Abstract
The problem of gas turbine engines inhomogeneous rotor blades stress-strain state has been studied. For this purpose, the new, more correct mathematical model, based on the special three-dimensional curvilinear finite elements has been used. Such elements have three modifications, applied for the blade feather and its transition zones correct modeling. The complex influence of vibration and heat loads on the blade feather has also been taken into consideration. The values of maximum dynamic stresses and their localization zones have also been found. The main concentrators of stresses are located in the transfer zones between the cooling channels and blade feather surfaces. The blade output edge is another zone of maximum dynamic stresses localization. It has also been found that the influence of the geometric parameters of cooling channels in the blade feather cavity on the value of maximum dynamic stresses is sharper than the influence of cooling holes on the blade output edge. By comparing the obtained calculated results with the experimental data, we can state the high adequacy and reliability of the developed mathematical model. All calculations and experimental procedures were held by equal boundary conditions. The results of the research can be used as a base for further studying of the whole rotor stress-strain state and processes of blades fatigue destruction.
Highlights
For the purpose of marine gas turbine engines trouble-free operations, we need to study vibration processes, which influence sharply reduces the durability of the whole turbine
Special attention should be paid to the turbine rotor blades, heavily loaded by the non-stationary gas flow
Wherе Те – matrix of the blade material temperature within the finite element e; Т0е – matrix of the gas flow temperature, contacting with the surface of the finite element е; Ве – mat rix of gradients for the finite element e; D – elasticity matrix. Usage of this mathematical model gives us an opportunity to calculate the field of dynamic stresses on the turbine blade feather surface for any mode of the blade’s oscillation, because application of the dependences (9)–(13) gives an opportunity to take into consideration any k-th harmonic of the vibration load
Summary
Nowadays one of the main trends in the power machine building area is a steady increase of turbine engines power. The main aim of the work is to research an influence of the turbine blades feather constructional non-homogeneity on the stress-strain state, caused by the complex effect of vibration and thermal loads. Wherе Те – matrix of the blade material temperature within the finite element e; Т0е – matrix of the gas flow temperature, contacting with the surface of the finite element е; Ве – mat rix of gradients for the finite element e; D – elasticity matrix Usage of this mathematical model gives us an opportunity to calculate the field of dynamic stresses on the turbine blade feather surface for any mode of the blade’s oscillation, because application of the dependences (9)–(13) gives an opportunity to take into consideration any k-th harmonic of the vibration load
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