脉冲爆震驱动下涡轮流场的非定常特征研究

刘俊余; 王治武; 李俊林; 张子旭

doi:10.13224/j.cnki.jasp.20230490

脉冲爆震驱动下涡轮流场的非定常特征研究

doi: 10.13224/j.cnki.jasp.20230490

刘俊余^1,,
王治武^{1, 2,*, ,},
李俊林¹,
张子旭¹

1.
西北工业大学动力与能源学院，西安 710072
2.
西北工业大学深圳研究院，广东深圳 518057

基金项目: 国家自然科学基金（12372338，U2241272）；陕西省自然科学基金（2023-JCYB-352，2022JZ-20）；广东省基础与应用基础研究基金（2023A1515011663）

详细信息

作者简介:
刘俊余（1997-），男，硕士，主要从事脉冲爆震燃烧室与轴流涡轮的匹配研究。E-mail：ljynwpu@163.com

通讯作者:
王治武（1981-），男，教授，博士，研究领域为燃烧与流动、爆震推进等。E-mail：malsoo@mail.nwpu.edu.cn

中图分类号: V231.2
计量
- 文章访问数: 456
- HTML浏览量: 269
- PDF量: 44
- 被引次数: 0
出版历程
- 收稿日期: 2023-07-28
- 网络出版日期: 2024-06-23

Unsteady characteristics of turbine flow field driven by pulse detonation

LIU Junyu^1
,,
WANG Zhiwu^{1, 2,*
, ,},
LI Junlin¹,
ZHANG Zixu¹

1.
School of Power and Energy，Northwestern Polytechnical University，Xi’an 710072，China
2.
Shenzhen Research Institute，Northwestern Polytechnical University，Shenzhen Guangdong 518057，China

摘要

摘要:
为了揭示脉冲爆震的非定常性对涡轮流场的影响，建立了GE-E³两级高压涡轮的三维数值模型，以研究爆震驱动下涡轮的流场特征。对50%叶高处的基元级流动进行分析，对动叶表面的分离流动以及叶顶间隙的泄漏流动进行了研究。结果表明：前导激波驱动燃气以超声速流过涡轮流道，导致燃气在叶栅斜切口出现了明显的超声速斜切口膨胀以及叶栅外的自由膨胀。前导激波与叶片相互作用会造成气流攻角的大幅变化，并产生多处局部逆压梯度，导致叶片表面出现严重的流动分离。此外，前导激波作用于动叶会增大叶顶间隙两侧的压差，使得间隙泄漏流量急剧增大，这增强了泄漏流与主流的剪切和掺混，导致主流区出现明显的熵增。
- 脉冲爆震涡轮发动机 /
- 轴流涡轮 /
- 基元级流动 /
- 分离流动 /
- 叶顶泄漏流动
Abstract:
To reveal the influence of the pulse detonation unsteady characteristics on the turbine flow field, a three-dimensional numerical model of the GE-E³ two-stage high pressure turbine was established. The detonation chamber outlet parameters were used as the boundary conditions of the turbine inlet to study the turbine flow driven by detonation. The elementary flow at 50% blade height was analyzed, and then the separation flow on the blade surface and the leakage flow in the tip clearance were studied. The results showed that the gas flow ran at supersonic speeds through the turbine channel, resulting in obvious oblique incision expansion and free expansion outside the cascade. The interaction between the leading shock and the blade changed the airflow attack angle significantly and produced local adverse pressure gradients, resulting in severe flow separation on the blade surface. The leading shock acting on the rotor blade increased the pressure difference on both sides of the tip clearance, and enhanced shearing and mixing between the leakage flow and the mainstream, resulting in a significant increase in entropy in the mainstream area.
- pulse detonation turbine engine /
- axial turbine /
- elementary stage flow /
- separation flow /
- tip leakage flow

HTML

图 1 GE-E³两级高压涡轮几何模型及网格划分

Figure 1. GE-E³ two-stage high pressure turbine geometry model and meshing

下载: 全尺寸图片幻灯片

图 2 爆震驱动下涡轮入口参数随时间的变化

Figure 2. Variation of turbine inlet parameters with time under detonation driving

下载: 全尺寸图片幻灯片

图 3 不同网格尺寸划分下第一级动叶叶顶间隙泄漏流线

Figure 3. Rotor 1 tip clearance leakage streamline under different mesh sizes

下载: 全尺寸图片幻灯片

图 4 数值模拟与试验参数的对比

Figure 4. Comparison of simulation and experimental results

下载: 全尺寸图片幻灯片

图 5 50%叶高处的基元级温度分布随时间的变化

Figure 5. Temperature of elementary stage with 50% blade height changes with time

下载: 全尺寸图片幻灯片

图 6 50%叶高处的基元级相对马赫数分布随时间的变化

Figure 6. Relative Mach number of elementary stage with 50% blade height changes with time

下载: 全尺寸图片幻灯片

图 7 动叶入口气流角和速度三角形示意图

Figure 7. Inlet flow angle and velocity triangle of rotor blade

下载: 全尺寸图片幻灯片

图 8 两级动叶的入口平均相对气流角和相对速度

Figure 8. Average inlet relative flow angle and relative velocity of two-stage rotor blades

下载: 全尺寸图片幻灯片

图 9 前导激波与作用于第一级动叶的相对速度和流线分布

Figure 9. Relative velocity and streamline distribution under the interaction between leading shock wave and Rotor 1

下载: 全尺寸图片幻灯片

图 10 第一级动叶压力面和吸力面处的极限流线

Figure 10. Limiting streamlines at the pressure and suction surfaces of Rotor 1

下载: 全尺寸图片幻灯片

图 11 前导激波作用下第一级动叶叶顶间隙中部的流线和压力分布

Figure 11. Streamline and pressure distribution in the middle of Rotor 1 tip clearance under the action of leading shock wave

下载: 全尺寸图片幻灯片

图 12 两级动叶的泄漏流量随时间的变化

Figure 12. Variation of leakage flow rate of two-stage rotor with time

下载: 全尺寸图片幻灯片

图 13 前导激波作用下第一级动叶50%弦长处的熵与流线

Figure 13. Entropy and streamline at 50% chord of Rotor 1 under leading shock

下载: 全尺寸图片幻灯片

图 14 前导激波作用下第一级动叶机匣端区的轴向涡量

Figure 14. Axial vorticity in the end region of Rotor 1 casing under the action of leading shock wave

下载: 全尺寸图片幻灯片

表 1 试验工况下涡轮性能参数的对比

Table 1. Comparison of turbine performance parameters under test conditions

参数试验结果数值结果

涡轮效率/% 92.53 93.33
落压比 5.014 4.969
流量/（kg/s） 11.80 12.54
功率/kW 2973 3066

下载: 导出CSV

表 2 两级动叶的总压恢复系数

Table 2. Total pressure recovery coefficient of two-stage rotor

工况条件总压恢复系数
第一级动叶处第二级动叶处

爆震驱动 0.81 0.87
NASA试验 0.94 0.96

下载: 导出CSV

参考文献(30)

[1]	LIU Yize,SUN Xiaoxiao,SETHI V,et al. Review of modern low emissions combustion technologies for aero gas turbine engines[J]. Progress in Aerospace Sciences,2017,94: 12-45. doi: 10.1016/j.paerosci.2017.08.001
[2]	KHANDELWAL B,KARAKURT A,SEKARAN P R,et al. Hydrogen powered aircraft: the future of air transport[J]. Progress in Aerospace Sciences,2013,60: 45-59. doi: 10.1016/j.paerosci.2012.12.002
[3]	LEE H S. The detonation phenomenon[M]. Cambridge,UK: Cambridge University Press,2008.
[4]	严传俊,范玮. 脉冲爆震发动机原理及关键技术[M]. 西安: 西北工业大学出版社,2005. YAN Chuanjun,FAN Wei. Principle and key technology of pulse detonation engine[M]. Xi’an: Northwestern Polytechnical University Press,2005 (in Chinese YAN Chuanjun, FAN Wei. Principle and key technology of pulse detonation engine[M]. Xi’an: Northwestern Polytechnical University Press, 2005 (in Chinese)
[5]	BHATTRAI S,TANG Hao. Comparative performance analysis of combined-cycle pulse detonation turbofan engines (PDTEs)[J]. Propulsion and Power Research,2013,2(3): 214-224. doi: 10.1016/j.jppr.2013.04.007
[6]	CHEN Wenjuan,FAN Wei,QIU Hua,et al. Thermodynamic performance analysis of turbofan engine with a pulse detonation duct heater[J]. Aerospace Science and Technology,2012,23(1): 206-212. doi: 10.1016/j.ast.2011.07.002
[7]	何龙,郑龙席,邱华,等. 脉冲爆震涡轮发动机性能计算[J]. 推进技术,2012,33(5): 665-670. HE Long,ZHENG Longxi,QIU Hua,et al. Calculating performance of pulse detonation turbo engine[J]. Journal of Propulsion Technology,2012,33(5): 665-670. (in Chinese HE Long, ZHENG Longxi, QIU Hua, et al. Calculating performance of pulse detonation turbo engine[J]. Journal of Propulsion Technology, 2012, 33(5): 665-670. (in Chinese)
[8]	邱华,徐泽阳,郑龙席,等. 脉冲爆震涡轮发动机增推装置性能试验[J]. 航空学报,2016,37(2): 522-532. QIU Hua,XU Zeyang,ZHENG Longxi,et al. Tests of pulse detonation turbine engine performance with thrust augmentation devices[J]. Acta Aeronautica et Astronautica Sinica,2016,37(2): 522-532. (in Chinese QIU Hua, XU Zeyang, ZHENG Longxi, et al. Tests of pulse detonation turbine engine performance with thrust augmentation devices[J]. Acta Aeronautica et Astronautica Sinica, 2016, 37(2): 522-532. (in Chinese)
[9]	DENG Junxiang,YAN Chuanjun,ZHENG Longxi,et al. Performance evaluation of hybrid gas turbine engine embedded with pulse detonation combustor[J]. International Journal of Turbo and Jet Engines,2011,28(3): 237-246.
[10]	LU Jie,ZHENG Longxi,WANG Zhiwu,et al. Experimental investigation on interactions between a two-phase multi-tube pulse detonation combustor and a centrifugal compressor[J]. Applied Thermal Engineering,2017,113: 426-434. doi: 10.1016/j.applthermaleng.2016.10.188
[11]	李晓丰,郑龙席,邱华,等. 脉冲爆震涡轮发动机原理性试验研究[J]. 实验流体力学,2013,27(6): 1-5. LI Xiaofeng,ZHENG Longxi,QIU Hua,et al. Experimental study on the principle of pulse detonation turbine engine[J]. Journal of Experiments in Fluid Mechanics,2013,27(6): 1-5. (in Chinese LI Xiaofeng, ZHENG Longxi, QIU Hua, et al. Experimental study on the principle of pulse detonation turbine engine[J]. Journal of Experiments in Fluid Mechanics, 2013, 27(6): 1-5. (in Chinese)
[12]	RASHEED A,FURMAN A,DEAN A. Experimental investigations of an axial turbine driven by a multi-tube pulsed detonation combustor system: AIAA2005-4209 [R]. Reston,US: the 41st AIAA Joint Propulsion Conference and Exhibit,2005.
[13]	RASHEED A,FURMAN A H,DEAN A J. Experimental investigation of the performance of a multitube pulse detonation turbine system[J]. Journal of Propulsion and Power,2011,27(3): 586-596. doi: 10.2514/1.B34013
[14]	FROLOV S M,SMETANYUK V A,GUSEV P A,et al. How to utilize the kinetic energy of pulsed detonation products?[J]. Applied Thermal Engineering,2019,147: 728-734. doi: 10.1016/j.applthermaleng.2018.10.102
[15]	QIU Hua,XIONG Cha,ZHENG Longxi. Experimental investigation of an air-breathing pulse detonation turbine prototype engine[J]. Applied Thermal Engineering,2016,104: 596-602. doi: 10.1016/j.applthermaleng.2016.05.077
[16]	GLASER A,CALDWELL N,GUTMARK E. Performance of an axial flow turbine driven by multiple pulse detonation combustors: AIAA2007-1244[R]. Reston,US: the 45th AIAA Aerospace Sciences Meeting and Exhibit,2007.
[17]	FERNELIUS M H,GORRELL S E. Mapping efficiency of a pulsing flow-driven turbine[J]. Journal of Fluids Engineering,2020,142(6): 061202.1-061202.9.
[18]	St GEORGE A,DRISCOLL R,GUTMARK E,et al. Experimental comparison of axial turbine performance under steady and pulsating flows[J]. Journal of Turbomachinery,2014,136(11): 111005.1-111005.11.
[19]	ANAND V,St GEORGE A,KNIGHT E,et al. Investigation of pulse detonation combustors: axial turbine system[J]. Aerospace Science and Technology,2019,93: 105350.1-105350.13.
[20]	LI Xiaofeng,ZHENG Longxi,QIU Hua,et al. Experimental investigations on the power extraction of a turbine driven by a pulse detonation combustor[J]. Chinese Journal of Aeronautics,2013,26(6): 1353-1359. doi: 10.1016/j.cja.2013.07.015
[21]	VAN ZANTE D,ENVIA E,TURNER M G. The attenuation of a detonation wave by an aircraft engine axial turbine[C]//Preceedings of 18th International Society for Air Breathing Engines (ISABE) Conference. Beijing: ISABE,2007: 1-12.
[22]	邓芃,郑龙席,王凌羿. 脉冲爆震燃烧室与冲击式涡轮匹配机理及效率的数值研究[J]. 航空动力学报,2018,33(8): 1864-1871. DENG Peng,ZHENG Longxi,WANG Lingyi. Numerical study on matching mechanism and efficiency of pulse detonation combustor and impulse turbine[J]. Journal of Aerospace Power,2018,33(8): 1864-1871. (in Chinese DENG Peng, ZHENG Longxi, WANG Lingyi. Numerical study on matching mechanism and efficiency of pulse detonation combustor and impulse turbine[J]. Journal of Aerospace Power, 2018, 33(8): 1864-1871. (in Chinese)
[23]	李晓丰,肖俊峰,胡孟起,等. 脉冲爆震燃气膨胀过程及能量转换难易度评价方法[J]. 航空动力学报,2021,36(8): 1586-1593. LI Xiaofeng,XIAO Junfeng,HU Mengqi,et al. Pulse detonation gas expansion process and evaluation method of energy conversion difficulty degree[J]. Journal of Aerospace Power,2021,36(8): 1586-1593. (in Chinese LI Xiaofeng, XIAO Junfeng, HU Mengqi, et al. Pulse detonation gas expansion process and evaluation method of energy conversion difficulty degree[J]. Journal of Aerospace Power, 2021, 36(8): 1586-1593. (in Chinese)
[24]	NANGO A,INABA K,KOJIMA T,et al. Numerical study on single-stage axial turbine with pulse detonation combustor: AIAA2009-294 [R]. Reston,US: the 47th AIAA Aerospace Sciences Meeting including the New Horizons Forum and Aerospace Exposition,2009.
[25]	XISTO C,PETIT O,GRÖNSTEDT T,et al. The efficiency of a pulsed detonation combustor-axial turbine integration[J]. Aerospace Science and Technology,2018,82/83: 80-91. doi: 10.1016/j.ast.2018.08.038
[26]	LIU Junyu,WANG Zhiwu,QIN Weifeng,et al. Effects of detonation initial conditions on performance of pulse detonation chamber-axial turbine combined system[J]. Energy,2023,278: 127765.1-127765. 12.
[27]	TIMKO L P. Energy efficient engine high pressure turbine component test performance report[R]. Cleveland,US: NASA Lewis Research Center,1984.
[28]	BINDON J P. The measurement and formation of tip clearance loss[J]. Journal of Turbomachinery,1989,111(3): 257-263. doi: 10.1115/1.3262264
[29]	崔晟,苏纬仪,孙斐,等. E³高压涡轮三维流场快速预测方法研究[J]. 推进技术,2022,43(11): 59-71. CUI Sheng,SU Weiyi,SUN Fei,et al. Rapid prediction method of three dimensional flow field for E³ high pressure turbine[J]. Journal of Propulsion Technology,2022,43(11): 59-71. (in Chinese CUI Sheng, SU Weiyi, SUN Fei, et al. Rapid prediction method of three dimensional flow field for E³ high pressure turbine[J]. Journal of Propulsion Technology, 2022, 43(11): 59-71. (in Chinese)
[30]	向欢. 涡轮内部非定常流动机理及应用研究[D]. 南京: 南京航空航天大学,2013. XIANG Huan. Mechanism and application research of unsteady flows in gas turbine[D]. Nanjing: Nanjing University of Aeronautics and Astronautics,2013. (in Chinese XIANG Huan. Mechanism and application research of unsteady flows in gas turbine[D]. Nanjing: Nanjing University of Aeronautics and Astronautics, 2013. (in Chinese)