EXHAUST EDUCTOR COOLING SYSTEM

A method and apparatus for cooling the heat generated by a gas turbine engin e mounted in a compartment is provided. The apparatus comprises a novel eductor (60) that incorporates a mixer nozzl e (70) to entrain sufficient air flow through the com- partment to provide all the necessary cooling. The...

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Bibliographische Detailangaben
Hauptverfasser:	KENZLER, KURT T, DAVIS, THOMAS W, SHEORAN, YOGENDRA Y, SCHMITTENBERG, MARC, LYON, CRAIG A, ROYALTY, CHARLES M
Format:	Patent
Sprache:	eng ; fre
Schlagworte:	AIRCRAFT ARRANGEMENTS OR MOUNTING OF POWER PLANTS OR PROPULSIONTRANSMISSIONS IN AIRCRAFT AVIATION BLASTING COMBUSTION ENGINES COSMONAUTICS EQUIPMENT FOR FITTING IN OR TO AIRCRAFT FLYING SUITS HEATING HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS JET-PROPULSION PLANTS LIGHTING MECHANICAL ENGINEERING PARACHUTES PERFORMING OPERATIONS TRANSPORTING WEAPONS
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Beschreibung
Zusammenfassung:	A method and apparatus for cooling the heat generated by a gas turbine engin e mounted in a compartment is provided. The apparatus comprises a novel eductor (60) that incorporates a mixer nozzl e (70) to entrain sufficient air flow through the com- partment to provide all the necessary cooling. The engine's oil cooler (62) is mounted to the eductor so that the entrained air flow passes through it and cools the engine's oil. The novel eductor also has mea ns for receiving a flow of high velocity air (68) from the engine and injecting this air downstream of the mixer nozzle to enhance the entraining of the cooling flow.