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    FLOW GUIDE ASSEMBLY
    1.
    发明专利
    FLOW GUIDE ASSEMBLY 审中-公开

    公开(公告)号：JP2003269384A

    公开(公告)日：2003-09-25

    申请号：JP2003061211

    申请日：2003-03-07

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： STAUBACH J BRENT ,  WAGNER JOEL H ,  AGGARWALA ANDREW S

    IPC: F01D5/30 ,  F01D5/14 ,  F04D29/32

    Abstract: PROBLEM TO BE SOLVED: To provide an end wall having a nonaxissymmetric trough for reducing an interference loss between a shock wave and an end wall. SOLUTION: An end wall shape reducing shock wave power in transonic turbine machine airfoil, includes the nonaxissymmetric trough 30 extending up to a point in the vicinity of a rear edge part of at least one flow passage 24 from a front part of at least the one flow passage 24. COPYRIGHT: (C)2003,JPO

    BLADE OR VANE TO BE COOLED FOR TURBINE ENGINE
    2.
    发明专利
    BLADE OR VANE TO BE COOLED FOR TURBINE ENGINE 审中-公开

    公开(公告)号：JP2002364305A

    公开(公告)日：2002-12-18

    申请号：JP2002137990

    申请日：2002-05-14

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： KOHLI ATUL ,  WAGNER JOEL H ,  AGGARWALA ANDREW S

    IPC: F01D5/14 ,  F01D5/18 ,  F01D9/02

    Abstract: PROBLEM TO BE SOLVED: To provide a film cooling system with high cost performance for facilitating the sideways expansion and secure adhesion of a cooling jet 70 over a high temperature face 24 of an article. SOLUTION: The article having a wall with the high temperature face 24 such as a blade or vane of a turbine engine comprises a recess 48 characterized by a descending side face 52 and an ascending side face 54. A cooling hole 6 bored on the wall 24 includes an outlet located on the ascending side face 54. When the article is operated, the cooling jet 70 is discharged from the outlet and a primary fluid flow F flowing on the ascending side face 54 is locally over-accelerated by the recess 48. The local over-acceleration of the primary fluid flow F turns the cooling jet 70 to flow on the high temperature face 24 to facilitate sideways expansion of the jet and formation of a protective cooling film continuing sideways together with the expanded jet.

    5.
    发明专利
    未知

    公开(公告)号：FR2836954B1

    公开(公告)日：2008-04-04

    申请号：FR0301678

    申请日：2003-02-12

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： STAUBACH J BRENT ,  WAGNER JOEL H ,  AGGARWALA ANDREW S

    IPC: F01D5/12 ,  F01D5/30 ,  F01D5/14 ,  F04D29/32

    Abstract: The present invention relates to an endwall shape for reducing shock strength on transonic turbomachinery airfoils which define at least one flow passage. The endwall shape includes a non-axisymmetric trough which extends from a leading portion of the at least one flow passage to a point near a trailing edge portion of the at least one flow passage.

    6.
    发明专利
    未知

    公开(公告)号：DE60218776T2

    公开(公告)日：2007-12-06

    申请号：DE60218776

    申请日：2002-05-21

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： KOHLI ATUL ,  WAGNER JOEL H ,  AGGARWALA ANDREW S

    IPC: F01D5/18 ,  F01D5/14 ,  F01D9/02

    Abstract: The invention resides in a film cooled article such as a turbine engine blade or vane, having a wall with a hot surface (26) to be film cooled. The hot surface (26) includes a depression (48) featuring a descending flank (52) and an ascending flank (54) . Coolant holes (60) , which penetrate through the wall, have discharge openings residing on the ascending flank (54) . During operation, the depression locally over-accelerates a primary fluid stream F flowing over the ascending flank while coolant jets (70) concurrently issue from the discharge openings. The local over-acceleration of the primary fluid deflects the jets onto the hot surface and spatially constrains the jets thus encouraging them to spread out laterally and coalesce into a laterally continuous, protective coolant film. In one embodiment, the depression (48) is a trough (50) . In another embodiment, the depression is a dimple (72) .

    7.
    发明专利
    未知

    公开(公告)号：DE602007001910D1

    公开(公告)日：2009-09-24

    申请号：DE602007001910

    申请日：2007-06-15

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： ALVANOS IOANNIS ,  WAGNER JOEL H

    IPC: F01D11/00 ,  F01D5/18

    Abstract: A system is disclosed for injecting a secondary fluid stream (42) into a primary fluid stream (28) with improved aerodynamic efficiency. The secondary fluid stream (42) is injected into the primary fluid stream (28) at a tangential angle and radial location that reduces both mixing and endwall losses. A platform (44) borders the primary fluid stream (28) and contains a trailing edge surface (68). A rail (80) extends radially from the platform (44) and one or more conduits (80) enter the rail (80) in a substantially radial direction. The conduits (82) extend through the radial length of the rail (80), continue into the platform (44), and terminate at the trailing edge surface (68). The secondary fluid stream (48) is conveyed by the conduits (82) through the rail (80) and the platform (44), to the trailing edge surface (68), for injecting into the primary fluid stream (28) at an optimal angle and radial location.

    8.
    发明专利
    未知

    公开(公告)号：DE60218776D1

    公开(公告)日：2007-04-26

    申请号：DE60218776

    申请日：2002-05-21

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： KOHLI ATUL ,  WAGNER JOEL H ,  AGGARWALA ANDREW S

    IPC: F01D5/18 ,  F01D5/14 ,  F01D9/02

    Abstract: The invention resides in a film cooled article such as a turbine engine blade or vane, having a wall with a hot surface (26) to be film cooled. The hot surface (26) includes a depression (48) featuring a descending flank (52) and an ascending flank (54) . Coolant holes (60) , which penetrate through the wall, have discharge openings residing on the ascending flank (54) . During operation, the depression locally over-accelerates a primary fluid stream F flowing over the ascending flank while coolant jets (70) concurrently issue from the discharge openings. The local over-acceleration of the primary fluid deflects the jets onto the hot surface and spatially constrains the jets thus encouraging them to spread out laterally and coalesce into a laterally continuous, protective coolant film. In one embodiment, the depression (48) is a trough (50) . In another embodiment, the depression is a dimple (72) .

    9.
    发明专利
    未知

    公开(公告)号：DE10310150A1

    公开(公告)日：2003-09-25

    申请号：DE10310150

    申请日：2003-03-07

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： STAUBACH J BRENT ,  WAGNER JOEL H ,  AGGARWALA ANDREW S

    IPC: F01D5/30 ,  F01D5/14 ,  F04D29/32

    Abstract: The present invention relates to an endwall shape for reducing shock strength on transonic turbomachinery airfoils which define at least one flow passage. The endwall shape includes a non-axisymmetric trough which extends from a leading portion of the at least one flow passage to a point near a trailing edge portion of the at least one flow passage.

    10.
    发明专利
    未知

    公开(公告)号：FR2836954A1

    公开(公告)日：2003-09-12

    申请号：FR0301678

    申请日：2003-02-12

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： STAUBACH J BRENT ,  WAGNER JOEL H ,  AGGARWALA ANDREW S

    IPC: F01D5/30 ,  F01D5/14 ,  F04D29/32 ,  F01D5/12

    Abstract: The present invention relates to an endwall shape for reducing shock strength on transonic turbomachinery airfoils which define at least one flow passage. The endwall shape includes a non-axisymmetric trough which extends from a leading portion of the at least one flow passage to a point near a trailing edge portion of the at least one flow passage.

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