A new method of digital simulation for an aircraft gas turbine engine control system

Guan, Yan-Shen; Warng, Juhng-Sheng; Lee, Tzu-Cheng

doi:10.1016/0307-904x(87)90171-5

Cited by 6 publications

(5 citation statements)

References 1 publication

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“…Variety of commercial and limited use in-house built software have been employed in the literature for transient modeling and validation of the developed models, i.e., GateCycle [ 40 , 45 ], DESTUR [ 26 ], GETRAN [ 58 , 219 ], TURBOMATCH [ 51 , 220 ], AMESim [ 42 ], Thermoflow [ 7 ], DYNGEN [ 32 , 221 ]. TERTS [ 222 ], TURBOTRANS [ 223 , 224 ], and FORTRAN based programs [ 50 , 51 , 206 , 225 ].…”

Section: Software Tools For Transient Modelingmentioning

confidence: 99%

Transient Behavior in Variable Geometry Industrial Gas Turbines: A Comprehensive Overview of Pertinent Modeling Techniques

Hashmi

Lemma

Ahsan

et al. 2021

Entropy

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Generally, industrial gas turbines (IGT) face transient behavior during start-up, load change, shutdown and variations in ambient conditions. These transient conditions shift engine thermal equilibrium from one steady state to another steady state. In turn, various aero-thermal and mechanical stresses are developed that are adverse for engine’s reliability, availability, and overall health. The transient behavior needs to be accurately predicted since it is highly related to low cycle fatigue and early failures, especially in the hot regions of the gas turbine. In the present paper, several critical aspects related to transient behavior and its modeling are reviewed and studied from the point of view of identifying potential research gaps within the context of fault detection and diagnostics (FDD) under dynamic conditions. Among the considered topics are, (i) general transient regimes and pertinent model formulation techniques, (ii) control mechanism for part-load operation, (iii) developing a database of variable geometry inlet guide vanes (VIGVs) and variable bleed valves (VBVs) schedules along with selection framework, and (iv) data compilation of shaft’s polar moment of inertia for different types of engine’s configurations. This comprehensive literature document, considering all the aspects of transient behavior and its associated modeling techniques will serve as an anchor point for the future researchers, gas turbine operators and design engineers for effective prognostics, FDD and predictive condition monitoring for variable geometry IGT.

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Section: Software Tools For Transient Modelingmentioning

confidence: 99%

Transient Behavior in Variable Geometry Industrial Gas Turbines: A Comprehensive Overview of Pertinent Modeling Techniques

Hashmi

Lemma

Ahsan

et al. 2021

Entropy

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“…The nonlinear mathematical model of the turbofan engine was established by a component method. The basic idea of engine modeling is Walsh and Fletcher (2004), Mattingly et al (2002), Fan (2008), Lian and Wu (2005), Yunus and Boles (2016), Wang and Yang (2004), Fred (1977), Guan et al (1987), Bhargava and Lakshmanan (1993), Zhang (1992), Sellers and Daniele (1975), Johnson (1990): Known characteristics of each part of the engine, from the inlet of the engine inlet to the outlet of the tail nozzle, gradually establish the gas flow equation and the thermodynamic process equation based on the principles of thermodynamics and aerodynamics; according to the relationship between engine flow balance, pressure balance, power balance, etc. The simultaneous equations of the engine’s joint work are obtained and the nonlinear dynamic and static equilibrium equations are jointly solved to obtain the relevant parameter values of the relevant sections and operating states of the engine.…”

Section: Construction Of Aero-engine and Fixed-wing Uav Modelsmentioning

confidence: 99%

Based on minimum fuel consumption mode integrated optimal control of fixed-wing UAV flight propulsion system

Han

Zhang

et al. 2021

AEAT

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Purpose In this paper, with the goal of reducing the fuel consumption of UAV, the engine performance optimization is studied and on the basis of aircraft/engine integrated control, the minimum fuel consumption optimization method of engine given thrust is proposed. In the case of keeping the given thrust of the engine unchanged, the main fuel flow of the engine without being connected to the afterburner is optimally controlled so as to minimize the fuel consumption. Design/methodology/approach In this study, the reference model real-time optimization control method is adopted. The engine reference model uses a nonlinear real-time mathematical model of a certain engine component method. The quasi-Newton method is adopted in the optimization algorithm. According to the optimization variable nozzle area, the turbine drop-pressure ratio corresponding to the optimized nozzle area is calculated, which is superimposed with the difference of the drop-pressure ratio of the conventional control plan and output to the conventional nozzle controller of the engine. The nozzle area is controlled by the conventional nozzle controller. Findings The engine real-time minimum fuel consumption optimization control method studied in this study can significantly reduce the engine fuel consumption rate under a given thrust. At the work point, this is a low-altitude large Mach work point, which is relatively close to the edge of the flight envelope. Before turning on the optimization controller, the fuel consumption is 0.8124 kg/s. After turning on the optimization controller, you can see that the fuel supply has decreased by about 4%. At this time, the speed of the high-pressure rotor is about 94% and the temperature after the turbine can remain stable all the time. Practical implications The optimal control method of minimum fuel consumption for the given thrust of UAV is proposed in this paper and the optimal control is carried out for the nozzle area of the engine. At the same time, a method is proposed to indirectly control the nozzle area by changing the turbine pressure ratio. The relevant UAV and its power plant designers and developers may consider the results of this study to reach a feasible solution to reduce the fuel consumption of UAV. Originality/value Fuel consumption optimization can save fuel consumption during aircraft cruising, increase the economy of commercial aircraft and improve the combat radius of military aircraft. With the increasingly wide application of UAVs in military and civilian fields, the demand for energy-saving and emission reduction will promote the UAV industry to improve the awareness of environmental protection and reduce the cost of UAV use and operation.

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“…By investigating the results authors claimed that this new method can be utilized for modeling and simulation of different types of gas turbine engines. 124…”

Section: A Historical Review Of Gas Turbine Engine Controlmentioning

confidence: 99%

“…By investigating the results authors claimed that this new method can be utilized for modeling and simulation of different types of gas turbine engines. 124 The authors proposed two samples of engine modeling. The first one shown with its figure is block diagram modeling and the second one is the suggested modeling, called ''method of spare parts.''…”

Section: A Historical Review Of Gas Turbine Engine Controlmentioning

confidence: 99%

A scientometric analysis and critical review of gas turbine aero-engines control: From Whittle engine to more-electric propulsion

Mohammadi

Fashandi

Jafari

et al. 2020

Measurement and Control

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The gas turbine aero-engine control systems over the past eight decades have been thoroughly investigated. This review purposes are to present a comprehensive reference for aero-engine control design and development based on a systematic scientometric analysis and to categorize different methods, algorithms, and approaches taken into account to improve the performance and operability of aircraft engines from the first days to present to enable this challenging technology to be adopted by aero-engine manufacturers. Initially, the benefits of the control systems are restated in terms of improved engine efficiency, reduced carbon dioxide emissions, and improved fuel economy. This is followed by a historical coverage of the proposed concepts dating back to 1936. A comprehensive scientometric analysis is then presented to introduce the main milestones in aero-engines control. Possible control strategies and concepts are classified into four distinct phases, including Single input- single output control algorithms, MIN-MAX or Cascade control algorithms, advanced control algorithms, More-electric and electronic control algorithms and critically reviewed. The advantages and disadvantages of milestones are discussed to cover all practical aspects of the review to enable the researchers to identify the current challenges in aircraft engine control systems.

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A new method of digital simulation for an aircraft gas turbine engine control system

Cited by 6 publications

References 1 publication

Transient Behavior in Variable Geometry Industrial Gas Turbines: A Comprehensive Overview of Pertinent Modeling Techniques

Transient Behavior in Variable Geometry Industrial Gas Turbines: A Comprehensive Overview of Pertinent Modeling Techniques

Based on minimum fuel consumption mode integrated optimal control of fixed-wing UAV flight propulsion system

A scientometric analysis and critical review of gas turbine aero-engines control: From Whittle engine to more-electric propulsion

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