面向航空发动机可调收扩喷管的安装性能协同优化方法

doi:10.7527/S1000-6893.2025.32176

Abstract

Abstract:

The technology for solving dynamic ordinary differential equations is used to solve the dynamic model of the engine in real time， and the bisection method is combined to achieve the real-time evaluation of the engine’s stability. Based on the dynamic simulation data of the model and the results of aerodynamic stability evaluation， an optimization method for the A8 control law and the A9/A8 area ratio that optimizes the installed thrust of the engine and aerodynamic stability based on the differential evolution algorithm is established， so as to realize the integrated joint simulation evaluation of the aircraft and the engine based on the flight conditions. The research shows that compared with the Sequential Least Squares Programming （SLSQP） method， the optimization method based on the differential evolution algorithm exhibits global optimality. The area optimization of the A8 of the aeroengine under three typical working conditions is performed， which are accelerating from Mach number 0.9 to Mach number 1.2 in the level flight state at an altitude of 11 km， cruising at Mach number 0.9 at an altitude of 11 km， and climbing from an altitude of 5 km to 11 km in the intermediate state. Compared with the design point， in the level flight state and climbing state， the optimization method based on the differential evolution algorithm realizes an increase in the time-averaged net thrust of the engine by 15.38% and 12.36% respectively by optimizing the A8 control law and the A9/A8 area ratio， and the fuel consumption is reduced by 6.88% in the cruising state. The results of this paper prove that the optimization method based on the differential evolution algorithm can increase the net thrust of the engine and reduce fuel consumption， and can provide theoretical methods and technical guidance for increasing the installed thrust of the aircraft.

Key words: installed thrust, optimization of nozzle adjustment plan, differential evolution algorithm, aerodynamic stability, afterbody drag

CLC Number:

V231

Sifang LIU, Weimin GAO, Zhibo REN, Fangchao TIAN, Zhiqiang SUN. Collaborative optimization method of installation performance for adjustable retracting and expanding nozzle for aero-engine[J]. Acta Aeronautica et Astronautica Sinica, 2026, 47(7): 632176.

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设计参数	设计值
风扇压比	4.1
压气机压比	5.1
涡轮前温度/K	2 000
总体质量流量/（kg·s^-1）	120
涵道比	0.8
N ₁转速/（r·min^-1）	9 000
N ₂转速/（r·min^-1）	15 000

Collaborative optimization method of installation performance for adjustable retracting and expanding nozzle for aero-engine

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