Analytic Parameterization of Stabilizing Controllers for the Moore-Greitzer Compressor Model

This work presents an extension, simplification and application of a design procedure for dynamic output feedback design for systems with nonlinearities satisfying quadratic constraints (QC). Our method was motivated by the challenges of output feedback control design for the three-state Moore-Greitzer (MG) compressor model. The classical three-state MG model is a nonlinear dynamical system that is widely used in stall/surge analysis and control design. First, we find the parameter set of the stabilizing dynamic output feedback controllers for the surge subsystem by using conditions for stability of a transformed system and the associated matching conditions. Second, we choose the optimal control parameters from the stabilizing set with respect to different desired criteria. We show the set of parameters of the stabilizing controllers for the surge subsystem and the set of parameters of the stabilizing controllers with extended integral part for MG compressor. We present simplified sufficient conditions for stabilization, new constraints for the corresponding parameters and examples of optimal problem for the surge subsystem of the Moore-Greitzer compressor model. We discuss the degree of robustness and clarify an alternative proof of stability of the closed-loop system with the surge subsystem and the stabilizing dynamic output feedback controller without an integral state. In addition, we show the derivation of a quadratic function by using CVX

Model Analysis and Nonlinear Control of Air Compressors

RÉSUMÉ Pendant des décennies, les turbines à gaz ont été des dispositifs importants et fiables dans les domaines de la production d'énergie, de l'industrie pétrochimique, et de l'aéronautique. Ces machines utilisent les compresseurs centrifuges et axiaux qui se dégradent en présence d’instabilités aérodynamiques telles que le pompage et le décrochage tournant. Ces dernières limitent la performance et peuvent causer des sollicitations mécaniques importantes, une réduction de la durée de vie, du bruit et des vibrations. De plus, dans les compresseurs axiaux à vitesse variable (CAVV), les variations de vitesse affectent la stabilité des systèmes et peuvent entraîner le pompage et le décrochage tournant. Cela limite le taux de variation de vitesse et pénalise la performance. Le travail présenté dans cette thèse dresse premièrement l'analyse de bifurcation du modèle des CAVVs afin d’étudier l'impact de la dynamique de la vitesse sur la stabilité de points de fonctionnement efficaces. Ici, le taux de variation de vitesse (accélération) est défini comme un nouveau paramètre du modèle et une analyse détaillée de bifurcation numérique est fournie. Les résultats des simulations dans le domaine temporel valident non seulement l'analyse de bifurcation, mais élargissent aussi nos connaissances sur la réponse transitoire du modèle, qui est d’une importance majeure. L'analyse réalisée révèle que les variations de vitesse peuvent mener à un décrochage tournant entièrement développé ainsi qu’au décrochage temporaire mentionné précédemment. Les résultats montrent que les instabilités développées dépendent fortement du taux d'accélération. L'impact des autres paramètres du modèle, les vitesses initiale et finale, et la contribution des modes du décrochage sont également étudiés. Au niveau du contrôle, malgré toutes les réalisations présentées, la conception d’une commande robuste même pour des systèmes de compression axiaux à vitesse constante demeure encore un problème difficile. Ici, deux méthodes de commande non linéaires: le contrôle par modes glissants et le contrôle par passivité sont proposées pour résoudre ce problème de stabilité. Ces deux approches traitent de tous les aspects difficiles du sujet qui apparaissent dans la littérature : l'impact des perturbations externes, le manque de connaissance précise des paramètres du modèle, et l'absence d’un retour d’état complet.---------- ABSTRACT For decades, gas turbines have been important, widespread, and reliable devices in the field of power generation, petrochemical industry, and aeronautics. They employ centrifugal and axial compressors which suffer from aerodynamic instabilities, namely, surge and rotating stall. These performance limiting instabilities can cause component stress, lifespan reduction, noise, and vibration. Furthermore, in variable speed axial compressors (VSACs), speed variations affect the system stability and can lead to surge and rotating stall. This limits the rate of speed variations and results in important performance penalties. The present work firstly addresses the bifurcation analysis of VSACs’ model to investigate the impact of speed dynamics on the stability of efficient operating points. Here, the rate of speed variations (acceleration rate) is defined as a new parameter of the model and a detailed numerical bifurcation analysis is provided. The results of time-domain simulations not only validate the results of bifurcation analysis, but also broaden our knowledge about the transient response of the model, which is a matter of importance as well. The analysis reveals that speed variations can lead to a fully developed rotating stall as well as the previously reported temporary stall developments. The results show that the developed instabilities depend to a great extent on the acceleration rate. The impact of other key issues such as throttle gain, viscosity factor, initial speed, final speed, and the contribution of stall modes are also explored. From the control point of view, despite reported achievements, robust control design for compression systems remains a challenging problem. In this work, at first, two nonlinear approaches are proposed to tackle the stability problem of constant-speed axial compressors (CSACs). The first approach is a robust passivity-based control and the second one is a second order sliding mode control. The approaches tackle the challenging problems being addressed in the literature such as: the impact of external perturbations, the lack of detailed parameters knowledge, and the absence of full-state feedback. They drive the control from pressure and mass flow measurements and use throttle and close-coupled valve actuations. Finally, this study reports that these methods can be used in the case of VSACs by applying the required modifications to simultaneously control speed and instabilities. This simultaneous control design has been an open problem and the proposed method can improve the performance of VSACs

Controlling Chaos and Bifurcation of Subsynchronous Resonance in Power System

Linear and nonlinear state feedback controllers are proposed to control the bifurcation of a new phenomenon in power system, this phenomenon of electro-mechanical interaction between the series resonant circuits and torsional mechanical frequencies of the turbine generator sections, which known as Subsynchronous Resonance (SSR). The first system of the IEEE second benchmark model is considered. The dynamics of the two axes damper windings, Automatic Voltage Regulator (AVR) and Power System Stabilizer (PSS) are included. The linear controller gives better initial disturbance response than that of the nonlinear, but in a small narrow region of compensation factors. The nonlinear controller not only can be easily implemented, but also it stabilizes the operating point for all values of the bifurcation parameter

Nonlinear Control and Modeling of Rotating Stall in an Axial Flow Compressor

This thesis focuses on understanding the use of air injection as a means of controlling rotating stall in an axial flow compressor, involving modeling, dynamical systems analysis, and experimental investigations. The first step towards this understanding was the development of a low order model for air injection control, the starting point of which was the Moore and Greitzer model for axial flow compressors. The Moore and Greitzer model was extended to include the effects of air injection and bifurcation analysis was performed to determine how the closed loop system dynamics are different from those of the open loop system. This low order model was then used to determine the optimal placement of the air injection actuators. Experimental work focused on verifying that the low order model, developed for air injection actuation, qualitatively captured the behavior of the Caltech compressor rig. Open loop tests were performed to determine how the placement of the air injectors on the rig affected the performance of the compressor. The positioning of the air injectors that provided the greatest control authority were used in the development of air injection controllers for rotating stall. The controllers resulted in complete elimination of the hysteresis associated with rotating stall. The use of a throttle actuator for the control of the surge dynamics was investigated, and then combined with an air injection controller for rotating stall; the resulting controller performed quite well in throttle disturbance rejection tests. A higher order model was developed to qualitatively match the experimental results with a simulation. The results of this modeling effort compared quite well with the experimental results for the open loop behavior of the Caltech rig. The details of how the air injection actuators affect the compressor flow were included in this model, and the simulation predicted the same optimal controller that was developed through experimentation. The development of the higher order model also included the investigation of systematic methods for determining the simulation parameters. Based on experimental measurements of compression system transients, the open loop simulation parameters were identified, including values for the compressor performance characteristic in regions where direct measurements were not possible. These methods also provided information on parameters used in the modeling of the pressure rise delivered by the compressor under unsteady flow conditions

Noisy Precursors for Nonlinear System Instability with Application to Axial Flow Compressors

This dissertation addresses monitoring of nonlinear systems for detection and prediction of incipient instabilities. The analysis and design presented here rely on the influence of noise on system behavior near the onset of instability. The work is of relevance to high performance engineering systems, which are often operated with a low stability margin in order to maximize performance. In such a stressed operating mode, a small or moderate disturbance can result in loss of stability of the nominal operating condition. This can be followed by operation in a new lower performance mode, oscillatory behavior, or even system collapse. All of these conditions can be viewed as bifurcations in the underlying dynamical models. Prediction of the precise onset points of these instabilities is made difficult by the lack of accurate models for complex engineering systems. Thus, in this thesis monitoring systems are proposed that can signal an approaching instability before it occurs, without requiring a precise system model. The approach taken in this work is based on precursors to instability that are features of the power spectral density of a measured output signal. The noise in the system can be naturally occurring noise or can be intentionally injected noise. The output signal can be measured directly from the physical system or from the system with an augmented monitoring system. Design of appropriate augmented monitoring systems is a major topic of this work. These monitoring systems result in enhancing precursor signals and also allow control of the precursor by tuning external parameters. This tuning is important in that it adds confidence to the detection of an impending instability. The methods developed on precursors for instablility are applied to models of axial flow compression systems. Existing results on bifurcations for such models and their relation to compressor stall provide a starting point for the analysis

Robust nonlinear control of vectored thrust aircraft

An interdisciplinary program in robust control for nonlinear systems with applications to a variety of engineering problems is outlined. Major emphasis will be placed on flight control, with both experimental and analytical studies. This program builds on recent new results in control theory for stability, stabilization, robust stability, robust performance, synthesis, and model reduction in a unified framework using Linear Fractional Transformations (LFT's), Linear Matrix Inequalities (LMI's), and the structured singular value micron. Most of these new advances have been accomplished by the Caltech controls group independently or in collaboration with researchers in other institutions. These recent results offer a new and remarkably unified framework for all aspects of robust control, but what is particularly important for this program is that they also have important implications for system identification and control of nonlinear systems. This combines well with Caltech's expertise in nonlinear control theory, both in geometric methods and methods for systems with constraints and saturations

Aeronautical engineering: A continuing bibliography with indexes (supplement 309)

This bibliography lists 212 reports, articles, and other documents introduced into the NASA scientific and technical information system in Oct. 1994. Subject coverage includes: design, construction and testing of aircraft and aircraft engines; aircraft components, equipment, and systems; ground support systems; and theoretical and applied aspects of aerodynamics and general fluid dynamics

EXPERIMENTAL EVALUATION OF A HIGH-GAIN CONTROL FOR COMPRESSOR SURGE SUPPRESSION

ABSTRACT The present paper considers the suppression of surge instability in compression systems by means of active control strategies based on a high-gain approach. A proper sensor-actuator pair and a proportional controller are selected which, in theory, guarantee system stabilization in any operating condition for a sufficiently high value of the gain. Furthermore, an adaptive control strategy is introduced which allows the system to automatically detect a suitable value of the gain needed for stabilization, without requiring any knowledge of the compressor and plant characteristics. The control device is employed to suppress surge in an industrial compression system based on a fourstage centrifugal blower. An extensive experimental investigation has been performed in order to test the control effectiveness in various operating points on the stalled branch of the compressor characteristic and at different compressor speeds. On one hand the experimental results confirm the good performance of the proposed control strategy, on the other they show some inherent difficulties in stabilizing the system at high compressor speeds due to the measurement disturbances and to the limited operation speed of the actuator. INTRODUCTION Surge instability strongly limits the operating range and the performance of compression systems. As it is known, surge occurs at low compressor flow rates, causing highly undesirable oscillations in the system. By means of a control system it is possible to attenuate or eliminate the phenomenon, so allowing the plant to operate in naturally unstable points. In particular, the active control techniques are based on the use of a suitable sensor/actuator pair in a closed loop control device. The control is effective if the actuation is capable of dissipating the unsteady energy surplus introduced in the system by the compressor when it operates in the stalled region. In the last decade much work has been devoted to the study of active suppression of compressor surge. A large part of the literature i