纺织学报 ›› 2025, Vol. 46 ›› Issue (03): 196-206.doi: 10.13475/j.fzxb.20231202101

• 机械与设备 • 上一篇    下一篇

基于响应面法的辅助喷嘴喷孔结构优化设计

沈敏1, 杨启2, 胡峰2, 王真2, 杨学正3, 吕永法3, 余联庆1,2()   

  1. 1.武汉纺织大学 三维纺织湖北省工程研究中心, 湖北 武汉 430200
    2.武汉纺织大学 机械工程与自动化学院, 湖北 武汉 430200
    3.日发纺织机械有限公司, 山东 聊城 252001
  • 收稿日期:2023-12-14 修回日期:2024-05-10 出版日期:2025-03-15 发布日期:2025-04-16
  • 通讯作者: 余联庆(1972—),男,教授,博士。主要研究方向为新型纺织机械。E-mail:2006110@wtu.edu.cn。
  • 作者简介:沈敏(1978—),女,博士。主要研究方向为高性能纺织机器。
  • 基金资助:
    国家自然科学基金项目(51505344);国家自然科学基金项目(11872048);山东省重点研发项目(2024CXGC010215);湖北省高等学校优秀中青年科技创新团队项目(T2022015);湖北省数字化纺织装备重点实验室开放课题(2020001)

Optimization design of nozzle orifice structure based on response surface method

SHEN Min1, YANG Qi2, HU Feng2, WANG Zhen2, YANG Xuezheng3, LÜ Yongfa3, YU Lianqing1,2()   

  1. 1. Three-dimensional Textile Hubei Engineering Research Center, Wuhan Textile University, Wuhan, Hubei 430200, China
    2. School of Mechanical and Automation, Wuhan Textile University, Wuhan, Hubei 430200, China
    3. Shandong Rifa Textile Machinery Co., Ltd., Liaocheng, Shandong 252001, China
  • Received:2023-12-14 Revised:2024-05-10 Published:2025-03-15 Online:2025-04-16

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摘要： 为降低辅助喷嘴的耗气量,建立不同椭圆形孔出口的辅助喷嘴与异形筘组成的流场,采用Fluent数值模拟得到沿合成流场中心轴线的气流速度与辅助喷嘴入口质量流;基于合成气流速度与辅助喷嘴射流集束型分析,设置椭圆孔参数范围,依据Box-Behnken设计试验,得到耗气量定量表达式,结合响应面方法分析辅助喷嘴椭圆孔结构参数对耗气量的影响。结果表明:改变椭圆孔在出口平面的旋转角度,对合成气流沿轴线速度和辅助喷嘴射流的径向速度影响显著;椭圆孔短轴长度对耗气量的影响显著于长轴长度,旋转角度的改变对耗气量的影响较小;辅助喷嘴耗气量与合成流场中心轴线波峰速度呈现非线性关系,最优模型相对试验组平均数值,合成气流波峰速度提升了2.25%,耗气量降低了7.35%。

关键词: 喷气织机, 辅助喷嘴, 喷孔结构, 响应曲面法, 耗气量

Abstract:

Objective The air consumption of the auxiliary nozzle accounts for approximately 75% of the air-jet loom. In order to address the issues of low jet velocity and high air consumption in the single circular-hole auxiliary nozzle, a novel-shaped orifice auxiliary nozzle was designed. The study investigated the influence of the outlet shape parameters of the auxiliary nozzle on the synthesized airflow within the novel-shaped reed groove. This paper reports on numerical simulations based on the Reynolds-Averaged Navier-Stokes (RANS) equations and a turbulent model for vortex viscosity, focusing on the three-dimensional synthesized flow field composed of the main nozzle jet and the auxiliary nozzle jet.

Method Firstly, three-dimensional synthesized flow field models for auxiliary nozzles A1, A2, A3, B1,B2 and B3 were established using Solidworks software. The synthetic flow field models were then grid-divided using specialized meshing software ICEM, and boundary condition parameters were set using computational fluid dynamics (CFD) software Fluent. Numerical simulations of the synthesized airflow were conducted based on the RANS equations, and the accuracy of the numerical results was validated through experiments. Secondly, building upon the analysis of experimental results, the range of outlet parameters for the auxiliary nozzles was defined, including the long axis, short axis, and rotation angle. Experimental combinations were generated using the Box-Behnken method, and calculations were performed using Fluent. Experimental results were presented as response surfaces, and regression equations were derived, with the accuracy of the regression equation verified through variance analysis. By analyzing the interactions between various factors, the impact of each factor on air consumption and speed was determined. In conclusion, a comparison of air consumption and average velocity among the experimental groups facilitated the identification of the optimal comprehensive performance model.

Results The numerical simulation results exhibit a decay trend in the airflow velocity curve that aligns with the experimental test results. The velocity of the primary jet rapidly decreases upon entry into the novel-shaped reed groove. When the auxiliary nozzle jet enters the reed groove, the synthesized airflow gets accelerated briefly, temporarily slowing down the overall decay of the synthesized airflow. The prioritization of the converging type of auxiliary nozzle is observed in the order of A1 > A2 > A3 and B3>B2>B1. The F-value of the response surface model for air consumption of the auxiliary nozzle under 0.3 MPa is 249.89, with a P-value smaller than 0.000 1, indicating the rationality of the selected model parameters. The results that R2=0.997 3, Adjusted R-squared (Radj2)=0.993 3, CV=1.14%<10%, and Adeq precision =56.082 8>4, indicating that the fitted regression equation conforms to the experimental principle and can be used for the analysis and prediction of air consumption. The F-value of the response surface model for velocity of the auxiliary nozzle under 0.4 MPa is 66.55, with a P-value smaller than 0.000 1, indicating the rationality of the selected model parameters. The results that R2=0.990 1, Radj2=0.975 2, CV=1.58%<10%, and Adeq precision =33.092 6>4, suggest that the fitted regression equation conforms to the experimental principle and can be used for the analysis and prediction of velocity. Through interaction analysis, it is observed that air consumption and velocity are positively correlated with the long and short axes, while the influence of the rotation angle on air consumption is relatively minimal, but the interaction between the rotation angle and the short axis has a significant effect on the velocity. Finally, compared with the average of the experimental group, the air consumption of the optimized model is reduced by 7.35%, and the average speed is increased by 2.25%.

Conclusion 1) The gas supply pressure of the elliptical hole auxiliary jet inlet is increased from 0.3 MPa to 0.4 MPa, and the air consumption of the elliptical hole auxiliary nozzle will be significantly increased. However, the distribution pattern of the response surface of the interaction of factors affecting air consumption is basically consistent. 2) The short axis of the elliptical hole has the most significant effect on the air consumption, followed by the long axis, while the change of rotation angle has no effect on the air consumption, and the interaction between the long axis and the short axis has the most significant effect on the air consumption. 3) The degree of influence on the peak value of the resultant air velocity is as follows: short axis > long axis > rotation angle, and the interaction of long axis-short axis and short axis-rotation angle on the velocity is significant; changing the rotation direction of the long axis of the elliptic hole has a significant effect on the resultant flow velocity. 4) A nonlinear relationship exists between the gas consumption of the auxiliary injection with elliptical holes and the peak velocity of the synthetic gas axis, and the gas consumption decreases when the speed increases.

Key words: air jet loom, auxiliary nozzle, spray hole, response surface methodology, air consumption

中图分类号: 

  • TS103.3

图1

椭圆孔辅助喷嘴结构参数"

图2

多个辅助喷嘴与异形筘组合三维模型"

图3

主、辅助喷嘴射流三维流场网格划分图"

图4

主、辅助喷嘴射流汇入异形筘道内气流测速原理"

图5

异形筘道内合成气流速度测量装置"

图6

数值模拟与实验得到合成气流沿轴向速度"

图7

沿辅助喷嘴出口轴线不同距离的速度云图"

表1

Box-Behnken试验设计因素水平"

水平 A
长轴长度/mm		 B
短轴长度/mm		 C
旋转角度/rad
-1 2.0 1.0 0
0 2.2 1.2 0.393
1 2.4 1.4 0.785

表2

响应面试验设计与结果"

试验
序号		 响应变量 响应值
长轴长
度/mm		 短轴长
度/mm		 旋转
角度/
rad		 H1:0.3MPa
耗气量/
(kg·h-1)		 H2:0.4MPa
耗气量/
(kg·h-1)
1 2.0 1.0 0.393 10.41 13.29
2 2.2 1.0 0 11.32 14.53
3 2.2 1.0 0.785 11.52 14.60
4 2.4 1.0 0.393 12.47 15.77
5 2.0 1.2 0.785 12.56 15.74
6 2.0 1.2 0 12.61 15.99
7 2.2 1.2 0.393 13.46 17.49
8 2.2 1.2 0.393 13.47 17.49
9 2.2 1.2 0.393 13.48 17.46
10 2.2 1.2 0.393 13.72 17.42
11 2.4 1.2 0.785 14.52 18.81
12 2.4 1.2 0 14.61 18.43
13 2.0 1.4 0.393 14.83 18.87
14 2.2 1.4 0 16.14 20.55
15 2.2 1.4 0.785 16.17 20.78
16 2.4 1.4 0.393 17.54 22.35

表3

0.3 MPa下耗气量回归方程的方差分析"

来源 平方和 自由度 均方和 F值 P值 显著性
模型 54.82 9 6.09 249.89 <0.000 1 **
A 9.53 1 9.53 390.81 <0.000 1 **
B 44.94 1 44.94 1 843.39 <0.000 1 **
C 0.001 0 1 0.001 0 0.041 5 0.845 2
AB 0.105 6 1 0.105 6 4.330 0 0.082 6
AC 0.000 4 1 0.000 4 0.016 0 0.903 5
BC 0.007 2 1 0.007 2 0.296 3 0.605 8
A2 0.004 6 1 0.004 6 0.186 9 0.680 6
B2 0.242 6 1 0.242 6 9.950 0 0.019 7 *
C2 0.000 3 1 0.000 3 0.012 6 0.914 3
残差 0.146 3 6 0.024 4
失拟项 0.099 2 3 0.033 1 2.11 0.278 1 不显著

图8

0.3 MPa下影响耗气量因素间交互响应曲面图"

图9

0.3 MPa下影响耗气量因素间交互响应平面图"

图10

0.4 MPa下影响耗气量因素间交互响应曲面图"

表4

0.4 MPa时速度响应面试验设计与结果"

实验
序号		 响应变量 响应结果
A长轴
长度/mm		 B
短轴
长度/mm		 C
旋转角度/
rad		 V
速度/(m·s-1)
1 2.0 1.0 0.393 63.15
2 2.2 1.0 0 65.66
3 2.2 1.0 0.785 59.01
4 2.4 1.0 0.393 68.86
5 2.0 1.2 0.785 64.50
6 2.0 1.2 0 63.80
7 2.2 1.2 0.393 71.55
8 2.2 1.2 0.393 71.55
9 2.2 1.2 0.393 69.48
10 2.2 1.2 0.393 73.26
11 2.4 1.2 0.785 73.35
12 2.4 1.2 0 74.20
13 2.0 1.4 0.393 74.06
14 2.2 1.4 0 73.31
15 2.2 1.4 0.785 80.31
16 2.4 1.4 0.393 88.29

表5

回归方程方差分析"

来源 平方和 自由度 均方和 F值 P值 显著性
模型 749 9 83.22 66.55 <0.000 1 **
A 192 1 192 153.54 <0.000 1 **
B 439.15 1 439.15 351.17 <0.000 1 **
C 0.005 1 0.005 0.004 0.951 6
AB 18.15 1 18.15 14.51 0.008 9 **
AC 0.600 3 1 0.600 3 0.48 0.514 3
BC 46.59 1 46.59 37.25 0.000 9 **
A2 2.31 1 2.31 1.85 0.222 9
B2 7.51 1 7.51 6 0.049 8 *
C2 42.44 1 42.44 33.94 0.001 1 **
残差 7.5 6 1.25
失拟项 0.326 6 3 0.108 9 0.045 5 0.984 8 不显著

图11

0.4 MPa下影响速度因素间交互响应曲面图"

图12

0.4 MPa下影响速度因素间交互响应平面图"

图13

波峰速度与耗气量的关系"

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