中科微点-全球专利检索

  1. Login
  2. Sign Up

Search Results

67 records (took 0.023 seconds)

    Cooled blades for a gas turbine engine
    11.
    发明专利
    Cooled blades for a gas turbine engine 未知

    公开(公告)号：AU684037B1

    公开(公告)日：1997-12-04

    申请号：AU4881290

    申请日：1990-01-12

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： HALL KENNETH B ,  AUXIER THOMAS A ,  MCCLELLAND ROBERT J

    IPC: F01D5/18

    Abstract: A turbine blade for a gas turbine engine has internal passages which are opened at their roots to supply pressure so that there is a constant flow of cooling air inside the blade in use. The blade has an airfoil surface and a number of internal passages inside the walls of the blade, some being formed adjacent the mid-chord section and extend from the root section to the tip section to define feed channels open at the blade root section. A number of radially spaced film cooling holes in the airfoil surface communicate with each feed channel to flow a film of cooling air adjacent the airfoil surface. A number of replenishment holes are radially spaced in the wall to flow air from the mid-chord section to the feed channel(s) to replenish the cooling air in the feed channel(s) that is otherwise lost in supplying air to the film cooling holes. A device communicates cooling air from the root section via the feed channels to discharge from orifices in the airfoil surface at the tip section.

    12.
    发明专利
    未知

    公开(公告)号：NO900803L

    公开(公告)日：1997-06-10

    申请号：NO900803

    申请日：1990-02-20

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： SELLERS ROBERT R ,  SOECHTING FRIEDRICH O ,  HUBER FRANK W ,  AUXIER THOMAS A

    IPC: F01D5/18 ,  F01D11/10 ,  F01D

    Abstract: An axial flow turbine comprises a number of air cooled blades each of which have an airfoil surface exposed to the working medium defining a pressure side, a suction side, a root section, a tip section, and a mid chord section. Each blade having internal passages including at least one radial passage (26) defining a first feed channel adjacent the pressure side conducting cooling air from the root section to an outlet opening in the tip section, a number of radially spaced film cooling holes (28) in the airfoil surface being fed cool air from the feed channel, a second radial passage (32) defining a feed chamber in the mid chord section conducting cooling air from the root section to an orifice in the tip section, a number of radially spaced replenishment cooling holes communicating with the feed chamber for replenishing air in the feed channel whereby the rotation of the turbine centrifuges the air in the radial passages to increase the pressure of the cooling air as the air progresses toward the tip section of the blade.

    COOLED BLADES FOR A GAS TURBINE ENGINE
    13.
    发明专利
    COOLED BLADES FOR A GAS TURBINE ENGINE 未知

    公开(公告)号：CA2007632A1

    公开(公告)日：1997-06-06

    申请号：CA2007632

    申请日：1990-01-12

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： SELLERS ROBERT R ,  SOECHTING FRIEDRICH O ,  HUBER FRANK W ,  AUXIER THOMAS A

    IPC: F01D5/18 ,  F01D11/10

    Abstract: An axial flow turbine comprises a number of air cooled blades each of which have an airfoil surface exposed to the working medium defining a pressure side, a suction side, a root section, a tip section, and a mid chord section. Each blade having internal passages including at least one radial passage (26) defining a first feed channel adjacent the pressure side conducting cooling air from the root section to an outlet opening in the tip section, a number of radially spaced film cooling holes (28) in the airfoil surface being fed cool air from the feed channel, a second radial passage (32) defining a feed chamber in the mid chord section conducting cooling air from the root section to an orifice in the tip section, a number of radially spaced replenishment cooling holes communicating with the feed chamber for replenishing air in the feed channel whereby the rotation of the turbine centrifuges the air in the radial passages to increase the pressure of the cooling air as the air progresses toward the tip section of the blade.

    FILM COOLANT PASSAGES FOR CAST HOLLOW AIRFOILS
    15.
    发明专利
    FILM COOLANT PASSAGES FOR CAST HOLLOW AIRFOILS 未知

    公开(公告)号：CA1274181A

    公开(公告)日：1990-09-18

    申请号：CA526012

    申请日：1986-12-22

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： AUXIER THOMAS A ,  FIELD ROBERT E

    IPC: B23K26/38 ,  F01D5/18 ,  F01D9/02

    Abstract: Film Coolant Passages for Cast Hollow Airfoils The external wall of a hollow airfoil for a gas turbine engine has a plurality of longitudinally aligned diffusing coolant passages having their outlets at the outer surface over which a hot gas is intended to flow. The airfoil external wall also includes a longitudinally extending slot formed in the inner surface thereof. Each of the coolant passages intersect such longitudinally extending slot to define metering inlets to each passage for receiving coolant fluid from the slot at a controlled rate. The coolant diffuses as it passes through each passage and exits as a thin film on the external surface of the airfoil. The slot is cast in the inner surface of the wall at the time of forming the airfoil; and the passages are machined into the wall from outside the airfoil. Very small, accurate metering areas for each passage can thereby be formed in single-piece hollow airfoils without access to the interior of the airfoil.

    16.
    发明专利
    未知

    公开(公告)号：TR23588A

    公开(公告)日：1990-04-19

    申请号：TR20290

    申请日：1990-03-07

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： HALL KENNETH B ,  CLELLAND ROBERT J MC ,  AUXIER THOMAS A

    IPC: F01D5/18 ,  F02C ,  F01P

    Abstract: A turbine blade for a gas turbine engine has internal passages which are opened at their roots to supply pressure so that there is a constant flow of cooling air inside the blade in use. The blade has an airfoil surface and a number of internal passages inside the walls of the blade, some being formed adjacent the mid-chord section and extend from the root section to the tip section to define feed channels open at the blade root section. A number of radially spaced film cooling holes in the airfoil surface communicate with each feed channel to flow a film of cooling air adjacent the airfoil surface. A number of replenishment holes are radially spaced in the wall to flow air from the mid-chord section to the feed channel(s) to replenish the cooling air in the feed channel(s) that is otherwise lost in supplying air to the film cooling holes. A device communicates cooling air from the root section via the feed channels to discharge from orifices in the airfoil surface at the tip section.

    Air-cooled gas turbine blade
    19.
    发明专利
    Air-cooled gas turbine blade 未知

    公开(公告)号：FR2798421A1

    公开(公告)日：2001-03-16

    申请号：FR9000791

    申请日：1990-01-24

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： HALL KENNETH B ,  MC CLELLAND ROBERT J ,  AUXIER THOMAS A

    IPC: F01D5/18

    Abstract: A turbine blade for a gas turbine engine has internal passages which are opened at their roots to supply pressure so that there is a constant flow of cooling air inside the blade in use. The blade has an airfoil surface and a number of internal passages inside the walls of the blade, some being formed adjacent the mid-chord section and extend from the root section to the tip section to define feed channels open at the blade root section. A number of radially spaced film cooling holes in the airfoil surface communicate with each feed channel to flow a film of cooling air adjacent the airfoil surface. A number of replenishment holes are radially spaced in the wall to flow air from the mid-chord section to the feed channel(s) to replenish the cooling air in the feed channel(s) that is otherwise lost in supplying air to the film cooling holes. A device communicates cooling air from the root section via the feed channels to discharge from orifices in the airfoil surface at the tip section.

Patent Agency Ranking