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    WALL COOLED IN AEROFOIL
    1.
    发明专利
    WALL COOLED IN AEROFOIL 失效

    公开(公告)号：JPS62168904A

    公开(公告)日：1987-07-25

    申请号：JP30757986

    申请日：1986-12-23

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： FIELD ROBERT EUGENE

    IPC: F01D5/18 ,  F01D9/02

    Abstract: A film cooling passage through the external wall of a hollow airfoil for a gas turbine engine has a metering section in series flow relation with a diffusing section leading to the passage outlet at the external surface of the airfoil over which a hot gas flows during operation. The diffusing section is generally rectangular in cross section perpendicular to the axis of the passage. Upstream and downstream longitudinally extending, spaced apart, facing surfaces of the diffusing section are joined together by a pair of spaced apart side walls which face each other and diverge from each other in the longitudinal direction toward the outlet of the passage. These side walls blend, along their length, with the downstream surface as a smooth curve of large radius. The diameter of the corner curvature of the passage is on the same order of magnitude as the distance between the upstream and downstream surfaces of the diffusing section at the location in question. The large corner curvatures, as opposed to filet radii, allow the side walls to diverge from each other at a greater angle without separation of the coolant fluid therefrom, permitting the spreading of smaller amounts of coolant air over a larger area of the airfoil external surface.

    FILM COOLING SLOT WITH METERED FLOW
    4.
    发明专利
    FILM COOLING SLOT WITH METERED FLOW 未知

    公开(公告)号：AU593309B2

    公开(公告)日：1990-02-08

    申请号：AU6668086

    申请日：1986-12-16

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： FIELD ROBERT EUGENE ,  PHILLIPS JAMES STEWART

    IPC: F01D5/18 ,  F01D25/12 ,  F01P1/06 ,  F01P7/02

    Abstract: The wall of a hollow airfoil for a gas turbine engine includes a film cooling slot therein elongated in the longitudinal direction and having a base within the wall and an outlet at the external surface of the airfoil. A plurality of metering passages extend from inlets at the internal surface of the wall and intersect the slot near its base. The metering passages are angled to direct a metered flow of coolant fluid at a sharp angle against a surface of the slot to cause turbulence and diffusion of the coolant fluid within the slot in order that the coolant fluid fill the entire slot. The coolant fluid thereupon exits the slot as a thin film over the surface of the airfoil downstream of the slot outlet along the full length of the slot.

    8.
    发明专利
    未知

    公开(公告)号：DE3683743D1

    公开(公告)日：1992-03-12

    申请号：DE3683743

    申请日：1986-12-18

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： PHILLIPS JAMES STEWART ,  FIELD ROBERT EUGENE

    IPC: F01D5/18 ,  F01D9/02

    Abstract: The wall of a hollow turbine airfoil has a longitudinally extending coolant outlet slot in its external surface which intersects, along its length, a longitudinally extending cylindrical channel within the wall. Metering passages extend from the inside surface of the airfoil wall to the cylindrical channel and direct a metered amount of coolant into the channel in a manner which results in a swirling motion being imparted to the fluid as the fluid diffuses within the channel. The coolant is thereupon ejected from the channel through the slot in the external surface as a film on the external surface of the airfoil along the length of the slot. The swirling of the fluid within the cylindrical channel helps diffuse the fluid such that the outlet slot becomes completely filled with coolant, whereby a film of coolant is created on the airfoil surface downstream of the slot over the full length of the slot.

    IMPROVED FILM COOLING PASSAGES - E.G. FOR TURBINE BLADES
    9.
    发明专利
    IMPROVED FILM COOLING PASSAGES - E.G. FOR TURBINE BLADES 未知

    公开(公告)号：AU599941B2

    公开(公告)日：1990-08-02

    申请号：AU6656086

    申请日：1986-12-15

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： FIELD ROBERT EUGENE

    IPC: F01D5/18 ,  F01D9/02 ,  F01D25/12 ,  F01P1/06 ,  F01P7/02

    Abstract: A film cooling passage through the external wall of a hollow airfoil for a gas turbine engine has a metering section in series flow relation with a diffusing section leading to the passage outlet at the external surface of the airfoil over which a hot gas flows during operation. The diffusing section is generally rectangular in cross section perpendicular to the axis of the passage. Upstream and downstream longitudinally extending, spaced apart, facing surfaces of the diffusing section are joined together by a pair of spaced apart side walls which face each other and diverge from each other in the longitudinal direction toward the outlet of the passage. These side walls blend, along their length, with the downstream surface as a smooth curve of large radius. The diameter of the corner curvature of the passage is on the same order of magnitude as the distance between the upstream and downstream surfaces of the diffusing section at the location in question. The large corner curvatures, as opposed to filet radii, allow the side walls to diverge from each other at a greater angle without separation of the coolant fluid therefrom, permitting the spreading of smaller amounts of coolant air over a larger area of the airfoil external surface.

    IMPROVED SURFACE FILM COOLING EFFECTIVENESS AND COOLING SLOTSTHEREFOR
    10.
    发明专利
    IMPROVED SURFACE FILM COOLING EFFECTIVENESS AND COOLING SLOTSTHEREFOR 未知

    公开(公告)号：AU6668086A

    公开(公告)日：1987-06-25

    申请号：AU6668086

    申请日：1986-12-16

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： FIELD ROBERT EUGENE ,  PHILLIPS JAMES STEWART

    IPC: F01D5/18 ,  F01D25/12 ,  F01P1/06 ,  F01P7/02

    Abstract: The wall of a hollow airfoil for a gas turbine engine includes a film cooling slot therein elongated in the longitudinal direction and having a base within the wall and an outlet at the external surface of the airfoil. A plurality of metering passages extend from inlets at the internal surface of the wall and intersect the slot near its base. The metering passages are angled to direct a metered flow of coolant fluid at a sharp angle against a surface of the slot to cause turbulence and diffusion of the coolant fluid within the slot in order that the coolant fluid fill the entire slot. The coolant fluid thereupon exits the slot as a thin film over the surface of the airfoil downstream of the slot outlet along the full length of the slot.

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