Inner shroud for holding blade roots of e.g. stator blade of high-pressure compressor in aircraft gas turbine, has U-profile provided with flat middle portion, where value defining geometry of blade roots is smaller than reference value

摘要

The shroud (29) has a U-profile provided with a flat middle portion (30) that comprises lateral legs (31), where end regions (32) of the legs are arranged at a distance to each other and to the middle portion. The flat middle portion is designed as a snug-fit, where a value defining geometry of blade roots is smaller than a reference value. The shroud is designed as a metal sheet molded ring, where a cross-section of the shroud exhibits equal walled thickness. An inlet film (33) is arranged at the middle portion, and a carrier tape is fixed at the middle portion for bearing the inlet film. An independent claim is also included for a method for manufacturing an inner shroud.