气体涡轮流量计性能优化的模拟与实验研究

以TRZ80气体涡轮流量计为研究对象,采用数值模拟与实验测试相结合的方法,提出了前整流器和后导流体的结构优化方案。通过对结构优化前后流量内部流场特征的分析,揭示了流量计结构与性能优化背后确切的流体力学机制。研究结果表明：前整流器和后导流体区域的压降突变与后导流体尾部的涡旋结构和回流现象是影响流量计计量性能的主要机制。优化的流量计结构可以明显减弱压降突变、涡旋结构与回流现象。优化的流量计结构既可以显著降低流量计的压力损失,又可以明显提高流量计的测量精度与稳定性,其压力损失和线性度误差分别降低了约48.58%和32.43%。研究结果有助于为今后开发与量产计量性能更好的气体涡轮流量计提供理论指导和技术支持。     

气体涡轮流量计结构优化研究

以TM80气体涡轮流量计为研究对象,采用数值模拟与实验测试相结合的方法对其进行结构优化研究。数值结果表明压力梯度骤变和边界层分离的出现主要由流量计的表芯支座和后导流体引起。由此提出了关于表芯支座坡度和后导流体直径的结构优化方法,将表芯支座的坡度设计为15°,将表芯支座侧面的台阶流转变成渐缩流;将后导流体直径缩减为62 mm,将后导流体侧面的台阶流转变成等直径的管道流。数值模拟和实验测试证实,当表芯支座坡度设计为15°、后导流体直径设计为62 mm时,流量计的压力损失显著降低,仪表系数变得更加稳定,线性度误差明显变小,说明该结构优化方法可以明显提升流量计的计量性能。研究结论有助于为今后开发性能更好的气体涡轮流量计提供有力的理论指导和技术支持。     

气体涡轮流量计的改进及实验测量

对气体涡轮流量计的主要组件引起的压力损失进行了对比实验测量，比较了整流栅形状、叶轮叶片数和后导流器不同结构对压损的影响程度。结果表明，后导流器相对整流栅和叶轮是产生压力损失的主要因素，采取改进的后导流结构，可以明显降低流量计的压损，同时得到更好的仪表系数值，提高流量计准确度。     

导流器结构对气体涡轮流量计曲线影响的试验研究

本文针对于丹东东发集团有限公司开发的DN100气体涡轮流量计研发初期曲线不好的问题,从分析导流器的结构入手,通过试验证明导流器尾端的混合室的大小与曲线形状有着规律性的关系,确定了最佳的混合室尺寸,进而使得DN100气体涡轮流量计的性能曲线得到了优化。     

叶片螺旋角对气体涡轮流量计性能影响的分析

在分析气体涡轮流量计结构和数学模型的基础上,针对涡轮叶片螺旋升角对仪表性能的影响,以安装35°、45°和55°三种不同叶片螺旋升角涡轮的DN150型气体涡轮流量计作为实验对象,搭建仪表负压检测平台,分别对仪表系数、压力损失和计量精度进行实验检定与对比分析。实验结果表明,合理设计涡轮叶片螺旋升角能显著改善气体涡轮流量计的性能,为叶片螺旋升角进一步优化及其对仪表性能影响规律的研究提供了实验基础。     

高压气体涡轮流量计的研制

阐述高压气体涡轮流量计研制的意义和设计依据;并介绍高压涡轮流量计的工作原理、结构特点、性能测试、计量特性等,以此证明研制的高压气体涡轮流量计可以作为贸易计量应用在高压管线上。     

带GPRS通信的流量计诊断器的研制

随着中国天然气行业进入高速发展期,气体流量计作为一种天然气贸易的计量仪表,它的性能直接影响到贸易双方的经济利益。本文简述了一种提供更好的诊断技术和多样性的诊断方法,从而降低流量计的运行成本并提高可靠性。其中,通过压损的大小来判断流量计是否出现异常。对于气体涡轮流量计,通过检测高低频信号输出情况也可以判断涡轮叶片或减速机构的传动比是否已发生损坏。对于旋进旋涡流量计可检测流体振动信号受压力波动或机械振动干扰的程度,从而判断旋进流量计是否适合用于其所处的使用场合。并且采用GPRS无线通信技术,实现将测量的过程参数远传至数据中心,组成远程数据采集监控系统(SCADA)。     

智能气体涡轮流量计的创新结构设计

我国天然气资源丰富,气体涡轮流量计一直是作为天燃气贸易计量的首选。本文论述气体涡轮流量计的机械结构上的几点优化设计,优化了气体涡轮流量计的曲线,提高了气体涡轮流量计的可靠性。     

口吹法初判气体涡轮流量计的小流量误差

针对当前气体涡轮流量计在生产及维修服务的标定效率低的问题,提出了一种口吹法,初步判别气体涡轮流量计的小流量误差,以避免对明显不合格产品做无效的标定,并通过分析气体涡轮流量计的计量性能特点和结合样机试验结果,进一步阐明该方法的实用性和高效性。     

气体涡轮流量计结构型式分析

通过对机械表头和电子表头两种结构型式的气体涡轮流量计的结构、工作原理、实际应用几方面所进行的分析比较,增加燃气计量用户对气体涡轮流量计产品的了解程度,便于在选型时做出正确的选择.     

涡轮流量计前导流器的结构与性能

对DN100气体涡轮流量计的关键部件之一前导流器引起的流量计压力损失进行试验测量和数值计算.对比分析两种不同结构前导流器对压力损失的影响,发现前导流器的结构变化不仅影响该部位的气流速度分布,使当地压力损失发生变化,更重要的是对后面各部件内的气体流动速度梯度和压力恢复也有明显影响,使总压损失进一步放大或减小.数值计算通过分析流动参数的变化从流动机理上解释了结构与压损间的关系.     

Developing a model for prediction of helical turbine flowmeter performance using CFD

In this article, a numerical model for prediction of turbine flowmeter performance is proposed. This model is consists of a novel iterative algorithm, based on torque balance theory. Despite previous studies, the effect of bearings drag torque on finding balance point is considered. Using an in-house code, the bearings torque of the flowmeter is calculated based on the finite difference method. The three-dimensional steady state internal flow field of turbine flowmeter is obtained from the Computational Fluid Dynamics (CFD) simulations. For evaluation of the model׳s accuracy the experiments on a 6 in. helical turbine flowmeter has been carried out for crude oil and water. Consequently, the K-factor and also linearity error for cases of fluids are achieved. The results were compared with experimental data and it is found that the numerical model results are reasonably accurate. Therefore, by using the proposed model, the heavy cost of design and optimization of turbine flowmeters can be reduced.     

CAN总线型智能涡轮流量计

针对涡轮流量计的工作要求和CAN现场总线的应用状况,介绍了以STC89C52RD单片机为核心,采用涡轮流量计、压力和温度传感器及CAN总线控制器等构成的CAN总线型智能涡轮流量计的软硬件设计。这种CAN总线型智能涡轮流量计能通过温压补偿实现对气体流量的准确测量与现场显示,可方便地与CAN总线网络进行挂接,实现基于CAN总线的远程监测。     

Controlling the secondary flows near endwall boundary layer fences in a 90° turning duct using approximate optimization method

This paper presents the optimization of an endwall boundary layer fence which improves the aerothermal characteristics of a gas turbine passage. The fence in a gas turbine passage effectively reduces secondary flow loss, which is generated in the cascade of the turbine. The turbine passage was simulated by a 90° turning duct (Re_D=360,000). The main purpose of the present investigation was to focus on finding a boundary layer fence with minimum total pressure loss in the passage and heat transfer coefficient on the endwall of the duct. An approximate optimization method was used for the investigation to secure the computational efficiency. Design variables were the fence shape factors (fence thickness, fence height, and fence width) as well as the radial position on the passage endwall. Results indicated that a significant improvement in aerodynamic performance can be achieved through the application of an optimized boundary layer fence. The optimized design reduced the mass-weighted average total pressure loss in the duct by 8.6% relative to the duct without the fence. The area-weighted average maximum Nusselt number on the endwall of the optimized design was decreased by 2.5% in comparison with the duct without the fence.     

负压排屑装置楔形结构优化设计与仿真

为解决超大长径比深孔加工排屑困难问题,在分析DF系统负压排屑作用机理的基础上,建立负压射流模型,通过采用填充部分前/后分离区所占区域的方法,设计了一种位于射流喷嘴处的楔形结构,以减少前/后分离区的能量损耗。理论计算及Fluent仿真优化实验结果表明,该楔形尺寸在长度L1=75 mm、宽度L2=1 mm时效果最好,切削液流速增大约10.07%,湍流动能增大约11.39%,负压区压力值减小约79.26%,该楔形结构提高了负压排屑能力,最大程度地减少了前/后分离区的能量损耗。     

Optimum Tilt Angle of Flow Guide in Steam Turbine Exhaust Hood Considering the Effect of Last Stage Flow Field

Heat transfer and vacuum in condenser are influenced by the aerodynamic performance of steam turbine exhaust hood. The current research on exhaust hood is mainly focused on analyzing flow loss and optimal design of its structure without consideration of the wet steam condensing flow and the exhaust hood coupled with the front and rear parts. To better understand the aerodynamic performance influenced by the tilt angle of flow guide inside a diffuser, taking a 600 MW steam turbine as an example, a numerical simulator CFX is adopted to solve compressible three-dimensional(3D) Reynolds time-averaged N-S equations and standard k-e turbulence model.And the exhaust hood flow field influenced by different tilt angles of flow guide is investigated with consideration of the wet steam condensing flow and the exhaust hood coupled with the last stage blades and the condenser throat.The result shows that the total pressure loss coefficient and the static pressure recovery coefficient of exhaust hood change regularly and monotonously with the gradual increase of tilt angle of flow guide. When the tilt angle of flow guide is within the range of 30° to 40°, the static pressure recovery coefficient is in the range of 15.27% to 17.03% and the total pressure loss coefficient drops to approximately 51%, the aerodynamic performance of exhaust hood is significantly improved. And the effectiveenthalpy drop in steam turbine increases by 0.228% to 0.274%. It is feasible to obtain a reasonable title angle of flow guide by the method of coupling the last stage and the condenser throat to exhaust hood in combination of the wet steam model, which provides a practical guidance to flow guide transformation and optimal design in exhaust hood.     

Analysis of viscosity effect on turbine flowmeter performance based on experiments and CFD simulations

Viscosity effect is one important factor that affects the performance of turbine flowmeter. The fluid dynamics mechanism of the viscosity effect on turbine flowmeter performance is still not fully understood. In this study, the curves of meter factor and linearity error of the turbine flowmeter changing with fluid viscosity variations were obtained from multi-viscosity experiments (the viscosity range covered is 1.0×10^–6 m²/s–112×10^–6 m²/s). The results indicate that the average meter factor of turbine flowmeter decreases with viscosity increases, while the linearity error increases. Furthermore, Computational Fluid Dynamics (CFD) simulation was carried out to analyze three-dimensional internal flow fields of turbine flowmeter. It was demonstrated that viscosity changes lead to changes of the wake flow behind the upstream flow conditioner blade and the flow velocity profile before fluid entering turbine rotor blade, which affect the distribution of pressure on the rotor blades, so impact the turbine flowmeter performance.