火箭推进
火箭推進
화전추진
JOURNAL OF ROCKET PROPULSION
2011年
4期
35-39
,共5页
李强%聂嵩%刘业奎%潘亮%马梦颖
李彊%聶嵩%劉業奎%潘亮%馬夢穎
리강%섭숭%류업규%반량%마몽영
过氧化氢发动机%推力室%燃烧%数值模拟
過氧化氫髮動機%推力室%燃燒%數值模擬
과양화경발동궤%추력실%연소%수치모의
hydrogen peroxide engine%thrust chamber%combustion%numerical simulation
采用离散相模拟颗粒随机轨道方法处理两相流动,采用SST后刊湍流模型,利用燃料的单步总反应模型模拟煤油蒸汽燃烧,针对过氧化氢/煤油发动机推力室,进行三维两相燃烧数值模拟。对推力室的总体流场特征及性能进行了初步研究,为开展进一步的数值研究奠定基础。
採用離散相模擬顆粒隨機軌道方法處理兩相流動,採用SST後刊湍流模型,利用燃料的單步總反應模型模擬煤油蒸汽燃燒,針對過氧化氫/煤油髮動機推力室,進行三維兩相燃燒數值模擬。對推力室的總體流場特徵及性能進行瞭初步研究,為開展進一步的數值研究奠定基礎。
채용리산상모의과립수궤궤도방법처리량상류동,채용SST후간단류모형,이용연료적단보총반응모형모의매유증기연소,침대과양화경/매유발동궤추력실,진행삼유량상연소수치모의。대추력실적총체류장특정급성능진행료초보연구,위개전진일보적수치연구전정기출。
The gas-liquid combustion and flow field in HTP/kerosene engine thrust chamber were numerically simulated in the paper. Discrete phase modeling (DPM) and SST k-to turbulence model were used to simulate the kerosene gas-liquid flow and turbulence respectively. A one-step general reaction model of fuel was employed to simulate the kerosene vapour combustion. The combustion flow field and performance parameters of the combustion chamber were numerically investigated. A foundation for the further numerical research was established in this paper.