Моделирование течения в двухрядных лопаточных венцах
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Дата
2015
ORCID
DOI
Науковий ступінь
Рівень дисертації
Шифр та назва спеціальності
Рада захисту
Установа захисту
Науковий керівник
Члени комітету
Видавець
НТУ "ХПИ"
Анотація
В работе рассмотрена тестовая задача моделирования течения в двухрядном лопаточном венце. представлены результаты численного моделирования течения в двухрядных лопаточных венцах осевого компрессора, точность расчета параметров расчета оценена с помощью верификации данных численного и известного физического эксперимента. Результаты расчета показали, что использование модели турбулентности SST Ментера, мелкой адаптивной нерегулярной расчетной сетки дает погрешность 5–7 %.
Aerodynamic improvement of compressor blade system is one of the ways to solve common problems of increasing the efficiency of transport and stationary gas turbine engine compressor ventilation systems. One of the factors reducing the efficiency of gas turbine engines for off-design conditions and the efficiency of the compressor, and the occurrence of rotating stall and surge is a stall in the blade rings of cascades. One of the most important tasks of improving the aerodynamic blade machines is preventing stall of blade rings and reducing losses. Application of energy methods to influence the flow in the wall layers is prevent or localize stall. One of the energetic methods is the use of tandem cascades. The aim is to examine the test problem of modeling the flow in tandem cascades. The solution of this prob lem is necessary to assess the accuracy of the numerical simulation compared with experimental results. The tandem cascades redistribute the energy in the inter-blade channels between the different areas of flow. The results of numerical modeling of flow in the tandem cascades of axial compressor are presented in the article. Comparing the results of numerical modeling and physical experimentation showed that the calculation error is between 5 and 7 %. Thus, the decision of test problem showed that the simulation of flow in tandem cascades can be used SST Menter turbulence model and small irregular adaptive meshes.
Aerodynamic improvement of compressor blade system is one of the ways to solve common problems of increasing the efficiency of transport and stationary gas turbine engine compressor ventilation systems. One of the factors reducing the efficiency of gas turbine engines for off-design conditions and the efficiency of the compressor, and the occurrence of rotating stall and surge is a stall in the blade rings of cascades. One of the most important tasks of improving the aerodynamic blade machines is preventing stall of blade rings and reducing losses. Application of energy methods to influence the flow in the wall layers is prevent or localize stall. One of the energetic methods is the use of tandem cascades. The aim is to examine the test problem of modeling the flow in tandem cascades. The solution of this prob lem is necessary to assess the accuracy of the numerical simulation compared with experimental results. The tandem cascades redistribute the energy in the inter-blade channels between the different areas of flow. The results of numerical modeling of flow in the tandem cascades of axial compressor are presented in the article. Comparing the results of numerical modeling and physical experimentation showed that the calculation error is between 5 and 7 %. Thus, the decision of test problem showed that the simulation of flow in tandem cascades can be used SST Menter turbulence model and small irregular adaptive meshes.
Опис
Ключові слова
двухрядная решетка, угол атаки, пограничный слой, компрессор, вязкость, сжимаемость, срыв, double-row grille, angle of attack, boundary layer, compressor, viscosity, compressibility, stall
Бібліографічний опис
Терещенко Ю. М. Моделирование течения в двухрядных лопаточных венцах / Ю. М. Терещенко, Е. В. Дорошенко, Д. Аболхассанзаде // Вестник Нац. техн. ун-та "ХПИ" : сб. науч. тр. Темат. вып. : Механико-технологические системы и комплексы. – Харьков : НТУ "ХПИ". – 2015. – № 22 (1131). – С. 75-77.