五方程多相流與化學反應的數值計算

Simulation of Multiphase and Chemical Reactive Flows Based on Five Equation model

黃于軒(Yu-Hsuan Huang)

指導教授 ： 牛仰堯

淡江大學/工學院/航空太空工程學系碩士班/碩士(2021年)

https://doi.org/10.6846/TKU.2021.00278

摘要

在超音速衝壓引擎模擬中，涉及到多相流與化學反應等複雜的物理現象，為了瞭解這些複雜的物理現象，本文目的在於發展出一套分析超音速衝壓引擎內部流場結構的數值模擬程式。在本研究中，我們首先透過五方程多相流模型與拉格朗日方法，模擬側向噴流問題中震波與液滴霧化蒸發間的交互作用，經比較結果後發現五方程多相流模型相較於單相的Navier-Stokes 方程在震波的捕捉上有較好的解析度。接著結合五方程多相流模型與單步的化學反應模型，模擬不同測試條件下無限長爆震管中胞格結構的形成與發展，並找到合適的單步化學反應模型模擬複雜的化學反應。最後將前兩個算例結合，針對DLR超燃衝壓引擎進行了初步的模擬，模擬結果顯示，在氣態燃料與液態燃料注入燃燒的模擬中，皆顯示了與實驗相似的流場結構。

關鍵字

多相流 ； 噴流 ； 震波 ； 粒子破碎 ； 汽化 ； 爆震波 ； 衝壓引擎

並列摘要

In the simulation of scramjet engines, many complex physical phenomena are involved, such as the fuel atomization, mass transition, and chemical reactions. In order to understand these complex physical phenomena, the purpose of the current thesis is to develop an in-house code for analyzing the flow structures of the scramjet engine. In this study, we first used the five-equation multiphase flow model and the Lagrangian method to reproduce the process of the fuel atomization and evaporation in a flow over side jet problem. Shock waves, recirculation zones and breakup processes of droplet particles were well captured. Comparing the results, we found that the five-equation multiphase model shows a better resolution in the shock capturing, comparing with the single phase Navier-Stokes equations. Then, we combined the five-equation multi-phase model and the single-step reaction model to simulate the formation of the cell structures in the detonation tube. The detonation waves under various operating conditions were discussed based on a single-step reaction model to model the complex reactions. Finally, a preliminary simulation of the DLR scramjet is performed. The current works have achieved satisfactory agreement compared to the experimental data no matter in reacting flow case or non-reacting flow case.

並列關鍵字

multi-phase flow ； side jet ； shock wave ； atomization ； detonation wave ； cellular structure ； scramjet engine

參考文獻

1. Niu, Y.-Y., et al., Development of a less-dissipative hybrid AUSMD scheme for multi-component flow simulations. Shock Waves, 2019. 29(5): p. 691-704.

2. Niu, Y.-Y., et al., Evaluation of breakup models for liquid side jets in supersonic cross flows. Numerical Heat Transfer, Part A: Applications, 2020: p. 1-17.

3. Huang, S.-I. and Y.-Y. Niu, Simulation of flowfields inside a detonation tube in Department of Aerospace Engineering. 2019, Tamkang University: New Taipei City.

4. Wu, S.-C. and Y.-Y. Niu, Numerical analysis performance of multiple pulse detonation tubes, in Department of Aerospace Engineering. 2020, Tamkang University: New Taipei City.

5. Yang, P. and Y.-Y. Niu, A preliminary simulation of two-dimensional high-speed reactive flows, in Department of Aerospace Engineering. 2021, Tamkang University: New Taipei City.