Patent ID: 11891958
Assignee: SAFRAN AIRCRAFT ENGINES
Field: Engines, pumps, turbines (Mechanical engineering)
Classification: CPC F  B | IPC B  F

Claim 1:
2. The method of claim 1, wherein:
the reference turbomachine has a second gate of a second discharge valve mounted on a second casing of the reference turbomachine, the second casing delimiting in its inside a second primary gas flow of the reference turbomachine, the second gate being designed to be able to be moved angularly by a second actuator depending on a second control signal of the second actuator between one and the other of:
a second opening position of a second orifice of the second casing to discharge through the second orifice portion of the second primary gas flow into a second secondary gas flow of the reference turbomachine located outside the second casing,
and a second closing position of the second orifice to prevent the second primary gas flow from passing through the second orifice,
the second gate being provided with a second gas seal gasket, able to be compressed against a second edge of the second orifice in the second closing position to seal closing of the second orifice.