TURBINE BLADE SYSTEM FOR GAS TURBINE ENGINE

摘要

PROBLEM TO BE SOLVED: To provide a structure for cooling a trailing edge region of a turbine blade. SOLUTION: This turbine blade system for the gas turbine engine is provided with the turbine blade 100 provided with the trailing edge region 102 extending in the longitudinal direction and the lateral direction from a face on a positive pressure side to a trailing edge. The trailing edge region 102 includes a plurality of riblets 104 extending in the longitudinal direction from the face on the positive pressure side to the trailing edge. The trailing edge region 102 defines a plurality of ejection slots 106 each laterally disposed between two of the riblets 104. The plurality of riblets 104 defines an upper side face 108 having at least a part in the longitudinal direction being curved relative to the pressure side face 110. Consequently, the upper side face 108 is substantially protected from high heat load propagated from the pressure side face 110 to promote flow of cooling air flowing out from the ejection slots 106 on the upper side face. COPYRIGHT: (C)2007,JPO&INPIT