Design Methodology for Thermal Protection of Hydrogen Peroxide and Kerosene Thrust Chamber Used by Combined Cycle Engine

被引：0

作者：

Han Z.-P. ^{[1
]}

Guo S. ^{[1
]}

Liu Y.-B. ^{[1
]}

Hou J.-L. ^{[1
]}

Wei B.-X. ^{[1
]}

Gang Q. ^{[1
]}

机构：

[1] Science and Technology on Scramjet Laboratory, Beijing Power Machinery Institute, Beijing

来源：

Tuijin Jishu/Journal of Propulsion Technology | 2021年 / 42卷 / 10期

关键词：

Combined cycle engine; Engineering calculation method; Hydrogen peroxide; Thermal protection; Thrust chamber;

D O I：

10.13675/j.cnki.tjjs.200004

中图分类号：

学科分类号：

摘要：

An engineering calculating method was built to fulfill the requirement of thermal protection design on a hydrogen peroxide and kerosene biopropellant thrust chamber embeded in rocket combined cycle engine. By modifying the convection heat transfer coefficient of burned gas and introducing the liquid film decomposition rate of coolant, the results match well with those of experiment and three dimensional coupled numerical simulation. Then, applied in the thermal protection of a thruster assembled in combined cycle engine, the result indicates that the cooling design is proved practicable, with liquid film cooling in the head and regenerative cooling in the body. The coolant is selected as hydrogen peroxide and the consumption of liquid film cooling makes up about 30%. The method manages to evaluate the performance of thermal protection conveniently, and contribute to the assessment of the overall performance. © 2021, Editorial Department of Journal of Propulsion Technology. All right reserved.

引用

页码：2267 / 2276

页数：9

共 19 条

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