|국가/구분||United States(US) Patent 등록|
|미국특허분류(USC)||060/262; 060/264; 239/265.19; 239/265.17; 181/220|
|발명자 / 주소|
|출원인 / 주소|
|대리인 / 주소||
|인용정보||피인용 횟수 : 27 인용 특허 : 13|
A gas turbine engine of a fan bypass type includes an exhaust shroud having a perforated tubular wall extending between a forward end and an aft end. The exhaust shroud is adapted to be affixed to a gas turbine engine exhaust for discharging engine exhaust gases without substantial blockage thereto. The perforations formed in the shroud wall communicate the regions at both sides of the shroud wall to pass fluid flow across the perforated shroud wall so that the mixing of the engine exhaust gases with a surrounding fluid flow is enhanced. The mixing of th...
1. 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...