航天推进技术研究院主办
[1]南向军,李斌,何国强,等.RBCC发动机冲压模态热力循环分析[J].火箭推进,2022,48(06):17-25.
NAN Xiangjun,LI Bin,HE Guoqiang,et al.Analysis on thermodynamic cycle of scramjet mode for RBCC engine[J].Journal of Rocket Propulsion,2022,48(06):17-25.
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NAN Xiangjun,LI Bin,HE Guoqiang,et al.Analysis on thermodynamic cycle of scramjet mode for RBCC engine[J].Journal of Rocket Propulsion,2022,48(06):17-25.
RBCC发动机冲压模态热力循环分析
《火箭推进》[ISSN:1672-9374/CN:CN 61-1436/V]
卷:
48
期数:
2022年06期
页码:
17-25
栏目:
目次
出版日期:
2022-12-25
- Title:
- Analysis on thermodynamic cycle of scramjet mode for RBCC engine
- 文章编号:
- 1672-9374(2022)06-0017-09
- 分类号:
- V231
- 文献标志码:
- A
- 摘要:
- 为了研究RBCC发动机的真实工作情况,基于地面试验数据,建立了一维性能分析模型,对发动机4 Ma、6 Ma冲压模态不同余气系数条件的性能进行了计算,与试验结果进行了对比,获得了发动机沿程气流参数分布。利用计算结果构建了发动机热力循环,分析了余气系数对循环效率、推进效率等性能参数的影响,提出了有效能产生率的概念,研究了余气系数对有效能产生率的影响以及有效能损失的途径。研究表明,建立的一维分析模型可以较好地计算发动机推力性能,与试验测量误差在10以内 发动机真实热力循环并非严格的等压释热,其有效能产生率在0.5～0.7之间 提高有效能产生率和减少排气中的有效能是发动机性能优化的主要方向。
- Abstract:
- In order to study the real working condition of RBCC engine, based on the ground test data, an one dimensional analysis model was established to calculate the performance of engine scramjet mode at different residual air coefficient of 4 Ma and 6 Ma conditions.Compared with the test results, the distribution of flow parameters along the engine was obtained.The thermodynamic cycle of engine was conducted by using the calculation results, and the influence of residual gas coefficient on the cycle efficiency and propulsion efficiency was analyzed.The concept of exergy generation rate was put forward, and the effect of residual gas coefficient on exergy generation rate and loss paths of exergy were studied.Research shows that the one dimensional performance analysis model can calculate the engine thrust performance well, and the error is less than 10.The real thermal cycle of the engine is not strict isobaric heat release, and its exergy generation rate is between 0.5-0.7.Improving the exergy generation rate and reducing the exergy of exhaust are the main directions for optimizing the engine performance.
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备注/Memo
收稿日期:2022-02-05 修回日期:2022-03-08
作者简介:南向军(1985—),男,博士,工程师,研究领域为火箭基组合循环发动机。
更新日期/Last Update:
1900-01-01