公开(公告)号：DE60038086T2

公开(公告)日：2009-03-05

申请号：DE60038086

申请日：2000-11-02

Applicant: UNITED TECHNOLOGIES CORP

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

IPC: F01D5/18 ,  F01D9/02 ,  F23R3/00

公开(公告)号：DE60041025D1

公开(公告)日：2009-01-22

申请号：DE60041025

申请日：2000-10-05

Applicant: UNITED TECHNOLOGIES CORP

Inventor： KVASNAK WILLIAM S ,  LAFLEUR RONALD S ,  MOROSO JOE ,  SOECHTING FRIEDRICH O ,  JOE CHRISTOPHER R ,  HAYES DOUGLAS A

IPC: F01D5/18 ,  F01D9/02 ,  F01D25/12

Abstract: A cooling circuit 22 disposed between a first wall portion 36 and a second wall portion 38 of a wall 24 for use in a gas turbine engine, comprises one or more inlet apertures 40, and one or more exit apertures 44. The inlet aperture(s) 40 provides a cooling airflow path into the cooling circuit 22 and the exit aperture(s) 44 provides a cooling airflow path out of the cooling circuit 22. The cooling circuit includes a plurality of first pedestals 34 extending between the first wall portion 36 and the second wall portion 38. The first pedestals 34 arc arranged in one or more rows 48. Preferably the distance between the pedestals 34 in a row 48 is greater than the distance between the rows 48. Also, preferably the passage 57, 90 between the pedestals 34 define a pair of throats 62, 64 with a diffuser 60 in between. The exit apertures 44 are preferably defined between a plurality of second and third pedestals 66, 68 with mating geometries.

公开(公告)号：DE60038086D1

公开(公告)日：2008-04-03

申请号：DE60038086

申请日：2000-11-02

Applicant: UNITED TECHNOLOGIES CORP

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

IPC: F01D5/18 ,  F01D9/02 ,  F23R3/00

公开(公告)号：DE60025074D1

公开(公告)日：2006-02-02

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.