Optimization of blades stagger angles of the three-spool axial compressor to improve of efficiency of the gas turbine engine

2017 ◽  
Author(s):  
Igor Egorov ◽  
Evgeny Marchukov ◽  
Grigorii Popov ◽  
Oleg Baturin ◽  
Evgenii Goriachkin ◽  
...  
Keyword(s):  
Gas Turbine ◽  
Axial Compressor ◽  
Gas Turbine Engine ◽  
Turbine Engine

scholarly journals Optimization of a Multistage Axial Compressor in a Gas Turbine Engine System

1992 ◽  
Author(s):  
I. N. Egorov
Keyword(s):  
Gas Turbine ◽  
Operation Mode ◽  
Axial Compressor ◽  
Gas Turbine Engine ◽  
Point Of View ◽  
Design Parameters ◽  
Turbine Engine ◽  
Non Linear Programming ◽  
Fan Blade ◽  
Multistage Axial Compressor

The work presents a procedure to determine the design parameters of multistage axial compressor (MAC) rows, the parameters optimum from the point of view to assure the best integrated indices of gas turbine engine (GTE) both at the design and off-design operation mode. Effectiveness of the proposed approach has been demonstrated with regards to solving the problems of optimum contouring by the radius of 7 rows of 4-stage fan included in a two-shaft turbofan. For the examples under consideration respective problems of non-linear programming have been set whose dimensionality reached up to 63 of the design parameters of fan blade rows. It is shown, that the requirement to provide the best engine characteristics, integrated matching both GTE component parts (in our case these are compressor blade rows) and integrated characteristics of components included in an engine is of more importance than assuring the highest efficiency of separate components under consideration.

scholarly journals Optimization of a three spool axial compressor to increase the efficiency of a gas turbine engine

2019 ◽  
Vol 604 ◽  
pp. 012048
Author(s):  
Evgenii Marchukov ◽  
Igor Egorov ◽  
Grigorii Popov ◽  
Oleg Baturin ◽  
Evgenii Goriachkin ◽  
...  
Keyword(s):  
Gas Turbine ◽  
Axial Compressor ◽  
Gas Turbine Engine ◽  
Turbine Engine

scholarly journals Adaptive Control of a Gas Turbine Engine for Axial Compressor Faults

1996 ◽  
Author(s):  
G. Lombardo
Keyword(s):  
Adaptive Control ◽  
Control System ◽  
Gas Turbine ◽  
Nonlinear Models ◽  
Axial Compressor ◽  
Gas Turbine Engine ◽  
Adaptive Control System ◽  
Turbine Engine ◽  
Definition Of ◽  
Real Time Optimization

An adaptive control system for a gas turbine engine which diagnoses conditions of axial compressor faults is proposed and analyzed. Nonlinear models of the gas turbine, neural networks and genetic algorithms are used in this research. The adaptive control system minimizes the reduction in gas turbine performance deriving from non-destructive faults. In the absence of faults, the system automatically performs the optimization of the engine between overhauls. Improvements concern the definition of adaptive control with faults in progress, and the real-time optimization of the engine during its operative life between overhauls. Simulation results of the suggested control system are also discussed.

scholarly journals Modelling the characteristics of axial compressor of variable flow passage geometry, working in the gas turbine engine system

2007 ◽  
Vol 14 (3) ◽  
pp. 27-32 ◽  
Author(s):  
Paweł Wirkowski
Keyword(s):  
Gas Turbine ◽  
Gas Turbines ◽  
Axial Compressor ◽  
Gas Turbine Engine ◽  
Dynamic Processes ◽  
Variable Flow ◽  
Flow Passage ◽  
Turbine Engine ◽  
Gas Dynamic ◽  
Engine System

Modelling the characteristics of axial compressor of variable flow passage geometry, working in the gas turbine engine system This paper concerns application of mathematical modelling methods to analyzing gas-dynamic processes in marine gas turbines. Influence of geometry changes in axial compressor flow passage on kinematical air flow characteristics, are presented. The elaborated mathematical model will make it possible to realize - in the future - simulative investigations of gas-dynamic processes taking place in a compressor fitted with controllable guide vanes.

scholarly journals Profitability of the gas-turbine engine with two-row blade wreaths in the axial compressor

2005 ◽  
Vol 26 (4) ◽  
Author(s):  
П.І. Греков ◽  
Л.Г. Волянська ◽  
Курош Хагані ◽  
В.Є. Алпатов
Keyword(s):  
Gas Turbine ◽  
Axial Compressor ◽  
Gas Turbine Engine ◽  
Turbine Engine

scholarly journals ОПРЕДЕЛЕНИЕ ДРОССЕЛЬНОЙ ХАРАКТЕРИСТИКИ ТУРБОВАЛЬНОГО ГТД НА ОСНОВЕ МЕТОДА МАТЕМАТИЧЕСКОГО МОДЕЛИРОВАНИЯ С ИСПОЛЬЗОВАНИЕМ ОДНО- И ДВУМЕРНЫХ ПОДХОДОВ К РАСЧЕТУ ПАРАМЕТРОВ КОМПРЕССОРА

2019 ◽  
pp. 21-30 ◽  
Author(s):  
Людмила Георгиевна Бойко ◽  
Вадим Анатольевич Даценко ◽  
Наталия Владимировна Пижанкова
Keyword(s):  
Experimental Data ◽  
Gas Turbine ◽  
Rotational Speed ◽  
Axial Compressor ◽  
Gas Turbine Engine ◽  
Compressor Blade ◽  
Turbine Engine ◽  
Operation Modes ◽  
Multi Stage ◽  
Wide Range

The results of mathematical modeling processes in the turboshaft gas turbine engine (GTE) are presented. The using calculation method based on a high-level GTE mathematical model, which is founded on a multi-stage axial compressor blade-to-blade description. The model was developed at the Aviation Theory Chair of National Aerospace University “KhAI”. The model is based on a multistage axial compressor thermodynamic parameters calculations using a 1D and 2D approaches to analyzing of the flow. The model named above allows one to take into account air intakes from of the compressor blade gaps, as well as adjusting the angles of installation of the rotary stator vanes depending on the rotational speed. The GTE model has a modular structure. To determine the compressor parameters the modules for 1D or 2D flow calculation can be connected. As the initial data, besides the data traditionally specified in the 1st level GTE models it is necessary to set the geometrical parameters of the compressor flow path and blades on the medium radius (for the 2nd level GTE model) or along with the blade height (for the 3rd level). Both calculating compressor parameters methods are verified and have a fairly wide experience of practical use. The article presents the results of calculating the maps of the GTE multi-stage compressor using one- and two-dimensional approaches. Comparison of the compressor performances achieved by using of these two methods among themselves and with the experimental data has shown their good agreement. The approach used to simulate the flow in compressors makes it possible to estimate, by calculation, the surge margin, to consider the incidence angles and other flow parameters in the blade gaps in a wide range of GTE operation modes. Such results, as well as a comparison with experimental data, are presented in the article. The article also demonstrates the results of applying the described above model to the gas turbine engine performances calculation. The engine has the 12-stage axial compressor with the stator blades position of the first stages regulation. The calculated line of joint operation modes of the gas generator units, the dependence of the power and specific fuel consumption on the rotational speed. Presented are the processes in GTE on stationary modes analyzing results given in the article showed the used model advantage, reliability and expediency of its practical application.

Approximation Method of the Gas Turbine Engine Compressor Characteristics

2021 ◽  
Author(s):  
Sergey Avdeev ◽  
Andrey Tkachenko
Keyword(s):  
Standard Deviation ◽  
Coordinate System ◽  
Gas Turbine ◽  
Approximation Method ◽  
Axial Compressor ◽  
Gas Turbine Engine ◽  
Polar Coordinate System ◽  
Approximation Technique ◽  
Turbine Engine ◽  
Polar Coordinate

Abstract A technique of representing and approximating of gas turbine engine (GTE) compressor maps is given. The aims of this study are to improve the efficiency of processing GTE test results and the reliability of GTE mathematical model. The paper analyzes various approaches of approximating, presenting, and generalizing the characteristics of compressors. The advantages and limitations of the existing compressor maps approximation methods are summarized in the paper. A comparison of the obtained approximating method is carried out against previously developed methods. Based on the performed analysis, a method is proposed for approximating of compressor maps, considering the requirements of identification of the GTE model. The resulting approximation method is based on the use of equations in a polar coordinate system. The study also analyzed the possibility of using the developed method in the system of thermodynamic calculations and analysis “ASTRA” (the program was developed at Samara University). The developed approximation technique was tested on the experimental characteristics of the low- and high-pressure axial compressor. The estimation of the quality of the approximation was carried out using the standard deviation. It has been demonstrated that the obtained approximating functions describe the experimental data quite well. The obtained values of the standard deviation in the polar coordinate system were less than 10%.

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