TURBINE VANE HAVING DEDICATED INNER PLATFORM COOLING
摘要
A turbine vane for a gas turbine engine core adaptable to be operated in a variety of thrust regimes is disclosed. Various construction details are developed which provide means to provide cooling of an inner platform of the turbine vane. In one particular embodiment, a turbine vane includes a hollow core permitting cooling fluid to pass through the vane and an inner platform having a pocket disposed therein, the pocket being in fluid communication with the core. Heat is exchanged between the platform and the cooling fluid within the pocket. Cooling holes extend between the pocket and a flow surface of a platform to provide cooling of the flow surface.
申请公布号
WO9417285(A1)
申请公布日期
1994.08.04
申请号
WO1994US00764
申请日期
1994.01.19
申请人
UNITED TECHNOLOGIES CORPORATION
发明人
MAGOWAN, JOHN, W.;PAWLACZYK, RICHARD, J.;PIGHETTI, ANNETTE, M.;SCHWARZ, RICHARD, A.