scholarly journals POSSIBILITIES OF APPLICATION OF THE METHODOLOGY FOR DETERMINING RATINGS OF A GAS TURBINE ENGINE TO IMPROVETHE QUALITY OF EQUIPMENT DIAGNOSTIC

2018 ◽  
pp. 83-87
Author(s):  
A. I. Mikhaylenko
Keyword(s):  
Gas Turbine ◽  
Gas Turbine Engine ◽  
Oil Field ◽  
Design Parameters ◽  
Flow Section ◽  
Turbine Engine ◽  
Current State ◽  
Entire Flow ◽  
Methodological Approaches

The article deals with theoretical and methodological approaches and practical approaches to improve the quality of gas turbine engine diagnostics. The author presents the main results of development of the calculating method for additional ratings in the entire flow section of the gas turbine engine GTE-6,3/MS which is used by LLC «RN-Uvatneftegaz» at the Tyamkinskoye oil field of Uvat district of Tyumen region. The conclusion is drawn that an expanded series of design parameters of a gas turbine engine makes it possible to improve the quality, reliability and depth of diagnostics of both the current state of equipment and after major overhaul.

Design and Analysis of a High Pressure Turbine Using Computational Methods for Small Gas Turbine Application

2013 ◽  
Author(s):  
Kishor Kumar ◽  
R. Prathapanayaka ◽  
S. V. Ramana Murthy ◽  
S. Kishore Kumar ◽  
T. M. Ajay Krishna
Keyword(s):  
High Pressure ◽  
Gas Turbine ◽  
Computational Methods ◽  
Gas Turbine Engine ◽  
Flow Coefficient ◽  
Design Parameters ◽  
Convergence Criterion ◽  
Turbine Engine ◽  
Design Point ◽  
Ansys Cfx

This paper describes the aerodynamic design and analysis of a high-pressure, single-stage axial flow turbine suitable for small gas turbine engine application using computational methods. The specifications of turbine were based on the need of a typical high-pressure compressor and geometric restrictions of small gas turbine engine. Baseline design parameters such as flow coefficient, stage loading coefficient are close to 0.23 and 1.22 respectively with maximum flow expansion in the NGV rows. In the preliminary design mode, the meanline approach is used to generate the turbine flow path and the design point performance is achieved by considering three blade sections at hub, mean and tip using the AMDC+KO+MK+BSM loss models to meet the design constraints. An average exit swirl angle of less than 5 degrees is achieved leading to minimum losses in the stage. Also, NGV and rotor blade numbers were chosen based on the optimum blade solidity. Blade profile is redesigned using the results from blade-to-blade analysis and through-flow analysis based on an enhanced Dawes BTOB3D flow solver. Using PbCFD (Pushbutton CFD) and commercially available CFD software ANSYS-CFX, aero-thermodynamic parameters like pressure ratios, aerodynamic power, and efficiencies are computed and these results are compared with one another. The boundary conditions, convergence criterion, and turbulence model used in CFD computations are set uniform for comparison with 8 per cent turbulence intensity. Grid independence study is performed at design point to optimize the grid density for off-design performance predictions. ANSYS-CFX and PbCFD have predicted higher efficiency of 3.4% and 1.2% respectively with respect to targeted efficiency of 89 per cent.

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 Assessment of Mechanical Design Parameters for an Aero Gas Turbine Engine Jet Pipe Casing using Finite Element Analysis

2020 ◽  
Vol 9 (5) ◽  
pp. 1197-1201
Keyword(s):  
Finite Element Analysis ◽  
Finite Element ◽  
Gas Turbine ◽  
Mechanical Design ◽  
Three Dimensional ◽  
Gas Turbine Engine ◽  
Design Parameters ◽  
Element Analysis ◽  
Engine Operation ◽  
Turbine Engine

Aero Gas Turbine engines power aircrafts for civil transport application as well as for military fighter jets. Jet pipe casing assembly is one of the critical components of such an Aero Gas Turbine engine. The objective of the casing is to carry out the required aerodynamic performance with a simultaneous structural performance. The Jet pipe casing assembly located in the rear end of the engine would, in case of fighter jet, consist of an After Burner also called as reheater which is used for thrust augmentation to meet the critical additional thrust requirement as demanded by the combat environment in the war field. The combustion volume for the After burner operation together with the aerodynamic conditions in terms of pressure, temperature and optimum air velocity is provided by the Jet pipe casing. While meeting the aerodynamic requirements, the casing is also expected to meet the structural requirements. The casing carries a Convergent-Divergent Nozzle in the downstream side (at the rear end) and in the upstream side the casing is attached with a rear mount ring which is an interface between engine and the airframe. The mechanical design parameters involving Strength reserve factors, Fatigue Life, Natural Frequencies along with buckling strength margins are assessed while the Jet pipe casing delivers the aerodynamic outputs during the engine operation. A three dimensional non linear Finite Element analysis of the Jet pipe casing assembly is carried out, considering the up & down stream aerodynamics together with the mechanical boundary conditions in order to assess the Mechanical design parameters.

Technological Trend of Aircraft Gas Turbines and its Effect on the Development for Ship Propulsion Plants

1970 ◽  
Author(s):  
N. K. H. Scholz
Keyword(s):  
Gas Turbine ◽  
Gas Turbines ◽  
Pressure Ratio ◽  
Gas Turbine Engine ◽  
Design Parameters ◽  
Turbine Engines ◽  
Gas Turbine Engines ◽  
Compression Pressure ◽  
Turbine Engine ◽  
Ship Propulsion

The effect of the main design parameters of the aero gas turbine engine cycle, namely combustion temperature and compression pressure ratio, on the specific performance values is discussed. The resulting development trend has been of essential influence on the technology. Relevant approaches are outlined. The efforts relating to weight and manufacturing expense are also indicated. In the design of aero gas turbine engines increasing consideration is given to the specific flight mission requirements, such as for instance by the introduction of the by-pass principle. Therefore direct application of aero gas turbine engines for ship propulsion without considerable modifications, as has been practiced in the past, is not considered very promising for the future. Nevertheless, there are possibilities to take advantage of aero gas turbine engine developments for ship propulsion systems. Appropriate approaches are discussed. With the experience obtained from aero gas turbine engines that will enter service in the early seventies it should be possible to develop marine gas turbine engines achieving consumptions and lifes that are competitive with those of advanced diesel units.

Optimization of Gas Turbine Engine Elements by Probability Criteria

1993 ◽  
Author(s):  
I. N. Egorov ◽  
G. V. Kretinin
Keyword(s):  
Stochastic Optimization ◽  
Gas Turbine ◽  
Axial Flow ◽  
Gas Turbine Engine ◽  
Design Parameters ◽  
Technical Object ◽  
Turbine Engine ◽  
Flow Compressor ◽  
Engine Components ◽  
Stochastic Setting

Procedure for the stochastic optimization of design parameters of gas turbine engine components for a prescribed level of production technology is discussed. Such combined criteria of the stochastic optimization as effectiveness-probability of realizing a design of an intricate technical object are proposed. With reference to the task of optimum designing the rows of a multistage axial flow compressor, there are presented the results, obtained for various probability criteria, in parallel with conducting their comparative analysis, and there are also investigated optimum stable (robust) characteristics of designs obtained for various levels of technology. There are also demonstrated a possibility of a significant increase in probability to realize in actual practice the design, obtained in stochastic setting, as compared to the design, obtained in deterministic setting.

scholarly journals АВТОМАТИЗАЦІЯ ВИПРОБУВАНЬ ЕЛЕКТРОННИХ РЕГУЛЯТОРОВ ГТД

2018 ◽  
pp. 108-112
Author(s):  
Дмитрий Сергеевич Бурунов ◽  
Андрей Олегович Таранишин
Keyword(s):  
Gas Turbine ◽  
Production Management ◽  
Human Factor ◽  
Gas Turbine Engine ◽  
Testing Time ◽  
Market Demand ◽  
Labor Costs ◽  
Turbine Engine ◽  
The Impact

To ensure the required reliability of electronic regulators, a complex of tests is required, consisting of metrological studies and testing of the operation of control and monitoring algorithms. Metrological studies and calibration are carried out using standard and specialized measuring equipment. To test the control and monitoring algorithms a specialized gas turbine engine simulator with a built-in mathematical model is required. In addition, control and verification equipment and specialized software are needed. The increasing production rates caused by the large market demand in these regulators and the need to ensure reliability lead to a significant increase in labor costs and the time required for testing, which is especially important in batch production. One of the options for reducing labor costs and improving the quality of test scores is the automation of this process. Automation - the highest stage in the development of technology, which is characterized by the implementation of production management and other socially necessary processes without direct participation in them. Increasing the degree of automation of the enterprise leads to an increase in the stability of the technological process, reducing the impact of the human factor, improving the transparency of production, which ultimately positively affects the quality of finished products. The use of automation of the testing process excludes the influence of the human factor, allows for more extensive testing of the operation of the control and monitoring algorithms. When testing time is shortened, the quality and reliability indicators of Element electronic regulators produced by Element JSC are improved. As a result, the estimated effort required to test the operation of the algorithms of one electronic regulator will be reduced by 4-5 times. The main problems in testing modern electronic gas turbine engine (GTE) regulators are described. The possibility of test automation in the mass manufacturing of gas turbine regulators by the example of the electronic regulators of an engine of a family RDTs-450M. Future direction of testing development of had detected.

ABRASIVE WEAR-RESISTANT SEAL MATERIALS OF THE GAS TURBINE ENGINE FLOW SECTION

2019 ◽  
pp. 67-74
Author(s):  
D.P. Farafonov ◽  
◽  
N.E. Leshchev ◽  
A.N. Afanasiev-Khodykin ◽  
N.I. Artemenko ◽  
...  
Keyword(s):  
Abrasive Wear ◽  
Gas Turbine ◽  
Gas Turbine Engine ◽  
Flow Section ◽  
Wear Resistant ◽  
Turbine Engine
Sign in / Sign up

Export Citation Format

Share Document