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

Claim 3:
4. The method of claim 2, comprising:
determining, for the turbomachine to be investigated, operating in flight, a first rotation speed of a first high-pressure compressor of the turbomachine to be investigated, and measured operating parameters comprising at least one quantity selected from among a first atmospheric pressure and a first altitude, and
determining, based on a model of the reference turbomachine giving a second gate angle of the reference turbomachine with respect to the second casing of the reference turbomachine, depending on a second rotation speed of a second high-pressure compressor of the reference turbomachine and on a second atmospheric pressure of the reference turbomachine or on a second operating altitude of the reference turbomachine, the reference droop angle, which is the second gate angle of the reference turbomachine which corresponds according to the model to the measured operating parameters,
the second gate angle corresponding to an angle of the second gate with respect to the second casing, which has been determined based on a second actual position of the second actuator, having itself been measured for the reference turbomachine operating in flight, when the second control signal is equal to a second set point closing signal of the second gate.