删除或更新信息,请邮件至freekaoyan#163.com(#换成@)

一种考虑壁面摩擦作用的发射井引射器设计方法

本站小编 Free考研考试/2021-12-21

閻愮懓鍤粩瀣祮閹兼粎鍌�2娑撳洨顫掗懓鍐埡閻㈤潧鐡欓悧鍫gカ閺傛瑱绱�
婢堆囧劥閸掑棛顏㈤棄瀣厴閺勵垳顑囨稉鈧▎陇鈧啰鐖洪敍灞筋嚠娴滃骸顩ф担鏇熺叀閹靛彞绗撴稉姘愁嚦閹稿洤鐣鹃弫娆愭綏閿涘本鍨ㄧ拋鍛婃箒瀵板牆顦块悿鎴︽6閵嗕境ree婢归€涙〃閸掑棗顒熸稊鐘电秹閼板啰鐖哄ǎ杈偓鏇氱瑩娑撴俺顕虫潏鍛嚤20楠炶揪绱濋幀鑽ょ波娴滃棜绉寸€圭偟鏁ら惃鍕瘹鐎规碍鏆€閺夋劖鐓$拠銏℃煙濞夋洖寮锋径宥勭瘎閺傝纭堕敍灞炬箒闂団偓鐟曚胶娈戦惇瀣箖閺夛拷
本文二维码信息
二维码(扫一下试试看!)
一种考虑壁面摩擦作用的发射井引射器设计方法
A Method for Design of Silo Ejector Concerning with Wall Friction
投稿时间:2020-02-21
DOI:10.15918/j.tbit1001-0645.2000.029
中文关键词:发射井壁面摩擦引射器函数静压协调函数驻点极限工作特性曲线
English Keywords:silowall frictionejector functionstatic pressure matching functionstagnation critical pointcharacteristic curve
基金项目:国家自然科学基金资助项目(51475462)
摘要点击次数:537
全文下载次数:373
中文摘要:
针对发射井优化设计问题,基于引射器函数方法提出了一种考虑壁面摩擦作用的发射井引射器准一维设计方法,建立了考虑壁面摩擦作用的引射器函数和静压协调函数.证明了考虑壁面摩擦作用时驻点速度小于声速,引射器不能达到第三极限,只能达到驻点极限.以实际算例分析了发动机总压、发射井横截面积、混合室出口压强变化时的引射器工作特性,画出了工作特性曲线.采用计算流体力学(computational fluid dynamics,CFD)方法,分别建模分析了发动机总压、发射井横截面积、混合室出口压强变化时发射井引射器中超声速射流流动形态,将CFD方法得到的混合室入口压强与准一维方法的结果进行了对比.结果表明,准一维方法得到的工作特性曲线与CFD方法的计算结果差距较小,在混合室背压变化时最大误差为4.31%,验证了准一维方法的准确性.
English Summary:
Aiming at the problem of silo design, a quasi-one dimensional method concerning with wall friction was proposed based on the ejector function method. A mathematical model of wall friction was proposed and ejector functions and static pressure matching functions concerning with wall friction were established. The analysis results prove that the velocity at the stagnation critical point is less than sonic speed, the stagnation critical point of ejector can be achieved and the third critical point is impossible to achieve. And then, the characteristics were analyzed with practical examples, considering the engine total pressure, the cross-sectional area of the silo and the outlet pressure of the mixing chamber changed respectively, and the characteristic curves were drawn. The flow patterns of supersonic jet ejectors were analyzed by CFD method, considering respectively the engine total pressure, the cross-sectional area of the silo and the outlet pressure of the mixing chamber changed. At the same time, the inlet pressures of ejectors obtained by CFD were compared with that obtained by the quasi-one dimensional method. The results show that the errors between the CFD method and the quasi-one dimensional method are little on characteristic curves and their largest value is 4.31% when the backpressure changes, which verified the quasi-one dimensional method.
查看全文查看/发表评论下载PDF阅读器
閹存劒璐熺拠鍙ュ敩鐞涱煉绱濋崚鍡曢煩鐠囧墽鈻肩挧鍕灐闁剧偓甯寸亸杈厴閼惧嘲褰�40%閹绘劖鍨氱挧姘舵尪閿涳拷
閹恒劌绠嶇挧姘舵尪閺夊啰娉妴鍌濐嚦娴狅綀銆冮崣顖炩偓姘崇箖娴滄帟浠堢純鎴犵搼闁柨绶炴稉鐑樻拱缁旀瑦甯归獮鍨吅娴肩姭鈧钒IP娴兼艾鎲抽垾婵撶礉閻€劍鍩涢柅姘崇箖鐠囧彞鍞悰銊ф畱閸掑棔闊╅柧鐐复閹存牗鎹i幎銉ㄥ枠娑旀澘鎮楅敍宀冾嚦娴狅綀銆冮懢宄板絿40%閹绘劖鍨氶妴鍌濐嚦娴狅綀銆冪拹顓濇嫳閺堫剛鐝禒璁崇秿娴溠冩惂閿涘苯娼庢禍顐㈠綀9閹舵ǜ鈧倸鐨㈤崚鍡曢煩闁剧偓甯撮妴浣规崳閹躲儱娴橀悧鍥╃搼閿涘苯褰傞崚鏉款劅閺嵚ゎ啈閸ф稏鈧胶娅ㄦ惔锕佸垱閸氀佲偓浣镐簳閸楁哎鈧礁浜曟穱掳鈧傅Q缁屾椽妫块妴浣虹叀娑斿簺鈧浇鐪撮悺锝囩搼閸氬嫬銇囬獮鍐插酱閵嗭拷
相关话题/火箭军工程大学 技术 陕西 工作 设计