公开(公告)号：DE19502998A1

公开(公告)日：2003-07-17

申请号：DE19502998

申请日：1995-01-31

Applicant: UNITED TECHNOLOGIES CORP

Inventor： SOECHTING FRIEDRICH O ,  AUXIER THOMAS A

IPC: F01D5/18

Abstract: The airfoil comprises of a leading edge (18) and a trailing edge (20) that is located downstream of a compressor airflow. The air is directed into internal chambers (55.56) within the airfoil and out through ports located along the pressure side of the airfoil between leading and trailing edges to form a cooling airflow. An additional film cooling hole (66) is located near the trailing edge of the airfoil. The film cooling hole admits an additional airflow into high and low pressure chambers (60,64) that are downstream of the initial internal airfoil flow. The two chambers are in communication via a passage (62). This creates a pressure drop in the downstream direction of the internal flow that causes the airflow from the exit (34) to adhere the pressure side of the airfoil thus producing a boundary layer airflow along the pressure side.

公开(公告)号：FR2798422B1

公开(公告)日：2002-07-26

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

公开(公告)号：AU684039B1

公开(公告)日：1997-12-04

申请号：AU4881490

申请日：1990-01-16

Applicant: UNITED TECHNOLOGIES CORP

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

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：TR23587A

公开(公告)日：1990-04-19

申请号：TR20390

申请日：1990-03-07

Applicant: UNITED TECHNOLOGIES CORP

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

IPC: F01D5/18 ,  F01D11/10 ,  F02C ,  F01P

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：DE60037926T2

公开(公告)日：2009-01-22

申请号：DE60037926

申请日：2000-08-04

Applicant: UNITED TECHNOLOGIES CORP

Inventor： KVASNAK WILLIAM A ,  THOLE KAREN A ,  SOECHTING FRIEDRICH O ,  ZESS GARY A

IPC: F01D9/02 ,  F01D9/04 ,  F01D5/14 ,  F15D1/12

公开(公告)号：DE19502998B4

公开(公告)日：2005-03-03

申请号：DE19502998

申请日：1995-01-31

Applicant: UNITED TECHNOLOGIES CORP

Inventor： SOECHTING FRIEDRICH O ,  AUXIER THOMAS A

IPC: F01D5/18

Abstract: The airfoil comprises of a leading edge (18) and a trailing edge (20) that is located downstream of a compressor airflow. The air is directed into internal chambers (55.56) within the airfoil and out through ports located along the pressure side of the airfoil between leading and trailing edges to form a cooling airflow. An additional film cooling hole (66) is located near the trailing edge of the airfoil. The film cooling hole admits an additional airflow into high and low pressure chambers (60,64) that are downstream of the initial internal airfoil flow. The two chambers are in communication via a passage (62). This creates a pressure drop in the downstream direction of the internal flow that causes the airflow from the exit (34) to adhere the pressure side of the airfoil thus producing a boundary layer airflow along the pressure side.

公开(公告)号：DE69821443T2

公开(公告)日：2004-12-16

申请号：DE69821443

申请日：1998-11-13

Applicant: UNITED TECHNOLOGIES CORP

Inventor： PRZIREMBEL HANS R ,  SOECHTING FRIEDRICH O

IPC: F01D5/18 ,  F01D9/02

Abstract: A hollow airfoil has a pressure side wall 12, a suction side wall 14, a cavity 16 formed between the pressure and suction side walls, a plurality of cooling ports 18 disposed within the pressure side wall 12, and a plurality of passages 42, each extending between the cavity 16 and one of the cooling ports 18. Each passage 42 has a first wall 54 adjacent the suction side wall 14, a pair of passage 58 side walls extending substantially toward the pressure side wall 12, and a second wall 56 adjacent the pressure side wall 12. Each passage further includes a pair of fillets 60,62 extending between the passage side walls 58 and the second wall 56. Alternatively, or in addition, each passage 42 includes a jog adjacent each cooling port 18 so as to extend parallel to the pressure side wall 12.

公开(公告)号：DE69821443D1

公开(公告)日：2004-03-11

申请号：DE69821443

申请日：1998-11-13

Applicant: UNITED TECHNOLOGIES CORP

Inventor： PRZIREMBEL HANS R ,  SOECHTING FRIEDRICH O

IPC: F01D5/18 ,  F01D9/02

Abstract: A hollow airfoil has a pressure side wall 12, a suction side wall 14, a cavity 16 formed between the pressure and suction side walls, a plurality of cooling ports 18 disposed within the pressure side wall 12, and a plurality of passages 42, each extending between the cavity 16 and one of the cooling ports 18. Each passage 42 has a first wall 54 adjacent the suction side wall 14, a pair of passage 58 side walls extending substantially toward the pressure side wall 12, and a second wall 56 adjacent the pressure side wall 12. Each passage further includes a pair of fillets 60,62 extending between the passage side walls 58 and the second wall 56. Alternatively, or in addition, each passage 42 includes a jog adjacent each cooling port 18 so as to extend parallel to the pressure side wall 12.

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.