Cooling device for a turboshaft engine on an aircraft

Details Cooling device for a turboshaft engine on an aircraft Cooling device for a turboshaft engine on an aircraft

1996-12-12

1998-09-15

Mojica, Virna Lissi

Aeronautics and astronautics

Aircraft power plants

Radiator arrangement

244117A, 244209, B64D 3310, B64C 2106

Patent

active

058067930

ABSTRACT:
A cooling device for an aircraft turboshaft engine includes a boundary layer suction device formed by a perforated external wall portion of the aircraft, a collector on the inside of the wall portion for receiving the air flowing in through the perforations, and a discharge device discharging the air from the collector. The cooling device is completed by a heat exchanger which is disposed in the path of the air flow through the collector, a pump for pumping fluid to be cooled through the heat exchanger from a circuit of the engine, and a regulator regulating the fluid flow through the exchanger to control the temperature of the fluid. The fluid which is cooled may be from the lubrication circuit, the fuel circuit, or an air circuit of the engine, and the boundary layer suction device is preferably disposed in the pod of the engine.

REFERENCES:
patent: 3510095 (1970-05-01), Chuan
patent: 4203566 (1980-05-01), Lord
patent: 4504030 (1985-03-01), Kniat et al.
patent: 4778130 (1988-10-01), Kim
patent: 5297765 (1994-03-01), Hughes et al.
patent: 5618363 (1997-04-01), Mullender et al.

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