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    GAS TURBINE ENGINE WITH HIGH TEMPERATURE SPOOL AND ASSOCIATED COOLING SYSTEM
    48.
    发明授权
    GAS TURBINE ENGINE WITH HIGH TEMPERATURE SPOOL AND ASSOCIATED COOLING SYSTEM 有权

    公开(公告)号：EP3045681B1

    公开(公告)日：2018-10-03

    申请号：EP16151310.6

    申请日：2016-01-14

    Applicant: United Technologies Corporation

    Inventor： MERRY, Brian D. ,  SUCIU, Gabriel L.

    IPC: F01D25/12 ,  F02C7/18 ,  F02C9/18 ,  F01D5/08

    CPC classification number: F02C9/18 ,  F01D5/082 ,  F01D5/084 ,  F01D5/088 ,  F01D25/12 ,  F02C3/10 ,  F02C7/18 ,  F05D2250/322 ,  F05D2260/20 ,  Y02T50/676

    Abstract: A gas turbine engine (20) includes a turbine section (54) that includes a turbine rotor (132) arranged in a plenum (180). A compressor section (54) includes a compressor rotor assembly (60) that has spaced apart inner and outer portions (71, 73) that provide an axially extending cooling channel (84). Compressor blades (78) extend radially outward from the outer portion (73) which provides an inner core flow path (C). A rotor spoke is configured to receive a first cooling flow (76) and fluidly connect the outer portion (73) to the cooling channel (84). The compressor rotor assembly (60) has a coolant exit (90) that is in fluid communication with the cooling channel (84). The compressor rotor assembly (60) is configured to communicate the first cooling flow (76) to the turbine rotor (132). A bleed source (91) is configured to provide a second cooling flow (190). A combustor section (56) includes an injector (120) in fluid communication with the bleed source (91). The tangential onboard injector (120) is configured to communicate the second cooling flow (190) to the turbine rotor (132).

    COMBINED DRIVE FOR COOLING AIR USING COOLING COMPRESSOR AND AIRCRAFT AIR SUPPLY PUMP
    49.
    发明公开
    COMBINED DRIVE FOR COOLING AIR USING COOLING COMPRESSOR AND AIRCRAFT AIR SUPPLY PUMP 审中-公开
    用冷却压缩机和飞机空气供给泵冷却空气的组合驱动器

    公开(公告)号：EP3239478A1

    公开(公告)日：2017-11-01

    申请号：EP17168271.9

    申请日：2017-04-26

    Applicant: United Technologies Corporation

    Inventor： SUCIU, Gabriel L. ,  MERRY, Brian D. ,  CHANDLER, Jesse M.

    IPC: F01D25/00 ,  F02C6/08 ,  F02C7/18 ,  F02C7/32 ,  F02C7/36

    CPC classification number: F02C7/185 ,  F02C3/04 ,  F02C6/08 ,  F02C7/32 ,  F02C7/36 ,  F05D2220/32 ,  Y02T50/675

    Abstract: A gas turbine engine (100) comprises a main compressor section having a high pressure compressor (108) with a downstream discharge, and more upstream locations. A turbine section has a high pressure turbine (117). A first tap (110) taps air from at least one of the more upstream locations in the compressor section, passes the tapped air through a heat exchanger (112) and then to a cooling compressor (114). The cooling compressor (114) compresses air downstream of the heat exchanger (112), and delivers air into the high pressure turbine (117). A second tap (208) taps air from the compressor section, passes the air across a cabin air pump (212), and delivers air from the cabin air pump (212) for use on an aircraft receiving the gas turbine engine (100). The cooling compressor (114) including a rotor, and the cabin air pump (212) including a rotor, and a drive (300) driven with the turbine section in turn drives both the cooling compressor rotor and the cabin air supply rotor.

    Abstract translation: 燃气涡轮发动机（100）包括主压缩机部分和更多的上游位置，主压缩机部分具有带有下游排气口的高压压缩机（108）。 涡轮机部分具有高压涡轮机（117）。 第一龙头（110）从压缩机部分的更上游位置中的至少一个中抽取空气，将抽取的空气通过热交换器（112），然后传送至冷却压缩机（114）。 冷却压缩机（114）压缩热交换器（112）下游的空气，并将空气输送到高压涡轮机（117）中。 第二龙头208从压缩机部分抽出空气，使空气穿过机舱空气泵212，并且从机舱空气泵212输送空气以用于接收燃气涡轮发动机100的飞机上。 包括转子的冷却压缩机（114）和包括转子的机舱空气泵（212）以及由该涡轮机部分驱动的驱动器（300）依次驱动冷却压缩机转子和机舱空气供给转子。

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