航空计算技术
航空計算技術
항공계산기술
Aeronautical Computing Technique
2015年
5期
15-19
,共5页
超燃冲压发动机性能%燃烧室准一维流模型%气流冲量%气流参数%燃料
超燃遲壓髮動機性能%燃燒室準一維流模型%氣流遲量%氣流參數%燃料
초연충압발동궤성능%연소실준일유류모형%기류충량%기류삼수%연료
scramjet performance%quasi-one-dimensional steady model%airflow impulse function%airflow parameters%fuels
针对设计状态下超燃冲压发动机前体／进气道出口总压恢复系数和马赫数、燃料当量比、后体／尾喷管静压膨胀系数及燃料特性对其性能的影响进行了初步分析。首先通过质量、动量和能量三大守恒定律，利用截面上气流冲量建立了发动机性能与气流参数的内在关系模型，然后对设计状态下超燃冲压发动机的性能进行了研究。研究结果表明，性能影响因素需要最优化折中考虑；燃料对发动机性能影响主要由其热值起决定作用。
針對設計狀態下超燃遲壓髮動機前體／進氣道齣口總壓恢複繫數和馬赫數、燃料噹量比、後體／尾噴管靜壓膨脹繫數及燃料特性對其性能的影響進行瞭初步分析。首先通過質量、動量和能量三大守恆定律，利用截麵上氣流遲量建立瞭髮動機性能與氣流參數的內在關繫模型，然後對設計狀態下超燃遲壓髮動機的性能進行瞭研究。研究結果錶明，性能影響因素需要最優化摺中攷慮；燃料對髮動機性能影響主要由其熱值起決定作用。
침대설계상태하초연충압발동궤전체／진기도출구총압회복계수화마혁수、연료당량비、후체／미분관정압팽창계수급연료특성대기성능적영향진행료초보분석。수선통과질량、동량화능량삼대수항정률，이용절면상기류충량건립료발동궤성능여기류삼수적내재관계모형，연후대설계상태하초연충압발동궤적성능진행료연구。연구결과표명，성능영향인소수요최우화절중고필；연료대발동궤성능영향주요유기열치기결정작용。
With regard to performance factors analysis of scramjet for air-breathing hypersonic flight vehi-cle in a state of standard design which include total-pressure recovery coefficient and Mach number of forebody /inlet exit,fuel equivalence ratio,static pressure expansion coefficient of afterbody/nozzle and fuel characteristic.Firstly,based on airflow impulse function of some cross section,the models of internal relation between scramjet performance and airflow parameters were decided through a quasi-one-dimen-sional steady model educed by conservation of mass,momentum and energy.What's more,the performance of supersonic mode for scramjet was researched in combination with instances.The results of research have illustrated that scramjet performance influence factors need to be optimization and compromise,and effection of fuels was determined by theirs caloric caloricity besides by numbers of carbon and hydrogen as well as theirs ratio.
