Infrared suppression system for a gas turbine engine
AssigneeGeneral Electric Company
InventorsJames Leroy Nye, Samuel Rothrock Barr, Thomas Chew, William Steyer
Life of this patent
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Abstract
An infrared suppression system is provided for an aircraft gas turbine engine for reducing the level of emitted infrared radiation from the engine exhaust. The hot exhaust stream emitted from the engine is mixed with the cooling airflows received from a plurality of sources in order to more effectively reduce the level of emitted infrared radiation. In addition, the infrared suppression system prohibits a direct line of sight back into the core engine.
Claims9
An infrared suppression system for an aircraft gas turbine engine of the type having an integral inlet particle separator including a particle collection chamber and blower for evacuating said chamber, comprises:
- means for directing the airflow from the integral inlet particle separator blower to the hot engine exhaust stream for mixing therewith,
- means for capturing a portion of the ambient ram airflow around the engine and directing it to the hot engine exhaust stream for mixing therewith, and
- wherein the engine is housed within an aircraft engine nacelle so as to define an annular bay area therebetween and cooling airflow is admitted to the bay area to cool the aircraft engine nacelle after which said bay cooling airflow is directed to the hot engine exhaust stream for mixing therewith.
Dependencies are inferred from the claim text.