公开(公告)号：DE4003804C2

公开(公告)日：1999-03-04

申请号：DE4003804

申请日：1990-02-08

Applicant: UNITED TECHNOLOGIES CORP

Inventor： HALL KENNETH B ,  MCCLELLAND 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.

公开(公告)号：AU698776B2

公开(公告)日：1998-11-05

申请号：AU6067496

申请日：1996-07-24

Applicant: UNITED TECHNOLOGIES CORP

Inventor： KRAFT ROBERT J ,  MCCLELLAND ROBERT J

IPC: F01D5/16 ,  F01D5/18 ,  F01D5/26 ,  F04D29/38 ,  F04D29/66

Abstract: A rotor blade (12) for a rotor assembly (8) is provided which includes a root (18), an airfoil (20) and a platform (22). The airfoil includes at least one cavity (40,42). The platform (22) extends laterally outward from the blade (12) between the root (18) and the airfoil (20), and includes an airfoil side, a root side, and an aperture extending between the root side of the platform and the cavity within the airfoil. A damper (24), which includes at least one bearing surface (68), may be received within the aperture and the cavity (40,42). The bearing surface (68) is in contact with a surface (50) within the cavity (40,42) and friction between the bearing surface (68) and the surface (50) within the cavity (40,42) damps vibration of the blade (12).

公开(公告)号：NO306740B1

公开(公告)日：1999-12-13

申请号：NO900804

申请日：1990-02-20

Applicant: UNITED TECHNOLOGIES CORP

Inventor： HALL KENNETH B ,  MCCLELLAND 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.

公开(公告)号：NO900804L

公开(公告)日：1997-06-10

申请号：NO900804

申请日：1990-02-20

Applicant: UNITED TECHNOLOGIES CORP

Inventor： HALL KENNETH B ,  MCCLELLAND 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.

公开(公告)号：SE9000112L

公开(公告)日：1998-05-03

申请号：SE9000112

申请日：1990-01-12

Applicant: UNITED TECHNOLOGIES CORP

Inventor： HALL KENNETH B ,  MCCLELLAND 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.

公开(公告)号：DE4003804A1

公开(公告)日：1998-01-08

申请号：DE4003804

申请日：1990-02-08

Applicant: UNITED TECHNOLOGIES CORP

Inventor： HALL KENNETH B ,  MCCLELLAND 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.

公开(公告)号：SE470599B

公开(公告)日：1998-09-14

申请号：SE9000112

申请日：1990-01-12

Applicant: UNITED TECHNOLOGIES CORP

Inventor： HALL KENNETH B ,  MCCLELLAND 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.

公开(公告)号：NO900804A

公开(公告)日：1997-06-10

申请号：NO900804

申请日：1990-02-20

Applicant: UNITED TECHNOLOGIES CORP

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

IPC: F01D5/18

CPC classification number: F01D5/187 ,  F01D5/186 ,  F05D2260/201 ,  F05D2260/2212 ,  Y02T50/671 ,  Y02T50/676

公开(公告)号：CA2007631A1

公开(公告)日：1997-06-06

申请号：CA2007631

申请日：1990-01-12

Applicant: UNITED TECHNOLOGIES CORP

Inventor： AUXIER THOMAS A ,  HALL KENNETH B ,  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.

公开(公告)号：DE69624420T2

公开(公告)日：2003-08-14

申请号：DE69624420

申请日：1996-07-31

Applicant: UNITED TECHNOLOGIES CORP

Inventor： KRAFT ROBERT J ,  MCCLELLAND ROBERT J

IPC: F01D5/16 ,  F01D5/18 ,  F01D5/26

Abstract: A rotor blade (12) for a rotor assembly (8) is provided which includes a root (18), an airfoil (20) and a platform (22). The airfoil includes at least one cavity (40,42). The platform (22) extends laterally outward from the blade (12) between the root (18) and the airfoil (20), and includes an airfoil side, a root side, and an aperture extending between the root side of the platform and the cavity within the airfoil. A damper (24), which includes at least one bearing surface (68), may be received within the aperture and the cavity (40,42). The bearing surface (68) is in contact with a surface (50) within the cavity (40,42) and friction between the bearing surface (68) and the surface (50) within the cavity (40,42) damps vibration of the blade (12).