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    GAS TURBINE ENGINE BUFFER SYSTEM
    1.
    发明申请
    GAS TURBINE ENGINE BUFFER SYSTEM 审中-公开
    气体涡轮发动机缓冲系统

    公开(公告)号：WO2013115971A2

    公开(公告)日：2013-08-08

    申请号：PCT/US2013021513

    申请日：2013-01-15

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： MUNSELL PETER M ,  STRIPINIS PHILIP S

    IPC: F02C6/08

    CPC classification number: F02C6/08 ,  F01D11/04 ,  F01D11/06 ,  F01D25/125 ,  F02C7/06 ,  F02C7/28 ,  F02C9/18 ,  F05D2260/601 ,  Y02T50/675 ,  Y10T29/49323

    Abstract: A gas turbine engine includes a buffer system that can communicate a buffer supply air to a portion of the gas turbine engine. The buffer system includes a first bleed air supply having a first pressure, a second bleed air supply having a second pressure that is greater than the first pressure, and an ejector that selectively augments the first bleed air supply to prepare the buffer supply air for communication to the portion of the gas turbine engine.

    Abstract translation: 燃气涡轮发动机包括缓冲系统，该缓冲系统可将缓冲器供给空气传送到燃气涡轮发动机的一部分。 缓冲系统包括具有第一压力的第一排气源，具有大于第一压力的第二压力的第二排放空气源，以及选择性地增加第一排气供应以准备用于通信的缓冲器供应空气的喷射器 到燃气涡轮发动机的部分。

    BUFFER SYSTEM THAT COMMUNICATES BUFFER SUPPLY AIR TO A PORTION OF A GAS TURBINE ENGINE
    6.
    发明公开
    BUFFER SYSTEM THAT COMMUNICATES BUFFER SUPPLY AIR TO A PORTION OF A GAS TURBINE ENGINE 有权
    PUFFERSYSTEM ZUR KOMMUNIKATION VON PUFFERZULUFT ZU EINEM TEIL EINES GASTURBINENTRIEBWERKS

    公开(公告)号：EP2809917A4

    公开(公告)日：2015-08-19

    申请号：EP13796350

    申请日：2013-01-16

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： MUNSELL PETER M ,  STRIPINIS PHILIP S

    IPC: F02C7/06 ,  F01D25/12 ,  F01D25/18 ,  F02C6/04 ,  F02C6/08 ,  F02C7/18 ,  F02G3/00

    CPC classification number: F02C6/08 ,  F01D25/125 ,  F01D25/183 ,  F02C7/18 ,  F05D2260/20 ,  F05D2270/335 ,  Y02T50/676

    Abstract: A gas turbine engine (20) includes a buffer system (60; 160; 260) that communicates a buffer supply air (62; 162; 262A, 262B) to a portion of the gas turbine engine (20). The buffer system (60; 160; 260) includes a first bleed air supply (64; 164; 264A, 264B) having a first pressure, a second bleed air supply (66; 166; 266A, 266B) having a second pressure that is greater than the first pressure, and a valve that selects between the first bleed air supply (64; 164; 264A, 264B) and the second bleed air supply (66; 166; 266A, 266B) to communicate the buffer supply air (62; 162; 262A, 262B) to the portion of the gas turbine engine (20).

    Abstract translation: 燃气涡轮发动机包括将缓冲器供给空气与燃气涡轮发动机的一部分连通的缓冲系统。 缓冲系统包括具有第一压力的第一排气源，具有大于第一压力的第二压力的第二排放空气源，以及在第一排气供应源和第二排气供应件之间进行选择以连通的阀 缓冲器向燃气涡轮发动机的部分供应空气。

    HIGH PRESSURE TURBINE COOLANT SUPPLY SYSTEM
    7.
    发明公开
    HIGH PRESSURE TURBINE COOLANT SUPPLY SYSTEM 审中-公开
    冷却液供给系统高压涡轮

    公开(公告)号：EP2855884A4

    公开(公告)日：2016-05-11

    申请号：EP13797827

    申请日：2013-05-15

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： MOSLEY JOHN H ,  ALVANOS IOANNIS ,  STRIPINIS PHILIP S ,  FREIBERG DOUGLAS PAUL ,  PINERO HECTOR M ,  O'CONNOR JOHN J ,  PIETROBON JON

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

    CPC classification number: F01D5/082 ,  F01D25/12

    Abstract: A gas turbine engine configured to rotate in a circumferential direction about an axis extending through a center of the gas turbine engine comprises a turbine stage. The turbine stage comprises a disk, a plurality of blades and a mini-disk. The disk comprises an outer diameter edge having slots, an inner diameter bore surrounding the axis, a forward face, and an aft face. The plurality of blades is coupled to the slots. The mini-disk is coupled to the aft face of the rotor to define a cooling plenum therebetween in order to direct cooling air to the slots. In one embodiment of the invention, the cooling plenum is connected to a radially inner compressor bleed air inlet through all rotating components so that cooling air passes against the inner diameter bore.

    BUFFER SYSTEM FOR A GAS TURBINE ENGINE
    9.
    发明公开
    BUFFER SYSTEM FOR A GAS TURBINE ENGINE 审中-公开
    缓冲系统的燃气涡轮发动机

    公开(公告)号：EP2809907A4

    公开(公告)日：2015-10-28

    申请号：EP13768600

    申请日：2013-01-09

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： MUNSELL PETER M ,  STRIPINIS PHILIP S

    IPC: F02C6/08 ,  F01D25/18 ,  F01D25/22 ,  F02C7/16 ,  F02C7/18

    CPC classification number: F02C7/18 ,  F01D25/183 ,  F01D25/22 ,  F02C6/08 ,  F02C7/185 ,  Y02T50/675 ,  Y10T29/49359

    Abstract: A buffer system for a gas turbine engine includes a heat exchanger having a first inlet and outlet and a second inlet and outlet. The first outlet is configured to provide a cooled pressurized fluid. First and second air sources are selectively fluidly coupled to the first inlet. A third air source is fluidly coupled to the second inlet. Multiple fluid-supplied areas are located remotely from one another and are fluidly coupled to the first outlet. The multiple fluid-supplied areas include multiple bearing compartments. A method of providing pressurized air in a gas turbine engine includes selectively providing pressurized air from multiple air sources to a heat exchanger to cool the pressurized air. The cooled pressurized air is distributed to multiple fluid-supplied areas within the gas turbine engine.

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