航天推进技术研究院主办
[1]张留欢,王君,马元,等.组合循环发动机轴对称环形可调喷管方案研究[J].火箭推进,2018,44(06):14-20.
ZHANG Liuhuan,WANG Jun,MA Yuan,et al.Study on adjustable axisymmetric annular nozzle of combined cycle propulsion system[J].Journal of Rocket Propulsion,2018,44(06):14-20.
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ZHANG Liuhuan,WANG Jun,MA Yuan,et al.Study on adjustable axisymmetric annular nozzle of combined cycle propulsion system[J].Journal of Rocket Propulsion,2018,44(06):14-20.
组合循环发动机轴对称环形可调喷管方案研究
《火箭推进》[ISSN:1672-9374/CN:CN 61-1436/V]
卷:
44
期数:
2018年06期
页码:
14-20
栏目:
研究与设计
出版日期:
2018-12-31
- Title:
- Study on adjustable axisymmetric annular nozzle of combined cycle propulsion system
- 文章编号:
- 1672-9374(2018)06-0014-07
- 分类号:
- V430-34
- 文献标志码:
- A
- 摘要:
- 针对组合循环发动机双流道轴对称环形喷管提出了一种可调方案,开展了特定工况下喷管三维流场数值仿真,与固定喷管、无扩张段喷管进行了对比。结果表明,通过环形喷管特定型面外壁沿轴向前后移动,可实现喷管喉部面积、面积膨胀比的连续调节,有效提高喷管推力性能; 在Ma2～5典型工况下,可调喷管推力系数均大于0.93,最高约0.974; 固定喷管在非设计点无法匹配发动机需求,可调喷管由于可调节喷管喉部面积,其流量可做到与发动机上游流量准确匹配。采用固定喷管,其流量相对可调喷管最大偏差可达50.6%; 环形可调喷管推力系数总体高于固定喷管和无扩张段喷管。相同工况下,可调喷管较固定喷管推力系数提高最高约31%,较无扩张段喷管推力系数提高最高约14.6%。
- Abstract:
- One new scheme about adjustable axisymmetric annular nozzle for dual flow path of CCP(combined cycle propulsion)system is presented in this study.The numerical simulation of nozzle's 3D flow field at specific operating conditions was carried out, and a comparison with fixed nozzle and nozzle without diverging part was done.The results show that the continuous adjustment of throat area and expansion ratio of the area can be achieved by driving the external cowl to move along the axial direction, which can improve the thrust performance of the nozzle effectively.The thrust coefficients of the adjustable nozzles are above 0.93 and even reaches 0.974 under the typical conditions of Ma 2～5.The fixed nozzle can't satisfied the need of engine at the off-design point, but mass flow rate of the adjustable nozzle can match the mass flow rate upstream of engine precisely due to its adjustable throat area.The maximum deviation of mass flow rate between the fixed nozzle and adjustable nozzle can reach 50.6%.The thrust coefficient of adjustable annular nozzle is higher than that of the fixed nozzle and the nozzle without diverging part.Under the same flight condition, the thrust coefficient of adjustable nozzle is 31% higher than the fixed nozzle, and 14.6% higher than the nozzle without diverging part.
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备注/Memo
收稿日期:2017-05-20; 修回日期:2018-07-04 基金项目: 装备预研航天科技联合基金(6141B0606260401) 作者简介: 张留欢(1986—),男,工程师,研究领域为组合推进系统气动热力技术
更新日期/Last Update:
2018-12-25