Replacement of part of engine case with dissimilar material
AssigneeUnited Technologies Corporation
InventorsGanesh Anantharaman, David J. Bartholic
Life of this patent
Estimating the term…
Abstract
A method of repairing a case for a gas turbine engine includes removing a first portion of the case from a second portion of the case and metallurgically joining a replacement material to the second portion of the case to form a repaired case. The first portion of the case includes a connection flange having a plurality of bolt holes formed therein. The replacement material has a different coefficient of thermal expansion than a parent material of the second portion of the case.
Claims16
A method of repairing a case for a gas turbine engine, the method comprising:
- removing the case from the gas turbine engine;
- removing a first portion of the case from a second portion of the case, wherein the first portion comprises a connection flange having a plurality of bolt holes formed therein;
- and
- metallurgically joining a replacement material to the second portion of the case to form a repaired case, wherein the replacement material has a different coefficient of thermal expansion than a parent material of the second portion;
- reinstalling the repaired case in the gas turbine engine, wherein the step of reinstalling the repaired case in the gas turbine engine comprises fastening the connection flange to an adjacent structure, and wherein the adjacent structure is made essentially of the replacement material of the case.
An assembly comprising:
- a first gas turbine engine component comprising a first metallic material;
- and
- a gas turbine engine case positioned adjacent to the first gas turbine engine component, wherein the gas turbine engine case comprises:
- a first portion comprising a parent metallic material;
- and
- a second portion comprising a replacement metallic material metallurgically joined to the first portion, wherein the replacement metallic material is different from the parent metallic material, wherein the replacement metallic material has the same material specifications as the first metallic material, and wherein the second portion of the gas turbine engine case includes a flange bolted to the first gas turbine engine component such that contact between the first gas turbine engine component and the gas turbine engine case occurs between materials with the same coefficient of thermal expansion.
A repaired gas turbine assembly comprising:
- a first gas turbine engine case component comprising a superalloy;
- and
- a second gas turbine engine case component positioned adjacent to the first gas turbine engine case component, wherein the second gas turbine engine case component comprises:
- a first portion comprising a parent material made of a stainless steel alloy;
- and
- a second portion comprising a flange fastened to the first gas turbine engine case component and metallurgically joined to the first portion of the second gas turbine engine case component, wherein the second portion comprises a repair material made of the same superalloy that comprises the first gas turbine engine case component, and wherein the stainless steel alloy and the superalloy have different coefficients of thermal expansion.
Dependencies are inferred from the claim text.