Numerical Investigation on the Effect of Fuel-Rich Degree in the RBCC Engine under the Ejector Mode

IF 1.1 4区 工程技术 Q3 ENGINEERING, AEROSPACE International Journal of Aerospace Engineering Pub Date : 2024-02-06 DOI:10.1155/2024/4340688
Yizhi Yao, Mingbo Sun, Menglei Li, Peibo Li, An Bin, Rui Gu, Jiaoru Wang, Feng Wei, Taiyu Wang, Jikai Chen
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Numerical simulations were conducted for various rocket mixing ratios (<span><svg height=\"8.8423pt\" style=\"vertical-align:-0.2064009pt\" version=\"1.1\" viewbox=\"-0.0498162 -8.6359 21.065 8.8423\" width=\"21.065pt\" xmlns=\"http://www.w3.org/2000/svg\" xmlns:xlink=\"http://www.w3.org/1999/xlink\"><g transform=\"matrix(.013,0,0,-0.013,0,0)\"></path></g><g transform=\"matrix(.013,0,0,-0.013,13.434,0)\"></path></g></svg><span></span><svg height=\"8.8423pt\" style=\"vertical-align:-0.2064009pt\" version=\"1.1\" viewbox=\"24.6471838 -8.6359 26.707 8.8423\" width=\"26.707pt\" xmlns=\"http://www.w3.org/2000/svg\" xmlns:xlink=\"http://www.w3.org/1999/xlink\"><g transform=\"matrix(.013,0,0,-0.013,24.697,0)\"></path></g><g transform=\"matrix(.013,0,0,-0.013,30.937,0)\"></path></g><g transform=\"matrix(.013,0,0,-0.013,33.901,0)\"></path></g><g transform=\"matrix(.013,0,0,-0.013,43.773,0)\"></path></g></svg><span></span><span><svg height=\"8.8423pt\" style=\"vertical-align:-0.2064009pt\" version=\"1.1\" viewbox=\"54.9861838 -8.6359 15.753 8.8423\" width=\"15.753pt\" xmlns=\"http://www.w3.org/2000/svg\" xmlns:xlink=\"http://www.w3.org/1999/xlink\"><g transform=\"matrix(.013,0,0,-0.013,55.036,0)\"></path></g><g transform=\"matrix(.013,0,0,-0.013,61.276,0)\"><use xlink:href=\"#g113-47\"></use></g><g transform=\"matrix(.013,0,0,-0.013,64.24,0)\"></path></g></svg>)</span></span> under subsonic (<span><svg height=\"11.8174pt\" style=\"vertical-align:-3.1815pt\" version=\"1.1\" viewbox=\"-0.0498162 -8.6359 32.873 11.8174\" width=\"32.873pt\" xmlns=\"http://www.w3.org/2000/svg\" xmlns:xlink=\"http://www.w3.org/1999/xlink\"><g transform=\"matrix(.013,0,0,-0.013,0,0)\"></path></g><g transform=\"matrix(.013,0,0,-0.013,12.416,0)\"></path></g><g transform=\"matrix(.0091,0,0,-0.0091,18.409,3.132)\"></path></g><g transform=\"matrix(.013,0,0,-0.013,25.242,0)\"><use xlink:href=\"#g117-34\"></use></g></svg><span></span><span><svg height=\"11.8174pt\" style=\"vertical-align:-3.1815pt\" version=\"1.1\" viewbox=\"36.4551838 -8.6359 15.699 11.8174\" width=\"15.699pt\" xmlns=\"http://www.w3.org/2000/svg\" xmlns:xlink=\"http://www.w3.org/1999/xlink\"><g transform=\"matrix(.013,0,0,-0.013,36.505,0)\"></path></g><g transform=\"matrix(.013,0,0,-0.013,42.745,0)\"><use xlink:href=\"#g113-47\"></use></g><g transform=\"matrix(.013,0,0,-0.013,45.709,0)\"></path></g></svg>)</span></span> and supersonic (<span><svg height=\"11.8174pt\" style=\"vertical-align:-3.1815pt\" version=\"1.1\" viewbox=\"-0.0498162 -8.6359 32.873 11.8174\" width=\"32.873pt\" xmlns=\"http://www.w3.org/2000/svg\" xmlns:xlink=\"http://www.w3.org/1999/xlink\"><g transform=\"matrix(.013,0,0,-0.013,0,0)\"><use xlink:href=\"#g113-78\"></use></g><g transform=\"matrix(.013,0,0,-0.013,12.416,0)\"><use xlink:href=\"#g113-98\"></use></g><g transform=\"matrix(.0091,0,0,-0.0091,18.409,3.132)\"><use xlink:href=\"#g190-103\"></use></g><g transform=\"matrix(.013,0,0,-0.013,25.242,0)\"><use xlink:href=\"#g117-34\"></use></g></svg><span></span><span><svg height=\"11.8174pt\" style=\"vertical-align:-3.1815pt\" version=\"1.1\" viewbox=\"36.4551838 -8.6359 15.699 11.8174\" width=\"15.699pt\" xmlns=\"http://www.w3.org/2000/svg\" xmlns:xlink=\"http://www.w3.org/1999/xlink\"><g transform=\"matrix(.013,0,0,-0.013,36.505,0)\"><use xlink:href=\"#g113-50\"></use></g><g transform=\"matrix(.013,0,0,-0.013,42.745,0)\"><use xlink:href=\"#g113-47\"></use></g><g transform=\"matrix(.013,0,0,-0.013,45.709,0)\"></path></g></svg>)</span></span> flight conditions. It was observed that a high fuel-rich degree in the rocket plume negatively impacts the eject performance under all conditions. However, it improves the overall performance (<span><svg height=\"14.0004pt\" style=\"vertical-align:-5.3645pt\" version=\"1.1\" viewbox=\"-0.0498162 -8.6359 13.4272 14.0004\" width=\"13.4272pt\" xmlns=\"http://www.w3.org/2000/svg\" xmlns:xlink=\"http://www.w3.org/1999/xlink\"><g transform=\"matrix(.013,0,0,-0.013,0,0)\"></path></g><g transform=\"matrix(.0091,0,0,-0.0091,4.719,3.132)\"></path></g><g transform=\"matrix(.0091,0,0,-0.0091,8.013,3.132)\"></path></g></svg>)</span> at high flight Mach numbers (<span><svg height=\"11.8174pt\" style=\"vertical-align:-3.1815pt\" version=\"1.1\" viewbox=\"-0.0498162 -8.6359 21.7785 11.8174\" width=\"21.7785pt\" xmlns=\"http://www.w3.org/2000/svg\" xmlns:xlink=\"http://www.w3.org/1999/xlink\"><g transform=\"matrix(.013,0,0,-0.013,0,0)\"><use xlink:href=\"#g113-78\"></use></g><g transform=\"matrix(.013,0,0,-0.013,12.416,0)\"><use xlink:href=\"#g113-98\"></use></g><g transform=\"matrix(.0091,0,0,-0.0091,18.409,3.132)\"><use xlink:href=\"#g190-103\"></use></g></svg>).</span> For supersonic conditions, increasing the fuel-rich degree promotes greater fuel participation in combustion, thereby enhancing RBCC engine performance. Nevertheless, the subsonic-supersonic mixing layer exhibits low evolution, resulting in a decrease in reaction efficiency from 29.2% to 12.0% as the <svg height=\"8.68572pt\" style=\"vertical-align:-0.0498209pt\" version=\"1.1\" viewbox=\"-0.0498162 -8.6359 9.93839 8.68572\" width=\"9.93839pt\" xmlns=\"http://www.w3.org/2000/svg\" xmlns:xlink=\"http://www.w3.org/1999/xlink\"><g transform=\"matrix(.013,0,0,-0.013,0,0)\"><use xlink:href=\"#g113-150\"></use></g></svg> decreases from 3.2 to 1.6. Consequently, there is an inefficient utilization of fuel. To optimize RBCC engine performance, the rocket fuel-rich degree can be appropriately increased. However, this increase should be limited to prevent fuel wastage arising from low reaction efficiency. Under subsonic conditions (<span><svg height=\"11.8174pt\" style=\"vertical-align:-3.1815pt\" version=\"1.1\" viewbox=\"-0.0498162 -8.6359 32.873 11.8174\" width=\"32.873pt\" xmlns=\"http://www.w3.org/2000/svg\" xmlns:xlink=\"http://www.w3.org/1999/xlink\"><g transform=\"matrix(.013,0,0,-0.013,0,0)\"><use xlink:href=\"#g113-78\"></use></g><g transform=\"matrix(.013,0,0,-0.013,12.416,0)\"><use xlink:href=\"#g113-98\"></use></g><g transform=\"matrix(.0091,0,0,-0.0091,18.409,3.132)\"><use xlink:href=\"#g190-103\"></use></g><g transform=\"matrix(.013,0,0,-0.013,25.242,0)\"><use xlink:href=\"#g117-34\"></use></g></svg><span></span><span><svg height=\"11.8174pt\" style=\"vertical-align:-3.1815pt\" version=\"1.1\" viewbox=\"36.4551838 -8.6359 15.699 11.8174\" width=\"15.699pt\" xmlns=\"http://www.w3.org/2000/svg\" xmlns:xlink=\"http://www.w3.org/1999/xlink\"><g transform=\"matrix(.013,0,0,-0.013,36.505,0)\"><use xlink:href=\"#g113-49\"></use></g><g transform=\"matrix(.013,0,0,-0.013,42.745,0)\"><use xlink:href=\"#g113-47\"></use></g><g transform=\"matrix(.013,0,0,-0.013,45.709,0)\"><use xlink:href=\"#g113-58\"></use></g></svg>),</span></span> the low kinetic energy of captured air leads to the occurrence of “negative thrust surface” and “wall impact” phenomena, which hinder the efficient and stable operation of the RBCC engine. Consequently, adjusting the fuel-rich degree alone cannot promote specific impulse (<span><svg height=\"14.0004pt\" style=\"vertical-align:-5.3645pt\" version=\"1.1\" viewbox=\"-0.0498162 -8.6359 13.4272 14.0004\" width=\"13.4272pt\" xmlns=\"http://www.w3.org/2000/svg\" xmlns:xlink=\"http://www.w3.org/1999/xlink\"><g transform=\"matrix(.013,0,0,-0.013,0,0)\"><use xlink:href=\"#g113-74\"></use></g><g transform=\"matrix(.0091,0,0,-0.0091,4.719,3.132)\"><use xlink:href=\"#g190-116\"></use></g><g transform=\"matrix(.0091,0,0,-0.0091,8.013,3.132)\"><use xlink:href=\"#g190-113\"></use></g></svg>),</span> and a low fuel-rich degree is considered an ideal strategy when combined with adjustable nozzle technology.","PeriodicalId":13748,"journal":{"name":"International Journal of Aerospace Engineering","volume":"184 1","pages":""},"PeriodicalIF":1.1000,"publicationDate":"2024-02-06","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":"0","resultStr":null,"platform":"Semanticscholar","paperid":null,"PeriodicalName":"International Journal of Aerospace Engineering","FirstCategoryId":"5","ListUrlMain":"https://doi.org/10.1155/2024/4340688","RegionNum":4,"RegionCategory":"工程技术","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":null,"EPubDate":"","PubModel":"","JCR":"Q3","JCRName":"ENGINEERING, AEROSPACE","Score":null,"Total":0}
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Abstract

The ejector mode of the Rocket-Based Combined-Cycle (RBCC) engine is characterized by high fuel consumption. This study is aimed at investigating the influence of the rocket fuel-rich degree on the RBCC engine’s performance under the ejector mode combined with simultaneous mixing and combustion (SMC). Numerical simulations were conducted for various rocket mixing ratios () under subsonic () and supersonic () flight conditions. It was observed that a high fuel-rich degree in the rocket plume negatively impacts the eject performance under all conditions. However, it improves the overall performance () at high flight Mach numbers (). For supersonic conditions, increasing the fuel-rich degree promotes greater fuel participation in combustion, thereby enhancing RBCC engine performance. Nevertheless, the subsonic-supersonic mixing layer exhibits low evolution, resulting in a decrease in reaction efficiency from 29.2% to 12.0% as the decreases from 3.2 to 1.6. Consequently, there is an inefficient utilization of fuel. To optimize RBCC engine performance, the rocket fuel-rich degree can be appropriately increased. However, this increase should be limited to prevent fuel wastage arising from low reaction efficiency. Under subsonic conditions (), the low kinetic energy of captured air leads to the occurrence of “negative thrust surface” and “wall impact” phenomena, which hinder the efficient and stable operation of the RBCC engine. Consequently, adjusting the fuel-rich degree alone cannot promote specific impulse (), and a low fuel-rich degree is considered an ideal strategy when combined with adjustable nozzle technology.
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喷射器模式下 RBCC 发动机富燃料度影响的数值研究
火箭联合循环(RBCC)发动机的喷射器模式具有高燃料消耗的特点。本研究旨在探讨火箭燃料富集程度对 RBCC 发动机在喷射器模式下结合同步混合和燃烧(SMC)性能的影响。在亚音速()和超音速()飞行条件下,对不同火箭混合比()进行了数值模拟。结果表明,在所有条件下,火箭羽流中的高燃料富集度都会对喷射性能产生负面影响。然而,在高飞行马赫数()时,它能改善整体性能()。在超音速条件下,增加燃料富集度会促进更多燃料参与燃烧,从而提高 RBCC 发动机的性能。然而,亚音速-超音速混合层的演化程度较低,导致反应效率从 29.2% 下降到 12.0%,马赫数从 3.2 下降到 1.6。因此,燃料的利用效率很低。为了优化 RBCC 发动机的性能,可以适当提高火箭燃料的富集度。但是,这种增加应受到限制,以防止因反应效率低而造成燃料浪费。在亚音速条件下(),捕获空气的低动能会导致 "负推力面 "和 "撞壁 "现象的出现,从而阻碍 RBCC 发动机的高效稳定运行。因此,仅调整燃料富余度无法提高比冲(),而低燃料富余度被认为是与可调喷嘴技术相结合的理想策略。
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来源期刊
CiteScore
2.70
自引率
7.10%
发文量
195
审稿时长
22 weeks
期刊介绍: International Journal of Aerospace Engineering aims to serve the international aerospace engineering community through dissemination of scientific knowledge on practical engineering and design methodologies pertaining to aircraft and space vehicles. Original unpublished manuscripts are solicited on all areas of aerospace engineering including but not limited to: -Mechanics of materials and structures- Aerodynamics and fluid mechanics- Dynamics and control- Aeroacoustics- Aeroelasticity- Propulsion and combustion- Avionics and systems- Flight simulation and mechanics- Unmanned air vehicles (UAVs). Review articles on any of the above topics are also welcome.
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