参考焓值法在高速槽道湍流中的修正

陈小平; 李新亮; 仲峰泉

doi:10.6052/0459-1879-12-308

参考焓值法在高速槽道湍流中的修正

doi: 10.6052/0459-1879-12-308

1.
中国科学院力学研究所高温气体国家重点实验室, 北京 100190
2. 浙江理工大学机械与自动控制学院, 浙江 310018

基金项目: 国家自然科学基金项目(11072248); 国家重大基础研究发展规划项目(2009CB724100); 国家高技术研究发展计划项目(2012AA01A304)和中国科学院知识创新工程项目(KJCX2-EW-J01)资助.

详细信息

通讯作者:
李新亮,研究员,主要研究方向:计算流体力学、湍流.E-mail:lixl@imech.ac.cn

中图分类号: V211.3
计量
- 文章访问数: 1830
- HTML全文浏览量: 62
- PDF下载量: 728
- 被引次数: 0
出版历程
- 收稿日期: 2013-03-06
- 修回日期: 2013-04-08
- 刊出日期: 2013-07-18

THE OPTIMIZED REFERENCE ENTHALPY METHOD USING IN HIGH-SPEED TURBULENT CHANNEL FLOWS

1.
State Key Lab. of High-temperature Gas Dynamics, Institute of Mechanics, Chinese Academy of Sciences, Beijing 100190, China
2. School of Mechanical Engineering and Automation, Zhejiang Sci-Tech University, Zhejiang 310018, China

Funds: The project was supported by the National Natural Science Fundation of China (11072248), the Major State Basic Research Development Program of China (2009CB724100), the National Key Technologies R&D Program of China (2012AA01A304) and the CAS Program (KJCX2-EW-J01).

摘要

摘要: 利用高来流马赫数为3, 5, 6, 7, 10的槽道湍流直接数值模拟(direct numerical simulations, DNS)数据, 评估和修正经典的参考焓值法. 研究表明在高来流马赫数槽道湍流中, 经典参考焓值法预测的壁面热流与DNS结果相差很大, 需要作适当的修正.修正参考焓值法Ⅰ和Ⅱ的预测结果明显优于经典参考焓值法;并且修正参考焓值法Ⅱ更加适用于高马赫数流动, 其壁面热流与DNS结果的相对误差在10%以内. 同时, 修正参考焓值法Ⅱ的普适性在超声速燃烧室隔离段热环境试验中得到了验证.
- 高超声速飞行 /
- 槽道湍流 /
- 直接数值模拟 /
- 参考焓值法
Abstract: Direct numerical simulations of high-speed turbulent channel flows have been performed. The classic reference enthalpy method was evaluated and optimized by using the data with inflow Mach numbers of 3, 5, 6, 7, and 10. In fully developed turbulent flow, studies have shown that the classic reference enthalpy method is not applicable in high-speed channel flows. The wall heat flux predicted by the optimized reference enthalpy methods I and II are much better than the classic reference enthalpy method; moreover, the optimized reference enthalpy method II is more suitable, whose errors are within 10% compared with DNS. At the same time, the optimized reference enthalpy method II has been verified based on the experiment data of thermal environment of supersonic combustor.
- high-speed flow /
- channel turbulent /
- direct numerical simulation /
- reference enthalpy method

HTML全文

参考文献(9)

Anderson JD. Hypersonic and High-Temperature, 2nd edn. New York: AIAA, 2006

Bertin JJ, Cummings RM. Critical hypersonic aerothermodynamic phenomena. Annual Review of Fluid Mechanics, 2006, 38: 129-157

Eckert ERG. Engineering Relations for Heat Transfer and Friction in High-Velocity Laminar and Turbulent Boundary Layer Flow Over Surfaces with Constant Pressure and Temperature. Transactions of the ASME, 1956

Heiser WH, Pratt DT. Hypersonic airbreathing propulsion. Washington, DC: AIAA, 1994

Sieder EN, Tate CE. Heat transfer and pressure drop of liquids in tubes. Industrial & Engineering Chemistry, 1936, 28: 1429-1435

Robert WS. Process Heat Transfer: Principles and Applications. Oxford: Elsevier Science, 2007

Meador WE, Smart MK. Reference enthalpy method developed from solutions of the boundary-layer equations. AIAA Journal, 2005, l43(1): 130-139

陈小平, 李新亮, 樊菁. 变比热真实气体效应的高超声速槽道湍流直接数值模拟. 中国科学: 物理学力学天文学, 2011, 41(8): 969-979 (Chen Xiaoing, Li XinLiang, Fan Jing. Direct numerical simulation of hypersonic turbulent channel flow in thermally perfect gas. Scientia Sinica Phys, Mech & Astron, 2011, 41(8): 969-979 (in Chinese))

袁涛, 李龙, 王晶等. 超声速燃烧隔离段热环境的实验测量与理论分析. 见:第四届高超声速科技学术会议, 2011. CSTAM 2011-2771 (Yuan Tao, Li Long, Fan Xuejun, et al. Measurement and calculation of thermal environment of supersonic combustor. In: The Proc. of the Fourth Hypersonic Technology Conference, 2011. CSTAM 2011-2771 (in Chinese))

施引文献

资源附件(0)

访问统计