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    CONTROL DEVICE FOR PREVENTING VIBRATION OF ROTOR STAGE OF GAS TURBINE ENGINE
    1.
    发明专利
    CONTROL DEVICE FOR PREVENTING VIBRATION OF ROTOR STAGE OF GAS TURBINE ENGINE 失效

    公开(公告)号：JPH11141307A

    公开(公告)日：1999-05-25

    申请号：JP26099798

    申请日：1998-08-31

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： EL-AINI YEHIA M ,  BENEDICT BARRY K ,  BAGHDADI SAMY ,  MATHENY A PAUL

    IPC: F01D5/16 ,  F01D5/10 ,  F01D5/14 ,  F01D5/26 ,  F01D25/06 ,  F04D29/66 ,  F04D29/68

    Abstract: PROBLEM TO BE SOLVED: To provide a device which minimizes or eliminates vibration of a moving blade of a rotor stage of a gas turbine engine. SOLUTION: This device 20 has a high pressure gas source 48 and a plurality of holes 50 for distributing the high pressure gas. A rotor stage 34 is rotated by center gas streams 24 distributed in a circumferential direction, having first and second areas. The gas streams in the first and second areas, are flowed respectively with first and second velocities. The first velocity is actually faster than the second velocity. The holes 50 for distributing the high,pressure gas are selectively formed on an upstream side of the a moving blade, and aligned in the second area. The high pressure gas, flowed out of the holes 50, enter the second area. It is thus possible to increase velocity of center gas stream in the second area, while acutally reduce difference the velocities of the center gas streams between the first and second areas.

    ROTOR STEP FOR GAS TURBINE ENGINE
    2.
    发明专利
    ROTOR STEP FOR GAS TURBINE ENGINE 失效

    公开(公告)号：JPH11236804A

    公开(公告)日：1999-08-31

    申请号：JP35696798

    申请日：1998-12-01

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： EL-AINI YEHIA M ,  COWLES BRADFORD A

    IPC: F01D5/16 ,  F01D5/10 ,  F01D25/06

    Abstract: PROBLEM TO BE SOLVED: To provide a vibration damping device which can be used in a rotor integrally equipped with rotor blades, is effective for periodical push-in actions and aperiodical perturbation, and also is effective for vibration of rotor blade having middle or low grade aspect ratio. SOLUTION: Rotor steps 32 for a gas turbine engine include a rotor disc and a plurality of rotor blades 36. The rotor disc is provided with a hole centering on the axis of rotation and a surface 40 in radial direction on the outside. The rotor blades 36 are extended from the surface 40 in radial direction on the outside to the outside in the radial direction and are distributed around the surface 40. At least one rotor blade 36 is positioned aslant (α) selectively relative to other adjacent rotor blade 36. This slant rotor blade increases the aerodynamic damping of the rotor steps.

    ROTOR STEP FOR GAS TURBINE ENGINE
    3.
    发明专利
    ROTOR STEP FOR GAS TURBINE ENGINE 失效

    公开(公告)号：JPH11236803A

    公开(公告)日：1999-08-31

    申请号：JP35696698

    申请日：1998-12-01

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： EL-AINI YEHIA M ,  COWLES BRADFORD A

    IPC: F01D5/16 ,  F01D5/10 ,  F01D5/14 ,  F01D5/26 ,  F01D25/06 ,  F04D29/66

    Abstract: PROBLEM TO BE SOLVED: To provide a vibration damping device which can be used in a rotor integrally equipped with rotor blades, is effective for periodical push-in actions and aperiodical perturbation, and also is effective for vibration of rotor blade having middle or a low aspect ratio. SOLUTION: Rotor steps 32 for a gas turbine engine include a rotor disc and a plurality of rotor blades 36. The rotor blades 36 are extended from the surface 40 in radial direction on the outside of the rotor disc and are positioned apart at a specified distance 42 from one another. The distance 42 is changed selectively so that the aerodynamic damping of each rotor blade is increased. This selectively changeable inter-blade distance is at least 80% of uniform inter-blade distance.

    5.
    发明专利
    未知

    公开(公告)号：DE69627915D1

    公开(公告)日：2003-06-12

    申请号：DE69627915

    申请日：1996-02-15

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： EL-AINI YEHIA M ,  BURGE JOSEPH C ,  MEECE CARL E

    IPC: F01D5/16

    Abstract: A rotor blade (14) for a turbine engine rotor assembly (10) is provided with apparatus for damping vibrations in the blade. The blade includes a pocket (26) formed in a surface. The apparatus for damping vibrations in the blade includes a damper (34) and a pocket lid (36). The damper (34) is received within the pocket (26) between an inner surface (32) of the pocket (26) and the pocket lid (36). The pocket lid is attached to the airfoil and contoured to match the curvature of the airfoil. The damper may be of a sinusoidal shape, or may comprise a plurality of strands (39) formed in a mesh (38).

    9.
    发明专利
    未知

    公开(公告)号：DE69627915T2

    公开(公告)日：2003-11-13

    申请号：DE69627915

    申请日：1996-02-15

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： EL-AINI YEHIA M ,  BURGE JOSEPH C ,  MEECE CARL E

    IPC: F01D5/16

    Abstract: A rotor blade (14) for a turbine engine rotor assembly (10) is provided with apparatus for damping vibrations in the blade. The blade includes a pocket (26) formed in a surface. The apparatus for damping vibrations in the blade includes a damper (34) and a pocket lid (36). The damper (34) is received within the pocket (26) between an inner surface (32) of the pocket (26) and the pocket lid (36). The pocket lid is attached to the airfoil and contoured to match the curvature of the airfoil. The damper may be of a sinusoidal shape, or may comprise a plurality of strands (39) formed in a mesh (38).

    Turbine engine rotor blade vibration damping device
    10.
    发明公开
    Turbine engine rotor blade vibration damping device 失效
    SchwungungsdämpferfürTurbinenschaufeln

    公开(公告)号：EP0727563A3

    公开(公告)日：1998-11-04

    申请号：EP96301044

    申请日：1996-02-15

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： EL-AINI YEHIA M ,  BURGE JOSEPH C ,  MEECE CARL E

    IPC: F01D5/16

    CPC classification number: F01D5/16 ,  Y10S416/50

    Abstract: A rotor blade (14) for a turbine engine rotor assembly (10) is provided with apparatus for damping vibrations in the blade. The blade includes a pocket (26) formed in a surface. The apparatus for damping vibrations in the blade includes a damper (34) and a pocket lid (36). The damper (34) is received within the pocket (26) between an inner surface (32) of the pocket (26) and the pocket lid (36). The pocket lid is attached to the airfoil and contoured to match the curvature of the airfoil. The damper may be of a sinusoidal shape, or may comprise a plurality of strands (39) formed in a mesh (38).

    Abstract translation: 提供了一种用于涡轮发动机转子组件的转子叶片，其包括根部，翼型件，平台以及用于阻尼翼型件中的振动的装置。 翼型件包括形成在弦向表面中的口袋。 用于阻尼叶片中的振动的装置包括阻尼器和袋盖。 阻尼器容纳在口袋的内表面和口袋盖之间的口袋内。 口袋盖通过传统的附接装置附接到翼型，并且轮廓以匹配翼型的曲率。

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