公开(公告)号：US20220082256A1

公开(公告)日：2022-03-17

申请号：US17535027

申请日：2021-11-24

Applicant: Raytheon Technologies Corporation

Inventor： Steven D. Porter ,  Jon E. Sobanski

IPC: F23R3/00 ,  B21D25/00 ,  B21D31/00 ,  F01D11/00 ,  F02C3/04 ,  F23M5/04 ,  F23R3/60

Abstract: An aerodynamic component of a gas turbine engine is provided and is fittable to a shell having a shell shape. The aerodynamic component includes a body having a component shape initially deviating from the shell shape prior to an assembly operation in which the aerodynamic component is to be fit to the shell. Deviation of the component shape from the shell shape aids in an establishment of a final desired shape of the aerodynamic component following the assembly operation.