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    INTERCOOLED COOLING AIR WITH HEAT EXCHANGER PACKAGING
    82.
    发明公开
    INTERCOOLED COOLING AIR WITH HEAT EXCHANGER PACKAGING 审中-公开

    公开(公告)号：EP3569841A1

    公开(公告)日：2019-11-20

    申请号：EP19173765.9

    申请日：2019-05-10

    Applicant: United Technologies Corporation

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

    IPC: F02C6/08 ,  F01D25/16 ,  F02C7/18 ,  F02K3/06 ,  F02K3/115

    Abstract: A gas turbine engine (20) includes a plurality of rotating components housed within a compressor section (24) and a turbine section (28). A tap (110) connects to the compressor section (24). A heat exchanger (112; 164; 292; 312) connects downstream of the tap (110). A cooling compressor (114; 162) connects downstream of the heat exchanger (112; 164; 292; 312), and the cooling compressor (114; 162) connects to deliver air to at least one of the rotating components. A core housing (152) has an outer peripheral surface (153) and a fan housing (154) defines an inner peripheral surface (156). At least one bifurcation duct (158, 160; 406, 408) extends between the outer peripheral surface (153) to the inner peripheral surface (156). The heat exchanger (112; 164; 292; 312) is disposed within the at least one bifurcation duct (158, 160; 406, 408).

    GAS TURBINE ENGINE COMPRESSOR ARRANGEMENT
    83.
    发明公开
    GAS TURBINE ENGINE COMPRESSOR ARRANGEMENT 审中-公开

    公开(公告)号：EP3546737A1

    公开(公告)日：2019-10-02

    申请号：EP19166650.2

    申请日：2019-04-01

    Applicant: United Technologies Corporation

    Inventor： HASEL, Karl L. ,  STAUBACH, Joseph B. ,  MERRY, Brian D. ,  SUCIU, Gabriel L. ,  DYE, Christopher M.

    IPC: F02K3/06 ,  F02C7/36 ,  F02C3/107

    Abstract: A gas turbine engine (10) includes, among other things, a fan (14; 714), a core engine, a bypass passage (58), and a bypass ratio defined as the volume of air passing into the bypass passage (58) compared to the volume of air passing into the core engine, the bypass ratio being greater than or equal to 10. A gear arrangement (62; 762) drives the fan (14; 714). A compressor section (19) includes both a low pressure compressor (18; 718) and a high pressure compressor (22). A turbine section (21) drives the gear arrangement (62; 762). An overall pressure ratio is provided by the combination of a pressure ratio across the low pressure compressor (18; 718) and a pressure ratio across the high pressure compressor (22), and greater than 50, measured at sea level and at a static, full-rated takeoff power. The pressure ratio across the high pressure compressor (22) is greater than 7.

    GAS TURBINE ENGINE CASE
    87.
    发明公开
    GAS TURBINE ENGINE CASE 审中-公开
    燃气轮机发动机壳

    公开(公告)号：EP3321476A1

    公开(公告)日：2018-05-16

    申请号：EP17204177.4

    申请日：2009-01-09

    Applicant: United Technologies Corporation

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

    IPC: F01D25/24

    CPC classification number: F01D25/24 ,  F01D25/243 ,  F01D25/246 ,  F05D2230/60 ,  Y02T50/671 ,  Y10T29/49826

    Abstract: A case (30) for a gas turbine engine includes a single-piece case (30) that includes a combustor case portion (30a) and a turbine case portion (30b) that is integrally formed with the combustor case portion (30a) as one piece (30). In one example, the single-piece case (30) includes a transition duct/mid-turbine frame case portion (30c) which is integrally formed with the combustor and turbine case portions (30a,30b).

    Abstract translation: 本发明的燃气轮机发动机壳体（30）具备：单体壳体（30），其具有燃烧器壳体部（30a）和与该燃烧器壳体部（30a）一体形成的涡轮壳体部（30b） （30）。 在一个示例中，单件式壳体30包括与燃烧器和涡轮壳体部分30a，30b一体形成的过渡导管/中间涡轮机框架壳体部分30c。

    ENGINE BLEED AIR AND COMPRESSOR SURGE MANAGEMENT
    88.
    发明公开
    ENGINE BLEED AIR AND COMPRESSOR SURGE MANAGEMENT 审中-公开
    发动机空气和压缩机喘振管理

    公开(公告)号：EP3260686A1

    公开(公告)日：2017-12-27

    申请号：EP17176981.3

    申请日：2017-06-20

    Applicant: United Technologies Corporation

    Inventor： TAYLOR, Stephen H. ,  LENTS, Charles E. ,  SUCIU, Gabriel L. ,  MERRY, Brian D. ,  CHANDLER, Jesse M.

    IPC: F02C6/08 ,  F02C7/18 ,  F02C7/32 ,  F01D25/12 ,  F02C9/18

    CPC classification number: F02C9/24 ,  F01D25/12 ,  F02C3/13 ,  F02C6/08 ,  F02C7/185 ,  F02C7/32 ,  F02C9/18 ,  F02K3/06 ,  F05D2270/301 ,  Y02T50/675

    Abstract: A gas turbine engine (20) includes a main compressor section (24). A booster compressor (72) includes an inlet (74) and an outlet (76). The inlet (74) receives airflow from the main compressor section (24) and the outlet (76) provides airflow to a pneumatic system (64). A recirculation passage (78) is between the inlet (74) and the outlet (76). A flow splitter valve (80) controls airflow between the outlet (76) and the inlet (74) through the recirculation passage (78) for controlling airflow to the pneumatic system (64) based on airflow output from the booster compressor (72). A bleed air system (100) for a gas turbine engine (20) and a method of controlling engine bleed airflow are also disclosed.

    Abstract translation: 燃气涡轮发动机（20）包括主压缩机部分（24）。 增压压缩机（72）包括入口（74）和出口（76）。 入口（74）接收来自主压缩机部分（24）的气流并且出口（76）将气流提供给气动系统（64）。 再循环通道（78）位于入口（74）和出口（76）之间。 分流阀（80）通过再循环通道（78）控制出口（76）和入口（74）之间的气流，用于基于从增压压缩机（72）输出的气流来控制流向气动系统（64）的气流。 还公开了用于燃气涡轮发动机（20）的引气系统（100）和控制发动机引气流的方法。

    INTERCOOLED COOLING AIR USING EXISTING HEAT EXCHANGER
    90.
    发明公开
    INTERCOOLED COOLING AIR USING EXISTING HEAT EXCHANGER 审中-公开
    ZWISCHENGEKÜHLTEKÜHLLUFTUNTER VERWENDUNG EINES BESTEHENDENWÄRMETAUSCHERS

    公开(公告)号：EP3121411A1

    公开(公告)日：2017-01-25

    申请号：EP16180657.5

    申请日：2016-07-21

    Applicant: United Technologies Corporation

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

    IPC: F02C6/08 ,  F02C9/18 ,  F02C7/18

    CPC classification number: F02C6/08 ,  F02C7/185 ,  F02C9/18 ,  F05D2220/3219 ,  F05D2260/211 ,  F05D2260/213 ,  Y02T50/671 ,  Y02T50/676

    Abstract: A gas turbine engine comprises a main compressor section having a high pressure compressor with a downstream discharge, and more upstream locations. A turbine section has a high pressure turbine. A tap taps air from at least one of the more upstream locations in the compressor section, passing the tapped air through a heat exchanger and then to a cooling compressor. The cooling compressor compresses air downstream of the heat exchanger, and delivers air into the high pressure turbine. The heat exchanger also receives air to be delivered to an aircraft cabin. An intercooling system for a gas turbine engine is also disclosed.

    Abstract translation: 燃气涡轮发动机包括具有下游排出口的高压压缩机和更多上游位置的主压缩机部分。 涡轮部分具有高压涡轮机。 抽头从压缩机部分中的上游位置中的至少一个抽头抽吸空气，将抽头的空气通过热交换器，然后通过冷却压缩机。 冷却压缩机压缩热交换器下游的空气，并将空气输送到高压涡轮机中。 热交换器还接收要传送到飞机机舱的空气。 还公开了一种用于燃气涡轮发动机的中间冷却系统。

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