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：DE4003803A1

公开(公告)日：1998-01-08

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

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：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：NO900803A

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

CPC classification number: F01D11/10 ,  F01D5/186 ,  F01D5/20 ,  F05D2260/201 ,  F05D2260/202 ,  Y02T50/671 ,  Y02T50/673 ,  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：AU594106B2

公开(公告)日：1990-03-01

申请号：AU6656186

申请日：1986-12-15

Applicant: UNITED TECHNOLOGIES CORP

Inventor： AUXIER THOMAS A ,  ANDERSON LEON R ,  HILL EDWARD C JR

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

公开(公告)号：GB2506092A

公开(公告)日：2014-03-26

申请号：GB9500234

申请日：1995-01-06

Applicant: UNITED TECHNOLOGIES CORP

Inventor： SOECHTING FRIEDRICH OTTO ,  AUXIER THOMAS A

IPC: F01D5/18

Abstract: Film cooling effectiv eness for internally air cooled turbine blades of gas turbine engines is enhanced by includi ng an interconnecting passage 68 to the film cooling hole 66 that is in communication with a lower internal pressure in the blade to create a suction at the exit end of the film hole to limit penetration into the working gas stream.

公开(公告)号：DE60031185T2

公开(公告)日：2007-08-23

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：DE69828757D1

公开(公告)日：2005-03-03

申请号：DE69828757

申请日：1998-12-02

Applicant: UNITED TECHNOLOGIES CORP

Inventor： TABBITA MARTIN G ,  DOWNS JAMES P ,  SOECHTING FRIEDRICH ,  AUXIER THOMAS A

IPC: F01D5/18

Abstract: A hollow airfoil 10 is provided with a trench 18 which is aligned with a stagnation line 42 extending along the leading edge 26. Cooling air apertures 38 extend between an inner cavity of the airfoil and the trench 18 to supply cooling air thereto.

公开(公告)号：DE69811562T2

公开(公告)日：2003-08-28

申请号：DE69811562

申请日：1998-05-20

Applicant: UNITED TECHNOLOGIES CORP

Inventor： NARCUS ANDREW R ,  HAYES DOUGLAS A ,  AUXIER THOMAS A

IPC: F02K3/06 ,  F01D17/10 ,  F02C9/18 ,  F02K3/075 ,  F02K3/077 ,  F02K3/10

Abstract: A bypass air valve for a gas turbine engine is provided which includes a liner 36, a strap 34, and means 40 for selectively actuating the valve. The liner 36 includes an inner radial surface 42, an outer radial surface 44, a plurality of first regions 46, and a plurality of second regions 48. Each first region 46 includes a plurality of first apertures 52. Each second region 48 includes a plurality of second apertures 56. The strap 34 includes a plurality of openings 78 and a plurality of third regions 76. Each third region 76 includes a plurality of third apertures 80. The valve may be selectively actuated into an open or a closed position. In the open position, the first regions 46 are substantially aligned with the openings 78 and the third regions 76 are substantially aligned with the second regions 48. In the closed position, the first regions 46 are substantially aligned with the third regions 76 and the second regions 48 are substantially aligned with the openings 78.