoid cross sectional shape and is substantially co-planar to the outer surface of the outer rim. The pathway may traverse the rotor section from the first rotor segment to the rear hub.

    Abstract translation: 燃气涡轮发动机可以包括轴向高压压缩机，其具有位于转子部分的内缘和外缘之间的空气流动路径。 空气流动路径包括入口端口，过渡段，轴向段和出口端口。 该通道可以是具有卵形横截面形状并且与外缘的外表面基本上共面的管。 该路径可以从第一转子段到后轮毂穿过转子部分。

    GAS TURBINE ENGINE AXIAL COMPRESSOR REAR HUB
    5.
    发明申请
    GAS TURBINE ENGINE AXIAL COMPRESSOR REAR HUB 有权
    气体涡轮发动机轴压缩机后排

    公开(公告)号：US20160032726A1

    公开(公告)日：2016-02-04

    申请号：US14793479

    申请日：2015-07-07

    Applicant: United Technologies Corporation

    Inventor： James Hill ,  Brian Merry ,  Gabriel Suciu

    IPC: F01D5/08 ,  F01D11/00

    CPC classification number: F01D5/085 ,  F01D5/084 ,  F01D11/003 ,  F01D11/005 ,  F02C7/12 ,  F02C7/28 ,  F04D29/083 ,  F04D29/321 ,  F04D29/584 ,  Y02T50/676

    Abstract: A gas turbine engine includes an axial high pressure compressor includes a rear hub disposed aft of an aft rotor segment. The rear hub includes an inner surface, an outer surface, and a sealing face, wherein the sealing face is sealingly engaged with the aft rotor segment, and in fluid communication with the cooling channel. The cooling channels are configured to delivery air to contact the inner surface of the rear hub.

    Abstract translation: 燃气涡轮发动机包括轴向高压压缩机，其包括设置在后转子部分的后方的后轮毂。 后轮毂包括内表面，外表面和密封面，其中密封面与后转子段密封接合，并与冷却通道流体连通。 冷却通道构造成输送空气以接触后轮毂的内表面。

    GAS TURBINE ENGINE AXIAL DRUM-STYLE COMPRESSOR ROTOR ASSEMBLY
    6.
    发明申请
    GAS TURBINE ENGINE AXIAL DRUM-STYLE COMPRESSOR ROTOR ASSEMBLY 有权
    气体涡轮发动机轴流式压缩机压缩机转子总成

    公开(公告)号：US20160032937A1

    公开(公告)日：2016-02-04

    申请号：US14793503

    申请日：2015-07-07

    Applicant: United Technologies Corporation

    Inventor： James Hill ,  Brian Merry ,  Gabriel Suciu

    IPC: F04D29/08 ,  F04D29/28 ,  F04D17/08

    CPC classification number: F04D29/083 ,  F01D11/005 ,  F01D11/006 ,  F04D17/08 ,  F04D17/122 ,  F04D29/284 ,  F04D29/286 ,  F05B2230/236

    Abstract: A gas turbine engine includes an axial compressor which includes a rotor assembly including a first rotor segment with a first inner rim, a first sealing surface, and a first aft engagement feature, and a second rotor segment positioned aft of the first rotor segment and having a second inner rim, a second sealing surface, and a second inner rim with a second fore engagement feature that is complementary to the first aft engagement feature. The first and second sealing surfaces are complementary to each other, and are bonded together via a transient liquid phase diffusion process. The first and second sealing surfaces are disposed on the outer rim. The first aft engagement member may be a notch that is complementary to the second fore engagement feature, which may be a shelf.

    Abstract translation: 一种燃气涡轮发动机包括轴向压缩机，其包括转子组件，该转子组件包括具有第一内缘的第一转子段，第一密封表面和第一后部接合特征，以及定位在第一转子段后面的第二转子段， 第二内边缘，第二密封表面和具有与第一后部接合特征互补的第二前部接合特征的第二内部边缘。 第一和第二密封表面彼此互补，并通过瞬态液相扩散工艺结合在一起。 第一和第二密封面设置在外缘上。 第一尾部接合构件可以是与第二前部接合特征互补的凹口，其可以是搁架。

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