Aircraft engine apparatus with reduced inlet vortex

Details Aircraft engine apparatus with reduced inlet vortex Aircraft engine apparatus with reduced inlet vortex

1998-07-24

2000-10-10

Poon, Peter M.

Aeronautics and astronautics

Aircraft power plants

60 39092, B64B 124, F02G 300

Patent

active

061293091

ABSTRACT:
An aircraft engine apparatus with a reduced inlet vortex is provided which utilizes a vortex disruption system that periodically discharges pulses of engine bleed fluid through at least one outlet port opening through the inlet of the engine nacelle to disrupt the engine inlet vortex. The vortex disruption system thereby prevents ingestion of foreign matter into the engine inlet without sacrificing engine power, efficiency, or aircraft cruise performance.

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