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US Patent 7870721 Gas turbine engine providing simulated boundary layer thickness increase

Patent 7870721 was granted and assigned to United Technologies on January, 2011 by the United States Patent and Trademark Office.

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Patent abstract

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.

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