A study of the influence of service operating time and a corrosive medium on the life of gas-turbine engine compressor blades

1981 ◽  
Vol 13 (4) ◽  
pp. 401-407 ◽  
Author(s):  
V. T. Troshchenko ◽  
A. V. Prokopenko ◽  
V. N. Torgov ◽  
M. V. Baumshtein ◽  
L. B. Getsov
Keyword(s):  
Gas Turbine ◽  
Corrosive Medium ◽  
Operating Time ◽  
Gas Turbine Engine ◽  
Compressor Blades ◽  
Turbine Engine ◽  
Engine Compressor

Development of a Touch Probing System for Gaging the Compressor Blades of the GTE

2018 ◽  
Vol 769 ◽  
pp. 242-249
Author(s):  
Nikolay Vladimirovich Ruzanov ◽  
Michael Alexandrovich Bolotov ◽  
Vadim Andreevich Pechenin ◽  
Ekaterina Robertovna Matek
Keyword(s):  
Mathematical Models ◽  
Gas Turbine ◽  
Strain Gage ◽  
Simulation Modeling ◽  
Gas Turbine Engine ◽  
Compressor Blades ◽  
Reference Element ◽  
Turbine Engine ◽  
Optimum Configuration ◽  
Engine Compressor

The article describes the touch probing system with the strain gage as the main measuring element. The device has small geometric dimensions and it was developed to measure the gas turbine engine compressor blades. To select the optimum configuration of the probing system, mathematical models of two principal configurations were developed. Simulation modeling of the force of the measured surface impact on the measuring tip was carried out in the Ansys environment for these assemblies. On the basis of practical experiments, the diagram of the deviation of the probe on the resistance of the strain gage was constructed. Reference element were measured to determine the accuracy of the designed touch probing system.

scholarly journals Influence of the stressed state of the surface layer on the endurance of gas turbine engine compressor blades

2019 ◽  
Vol 18 (1) ◽  
pp. 109-117
Author(s):  
M. B. Sazonov ◽  
L. V. Solovatskaya
Keyword(s):  
Residual Stress ◽  
Stressed State ◽  
Gas Turbine ◽  
Gas Turbine Engine ◽  
Graphical Analysis ◽  
Compressor Blade ◽  
Compressor Blades ◽  
Turbine Engine ◽  
Compressive Stresses ◽  
Engine Compressor

Different types of final strengthening treatment of gas turbine engine (GTD) compressor blades are considered. The influence of each type of treatment on the formation of roughness of the surface with favorable microrelief, as well as on the level and depth of distribution of residual compressive stresses in the compressor blade airfoil is analyzed. The causes of blade fatigue failure are described and methods of controlling this kind of failure are presented. The results of testing special specimens made of VT9 titanic alloy are presented to establish the influence of final strengthening treatment modes on the compressor blade resistance to fatigue stress. The results of testing residual stress distribution along the thickness of compressor blade airfoil are presented. A method of improving dynamic strengthening of specimens due to the protection of compressor blade edges is discussed. The results of semi-graphical analysis of the stressed state of low-pressure and medium-pressure compressor blades made of VT9 alloy are presented. They take into account residual stresses, as well as operating load stresses in the process of operation. We show that it is possible to increase the limit of the blade endurance due to the optimization of residual stress diagrams by improving the final strengthening technology with the use of dust blasting.

scholarly journals Dependence of thermogasodynamic parameters of operation of a helicopter gas turbine engine on its operation and dust in the atmosphere

2021 ◽  
Vol 66 (3) ◽  
pp. 307-319
Author(s):  
V. A. Potapov ◽  
A. A. Sanko ◽  
M. V. Kudin
Keyword(s):  
Gas Turbine ◽  
Stokes Equations ◽  
Block Diagram ◽  
Operating Time ◽  
Erosive Wear ◽  
Gas Turbine Engine ◽  
Operating Conditions ◽  
Compressor Blades ◽  
Turbine Engine ◽  
Gas Turbine Compressor

By scanning the blades of the impeller and the guide devices of the full-scale compressor of the helicopter gas turbine engine, a solid-state design model of the compressor with a tunable geometry in the height of the blades was developed. The empirical dependencies of the values of nonlinear wear of the blade of the 1st stage of the compressor on the operating time and the concentration of dust in the air are presented. A block diagram of the procedure for calculating the characteristics and parameters of a helicopter gas turbine compressor is presented. When calculating the flow in the gas–air path of the compressor, the numerical solution of the Navier–Stokes equations averaged by Reynolds, the finite element method in combination with the establishment of patterns of erosive wear of the blades depending on the operating conditions of the engine is used. Mathematical dependencies of the thermogasodynamic parameters of the helicopter gas turbine compressor operation on its operating time and the dustiness of the atmosphere are obtained using modeling. The obtained results can be used in the development of a methodology for automated monitoring of the wear condition of the compressor blades of a helicopter gas turbine engine according to its thermogasodynamic parameters, applied to various climatic operating conditions.

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