航空计算技术
航空計算技術
항공계산기술
AERONAUTICAL COMPUTER TECHNIQUE
2014年
3期
62-65
,共4页
旋转%固体火箭发动机喷管%流场仿真%热结构耦合分析
鏇轉%固體火箭髮動機噴管%流場倣真%熱結構耦閤分析
선전%고체화전발동궤분관%류장방진%열결구우합분석
spinning%SRM nozzle%flow field simulation%thermo-structure coupled analysis
以某固体火箭发动机喷管为例，研究其旋转情况下的流动、传热及热结构响应性能。利用雷诺应力湍流模型，结合增强型壁面函数，求解N-S方程。以喷管内壁面温度分布为边界条件，求解二维轴对称瞬态热传导方程。将瞬态温度场按时间步长加载，进行瞬态静力学分析，得到不同转速下的流场、温度场及应力场。结果表明，喷管在旋转情况下，喷管内壁面尤其是喉部及扩张段温度分布在转速为100 r／min及600 r／min左右时变化剧烈；旋转内流场与喷管结构的耦合作用加剧了喷管的传热，尤其是喉衬的烧蚀，特征点温度值随转速增大而升高；最大热应力位于喷管最外层尾端，整体热应力在转速低于100 r／min时得到释放，随着转速的不断增大，喷管整体最大热应力及扩张段特征点应力随之增大，而喉衬特征点由于旋转导致了温度梯度降低，其应力值随之减小。
以某固體火箭髮動機噴管為例，研究其鏇轉情況下的流動、傳熱及熱結構響應性能。利用雷諾應力湍流模型，結閤增彊型壁麵函數，求解N-S方程。以噴管內壁麵溫度分佈為邊界條件，求解二維軸對稱瞬態熱傳導方程。將瞬態溫度場按時間步長加載，進行瞬態靜力學分析，得到不同轉速下的流場、溫度場及應力場。結果錶明，噴管在鏇轉情況下，噴管內壁麵尤其是喉部及擴張段溫度分佈在轉速為100 r／min及600 r／min左右時變化劇烈；鏇轉內流場與噴管結構的耦閤作用加劇瞭噴管的傳熱，尤其是喉襯的燒蝕，特徵點溫度值隨轉速增大而升高；最大熱應力位于噴管最外層尾耑，整體熱應力在轉速低于100 r／min時得到釋放，隨著轉速的不斷增大，噴管整體最大熱應力及擴張段特徵點應力隨之增大，而喉襯特徵點由于鏇轉導緻瞭溫度梯度降低，其應力值隨之減小。
이모고체화전발동궤분관위례，연구기선전정황하적류동、전열급열결구향응성능。이용뢰낙응력단류모형，결합증강형벽면함수，구해N-S방정。이분관내벽면온도분포위변계조건，구해이유축대칭순태열전도방정。장순태온도장안시간보장가재，진행순태정역학분석，득도불동전속하적류장、온도장급응력장。결과표명，분관재선전정황하，분관내벽면우기시후부급확장단온도분포재전속위100 r／min급600 r／min좌우시변화극렬；선전내류장여분관결구적우합작용가극료분관적전열，우기시후츤적소식，특정점온도치수전속증대이승고；최대열응력위우분관최외층미단，정체열응력재전속저우100 r／min시득도석방，수착전속적불단증대，분관정체최대열응력급확장단특정점응력수지증대，이후츤특정점유우선전도치료온도제도강저，기응력치수지감소。
A numerical study on a solid rocket motor nozzle is conducted to analyze the flow ,heat transfer and thermo-structure performance .Reynolds Stress viscous model and enhanced wall function are used to solve Navier-Stokes equations .By setting the inner wall temperature distribution as boundary condition , the two-dimensional axisymmetric transient heat transfer equation is solved .By loading the temperature field by step time , a transient static structure analysis is proposed .The flow field , temperature field and stress field are obtained .The results show that for this nozzle ,spinning lead to a severe change in inner wall temperature distribution especially at nozzle insert and the divergent section when speed is 100 r/min and 600 r/min.A coupled effect of spinning flow field and structure results in severe heat transfer espe -cially erosion of nozzle insert .The temperature of the characteristic points increases along with the spin-ning speed .The maximum Von-Mises stress is at end of the outermost .The entire stress can released when spinning speed is lower than 100 r/min.The maximum Von-Mises stress of the nozzle and the char-acteristic point at divergent section increases with the spinning speed , while the characteristic point at nozzle insert decreases because of temperature gradient decreasing leading by spinning .
