Design of three nozzle control plans for aero engines and robustness analysis
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摘要:
喷管临界面积控制计划是航空发动机运行安全和性能表现的重要保障，但是其易受到传感器漂移、导叶漂移等多元不确定性因素的影响，导致发动机的喘振裕度和推力下降。为了定量分析传感器和导叶漂移对发动机的影响，提出了一种基于风扇喘振裕度约束的喷管临界面积控制计划设计方法，利用发动机部件级模型设计了增压比、落压比和转差控制计划，验证了三种喷管控制计划的同一性，分析了三种控制计划在典型工况点时压力传感器和高压导叶分别发生漂移时的鲁棒性。结果表明：在面对压力传感器漂移时，相比落压比控制计划，增压比控制计划鲁棒性更好；在面对导叶漂移时，增压比控制计划鲁棒性最好，落压比控制计划的鲁棒性次之，转差控制计划的鲁棒性最差。
Abstract: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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Key words:
- low-bypass ratio turbofan engine /
- nozzle control plan /
- sensor drift /
- vane drift /
- robustness analysis
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图 2 发动机不同工作状态喷管控制计划
Figure 2. Nozzle control plan for different engine operating states
图 3 风扇换算流量-压比部件特性
Figure 3. Fan corrected flow-pressure ratio component characteristics
图 7 设计点中间状态传感器漂移对发动机性能影响
Figure 7. Impact of sensor drift at intermediate state of the design point on engine performance
图 8 设计点最大加力状态传感器漂移对发动机性能影响
Figure 8. Impact of sensor drift at maximum afterburner state of the design point on engine performance
图 9 工况点H=11 km、Ma=0.9中间状态传感器漂移对发动机性能影响
Figure 9. Impact of sensor drift at intermediate state of the operating point H=11 km，Ma=0.9 on engine performance
图 10 工况点H=11 km、Ma=0.9最大加力状态传感器漂移对发动机性能影响
Figure 10. Impact of sensor drift at maximum afterburner state of the operating point H=11 km，Ma=0.9 on engine performance
图 12 设计点中间状态高压压气机导叶漂移对发动机性能影响
Figure 12. Impact of high-pressure compressor vane drift at intermediate state of the design point on engine performance
图 13 设计点最大加力状态高压压气机导叶漂移对发动机性能影响
Figure 13. Impact of high-pressure compressor vane drift at maximum afterburner state of the design point on engine performance
图 14 工况点H=11 km、Ma=0.9中间状态高压压气机导叶漂移对发动机性能影响
Figure 14. Impact of high-pressure compressor vane drift at intermediate state of the operating point H=11 km，Ma=0.9 on engine performance
图 15 工况点H=11 km、Ma=0.9最大加力状态高压压气机导叶漂移对发动机性能影响
Figure 15. Impact of high-pressure compressor vane drift at maximum afterburner state of the operating point H=11 km，Ma=0.9 on engine performance
表 2 三种控制计划传感器使用情况
Table 2. Sensor usage in three control plans
喷管控制计划 所用传感器参数 增压比控制计划 pt2, pt6, n1, Tt2 落压比控制计划 ps31, pt6, n2, Tt25 转差控制计划 n1, n2, Tt2, Tt25 
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