Abstract
The sequential quadratic programming algorithm was applied to the performance seeking control of multi-variable turbofan engine. According to the actual condition of aircraft cruise status, the constant thrust condition is added in the constraint functions of nonlinear programming. Based on the mathematical modes of turbofan engine, the SQP algorithm is adopted to the minimum fuel consumption mode of cruise condition. The simulation results show that after the optimization process, the engine fuel consumption rate decreased by nearly 2%, and the turbine temperature dropped by about 1.2%, the dual optimization benefits have been achieved. There are great potentials in engineering applications.
Highlights
Since the nineties of last century, the aero-engine performance seeking control technology is the latest development of integrated control of aircraft and aero-engine
When the nonlinear aeroengine was linearized, it will inevitably result in the conversion error, and the final global optimal solution will deviate from the actual global optimal point
The SQP algorithm was introduced into the aero-engine performance seeking control, which solves the problem of constraint condition and optimization algorithm under the minimum fuel consumption mode
Summary
Since the nineties of last century, the aero-engine performance seeking control technology is the latest development of integrated control of aircraft and aero-engine. The SQP algorithm was introduced into the aero-engine performance seeking control, which solves the problem of constraint condition and optimization algorithm under the minimum fuel consumption mode. Integrated control system based on the aero-engine performance seeking control technology is shown, the system is a typical upper and lower computer structure. The performance seeking control technology is expressed as a non-linear programming form. By optimizing control law of the engine in the minimum fuel consumption mode, the fuel consumption of the engine will reduce while the engine thrust meets the needs of steady-state flight. It will help improving the flight performance of aircraft. Where sfc is specific fuel consumption, WF is fuel flow of combustor, A8 is outlet area of nozzle, PNF is relative speed of fan, PNC is relative speed of compressor, T5 is outlet temperature of low pressure turbine
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