|국가/구분||United States(US) Patent 등록|
|미국특허분류(USC)||060/226.1; 060/226.3; 060/262; 244/053.0B; 137/015.1|
|발명자 / 주소|
|출원인 / 주소|
|대리인 / 주소||
|인용정보||피인용 횟수 : 18 인용 특허 : 10|
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...
What is claimed is: 1. A gas turbine engine comprising: a fan nacelle that comprises an inner fan nacelle surface which defines an inlet duct; and a nacelle contoured surface disposed in said fan nacelle for selectively reducing an inlet area of said inlet duct to increase acoustic attenuation associated therewith, said nacelle contoured surface segmented around the circumference of said fan nacelle to selectively permit asymmetrical deployment thereof and selectively reduce the inlet area of the inlet duct asymmetrically. 2. The gas turbine engine o...