CAJ | 학술논문

为准确模拟固体火箭发动机燃烧室内流场，采用基于格心的迎风型有限体积法求解定常雷诺平均Navier-Stokes方程，在空间离散方法上，采用AUSM-PW矢通量分裂格式，时间推进采用三阶三步TVD型Runge-Kutta显式方法，将Ment-er F R提出的SST( shear-stress-transport)湍流模型及其改进形式用于燃烧室湍流流场的数值模拟，并将计算结果与Wilcox的和Spalart-Allmaras湍流模型进行了对比。结果表明， Menter F R的SST湍流模型计算的燃烧室内的径向速度分布与实验值吻合得最好，最大误差约为5.1%；计算的燃烧室内湍流强度分布与实验的规律一致，而其余湍流模型计算的结果与实验值有很大差异。
위준학모의고체화전발동궤연소실내류장，채용기우격심적영풍형유한체적법구해정상뢰낙평균Navier-Stokes방정，재공간리산방법상，채용AUSM-PW시통량분렬격식，시간추진채용삼계삼보TVD형Runge-Kutta현식방법，장Ment-er F R제출적SST( shear-stress-transport)단류모형급기개진형식용우연소실단류류장적수치모의，병장계산결과여Wilcox적화Spalart-Allmaras단류모형진행료대비。결과표명， Menter F R적SST단류모형계산적연소실내적경향속도분포여실험치문합득최호，최대오차약위5.1%；계산적연소실내단류강도분포여실험적규률일치，이기여단류모형계산적결과여실험치유흔대차이。
In order to accurately simulate the solid rocket motor inner flow field,the Reynolds-average Navier-Stokes equations were solved with three-order three-step Runge-Kutta iterative algorithm by cell center finite volume method, AUSM-PW scheme were implemented for spatial discretization. Also, SST ( shear-stress-transport) turbulence model developed by Menter was used to simulate the turbulence flow field of the combustion chamber. Then the result was compared with Wilcox and Spalart-Allmaras turbu-lence model. Simulated results show that the general agreement between computed axial velocity profiles and experimental result is excellently good and the maximum error is only about 5.1%.The overall trends of the numerical turbulent intensity match quite well with experiment for all locations, and there is big disagreement between experiment and the other turbulence models.