Device for assisting with regulation of propellers of aeronautical turbomachinery
AssigneesSafran, Safran Aircraft Engines
InventorsHenri Yesilcimen, Anthony Binder, Panagiotis Giannakakis
Life of this patent
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Abstract
This control device for a propulsion system, comprising means for calculating a blade-pitch setpoint of at least one propeller of the propulsion system, the calculation means using a performance predictive model of the propeller taking account of at least one flight speed for adapting a blade-pitch angle setpoint, is characterised in that the performance predictive model of the propeller is configured to use polar charts implemented in the form of a mathematical law.
Claims11
A turboprop engine comprising:
- an actuator configured to control a blade pitch;
- and
- control device for a propulsion system, the control device comprising one or more processors, wherein the one or more processors are configured to determine a blade-pitch setpoint of at least one propeller of the propulsion system using a performance predictive model of the propeller taking account of at least one flight speed for adapting a blade pitch angle setpoint,
- wherein the performance predictive model of the propeller is configured to use polar charts implemented in the form of a mathematical law, comprising:
- a first polar diagram giving a lift coefficient as a function of angle of incidence, relative Mach number, and a ratio between flight speed and peripheral speed of the propeller;
- and
- a second polar diagram giving a drag coefficient as a function of the lift coefficient, the relative Mach number, and the ratio between the flight speed and the peripheral speed of the propeller,
- wherein the actuator is configured to adapt the blade pitch depending on a difference between a measured instantaneous blade pitch angle and the blade pitch angle setpoint.
A method for controlling a propulsion system of a turboprop engine, comprising:
- determining, by one or more processors, a blade-pitch setpoint of at least one propeller of the propulsion system, during which a step of predicting the performance of the propeller is performed taking account of at least one flight speed to adapt a blade-pitch angle setpoint, said prediction step being characterised by the use of the polar charts implemented in the form of a mathematical law, comprising:
- a first polar diagram giving a lift coefficient as a function of angle of incidence, relative Mach number, and a ratio between flight speed and peripheral speed of the propeller;
- and
- a second polar diagram giving a drag coefficient as a function of the lift coefficient, the relative Mach number, and the ratio between the flight speed and the peripheral speed of the propeller;
- and
- adapting, by an actuator, a blade pitch of the turboprop engine depending on a difference between a measured instantaneous blade pitch angle and the blade pitch angle setpoint.
Dependencies are inferred from the claim text.