Patent ID: 8206092
Filing Date: 2012-06-26
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, each of the segments having ends, the segments being positioned in an end-to-end orientation such that each adjacent pair of the segments forms an intersegment gap therebetween, each intersegment gap being defined, at least partially, by a first recess and a first protrusion, the first protrusion being sized and shaped to be received by the first recess, one of the first recess and the first protrusion being located on an end of a first segment of an adjacent pair of the segments, another of the first recess and the first protrusion being located on an end of a second segment of the adjacent pair of the segments, wherein the first recess extends along an entire width of the end on which the first recess is located, wherein the first protrusion extends along an entire width of the end on which the first protrusion is located.