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Passive boundary layer bleed system for nacelle inlet airflow control
Passive boundary layer bleed system for nacelle inlet airflow control
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机译:机舱入口气流控制的被动边界层放气系统
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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.
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