Bleed valve of a compressor, in particular a compressor of a bypass aero-engine
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United States of America Patent
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-
Jul 8, 2003
Grant Date -
Nov 22, 2001
app pub date -
Dec 8, 2000
filing date -
Dec 10, 1999
priority date (Note) -
In Force
status (Latency Note)
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Abstract
This invention relates to a bleed valve of a compressor, in particular a compressor of a bypass aero-engine, with a guiding device provided downstream of a valve body in the bleed duct, said guiding device directing the bleed airflow from a compressor duct to a bypass duct in such a manner that the direction of the flow of the bleed airflow is imparted with a component which is unidirectional with the airflow carried in the bypass duct. The present invention provides a dissipation screen in the bleed duct between the valve body and the guiding device to reduce the energy contained in the bleed airflow, thereby decreasing the loading of the bypass duct. Moreover, the present invention provides for an attenuation chamber downstream of the dissipation screen as viewed in the direction of the bleed airflow. In a preferential arrangement, the guiding device is a plate which is essentially parallel to the wall of the bypass duct and which contains a plurality of bores inclined in the direction of flow of the airflow carried in the bypass duct.
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