Patent ID: 6588214
Filing Date: 2003-07-08
Classification: F01D,F05B,F05D

Abstract:
A wear reduction device for a gas turbine engine combustor transition piece end frame havinga plurality of radially outward extending U-shaped slots about the periphery of said end frame, each of said slots including a pair of substantially parallel sidewalls; and, at least four generally L-shaped wear strip inserts, each of said inserts includes a first leg portion and a second leg portion, said first leg portion is integral with said second leg portion and substantially perpendicular thereto, wherein said first leg portion of each of said inserts is received within one of said U-shaped slots proximate one of said sidewalls of said slot such that said first leg portion is parallel to said sidewall and said second leg portion is fixed to said end frame; wherein said first leg portion extends away from said second leg portion a first distance, the second leg portion extends away from said first leg portion a second distance, and the first distance is greater than the second distance.