| To solve the problem of subjective interference of designers and difficulty in determining the weight coefficients during
engine modification or performance optimization, a gas turbine engine was taken as the research object, the net thrust (F N ), specific fuel
consumption (S FC ) and the minimum cross-sectional area of the nozzle (A 8 ) were taken as the optimization target parameters, and the
sensitivity analysis method was used to solve the objective weight, and the comprehensive weight was calculated by combining the Entropy
Weight Method, and the overall performance optimization research was carried out based on the nonlinear weighting method. The results
show that the comprehensive weights of S FC , F N , and A 8 are 0.5204, 0.26125, and 0.21835, respectively, of which S FC accounts for the largest
comprehensive weight, indicating that the optimization of S FC can give full play to betterthe performance of the engine, and S FC optimization
is relatively easier and less expensive. The design values of the overall engine performance parameters (S FC , F N , A 8) have 5.32%, 0.67%, and
3.25% optimization space respectively, indicating that under the premise of little change in thrust, it can be optimized according to the idea
of greatly reducing fuel consumption and reducing A 8 . The optimization result not only overcomes the shortcomings of subjective factors
interference of previous designers, but also meets the current component design level of the engine and the requirements of cost optimiza?
tion, which can provide an effective basis for designers to make target trade-offs in the engine scheme design stage. |