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：SE9000236L

公开(公告)日：1998-05-03

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：DE68906594D1

公开(公告)日：1993-06-24

申请号：DE68906594

申请日：1989-04-20

Applicant: UNITED TECHNOLOGIES CORP

Inventor： HALL KENNETH B ,  AUXIER THOMAS A ,  BROWN WESLEY D

IPC: F01D5/08 ,  F01D5/18 ,  F01D25/32 ,  F02C7/30

公开(公告)号：ES2015675A6

公开(公告)日：1990-09-01

申请号：ES8901829

申请日：1989-05-30

Applicant: UNITED TECHNOLOGIES CORP

Inventor： AUXIER THOMAS A ,  FIELD ROBERT E ,  RANNIE JAMES B

IPC: F02K1/82 ,  F23R3/00 ,  F24H8/00 ,  F23R3/08

Abstract: UNA CAMISA PARA CONDUCTO DE GAS CALIENTE. SE FIJAN PLACAS DE CAMISA SOLAPADAS (12), (14), (16) EN EL EXTREMO CORRIENTE ARRIBA A LA SUPERFICIE DE SOPORTE (22). AIRE DE REFRIGERACION (26) SUMINISTRADO A TRAVES DE CAMARAS COMPARTIMENTALES (24) PASA ENTRE (54) LAS PLACAS Y SOBRE (56) LA SUPERFICIE DE LAS PLACAS. DEPRESIONES ALARGADAS COMPLEMENTARIAS (40), (46) GUIAN DE FORMA SELECTIVA EL FLUJO DE AIRE Y PROPORCIONAN FLEXIBILIDAD PARA ABSORBER EXPANSIONES TRANSVERSALES.

公开(公告)号：AU6674386A

公开(公告)日：1987-06-25

申请号：AU6674386

申请日：1986-12-17

Applicant: UNITED TECHNOLOGIES CORP

Inventor： AUXIER THOMAS A ,  FIELD ROBERT EUGENE

IPC: B23K26/38 ,  F01D5/18 ,  F01D9/02 ,  F01D25/12 ,  F01P1/06 ,  F01P7/02

公开(公告)号：DE60041366D1

公开(公告)日：2009-02-26

申请号：DE60041366

申请日：2000-06-23

Applicant: UNITED TECHNOLOGIES CORP

Inventor： AUXIER THOMAS A ,  DOWNS JAMES P ,  CALHOUN WILLIAM H ,  KVASNAK WILLIAM S ,  SOECHTING FRIEDRICH O ,  HAYES DOUGLAS A

IPC: F01D5/18 ,  F01D9/02

Abstract: A method and apparatus for cooling a wall within a gas turbine engine is provided which comprises the steps of: (1) providing a wall having an internal surface and an external surface; (2) providing a cooling microcircuit within the wall that has a passage for cooling air that extends between the internal surface and the external surface; and (3) increasing heat transfer from the wall to a fluid flow within the passage by increasing the average heat transfer coefficient per unit flow within the microcircuit. According to one aspect, the present invention method and apparatus can be tuned to substantially match the thermal profile of the wall at hand.

公开(公告)号：DE60031185D1

公开(公告)日：2006-11-16

申请号：DE60031185

申请日：2000-06-23

Applicant: UNITED TECHNOLOGIES CORP

Inventor： AUXIER THOMAS A ,  DOWNS JAMES P ,  CALHOUN WILLIAM H ,  KVASNAK WILLIAM S ,  SOECHTING FRIEDRICH O ,  HAYES DOUGLAS A

IPC: F01D5/18 ,  F01D9/02

Abstract: A method and apparatus for cooling a wall within a gas turbine engine is provided which comprises the steps of: (1) providing a wall having an internal surface and an external surface; (2) providing a cooling microcircuit within the wall that has a passage for cooling air that extends between the internal surface and the external surface; and (3) increasing heat transfer from the wall to a fluid flow within the passage by increasing the average heat transfer coefficient per unit flow within the microcircuit. According to one aspect, the present invention method and apparatus can be tuned to substantially match the thermal profile of the wall at hand.

公开(公告)号：DE60025074T2

公开(公告)日：2006-06-29

申请号：DE60025074

申请日：2000-06-23

Applicant: UNITED TECHNOLOGIES CORP

Inventor： AUXIER THOMAS A ,  KVASNAK WILLIAM S ,  DOWNS JAMES P ,  SOECHTING FRIEDRICH O ,  CALHOUN WILLIAM H ,  HAYES DOUGLAS A

IPC: F01D5/18 ,  F01D9/02

Abstract: A method and apparatus for cooling a wall within a gas turbine engine is provided which comprises the steps of: (1) providing a wall having an internal surface and an external surface; (2) providing a cooling microcircuit within the wall that has a passage for cooling air that extends between the internal surface and the external surface; and (3) increasing heat transfer from the wall to a fluid flow within the passage by increasing the average heat transfer coefficient per unit flow within the microcircuit. According to one aspect, the present invention method and apparatus can be tuned to substantially match the thermal profile of the wall at hand.

公开(公告)号：CA2007632C

公开(公告)日：2000-03-14

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 internally air cooled turbine blade for a gas turbine engine of the type including a trailing edge section, leading edge section and mid chord section wherein each section includes a straight through radial passage communicating cooling air from the root to the tip of the blade, and the radial passages (feed channels) on the pressure side and suction side supply the cooling air to the film cooling holes in the airfoil surface and the radial passage (feed chamber) in the mid chord section replenishes the feed channels with cooling air through replenishment cooling holes interconnecting the feed channels and feed chamber. The rotation of the blade imparts a centrifugal pumping action to the air within the feed chamber for maximizing the cooling effectiveness of the cooling air. The air discharging at the tip cools the tip of the blade and provides tip aerodynamic sealing and the leading edge and trailing edge are similarly fed cooling air.

公开(公告)号：NO306739B1

公开(公告)日：1999-12-13

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

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.