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    STALL BUFFERING SYSTEM
    1.
    发明专利
    STALL BUFFERING SYSTEM 失效

    公开(公告)号：JP2000204967A

    公开(公告)日：2000-07-25

    申请号：JP36979099

    申请日：1999-12-27

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： GYSLING DANIEL L ,  FEULNER MATTHEW ,  EVEKER KEVIN

    IPC: F01D5/26 ,  F02C9/00 ,  F04D29/66

    Abstract: PROBLEM TO BE SOLVED: To prevent the occurrence of aerodynamic instability of an aero-engine. SOLUTION: This system is arranged at the inlet of the rotor of an engine 200 separately from turbofan blades 202, 204, 206, 208, 210, 212, 214, and 216 and provided with a flatter sensor to generate a sensor signal to indicate resonance of a turbofan blade related to a stall flatter. From the sensor signal, a command signal containing a space Fourier component(SFC) of disturbance coinciding with the natural frequency of the mode of a given structure of a fan blade having a given diameter node and a real time amplitude component is generated by a control device.

    TANGENTIALLY DIRECTED ACOUSTIC JET CONTROLLING BOUNDARY LAYERS
    2.
    发明申请
    TANGENTIALLY DIRECTED ACOUSTIC JET CONTROLLING BOUNDARY LAYERS 审中-公开
    方向引导的声控喷射控制边界层

    公开(公告)号：WO0055036A3

    公开(公告)日：2001-02-22

    申请号：PCT/US0004792

    申请日：2000-02-25

    Applicant: UNITED TECHNOLOGIES CORP ,  MCCORMICK DUANE C ,  GYSLING DANIEL L

    Inventor： MCCORMICK DUANE C ,  GYSLING DANIEL L

    IPC: B64C21/02 ,  B64C23/00 ,  F01D25/24 ,  F01D25/30 ,  F02C7/00 ,  F02C7/04 ,  F04D29/42 ,  F04D29/52 ,  F04D29/68 ,  F15D1/12

    CPC classification number: F15D1/12 ,  B64C23/00 ,  B64C2230/02 ,  B64C2230/04 ,  B64C2230/16 ,  B64C2230/28 ,  Y02T50/166

    Abstract: The nozzle of an acoustic jet directs high momentum flux gas particles essentially tangentially into the boundary layer of the flow in a diffuser, an engine air inlet, a jet engine gas flow path or on the suction surface of an airfoil, the gas particles in the chamber of the tangential acoustic jet being replenished with approaching low momentum flux particles drawn from the gas flow in a direction normal to the surface, thereby to provide a net time-averaged flow of increased momentum flux particles to defer the onset of boundary layer separation and/or reduce the thickness of the boundary layer. The acoustic jet is driven by a gas pressure oscillation generator which may be a loudspeaker, a resonant solenoid piston, a cranked piston, or the like.

    Abstract translation: 声学喷嘴的喷嘴将高动量通量气体颗粒基本切向地引导到扩散器，发动机空气入口，喷气发动机气体流动路径中或在翼型的吸力表面上的流动的边界层中，气体颗粒在 切向声射流的腔室被补充有接近从垂直于表面的方向从气流中吸取的低动量通量粒子，从而提供增加的动量通量粒子的净时间平均流，推迟边界层分离的开始， /或减小边界层的厚度。 声射流由气体压力振荡发生器驱动，气体振荡发生器可以是扬声器，谐振电磁阀活塞，曲柄活塞等。

    4.
    发明专利
    未知

    公开(公告)号：DE69521816D1

    公开(公告)日：2001-08-23

    申请号：DE69521816

    申请日：1995-11-02

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： EVEKER KEVIN M ,  GYSLING DANIEL L ,  NETT CARL N ,  WANG HUA O

    IPC: F02C7/057 ,  F02K3/06 ,  F04D27/02

    Abstract: PCT No. PCT/US95/17145 Sec. 371 Date Nov. 2, 1995 Sec. 102(e) Date Nov. 2, 1995 PCT Filed Nov. 2, 1995 PCT Pub. No. WO97/00381 PCT Pub. Date Jan. 3, 1997A technique for controlling compressor stall and surge is disclosed. In a gas turbine engine, static pressure asymmetry is sensed at a plurality of locations along the circumference of the compressor inlet. Time rate of change of the mass flow in the compressor is also estimated using pressure measurements in the compressor. A signal processor uses these signals to modulate a compressor bleed valve responsive to the level of flow property asymmetry, the time rate of change of the annulus average flow to enhance operability of the compressor.

    TANGENTIALLY DIRECTED ACOUSTIC JET CONTROLLING BOUNDARY LAYERS
    5.
    发明专利
    TANGENTIALLY DIRECTED ACOUSTIC JET CONTROLLING BOUNDARY LAYERS 未知

    公开(公告)号：CA2361824A1

    公开(公告)日：2000-09-21

    申请号：CA2361824

    申请日：2000-02-25

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： MCCORMICK DUANE C ,  GYSLING DANIEL L

    IPC: B64C21/02 ,  B64C23/00 ,  F01D25/24 ,  F01D25/30 ,  F02C7/00 ,  F02C7/04 ,  F04D29/42 ,  F04D29/52 ,  F04D29/68 ,  F15D1/12

    Abstract: The nozzle of an acoustic jet directs high momentum flux gas particles essentially tangentially into the boundary layer of the flow in a diffuser, an engine air inlet, a jet engine gas flow path or on the suction surface of an airfoil, the gas particles in the chamber of the tangential acoustic jet bei ng replenished with approaching low momentum flux particles drawn from the gas flow in a direction normal to the surface, thereby to provide a net time- averaged flow of increased momentum flux particles to defer the onset of boundary layer separation and/or reduce the thickness of the boundary layer. The acoustic jet is driven by a gas pressure oscillation generator which may be a loudspeaker, a resonant solenoid piston, a cranked piston, or the like.

    TANGENTIALLY DIRECTED ACOUSTIC JET CONTROLLING BOUNDARY LAYERS
    6.
    发明专利
    TANGENTIALLY DIRECTED ACOUSTIC JET CONTROLLING BOUNDARY LAYERS 未知

    公开(公告)号：CA2361824C

    公开(公告)日：2008-06-10

    申请号：CA2361824

    申请日：2000-02-25

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： MCCORMICK DUANE C ,  GYSLING DANIEL L

    IPC: B64C21/02 ,  B64C23/00 ,  F01D25/24 ,  F01D25/30 ,  F02C7/00 ,  F02C7/04 ,  F04D29/42 ,  F04D29/52 ,  F04D29/68 ,  F15D1/12

    Abstract: The nozzle of an acoustic jet directs high momentum flux gas particles essentially tangentially into the boundary layer of the flow in a diffuser, an engine air inlet, a jet engine gas flow path or on the suction surface of an airfoil, the gas particles in the chamber of the tangential acoustic jet being replenished with approaching low momentum flux particles drawn from the gas flow in a direction normal to the surface, thereby to provide a net time- averaged flow of increased momentum flux particles to defer the onset of boundary layer separation and/or reduce the thickness of the boundary layer. The acoustic jet is driven by a gas pressure oscillation generator which may be a loudspeaker, a resonant solenoid piston , a cranked piston, or the like.

    Tangentially directed acoustic jet controlling boundary layers
    8.
    发明专利
    Tangentially directed acoustic jet controlling boundary layers 未知

    公开(公告)号：AU5865200A

    公开(公告)日：2000-10-04

    申请号：AU5865200

    申请日：2000-02-25

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： MCCORMICK DUANE C ,  GYSLING DANIEL L

    IPC: B64C21/02 ,  B64C23/00 ,  F01D25/24 ,  F01D25/30 ,  F02C7/00 ,  F02C7/04 ,  F04D29/42 ,  F04D29/52 ,  F04D29/68 ,  F15D1/12

    Abstract: The nozzle of an acoustic jet directs high momentum flux gas particles essentially tangentially into the boundary layer of the flow in a diffuser, an engine air inlet, a jet engine gas flow path or on the suction surface of an airfoil, the gas particles in the chamber of the tangential acoustic jet being replenished with approaching low momentum flux particles drawn from the gas flow in a direction normal to the surface, thereby to provide a net time-averaged flow of increased momentum flux particles to defer the onset of boundary layer separation and/or reduce the thickness of the boundary layer. The acoustic jet is driven by a gas pressure oscillation generator which may be a loudspeaker, a resonant solenoid piston, a cranked piston, or the like.

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