Numerical study of flow in the stage of an axial compressor with different topology of computational grid

Tereshchenko, Yuriy; Дорошенко, Екатерина Викторовна; Lastivka, Ivan

doi:10.15587/1729-4061.2017.101315

Cited by 2 publications

(1 citation statement)

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“…Автори роблять висновок, що для моделювання течії в лопаткових вінцях найбільш підходить модель турбулентності SST, яка більш точно описує течію як в ядрі потоку, так і в пограничному шарі. В роботі [6] при виборі моделі турбулентності для моделювання течії в осьовому компресорі автори зупиняють свій вибір також на моделі SST.…”

Section: вступunclassified

Вибір І Обґрунтування Методу Генерації Сітки Для Моделювання Течії У Вентиляторі Газотурбінного Двигуна

Хижняк¹,

Дорошенко²,

Усенко³

2020

aktt

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The study of flow in aircraft gas turbine engines is one of the main components for the creation of new compressors and fans with improved aerodynamic, acoustic, strength, overall weight, and other characteristics. In modern scientific research, the methods of the physical experiment are used at the final stages of flow studies in blade machines. a numerical experiment is used in the early stages. An obvious advantage of the numerical experiment is the ability to study many variants of constructions under different input and boundary conditions in a short period. However, a numerical experiment requires a preliminary selection and justification of its parameters and components. One such important component is the type of calculation mesh. The literature review shows that it is impossible to make an unambiguous conclusion about the choice of the type of method for generating the finite element mesh and the turbulence model. This work aims to compare a hybrid and structured mesh for flow modeling in an axial fan of a bypass engine with a high bypass ratio. Two impellers of a bypass engine with a high bypass ratio are selected as the object of study. Flow simulation in fans was studied at a rotor speed of 2202 rpm in the range of values of the gas-dynamic flow function at the inlet q (λ) = 0.4 ... 0.65. Based on the literature review, the system of Navier-Stokes equations was closed by the SST turbulent model. To select and substantiate the method of finite-element grid generation, a structured and hybrid mesh for two fan variants were constructed. According to the results of the calculations, the dependence of the pressure ratio of fan π on the gas-dynamic flow function at the inlet q (λ) was constructed. According to the results of the study, it can be stated that the discrepancy of the calculations for the impellers in the axial fan of a bypass engine with a high bypass ratio with structured and hybrid meshes will be up to 2 %. When choosing the method of mesh generation, the time of calculation is also an important factor. Studies have shown that the calculation with a structured mesh took place in less time by 50 ... 70% than when using a hybrid mesh for one variant of the geometry.

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Section: вступunclassified