Device for bleeding off and cooling hot air in an aircraft engine
AssigneeAerospatiale Societe Nationale Industrielle
InventorAlain Porte
Life of this patent
Estimating the term…
Abstract
The present invention relates to a device for bleeding off and cooling hot air in an aircraft engine, including: at least one hot air take-off at the outlet of the low pressure and/or high pressure stages of the compressors of the engine, a cold air take-off downstream of the fan of the a engine, a precooling heat exchanger between said hot air and said cold air, and hot air and/or cold air flow rate regulating valves. According to the invention, said heat exchanger (18) is arranged at the forward part (13A) of the engine (1) support pylon (13), being traversed by said air stream (21) which leaves the fan (6) and is not directed toward the compressors (3).
Claims15
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 cold air in the downstream direction;
- a fairing assembly comprising an air intake, a fan shroud and outer and inner fairings;
- linking means for connecting the engine body and the fan shroud;
- and
- engine support means for connecting the engine to the body of the aircraft;
- said device comprising:
- a first flow line for bleeding off the hot air from the compressor;
- a perforated shroud arranged transversely in the flow of the cold air and traversed by said first flow line;
- and
- a second flow line, connected to said first flow line, for receiving the hot air which has passed through the first flow line and the perforated shroud and for conveying the hot air to the body of the aircraft.
Dependencies are inferred from the claim text.