A Study on the Stall Detection of an Axial Compressor through Pressure Analysis

Chen, Haoying; Sun, Fengyong; Zhang, Haibo; Luo, Wei

doi:10.3390/app7080766

Cited by 3 publications

(2 citation statements)

References 15 publications

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“…When the aircraft is in high Mach number cruise, the upstream and downstream flow fields of the inlet are prone to fluctuate due to the drop of shock wave, the change of atmospheric environment, or the launch of weapon. It causes the change of inlet normal shock wave position and then affects the stability of inlet or even causes the engine surge [12][13][14].…”

Section: Introductionmentioning

confidence: 99%

Study on Inlet and Engine Integrated Model with Normal Shock Position Feedback

Chen

Zhang

et al. 2020

International Journal of Aerospace Engineering

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In order to consider the inlet and engine integrated model of supersonic airliner, the dynamic identification and control of inlet normal shock are studied. The research is based on the bleed air flow rate under supersonic conditions. With the two-dimensional CFD model of supersonic inlet, the dynamic and static effects of the bleeding flow rate on the normal shock position were investigated. The transfer function was identified, and simultaneously the paper carried out a comprehensive study of inlet and engine integrated model, which is established based on the inlet shock position model and engine component level model. The relationship between normal shock position and total pressure recovery coefficient has been taken into consideration in this model. Based on the inlet and engine integrated model, the closed-loop control simulation of normal shock position is carried out. The results show that the model could resist the disturbance of the inlet flow and keep the inlet and engine matching operation point stable near the optimal value.

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Section: Introductionmentioning

confidence: 99%

Study on Inlet and Engine Integrated Model with Normal Shock Position Feedback

Chen

Zhang

et al. 2020

International Journal of Aerospace Engineering

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“…A new generation of environmentally friendly supersonic passenger aircraft with low sound boom has been developed. 1–5 National Aeronautics and Space Administration (NASA) and major American aerospace companies, such as Boeing, Lockheed Martin, Gulfstream Aerospace, and Aerion Company, are focusing on low-boom Supersonic Commercial Transport aircraft to reduce the sound level on the ground. 6–9…”

Section: Introductionmentioning

confidence: 99%

Study on integrated control for supersonic inlet and turbofan engine model

Chen

Zhang

et al. 2020

Proceedings of the Institution of Mechanical Engineers, Part G:

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Considering the supersonic inlet model with normal shock position feedback, the integrated control method of inlet and turbofan engine is studied. The integrated model includes the supersonic inlet model and the component level model of engine. Combining the relationship between the normal shock position and the total pressure recovery coefficient, the supersonic inlet and engine model is constructed. On the basis of this model, the normal shock position closed-loop control simulation is carried out, which shows that the normal shock position matching point could be stabilized near the optimal value while restraining the inlet stream disturbance. Furthermore, based on the H∞ control algorithm, an inlet and engine integrated control is designed to control the installation thrust and turbine pressure ratio with fuel, nozzle throat area, and normal shock position as control variables. The simulation results show that the response time of the integrated control is faster than the independent control. The integrated control has stronger ability to restrain the atmospheric disturbance, which could ensure the stable and reliable operation of the propulsion system.

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Wide-Range High-Confidence Surge Margin Estimation Method for Aircraft Engine

Chen,

Sheng,

Liu

et al. 2023

SAE Technical Paper Series

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<div class="section abstract"><div class="htmlview paragraph">The confidence of the onboard adaptive model in estimating surge margin significantly affects the operating stability in an aircraft engine’s active surge margin control process. Unfortunately, the existing onboard adaptive models lack high confidence, although wide-ranging in estimation, due to the unknown surge boundaries in component characteristics. Therefore, this paper first accurately estimates the actual surge margin during the engine operating near-surge boundary using a pressure correlation measurement technology. Then, innovatively, the estimated surge margin is used to correct the surge boundary of the nonlinear onboard model of the engine to obtain the actual surge boundary, thereby guaranteeing confidence. Finally, a nonlinear onboard adaptive model based on an improved spherical unscented Kalman filter is employed to achieve wide-range high-confidence surge margin estimation throughout the engine’s life cycle. Simulation results demonstrate that the proposed method is effective and has a high-confidence level in surge margin estimation, ensuring estimation accuracy of over 95% for both standard and degraded engines, far surpassing existing techniques. The proposed method provides a technical means for sensing surge margin in future high-stability engine active control.</div></div>

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A Study on the Stall Detection of an Axial Compressor through Pressure Analysis

Cited by 3 publications

References 15 publications

Study on Inlet and Engine Integrated Model with Normal Shock Position Feedback

Study on Inlet and Engine Integrated Model with Normal Shock Position Feedback

Study on integrated control for supersonic inlet and turbofan engine model

Wide-Range High-Confidence Surge Margin Estimation Method for Aircraft Engine

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