Automatic blade pitch control
AssigneeSafran Aircraft Engines
InventorsSébastien Jean Fernand Deneuve, Charles Ying
Life of this patent
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Abstract
The invention relates to a method for controlling a pitch angle of the vanes or blades of a propellant body of a turbine engine, comprising generating a pitch command (ifinal) according to a rotational speed of the propeller (XNmes) and a speed setpoint (XNcons), the method comprises a nominal regulating chain (13), wherein the pitch command is further generated according to a value of a pitch angle (βmes) of the vanes or blades of the propellant body, and an off-nominal regulating chain (16), wherein the pitch command is generated independently of a value of a pitch angle of the vanes or blades of the propellant body.
Claims7
A method for controlling a setting angle of vanes or blades of a propeller of a turbomachine, the method comprising generating a setting command, the setting command being a function of a speed of rotation of the propeller and of a rating setpoint,
- wherein generating the setting command comprises:
- generating, in a nominal controlling line, a nominal setting command as a function of a value of a setting measurement of the vanes or the blades of the propeller, and
- generating, in a downgraded controlling line, a downgraded setting command independently of the value of the setting measurement of the vanes or the blades of the propeller,
- wherein the method further comprises:
- a selection step of selecting the downgraded controlling line so that the setting command is equal to the downgraded setting command, or the nominal controlling line so that the setting command is equal to the nominal setting command,
- a supply step of supplying the setting command to an actuator configured to modify the setting angle, and
- before the supply step and after the selection step, a command return step so that the setting command is directly sent to at least one of the nominal controlling line and the downgraded controlling line,
- wherein the actuator changes the setting angle based on the setting command.
A device for controlling the setting of a propeller of a turbomachine comprising an actuator configured to modify a setting angle of the propeller, the device comprising:
- a controller,
- a first sensor configured to determine a value of a setting angle of the propeller,
- a second sensor configured to determine a speed of rotation of the propeller, the controller being configured to:
- in a nominal controlling mode, supply a nominal setting command to the actuator, the nominal setting command being a function of a rating setpoint, of the value of the setting angle and of the speed of rotation of the propeller;
- in a downgraded controlling mode, supply a downgraded setting command to the actuator, the downgraded setting command being a function of the rating setpoint and of the speed of rotation of the propeller, the downgraded setting command being independent on the value of the setting angle;
- the device further comprising a selector configured to select the nominal controlling mode or the downgraded controlling mode of the controller, and supply the nominal setting command or the downgraded setting command that corresponds to the nominal controlling mode or the downgraded controlling mode that is selected to an actuator configured to modify the setting angle,
- wherein the actuator changes the setting angle based on the nominal controlling mode or the downgraded controlling mode selected by the selector.
Dependencies are inferred from the claim text.