| 摘要 |
<P>PROBLEM TO BE SOLVED: To provide a vane cluster for conducting film cooling of a vane platform in a gas turbine engine component. <P>SOLUTION: Each vane cluster 60 for forming a vane ring of the gas turbine engine component has a first airfoil 62, a second airfoil 64, a platform segment 68 and a shroud segment 72. The cluster 60 has a cooling passage and part of cooling air flowing in from inlet ports 110, 112 flows to the platform segment 68 via the airfoils and cools the platform. The cooling air flows out from an outlet hole 120. Owing to the cluster of this invention, the platform is efficiently cooled and inconvenient influence of air flowing into the platform is decreased. <P>COPYRIGHT: (C)2008,JPO&INPIT |
