Effects of a dual-cavity flameholder on the flameholding characteristics and flame behavior for low flight Mach numbers

IF 3.4 2区物理与天体物理 Q1 ENGINEERING, AEROSPACE

Acta Astronautica Pub Date : 2025-09-12 DOI:10.1016/j.actaastro.2025.09.024

Kei Norimatsu , Noriko Katsumura , Satoshi Nishiura , Taku Kudo , Akihiro Hayakawa , Hideaki Kobayashi

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Abstract

Flame chemiluminescence, pressure profiles, flameholding limits, OH chemiluminescence, and shadowgraph images in a scramjet model combustor with a dual-cavity flameholder and burned-gas injection were investigated experimentally. The main objective of this study was to clarify the flameholding characteristics of a dual-cavity flameholder and investigate the advantages of using it over a single-cavity flameholder for low-flight Mach numbers. The mainstream conditions were a Mach number of 2.8, total temperature of 700 ± 50 K, and total pressure of 0.6 MPa. The results showed that the flame chemiluminescences of the single- and dual-cavity were very similar. However, the pressure rise in the dual-cavity flameholder was higher than that in the single-cavity flameholder around the downstream cavity. This means that the dual-cavity flameholder increased the fuel consumption. In other words, the combustion efficiency increased. It was also clarified that the dual-cavity flameholder improved the flameholding characteristics compared with the single-cavity flameholder. High-speed OH chemiluminescence images showed that the flameholding characteristics were improved by the specific ignition process of the dual-cavity flameholder. The specific ignition process was flame propagation from downstream to upstream in the combustor. High-speed shadowgraphs and OH chemiluminescence images showed that the shock wave generated by combustion caused the flame to propagate upstream. In addition, the dual-cavity flameholder temporarily stabilized the flame around the downstream cavity during ignition process. The study results showed that the dual-cavity flameholder improves the flameholding characteristics of the scramjet model combustor owing to temporary flameholding in the downstream cavity for low-flight Mach number conditions.

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低飞行马赫数条件下双腔火焰保持器对火焰保持特性和火焰行为的影响

实验研究了超燃冲压发动机模型燃烧室的火焰化学发光、压力分布、持火极限、OH化学发光和阴影图像。本研究的主要目的是澄清双腔火枪的持火特性，并研究在低飞行马赫数时使用它比使用单腔火枪的优势。主流工况为马赫数2.8，总温度700±50 K，总压0.6 MPa。结果表明，单腔和双腔的火焰化学发光非常相似。但在下游空腔周围，双腔火焰的压力上升高于单腔火焰。这意味着双腔火焰支架增加了燃料消耗。也就是说，燃烧效率提高了。研究还表明，与单腔火嘴相比，双腔火嘴改善了其持火特性。高速OH化学发光图像表明，双腔火焰支架的特定点火过程改善了其持焰特性。具体的点火过程是火焰在燃烧室内由下游向上游传播。高速阴影图像和OH化学发光图像显示，燃烧产生的激波使火焰向上游传播。此外，双腔火焰支架在点火过程中暂时稳定了下游腔周围的火焰。研究结果表明，在低飞行马赫数条件下，双腔火焰保持器由于在下游腔内存在暂时的火焰保持，改善了超燃冲压发动机模型燃烧室的火焰保持特性。

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.