Research On Performance Matching Of Micro Turboprop Engine

Engine performance calculation is significant in guiding the basic theoretical research,model design,test and use of aero-engines.The micro turboprop engine is widely used in military-civilian integration fields such as UAV and model airplane because of its small size,high thrust-weight ratio,high energy density,and easy maintenance.In this paper,the overall performance simulation and ground bench test of a micro twin-shaft turboprop engine are carried out.Firstly,for the twin-shaft turboprop,the calculation method of its aero-thermal power and performance parameters at design point is introduced.According to the working process parameters and flight conditions at engine design point,the aero-thermal calculation is performed using thermodynamic formulas as about the energy conservation and component efficiency,thus obtaining the thrust,specific fuel consumption and other performance parameters under engine design conditions.Combined with the characteristics of the propeller,the calculation methods for the performance matching between the engine and propeller with fixed and variable pitch are described respectively,which provides theoretical guidance to realize the overall performance calculation of the integrated propeller-engine.Aiming at a micro twin-shaft turboprop engine,a CFD calculation is carried out on its compressor,gas turbine,power turbine,propeller,etc.According to the engine design parameters and the component characteristics,the integrated simulation of the propeller and engine is carried out using the gas turbine commercial software.As a result,the simulation calculation of performance matching of integrated propeller-engine under variable working conditions is realized,the steady-state co-working lines of various components and the characteristics of the engine under variable working conditions are obtained,and the throttle,speed and altitude characteristics of the turboprop engine are predicted and analyzed.For the micro turboprop engine studied in this paper,the ground test platform is built and debugged to carry out bench test experiments on the overall engine performance and the engine performance parameters such as thrust,specific fuel consumption,rotational speed of gasgenerator and propeller under different operating conditions are obtained.Then,the experimental data and simulation result is compared,verified and analyzed.The results show that,the propeller thrust and rotational speed change with the rotational speed of the gasgenerator,and as the engine throttle increases,the experimental data and the simulation results of the law of this change gradually become consistent.When the rotation speed of core engine is 95000 rpm,the error becomes the smallest,and the comparison errors of propeller thrust and rotational speed is 2% and 0.55% respectively,which proves a relatively good contrast effect.The research above combines the characteristics of the propeller components to establish a calculation method for the overall performance of the integrated propeller-engine,and the effectiveness of the method is verified through experiments,which provides an effective basis for the development and improvement of the micro turboprop engine.