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：CA2007631C

公开(公告)日：2000-03-14

申请号：CA2007631

申请日：1990-01-12

Applicant: UNITED TECHNOLOGIES CORP

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

IPC: F01D5/18

Abstract: An internally cooled turbine blade for a gas turbine engine is modified at the leading and trailing edges to include a dynamic cool air flowing radial passageway with an inlet at the root and a discharge at the tip feeding a plurality of radially spaced film cooling holes in the airfoil surface. Replenishment holes communicating with the serpentine passages radially spaced in the inner wall of the radial passage replenish the cooling air lost to the film cooling holes. The discharge orifice is sized to match the backflow margin to achieve a constant film hole coverage throughout the radial length. Trip strips may be employed to augment the pressure drop distribution

公开(公告)号：DE69414209T2

公开(公告)日：1999-06-10

申请号：DE69414209

申请日：1994-08-23

Applicant: UNITED TECHNOLOGIES CORP

Inventor： AUXIER THOMAS A ,  HALL KENNETH B

IPC: F01D5/18 ,  F01D9/02 ,  F02C7/18

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.

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.

公开(公告)号：DE69613307T2

公开(公告)日：2001-09-20

申请号：DE69613307

申请日：1996-10-10

Applicant: UNITED TECHNOLOGIES CORP

Inventor： SOECHTING FRIEDRICH O ,  PLANK WILLIAM L ,  HALL KENNETH B

IPC: F01D9/02 ,  F01D5/18 ,  F01D9/04 ,  F01D25/12 ,  F02C7/18

Abstract: A vane assembly (14) for a gas turbine engine (12) includes a plurality of vanes (28), each having a forward compartment (44) and an aft compartment (46), an inner vane support (30), a casing (16), and apparatus (50,54) for maintaining a pressure difference between the compartments. The casing (16), which includes an annulus (18), is positioned radially outside of the vanes. The vanes (28) extend between the inner vane support (30) and the casing (16). The apparatus for maintaining a pressure difference may comprise a flow meter (50,54) at the entrance to the aft compartment. A modulating valve (22) may be provided to control the flow of cooling air into the annulus, and thus into the vanes.

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.

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.