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公开(公告)号：WO9529331A2
公开(公告)日：1995-11-02
申请号：PCT/US9504411
申请日：1995-04-11
Applicant: UNITED TECHNOLOGIES CORP
Inventor： SHARMA OM PARKASH
Abstract: The first stage of vanes (16) and second stage of vanes (24) each contain the same number of vanes. The second stage of vanes are located such that the wake flow (38) from the first stage of vanes falls on or near the leading edge, after passing through the stage of rotating blades.
Abstract translation: 叶片（16）的第一阶段和叶片（24）的第二阶段各自包含相同数量的叶片。 叶片的第二级定位成使得来自叶片的第一级的尾流（38）在通过旋转叶片的阶段之后落在前缘上或附近。
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公开(公告)号：CA2557234A1
公开(公告)日：2007-02-28
申请号：CA2557234
申请日：2006-08-25
Applicant: UNITED TECHNOLOGIES CORP
Inventor： CUNHA FRANK , PIETRASZKIEWICZ EDWARD F , SHARMA OM PARKASH
Abstract: A method for manufacturing a cooling microcircuit in a blade-outer-air-seal is provided. The method broadly comprises the steps of forming a first section of the blade-outer-air-seal having a first exposed internal wall, forming a second section of the blade-outer-air-seal having a second exposed internal wall, and forming at least one cooling microcircuit on at least one of the first and second exposed internal walls.
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公开(公告)号：CA2557233A1
公开(公告)日：2007-02-28
申请号：CA2557233
申请日：2006-08-25
Applicant: UNITED TECHNOLOGIES CORP
Inventor： PIETRASZKIEWICZ EDWARD F , SHARMA OM PARKASH , CUNHA FRANK
Abstract: A method for manufacturing a turbine engine component comprises the steps of forming a first half of an airfoil portion of the turbine engine component and forming a plurality of microcircuits having at least one passageway on an exposed internal wall of the first half of the airfoil portion. The method further comprises forming a second half of the airfoil portion of said turbine engine component, and forming at least one additional cooling microcircuit having at least one passageway on an exposed internal wall of the second half of the airfoil portion. Thereafter, the first half is placed in an abutting relationship with the second half after the cooling microcircuits have been formed and inspected. The first half and the second half are joined together to form the airfoil portion.
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公开(公告)号：CA2557236A1
公开(公告)日：2007-02-28
申请号：CA2557236
申请日：2006-08-25
Applicant: UNITED TECHNOLOGIES CORP
Inventor： PIETRASZKIEWICZ EDWARD F , SHARMA OM PARKASH
Abstract: A method for forming a component for use in a gas turbine engine, such as a turbine vane construction is provided. The method broadly comprises the steps of: forming a first aerodynamic structure having a first platform with a leading edge and a trailing edge, and an edge with an airfoil suction side structure; forming a second aerodynamic structure having a second platform with a leading edge and a trailing edge, and an first edge with an airfoil pressure side structure; and joining the two structures together so that the airfoil suction side structure mates with the airfoil pressure side structure to form an airfoil.
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公开(公告)号：SG130131A1
公开(公告)日：2007-03-20
申请号：SG2006053581
申请日：2006-08-07
Applicant: UNITED TECHNOLOGIES CORP
Inventor： CUNHA FRANK , SHARMA OM PARKASH , PIETRASZKIEWICZ EDWARD F
Abstract: A method for manufacturing a turbine engine component comprises the steps of forming a first half of an airfoil portion of the turbine engine component and forming a plurality of microcircuits having at least one passageway on an exposed internal wall of the first half of the airfoil portion. The method further comprises forming a second half of the airfoil portion of said turbine engine component, and forming at least one additional cooling microcircuit having at least one passageway on an exposed internal wall of the second half of the airfoil portion. Thereafter, the first half is placed in an abutting relationship with the second half after the cooling microcircuits have been formed and inspected. The first half and the second half are joined together to form the airfoil portion.
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Patent Agency Ranking
公开(公告)号：SG130124A1
公开(公告)日：2007-03-20
申请号：SG2006053292
申请日：2006-08-07
Applicant: UNITED TECHNOLOGIES CORP
Inventor： CUNHA FRANK , SHARMA OM PARKASH , PIETRASZKIEWICZ EDWARD F
Abstract: A method for manufacturing a cooling microcircuit in a blade-outer-air-seal is provided. The method broadly comprises the steps of forming a first section of the blade-outer-air-seal having a first exposed internal wall, forming a second section of the blade-outer-air-seal having a second exposed internal wall, and forming at least one cooling microcircuit on at least one of the first and second exposed internal walls.
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公开(公告)号：CA2558479A1
公开(公告)日：2007-02-28
申请号：CA2558479
申请日：2006-08-25
Applicant: UNITED TECHNOLOGIES CORP
Inventor： SHARMA OM PARKASH , PIETRASZKIEWICZ EDWARD F , CUNHA FRANK
Abstract: A method for manufacturing a turbine engine component comprises the steps of forming a first half of an airfoil portion of the turbine engine component and forming a first cooling microcircuit having at least one passageway on an exposed internal wall of the first half of the airfoil portion. The method further comprises forming a second half of the airfoil portion of said turbine engine component, forming a second cooling microcircuit having at least one passageway on an exposed internal wall of the second half of the airfoil portion, and placing the first half in an abutting relationship with the second half after the cooling microcircuits have been formed and inspected.
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公开(公告)号：SG130130A1
公开(公告)日：2007-03-20
申请号：SG2006053573
申请日：2006-08-07
Applicant: UNITED TECHNOLOGIES CORP
Inventor： SHARMA OM PARKASH , CUNHA FRANK , PIETRASZKIEWICZ EDWARD F
Abstract: A method for manufacturing a turbine engine component comprises the steps of forming a first half of an airfoil portion of the turbine engine component and forming a first cooling microcircuit having at least one passageway on an exposed internal wall of the first half of the airfoil portion. The method further comprises forming a second half of the airfoil portion of said turbine engine component, forming a second cooling microcircuit having at least one passageway on an exposed internal wall of the second half of the airfoil portion, and placing the first half in an abutting relationship with the second half after the cooling microcircuits have been formed and inspected.
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公开(公告)号：SG130128A1
公开(公告)日：2007-03-20
申请号：SG2006053532
申请日：2006-08-07
Applicant: UNITED TECHNOLOGIES CORP
Inventor： PIETRASZKIEWICZ EDWARD F , SHARMA OM PARKASH
Abstract: A method for forming a component for use in a gas turbine engine, such as a turbine vane construction is provided. The method broadly comprises the steps of: forming a first aerodynamic structure having a first platform with a leading edge and a trailing edge, and an edge with an airfoil suction side structure; forming a second aerodynamic structure having a second platform with a leading edge and a trailing edge, and an first edge with an airfoil pressure side structure; and joining the two structures together so that the airfoil suction side structure mates with the airfoil pressure side structure to form an airfoil.
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公开(公告)号：AU5850796A
公开(公告)日：1996-11-18
申请号：AU5850796
申请日：1996-04-17
Applicant: UNITED TECHNOLOGIES CORP
Inventor： GERTZ JEFFREY B , SHARMA OM PARKASH , EVEKER KEVIN M , NETT CARL N , GYSLING DANIEL L , FEULNER MATTHEW R
IPC: F04D27/02
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