Numerical simulation of film cooling in supersonic flow (A04)

超音速流中气膜冷却的数值模拟（A04）

• 批准号: 50008755
• 金额: --
• 依托单位: Institut für Aerodynamik und Gasdynamik (IAG)
• 依托单位国家: 德国
• 项目类别: CRC/Transregios
• 财政年份: 2008
• 资助国家: 德国
• 起止时间: 2007-12-31 至 2019-12-31
• 项目状态: 已结题
• 来源: https://gepris.dfg.de/gepris/projekt/50008755?language=en
• 关键词: Numerical; simulation; film; cooling; supersonic

Film cooling of a rocket nozzle extension is investigated using direct numerical or large-eddy simulations of the two-component-gas turbulent boundary-layer flow. The simulations of cooling-gas injection through a backward-facing-step slit or by slots or holes at the wall are closely coordinated with the shock-tunnel ex-periments at the RWTH Aachen (sub-project A2) employing gaseous H2O as hot gas and N2, CO2, He, Ar as coolant. The work is aimed at concluding in recommendations for the practical application of film cooling in the nozzle extension, and working out numerical-method and modelling specifications for the demonstrator-concept subproject K4, gained by a combined experimental and numerical effort.

采用直接数值模拟或大涡模拟方法研究了火箭喷管外伸段的二组分气体湍流边界层流动的气膜冷却。通过后向台阶缝或壁面缝或孔注入冷却气体的模拟与亚琛RWTH（子项目A2）的激波风洞实验密切配合，实验采用气态H_2O作为热气体，N_2、CO_2、He、Ar作为冷却剂。这项工作的目的是总结在喷嘴扩展的薄膜冷却的实际应用的建议，并制定了数值方法和建模规范的演示概念子项目K4，通过实验和数值相结合的努力。