Design And Simulation Of Turboprop Engine Integrated Control Law

Compared with aero piston engines,turboprop engines have the advantages of higher power-to-weight ratio,smaller windward area,smaller vibration and more superior performance with increasing altitude,especially flying at low altitude.Compared with turbojet and turbofan engines,turboprop engines can reach lower specific fuel consumption(SFC)and larger thrust at take-off state.With the progress of engine and propeller technology,the control demand for turboprop engine is increasing,as well as the number of peration parameters by the pilot.If the controls of engine and propeller are integrated,the propulsion efficiency of the propeller can be improved,and the economic efficiency of the turboprop engine can be increased further.Also,the work burden of the pilot can he reduced,and the error rate of the pilot operation can be decreased.This paper analyzes the domestic and foreign status of turboprop engines.Based on a double-rotor turboprop engine with free power turbine,the mathematical models of the turboprop engine on static and dynamic states are created by using the method of variable specific heat and component principle.Combined with the equirements of engineering,a closed-loop integrated control law is proposed for the double-rotor turboprop engine,including start control,above idle control,feathering and reversing propeller control and shut down control.Finally,a semi-physical simulation test is carried out.The test results show that the mathematical models of the turboprop engine accords with the principle of aero engine,and the integrated control law for turboprop engine can realize the control for the engine and propeller.All the control parameters of the engine are within reasonable ranges.Under the condition of uring safety of the turboprop engine,the matching between engine and propeller can be improved effectively.In conclusion,the integrated control law is reasonable and feasible.