Flow and Heat Transfer Characteristics of Film Cooling on Hypersonic Nozzles

被引：0
|
作者：
Hu Z.-Y. [1 ,2 ]
Xing Y.-F. [1 ]
Zhong F.-Q. [1 ,2 ]
机构：
[1] State Key Laboratory of High Temperature Gas Dynamics, Institute of Mechanics, Chinese Academy of Sciences, Beijing
[2] College of Engineering Science, University of Chinese Academy of Sciences, Beijing
来源：
Tuijin Jishu/Journal of Propulsion Technology | 2023年 / 44卷 / 12期
关键词：
Film cooling; Hypersonic nozzle; Numerical simulation; Outflow quality; Wall heat flux;
D O I：
10.13675/j.cnki.tjjs.2207058
中图分类号：
学科分类号：
摘要：
Based on the Reynolds Average methods with SST k-ω turbulence model，the flow and heat transfer properties of the Mach 6 hypersonic nozzle with gaseous film cooling are numerically investigated. The effects of mass flow rate，geometric parameters of slot（including slot height and step height）and location of the slot on the heat flux（especially at the throat）and the outflow quality are analyzed carefully. Numerical research results indicate that the introduction of gaseous film cooling can reduce the heat load on the wall effectively，especially at the throat. The velocity distribution at the nozzle exit is not influenced by the gaseous film cooling but the temperature distribution is quite different with and without the film cooling. The numerical research shows that when the mass flow rate of gaseous film cooling M is only 3.53% of the mainstream，the heat flux at the nozzle throat decreases by 30.1%，and when M reach 14.27%，the heat flux at the nozzle throat decreases by 87.3%. The change of slot height and location of the slot can change the cooling efficiency，but the change of step height has nearly no influence. © 2023 Journal of Propulsion Technology. All rights reserved.
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