中科微点-全球专利检索

  1. Login
  2. Sign Up

Search Results

7 records (took 0.021 seconds)

    TURBINE VANES WITH VARIABLE FILLETS
    2.
    发明申请
    TURBINE VANES WITH VARIABLE FILLETS 审中-公开
    具有可变填料的涡轮风扇

    公开(公告)号：WO2015009418A1

    公开(公告)日：2015-01-22

    申请号：PCT/US2014/044039

    申请日：2014-06-25

    Applicant: UNITED TECHNOLOGIES CORPORATION

    Inventor： OLS, John T. ,  MENTZ, Karl A. ,  ALLEN, Richard N. ,  PORTER, Steven D. ,  JUREK, Renee J. ,  SANCHEZ, Paul K. ,  PINERO, Sandra S.

    IPC: F01D9/04 ,  F01D5/14 ,  F02C7/04

    CPC classification number: F01D9/041 ,  F01D5/02 ,  F01D5/143 ,  F01D9/04 ,  F01D25/246 ,  F05D2220/32 ,  F05D2240/12 ,  F05D2240/303 ,  F05D2240/304 ,  F05D2240/80 ,  F05D2250/71 ,  F05D2250/90 ,  Y02T50/673

    Abstract: An airfoil extends between radially inner and radially outer platforms. The airfoil extends between a leading edge and a trailing edge, and merges into facing surfaces of the radially inner and outer platforms. A variable fillet merges a facing surface of one of the radially inner and outer platforms into a wall of the airfoil. The variable fillet has a length extending away from a surface of the airfoil and a height extending away from the facing surface of at least one of the radially inner and outer platforms outwardly on to the airfoil. The variable fillet has a greater length at one of the leading edge and the trailing edge. A spaced portion has a shorter length at locations spaced from at least one of the leading and trailing edges. A mid-turbine frame and a gas turbine engine are also disclosed.

    Abstract translation: 翼型件在径向内部和径向外部平台之间延伸。 翼型件在前缘和后缘之间延伸，并且合并到径向内外平台的相对表面中。 可变圆角将径向内平台和外平台之一的相对表面合并成翼型的壁。 可变圆角具有远离翼型件的表面延伸的长度以及远离径向内部和外部平台中的至少一个的相对表面向外延伸到翼型的高度。 可变圆角在前缘和后缘之一处具有更大的长度。 间隔部分在与前缘和后缘中的至少一个间隔开的位置处具有较短的长度。 还公开了中涡轮机架和燃气涡轮发动机。

    COOLED COOLING AIR FOR BLADE AIR SEAL THROUGH OUTER CHAMBER
    5.
    发明公开
    COOLED COOLING AIR FOR BLADE AIR SEAL THROUGH OUTER CHAMBER 审中-公开

    公开(公告)号：EP3382156A1

    公开(公告)日：2018-10-03

    申请号：EP18165234.8

    申请日：2018-03-29

    Applicant: United Technologies Corporation

    Inventor： ORTIZ, Jonathan ,  SURACE, Raymond ,  JUREK, Renee J. ,  PROPHETER-HINCKLEY, Tracy A.

    IPC: F01D11/24 ,  F01D9/06

    Abstract: A gas turbine engine (20) includes a compressor section (24), a combustor (56), and a turbine section (28). The combustor (56) has a radially outer surface that defines a diffuser chamber (112) radially outwardly of the combustor (56). The turbine section (28) has a high pressure turbine first stage blade (118) that has an outer tip, and a blade outer air seal (126) positioned radially outwardly of the outer tip. A tap (102) for tapping air has been compressed by the compressor (56) and is passed through a heat exchanger (104). The air downstream of the heat exchanger (104) passes through at least one pipe (120) and into a manifold (122) radially outward of the blade outer air seal (126), and then passes across the blade outer air seal (126) to cool the blade outer air seal (126).

Patent Agency Ranking