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：DE69409332D1

公开(公告)日：1998-05-07

申请号：DE69409332

申请日：1994-12-12

Applicant: UNITED TECHNOLOGIES CORP

Inventor： KELCH GEORGE W ,  AUXIER THOMAS A

IPC: F01D11/00 ,  F01D11/08 ,  F01D25/12 ,  F02C7/18 ,  F02C7/28

Abstract: The seal comprises arcuate seal segments extending circumferentially about the flow path, each segment spaced radially outward from the turbine blades. Each seal segment includes an arcuate sealing surface having a first end, a second end opposite the first end, and a radius of curvature equal to the distance between the sealing surface and the axis. There is a supply surface opposite and in spaced relation to the sealing surface and having cooling orifices. There is a first end surface extending along the entire first end, and a second end surface extending along the entire second end. The first and second end surfaces extend from the sealing surface to the supply surface. Each of the first and second end surfaces includes a planar perpendicular surface and a planar canted surface intersecting at an included angle of between 100 degrees and 140 degrees. Each canted surface is canted in the first direction.

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：CA1274776A

公开(公告)日：1990-10-02

申请号：CA526021

申请日：1986-12-22

Applicant: UNITED TECHNOLOGIES CORP

Inventor： ANDERSON LEON R ,  AUXIER THOMAS A

IPC: F01D5/18

Abstract: Film Cooled Vanes and Turbines The film of cooling air adjacent the outer surface of the airfoil of a turbine of a gas turbine engine issuing from internally of the turbine subsequent to cooling is controlled by regulating the pressure ratio of the internal to external pressures by forming an internal chamber extending longitudinally in the turbine and having fixed orifices admitting cooling air therein bearing a predetermined relationship to the exit orifices forming the film of cooling air. By regulating this pressure ratio the diameter of the exit holes can be longer than heretofore designs for a given application so that they can be precast rather than drilled and can be arranged to give fuller coverage of films of cooling air on the outer surface of the airfoil.

公开(公告)号：CA1273583A

公开(公告)日：1990-09-04

申请号：CA526009

申请日：1986-12-22

Applicant: UNITED TECHNOLOGIES CORP

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

IPC: F01D5/18 ,  F01D9/02

Abstract: Coolant Passages With Full Coverage Film Cooling Slot The wall of a hollow airfoil has a longitudinally extending slot in its external surface which is intersected, at its base, by a plurality of coolant passages in a longitudinally extending row. Each coolant passage has a metering portion at its inner end which communicates with a coolant compartment within the hollow airfoil. Each passage includes a pair of walls downstream of the metering portion which diverge from each other in the longitudinal direction and intersect with the base of the slot to form an outlet for the passage. The diverging walls of adjacent passages substantially meet each other at the base of the slot, wherein coolant fluid from the metering portions of the passages diffuses in the longitudinal direction as it flows toward and into the slot, filling the entire slot and forming a thin, continuous film of coolant downstream of and along the entire length of the slot over the external surface of the airfoil.

公开(公告)号：AU591952B2

公开(公告)日：1989-12-21

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