Rolls-Royce Corporation

John R Ballard

Michael J Buller

George H Bennett

Leslie A Lee

Peter H Timmis

A gas turbine engine infra-red radiation suppressor comprising an exhaust nozzle which is surrounded by a duct having a plurality of diffuser vanes at its downstream end. The exhaust nozzle and duct constitute an ejector which is powered by the exhaust efflux from the exhaust nozzle and draws ambient air into the duct through a gap between the exhaust nozzle and the duct. The air serves to cool the exhaust efflux and thereby reduce its infra-red radiation emission, and the diffuser vanes prevent direct line of sight of the hot exhaust nozzle.

Gas turbine engine infra-red radiation suppressor

An air intake for a helicopter mounted gas turbine engine comprises two intake portions which comprises vortex separator panels. One panel is generally forward facing while the other is generally sideways facing. A panel is pivotally mounted between the separator panels so as to pivot between a first position in which it obturates the generally sideways facing panel and a second position in which it obturates neither of the separator panels. The arrangement is such that when the helicopter is in fast forward flight, the pressure of the ram air flow through the generally forward facing inlet panel causes the pivoted panel to pivot to the position in which it obturates the generally sideways facing inlet panel.

Air intakes of aircraft mounted gas turbine engines

A gas turbine engine and its associated air intake system in which the air intake system comprises a generally horizontally extending duct through which an airflow is induced by an ejector pump powered by the engine. A portion of the air passing through the duct is directed through a second duct to the air inlet of the engine. The second duct is connected to the first duct in such a manner that the air directed to the engine air inlet is derived from a vertically upper region of the first duct. The arrangement is intended to reduce the amount of airborne particulate material ingested by the gas turbine engine.

Gas turbine engine and its associated air intake system

A gas turbine engine cowling suitable for a helicopter contains a gas turbine engine having a vortex tube separator panel for the purpose of separating water droplets and particulate material from engine inlet air. The vortex tube separator panel is mounted in a duct extending the length of the cowling so that air passing through the duct supplies air for passing through the panel to the engine inlet as well as maintaining a flow of air transverse to the panel. The air flow transverse to the panel ensures that blockage of the panel by ice is substantially reduced or eliminated. Under forward flight conditions, ram air passes through the duct but during hovering, the air flow through the duct is induced by an ejector powered by the exhaust efflux from the engine. The portion of the air flow through the duct which does not enter the gas turbine engine is utilized in the cooling of the engine exhaust efflux in order to reduce the amount of infra-red radiation emitted thereby.

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Chesham, United Kingdom

John R Ballard