Gas turbine engine providing simulated boundary layer...

Details Gas turbine engine providing simulated boundary layer... Gas turbine engine providing simulated boundary layer...

2011-01-18

2011-01-18

Cuff, Michael (Department: 3741)

Power plants

Reaction motor

Interrelated reaction motors

C137S015100

Reexamination Certificate

active

07870721

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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