scholarly journals Expert Systems for the Simulation of Gas Turbine Engines

1992 ◽  
Author(s):  
G. Torella
Keyword(s):  
Expert Systems ◽  
Fault Simulation ◽  
Knowledge Bases ◽  
Turbine Engines ◽  
Full Detail ◽  
Gas Turbine Engines ◽  
Control Laws ◽  
Engine Simulation ◽  
Operating Limits ◽  
Set Up

The paper deals with the possibility to develop effective Expert Systems for the simulation, the monitoring and the diagnostics of engines. The work concerns with the development of suitable Knowledge Bases and Expert Systems for different activities. The approach to the problem deals with Expert Systems for engine simulation. These Systems give the operating limits of the engine and the required control laws for reaching assigned values of performance. Other Expert Systems have been developed for fault simulation. The matrices of influence have proved to be suitable for constructing effective Knowledge Bases. Finally Expert Systems for engine diagnostics have been set-up. The paper shows in full detail the methods, the techniques and several applications of the developed codes.

Application of neural network expert systems for monitoring, diagnostics and forecasting of technical condition of aircraft engines

2020 ◽  
pp. 51-59
Author(s):  
Д.О. Пушкарёв
Keyword(s):  
Neural Network ◽  
Expert Systems ◽  
Gas Turbine ◽  
Technical Condition ◽  
Turbine Engines ◽  
Gas Turbine Engines ◽  
Fuzzy Interference System ◽  
Interference System ◽  
Monitoring And Diagnostics ◽  
Technical Operation

Рассматривается применение нейросетевых экспертных систем в области контроля, диагностики и прогнозирования технического состояния авиационных ГТД на основе нечеткой логики. Показана методика для решения таких задач в области технической эксплуатации авиационной техники совместно с использованием фаззи-интерференсной системы программы MATLAB. Используя статистические данные о работе двигателя формируется экспертная система на основе нейронной сети позволяющая осуществлять контроль и диагностику ГТД, а также прогнозировать дальнейшее техническое состояния анализируемого двигателя. The application of neural network expert systems in the field of monitoring, diagnostics and forecasting of the technical condition of aviation gas turbine engines based on fuzzy logic is considered. The technique for solving such problems in the field of technical operation of aircraft and using the fuzzy-interference system of the MATLAB program is shown. Using statistical data on the operation of the engine, an expert system is based on the fundamental of a neural network that provide monitoring and diagnostics of gas turbine engines, as well as predicting the further technical condition of the analyzed engine.

scholarly journals The Methodology of Stochastic Optimization of Parameters and Control Laws for the Aircraft Gas-Turbine Engines Flow Passage Components

1999 ◽  
Author(s):  
I. N. Egorov ◽  
G. V. Kretinin ◽  
S. S. Kostiuk ◽  
I. A. Leshchenko ◽  
U. I. Babi
Keyword(s):  
Stochastic Optimization ◽  
Gas Turbine ◽  
Stochastic Approach ◽  
Turbine Engines ◽  
Problem Solution ◽  
Gas Turbine Engines ◽  
Control Laws ◽  
Flow Passage ◽  
Optimum Solution ◽  
And Control

This paper presents the main theses of stochastic approach to the multimeasure parameters and control laws optimization for the aircraft gas-turbine engines. The methodology allows us to optimize the engines taking into account the technological deflections which inevitably take place in the process of manufacturing of the engine’s components as well as engine’s control deflections. The stochastic optimization is able to find highly robust solutions, stable to inaccuracies in technological processes. The effectiveness of the methodology is shown by example of optimization problem solution to find the control laws for the flow passage controllable elements of the 4-th generation aircraft mixed-flow turbofan engine. The use of information about the existing and advanced production technology levels during the optimization process, including some components manufacturing accuracy, allows us to considerably increase the probability of optimum solution implementation in practice. In real engine there are some components manufacturing deflections as well as control accuracy deflections. It results a certain engine’s performance deviation. An engine optimization classic deterministic approach can not take into account this circumstance, so the probability of an optimum design implementation is too low.

Multicriteria Optimization of Time Control Laws of Short Take-Off and Vertical Landing Aircraft Power Plant

1997 ◽  
Author(s):  
I. N. Egorov ◽  
G. V. Kretinin ◽  
I. A. Leshchenko
Keyword(s):  
Power Plant ◽  
Multicriteria Optimization ◽  
Complex Structure ◽  
Turbine Engines ◽  
Gas Turbine Engines ◽  
Control Laws ◽  
Time Control ◽  
Process Adaptation ◽  
Optimization Methodology ◽  
Vertical Landing

A multicriteria optimization methodology has been discussed to determine time control laws of advanced aircraft gas turbine engines of complex structure. The resulting optimum control laws ensure top improvement of several defined power plant effectiveness criteria in the system of aircraft at transient work modes. The power plant work quality increase effect is attained due to its work process adaptation for numerous requirements from the side of the aircraft. The proposed methodology effectiveness has been shown by the example of optimizing problem solving to determine time control laws of variable elements of short take-off and vertical landing aircraft power plant.

scholarly journals Study on the Influence of Air Bleeds on the Behaviour and on the Performance of Gas Turbine Engines

1991 ◽  
Author(s):  
Giovanni Torella
Keyword(s):  
Gas Turbine ◽  
Fault Simulation ◽  
Engine Performance ◽  
Thermodynamic Characteristics ◽  
Computer Programs ◽  
Turbine Engines ◽  
Gas Turbine Engines ◽  
Design Codes ◽  
Design Point ◽  
Air System

The influence of air system an engine performance and behaviour is considered. A method based on the polytropic efficiency concept has been developed in order to calculate the thermodynamic characteristics of air bleed. This method has been included in the “Design Point” and “Off Design” codes of different configuration engines. The paper shows the wide applications of the programs for several calculations. Moreover the results of the faults of air system are shown by both diagnostic and fault simulation computer programs.

Performance Deterioration Modeling in Aircraft Gas Turbine Engines

1998 ◽  
Vol 120 (2) ◽  
pp. 344-349 ◽  
Author(s):  
A. V. Zaita ◽  
G. Buley ◽  
G. Karlsons
Keyword(s):  
Gas Turbine ◽  
Gas Turbines ◽  
Operating Time ◽  
Performance Model ◽  
Turbine Engines ◽  
Gas Turbine Engines ◽  
Engine Simulation ◽  
Performance Deterioration ◽  
Data Correlations ◽  
Design Characteristics

Steady-state performance models can be used to evaluate a new engine’s baseline performance. As a gas turbine accumulates operating time in the field, its performance deteriorates due to fouling, erosion, and wear. This paper presents the development of a model for predicting the performance deterioration of aircraft gas turbines. The model accounts for rotating component deterioration based on the aircraft mission profiles and environmental conditions and the engine’s physical and design characteristics. The methodology uses data correlations combined with a stage stacking technique for the compressor and a tip rub model, along with data correlations for the turbine to determine the amount of performance deterioration. The performance deterioration model interfaces with the manufacturer’s baseline engine simulation model in order to create a deteriorated performance model for that engine.

scholarly journals Distinctive Features of Altitude-velocity Characteristics of Detonation Gas Turbine Engines

2018 ◽  
Vol 220 ◽  
pp. 03008
Author(s):  
Andrey Tkachenko ◽  
Viktor Rybakov ◽  
Evgeny Filinov
Keyword(s):  
Mathematical Model ◽  
Gas Turbine ◽  
Three Dimensional ◽  
Turbine Engines ◽  
Gas Turbine Engines ◽  
Gas Generator ◽  
Control Laws ◽  
Turbine Engine ◽  
Distinctive Features ◽  
Detonation Engine

The paper describes the distinctive features of the altitude-velocity characteristics of detonation gas turbine engines. The necessity of developing a new type of gas turbine engines is substantiated and the main features of detonation engines are described. The principal constructive scheme of detonation gas turbine engines is presented. Developed the one-dimensional mathematical model of detonation gas turbine engine. This model describes a working process in a gas generator and a traction module. Its verification with a real prototype is performed. A number of studies were carried out using the developed mathematical model. A comparison of the pulsating engine with the classic afterburner was performed. From the obtained results it is concluded that detonation engines are more economical than the engines of traditional schemes. It was also revealed that it is possible to obtain a range of flight speeds depending on a certain height only by adjusting the gas generator according to different control laws. In this regard, the purpose of further work will be the development of a three-dimensional mathematical model of the detonation engine and the creation on its basis of a stand of virtual tests for further research.

Neural Networks for the Diagnostics of Gas Turbine Engines

1996 ◽  
Author(s):  
G. Torella ◽  
G. Lombardo
Keyword(s):  
Neural Networks ◽  
Gas Turbine ◽  
Back Propagation ◽  
Learning Rate ◽  
Turbine Engines ◽  
Gas Turbine Engines ◽  
Turbine Engine ◽  
Classical Architecture ◽  
Set Up ◽  
The One

The paper describes the activities carried out for developing and testing Back Propagation Neural Networks (BPNN) for the gas turbine engine diagnostics. One of the aims of this study was to analyze the problems encountered during training using large number of patterns. Each pattern contains information about the engine thermodynamic behaviour when there is a fault in progress. Moreover the research studied different architectures of BPNN for testing their capability to recognize patterns even when information is noised. The results showed that it is possible to set-up and optimize suitable and robust Neural Networks useful for gas turbine diagnostics. The methods of Gas Path Analysis furnish the necessary data and information about engine behaviour. The best architecture, among the ones studied, is formed by 13, 26 and 47 neurons in the input, hidden and output layer respectively. The investigated Nets have shown that the best encoding of faults is the one using a unitary diagonal matrix. Moreover the calculation have identified suitable laws of learning rate factor (LRF) for improving the learning rate. Finally the authors used two different computers. The first one has a classical architecture (sequential, vectorial and parallel). The second one is the Neural Computer, SYNAPSE-1, developed by Siemens.

Multi-disciplinary simulation of propeller-turboprop aircraft flight

2012 ◽  
Vol 116 (1184) ◽  
pp. 985-1014 ◽  
Author(s):  
A. Filippone ◽  
Z. Mohamed-Kassim
Keyword(s):  
System Integration ◽  
Flight Mechanics ◽  
Noise Model ◽  
Turbine Engines ◽  
Gas Turbine Engines ◽  
Component Level ◽  
Engine Simulation ◽  
Aircraft Flight ◽  
Turboprop Engine ◽  
Semi Empirical

Abstract This contribution presents a novel simulation for a fixed-wing aircraft powered by gas turbine engines and advanced propellers (turboprops). The work is part of a large framework for the simulation of aircraft flight through a multi-disciplinary approach. Novel numerical methods are presented for flight mechanics, turboprop engine simulation (in direct and inverse mode), and propeller dynamics. We present in detail the integration of the propeller with the airframe, aircraft and tonal noise model. At the basic level, we address a shortfall in multi-disciplinary integration in turboprop-powered aircraft, including economical operations and environmental emissions (exhausts and noise). The models introduced are based on first principles, supplied with semi-empirical correlations, if required. Validation strategies are presented for component-level analysis and system integration. Results are presented for aerodynamics, specific air range, optimal cruise conditions, payload-range performance, and propeller noise. Selected results are shown for the ATR 72-500, powered by PW127M turboprop engines and F568-1 propellers.

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