Patent ID: 6640537
Filing Date: 2003-11-04
Classification: F02K,F05D,Y02T

Abstract:
A gas turbine engine comprising:a turbine portion; a combustor portion; a compressor portion driven by the turbine portion; and a noise reducing apparatus mounted to the engine at an exit end of the engine, the apparatus including an annular wall extending from a first open end to a second open end, the wall communicating directly with the exit end to thereby conduct engine exhaust gases therethrough, the wall having a plurality of perforations therethrough in a staggered offset pattern, the plurality of perforations disposed substantially over the entire surface of the annular wall, the annular wall being open to the atmosphere and free of obstruction radially outwardly thereof, the second open end of the annular wall having a trailing edge deviated from a straight line in a circumferential direction of the annular wall when being viewed in a longitudinal cross-section of the annular wall.