平面叶栅边界层的转捩试验及数值模拟

doi:10.19596/j.cnki.1001-246x.8600

摘要/Abstract

摘要：

基于温敏漆(TSP)技术，以跨音速平面叶栅为研究对象，开展平面叶栅边界层转捩位置的试验以及数值模拟研究。试验结果表明：利用TSP测量技术可以得到平面叶栅表面的温度分布，进而判断边界层转捩位置。通过CFD(Computational Fluid Dynamics)数值方法完成验证工作。

关键词: 跨音速平面叶栅, 转捩, 温敏漆, 计算流体力学

Abstract:

Based on TSP (Temperature Sensitive Paints) technology, the experiment and numerical simulation of the boundary layer transition position of the plane cascade are carried out. The experimental results show that the temperature distribution on the surface of the plane cascade can be obtained by TSP measurement technology, and then the boundary layer transition position can be judged. The verification work was completed by CFD (Computational Fluid Dynamics) numerical method.

Key words: transonic planar cascade, transition, temperature sensitive paints, computational fluid dynamics

孙天野, 祝宝山, 王红彪. 平面叶栅边界层的转捩试验及数值模拟[J]. 计算物理, 2023, 40(3): 307-313.

Tianye SUN, Baoshan ZHU, Hongbiao WANG. Experimental and Numerical Simulation of Boundary Layer Transition in Plane Cascade[J]. Chinese Journal of Computational Physics, 2023, 40(3): 307-313.

图/表 11

图1 风洞试验装置实物图(a)风洞试验段; (b) 叶栅模型

Fig.1 Physical drawing of wind tunnel test device

表1 跨声速VKI-RG涡轮叶型设计参数及叶栅参数

Table 1 Design parameters and cascade parameters of transonic VKI-RG turbine blade

参数	进口气流角/°	叶型安装角/°	叶型稠度	叶型弦长/mm	叶栅展弦比	叶栅叶片数
数值	30	33.3	1.408 45	95	2.0	7

图2 叶片涂层与光路布置示意图(a) 涂层结构；(b)光源、相机与叶栅位置

Fig.2 Blade coating and optical layout diagram

表2 风洞吹风试验车次

Table 2 Wind tunnel test runs

车次	进口总压/kPa	出口静压/kPa	出口马赫数	进口雷诺数/10⁵	进口湍流度/%
1	172	86.7	1.03	8.6	0.3
2	170	72.1	1.2	8.6	0.3
3	59.1	53.1	0.4	3.1	0.3
4	103	51.1	1.05	5.1	0.3

图3 计算域

Fig.3 Computation domain

图4 叶栅网格(a)叶片网格分布；(b)局部网格分布

Fig.4 Cascade grid

图5 计算域的边界条件

Fig.5 Boundary conditions of the computational domain

表3 数值计算设置

Table 3 Numerical calculation settings

Item	Setting
Inlet boundary condition	Total pressure
Outlet boundary condition	Static pressure
Blade wall condition	No slip wall
Upper and lower surfaces	No slip wall
Advection scheme	High-resolution
Turbulence numeric	High-resolution
Residual convergence criterion	1×10^-5

图6 不同马赫数和雷诺数下的TSP测量结果

Fig.6 TSP Measurement results at different mach numbers and reynolds numbers

图7 叶片表面等熵马赫数对比(α=0°，Ma2=0.78)

Fig.7 Comparison of isentropic Mach number on blade surface(α=0°, Ma2=0.78)

图8 转捩位置对比

Fig.8 Comparison of transition positions

参考文献 30

1	RESHOTKO E . Boundary-layer stability and transition[J]. Annual Review of Fluid Mechanics, 1976, 8, 311- 349. DOI
2	MOIN P , MAHESH K . Direct numerical simulation: A tool in turbulence research[J]. Annual Review of Fluid Mechanics, 1998, 30, 539- 578. DOI
3	HERBERT T . Secondary instability of boundary layers[J]. Annual Review of Fluid Mechanics, 1988, 20, 487- 526. DOI
4	COULL J , HODSON H . Unsteady turbines boundary-layer transition in low-pressure[J]. Journal of Fluid Mechanics, 2011, 681, 370- 410. DOI
5	ZHONG X , WANG X . Direct numerical simulation on the receptivity, instability, and transition of hypersonic boundary layers[J]. Annual Review of Fluid Mechanics, 2012, 44 (1): 527- 561. DOI
6	PARZIALE N , SHEPHERD J , HORNUNG H G . Differential interferometric measurement of instability in a hypervelocity boundary layer[J]. AIAA Journal, 2013, 51 (3): 750- 754. DOI
7	CAI Linfeng , LI Haoge , CHEN Weifang . Analysis of steady cross-flow instability transition in boundary layer of infinitely extended swept wing[J]. Chinese Journal of Computational Physics, 2019, 36 (2): 175- 181.
8	ZHU D , LIU Z , YUAN X . Mechanism of porous surface delaying hypersonic boundary layer transition[J]. Chinese Journal of Computational Physics, 2016, 33 (2): 163- 169.
9	PAN Honglu , GUAN Faming , YUAN Xiangjiang , et al. Unsteady interaction on flat plate/isolated roughness element in hypersonic flow[J]. Chinese Journal of Computational Physics, 2015, 32 (5): 537- 544. DOI
10	GAN Zhou . Numerical simulation method based on layer flow energy turbulence model[J]. Chinese Journal of Computational Physics, 2013, 30 (2): 169- 179. DOI
11	YU Qiuyang , BAO Yun , WANG Shengye , et al. The DDES method of the B-C transition model simulates the transition large separation flow[J]. Chinese Journal of Computational Physics, 2020, 37 (1): 46- 54.
12	MATSUMURA S, SCHNEIDER S, BERRY S. Flow visualization measurement techniques for high-speed transition research in the Boeing/AFOSR Mach-6 quiet tunnel[C]. Aiaa/asme/sae/asee Joint Propulsion Conference & Exhibit, 2013.
13	KWAK D Y, YOSHIDA K, NOGUCHI M, et al. Boundary layer transition measurement using Preston tube on NEXST-1 flight test[R]. AIAA 2007-4173, 2007.
14	DRAKE A. Oil film interferometry in the development of long endurance aircraft[R]. AIAA 2210-43, 2010.
15	HILFER M, DUFHAUS S, YORITA D, et al. Application of pressure and temperature-sensitive paint on a highly loaded turbine guide vane in a transonic linear cascade[C]. Global Power and Propulsion Society Forum, 2017.
16	FEY U, KONRATH R, KIRMSE T, et al. Advanced measurement techniques for high Reynolds number testing in cryogenic wind tunnels[R]. AIAA 2010-1301, 2010.
17	HAUSMANN F, SCHROEDER W, LIMBERG W. Development of a multi-sensor hot-film measuring technique for transition detection in cruise flight[C]. 40th AIAA Aerospace Sciences Meeting & Exhibit, 2002.
18	ZHU J , GAO Z H , ZHAN H , et al. A high-speed nature laminar flow airfoil and its experimental study in wind tunnel with nonintrusive measurement technique[J]. Chinese Journal of Aeronautics, 2009, 22 (3): 225- 229. DOI
19	HAUSMANN F, SCHROEDER W, LIMBERG W. Development of a multi-sensor hot-film measuring technique for transition detection in cruise flight[C]. 40th AIAA Aerospace Sciences Meeting & Exhibit, 2002.
20	HALSTEAD D, WISLER D, OKIISHI T, et al. Boundary layer development in axial compressors and turbine: Part 1 of 4 composite picture[R]. ASME, 1995: 95-GT-461.
21	CHEN Z , GUO Y C , GAO C . Principle and technology of three-dimensional PIV[J]. Journal of Experiments in Fluid Mechanics, 2006, 20 (4): 77-82+105
22	MEDINA H, BENARD E, HUANG J C, et al. Study of the fluid mechanics of transitional steady and pulsed impinging jets using a high-speed PIV system[R]. AIAA 2008: 2008-766.
23	HORSTMANN K H, REDEKER G, QUAST A, et al. Flight tests with a natural laminar flow glove on a transport aircraft. [R]. AIAA 1990: 90-3044.
24	HORSTMANN K H, QUAST A, REDEKER G. Flight and wind-tunnel investigation on boundary layer transition at reynold number up to 10 to the 7^th[C]//Proceedings of the 16^th ICAS Congress, Israel, 1988, 2: 979-986.
25	HOLMES B J, GALL P D, CROOM C C, et al. A new method for laminar boundary layer transition visualization in flight: Color changes in liquid crystal coatings: NASA-TM-87666[R]. Washington D C: NASA, 1986.
26	MEE D J, WALTON T W, HARRISON S B, et al. A comparison of liquid crystal techniques for transition detection: AIAA-1991-0062[R]. Reston, VA: AIAA, 1991.
27	KAMEDA M. Fast-responding pressure-sensitive paints for unsteady flow measurement[C]. 10^th Pacific Symposium on flow visualization and image processing, Naple, Italy, 2015.
28	GREGORY J W , SAKAUE H , LIU T , et al. Fast pressure-sensitive paint for flow and acoustic diagnostics[J]. Annual Review of Fluid Mechanics, 2014, 46, 303- 330.
29	ZHU Y , CHEN X , WU J , et al. Aerodynamic heating in transitional hypersonic boundary layers: Role of second-mode instability[J]. Physics of Fluids, 2018, 30 (1): 011701.
30	FEY U, EGAMI Y, ENGLER H R, et al. High Reynolds number transition detection by means of temperature sensitive paint[C]. 44^th AIAA Aerospace sciences meeting and exhibit, Reno, Nevada, AIAA 2006: 2006-514.

[1]	郭勇颜, 曾志春, 何磊, 何乾伟, 严雪琴, 赵钟. DLR-F11高升力构型的数值模拟[J]. 计算物理, 2023, 40(4): 401-415.
[2]	肖聪, 张士诚, 马新仿, 周彤, 侯腾飞. 基于模型降维和递归神经网络的油藏参数反演[J]. 计算物理, 2022, 39(5): 564-578.
[3]	余秋阳, 包芸, 王圣业, 王光学. B-C转捩模型的DDES方法模拟转捩大分离流动[J]. 计算物理, 2020, 37(1): 46-54.
[4]	张珑慧, 由长福. 基于有限体积虚拟区域方法的两相流动直接模拟[J]. 计算物理, 2019, 36(3): 291-297.
[5]	蔡林峰, 李昊歌, 陈伟芳. 无限展长后掠翼边界层定常横流不稳定转捩分析[J]. 计算物理, 2019, 36(2): 175-181.
[6]	陈永彬, 唐智礼, 盛建达. 跨音速自然层流翼型多目标优化设计[J]. 计算物理, 2016, 33(3): 283-296.
[7]	潘宏禄, 关发明, 袁湘江, 卜俊辉. 高超声速平板边界层/圆柱粗糙元非定常干扰[J]. 计算物理, 2015, 32(5): 537-544.
[8]	甘文彪, 周洲. 基于层流动能湍流模型的数值模拟方法[J]. 计算物理, 2013, 30(2): 169-179.
[9]	陈林, 袁湘江. 转捩边界层中的上喷下扫运动[J]. 计算物理, 2013, 30(1): 53-60.
[10]	陈荣钱, 伍贻兆, 夏健. 应用随机模型方法预测汽车风噪声[J]. 计算物理, 2013, 30(1): 98-104.
[11]	邓枫, 覃宁, 伍贻兆. EGO方法的训练算法及应用[J]. 计算物理, 2012, 29(3): 326-332.
[12]	陈荣钱, 伍贻兆, 夏健. 基于SNGR方法的后缘噪声数值模拟[J]. 计算物理, 2011, 28(5): 698-704.
[13]	索奇峰, 吴晴, 钟易成, 李明水. 振动桥梁CFD数值模拟的网格运动算法[J]. 计算物理, 2011, 28(4): 547-553.
[14]	吴晴, 钟易成, 余少志, 胡骏. 基于LU-SGS的非结构弹簧网格迭代算法[J]. 计算物理, 2009, 26(6): 806-812.
[15]	成娟, 舒其望. 计算流体力学中的高精度数值方法回顾[J]. 计算物理, 2009, 26(5): 633-655.