| Citation: | HU Qiuchen, CHEN Yuchun, LING Wenhui, et al. Design of three nozzle control plans for aero engines and robustness analysis[J]. Journal of Aerospace Power, 2026, 41（2）：20240859 doi: 10.13224/j.cnki.jasp.20240859
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The nozzle critical area control plan is an important safeguard for the operational safety and performance of aero-engines. However, it is susceptible to multiple uncertainties such as sensor drift and guide vane drift, which may lead to a reduction in the engine’s surge margin and thrust. To quantitatively analyze the impact of sensor and vane drift on the engine, a nozzle critical area control plan design method based on fan surge margin constraints was proposed. A component-level engine model was used to develop the control plans for engine pressure ratio, pressure drop ratio, and difference of rotational speed. The equivalence of the three nozzle control plans was verified, and the robustness of these strategies was analyzed under conditions where speed, temperature, pressure sensors, and high-pressure vanes experienced drift at typical operating points. The results showed that, in case of pressure sensor drift, the pressure ratio control plan exhibited better robustness than the pressure drop ratio control plan. In the case of guide vane drift, the pressure ratio control plan demonstrated the best robustness, followed by the pressure drop ratio control plan, while the slip ratio control plan showed the least robustness.
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