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 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.

Design Considerations for Nuclear-Aircraft Gas-Turbine Engines

1959 ◽  
Author(s):  
D. R. Riley
Keyword(s):  
Power Plant ◽  
Gas Turbine ◽  
Turbine Engines ◽  
Gas Turbine Engines ◽  
Radiation Level ◽  
Design Considerations ◽  
Nuclear Heating

Many new design considerations are encountered in the design of nuclear aircraft gas-turbine engines. The effect that the power-plant configurations, the cycle, radiation level, residual radiation, and nuclear heating have on the design is discussed in this paper.

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.

Marine steam-gas semi-closed cycle power plant for peak loads

2021 ◽  
Vol 2 ◽  
pp. 21-25
Author(s):  
Vladimir Baranovsky ◽  
Maxim Lipatov
Keyword(s):  
Diesel Engine ◽  
Power Plant ◽  
Power Plants ◽  
High Efficiency ◽  
Turbine Engines ◽  
Gas Turbine Engines ◽  
Closed Cycle ◽  
Peak Loads ◽  
Wide Range ◽  
Gas Power Plant

A wide range of efficient gas turbine engines has been developed at UEC NPO Saturn, Russia. Those engines can be successfully used for developing a marine steam-gas semi-closed cycle power plant to compensate peak loads on ships and vessels. This compact steam-gas power plant will demonstrate high efficiency which doesn’t change significantly depending on the load when compared to conventional steam-gas power plants. Also, this solution can possibly change the diesel engine prevalence among marine power plants.

Ship Gas Turbine Engine With the Intermediate Gas Reheating Before the Power Overexpansion Turbine

2012 ◽  
Author(s):  
O. Andriets ◽  
V. Matviienko ◽  
V. Ocheretianyi
Keyword(s):  
Power Plant ◽  
Gas Turbine ◽  
Specific Power ◽  
Turbine Engines ◽  
Gas Turbine Engines ◽  
Turbine Engine ◽  
Exhaust Gases ◽  
Power Turbine ◽  
Operating Regimes ◽  
Additional Fuel

Gas-turbine engines (GTE) posses a number of technical merits and they are widely used in the structure of ship propulsion complexes. However, if GTE is used as a ship cruise engine it is necessary to increase efficiency with the goal to be competitive to diesels. Increasing of the simple cycle GTE efficiency is possible due to the overexpansion turbine employment, where the internal energy of exhaust gases is used. That allows to obtain, deducting energy expenses on exhaust gases pressing, the additional useful work without the additional fuel expenses. Power overexpansion turbine employment leads to raising of power plant heaviness, that’s why it is desirable to increase engine power when its weight is constant. Insertion of the intermediate gas reheating before power turbine in the thermal scheme of GTE with the power overexpansion turbine considerably increases GTE’s specific power. GTE with the intermediate gas reheating before the power overexpansion turbine have greater specific power and they are more economic than simple cycle’s GTE on a large spectrum of ship’s power plant operating regimes. GTE with intermediate gas reheating before the power overexpansion turbine have stable efficiency on operating regimes, that’s why it is preferable to employ them for hydrofoil ships.

An Evaluation of the Effect of Ambient Conditions on the Integration of Inlet Conditioning Systems With Industrial Gas Turbine Engines

2003 ◽  
Author(s):  
Janel N. Nixon ◽  
Mark Waters ◽  
Dimitri Mavris
Keyword(s):  
Power Plant ◽  
Power Systems ◽  
Gas Turbine ◽  
Robust Design ◽  
Operating Conditions ◽  
Turbine Engines ◽  
Gas Turbine Engines ◽  
Ambient Conditions ◽  
Temperature And Humidity ◽  
Industrial Gas Turbine

All industrial power systems are influenced by ambient parameters, and power plant output fluctuates significantly with changes in ambient conditions such as pressure, temperature, and humidity. The use of an inlet conditioning system is frequently proposed to lower the temperatures at the inlet of an industrial gas turbine engine, particularly in hot and arid regions. To evaluate such a system, a robust design methodology has been developed whereby ambient operating conditions and their impacts can be modeled easily and accurately. Ambient models are developed that are specific to a given locale and consider daily and annual variations in temperature and humidity. A robust design is one that has a high probability of meeting design goals, and at the same time, is insensitive to operational uncertainty. This paper addresses the possibility of enhancing the robustness of gas turbine engines by means of technology additions. The results of this study have been developed in part using the probabilistic analysis techniques developed at the Aerospace System Design Laboratory at Georgia Tech, and they demonstrate how differing ambient conditions can affect the decision to install an inlet conditioning system with the engine [1]. An industrial gas turbine power plant is modeled, and the ambient models are integrated with the engine model and used to predict the overall impact on power plant net revenue over a year-long period of operation. This is done at four specified locales each with widely different ambient characteristics.

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.

scholarly journals OPERATION OF ELECTRIC HEAT-GENERATION GAS TURBINE PLANTS OF COMPLEX CYCLES ON NOMINAL AND VARIABLE MODES

2021 ◽  
Vol 2 (37(64)) ◽  
pp. 17-22
Author(s):  
V. Matveenko ◽  
A. Dologlonyan ◽  
A. Klimenko ◽  
V. Ocheretianyi
Keyword(s):  
Power Plant ◽  
Gas Turbine ◽  
Turbine Engines ◽  
Gas Turbine Engines ◽  
Working Process ◽  
Turbine Engine ◽  
Energy Flows ◽  
Heat Regeneration ◽  
Electric Heat ◽  
Partial Loads

The results of research and development of cogeneration gas turbine engines (GTE) of complex cycles are presented. It is shown that the use of an overexpansion turbine (OT) in a gas turbine engine makes it possible to increase the efficiency of the engine on a par with the use of heat regeneration (R). The combination of these two methods in a GTE with OT and R provides a further increase in the engine's efficiency. It has been established that at partial loads, each design scheme has its own patterns of change in engine characteristics, which determine the field of application of cogeneration gas turbine engines. Examples of the possibilities of changing the working process in the engine are given, which allow to control the energy flows in the cogeneration power plant.

Integration of Control and Fuel System Components Today and Tomorrow

1969 ◽  
Author(s):  
L. J. Moulton
Keyword(s):  
Control Systems ◽  
Gas Turbine ◽  
Turbine Engines ◽  
Gas Turbine Engines ◽  
Fuel System ◽  
New Techniques ◽  
Additional Weight ◽  
Time Control ◽  
System Components ◽  
Improved Performance

New gas turbine engines, because of their requirements for improved performance at lower weights, are placing additional requirements on the control and fuel system. At the same time control and fuel system must weigh less. Integration of certain control and fuel system components is one approach which has allowed some of these seemingly conflicting requirements to be met. While future control systems may be able to achieve some additional weight savings by additional integration, further use of new techniques particularly those in electronic and pneumatic computational components seem areas to be explored if step reductions in control weight and volume are to be attained.

Sign in / Sign up

Export Citation Format

Share Document