Designing Forging and Die Tooling for the Manufacture of Turbine Engine Compressor Blades in Siemens NX

2016 ◽  
Vol 684 ◽  
pp. 497-506 ◽  
Author(s):  
D.S. Goryainov ◽  
V.V. Anokhin ◽  
Aleksey Shlyapugin

For designing forging and die tooling for bulk forging a necessity in using the data of the geometry of the part produced arises. Obviously, the use as a data source for designing drawings of commonly applied in “manual alternate design” (without a computer) especially such complex parts as compressor blades is not perspective because of the complexity of developing theoretical contour specified by a point cloud. In this case the use of special tooling of direct modeling that provides changing the original model of the part developed by the designers is a perspective one. It should be taken into account during the process of forging and die tooling designing that it is necessary to register the special features of the technology, upon that, the technologist should be highly proficient in using the software. The work given describes the designing technique of gas turbine compressor blade with the account of using the potential of NX Siemens program.

2019 ◽  
Vol 18 (1) ◽  
pp. 109-117
Author(s):  
M. B. Sazonov ◽  
L. V. Solovatskaya

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.


2018 ◽  
Vol 769 ◽  
pp. 242-249
Author(s):  
Nikolay Vladimirovich Ruzanov ◽  
Michael Alexandrovich Bolotov ◽  
Vadim Andreevich Pechenin ◽  
Ekaterina Robertovna Matek

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.


2016 ◽  
Vol 685 ◽  
pp. 334-339 ◽  
Author(s):  
Vadim Andreevich Pechenin ◽  
Michael Alexandrovich Bolotov ◽  
N.V. Ruzanov

This paper presents the technique of decomposition of form deviation based on the use of wavelet filter and Fourier transform. The method allows decomposing the total deviation into systematic, random systematic (waviness) and random components. The method testing was carried out for the statistics of the deviation of the suction side of the turbine engine compressor blade. The accuracy check of the estimates of form deviations generated by the method in a series of simulated surfaces with pre-laid characteristics was carried out. The results showed that the method of decomposition allows one to estimate exactly the components of the form deviation of the simulated surfaces in their series.


Author(s):  
Александр Михайлов ◽  
Alexander Mikhailov ◽  
А. Байков ◽  
A. Baykov ◽  
В. Михайлов ◽  
...  

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.


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