Combustion flow field and thermal protection performance of a liquid oxygen/kerosene engine with pintle injectors

IF 3.1 2区物理与天体物理 Q1 ENGINEERING, AEROSPACE

Acta Astronautica Pub Date : 2024-09-30 DOI:10.1016/j.actaastro.2024.09.065

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引用次数: 0

Abstract

A pintle injector is a convenient method for adjusting propellant combustion and has received extensive attention in recent years. However, few studies have examined the effects of the injection direction and momentum ratio (ratio of liquid oxygen momentum to kerosene momentum) on the flow field, temperature field, and dual-belt liquid film cooling effect in the combustion chamber. This study verified a new computational fluid dynamics (CFD) engine combustion model based on a pintle injector through a hot-test experiment. A simulation was conducted using this model. With different injection directions, when the momentum ratio was increased, the trends in the combustion efficiency and chamber pressure growth were entirely opposite. For the axial kerosene and radial liquid oxygen injection direction of liquid film cooling, when the momentum ratio was 0.73–0.9, the proportion of the first ring belt liquid film flow was selected as 5–10 %, and the second ring belt liquid film flow proportion was selected as 5–7%. When the momentum ratio was less than 0.73, the liquid film flow proportions for both the first and second ring belts were selected as 5 %. When the total liquid film flow proportion was 10 %, the chamber pressure decreased by 0.2–0.3 MPa, and the combustion efficiency decreased by 8–10 %. This numerical study provides guidance for studying the combustion characteristics and cooling performance of pintle-type rocket combustion chambers.

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采用针形喷射器的液氧/煤油发动机的燃烧流场和热保护性能

凤尾喷射器是一种调整推进剂燃烧的便捷方法，近年来受到广泛关注。然而，很少有研究探讨喷射方向和动量比（液氧动量与煤油动量之比）对燃烧室流场、温度场和双带液膜冷却效果的影响。本研究通过热试实验验证了基于针形喷油器的新型计算流体动力学（CFD）发动机燃烧模型。使用该模型进行了模拟。在不同的喷射方向上，当动量比增加时，燃烧效率和燃烧室压力的增长趋势完全相反。对于液膜冷却的轴向煤油和径向液氧喷射方向，当动量比为 0.73-0.9 时，第一环带液膜流比例选择为 5-10%，第二环带液膜流比例选择为 5-7%。当动量比小于 0.73 时，第一环带和第二环带的液膜流量比例均为 5%。当总液膜流比例为 10 % 时，燃烧室压力降低了 0.2-0.3 MPa，燃烧效率降低了 8-10%。这项数值研究为研究品特型火箭燃烧室的燃烧特性和冷却性能提供了指导。

本文章由计算机程序翻译，如有差异，请以英文原文为准。

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来源期刊

Acta Astronautica 工程技术-工程：宇航

CiteScore

7.20

自引率

22.90%

发文量

599

审稿时长

53 days

期刊介绍： Acta Astronautica is sponsored by the International Academy of Astronautics. Content is based on original contributions in all fields of basic, engineering, life and social space sciences and of space technology related to: The peaceful scientific exploration of space, Its exploitation for human welfare and progress, Conception, design, development and operation of space-borne and Earth-based systems, In addition to regular issues, the journal publishes selected proceedings of the annual International Astronautical Congress (IAC), transactions of the IAA and special issues on topics of current interest, such as microgravity, space station technology, geostationary orbits, and space economics. Other subject areas include satellite technology, space transportation and communications, space energy, power and propulsion, astrodynamics, extraterrestrial intelligence and Earth observations.