Verfahren zu formung von gasturbinentriebwerkskomponenten

AT1909544TInactive Publication Date: 2026-05-15RTX CORP
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Patent Information

Application Number
AT2020191544T
Authority / Receiving Office
AT · AT
Patent Type
Patents
Current Assignee / Owner
Priority Date
2019-08-29
Filing Date
2020-08-18
Publication Date
2026-05-15
Estimated Expiration
Not applicable · inactive patent

AI Technical Summary

Technical Problem

Current methods for forming gas turbine engine components, such as hollow fan blades, face challenges in achieving precise deformation and temperature control to maintain structural integrity and aerodynamic performance, particularly in establishing the correct stagger angle and minimizing residual stresses.

Method used

A method involving attaching a cover skin to an airfoil body, heating it between dies, and deforming it while maintaining precise temperature control, followed by controlled cooling to establish a predefined temperature gradient, which allows for the formation of components with minimal change in stagger angle and reduced residual stresses.

Benefits of technology

This method enables the production of gas turbine engine components with improved structural integrity and aerodynamic performance by maintaining the desired stagger angle and minimizing residual stresses, enhancing fatigue capability and overall engine efficiency.

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Abstract

A method of forming a gas turbine engine component (260) according to an example of the present disclosure includes, among other things, attaching a cover skin (270) to an airfoil body (268), the airfoil body (268) and the cover skin (270) cooperating to establish pressure and suction sides (PS, SS) of an airfoil (261), positioning the airfoil (261) between first and second dies (287-1, 287-2) of a deforming station (284-2), heating the airfoil body (268) to a first predefined temperature threshold between the first and second dies (287-1, 287-2), and moving the first die (287-1) relative to the second die (287-2) to hold the airfoil (261) between the first and second dies (287-1, 287-2) subsequent to the heating step, and then deforming the airfoil (261) between the first and second dies (287-1, 287-2).
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