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    MISTAKE PROOF IDENTIFICATION FEATURE FOR TURBINE BLADES
    11.
    发明专利
    MISTAKE PROOF IDENTIFICATION FEATURE FOR TURBINE BLADES 未知

    公开(公告)号：CA2555833C

    公开(公告)日：2015-12-22

    申请号：CA2555833

    申请日：2006-08-11

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： KANG MOON-KYOO BRIAN ,  LONCZAK KENNETH A ,  PIETRASZKIEWICZ EDWARD F

    IPC: F01D5/12

    Abstract: An identification feature is used to unmistakably identify internal features present in different generations of turbine blade designs. The identification feature is located on a root portion of the turbine blade and protrudes to provide a visually identifiable feature that is also readable by a coordinate measuring machine, but does not interfere with installation or operation of the turbine blade. The weight of the identification feature is in a specific proportion to the weight of the turbine blade in order to prevent interfere with operation of the turbine blade during high-speed rotation in a gas turbine engine.

    TURBINE VANE CONSTRUCTION
    13.
    发明专利
    TURBINE VANE CONSTRUCTION 未知

    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

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

    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.

    MISTAKE PROOF IDENTIFICATION FEATURE FOR TURBINE BLADES
    14.
    发明专利
    MISTAKE PROOF IDENTIFICATION FEATURE FOR TURBINE BLADES 未知

    公开(公告)号：CA2555833A1

    公开(公告)日：2007-02-15

    申请号：CA2555833

    申请日：2006-08-11

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： KANG MOON-KYOO BRIAN ,  PIETRASZKIEWICZ EDWARD F ,  LONCZAK KENNETH A

    IPC: F01D5/12

    Abstract: An identification feature is used to unmistakably identify internal features present in different generations of turbine blade designs. The identification feature is located on a root portion of the turbine blade and protrudes to provide a visually identifiable feature that is also readable b y a coordinate measuring machine, but does not interfere with installation or operation of the turbine blade. The weight of the identification feature is in a specific proportion to the weight of the turbine blade in order to prevent interfere with operation of the turbine blade during high-speed rotation in a gas turbine engine.

    Cooled airfoil with reduced internal turn losses
    15.
    发明专利
    Cooled airfoil with reduced internal turn losses 未知

    公开(公告)号：AU2006202304A1

    公开(公告)日：2006-12-14

    申请号：AU2006202304

    申请日：2006-05-30

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： KOHIL ATUL ,  PIETRASZKIEWICZ EDWARD F

    IPC: F01D5/18 ,  F01D5/08 ,  F01D5/14

    Abstract: A cooled airfoil ( 10 ) has an internal fluid passage ( 34 ) that includes upstream and downstream legs, such as a co-centrifugal leg ( 40 ) and a counter-centrifugal leg ( 42 ). The legs are separated from each other by a rib ( 44 ) but are connected in series with each other. The airfoil also includes a vent passage ( 56 ) for venting fluid from the internal passage. The intake ( 60 ) to the vent passage resides in the counter-centrifugal leg. The vent at least partially counteracts the separation potential of a separation susceptible region ( 54 ) by allowing some of the coolant to vent from the passage leg ( 42 ).

    DIRT SEPARATOR FOR GAS TURBINE AIR SUPPLY
    18.
    发明专利
    DIRT SEPARATOR FOR GAS TURBINE AIR SUPPLY 未知

    公开(公告)号：SG130170A1

    公开(公告)日：2007-03-20

    申请号：SG2006058184

    申请日：2006-08-25

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： SILVERMAN RICHARD ,  BECKWITH BARRY ,  OAENEILL LISA ,  PIETRASZKIEWICZ EDWARD F

    Abstract: A gas turbine engine is provided with a radially outer cooling air flow. A dirt separator is placed in the path of the radially outer cooling air flow, and includes a radially outer leg that defines a space to capture dirt or other impurities. A radially inner leg of the dirt separator includes open air flow passages to allow air to flow through the inner leg and downstream to cool various components within the gas turbine engine.

    MANUFACTURABLE AND INSPECTABLE MICROCIRCUITS
    19.
    发明专利
    MANUFACTURABLE AND INSPECTABLE MICROCIRCUITS 未知

    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.

    TURBINE VANE CONSTRUCTION
    20.
    发明专利
    TURBINE VANE CONSTRUCTION 未知

    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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