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    INTERCOOLED COOLING AIR USING COOLING COMPRESSOR AS STARTER
    22.
    发明申请
    INTERCOOLED COOLING AIR USING COOLING COMPRESSOR AS STARTER 审中-公开
    使用冷却压缩机作为起动机的隔热冷却空气

    公开(公告)号：US20160237909A1

    公开(公告)日：2016-08-18

    申请号：US14837009

    申请日：2015-08-27

    Applicant: United Technologies Corporation

    Inventor： Nathan Snape ,  Gabriel L. Suciu ,  Brian D. Merry

    IPC: F02C7/18 ,  F02K3/075 ,  F02K3/065 ,  F02C3/04 ,  F02K3/02

    CPC classification number: F02C7/185 ,  F02C3/04 ,  F02C6/08 ,  F02C7/277 ,  F02C7/32 ,  F02K3/025 ,  F02K3/065 ,  F02K3/075 ,  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, passes 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 cooling compressor is connected to be driven with at least one rotor in the main compressor section. A source of pressurized air is selectively sent to the cooling compressor to drive a rotor of the cooling compressor to rotate, and to in turn drive the at least one rotor of the main compressor section at start-up of the gas turbine engine. An intercooling system 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。 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。 冷却压缩机被连接以在主压缩机部分中用至少一个转子驱动。 加压空气源被选择性地送到冷却压缩机以驱动冷却压缩机的转子旋转，并且在燃气涡轮发动机起动时又驱动主压缩机段的至少一个转子。 还公开了一种中间冷却系统。

    INTERCOOLED COOLING AIR USING EXISTING HEAT EXCHANGER
    23.
    发明申请
    INTERCOOLED COOLING AIR USING EXISTING HEAT EXCHANGER 审中-公开
    使用现有热交换器的干式冷却空气

    公开(公告)号：US20160237908A1

    公开(公告)日：2016-08-18

    申请号：US14804534

    申请日：2015-07-21

    Applicant: United Technologies Corporation

    Inventor： Nathan Snape ,  Gabriel L. Suciu ,  Brian D. Merry ,  Jesse M. Chandler

    IPC: F02C7/18

    CPC classification number: F02C6/08 ,  F02C7/143 ,  F02C7/185 ,  F02C7/32 ,  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。 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，使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。

    SYSTEM AND APPARATUS FOR DIVERSIFIED GEARBOX
    24.
    发明申请
    SYSTEM AND APPARATUS FOR DIVERSIFIED GEARBOX 有权
    用于分散式齿轮箱的系统和装置

    公开(公告)号：US20160201567A1

    公开(公告)日：2016-07-14

    申请号：US14596692

    申请日：2015-01-14

    Applicant: United Technologies Corporation

    Inventor： Hung Duong ,  Nathan Snape ,  Gabriel L. Suciu

    IPC: F02C7/32 ,  F16H57/038 ,  F02C3/04 ,  F16H57/025

    CPC classification number: F02C7/32 ,  F01D15/12 ,  F02C3/04 ,  F02C7/36 ,  F05D2250/11 ,  F05D2250/314 ,  F05D2260/4031 ,  F05D2260/532 ,  F16H1/222 ,  F16H57/02 ,  F16H57/025 ,  F16H57/038

    Abstract: A gas turbine engine assembly comprising, a gearbox including a first housing that includes a first auxiliary gear drive on a first portion thereof, a second housing that includes a second auxiliary gear drive on a second portion thereof, and a third housing that includes a third auxiliary gear drive on a third portion thereof, the housings being interconnected so that the first portion of the first housing, the second portion of the second housing and the third portion of the third housing form a substantially triangular polyhedron shape, with the second portion of the second housing disposed between the first portion of the first housing and the third portion of the third housing. The first auxiliary gear drive, the second auxiliary gear drive and the third auxiliary gear drive project outwardly in mutually divergent directions.

    Abstract translation: 一种燃气涡轮发动机组件，包括：齿轮箱，包括第一壳体，所述第一壳体在其第一部分上包括第一辅助齿轮传动;第二壳体，其在其第二部分上包括第二副齿轮传动;第三壳体，包括第三壳体， 辅助齿轮传动在其第三部分上，所述壳体互连，使得第一壳体的第一部分，第二壳体的第二部分和第三壳体的第三部分形成大致三角形的多面体形状，第二部分 所述第二壳体设置在所述第一壳体的所述第一部分和所述第三壳体的第三部分之间。 第一辅助齿轮传动装置，第二辅助齿轮传动装置和第三辅助齿轮传动装置在相互发散的方向上向外突出。

    MULTI-BYPASS STREAM GAS TURBINE ENGINE WITH ENLARGED BYPASS FLOW AREA
    25.
    发明申请
    MULTI-BYPASS STREAM GAS TURBINE ENGINE WITH ENLARGED BYPASS FLOW AREA 审中-公开
    多旁路流量涡轮发动机，带有大气旁路流域

    公开(公告)号：US20150152789A1

    公开(公告)日：2015-06-04

    申请号：US14534318

    申请日：2014-11-06

    Applicant: United Technologies Corporation

    Inventor： Michael R. Thomas ,  Nathan Snape

    IPC: F02C9/18 ,  F02C3/04

    CPC classification number: F02C9/18 ,  F02C7/14 ,  F02C7/141 ,  F02C7/185 ,  F02C7/32 ,  F02K3/00 ,  F02K3/02 ,  F02K3/025 ,  F02K3/04 ,  F02K3/077

    Abstract: A gas turbine engine comprises a first bypass flow path housing configured within the engine, radially exterior to an engine core housing, and a second bypass flow path housing configured within the engine, radially exterior to the first bypass flow path housing. An axially downstream portion of the first bypass flow path housing includes a stepwise increase in area compared with an axially adjacent upstream portion of the first bypass flow path housing, thereby defining a component placement cavity in the axially downstream portion.

    Abstract translation: 燃气涡轮发动机包括构造在发动机内部的发动机内部的第一旁通流动路径壳体，以及配置在发动机内部的第一旁通流动路径壳体的径向外部的第二旁通流动路径壳体。 第一旁路流路壳体的轴向下游部分包括与第一旁通流路壳体的轴向相邻的上游部分相比逐渐增加的面积，从而在轴向下游部分中限定部件放置空腔。

    Aircraft thermal management system
    26.
    发明授权
    Aircraft thermal management system 有权

    公开(公告)号：US11156161B2

    公开(公告)日：2021-10-26

    申请号：US16111870

    申请日：2018-08-24

    Applicant: United Technologies Corporation

    Inventor： Nathan Snape ,  James D. Hill ,  Gabriel L. Suciu ,  Brian Merry

    IPC: F02C7/14

    Abstract: An aircraft thermal management system includes a first fluid system containing a first fluid, a fluid loop containing a thermally neutral heat transfer fluid, a second fluid system containing a second fluid, a first heat exchanger configured to transfer heat from the first fluid to the thermally neutral heat transfer fluid, and a second heat exchanger configured to transfer heat from the thermally neutral heat transfer fluid to the second fluid. The fluid loop is configured to provide the thermally neutral heat transfer fluid to the first heat exchanger at a pressure that matches the pressure of the first fluid.

    Intercooled cooling air heat exchanger arrangement
    27.
    发明授权
    Intercooled cooling air heat exchanger arrangement 有权

    公开(公告)号：US11073085B2

    公开(公告)日：2021-07-27

    申请号：US15346169

    申请日：2016-11-08

    Applicant: United Technologies Corporation

    Inventor： Joseph B. Staubach ,  Nathan Snape

    IPC: F02C7/18 ,  F02C3/04 ,  F02C9/18 ,  F02K3/077

    Abstract: An intercooled cooling system for a gas turbine engine is provided. The intercooled cooling system includes a plurality of cooling stages in fluid communication with an air stream utilized for cooling. A first cooling stage of the plurality of cooling stages is fluidly coupled to a bleed port of a compressor of the gas turbine engine to receive and cool bleed air with the air stream to produce a cool bleed air. The intercooled cooling system also includes a pump fluidly coupled to the first cooling stage to receive the cool bleed air and increase a pressure of the cool bleed air to produce a pressurized cool bleed air. A second cooling stage of the plurality of cooling stages is fluidly coupled to the pump to receive and cool the pressurized cool bleed air to produce an intercooled cooling air, which is provided to the gas turbine engine.

    Intercooled cooled cooling integrated air cycle machine
    28.
    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.

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