Patent ID: 8128349
Filing Date: 2012-03-06
Classification: F01D,F05D

Abstract:
1. A blade outer air seal assembly for a gas turbine engine comprising: an annular arrangement of outer air seal segments defining an inner diameter surface; intersegment gaps located between the outer air seal segments, each of the gaps being located between a corresponding adjacent pair of the segments; and recesses spaced about the inner diameter surface, each of the recesses communicating with a corresponding one of the gaps; wherein a first of the gaps is defined by a blade departure end of a first of the segments and a blade arrival end of a second of the segments; wherein a radially innermost portion of the blade arrival end is located radially outboard of a radially innermost portion of the blade departure end; wherein the blade arrival end exhibits an inside radius curvature; and wherein the blade departure end exhibits an outside radius curvature.