涡流冷壁旋流燃烧室的数值模拟

推进技术 ›› 2015, Vol. 36 ›› Issue (3): 436-442.

涡流冷壁旋流燃烧室的数值模拟

徐舟¹,曾卓雄²,徐义华¹

南昌航空大学飞行器工程学院，江西南昌 330063,上海电力学院能源与机械工程学院，上海 200090,南昌航空大学飞行器工程学院，江西南昌 330063

发布日期:2021-08-15
作者简介:徐舟(1992—)，男，硕士生，研究领域为航空工程。 E-mail: nhxz1992@163.com 通讯作者:曾卓雄(1972—)，男，博士，教授，研究领域为航空宇航推进理论与工程。
基金资助:
国家自然科学基金(51066006；51266013)；航空科学基金(2013ZB56002；2013ZB56004)；江西省研究生创新基金(YC2014-S397)。

Numerical Simulation of a Swirling Combustor with Vortex Cooling Wall

Aircraft Engineering College，Nanchang Hangkong University，Nanchang 330063，China,College of Power and Mechanical Engineering, Shanghai University of Electric Power, Shanghai 200090，China and Aircraft Engineering College，Nanchang Hangkong University，Nanchang 330063，China

Published:2021-08-15

摘要/Abstract

摘要： 为了获得涡流冷壁旋流燃烧室的双旋涡结构对其燃烧流动性能的影响规律，改变切向入口的进口速度，对其内部流场进行了数值模拟。结果表明:在燃烧工况下，双旋涡结构较冷态时更难形成；随着切向入口的进口速度增加，涡流冷壁旋流燃烧室的燃烧效率较旋流燃烧室增大2%左右，壁面温度从1200K降低至600K，出口CO₂的排放量降低；双旋涡结构会增加燃烧室的总压损失，但是增加的程度很小。

关键词: 涡流冷壁；旋流；燃烧室；数值模拟

Abstract: In order to study the effects of bidirectional vortices on swirling combustor with vortex cold wall，different velocity of the tangential inlet were used and compared by CFD. The results show that bidirectional vortexes are harder to form in swirling combustor while under combustion than cold condition. As the velocity of the tangential inlet increase，the combustion efficiency increases by about 2% than swirling combustor. The wall temperature reduces from 1200K to 600K，and the emission of carbon dioxide also reduces. Bidirectional vortexes improve the total pressure loss of the combustor，but the range of that is narrow.

Key words: Vortex cold-wall；Swirl；Combustor；Numerical simulation

徐舟,曾卓雄,徐义华. 涡流冷壁旋流燃烧室的数值模拟[J]. 推进技术, 2015, 36(3): 436-442.

XU Zhou¹,ZENG Zhuo-xiong²,XU Yi-hua¹. Numerical Simulation of a Swirling Combustor with Vortex Cooling Wall[J]. Journal of Propulsion Technology, 2015, 36(3): 436-442.

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