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    2.
    发明专利
    未知

    公开(公告)号：DE69318313D1

    公开(公告)日：1998-06-04

    申请号：DE69318313

    申请日：1993-11-09

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： HANSEN JAMES O ,  NOVOTNAK DAVID

    IPC: C22C14/00 ,  C22F1/18 ,  F01D5/28

    Abstract: A non-burning Ti-V-Cr alloy which is heat treated to decrease its susceptibility to embrittlement in gas turbine engine compressor applications. The invention heat treat cycle consists of an isothermal holding period below the alpha solvus temperature, a slow ramp down to a lower temperature, a second holding period at a lower temperature, a third ramp down to an even lower temperature, and a final holding period at the third temperature. Other suitable heat treat cycles within the concept of the invention include a single holding period below the alpha solvus temperature double holding periods below the alpha solvus temperature with a ramp from a higher to a lower temperature and a continuous ramp below the alpha solvus temperature with no holding period.

    HYBRID METAL FAN BLADE
    5.
    发明申请
    HYBRID METAL FAN BLADE 审中-公开
    混合金属风扇叶片

    公开(公告)号：WO2014196987A3

    公开(公告)日：2015-02-26

    申请号：PCT/US2013046819

    申请日：2013-06-20

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： DEAL JAMES L ,  SCHIRRA JOHN J ,  DROZDENKO LEE ,  GRAVES WILLIAM R ,  HANSEN JAMES O ,  WEISSE MICHAEL A ,  WATSON THOMAS J

    IPC: F01D5/14 ,  F01D5/28 ,  F04D29/38

    CPC classification number: F01D5/288 ,  F01D5/147 ,  F04D29/023 ,  F04D29/324 ,  F05D2220/36 ,  F05D2230/23 ,  F05D2240/303 ,  F05D2300/121 ,  F05D2300/124 ,  F05D2300/174 ,  Y02T50/672

    Abstract: A fan blade comprises an airfoil portion and a sheath portion. The sheath portion has a sheath head section, a first sheath flank, and a second sheath flank, both flanks extending chordwise from the forward sheath section. The sheath portion is bonded to the airfoil portion such that the sheath head section covers the forward airfoil edge, defining a blade leading edge. The first sheath flank covers a portion of the first airfoil surface proximate the airfoil forward edge, jointly defining a blade suction surface. The second sheath flank covers a portion of the second airfoil surface proximate the airfoil forward edge, jointly defining a blade pressure surface. The first metallic material is an aluminum alloy containing between about 0.5 wt% and about 3.0 wt% of lithium.

    Abstract translation: 风扇叶片包括翼型部分和鞘部分。 护套部分具有鞘头部分，第一护套侧面和第二护套侧面，两个侧面从前鞘部分向翼伸出。 护套部分结合到翼型部分，使得鞘头部分覆盖前翼型边缘，限定叶片前缘。 第一护套侧面覆盖靠近翼型件前缘的第一翼型件表面的一部分，共同限定叶片抽吸表面。 第二护套侧面覆盖靠近翼型件前缘的第二翼型件表面的一部分，共同限定叶片压力表面。 第一种金属材料是含有约0.5wt％至约3.0wt％的锂的铝合金。

    7.
    发明专利
    未知

    公开(公告)号：DE69318313T2

    公开(公告)日：1998-08-20

    申请号：DE69318313

    申请日：1993-11-09

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： HANSEN JAMES O ,  NOVOTNAK DAVID

    IPC: C22C14/00 ,  C22F1/18 ,  F01D5/28

    Abstract: A non-burning Ti-V-Cr alloy which is heat treated to decrease its susceptibility to embrittlement in gas turbine engine compressor applications. The invention heat treat cycle consists of an isothermal holding period below the alpha solvus temperature, a slow ramp down to a lower temperature, a second holding period at a lower temperature, a third ramp down to an even lower temperature, and a final holding period at the third temperature. Other suitable heat treat cycles within the concept of the invention include a single holding period below the alpha solvus temperature double holding periods below the alpha solvus temperature with a ramp from a higher to a lower temperature and a continuous ramp below the alpha solvus temperature with no holding period.

    Heat treatment to reduce embrittlement of tatanium alloys
    8.
    发明专利
    Heat treatment to reduce embrittlement of tatanium alloys 未知

    公开(公告)号：AU5896294A

    公开(公告)日：1994-07-19

    申请号：AU5896294

    申请日：1993-11-09

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： HANSEN JAMES O ,  NOVOTNAK DAVID

    IPC: C22C14/00 ,  C22F1/18 ,  F01D5/28

    Abstract: A non-burning Ti-V-Cr alloy which is heat treated to decrease its susceptibility to embrittlement in gas turbine engine compressor applications. The invention heat treat cycle consists of an isothermal holding period below the alpha solvus temperature, a slow ramp down to a lower temperature, a second holding period at a lower temperature, a third ramp down to an even lower temperature, and a final holding period at the third temperature. Other suitable heat treat cycles within the concept of the invention include a single holding period below the alpha solvus temperature double holding periods below the alpha solvus temperature with a ramp from a higher to a lower temperature and a continuous ramp below the alpha solvus temperature with no holding period.

    Heat Treatment to Reduce Embrittlement of Tatanium Alloys
    10.
    发明专利
    Heat Treatment to Reduce Embrittlement of Tatanium Alloys 未知

    公开(公告)号：CA2148581A1

    公开(公告)日：1994-07-07

    申请号：CA2148581

    申请日：1993-11-09

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： HANSEN JAMES O ,  NOVOTNAK DAVID

    IPC: C22C14/00 ,  C22F1/18 ,  F01D5/28

    Abstract: A non-burning Ti-V-Cr alloy which is heat treated to decrease its susceptibility to embrittlement in gas turbine engine compressor applications. The invention heat treat cycle consists of an isothermal holding period below the alpha solvus temperature, a slow ramp down to a lower temperature, a second holding period at a lower temperature, a third ramp down to an even lower temperature, and a final holding period at the third temperature. Other suitable heat treat cycles within the concept of the invention include a single holding period below the alpha solvus temperature double holding periods below the alpha solvus temperature with a ramp from a higher to a lower temperature and a continuous ramp below the alpha solvus temperature with no holding period.

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