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Now showing items 1 - 16 of 36

  • Bond graph modeling of a jet engine with electric starter

    Montazeri-Gh, Morteza   Fashandi, Seyed Alireza Miran  

    Following the technological advances in recent decades, advanced electronic systems linked to the gas turbine industry are increasingly considered by the designers of this field. For this purpose, new airborne systems in conjunction with jet engines are developed, which are incorporated in many challenging design problems such as control law and configuration design. Thus, a comprehensive modeling structure is needed that can bolster the integrity of the system development such as the bond graph approach, which is known as an efficient method for modeling complicated mechatronic systems. In this paper, modeling and simulation of a jet engine dynamic performance and aircraft motion are achieved based on the bond graph approach. At first, the electric starter bond graph model is constructed and physical relationships governing each engine component are obtained. In the aftermath, the modulated energy fields are developed for the jet engine components. Subsequently, the bond graph model of the engine is numerically simulated and experimentally tested and verified for a small jet engine. Finally, bond graph modeling and simulation of integrated engine and aircraft system is presented. The test results indicate the acceptable accuracy of the modeling approach which can be applied for innovative diagnosis and control systems design.
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  • Real-time simulation of a turbo-shaft engine's electronic control unit

    Montazeri-Gh, Morteza   Abyaneh, Soroush  

    Hardware-in-the-loop (HIL) simulation is a comprehensive and repeatable manner for system-level testing of any control system. One of the first steps in an HIL simulation is to execute a preliminary real-time test where all parts of the control system are modeled numerically on separate personal computers (PC). In this paper, a real-time simulation of such preliminary real-time test has been conducted for an electronic control unit (ECU) of a gas turbine engine. The plant of the control system is a gas turbine model for a two-shaft turbo-shaft engine, loaded on an industrial personal computer. The turbine's controller is actually another computer on which ECU's software model is generated via software as well. ECU acts as a controller for the gas turbine and it ensures the operational reliability by limiting the angular speed, angular acceleration of the engine's shafts and other parameters within their allowable working range. Signal interactions between control system parts are created via data acquisition cards. Different gas turbine load functions are fed as inputs to the engine model and results are compared to those of a same control system, modeled completely on an individual PC in real time. The latter is otherwise known as software-in-the-loop (SIL) simulation. The results show the acceptable functionality of the test setup.
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  • Theoretical and Experimental Study of a Micro Jet Engine Start-Up Behaviour

    Montazeri-Gh, Morteza   Fashandi, Seyed Alireza Miran   Jafari, Soheil  

    Proper functioning of the start-up process in a micro jet engine is of great importance. This is due to the fact that the combustion chamber of such engine is so small and therefore, there is little time for fuel and air mixture to be present in the chamber. Hence, failed starts or repetitive attempts by the electric starter are very likely due to non-formation of the initial combustion. Also, the performance of the turbine start-up, impressively affects the limited life time of the micro jet engine. In this paper, an experimental study on the injection of compressed air during the start-up of a micro jet engine to improve its performance has been conducted. For this purpose, test components' layout and a monitoring system are designed. The allowable pressure of the air injection has been calculated using both the engine dynamic model and experimental tests. The simulation results have also been compared and validated with the experimental test results. Finally, several tests were conducted to study the injection process of the compressed air form which, several results have been deduced including the reduction of maximum exhaust gas temperature (EGT) during the start-up, reduction of the start-up time interval and service lifetime enhancement. The method proposed in this paper is applicable on any micro jet engine with the similar structural form and starting process.
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  • Real-time simulation of a turbo-shaft engine\"s electronic control unit

    Montazeri-Gh, Morteza   Abyaneh, Soroush  

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  • Near-Optimal SOC Trajectory for Traffic-Based Adaptive PHEV Control Strategy

    Montazeri-Gh, Morteza   Pourbafarani, Zeinab  

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  • Application of Bond Graph approach in dynamic modelling of industrial gas turbine

    Montazeri-Gh, Morteza   Fashandi, Seyed Alireza Miran  

    Nowadays, gas turbines play a significant role in industry and power generation units. Therefore, any increase in their performance efficiency, is designers' major concern. Power generation system's principal considerations are performance, weight and reliability. Gas turbine engine is considered as a probable choice for such applications. This research develops and validates a Bond Graph model based on flow of energy and information of a gas turbine engine. Here, modelling of the gas turbine engine is achieved based on the pseudo Bond Graph approach. Subsequently, by coupling the Bond-Graph component models, a unified framework for model representation is presented. Also, to study the effect of changing external load on turbine's performance, an industrial two-shaft gas turbine is simulated under large transient loads based on the previously developed component models. Finally, the commercial gas turbine simulation program (GSP) is used to validate the simulation results. Transient response simulations indicate an acceptable error between the GSP and Bond Graph model outputs.
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  • Application of Bond Graph approach in dynamic modelling of industrial gas turbine

    Montazeri-Gh, Morteza   Fashandi, Seyed Alireza Miran  

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  • Improvement of Min-Max limit protection in aircraft engine control:An LMI approach

    Imani, Amin   Montazeri-Gh, Morteza  

    Current aircraft engine control logic employs a Min-Max selector structure. This structure must provide desired thrust and prevent the engine from exceeding any safety or operational limits. Careful analysis shows that there is no assurance for traditional Min-Max algorithm with linear compensators to protect output limits in transient regime, while limit violation can cause serious damages and even lead to loss of engine. In this paper, according to analysis outcomes, a strategy is presented to design linear regulators of Min-Max selector control to improve transient limit protection. For this objective, the isolated limitation loops are designed overshoot/undershoot-free to reduce the possibility of limit violation during activeness of the individual limit regulator. Despite the success of this approach, it is observed that some outputs influenced by engine acceleration or deceleration exceed their limits when other loop regulators are active. To overcome this problem, the limit values of these outputs are considered in controller design process of other loops using state feedback method and a set of linear matrix inequalities (LMIs). Simulation results show that the proposed approach effectively decreases the possibility of transient limit violation and can improve Min-Max limit protection in aircraft engine control. (C) 2017 Elsevier Masson SAS. All rights reserved.
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  • Active Fault Tolerant Control with self-enrichment capability for gas turbine engines

    Mohammadi, Ehsan   Montazeri-Gh, Morteza  

    In this paper, an Active Fault Tolerant Control (AFTC) system with self-enrichment capability is proposed to deal with both the anticipated and unanticipated gas-path performance deteriorations in the industrial gas turbine engines. For this purpose, a hybrid fault diagnosis system with self-enrichment capability is proposed to take advantage of the positive features of fuzzy-based and global optimization-based Fault Detection and Identification (FDI) methods. The proposed FDI system provides the possibility of dealing with the unanticipated or unknown deteriorations. In order to design the proposed AFTC system, the parameters of the control system are optimized for a set of predefined deteriorations and through this a bank of control system parameters is created for the anticipated health conditions. The proposed FDI system verifies whether the detected health condition is an anticipated condition or not. In the case of the anticipated deteriorations, the proposed AFTC system selects the controller parameters from the bank of control system parameters, according to the current health condition; while in the case of the unanticipated deteriorations, the controller parameters will be determined through the optimization process. By adding the new set of optimized parameters to the bank of control system parameters, the database of the proposed AFTC system will gradually enrich to cope with a broader range of the engine deteriorations. The results obtained in the present work reveal that, the proposed AFTC system can preserve the engine safety and operational constraints; in the case of some deteriorations at the expense of a drop in the availability (due to a necessary trip or load shedding) and in some other cases even without losing the engine availability (by avoiding any unnecessary trip or load shedding). This is while, according to the results obtained, in the case of some health conditions, employing the controller designed for clean condition may cause the turbine over-temperature, loss of surge margin, and also a drop in the availability. (C) 2016 Elsevier Masson SAS. All rights reserved.
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  • Development a new power management strategy for power split hybrid electric vehicles

    Montazeri-Gh, Morteza   Mahmoodi-k, Mehdi  

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  • A Multi-loop Switching Controller for Aircraft Gas Turbine Engine with Stability Proof

    Imani, Amin   Montazeri-Gh, Morteza  

    In this paper, a Min-Max switching controller containing multiple state feedback regulators and fuel flow rate saturation is designed for a high bypass two-spool turbofan engine. Due to the switching nature of Min-Max algorithm and the presence of saturation function, stability analysis is an important issue in the process of controller design. Therefore, a methodology is presented to analyze the stability of the closed loop system. For this objective, the Min and Max selectors and the saturation block are replaced by their nonlinear equivalents and the structure of the control system is transformed into the canonical configuration of Lure's system. Then, the condition for absolute stability is extracted using the Multivariable Circle Criterion. An asymptotic stability proof is achieved for the closed loop system and the performance of the designed multiregulator Min-Max controller in tracking a desired fan speed scenario and limit management is compared with the well-known Min-Max/SMC technique.
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  • Performance Enhancement of Global Optimization-Based Gas Turbine Fault Diagnosis Systems

    Mohammadi, Ehsan   Montazeri-Gh, Morteza  

    Fault detection and identification of gas turbines is a crucial process for providing engine safe operation and decreasing the maintenance costs. In studies conducted in the field of global optimization-based gas turbine fault diagnosis, the genetic algorithm as the most well-known evolutionary optimization algorithm is usually employed to identify the engine health parameters. However, because of the evolutionary and stochastic nature of this algorithm, the genetic-algorithm-based diagnosis usually suffers from computational burden and reliability. To mitigate this problem, in the present work, a comparative study has been performed on the global optimization-based gas turbine fault diagnosis, and it is shown that an innovative hybrid optimization algorithm as a fault detection and identification system can significantly enhance the performance of the conventional optimization-based diagnosis systems, even in the presence of measurement noise. The results obtained indicate that the fault detection and identification system based on the hybrid invasive weed optimization/particle swarm optimization algorithm outperforms all the examined diagnosis systems (i.e., the genetic-algorithm-based, particle-swarm-optimization-based, and invasive weed-optimization-based fault detection and identification system) in terms of accuracy, reliability, and especially computational cost. The results demonstrate that the genetic-algorithm-based fault detection and identification system showed the weakest performance among all the examined diagnosis systems.
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  • A Min-Max multiregulator system with stability analysis for aeroengine propulsion control

    Imani, Amin   Montazeri-Gh, Morteza  

    Stability analysis is an essential issue in Min-Max multiregulator control strategy for commercial aircraft engines. In this paper, a Min-Max selector scheme along with a stability analysis method is provided for aeroengine propulsion control. It is assumed that the main regulator is a dynamic compensator and the limit regulators are constant gains. The regulators are determined in such a way that the individual control loops are stable. However, due to the switching nature of Min-Max structure, the stability of single loops does not necessarily ensure the overall system stability. In order to analyze the stability of the presented Min-Max approach, the architecture of the control system is transformed into the canonical form of Lure's system and the condition for absolute stability is specified using Multivariable Circle Criterion. The theoretical results can also be applied to investigate the stability of min-only or max-only schemes. Afterwards, using the provided methodology, the global asymptotic stability is proved for the control system of a high bypass two-spool turbofan engine and the performance of the designed Min-Max controller in tracking a desired fan speed and limit protection in fault-free and fault tolerant situations is compared with the well-known Min-Max/SMC approach. (C) 2018 ISA. Published by Elsevier Ltd. All rights reserved.
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  • Design and HIL-based verification of the fuel control unit for a gas turbine engine

    Salehi, Amin   Montazeri-Gh, Morteza  

    The correct operation of a gas turbine engine depends on the accurate and stable performance of fuel control system and its components such as fuel control unit. Fuel control unit is an electro-hydraulic actuator of fuel control system whose function is to supply, regulate and send the fuel to the engine according to the electronic control unit command. In this paper, a new fuel control unit has been developed based on the load sensing concept for a turboshaft gas turbine engine. In the designed fuel control unit, the fuel flow rate is controlled by adjusting the fuel pressure. A NARX model and ANFIS controller is employed to design the pressure controller. A hardware in the loop framework, comprising of hydraulic circuit, sensors, data acquisition card and computers, is developed to evaluate the performance of the fuel control unit alongside the real-time simulation of other component such as engine and electronic control unit. Moreover, the consumed power by the fuel control unit is evaluated and a considerable improvement is indicated compared to typical fuel control units.
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  • Analyzing different numerical linearization methods for the dynamic model of a turbofan engine

    Montazeri-Gh, Morteza   Rasti, Ali  

    State equations of aircraft engine dynamics usually required for controller design, are not available in closed form, so the dynamic models are commonly linearized numerically. Development of model-based controllers for aeroengine in the recent years necessitates the use of accurate linear models. However, there is no comprehensive study about the accuracy of the linear models obtained from nonlinear engine models. In this paper, the accuracy of different numerical linearization methods for linearizing the dynamic model of a turbofan engine is investigated. For this objective, a thermodynamic model of a two-spool turbofan engine is considered and three various numerical linearization methods are defined. The first method is based on the perturbation technique, including ordinary and central difference perturbation. The second one is a system identification method and the third one is tuning the elements of the matrices of the linear state-space model using genetic algorithm. The accuracy analysis of the presented procedures is performed for both single-input and double-input cases. In the single-input case, the fuel mass flow rate and in the double-input, in addition to the fuel, the bleed air taken from between the two compressors are considered as control variables. Finally, by defining different error criterions, the accuracy of the linearization methods is evaluated. The results show that the linear model obtained from system identification and central difference perturbation methods have higher percentage of compliances compared to the others.
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  • ERROR EVALUATION OF HARDWARE-IN-THE-LOOP SIMULATION OF A GAS TURBINE ENGINE FUEL CONTROLLER

    Montazeri-Gh, Morteza   Abyaneh, Soroush  

    Correct implementation of a fuel control algorithm for a gas turbine engine (GTE) in an electronic control unit (ECU) is one of the basic challenges in the development of a GTE fuel control system. A common measure in such implementation is the error of the hardware-in-the-loop (HIL) simulation test. In this paper, evaluation and diminution of the hardware-in-the-loop test error for a gas turbine engine fuel controller is presented. For this purpose, a fuel controller has been designed for a power generating gas turbine engine. The designed controller was then implemented in the PC104 hardware and tested in an HIL simulation. The test results were then evaluated in order to study the controller functionality. In this study, a procedure is proposed for evaluating the implementation of the fuel control algorithm in PC104 and diminishing the HIL simulation errors. Finally, it is shown that the proposed approach to decreasing the HIL simulation error is effective.
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