Steady state simulation method of whole aero-engine based on circumferentially averaged method

A numerical simulation method of the whole aero-engine based on the circumferentially averaged method was developed independently. Based on the Navier-Stokes equation, the governing equation of the circumferentially averaged throughflow model was deduced. In view of the shortcomings of the traditional model for the source terms of the equation, an inviscid blade force model considering the influence of airfoil, a compressor spanwise distribution loss model based on machine learning, and a circumferential non-uniformity model based on theoretical analysis were proposed. On this basis, the quasi-3D modeling of the combustion chamber was further completed, and finally the quasi-3D steady state simulation of the whole aero-engine was realized. The whole aero-engine simulation of turbojet engine WP11 was completed by using the whole aero-engine circumferentially averaged steady state simulation program CAM developed, and the simulation results of the Russian S2 program AES-S2 were compared and analyzed. The results showed that compared with the Russian S2 program AES-S2, the circumferentially aver-aged quasi-3D simulation program developed had higher simulation accuracy. In comparison of the quasi-3D calculation results of WP11’s design point, the error of turbine mass flow calculated by CAM was less than that of AES-S2 by over 8%. In terms of engine thrust, the error was reduced by more than 16%. The convergence of CAM was better. The amplitude of the turbine mass flow calculated by CAM was less than that of AES-S2 by over 10%. In terms of engine thrust, the amplitude of the calculation result was reduced by more than 20%. © 2022 BUAA Press. All rights reserved.