聯管試驗設備之衝壓燃燒室流場模擬分析

Abstract

本研究敘述對富燃料推進劑聯管試驗系統之衝壓引擎燃燒室流場模擬分析，其主要完成的工作項目有以下幾點：(1)甲烷燃料之二維穩態流場模擬、(2)氫燃料之三維穩態流場模擬、(3)氫燃料之三維暫態流場模擬以及(4)三維氫燃燒與不同進氣角度之探討。本研究所採用的紊流模組為雙方程式k-epsilon紊流模組，此為工業界廣泛應用之紊流模組；而燃燒模組的部分則採用非預混燃燒模組。 研究目的為藉由各種流場條件以及各種燃料參數作測試，並引用文獻中的超音速流場以及燃燒流場問題加以驗證，再與文獻中之實驗以及模擬數據比較，均得到相當吻合的結果。藉由兩個驗證範例，來了解其對燃燒室流場結構之物理特性，如迴流區、紊流、邊界層、衝壓進氣角度之效應等。對所使用數值模擬工具的應用性作了一系列的探討，並且從壓力、溫度、馬赫數、超音速流、燃料與空氣混合及燃燒反應物成分等資訊，對聯管試驗系統衝壓引擎燃燒室流場提供了有助益的資料，並能對實際的實驗操作提供重要的參考依據。

This study simulates the hydrogen-air combustion flow fields in a connected pipe ramjet test facility. The following objectives where achieved：(1) the simulation of two dimensional steady combustion flow using methane, (2) the simulation of three dimensional steady combustion flow using hydrogen, (3) the simulation of three dimensional transient combustion flow using hydrogen, (4) the study of three dimensional steady combustion flow using hydrogen with different incoming angle. Two models are implemented for solving the hydrogen-air combustion flow, k-epsilon turbulence model and non-premixed combustion model. Various flow conditions have been simulated for investigating the aerodynamics properties .The simulation results of supersonic flow problem and combustion flow problem are in good agreement with the work by which method, the two computational examples provide the details for the flow structure, such as shock wave, turbulence flow, boundary layer, effect of incoming angle etc. An investigation on application of the numerical method has achieved. The simulation gives useful information for designing the connected pipe ramjet test facility.