Browsing by Author "Zhang, Shuguang"
Now showing 1 - 3 of 3
Results Per Page
Sort Options
Item Open Access Gas turbine aero-engines real time on-board modelling: A review, research challenges, and exploring the future(Elsevier, 2020-12-22) Wei, Zhiyuan; Zhang, Shuguang; Jafari, Soheil; Nikolaidis, TheoklisOn-board real time modelling for gas turbine aero-engines has been extensively used for engine performance improvement and reliability. This has been achieved by the utilization of on-board model for the engine's control and health management. This paper offers a historical review of on-board modelling applied on gas turbine engines and it also establishes its limitations, and consequently the challenges, which should be addressed to apply the on-board real time model to new and the next generation gas turbine aero-engines. For both applications, i.e. engine control and health management, claims and limitations are analysed via numerical simulation and publicly available data. Regarding the former, the methods for modelling clean and degraded engines are comprehensively covered. For the latter, the techniques for the component performance tracking and sensor/actuator diagnosis are critically reviewed. As an outcome of this systematic examination, two remaining research challenges have been identified: firstly, the requirement of a high-fidelity on-board modelling over the engine life cycle, especially for safety-critical control parameters during rapid transients; secondly, the dependability and reliability of on-board model, which is critical for the engine protection in case of on-board model failure. Multiple model-based on-board modelling and runtime assurance are proposed as potential solutions for the identified challenges and their potential and effectiveness are discussed in detail.Item Open Access Hybrid Wiener model: an on-board approach using post-flight data for gas turbine aero-engines modelling(Elsevier, 2020-11-21) Wei, Zhiyuan; Jafari, Soheil; Zhang, Shuguang; Nikolaidis, TheoklisOn-board modelling of gas turbine aero-engines over the life cycle is a promising solution for engine performance improvement and future aero-propulsion requirements. In this paper, an on-board modelling approach named Hybrid Wiener model (HWM) is proposed for gas turbine aero-engines using post-flight engine monitoring data, which aims at estimating the unmeasured safety-critical control parameters (i.e. thrust, surge margin, and turbine entry temperature) by monitoring the engine degradation effects. Common on-board models for nominal engines, i.e. piecewise linear model, novel generalized describing function, and Wiener model, are systematically tested on a validated turbofan engine aero-thermal model. Simulations demonstrate that Wiener model is the best candidate for nominal engines. HWM is therefore constructed with the integration of on-line Wiener models and an off-line adaptation approach. The on-line part computes the unmeasured safety-critical parameters in a real-time manner. Meanwhile, the off-line adaptation part serves to periodically update the nonlinear static blocks of on-line Wiener models using the post-flight data in order to match the particular degraded engine. Idle to full-power rapid transient simulations of HWM are carried on the turbofan engine aero-thermal model for degradation simulations using publicly available data. Results from the studied turbofan engine at different flight cycles demonstrate that HWM is not only able to guarantee the steady accuracy for thrust, surge margin, and turbine entry temperature, but also ensures that the maximum transient errors for these safety-critical parameters are less than 4.66% during rapid acceleration states. Moreover, the percent errors of peak values for surge margin and turbine entry temperature between HWM and the engine are within 0.50%. The performance of the proposed HWM over the engine life cycle is therefore confirmedItem Open Access Self-enhancing model-based control for active transient protection and thrust response improvement of gas turbine aero-engines(Elsevier, 2021-12-29) Wei, Zhiyuan; Zhang, Shuguang; Jafari, Soheil; Nikolaidis, TheoklisA self-enhancing active transient protection (SeATP) control approach using model-based strategies is proposed for gas turbine aero-engines, which aims at pro-actively handling surge margin limit and turbine entry temperature limit over the life cycle. The feature of SeATP is a bank of self-enhancing loops with periodically updated controller parameters for different flight cycles. This is realized by an off-line gain tuning via global optimization approach. Additionally, a sensor-based baseline controller and a model-based active transient protection (ATP) controller (with fixed gains) are developed as comparison bases. Numerical simulations for the examined controllers are carried on a validated aero-thermal turbofan engine model for idle to full-power acceleration tests in Matlab/Simulink environment. Simulation results demonstrate that ATP controller owns a considerable thrust response improvement for both the new engine and a severely degraded engine, compared with the baseline controller. Moreover, the proposed SeATP controller ensures a 65.77% recovery rate of thrust response deviation caused by the ATP controller for the degraded engine. Particularly, a low transient surge margin trajectory and a high turbine entry temperature route are fulfilled by the SeATP controller. SeATP controller also shows better robustness performance for degradation variation than ATP controller. Hence, the SeATP control performance is confirmed.