Gas turbine engine transition liner assembly and repair

Details Gas turbine engine transition liner assembly and repair Gas turbine engine transition liner assembly and repair

2007-03-06

2007-03-06

Rodriguez, William H. (Department: 3746)

Metal working

Method of mechanical manufacture

Impeller making

C029S402030, C029S402120, C060S752000

Reexamination Certificate

active

11068221

ABSTRACT:
A method of repairing a damaged combustion gas transition liner for a gas turbine engine and an improved damage-resistant transition liner that mounts adjacent to the edge of one of the engine's combustion chambers. In a particular embodiment, the gas turbine engine is a reverse flow type and the transition liner has a scalloped, circular shape with a damaged outer edge portion. The outer edge portion of the liner is removed and replaced with a new ring-shaped edge portion. The new ring-shaped edge portion has a layer of damage-resistant material that is more robust than the original liner material. The layer of damage-resistant material is located such that it will be adjacent to the edge of the combustion chamber when the gas turbine engine is reassembled. A new transition liner assembly with the damage-resistant edge also is provided.

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