|국가/구분||United States(US) Patent 등록|
|미국특허분류(USC)||137/015.1; 244/053B; 060/226.1; 181/213|
|발명자 / 주소|
|출원인 / 주소|
|대리인 / 주소||
|인용정보||피인용 횟수 : 6 인용 특허 : 17|
A gas turbine engine comprising a fan section, a compressor, a combustor and a turbine, includes a nacelle having an inner nacelle surface defining an inlet duct designed to reduce an inlet duct area of the inlet duct to increase acoustic attenuation. The gas turbine engine also includes a spinner, disposed forward of the fan section, that includes features to increase acoustic attenuation. In one embodiment of the present invention, the nacelle includes a nacelle contoured surface protruding radially inward from the inner nacelle surface to reduce the i...
1. A gas turbine engine comprising: a nacelle enclosing a fan section, a compressor, a combustor and a turbine, said nacelle including an inner nacelle surface defining an inlet duct having a flow area; andan actuator disposed in said inner nacelle surface for selectively reducing said flow area to increase the Mach number of air into said gas turbine engine to enhance acoustic attenuation associated with said inlet duct, wherein said actuator comprises an inflatable bladder disposed in said nacelle and having an inflated state wherein said inflatable bl...