Aircraft engine apparatus with reduced inlet vortex
AssigneeMcDonnell Douglas Corporation
InventorsDavid M. Smith, John Dorris, III
Life of this patent
Estimating the term…
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.
Claims17
An aircraft engine apparatus having a reduced inlet vortex, the aircraft engine apparatus comprising:
- an aircraft engine having an engine nacelle extending lengthwise between an opposing inlet and exhaust nozzle;
- and
- a vortex disruption system comprising at least one outlet port opening through said inlet of said engine nacelle, wherein said vortex disruption system bleeds fluid from said aircraft engine and periodically discharges pulses of fluid through said at least one outlet port such that the periodic pulses of fluid disrupt the inlet vortex while the aircraft is on the ground.
A vortex disruption system for disrupting an inlet vortex generated by an aircraft engine having an engine nacelle, the vortex disruption system comprising:
- at least one engine bleed port for receiving fluid from the aircraft engine;
- at least one outlet port opening through an inlet of the engine nacelle of the aircraft engine;
- at least one passageway for establishing fluid communication between said bleed port and said at least one outlet port;
- and
- means for permitting intermittent fluid flow through said tube such that pulses of fluid are periodically discharged through said at least one outlet port such that the periodic pulses of fluid disrupt the inlet vortex.
A method of reducing an inlet vortex generated by an aircraft engine, comprising the steps of:
- drawing fluid through an engine nacelle of the aircraft engine having an opposed inlet and exhaust nozzle;
- bleeding off a portion of the fluid flowing through the aircraft engine during said drawing step;
- and
- periodically discharging pulses of fluid bled from the fluid flowing through the aircraft engine while the aircraft is on the ground, wherein said discharging step comprises periodically discharging pulses of fluid through at least one outlet port that opens through the inlet of the engine nacelle such that the periodic pulses of fluid disrupt the inlet vortex.
Dependencies are inferred from the claim text.