| 摘要 |
<p>TURBINE COOLING Apparatus for cooling the case and the nozzle guide vanes in the turbine section of a gas turbine engine is disclosed. A plurality of guide vanes is cantilevered from the case and extends radially inward across the path of working medium gases flowing through the turbine. A ring, which is deformable to provide radial sealing in operative response to pressure forces exerted by medium gases on the airfoil section of each guide vane, is disposed between the vanes and the case forming an annular chamber which is adapted to receive cooling air and from which the cooling air is flowable to the vanes during operation of the engine.</p> |
