CAJ | 학술논문

应用CFD方法对不同收缩型面设计方案进行了数值模拟，并对结果进行了对比分析。结果表明：①采用伯努利双扭线进气结构，收缩段后直段区域径向马赫数梯度较大，收缩段出口附近壁面静压变化剧烈，压力损失较大；②无伯努利双扭线进气结构，双三角函数收缩型面(DTC)壁面静压变化率较小；③不同工况下，伯努利双扭线和圆柱-四次曲线-圆锥-四次曲线组合收敛曲线(CQCQ)型线组合、伯努利双扭线和DTC型线组合、仅CQCQ型线、仅DTC型线四种结构，壁面附面层厚度在收缩段出口基本一致；④进行大流量发动机试验，高空台可参考选用仅CQCQ型线和仅DTC型线作为亚声速进气结构。
응용CFD방법대불동수축형면설계방안진행료수치모의，병대결과진행료대비분석。결과표명：①채용백노리쌍뉴선진기결구，수축단후직단구역경향마혁수제도교대，수축단출구부근벽면정압변화극렬，압력손실교대；②무백노리쌍뉴선진기결구，쌍삼각함수수축형면(DTC)벽면정압변화솔교소；③불동공황하，백노리쌍뉴선화원주-사차곡선-원추-사차곡선조합수렴곡선(CQCQ)형선조합、백노리쌍뉴선화DTC형선조합、부CQCQ형선、부DTC형선사충결구，벽면부면층후도재수축단출구기본일치；④진행대류량발동궤시험，고공태가삼고선용부CQCQ형선화부DTC형선작위아성속진기결구。
CFD technique was utilized to numerically simulate different contraction contour schemes and comparison analysis of results was also conducted. The results show that 1) for inlet duct of altitude simula-tion cell with bernoulli’s lemniscates inlet installed, gradient of radial Mach number is large in straight sec-tion after contractive section, gradient of static pressure on wall near outlet has a sharp change and introduc-es a large pressure loss;2)for inlet duct of altitude simulation cell without bernoulli’s lemniscates inlet in-stalled, Dual-trigonometric Function Contraction contour(DTC) makes a lower gradient of static pressure;3) under different operating conditions, height of boundary layer in outlet of contractive section is same for Ber-noulli’s Lemniscates-Cylinder Quartic Cone Quartic (CQCQ), Bernoulli’s Lemniscates-DTC, Only CQCQ and Only DTC Contour of inlet duct;4) Only CQCQ contour and Only DTC contour is better for Large-Dis-charge Engine in simulated altitude test.