초록 ▼

According to the invention, said precooling heat exchanger (18) comprises at least one (12A) of said linking arms (12) between the engine body (2) and the fan shroud (9), the said linking arm or arms (12A) acting as the exchanger, exhibiting a hollow structure traversed longitudinally by at least so

According to the invention, said precooling heat exchanger (18) comprises at least one (12A) of said linking arms (12) between the engine body (2) and the fan shroud (9), the said linking arm or arms (12A) acting as the exchanger, exhibiting a hollow structure traversed longitudinally by at least some of the hot air bled off at the outlet of the low pressure and/or high pressure stages of the compressors (3) of the engine.

대표청구항 ▼

[ I claim:] [1.] A device for bleeding off and cooling hot air in an engine of an aircraft, the aircraft having a body, said engine comprising:an engine body having a compressor, a combustion chamber and a turbine, the engine defining an upstream direction and a downstream direction;a fan, arranged

[ I claim:] [1.] A device for bleeding off and cooling hot air in an engine of an aircraft, the aircraft having a body, said engine comprising:an engine body having a compressor, a combustion chamber and a turbine, the engine defining an upstream direction and a downstream direction;a fan, arranged in the upstream direction from the engine body, for causing a flow of air in the downstream direction;a fairing assembly comprising an air intake, a fan shroud and outer and inner fairings;a plurality of linking arms for connecting the engine body with the fan shroud; andengine support means for connecting the engine to the body of the aircraft;said device comprising:hot air take-off means, in communication with the engine, for taking off hot air from the engine,a cold air take-off means, disposed downstream of the fan of the engine, for taking off cold air from the flow of air coming from the fan; anda precooling heat exchanger for causing a heat exchange between said hot air taken off by the hot air take-off means and said cold air taken off by the cold air take-off means, the precooling heat exchanger comprising at least one of the plurality of linking arms, said at least one of the plurality of linking arms having (i) a hollow structure traversed longitudinally in a first direction by at least a portion of the hot air and an internal partitioned portion in which the cold air flows in a second direction which is opposite to the first direction. [13.] A device for bleeding off and cooling hot air in an engine of an aircraft, the aircraft having a body, said engine comprising:an engine body having a compressor, a combustion chamber and a turbine, the engine defining an upstream direction and a downstream direction;a fan, arranged in the upstream direction from the engine body, for causing a flow of air in the downstream direction;a fairing assembly comprising an air intake, a fan shroud and outer and inner fairings;a plurality of linking arms for connecting the engine body with the fan shroud; andengine support means for connecting the engine to the body of the aircraft; said device comprising:hot air take-off means, in communication with the engine, for taking off hot air from the engine,a cold air take-off means, disposed downstream of the fan of the engine, for taking off cold air from the flow of air coming from the fan; anda precooling heat exchanger for causing a heat exchange between said hot air taken off by the hot air take-off means and said cold air taken off by the cold air take-off means, the precooling heat exchanger comprising a plurality of groups of linking arms within the plurality of linking arms, each of said plurality of groups of linking arms having a hollow structure traversed longitudinally by at least a portion of the hot air;wherein the hot air take-off means comprises:a first trunking for bleeding off the hot air from the engine;a first tapping leading from the first trunking to said plurality of groups of linking arms, said first tapping comprising (i) a first plurality of branches, each leading from the first trunking to a linking arm in the plurality of groups, and (ii) a second plurality of branches, each leading from a linking arm in the plurality of groups, joining together in a duct; anda second tapping leading from the first trunking, passing transversely through the engine and rejoining said duct so as to form a second trunking leading to the body of the aircraft.