发明申请
US20130177384A1 TURBINE NOZZLE COMPARTMENTALIZED COOLING SYSTEM 有权
涡轮喷嘴均衡冷却系统

TURBINE NOZZLE COMPARTMENTALIZED COOLING SYSTEM
摘要:
The present application provides a compartmentalized cooling system for providing a cooling flow in a turbine with a flow of combustion gases therein. The compartmentalized cooling system may include a turbine nozzle and a cooling baffle. The turbine nozzle may include an airfoil insert and a nozzle outer sidewall. The cooling baffle may include a high pressure cooling passage in communication with the airfoil insert in a first circuit and an impingement plate positioned about the nozzle outer sidewall in a second circuit.
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