公开(公告)号：JP2001164903A

公开(公告)日：2001-06-19

申请号：JP2000346058

申请日：2000-11-14

Applicant: UNITED TECHNOLOGIES CORP

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

IPC: F01D5/18 ,  F01D9/02 ,  F23R3/00

Abstract: PROBLEM TO BE SOLVED: To provide a device and a method of cooling a wall 12 used in a gas turbine engine. SOLUTION: A microcircuit 10 to cool the wall 12 of a gas turbine engine contains a cooling air passage 11 having a plurality of segments 36 interconnected in series by one or more chambers 38, an inlet hole 40, and an outlet hole 42. The inlet hole 40 is connected to a cooling air passage 11 on one side of the wall 12 and the outlet hole 42 is connected to the cooling air passage on the other side of the wall 12. Cooling air on the inlet hole 40 side of the wall 12 flows in the cooling air passage 11 through the inlet hole 40 and flows out through the outlet hole 42.

公开(公告)号：JP2001065304A

公开(公告)日：2001-03-13

申请号：JP2000232601

申请日：2000-08-01

Applicant: UNITED TECHNOLOGIES CORP

Inventor： WILLIAM A VASUNAKKU ,  SOECHTING FRIEDRICH O ,  KAREN A TOLL ,  GARRY A ZESU

IPC: F01D9/02 ,  F01D5/14 ,  F01D9/04

Abstract: PROBLEM TO BE SOLVED: To control the movement of the core gas flow toward the radial boundary at both of inner and outer sides of a core gas passage by increasing a speed of the core gas flow for preventing the generation of the secondary flow of the core gas flow toward a wall in an area where a front edge of a blade is adjacent to the wall. SOLUTION: A turbine of a gas turbine engine has a plurality of stationary blade segments 26 on a plurality of stationary blade stages. Each stationary blade segment 26 has at least one blade 28 extending between platforms 30, 32 as the inner and outer walls. Here, a means 38 for changing the direction of the core gas flow is used for separating the core gas flow of high temperature from a region where a front edge 50 of the blade 28 is adjacent to the walls 30, 32. Whereby a speed of the core gas flow is increased, the pressure gradient is reduced, and the secondary core gas flow in the directions of walls 30, 32 can be reduced. A fillet 48 extending in the longitudinal direction or the height direction from the front edge 50 of the blade 28 forms the means 38.