Improvements in or relating to blades for a gas turbine engine: fabrication of compressor blades and discs

Composites ◽  
1970 ◽  
Vol 1 (6) ◽  
pp. 379-380
Keyword(s):  
Gas Turbine ◽  
Gas Turbine Engine ◽  
Compressor Blades ◽  
Turbine Engine

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 Performance simulation of multi-stage axial-flow compressor of turbo-shaft engine with account for erosive wear nonlinearity of its blades

2020 ◽  
Vol 23 (5) ◽  
pp. 39-53
Author(s):  
V. A. Potapov ◽  
A. A. Sanko
Keyword(s):  
Gas Turbine ◽  
Axial Flow ◽  
Erosive Wear ◽  
Gas Turbine Engine ◽  
Compressor Blades ◽  
Turbine Engine ◽  
Axial Flow Compressor ◽  
Multi Stage ◽  
Rotor Wing ◽  
Flow Compressor

The construction and useful practice of gas-turbine engine diagnosis systems depend largely on the availability of the engine mathematical models and its certain components in their structure. Utilization of multi-stage axial flow compressor performance with account for erosive wear of its parts during the operation fundamentally raises possibilities of such systems as erosive wear of flow channel, blade rings of impellers and vane rings of multi-stage compressor is a common cause of preschedule gas-turbine engine detaching from an aircraft. As evidenced by various contributions presented in the article, special emphasis on abrasive wear impact assessment on axial flow compressor performance is placed upon rotor-wing turbo-shaft engine due to their particular operating conditions. One of the main tasks in the process of mathematic simulation of an axial flow compressor blade ring is consideration of its wear type that again has a nonlinear distribution along the level of the blade. In addition, wear rate at entry and exit blade edges often have different principles. Detecting of these principles and their consideration when constructing the compressor mathematical model is a crucial task in diagnostic assessment and integrity monitoring of rotor-wing turbo-shaft engine in operation. The article represents a concept to an estimate nonlinear erosive wear effect of axial flow compressor blades on its performance based on the three-dimensional flow approach in the gas-air flow duct of compressor with a formulation of the blade rings. This approach renders possible to take into account the nonlinearity of the compressor blades wear during their operation. Through the example of the inlet compressor stage of a rotor-wing aircraft gas-turbine engine, the engine pump properties predictions with different kind of rotor blade wear have been presented.

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
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