Life Enhancement of a Gas Turbine Engine by Temperature Control

Prakash, R.; Rao, Shodhan; Skarvan, Charles A.

doi:10.1515/tjj.1990.7.3-4.187

Cited by 7 publications

(7 citation statements)

References 3 publications

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“…[15][16][17][18] Some other papers have also tended to the extraction of linear models via simplification of thermodynamic equations. 19,20 The methods based on model identification have been utilized as well-known methods for the purpose of generating dynamic models of the gas turbine, and are classified as linear and nonlinear methods. Many of the studies conducted the field have been based on nonlinear methods and noticeable papers have been published in the field of identification based on NARX and NARMAX, [21][22][23][24][25] artificial neural networks, 26,27 fuzzy, 28,29 liner-nonlinear block structure methods (Wiener), [30][31][32] Hammerstein, 33,34 Wiener-Hammerstein, [35][36][37][38] etc.…”

Section: Introductionmentioning

confidence: 99%

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Linear Transfer Functions Extraction for a Power Generation Three-Shaft Gas Turbine Based on Actual Specifications

Mehrpanahi

Payganeh

Arbabtafti

2020

Proceedings of the Institution of Mechanical Engineers, Part C:

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The design and testing of various types of controllers require accurate and reliable transfer functions that are compatible with the performance condition of the system. In this paper, the linear and the nonlinear methods have been utilized for extracting the transfer functions for a three-shaft industrial gas turbine. The main variables are the fuel input and environment temperature, while the main outputs are the LPT exhaust gas temperature and the generated power. According to the nonlinear structure of the system and the input variation intervals, the quasi-amplitude-modulated pseudo random binary sequence signals have been utilized for generating input parameters. Finally, the results extracted from the selected methods were compared to the outputs of real performance data under loading and unloading conditions. Based on the comparison between the accuracies obtained by the results, the auto-regressive moving average with eXogenous, try and error transfer function and linearized Hammerstein model methods are proposed, respectively. The outcome of using the controller indicated higher compatibility from transfer functions as compared to the reference dynamic model.

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Section: Introductionmentioning

confidence: 99%

“…15–18 Some other papers have also tended to the extraction of linear models via simplification of thermodynamic equations. 19,20…”

Section: Introductionmentioning

confidence: 99%

Linear Transfer Functions Extraction for a Power Generation Three-Shaft Gas Turbine Based on Actual Specifications

Mehrpanahi

Payganeh

Arbabtafti

2020

Proceedings of the Institution of Mechanical Engineers, Part C:

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“…Some of these factors are related to the engine construction processes while others depend on the engine performance and how it is being controlled [1]. EGT during the start-up is a key parameter which represents the thermal stress on the engine and the combustion chamber overall operability condition.…”

Section: Introductionmentioning

confidence: 99%

Theoretical and Experimental Study of a Micro Jet Engine Start-Up Behaviour

2018

Teh. vjesn.

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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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“…The first one is linearization, however, due to the local nature of linearization techniques, the model such obtained is only valid within a vicinity of certain operating point (usually within 3-5% of engine shaft speed), and this explains the reason that gain scheduling has been universally adopted in aircraft engine control system design, with the most recent development called linear parameter varying control [19][20][21]. While gain scheduling control has long been a standard practice [22] (particularly for civil aircraft engine controls), its performance may deteriorate seriously during controller switching, and this leads to the development of linear parameter varying (LPV) control to obtain "smooth" transition of controller switching. This LPV approach to MBD of transient control has been extensively investigated in SNECMA [23][24][25][26][27][28] and the following challenges have been identified: 1) the LPV model of turbofan engines is difficult to obtain; 2) control design is relatively difficult to perform due to the non-convexity of LMI; 3 ) t h e o r d e r o f r e s u l t i n g controllers is relatively high.…”

Section: Introductionmentioning

confidence: 99%

Model-based Acceleration Control of Turbofan Engines with a Hammerstein-Wiener Representation

Wang

et al. 2017

International Journal of Turbo &Amp; Jet-Engines

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This version is available at https://strathprints.strath.ac.uk/55823/ Strathprints is designed to allow users to access the research output of the University of Strathclyde. Unless otherwise explicitly stated on the manuscript, Copyright © and Moral Rights for the papers on this site are retained by the individual authors and/or other copyright owners. Please check the manuscript for details of any other licences that may have been applied. You may not engage in further distribution of the material for any profitmaking activities or any commercial gain. You may freely distribute both the url (https://strathprints.strath.ac.uk/) and the content of this paper for research or private study, educational, or not-for-profit purposes without prior permission or charge.Any correspondence concerning this service should be sent to the Abstract: Acceleration control of turbofan engines is conventionally designed through either schedule-based or acceleration-based approach. With the widespread acceptance of model-based design in aviation industry, it becomes necessary to investigate the issues associated with model-based design for acceleration control. In this paper, the challenges for implementing model-based acceleration control are explained; a novel Hammerstein-Wiener representation of engine models is introduced; based on the Hammerstein-Wiener model, a nonlinear generalized minimum variance type of optimal control law is derived; the feature of the proposed approach is that it does not require the inversion operation that usually upsets those nonlinear control techniques. The effectiveness of the proposed control design method is validated through a detailed numerical study.

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Life Enhancement of a Gas Turbine Engine by Temperature Control

Cited by 7 publications

References 3 publications

Linear Transfer Functions Extraction for a Power Generation Three-Shaft Gas Turbine Based on Actual Specifications

Linear Transfer Functions Extraction for a Power Generation Three-Shaft Gas Turbine Based on Actual Specifications

Theoretical and Experimental Study of a Micro Jet Engine Start-Up Behaviour

Model-based Acceleration Control of Turbofan Engines with a Hammerstein-Wiener Representation

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