脉冲爆震燃气冲击下涡轮性能及其优化策略研究进展

郑龙席; 刘可心; 卢杰; 肖治邑; 黄康

doi:10.13224/j.cnki.jasp.20240471

脉冲爆震燃气冲击下涡轮性能及其优化策略研究进展

doi: 10.13224/j.cnki.jasp.20240471

郑龙席¹,
刘可心^1,,
卢杰¹,
肖治邑¹,
黄康^2,*, ,

1.
西北工业大学动力与能源学院，西安 710072
2.
中国空气动力研究与发展中心空天技术研究所，四川绵阳 621000

基金项目: 跨域飞行交叉技术实验室开放课题（2024-KF-02208）；中国航天基金会空天动力公益专项基金（KDJJ20230402010）

详细信息

作者简介:
郑龙席（1970-），男，教授、博士生导师，博士，主要从事新概念航空发动机燃烧与流动研究

通讯作者:
黄康（1986-），男，高级工程师，博士，主要从事航空动力机械的设计、仿真及应用的研究。E-mail：huangkang@cardc.cn

中图分类号: V235
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出版历程
- 收稿日期: 2024-07-12
- 网络出版日期: 2025-04-04

Research progress on turbine performance and optimization strategy under pulse detonation gas impact

ZHENG Longxi¹,
LIU Kexin^1
,,
LU Jie¹,
XIAO Zhiyi¹,
HUANG Kang^{2,*
, ,}

1.
School of Power and Energy，Northwestern Polytechnical University，Xi’an 710072，China
2.
Aerospace Technology Institute，China Aerodynamics Research and Development Center，Mianyang Sichuan 621000，China

摘要

摘要:
脉冲爆震燃烧室出口强非稳态燃气对涡轮性能有显著影响，脉冲爆震燃烧室与涡轮部件匹配问题是制约脉冲爆震涡轮发动机研制的难点之一。鉴于此，为了理清脉冲爆震燃气冲击下涡轮性能及其优化策略的研究进展，以脉冲爆震燃烧室排气特性为切入点，简要介绍了排气流场的流动特征和演化过程。然后，从理论分析、实验测试和数值仿真这3个方面，总结归纳了脉冲爆震燃气冲击下的涡轮性能评估方法、涡轮工作特性、涡轮内部流动特性及损失机理等关键问题的研究现状。在此基础上，提出了脉冲爆震燃气冲击下涡轮性能的优化策略，包括稳压装置、激波衰减装置、涡轮叶型优化设计等，并指出多种优化策略的有机融合是未来的研究方向之一。最后，梳理了西北工业大学在脉冲爆震燃烧室与涡轮部件匹配领域的研究成果，并展望了该领域仍有待突破的关键问题。
- 脉冲爆震涡轮发动机 /
- 脉冲爆震燃烧燃气 /
- 涡轮性能 /
- 优化策略 /
- 非稳态能量利用
Abstract:
The intensely unsteady exhaust flow from pulse detonation combustor has a significant impact on turbine performance. The matching problem between pulse detonation combustor and turbine components is one of the difficulties restricting the development of pulse detonation turbine engine. In order to clarify the research progress on turbine performance and optimization strategies under pulse detonation gas impact, the flow characteristics and evolution process of exhaust flow field were briefly introduced with the pulse detonation combustor exhaust characteristics as the starting point. From the aspects of theoretical analysis, experimental testing and numerical simulation, the research status of key issues such as turbine performance evaluation methods, turbine operating characteristics, turbine internal flow characteristics and loss mechanism under pulse detonation gas impact was summarized. The research achievements of Northwestern Polytechnical University in the field of pulse detonation combustor and turbine component matching were reviewed, and the key problems to be solved in this field were prospected. Optimization strategies for turbine performance under pulse detonation gas impact were proposed, including stabilized pressure device, shock attenuation device, and turbine blade optimization design, etc. This indicates that the organic integration of various optimization strategies is one of the future research directions.
- pulse detonation turbine engine /
- pulse detonation gas /
- turbine performance /
- optimization strategy /
- unsteady energy utilization

HTML

图 1 PDC排气流场的流动特征和发展演化过程^[15-16]

Figure 1. Detailed flow characteristics and evolution process of the exhaust flow field of PDC^[15-16]

下载: 全尺寸图片幻灯片

图 2 脉冲爆震驱动涡轮的非定常模型示意图^[30]

Figure 2. Schematic of unsteady model for a pulse detonation driven turbine^[30]

下载: 全尺寸图片幻灯片

图 3 基于质量流量平均获得的一个循环周期内转子攻角的变化情况^[72]

Figure 3. Time-history of mass flow rate-weighted averaged rotor incidence angle over a duty^[72]

下载: 全尺寸图片幻灯片

图 4 涡轮进、出口参数的相位平移现象^[69]

Figure 4. Phase shift between turbine inlet and outlet parameters^[69]

下载: 全尺寸图片幻灯片

图 5 带稳压腔的多管PDC实验台示意图^[73]

Figure 5. Sketch of a multi-tube PDC test rig with a plenum^[73]

下载: 全尺寸图片幻灯片

图 6 激波分配器内部激波的相互作用^[78-79]

Figure 6. Interaction of shock waves in shock divider^[78-79]

下载: 全尺寸图片幻灯片

图 7 基于自适应代理模型和CSM方法的优化框架^[83]

Figure 7. Optimization framework based on adaptive surrogate model and complex shape method^[83]

下载: 全尺寸图片幻灯片

图 8 西北工业大学PDTE原理性实验系统^[89]

Figure 8. Experimental setup of PDCE designed by Northwestern Polytechnical University^[89]

下载: 全尺寸图片幻灯片

表 1 真实脉冲爆震来流和模拟脉冲爆震来流的涡轮性能实验台概况一览表

Table 1. List of turbine performance test rig for real pulse detonation gas and simulated pulse detonation gas

研究机构	脉动气流来源	管数	涡轮类型	工作频率/Hz	代表性工作/结论
GE全球研究中心★^[38-43]	PDC	8	单级轴流涡轮	30	脉冲爆震燃气冲击下与等压燃烧驱动下的涡轮效率几乎相同
辛辛那提大学★^[44-48]	PDC	6	轴流动力涡轮	20	涡轮效率和单位功率随PDC填充系数和燃油当量比的增加而增加
赖特-帕特森空军基地^[49-52]	PDC	4	径流涡轮	10～30	PDC驱动下的涡轮单位输出功相比等压燃烧提高了41.3%
辛辛那提大学^[53-56]	PDC	6	单级轴流涡轮	5～20	涡轮性能主要与校正后的质量流量和转子攻角有关
杨百翰大学^[57-61]	旋转球阀	6	单级轴流涡轮	10～40	压力脉动幅值是导致涡轮效率下降的主要原因，攻角变化是根本原因
柏林工业大学^[62-65]	电磁阀	7	单级轴流涡轮	< 20	探索了极值搜索控制等方法用于减轻涡轮进口压力波动的可行性
注：★表示在涡轮前有旁路空气与PDC排气进行掺混。

下载: 导出CSV

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