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Turbine cooling air sealing with associated turbine engine and method for reengineering a gas turbine engine
Turbine cooling air sealing with associated turbine engine and method for reengineering a gas turbine engine
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机译:具有相关涡轮发动机的涡轮冷却空气密封件以及用于对燃气涡轮发动机进行再工程的方法
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摘要
A turbine engine section (18) has a stationary vane stage (100) and a rotating blade stage (54, 74). The blade stage (54, 74) is spaced from the vane stage (100) to form an annular chamber therebetween. A manifold (126) delivers a pressurized fluid to the chamber. An outer diameter (OD) sealing means restricts leakage of the pressurized fluid from the chamber. An inner diameter (ID) sealing means restricts leakage of the pressurized fluid from the chamber. A flow guide (146; 358) extends radially between the inner diameter sealing means and the manifold (126). The flow guide (146; 358) bisects the chamber to form a stationary chamber portion and a rotating chamber portion, the rotating chamber portion at least partially along a disk of the first blade stage.
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