United Technologies Corporation

Ephraim C Davis

Garrett Kernozicky

Thomas P Cap

Christopher J Bischof

Bryan G Parrette

Larry D Cronin

Paul Balko

A method for use in repairing gas turbine engine components includes applying a stress to a first gas turbine engine component to cause surface cracking on the first gas turbine engine component and establishing a location of an elevated stress region of a second gas turbine engine component based upon the location of the surface cracking on the first gas turbine engine component.

Method for establishing a location of an elevated stress region

A tool for correcting the twist angle of a turbine blade includes an adaptor configured to engage a tip of the blade, a socket drive configured to engage the adaptor, a first handle connected to a first side of the socket drive, a second handle connected to a second side of the socket drive, and a torque gauge configured to measure a load applied to the blade.

Turbine blade twist angle correction tooling

A method of correcting a twist angle of a gas turbine engine blade includes measuring an existing twist angle of the blade, applying a first angular load to a first end of the blade; and measuring a repaired twist angle of the blade. The first angular load applied to the first end of the blade is based on an empirical correlation between a plurality of angular loads necessary to produce a plurality of twist angle correction values.

Methods for correcting twist angle in a gas turbine engine blade

A method of developing a repair process for a gas turbine engine component deformed during engine operation includes determining peak stress locations in a model of the component, applying loads to sample components based on the model to produce geometrical correction values in the samples, generating data from the samples including the loads applied and the geometrical correction values produced, destructively analyzing the samples at the peak stress locations for structural imperfections, and correlating the loads applied to the geometrical correction values produced to determine allowable loads necessary to produce target geometrical correction values in a used component substantially free of structural imperfections.

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No Richland Hills, TX, United States of America

Ephraim C Davis