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    INTERCOOLED COOLING AIR WITH DUAL PASS HEAT EXCHANGER
    13.
    发明申请
    INTERCOOLED COOLING AIR WITH DUAL PASS HEAT EXCHANGER 有权
    双通道热交换器的双向冷却空气

    公开(公告)号：US20160312704A1

    公开(公告)日：2016-10-27

    申请号：US14695504

    申请日：2015-04-24

    Applicant: United Technologies Corporation

    Inventor： Gabriel L. Suciu ,  Jesse M. Chandler ,  Joseph Brent Staubach ,  Brian D. Merry ,  Wesley K. Lord

    IPC: F02C7/18

    CPC classification number: F02C7/185 ,  F01D25/12 ,  F02C3/13 ,  F02C7/143 ,  F05D2210/44 ,  F05D2220/3212 ,  F05D2220/3218 ,  F05D2260/211 ,  F05D2260/213 ,  F05D2260/606 ,  Y02T50/676

    Abstract: A gas turbine engine comprises a main compressor section having a downstream most end, 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, passes the tapped air through a heat exchanger and then to a cooling compressor. The cooling compressor compresses ng air downstream of the heat exchanger, and delivers air into the high pressure turbine. The heat exchanger has at least two passes, with one of the passes passing air radially outwardly, and a second of the passes returning the air radially inwardly to the compressor. 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最末端和更上游位置的主压缩机部分。 涡轮机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，然后传递到冷却压缩机。 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。 热交换器具有至少两个通道，其中一个通道径向向外通过空气，另一个通道使空气径向向内返回到压缩机。 还公开了一种用于燃气涡轮发动机的中间冷却系统。

    INTERCOOLED COOLING AIR WITH AUXILIARY COMPRESSOR CONTROL
    14.
    发明申请
    INTERCOOLED COOLING AIR WITH AUXILIARY COMPRESSOR CONTROL 审中-公开
    具有辅助压缩机控制的隔热冷却空气

    公开(公告)号：US20160237907A1

    公开(公告)日：2016-08-18

    申请号：US14745550

    申请日：2015-06-22

    Applicant: United Technologies Corporation

    Inventor： Brian D. Merry ,  Gabriel L. Suciu ,  Jesse M. Chandler ,  Joseph Brent Staubach ,  Gary D. Roberge

    IPC: F02C7/18 ,  F02C3/04

    CPC classification number: F02C7/18 ,  F02C7/185 ,  F05D2260/213 ,  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, which compresses air downstream of the heat exchanger, and delivers air into the high pressure turbine. The cooling compressor rotates at a speed proportional to a speed of at least one rotor in the turbine section. The cooling compressor is allowed to rotate at a speed that is not proportional to a speed of the at least one rotor under certain conditions. 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的主压缩机部分和更多的上游位置。 涡轮机部分具有高压涡轮机。 分接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，使抽头的空气通过热交换器，然后到达冷却压缩机，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 。 冷却压缩机以与涡轮机部分中的至少一个转子的速度成比例的速度旋转。 允许冷却压缩机在某些条件下以与至少一个转子的速度成比例的速度旋转。 还公开了一种用于燃气涡轮发动机的中间冷却系统。

    Modifying Direct Drive Gas Turbine Engine Core to Provide a Geared Turbofan
    15.
    发明申请
    Modifying Direct Drive Gas Turbine Engine Core to Provide a Geared Turbofan 审中-公开
    改装直接驱动燃气轮机发动机内核，提供齿轮式涡轮风扇

    公开(公告)号：US20150361921A1

    公开(公告)日：2015-12-17

    申请号：US14711861

    申请日：2015-05-14

    Applicant: United Technologies Corporation

    Inventor： Frederick M. Schwarz ,  Joseph Brent Staubach

    IPC: F02K3/02 ,  F02K3/075 ,  F02K3/065

    CPC classification number: F02C7/36 ,  F02C3/107 ,  F02K3/06 ,  F05D2230/80 ,  F05D2260/4031 ,  Y10T29/49323 ,  Y10T29/49718

    Abstract: A method comprises the steps of modifying a direct drive engine, which includes a first fan rotor, a high pressure compressor driven by a high pressure turbine on a first high spool and a first low pressure turbine designed to drive a first low pressure compressor on a first low spool, and the fan rotor all at the same speed. The modifying step includes providing a second fan rotor, second low spool, including a second low pressure compressor rotor and second low pressure turbine rotor and incorporating a gear reduction between a shaft driven by the second low pressure turbine rotor and the second fan rotor to provide a geared turbofan, such that at least a portion of the design of the high pressure compressor rotor, the combustor and the high pressure turbine rotor from the designed direct drive engine are utilized in the geared turbofan. A gas turbine engine is also disclosed.

    Abstract translation: 一种方法包括以下步骤：修改直接驱动发动机，其包括第一风扇转子，由第一高阀芯上的高压涡轮机驱动的高压压缩机和设计成驱动第一低压压缩机的第一低压涡轮机 第一个低阀芯，风扇转子全部以相同的速度。 修改步骤包括提供第二风扇转子，第二低阀芯，包括第二低压压缩机转子和第二低压涡轮转子，并且在由第二低压涡轮转子驱动的轴和第二风扇转子之间并入减速齿轮，以提供 齿轮式涡扇，使得来自设计的直接驱动发动机的高压压缩机转子，燃烧器和高压涡轮机转子的设计的至少一部分被用于齿轮传动风扇。 还公开了一种燃气涡轮发动机。

    Intercooled cooled cooling integrated air cycle machine
    16.
    发明授权
    Intercooled cooled cooling integrated air cycle machine 有权

    公开(公告)号：US10794290B2

    公开(公告)日：2020-10-06

    申请号：US15806992

    申请日：2017-11-08

    Applicant: UNITED TECHNOLOGIES CORPORATION

    Inventor： Nathan Snape ,  Joseph Brent Staubach ,  Frederick M. Schwarz

    IPC: F02C6/08 ,  F02C7/18 ,  B64D13/08 ,  F02C9/18 ,  B64D13/06

    Abstract: A first cooling stage is fluidly coupled to a bleed port of a compressor to receive and cool bleed air with the air stream to produce a cool bleed air. A cooling pump receives and increases a pressure of the cool bleed air to produce a pressurized cool bleed air. A second cooling stage is fluidly coupled to the pump to receive and cool the pressurized cool bleed air to produce an intercooled cooling air. A valve is downstream of the first cooling stage, the valve selectively delivering air into a mixing chamber where it is mixed with air from a tap that is compressed to a higher pressure than the air from the bleed port, and the valve also selectively supplying air from the first cooling stage to a use on an aircraft associated with the gas turbine engine. A method is also disclosed.

    INTERCOOLED COOLING AIR WITH DUAL PASS HEAT EXCHANGER
    19.
    发明申请
    INTERCOOLED COOLING AIR WITH DUAL PASS HEAT EXCHANGER 审中-公开

    公开(公告)号：US20180066587A1

    公开(公告)日：2018-03-08

    申请号：US15807911

    申请日：2017-11-09

    Applicant: United Technologies Corporation

    Inventor： Gabriel L. Suciu ,  Jesse M. Chandler ,  Joseph Brent Staubach ,  Brian D. Merry ,  Wesley K. Lord

    IPC: F02C7/18 ,  F02C3/13 ,  F02C7/143 ,  F01D25/12

    Abstract: A gas turbine engine comprises a main compressor section having a downstream most end, 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, passes the tapped air through a heat exchanger and then to a cooling compressor. The cooling compressor compresses ng air downstream of the heat exchanger, and delivers air into the high pressure turbine. The heat exchanger has at least two passes, with one of the passes passing air radially outwardly, and a second of the passes returning the air radially inwardly to the compressor. An intercooling system for a gas turbine engine is also disclosed.

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