Patent ID: 6925810
Filing Date: 2005-08-09
Classification: F01D,Y02T,Y10T

Abstract:
1. A repaired gas turbine engine comprising: a combustion chamber having an annular edge portion; a transition liner body made of a first material and having a first edge portion, a second edge portion and a curved wall therebetween, the first edge portion shaped to fit adjacent to the annular edge portion of the combustion chamber and having a cut edge portion thereoh, and the second edge portion shaped to fit adjacent to the opening of the turbine section of the engine, such that the curved wall of the transition liner body guides the flow of combustion gasses from the combustion chamber to the turbine section of the engine; a replacement ring section coupled to the cut edge portion, the replacement ring section comprising the first material and having an inner surface; and a layer of a second, damage-resistant material deposited on the replacement ring inner surface and on the annular edge portion of the combustion chamber, the second material being resistant to wear damage caused by contact between the transition liner first edge portion and the annular edge portion of the combustion chamber.