公开(公告)号：US11428166B2

公开(公告)日：2022-08-30

申请号：US17096046

申请日：2020-11-12

申请人： Solar Turbines Incorporated

发明人： Scott L. Stafford ,  Juan Yin ,  Steven D. Gray

IPC分类号： F02C7/12 ,  F02C6/00 ,  F02C7/04

摘要： Gas turbine engines generally comprise a first-stage nozzle guide vane. Temperatures in a trailing-edge area of the suction-side wall of such vanes can exceed material and coating limits. While an insert can be used to form passages for cooling air to flow along the inner surfaces of the vane walls, design constraints prevent the insert from extending beyond a certain point into the trailing edge of the vane. Accordingly, a fin is disclosed for insertion downstream of the insert. By eliminating sudden expansion beyond the downstream end of the insert and maintaining the speed of the cooling air across the trailing-edge area of the suction-side wall, the fin improves the cooling coefficient for the trailing-edge area, so as to prevent or reduce excessive temperatures in the trailing-edge area.

公开(公告)号：US20220145799A1

公开(公告)日：2022-05-12

申请号：US17096046

申请日：2020-11-12

申请人： Solar Turbines Incorporated

发明人： Scott L. Stafford ,  Juan Yin ,  Steven D. Gray

IPC分类号： F02C7/12 ,  F02C6/00 ,  F02C7/04

摘要： Gas turbine engines generally comprise a first-stage nozzle guide vane. Temperatures in a trailing-edge area of the suction-side wall of such vanes can exceed material and coating limits. While an insert can be used to form passages for cooling air to flow along the inner surfaces of the vane walls, design constraints prevent the insert from extending beyond a certain point into the trailing edge of the vane. Accordingly, a fin is disclosed for insertion downstream of the insert. By eliminating sudden expansion beyond the downstream end of the insert and maintaining the speed of the cooling air across the trailing-edge area of the suction-side wall, the fin improves the cooling coefficient for the trailing-edge area, so as to prevent or reduce excessive temperatures in the trailing-edge area.