Torque control system
AssigneeUnited Technologies Corporation
InventorAnthony N. Martin
Life of this patent
Estimating the term…
Abstract
The dynamic instabilities in a system which controls prime mover output torque and angular velocity separately are avoided by deriving an accelerating torque signal in an output torque controller where it is added to a sensed torque signal, and the added signal is compared to a commanded torque signal, the difference signal value therebetween serving to control the output torque.
Claims13
Apparatus for providing a signal for controlling the output torque of a prime mover driving a load in a system having rotating parts of known rotational inertia including an output shaft controlled at a commanded torque value, the output shaft controlled at a commanded angular velocity by controlling the load absorbing capacity of the load, the system having signals associated therewith having magnitudes indicative of the actual angular velocity, a commanded torque value and an actual sensed torque value, comprising:
- means responsive to changes in the actual angular velocity signal for providing a load torque transient signal indicative of the presence of a changing load torque, said load torque transient signal having a present value indicative of the present value of said changing load torque;
- and
- summing means, responsive to said torque transient signal, to the commanded torque signal and to the sensed torque signal for adding the present values thereof for providing a prime mover output torque error signal compensated for load torque transients for controlling the output torque of the prime mover.
Apparatus for providing a fuel flow signal for controlling the output torque of an aircraft single shaft turboprop engine of known rotational inertial at a commanded torque value by controlling engine fuel flow, the engine output shaft having a propeller and shaft of known rotational inertia attached by means of gears thereto controlled at a commanded angular velocity by controlling the pitch of the propeller blades, the aircraft having signals associated therewith having magnitudes indicative of the actual propeller angular velocity, a commanded torque value and an actual sensed torque value, comprising:
- means responsive to the signal indicative of actual propeller angular velocity for providing a load torque transient signal indicative of the presence of a changing load torque exerted on the propeller shaft, said load torque transient signal having a present value indicative of the present value of said changing load torque;
- and
- summing means, responsive to said load torque transient signal, to the commanded torque signal and to the sensed torque signal for adding the present values thereof for providing an engine output torque error signal as a fuel flow signal compensated for load torque transients for controlling the fuel flow and hence the output torque of the engine.
Apparatus for providing a fuel flow signal for controlling the output torque of an aircraft two-shaft turboprop engine having a gas generator with a free turbine for driving a compressor on an outer shaft, and having a power turbine on an inner output shaft fluidly coupled to said gas generator for driving the inner shaft at a commanded output torque value by controlling engine fuel flow, the power turbine and inner shaft having a known rotational inertia, the engine output shaft having a propeller and shaft of known rotational inertia attached by means of gears thereto controlled at a commanded angular velocity by controlling the pitch of the propeller blades, the aircraft having signals associated therewith having magnitudes indicative of the actual propeller angular velocity, a commanded torque value and an actual sensed torque value, comprising:
- means responsive to the signal indicative of actual propeller angular velocity for providing a load torque transient signal indicative of the presence of a changing load torque exerted on the propeller shaft, said load torque transient signal having a present value indicative of the present value of said changing load torque;
- and
- summing means, responsive to said load torque transient signal, to the commanded torque signal and to the sensed torque signal for adding the present values thereof for providing an engine output torque error signal as a fuel flow signal compensated for load torque transients for controlling the fuel flow and hence the output torque of the engine.
Apparatus for providing a fuel flow signal for controlling the output torque of an helicopter single shaft turboprop engine of known rotational inertia at a commanded torque value by controlling engine fuel flow, the engine having a rotor and rotor shaft of known rotational inertia attached by means of gears thereto controlled at a commanded angular velocity by controlling the pitch of the rotor blades, the helicopter having signals associated therewith having magnitudes indicative of the actual rotor angular velocity, a commanded torque value and an actual sensed torque value, comprising:
- means responsive to the signal indicative of actual rotor angular velocity for providing a load torque transient signal indicative of the presence of a changing load torque exerted on the rotor shaft, said torque transient signal having a present value indicative of the present value of said changing load torque;
- and
- summing means, responsive to said load torque transient signal, to the commanded torque signal and to the sensed torque signal for adding the present values thereof for providing an engine output torque error signal as a fuel flow signal compensated for load torque transients for controlling the fuel flow and hence the output torque of the engine.
Apparatus for providing a fuel flow signal for controlling the output torque of a helicopter two-shaft turboprop engine having a gas generator with a free turbine for driving a compressor on an outer shaft and a power tubine on an inner output shaft fluidly coupled to said gas generator for driving the inner shaft at a commanded output torque value by controlling engine fuel flow, the power turbine and inner shaft having a known rotational inertia, the engine output shaft having a rotor and rotor shaft of known rotational inertia attached by means of gears thereto controlled at a commanded angular velocity by controlling the pitch of the rotor blades, the helicopter having signals associated therewith having magnitudes indicative of the actual rotor angular velocity, a commanded torque value and an actual sensed torque value, comprising:
- means responsive to the signal indicative of actual rotor angular velocity for providing a load torque transient signal indicative of the presence of a change in the load torque exerted on the rotor shaft, said torque transient signal having a present value indicative of the present value of said change in load torque;
- and
- summing means, responsive to said load torque transient signal, to the commanded torque signal and to the sensed torque signal for adding the present values thereof for providing an engine output torque error signal as a fuel flow signal compensated for load torque transients for controlling the fuel flow and hence the output torque of the engine.
Apparatus for controlling the output torque of an engine in a system in which the output speed of the engine is controlled at a selected speed, comprising:
- means responsive to a sensed engine output speed signal for providing a load torque transient signal indicative of the magnitude of any load torque transients present;
- and
- summing means, responsive to the load torque transient signal, to a commanded engine output torque signal and to a sensed engine output torque signal for adding the load torque transient signal, the commanded engine output torque signal and the sensed engine output torque signal for providing a compensated engine output torque error signal for controlling the output torque of the engine.
Dependencies are inferred from the claim text.