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    COMPLEX AIR SUPPLY SYSTEM FOR GAS TURBINE ENGINE AND ASSOCIATED AIRCRAFT
    4.
    发明公开
    COMPLEX AIR SUPPLY SYSTEM FOR GAS TURBINE ENGINE AND ASSOCIATED AIRCRAFT 审中-公开

    公开(公告)号：EP3489488A1

    公开(公告)日：2019-05-29

    申请号：EP18208970.6

    申请日：2018-11-28

    申请人： United Technologies Corporation

    发明人： STAUBACH, Joseph Brent ,  SNAPE, Nathan ,  SCHWARZ, Frederick M. ,  LENTS, Charles E. ,  IKEDA, Michael K.

    IPC分类号： F02C7/14 ,  F02C7/18 ,  F02C7/32 ,  F02C7/224

    摘要： A lower pressure tap (46) is connected to a first heat exchanger (48) to be cooled by cooling air, and then to a selection valve (52). The selection valve (52) selectively delivers the lower pressure tap air to a boost compressor (44). The lower pressure tap air downstream of the boost compressor (44) is connected to cool the at least one turbine (32). The selection valve (52) also selectively delivers a portion of the lower pressure tap air across a first cooling turbine (78), and to a line (79) associated with an air delivery system for a cabin (80) on an associated aircraft. A portion of the air downstream of the first cooling turbine (78) is connected to a second cooling turbine (84), and air downstream of the second cooling turbine (84) is connected for use in a cold loop (88).

    INTERCOOLED COOLED COOLING INTEGRATED AIR CYCLE MACHINE
    5.
    发明公开
    INTERCOOLED COOLED COOLING INTEGRATED AIR CYCLE MACHINE 审中-公开

    公开(公告)号：EP3483418A1

    公开(公告)日：2019-05-15

    申请号：EP18205264.7

    申请日：2018-11-08

    申请人： United Technologies Corporation

    发明人： SNAPE, Nathan ,  STAUBACH, Joseph Brent ,  SCHWARZ, Frederick M.

    IPC分类号： F02K3/115 ,  F02C6/08 ,  F02C7/143 ,  F02C7/18

    摘要： A first cooling stage (210) is fluidly coupled to a bleed port (145) of a compressor (24) to receive and cool bleed air with the air stream (275) to produce a cool bleed air. A cooling pump (105) receives and increases a pressure of the cool bleed air to produce a pressurized cool bleed air. A second cooling stage (215) is fluidly coupled to the pump (105) to receive and cool the pressurized cool bleed air to produce an intercooled cooling air. A valve (196) is downstream of the first cooling stage (210), the valve selectively delivering air into a mixing chamber (180) where it is mixed with air from a tap (165) that is compressed to a higher pressure than the air from the bleed port (145), and the valve (196) also selectively supplying air from the first cooling stage (210) to a use (290) on an aircraft associated with the gas turbine engine (20).

    COOLED COOLING AIR SYSTEM HAVING SHUTOFF VALVE AND PROPULSOR
    6.
    发明公开
    COOLED COOLING AIR SYSTEM HAVING SHUTOFF VALVE AND PROPULSOR 审中-公开

    公开(公告)号：EP3483411A1

    公开(公告)日：2019-05-15

    申请号：EP18205748.9

    申请日：2018-11-12

    申请人： United Technologies Corporation

    发明人： SCHWARZ, Frederick M. ,  HERRING, Neal R.

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

    摘要： A gas turbine engine includes a fan rotor, a compressor aft of the fan rotor, a combustor aft of the compressor, and a turbine section aft of the combustor, the turbine section configured to drive the compressor section and the fan rotor. A cooling air system includes an input connected to a compressed air tap, an output connected to at least the turbine section, and a heat exchanger having a first path and a second path. The first path is disposed between the input and the output. A valve and a propulsor are disposed along a lower pressure cooling air path. The heat exchanger second path is in fluid communication with at least a portion of the lower pressure cooling air path. The valve is configured to control flow within the heat exchanger second path.

    COOLED GAS TURBINE ENGINE COOLING AIR WITH COLD AIR DUMP
    10.
    发明公开
    COOLED GAS TURBINE ENGINE COOLING AIR WITH COLD AIR DUMP 审中-公开

    公开(公告)号：EP3348812A1

    公开(公告)日：2018-07-18

    申请号：EP18152098.2

    申请日：2018-01-17

    申请人： United Technologies Corporation

    发明人： SCHWARZ, Frederick M. ,  SNAPE, Nathan

    IPC分类号： F02C7/18 ,  F02C7/36

    CPC分类号： F02C7/185 ,  F01D25/28 ,  F02C3/04 ,  F02C7/08 ,  F02C7/16 ,  F02C7/18 ,  F02C7/36 ,  F02C9/18 ,  F05D2260/213 ,  Y02T50/675

    摘要： A high pressure compressor (110) has a downstream most end (119). A housing (106) surrounds the compressor section and a turbine section. A low pressure turbine (116) has a downstream most end. A first tap (124) selectively taps high pressure cooling air from a location downstream of the downstream most end (119) in the high pressure compressor (110) and passes the high pressure cooling air through a heat exchanger (128). A second tap (118) taps compressed air from a location upstream of the downstream most end (119) in the high pressure compressor (110), and passes air over the heat exchanger (128), cooling the high pressure cooling air. A chamber (122) is defined between the core engine housing (106) and a nacelle (104) airflow wall, and the second tap air flows through the chamber (122). The second tap air moves from the chamber (122) into a core engine flow (C) at a location (134;140;142) downstream of the downstream most end of the low pressure turbine (116).