公开(公告)号：FR2798422A1

公开(公告)日：2001-03-16

申请号：FR9000792

申请日：1990-01-24

Applicant: UNITED TECHNOLOGIES CORP

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

IPC: F01D5/18 ,  F01D5/20 ,  F01D1/00

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.

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.

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.

公开(公告)号：FR2798423A1

公开(公告)日：2001-03-16

申请号：FR9000793

申请日：1990-01-24

Applicant: UNITED TECHNOLOGIES CORP

Inventor： HUBER FRANK W ,  DIETRICH DOUGLAS J

IPC: F01D5/18 ,  F01D5/20 ,  F01D11/10 ,  F01D1/00

Abstract: The axial flow turbine includes a number of internally air cooled turbine blades each having a tip section mounted adjacent the shroud and defining with it a gap that is susceptible of leaking engine working medium. Each internally cooled blade has an airfoil surface exposed to the engine working medium defining a pressure surface and a suction surface. A device minimises the leakage by providing a buffer zone in the gap. The device includes an orifice located in the tip section adjacent the pressure surface. The orifice is skewed relative to the rotation axis of the blade for leading air from internally of the blade into the gap toward the pressure side of the blades. The stream of air discharging from the orifice defines a buffer zone.

公开(公告)号：DE4003803C2

公开(公告)日：1999-06-17

申请号：DE4003803

申请日：1990-02-08

Applicant: UNITED TECHNOLOGIES CORP

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

IPC: F01D5/18 ,  F01D11/10

公开(公告)号：SE470601B

公开(公告)日：1998-09-14

申请号：SE9000236

申请日：1990-01-23

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.

公开(公告)号：DE4003802A1

公开(公告)日：1998-01-15

申请号：DE4003802

申请日：1990-02-08

Applicant: UNITED TECHNOLOGIES CORP

Inventor： HUBER FRANK W ,  DIETRICH DOUGLAS J

IPC: F01D5/14 ,  F01D5/18 ,  F01D11/10 ,  F02C7/18 ,  F02C7/28

Abstract: The axial flow turbine includes a number of internally air cooled turbine blades each having a tip section mounted adjacent the shroud and defining with it a gap that is susceptible of leaking engine working medium. Each internally cooled blade has an airfoil surface exposed to the engine working medium defining a pressure surface and a suction surface. A device minimises the leakage by providing a buffer zone in the gap. The device includes an orifice located in the tip section adjacent the pressure surface. The orifice is skewed relative to the rotation axis of the blade for leading air from internally of the blade into the gap toward the pressure side of the blades. The stream of air discharging from the orifice defines a buffer zone.

公开(公告)号：NO900805A

公开(公告)日：1997-06-10

申请号：NO900805

申请日：1990-02-20

Applicant: UNITED TECHNOLOGIES CORP

Inventor： HUBER FRANK W ,  DIETRICH DOUGLAS H

IPC: F01D5/20 ,  F01P20060101 ,  F02C20060101

公开(公告)号：DE4042729C2

公开(公告)日：2002-10-31

申请号：DE4042729

申请日：1990-02-08

Applicant: UNITED TECHNOLOGIES CORP

Inventor： HUBER FRANK W ,  DIETRICH DOUGLAS J

IPC: F01D5/14 ,  F01D5/18 ,  F01D11/10 ,  F01D5/20

Abstract: The axial flow turbine includes a number of internally air cooled turbine blades each having a tip section mounted adjacent the shroud and defining with it a gap that is susceptible of leaking engine working medium. Each internally cooled blade has an airfoil surface exposed to the engine working medium defining a pressure surface and a suction surface. A device minimises the leakage by providing a buffer zone in the gap. The device includes an orifice located in the tip section adjacent the pressure surface. The orifice is skewed relative to the rotation axis of the blade for leading air from internally of the blade into the gap toward the pressure side of the blades. The stream of air discharging from the orifice defines a buffer zone.

公开(公告)号：FR2798423B1

公开(公告)日：2002-10-11

申请号：FR9000793

申请日：1990-01-24

Applicant: UNITED TECHNOLOGIES CORP

Inventor： HUBER FRANK W ,  DIETRICH DOUGLAS J

IPC: F01D5/18 ,  F01D5/20 ,  F01D11/10 ,  F01D1/00