AIR DISCHARGE SYSTEM FOR AN AERONAUTICAL TURBINE ENGINE COMPRESSOR

The invention relates to an air discharge system for an aviation turbomachine compressor, the discharge system including at least one discharge valve (10) each valve comprising a valve body suitable for moving between an open position and a closed position of the discharge valve, a camshaft (22) com...

Ausführliche Beschreibung

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Bibliographische Detailangaben
Hauptverfasser: COLOTTE BAPTISTE, GAULLY BRUNO
Format: Patent
Sprache:eng
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Beschreibung
Zusammenfassung:The invention relates to an air discharge system for an aviation turbomachine compressor, the discharge system including at least one discharge valve (10) each valve comprising a valve body suitable for moving between an open position and a closed position of the discharge valve, a camshaft (22) comprising a cylindrical rod carrying a cam mounted to bear against the valve body in such a manner that rotating the camshaft causes the valve body to move between its open and closed positions, and means for keeping the cam bearing permanently against the valve body. The system further includes at least one main electric motor (30) having its rotor suitable for driving the camshaft of each discharge valve in rotation, and an electronic control system (32) for controlling each main electric motor.