航天推进技术研究院主办
[1]邓诗雨,金志光,柯玉祥.宽域组合发动机低速段冲压通道阻力特性[J].火箭推进,2022,48(06):44-51.
DENG Shiyu,JIN Zhiguang,KE Yuxiang.Drag characteristics of ramjet chanel of combined cycle engine at low speeds[J].Journal of Rocket Propulsion,2022,48(06):44-51.
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DENG Shiyu,JIN Zhiguang,KE Yuxiang.Drag characteristics of ramjet chanel of combined cycle engine at low speeds[J].Journal of Rocket Propulsion,2022,48(06):44-51.
宽域组合发动机低速段冲压通道阻力特性
《火箭推进》[ISSN:1672-9374/CN:CN 61-1436/V]
卷:
48
期数:
2022年06期
页码:
44-51
栏目:
目次
出版日期:
2022-12-25
- Title:
- Drag characteristics of ramjet chanel of combined cycle engine at low speeds
- 文章编号:
- 1672-9374(2022)06-0044-08
- 分类号:
- V431-34
- 文献标志码:
- A
- 摘要:
- 以双通道涡轮/冲压组合发动机为例,在不影响涡轮通道工作状况条件下,研究了低速段冲压通道富余气流处理方式对发动机阻力特性影响。采用动量定理与壁面积分两种方法对比了冲压通道开启与关闭两种方案下发动机总体受力情况,提出了一种冲压通道冷态尾喷管节流减阻措施。研究表明:两种受力分析方法结果一致,均能准确评估发动机受力 相比于冲压通道关闭、气流高速绕过发动机的情况,冲压通道开启状态下,进气道溢流阻力小,即富余高速气流经冲压通道减速后,直接排出发动机所产生的阻力更低,且来流马赫数越低,两种方案的阻力差距越大 此外,合理控制冲压通道下游尾喷管喉道面积,降低冲压通道内的流速对发动机总体有明显减阻效果, Ma∞=0.8、1.0时减阻最为明显,最高减阻54.0。
- Abstract:
- The effect of excess flow on drag characteristics of turbine based combined cycle engine was studied at low speeds, when the working conditions of the turbine channel were not affected.Both momentum theorem and wall force integral method were adopted to analyze the overall forces of an engine.By comparing the schemes of opening and closing ramjet channel, a drag reduction approach by adjusting the ramjet nozzle throat area in cold state was presented.The study indicates that the two analytical methods have consistent results, evaluating the force of engine accurately.The spillage drag is lower when the ramjet channel keeps open than closed.The drag will be further reduced when the high-speed surplus air was decelerated passing through ramjet channel, and the drag disparity between two schemes becomes greater when the incoming Mach number decreases.In addition, there are also significant drag reduction effect by controlling the downstream nozzle throat area and slowing down theair speed in ramjet channel.A maximum drag reduction of 54 was achieved at freestream Mach number 0.8 and 1.0.
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备注/Memo
收稿日期:2022-03-29 修回日期:2022-06-08
基金项目:1912项目
作者简介:邓诗雨(1998—),男,硕士,研究领域为内流气体动力学。
更新日期/Last Update:
1900-01-01