公开(公告)号：JP2000186504A

公开(公告)日：2000-07-04

申请号：JP36051599

申请日：1999-12-20

Applicant: UNITED TECHNOLOGIES CORP

Inventor： TABBITA MARTIN G ,  DOWNS JAMES P ,  SOECHTING FRIEDRICH O ,  THOMAS A OUKIYAA ,  STEINBAUER JR FREDERICK

IPC: F02C7/00 ,  F01D5/18

Abstract: PROBLEM TO BE SOLVED: To form a uniform and stable cooling air film in the downstream of the front edge on both sides of an air foil by expanding the space between adjacent openings to reduce a high stress area, eliminating uncooled areas in the individual cooling points and between them, and eliminating uncooled areas in the middle of the cooling opening and on its downstream. SOLUTION: A tubine blade 10 of a gas turbine engine has a root part 12, a platform 14, an air foil 16 and a blade tip 18. The air foil 16 has one, two or more inner cavities surrounded with an outer wall 22, and at least one of them is located in the vicinity of the front edge 24 of the air foil 16 and plural cooling openings 26. The cooling openings 26 are arranged along the front edge 24 to provide a passage for allowing cooling air to pass through the outer wall 22. Plural first and second openings are provided and respectively directed toward the suction side part 28 and the pressure side part 30. The flow of cooling air crosses the front edge 24 to perform suitable cooling.