分流板与侧壁缝隙对TBCC排气系统性能影响研究

张世杰; 葛建辉; 马钊; 徐惊雷

doi:10.13700/j.bh.1001-5965.2022.0842

分流板与侧壁缝隙对TBCC排气系统性能影响研究

doi: 10.13700/j.bh.1001-5965.2022.0842

1.
南京航空航天大学能源与动力学院，南京 210016
2.
中国航发四川燃气涡轮研究院，绵阳 621000

基金项目: 国家科技重大专项(2019-II-0007-0027)；中国博士后科学基金(2022M721598)

详细信息

通讯作者:
E-mail：xujl@nuaa.edu.cn

中图分类号: V231.3
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出版历程
- 收稿日期: 2022-10-10
- 录用日期: 2023-01-17
- 网络出版日期: 2023-02-15
- 整期出版日期: 2024-11-30

Influence of gap between splitter plate and side wall on performance of TBCC exhaust system

1.
College of Energy and Power Engineering，Nanjing University of Aeronautics and Astronautics，Nanjing 210016，China
2.
AECC Sichuan Gas Turbine Establishment，Mianyang 621000，China

Funds: National Science and Technology Major Project of the Ministry of Science and Technology of China (2019-II-0007-0027); China Postdoctoral Science Foundation (2022M721598)

More Information

Corresponding author: E-mail：xujl@nuaa.edu.cn

摘要

摘要:
为研究涡轮基组合循环(TBCC)排气系统的分流板与侧壁之间的缝隙对其性能的影响，利用数值仿真方法研究不同缝隙长度和宽度下喷管性能参数变化规律，针对涡轮通道和冲压通道在不同工作状态下有无缝隙对喷管性能的影响进行研究。结果表明，在喷管双通道均为欠膨胀状态时，分流板与侧壁之间存在缝隙漏气的情况下，对于漏出气体的涡轮通道，随着缝隙长度的增加，其推力系数下降、升力增加，而冲压通道推力系数几乎无变化，但升力增加。缝隙宽度变化对喷管性能的影响与长度的影响规律一致。此外，通过对不同喷管工作状态的研究发现，缝隙的存在会降低推力系数，缝隙的相对宽度为0.033、相对长度为0.31时，2.8%的漏气量能造成超过1%的推力系数的损失。
- 涡轮基组合循环 /
- 分流板 /
- 缝隙 /
- 漏气 /
- 推力系数
Abstract:
In order to study the influence of the gap between splitter plate and side wall of a turbine-based combined cycle (TBCC) exhaust system on its performance, the numerical simulation method was used to analyze the influence of different gap lengths and widths on the performance parameters of the nozzle. Then, the influence of whether there was a gap between the turbine channel and the stamping channel under different working conditions on the nozzle performance was studied. The results show that when two channels of the nozzle are under-expanded, there is a gap between splitter plate and side wall. For the turbine channel with gas leakage, the thrust coefficient of the turbine channel decreases, and the lift increases with the increase in the gap length, while the thrust coefficient of the stamping channel has almost no change, but the lift increases. In addition, the influence of gap width change on nozzle performance is consistent with that of length. The research on different nozzle working conditions finds that the existence of gaps always reduces the thrust coefficient. When the relative width and length of the gap are 0.033 and 0.31, 2.8% of the gas leakage can cause more than 1% loss of the thrust coefficient.
- turbine based combined cycle /
- splitter plate /
- gap /
- gas leakage /
- thrust coefficient

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图 1 单边膨胀喷管控制体示意

Figure 1. Control body diagram for single-sided expansion nozzle

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图 2 喷管构型

Figure 2. Structure of nozzle

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图 3 二次流喷射喷管计算网格

Figure 3. Calculation grid of nozzle for secondary flow jet

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图 4 数值仿真与试验的壁面压力分布结果对比

Figure 4. Comparison of wall pressure distribution results between numerical simulation and test results

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图 5 对称面处喷管构型

Figure 5. Nozzle configuration at symmetric plane

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图 6 计算网格和边界条件设置

Figure 6. Calculation grid and boundary condition setting

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图 7 不同网格尺度下涡轮通道上膨胀面的压力分布

Figure 7. Pressure distribution on upper expansion plane of turbine channel at different grid scales

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图 8 分流板与侧壁间缝隙结构示意

Figure 8. Schematic diagram of the gap structure between splitter plate and the sidewall

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图 9 喷管三维计算网格

Figure 9. Three-dimensional calculation grid of nozzle

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图 10 分流板缝隙漏气长度对喷管升力、推力系数的影响

Figure 10. Effect of gas leakage length of splitter plate on nozzle lift and thrust coefficient of nozzle

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图 11 涡轮通道声速线

Figure 11. Sonic line of turbine channel

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图 12 分流板漏气位置处的流动情况

Figure 12. Flow at gas leakage position

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图 13 缝隙中心截面处的马赫数云图

Figure 13. Mach number cloud map at center of gap

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图 14 不同长度工况下缝隙中心位置处涡轮通道上膨胀面压力分布

Figure 14. Pressure distribution on upper expansion plane of turbine channel at center of gap under different length condition

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图 15 不同长度工况下缝隙中心位置处分流板上壁面压力分布

Figure 15. Pressure distribution on upper wall of splitter plate at center of gap under different length condition

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图 16 分流板缝隙漏气宽度对喷管升力、推力系数的影响

Figure 16. Effect of gas leakage width of splitter plate on nozzle lift and thrust coefficient of nozzle

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图 17 不同宽度的分流板缝隙中心位置处的马赫数云图

Figure 17. Mach number nephogram at the center of the gap in the splitter plate with different widths

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图 18 不同宽度工况下缝隙中心截面上涡轮通道上膨胀面的压力分布

Figure 18. Pressure distribution on upper expansion plane of turbine channel at center of gap under different width condition

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图 19 不同宽度工况下缝隙中心截面上分流板上壁面的压力分布

Figure 19. Pressure distribution on upper wall of splitter plate at center of gap under different width condition

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图 20 分流板上壁面压力提取位置

Figure 20. Extraction position of upper wall pressure of splitter plate

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图 21 分流板上壁面不同位置的压力分布

Figure 21. Pressure distribution at different positions of upper wall of splitter plate

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图 22 缝隙中心面上的二维流线图

Figure 22. Two-dimensional streamlines on center surface of gap

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表 1 组合喷管边界条件参数

Table 1. Parameter setting of boundary condition of combined nozzle

$P_{\mathrm{tur}}^* $/kPa	$P_{\mathrm{ram}}^* $/kPa	$T_{\mathrm{tur}}^* $/K	$T_{\mathrm{ram}}^* $/K	H/km
185.0	145.0	2 072	1 397	16.8

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表 2 不同分流板缝隙长度下的漏气量

Table 2. Gas leakage under different gap lengths of splitter plate

漏气长度l/L_s	结构	流量/（kg·s⁻¹）	漏气量（相对于涡轮流量）/%
0	涡轮	0.141 7	0
0	冲压	0.065 2	0
0.24	涡轮	0.142 0	1.54
0.24	冲压	0.065 1	1.54
0.31	涡轮	0.142 7	2.12
0.31	冲压	0.065 1	2.12
0.51	涡轮	0.145 6	3.99
0.51	冲压	0.065 1	3.99
注：漏气量=泄漏量/涡轮流量×100%。

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表 3 喷管各通道壁面压力积分

Table 3. Pressure integral of each part of nozzle N

部位	l/L_s=0		l/L_s=0.24		l/L_s=0.31		l/L_s=0.51
部位	x方向	y方向	x方向	y方向	x方向	y方向	x方向	y方向
冲压通道下壁面	−0.12	−64.82	−0.11	−64.89	−0.13	−64.99	−0.12	−65.02
分流板下壁面	−0.04	83.73	−0.05	84.53	−0.06	85.00	−0.10	86.22
分流板上壁面	−49.04	−390.48	−48.21	−384.70	−47.90	−382.41	−46.90	−375.45
涡轮通道上壁面	125.71	430.03	126.29	426.09	125.98	424.77	124.45	421.17

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表 4 不同分流板缝隙宽度下的漏气量

Table 4. Gas leakage under different gap widths of splitter plate

w/h	结构	流量/（kg·s⁻¹）	漏气量（相对于涡轮流量）/%
0	涡轮	0.141 7	0
0	冲压	0.065 2	0
0.017	涡轮	0.143 3	1.29
0.017	冲压	0.065 1	1.29
0.033	涡轮	0.144 7	2.88
0.033	冲压	0.065 1	2.88
0.047	涡轮	0.145 6	3.99
0.047	冲压	0.065 1	3.99

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表 5 4种不同状态边界条件设置

Table 5. Boundary conditions for four different states

工况	$P_{\mathrm{tur}}^* $/kPa	$P_{\mathrm{ram}}^* $/kPa	$T_{\mathrm{tur}}^* $/K	$T_{\mathrm{ram}}^* $/K	P_b/kPa
1	185.0	145.0	2072	1397	9.054
2	31.7	25.0	1000	800	9.054
3	185.0	25.0	2072	800	9.054
4	31.7	145.0	1000	1397	9.054

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表 6 不同状态下有无漏气的喷管性能

Table 6. Nozzle performance with or without gas leakage under different states

工况	缝隙宽度	C_fx	L/N	漏气量/%
1	w/h=0	0.938 5	63.07	0
1	w/h=0.033	0.925 3	69.31	2.88
2	w/h=0	0.909 9	−3.34	0
2	w/h=0.033	0.898 4	−3.13	2.59
3	w/h=0	0.930 9	49.15	0
3	w/h=0.033	0.9124	51.98	2.88
4	w/h=0	0.9420	11.61	0
4	w/h=0.033	0.9410	11.89	0.26

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