|국가/구분||United States(US) Patent 등록|
|발명자 / 주소|
|출원인 / 주소|
|대리인 / 주소||
|인용정보||피인용 횟수 : 18 인용 특허 : 46|
A nacelle assembly for a gas turbine engine includes a fan cowl disposed about an axis, a core cowl within the fan cowl and a bleed passage having an inlet that receives a bleed airflow and an outlet that discharges the bleed airflow in an upstream direction from the outlet. The bleed airflow is selectively introduced near a boundary layer of an inlet lip section of the fan cowl.
What is claimed is: 1. A nacelle assembly, comprising:a fan cowl disposed about an axis;a core cowl at least partially within said fan cowl;a low pressure compressor stage and a high pressure compressor stage disposed within said core cowl; anda bleed passage at least partially disposed within said fan cowl and having an inlet that receives a bleed airflow and an outlet that discharges said bleed airflow in an upstream direction from said outlet, wherein said bleed airflow is selectively communicated from a location separate from the high pressure compre...