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    GAS TURBINE ENGINE WITH LOW STAGE COUNT LOW PRESSURE TURBINE
    141.
    发明公开
    GAS TURBINE ENGINE WITH LOW STAGE COUNT LOW PRESSURE TURBINE 审中-公开
    燃气轮机发动机低台数低压涡轮机

    公开(公告)号：EP2776318A1

    公开(公告)日：2014-09-17

    申请号：EP12863186.8

    申请日：2012-12-31

    申请人： United Technologies Corporation

    发明人： SUCIU, Gabriel L. ,  MERRY, Brian D. ,  DYE, Christopher, M. ,  JOHNSON, Steven B. ,  SCHWARZ, Frederick M.

    IPC分类号： B64D27/10

    CPC分类号： B64D27/26 ,  B64D2027/264 ,  B64D2027/266 ,  F01D25/162 ,  F02C3/107 ,  F02C7/20 ,  F02K3/06 ,  F02K3/075 ,  F05D2260/4031 ,  F05D2260/40311

    摘要： A gas turbine engine according to an exemplary aspect of the present disclosure includes a gear train defined along an engine centeriine axis, and a spool along said engine centeriine axis which drives the gear train, the spool includes a low stage count low pressure turbine. In a further non-limiting embodiment of any of the foregoing gas turbine engine embodiments, the low stage count may include three to six (3-6) stages. Additionally or alternatively, the low stage count may include three (3) stages. Additionally or alternatively, the low stage count may include five (5) or six (6) stages.

    摘要翻译： 根据本公开的示例性方面的燃气涡轮发动机包括沿着发动机中心轴线限定的齿轮系和沿着驱动齿轮系的所述发动机中心轴线的阀芯，阀芯包括低级计数低压涡轮。 在任何前述燃气涡轮发动机实施例的进一步的非限制性实施例中，低级计数可包括三至六（3-6）级。 另外或可选地，低阶段计数可以包括三（3）个阶段。 另外或可选地，低阶段计数可以包括五（5）或六（6）阶段。

    HEAT EXCHANGER FOR GAS TURBINE ENGINE
    143.
    发明公开
    HEAT EXCHANGER FOR GAS TURBINE ENGINE 审中-公开

    公开(公告)号：EP3680478A2

    公开(公告)日：2020-07-15

    申请号：EP20156729.4

    申请日：2016-08-04

    申请人： United Technologies Corporation

    发明人： DUESLER, Paul W. ,  SCHWARZ, Frederick M.

    IPC分类号： F02K3/115 ,  F02C7/141 ,  F02C7/18 ,  F02C7/20 ,  F04D29/58

    摘要： A heat exchanger (400; 900) for a gas turbine engine (110) is provided and comprises a baffle (436, 16) comprising a cobalt alloy configured to form an oxidized layer (30) over an outer surface of the baffle (436, 16) in response to an increase in temperature, the oxidized layer providing a lubricating surface. The heat exchanger further comprises a tube (22) inserted at least partially through the baffle (436, 16), an inlet (12) coupled to a first end of the tube (22), and an outlet (14) coupled to a second end of the tube (22).

    INTERCOOLED COOLING AIR WITH LOW TEMPERATURE BEARING COMPARTMENT AIR
    147.
    发明公开
    INTERCOOLED COOLING AIR WITH LOW TEMPERATURE BEARING COMPARTMENT AIR 审中-公开

    公开(公告)号：EP3584427A1

    公开(公告)日：2019-12-25

    申请号：EP19179765.3

    申请日：2019-06-12

    申请人： United Technologies Corporation

    发明人： SCHWARZ, Frederick M. ,  LEVASSEUR, Glenn ,  MERRY, Brian D.

    IPC分类号： F02C6/08 ,  F02C7/18 ,  F02C9/18 ,  F02C7/06

    摘要： A gas turbine engine (20) includes a plurality of rotatable components housed within a main compressor section (102) and a turbine section (122). A cooling system (100; 199; 209) is connected to tap air from said main compressor section (102). A first tap (106) is connected to a first heat exchanger (110). The first heat exchanger (110) is connected to a cooling compressor (112) for raising a pressure of the tapped air downstream of the first heat exchanger (110). A second heat exchanger (124) is downstream of the cooling compressor (112), and a connection is downstream of the second heat exchanger (124) for delivering air to a bearing compartment (130). A connection intermediate the cooling compressor (112) and the second heat exchanger (124) delivers cooling air to at least one of the rotatable components.

    HEAT EXCHANGER FOR COOLED COOLING AIR WITH ADJUSTABLE DAMPER
    149.
    发明公开
    HEAT EXCHANGER FOR COOLED COOLING AIR WITH ADJUSTABLE DAMPER 审中-公开

    公开(公告)号：EP3567271A1

    公开(公告)日：2019-11-13

    申请号：EP19181390.6

    申请日：2017-01-13

    申请人： United Technologies Corporation

    发明人： DUESLER, Paul W. ,  SCHWARZ, Frederick M.

    IPC分类号： F16F7/08 ,  F02C7/18 ,  F02C7/32

    摘要： A heat exchanger (HEX) (10; 400; 900) for cooling air in a gas turbine engine (110) is provided. An adjustable damper (180) is provided. The adjustable damper (180) may be for damping a movement of the HEX (10; 400; 900) relative to the gas turbine engine (110). An adjustable damper (180) may comprise: a first tube (190); a second tube (192) located at least partially within the first tube (190); a housing (184) coupled to the second tube (192); a moveable member (188), the moveable member (188) comprising a contacting surface (189) in contact with the second tube (192); an adjusting member (182) adjustably coupled to the housing (184); and a spring member (186) located between the moveable member (188) and the adjusting member (182), the spring member (186) configured to at least one of compress or decompress in response to adjusting member (182) moving relative to the housing (184).