Method for braking an aircraft turbine engine
AssigneeSafran Aircraft Engines
InventorsJacques Auriol, Pierre-Alain Jean Philippe Reigner
Life of this patent
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Abstract
Method for braking an aircraft turbine engine including a fan or a propeller connected to a turbine by a shaft and an electric generator connected to the shaft, the method comprising the following steps: a request to brake the turbine engine by thrust reversal; a calculation of a turbine braking setpoint by a control system; and in response to the braking setpoint, an adjustment by the control system of a resistance of a dissipative load to draw electric power from the electric generator to the dissipative load.
Claims12
A braking method for braking an aircraft turbine engine comprising a fan or a propeller connected to a turbine by a shaft and an electric generator connected to the shaft, the method comprising the following steps:
- a request to brake the turbine engine by thrust reversal;
- a calculation of a turbine braking setpoint by a control system;
- and
- in response to the calculation of the turbine braking setpoint, an adjustment by the control system of a resistance of a dissipative load to draw electric power from the electric generator to the dissipative load.
An aircraft turbine engine comprising a fan or a propeller connected to a turbine by a shaft, and an electric generator connected to the shaft, wherein the aircraft turbine engine further comprises a control system configured to calculate a turbine braking setpoint in response to a request to brake the turbine engine by thrust reversal, and wherein the control system is further configured to adjust a resistance of a dissipative load in response to the turbine braking setpoint to draw electric power from the electric generator to the dissipative load.
Dependencies are inferred from the claim text.