EJECTOR-TYPE OIL COOLING SYSTEM FOR AUXILIARY AIRCRAFT ENGINE Russian patent published in 1999 - IPC

Abstract RU 2131380 C1

FIELD: aviation. SUBSTANCE: system includes oil cooler located in flow of air created by means of ejector mounted near exhaust nozzle of engine. Oil cooler is located in engine bay in pointed tail section; air intake is mounted in hatch for maintenance of engine bay which is flush with outer skin. Air intake has rectangular form and complies with configuration of aircraft in intake zone. Diffuser is mounted behind air intake hole of air intake. EFFECT: enhanced efficiency of engine cooling. 3 cl, 3 dwg

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RU 2 131 380 C1

Authors

Andreas Vinter

Fol'Ker Khibel'

Andreas Korus

Dates

1999-06-10—Published

1997-05-14—Filed