CAJ | 학술논문

将边界元计算方法应用到三维N-S方程求解程序中,流体部分采用有限差分法求解N-S方程,边界元法求解固体区域热传导方程.开发气热耦合计算程序对NASA-MarkII高压气冷涡轮叶栅热环境进行气热耦合分析.利用边界元法特有的优势(降维、解析与离散相结合的特点),避免了固体区域的网格生成和内部节点求解工作,提高了计算精度.结果表明,耦合计算程序能够高效、准确求解多场的气热耦合问题,计算结果与实验结果吻合的较好,二者平均误差为3 %.
장변계원계산방법응용도삼유N-S방정구해정서중,류체부분채용유한차분법구해N-S방정,변계원법구해고체구역열전도방정.개발기열우합계산정서대NASA-MarkII고압기랭와륜협책열배경진행기열우합분석.이용변계원법특유적우세(강유、해석여리산상결합적특점),피면료고체구역적망격생성화내부절점구해공작,제고료계산정도.결과표명,우합계산정서능구고효、준학구해다장적기열우합문제,계산결과여실험결과문합적교호,이자평균오차위3 %.
A boundary element calculation method was used in a program for solving a three-dimensional N-S equation. The finite difference method was adopted in the fluid portion of the coupled calculation program to solve the N-S equation,and the boundary element method,to solve the heat conduction equation for the solid zone. A newly-developed gas-thermal coupled calculation program was employed to conduct a gas-thermal coupled analysis of the thermal environment in NASA-Mark II HP air-cooled turbine cascades. By utilizing the advantages(features combining a decrease in dimension with analysis and discreteness)specific to the boundary element method,the authors have avoided the grid generation in the solid area and the solution-seeking of interior nodes,thus enhancing the calculation precision. The calculation results show that the coupled calculation program can effectively and accurately solve the gas-thermal coupled problems in multiple fields. The results of calculation correspond relatively well with those of the test ones,and their average error is assessed at 3%.