| 摘要 |
<p><P>PROBLEM TO BE SOLVED: To provide a system for easily strengthening local cooling of a gas turbine engine. <P>SOLUTION: A turbine nozzle segment includes an airfoil vane part extending between an inner band. an aft flange and an outer band including a radial inner surface. A turbine shroud segment is coupled downstream from the turbine nozzle segment, and the turbine shroud segment includes a leading edge and the radial inner surface. A cooling fluid supply source is fluidly communicated and coupled with the turbine nozzle segment, and include facilitating preferential cooling of a turbine shroud, by designating a flow passage for a cooling fluid via a first group of a cooling opening having the large total cross-sectional area and a second group of a cooling opening having the small total cross-sectional area, by guiding the cooling fluid of designating the flow passage to a turbine nozzle outer band aft flange at an inclined delivery angle toward the leading edge of the turbine shroud segment. <P>COPYRIGHT: (C)2008,JPO&INPIT</p> |
