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.