穿音速轉子葉串流場於不同紊流模式下之數值研究

The Investigation of Transonic Rotor Cascades Flowfield Using Different Turbulence Models

10.6124/TAASRC.200003_32(1).03

苗志銘(Jr-Ming Miao)；戴昌賢(Chang-Hsien Tai)；徐子圭(Uzu-Kuei Hsu)；吳振源(Zhen-Yuan Wu)

穿音速轉子 ； 分離包 ； CFD ； 模流模式 ； Transonic Rotors ； Separation Bubble ； CFD ； Turbulent Models

中國航空太空學會學刊

32卷1期（2000 / 03 / 01）

33 - 40

繁體中文

本研究主要使用計算流體力學之方法，探討燃氣渦輪機渦輪葉片串列間之複雜流場現象。然葉片表面流場邊界層內之流場特性大部特爲紊流，且層紊流轉性現象(transition)對渦輪葉片的熱傳設計有決定性的影響，因此本文以四種不同之紊流模式，且以VKI-CT2穿音速渦輪葉片爲測試模型來做探討，測試參數爲入口角度，分別爲15、30、45，以及紊流強度爲3%、6%、9%。本文所採用之數學模式爲三維依時性之雷諾均值Navier-Stokes方程組；爲適用於各式葉片流場計算，採用在物理空間中逕行離散之有限體積法(Finite-Volume Method)。同時方程式中另加入不同之紊流模式的（如B-L､κ-ε､R-k-ε､RNG κ-ε），用以模擬氣流流經渦輪葉片間所產生複雜現象。研究成果顯示，葉片表面之分離、渦流現象以及震波發生位置均可充分加以掌握。

In this study, a three-dimensional Navior-Stokes analyzer based on control volume method is developed to simulate the complex flow field within a turbomachinery. With VKI-CT2 turbine blade as the test model, numerical results are compared experimented data and shows the existence of separation-transition bubble and the interaction of shock with turbulent boundary layer flow. The governing Navier-Stokes equation are solved by an improved numerical method that uses an upwind flux-difference split scheme for spatial descretization and an explicit optimally smoothing multistage scheme for time integration. Turbulent stresses are approximated by modify Baldwin-Lomax algebra､κ-ε､R-k-ε and RNG κ-ε turbulence models. The test parameters are the inlet angle which are15, 30, 45 and the turbulent intensity which are 3%, 6%, 9%. According to the results of this research, this analyzer can indeed effectively modulate and simulate the aerodynamic characteristic of the transonic turbine rotor