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.

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 Life complex increase of all groups of compressor blades of a turbo-shaft gas turbine engine on the basis of a functionally-directed approach

2017 ◽  
Vol 2 (9) ◽  
pp. 42-48 ◽  
Author(s):  
Александр Михайлов ◽  
Alexander Mikhailov ◽  
А. Байков ◽  
A. Baykov ◽  
В. Михайлов ◽  
...  
Keyword(s):  
Gas Turbine ◽  
Gas Turbine Engine ◽  
Compressor Blade ◽  
Erosion Wear ◽  
Compressor Blades ◽  
Turbine Engine ◽  
Complex Increase

The analysis of peculiarities in compressor blade operation of the turbo-shaft gas turbine engine is carried out. At the same time the compressor blade structuring into groups is carried and it is shown that structural groups of blades operate under different conditions of operation. It is defined, that different structural groups of compressor blades have their own definite peculiarities of operation and erosion wear. It is shown, that the erosion wear of all groups of compressor blades may be characterized by irregularities of three kinds. In the paper a general approach to life increase of all groups of compressor blades in a helicopter gas turbine engine is offered.

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

Enhanced Experimental Testing of New Erosion-Resistant Compressor Blade Coatings

2016 ◽  
Vol 138 (11) ◽  
Author(s):  
Sean G. Leithead ◽  
William D. E. Allan ◽  
Linruo Zhao ◽  
Qi Yang
Keyword(s):  
Gas Turbine ◽  
Physical Vapor Deposition ◽  
Experimental Testing ◽  
National Research Council ◽  
Gas Turbine Engine ◽  
Compressor Blade ◽  
Operating Conditions ◽  
Compressor Blades ◽  
Turbine Engine ◽  
Better Than

Performance differences between bare 17-4PH steel V103 profile (NACA 6505 with rounded leading edge (LE) and trailing edge (TE)) gas turbine engine axial compressor blades, and those coated with either a chromium-aluminum-titanium nitride (CrAlTiN) or a titanium-aluminum nitride (TixAl1−xN) erosion-resistant coating were tested. A coating thickness of 16 μm was used, based on experimental results in the literature. Coatings were applied using arc physical vapor deposition at the National Research Council of Canada (NRC). All blades were tested under identical operating conditions in the Royal Military College of Canada (RMC) turbomachinery erosion rig. Based on a realism factor (RF) defined by the authors, this experimental rig was determined to provide the best known approximation to actual compressor blade erosion in aircraft gas turbine engine axial compressors. An average brown-out erosive media concentration of 4.9 g/m3 of air was used during testing. An overall defined Leithead–Allan–Zhao (LAZ) score metric, based on mass and blade dimension changes, compared the erosion-resistant performance of the bare and coated blades. Blade surface roughness data were also obtained. Based on the LAZ Score, CrAlTiN-coated blades performed at least 79% better than bare blades, and TixAl1−xN-coated blades performed at least 93% better than bare blades. The TixAl1−xN-coated blades performed at least 33% better than the CrAlTiN-coated blades. Extrapolation of results predicted that a V-22 Osprey tiltrotor military aircraft, for example, could fly up to 79 more missions with TixAl1−xN-coated compressor blades in brown-out sand concentrations than with uncoated blades.

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