GAS TURBINE NACELLE COMPRISING A PASSIVE BOUNDARY LAYER BLEED SYSTEM
摘要
A nacelle for a gas turbine engine system includes a housing that has a pressure side and a suction side. A passage extends between the pressure side and the suction side for permitting airflow from the pressure side to the suction side. The passage includes a first curved section that has an inlet at the pressure side. A linear section is connected with the first curved section. A second curved section is connected with the linear section and has an outlet at the suction side. The outlet has a cross sectional area smaller than a cross sectional area of the linear section.
申请公布号
EP2077963(A2)
申请公布日期
2009.07.15
申请号
EP20060825796
申请日期
2006.10.12
申请人
UNITED TECHNOLOGIES CORPORATION
发明人
ZYSMAN, STEVEN H.;LORD, WESLEY K.;MILLER, ROBERT M.;ATASSI, OLIVER V.