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    11.
    发明专利
    未知

    公开(公告)号：AT381976T

    公开(公告)日：2008-01-15

    申请号：AT05250321

    申请日：2005-01-24

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： PALAZZINI CHRISTOPHER M ,  WEISSE MICHAEL A ,  SENECAL DOUGLAS A

    IPC: B23P15/04 ,  F01D5/14 ,  F01D5/18 ,  F02C7/00 ,  F04D29/32 ,  F04D29/38

    Abstract: Hollow fan blades (30) for turbo fan gas turbine engines are formed of two separate detail halves (30a;30b). Each detail half (30a;30b) has a plurality of cavities (40) and ribs (42) machined out to reduce weight. The floor (48) and opposite interior walls (50) of each cavity (40) are machined simultaneously. The configuration minimizes the number of cutter plunge cuts for the internal cavities, and maximizes cutter size, in order to minimize the time required to machine them. These detail halves (30a;30b) are subsequently bonded and given an airfoil shape in the forming operation.

    12.
    发明专利
    未知

    公开(公告)号：FR2632357A1

    公开(公告)日：1989-12-08

    申请号：FR8907339

    申请日：1989-06-02

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： CHAPLIN GARY F ,  PANNONE JOHN L ,  WEISSE MICHAEL A

    IPC: F01D9/02 ,  F01D5/22 ,  F01D11/00 ,  F01D11/02

    Abstract: A stator vane assembly 30 for a rotary machine is disclosed. The stator vane assembly includes an array of stator vanes 44 and an inner air seal 46. Various construction details which damp vibrational stresses in the vanes are developed. In one embodiment, the stator vanes slidably engage the inner air seal. The inner air seal is urged radially into sliding contact with the vanes at the inner ends 52 of the vanes by a resilient device such as a radial spring member 70. In one detailed embodiment, the stator vane has at least two airfoils 55b,c which are circumferentially spaced at their inner ends leaving a circumferential gap therebetween.

    13.
    发明专利
    未知

    公开(公告)号：DE602005003973T2

    公开(公告)日：2009-01-08

    申请号：DE602005003973

    申请日：2005-01-24

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： PALAZZINI CHRISTOPHER M ,  WEISSE MICHAEL A ,  SENECAL DOUGLAS A

    IPC: B23P15/04 ,  F01D5/14 ,  F01D5/18 ,  F02C7/00 ,  F04D29/32 ,  F04D29/38

    Abstract: Hollow fan blades (30) for turbo fan gas turbine engines are formed of two separate detail halves (30a;30b). Each detail half (30a;30b) has a plurality of cavities (40) and ribs (42) machined out to reduce weight. The floor (48) and opposite interior walls (50) of each cavity (40) are machined simultaneously. The configuration minimizes the number of cutter plunge cuts for the internal cavities, and maximizes cutter size, in order to minimize the time required to machine them. These detail halves (30a;30b) are subsequently bonded and given an airfoil shape in the forming operation.

    14.
    发明专利
    未知

    公开(公告)号：AT401161T

    公开(公告)日：2008-08-15

    申请号：AT05250320

    申请日：2005-01-24

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： WHITESELL DANIEL J ,  PALAZZINI CHRISTOPHER M ,  WEISSE MICHAEL A

    IPC: B23P15/04 ,  F01D5/14 ,  F01D5/18 ,  F02C3/06 ,  F02C7/16 ,  F04D29/32 ,  F04D29/38

    Abstract: A method for making a hollow fan blade includes the steps of: forming a plurality of ribs (42) on a first substrate (31), the first substrate (31) including cavities (40) on either side of each of the plurality of ribs; abutting the plurality of ribs (42) on the first substrate (31) with a second substrate (31) to form a hollow fan blade (30); and forming the hollow fan blade (30) into an airfoil shape while pressure inside the cavities (40) is substantially ambient pressure.

    16.
    发明专利
    未知

    公开(公告)号：DE602005007272D1

    公开(公告)日：2008-07-17

    申请号：DE602005007272

    申请日：2005-01-24

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： OWEN WILLIAM D ,  WEISSE MICHAEL A ,  WHITESELL DANIEL J

    IPC: B23P15/04 ,  F01D5/14 ,  F01D5/18 ,  F02C7/00 ,  F04D29/32 ,  F04D29/38

    Abstract: Hollow fan blades for turbo fan gas turbine engines are formed of two separate detail halves (30a;30b). Each detail half (30a) has a plurality of cavities (40) and ribs (70) machined out to reduce weight. These detail halves are subsequently bonded and given an airfoil shape in the forming operation. In the present invention, the ribs (70) are oriented and biased to provide stiffness as needed in different sections of the fan blade with smooth transitions between regions. In particular, ribs (72a) in a first region (A) of the detail substrate (61) are formed so as not to be parallel to ribs (72c) in a second region (B) of the substrate. The result is a blade with good protection from a wide spectrum of external threats.

    STATOR VANE ASSEMBLY FOR AN AXIAL FLOW ROTARY MACHINE
    18.
    发明专利
    STATOR VANE ASSEMBLY FOR AN AXIAL FLOW ROTARY MACHINE 未知

    公开(公告)号：GB2219355B

    公开(公告)日：1992-03-18

    申请号：GB8912546

    申请日：1989-06-01

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： CHAPLIN GARY FRANCES ,  PANNONE JOHN L ,  WEISSE MICHAEL A

    IPC: F01D9/02 ,  F01D5/22 ,  F01D11/00 ,  F01D11/02

    Abstract: A stator vane assembly 30 for a rotary machine is disclosed. The stator vane assembly includes an array of stator vanes 44 and an inner air seal 46. Various construction details which damp vibrational stresses in the vanes are developed. In one embodiment, the stator vanes slidably engage the inner air seal. The inner air seal is urged radially into sliding contact with the vanes at the inner ends 52 of the vanes by a resilient device such as a radial spring member 70. In one detailed embodiment, the stator vane has at least two airfoils 55b,c which are circumferentially spaced at their inner ends leaving a circumferential gap therebetween.

    STATOR VANE ASSEMBLY SEAL AND ANTI-VIBRATION ARRANGEMENT
    19.
    发明专利
    STATOR VANE ASSEMBLY SEAL AND ANTI-VIBRATION ARRANGEMENT 未知

    公开(公告)号：GB2219355A

    公开(公告)日：1989-12-06

    申请号：GB8912546

    申请日：1989-06-01

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： CHAPLIN GARY FRANCES ,  PANNONE JOHN L ,  WEISSE MICHAEL A

    IPC: F01D9/02 ,  F01D5/22 ,  F01D11/00 ,  F01D11/02

    Abstract: A stator vane assembly 30 for a rotary machine is disclosed. The stator vane assembly includes an array of stator vanes 44 and an inner air seal 46. Various construction details which damp vibrational stresses in the vanes are developed. In one embodiment, the stator vanes slidably engage the inner air seal. The inner air seal is urged radially into sliding contact with the vanes at the inner ends 52 of the vanes by a resilient device such as a radial spring member 70. In one detailed embodiment, the stator vane has at least two airfoils 55b,c which are circumferentially spaced at their inner ends leaving a circumferential gap therebetween.

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