Patent ID: 9080449
Filing Date: 2015-07-14
Classification: F01D

Abstract:
1. A seal assembly for a gas turbine engine, comprising: an annular body that includes a first flange and a second flange spaced from said first flange, said first flange and said second flange both including an upstream face and a downstream face; a flow-through tube extending through said upstream face and said downstream face of each of said first flange and said second flange of said annular body and including an upstream orifice, a downstream orifice and a tube body that extends between said upstream orifice and said downstream orifice, said tube body including an axial portion and a tangential portion, wherein said axial portion and said tangential portion together communicate a conditioning airflow in an upstream direction from said downstream orifice toward said upstream orifice of said flow-through tube.