高温超导电缆低温系统数据实时监控

介绍自行研制的高温超导电缆低温系统的实时监控系统.该系统包括温度测量、压力测量、流量测量、液位测量4部分.该系统基于计算机和MCGS组态软件,具有操作简便、运行可靠、采集高效精确等优点,并通过与高温超导电缆的通电实验.结果表明,这套数据实时监控系统能满足高温超导电缆低温系统的各项参数的测量要求.该监控系统的成功研制,为类似的超导低温工程项目中数据的采集和控制提供了参考.     

基于ARM的石油压裂液位监测系统

针对石油勘探作业期间实时监控液罐液位的工程需求,设计了一套基于ARM的实时液位监控系统,该系统由超声波发射接收模块、无线通信模块、上位机终端3部分组成.利用超声波测距技术和433M无线组网技术,实现了液位测量和无线数据传输功能;利用ARM在待机模式下功耗最低的特性,设计不同工作模式,并配合以降低功耗为目的的硬件电路设计,实现了低功耗目标.实验结果表明:在低温、湿度较大的环境中,液位测量精度达到1cm,并能长时间连续工作,无线通信正常,并成功应用于工程实践中.     

中子慢化器低温及真空性能测试系统设计北大核心CSCD

中子慢化器低温及真空性能测试系统,用于验证中国散裂中子源氢慢化器的低温性能和真空密封性。此套系统由供液系统、气体加热系统、流量控制系统、温度与压力监测系统组成,采用液氮替代液氢作为测试介质,通过加热器对液氮直接加热的方式获得低温氮气。每根输液管道都是独立的真空单元,配有真空抽口,采用双层不锈钢管道,管道之间做绝热处理。通过控制加热器与内管的装配精度来保证气体换热效率。使用Lakeshore Model 336温控仪和TELEDYNE HASTINGS流量控制器进行气体温度和流量调节。该系统气体输出温度精度达到±5 K,气体输出流量约500 L/min±10%。此套系统不仅为大型低温系统提供安全可靠的低温测试工作介质,同时节约了实验成本,将来在航空航天领域能得以应用推广。     

中子慢化器低温及真空性能测试系统设计

中子慢化器低温及真空性能测试系统,用于验证中国散裂中子源氢慢化器的低温性能和真空密封性。此套系统由供液系统、气体加热系统、流量控制系统、温度与压力监测系统组成,采用液氮替代液氢作为测试介质,通过加热器对液氮直接加热的方式获得低温氮气。每根输液管道都是独立的真空单元,配有真空抽口,采用双层不锈钢管道,管道之间做绝热处理。通过控制加热器与内管的装配精度来保证气体换热效率。使用Lakeshore Model 336温控仪和TELEDYNE HASTINGS流量控制器进行气体温度和流量调节。该系统气体输出温度精度达到±5 K,气体输出流量约500 L/min±10%。此套系统不仅为大型低温系统提供安全可靠的低温测试工作介质,同时节约了实验成本,将来在航空航天领域能得以应用推广。     

63.2 K以下的深度过冷液氧制备研究

采用深度过冷方式对液氧推进剂进行致密化能够显著提升密度并增加显冷量,然而当前国内系统制备的过冷液氧温度均在70 K以上,致密化提升效果有限。鉴于此,设计和搭建了基于减压冷却原理的深度过冷氧制备系统,拟将液氧温度过冷至液氮三相点温度63.2 K以下,并分析采用不同低温介质时的液氧推进剂降温特性。结果表明,当以液氮为低温介质时,液氧推进剂在98 min内就可冷却至65.4 K;当以液氧为低温介质时,液氧推进剂降温速率相对较慢,需要大约350 min才可达到65.4 K,但继续进行抽空减压后,液氧推进剂温度可降至61.8 K;同时,在绝热工况下,致密化液氧能较好地维持过冷状态,方便后续的输运和应用。     

低温推进剂加注流程动态特性仿真

在建立低温真空管路、低温真空阀门、低温真空容器、低温过滤器等单机低温设备仿真模型的基础上,按照实际管路系统布局建立了某低温火箭液氧加注系统三维仿真模型。依据实际低温加注工序和参数,完成了加注全流程动态特性分析和仿真,对加注过程中温度、压力、流量、液位等参数进行了仿真预示。通过与试验数据对比,证明了系统全流程动态特性仿真的可行性和有效性。研究成果可用于低温加注系统方案优化设计、工艺流程设计、故障预案演示等,同时可作为开展低温系统加注过程自动化测试、加注和健康管理的基础。     

紧凑式低温热交换器实验台测量系统

介绍了自行研制的紧凑式低温热交换器实验台的实时测量系统,包括温度、压力、流量测量三个方面.该系统基于计算机和力控组态软件,选用合适的传感器,采用A/D采集模块实现紧凑式低温热交换器实验台测试装置数据的实时显示和记录.测量系统具有操作简便、运行可靠等优点.用户界面具有强大的报表功能.该系统实现了低温测量和电量测量的有机结合,其经验可用于指导低温系统测量的数据采集.     

喷射泵-液环泵联合抽空液氧过冷方案仿真研究

采用微元方法对液氧抽空过冷的传热传质过程进行仿真模拟,分析了喷射真空泵工作流体流量和压力、最低被引射流体压力和初始液位对于液氧抽空过程的降压特性、抽空时间及剩余液位的影响,获得喷射真空泵与液环泵联合抽真空的液氧过冷系统最佳工作条件:针对本研究液氧贮存系统,当储罐初始液位95%时,采用喷射真空泵工作流体流量为0.25 kg/s、喷射压力为5 MPa,最低被引射流体压力为34.35 kPa,后采用抽速5 m~3/min的液环泵,可以18小时内将60 m3的液氧储罐抽空至10 kPa,且剩余液位达75%以上。     

柔性极板电容式液位传感器的研究和应用

目的 为了解决传统硬质极板电容式液位传感器在曲面容器上性能不佳的问题.方法 从寄生电容的基本原理出发,研发一种可以包覆于圆柱面容器的柔性极板电容式液位传感器,建立液位与电容量间的数学关系,完成相应的软、硬件设计,通过STM32与柔性极板电容式液位传感器之间的I2C通信,实现液位传感器的在线水位检测,完成传感器性能测试实验,包括线性度、重复性、迟滞特性,并提出一种基于该传感器的流量测量方法.结果 该传感器工作稳定,具有良好线性度,重复性误差为2.70％,在有效测量范围的迟滞特性参数都小于1.69％.结论 该柔性极板电容式液位传感器安装使用便捷、与容器外壁贴合度较好,且测量结果不受容器水平横截面积、待测液体成分的限制,可以实时监测连续液位的变化.制作的传感器可以用在直径20 mm和更小的待测容器上,也可用作微小流量测量.     

基于低温制冷机的低温流体电容式密度测量

设计并搭建了一套基于G-M低温制冷机的电容式密度测量实验装置,由平行板电容器、样品流体测试腔、充排气体管路、低温制冷机、温度测量与控制单元、压力测量单元、真空绝热保护腔以及高真空排气系统八个部分组成。该系统适用温度测量范围为15—300 K,压力测量范围0.01—0.3 MPa。实验中的低温液体由常温气体经低温制冷机冷却液化得到,并蓄存在装有平行板电容器的样品测试腔内。该测试腔上开有视窗,可用于观察冷却过程中低温液体的形成及其液位。对受控压力及温度下的液氮、液氩两种低温流体的密度进行了测量,所得数据与文献实验值及美国NIST标准数据吻合良好,液相区相对偏差小于±0.5%。该密度测量系统今后可用于测量其他流体(包括混合物)在低温下的p-ρ-T数据,还有望经过改进和集成化设计后实现LNG和空分等工业领域的低温流体密度在线实时监测。     

Development of density and mass flow rate measurement technologies for slush hydrogen

Slush hydrogen is a two-phase solid-liquid cryogenic fluid consisting of solid hydrogen particles in liquid hydrogen. Compared to liquid hydrogen, the density is about 16% greater at a solid mass ratio (solid fraction) of 50%, and the cryogenic heat capacity (enthalpy) is about 18% higher. Various applications are anticipated, including fuel for reusable space shuttles, coolant for cold neutron generation, as well as the transport and storage of hydrogen as a clean energy source. At a solid fraction of within 50%, piped transport can be conducted in the same way as for normal fluids. This paper reports on the slush hydrogen technology in terms of the measurement of the density and the mass flow rate.     

Capacitance based mass metering for cryogenic fluids

This paper describes a method for measuring the mass of cryogenic fluids in on-board rocket propellant tanks or ground storage tanks. Linear approximations to the Clausius-Mossotti relationship serve as the foundation for a capacitance based mass sensor, regardless of fluid density stratification or tank shape. Sensor design considerations are presented along with the experimental results for a capacitance based mass gage tested in liquid nitrogen. This test data is shown to be consistent with theory resulting in a demonstrated mass measurement accuracy of ±0.75% and a deviation from linearity of less than ±0.30% of full scale mass. Theoretical accuracies are also shown to be ±0.73% for hydrogen and ±1.39% for oxygen for a select range of pressures and temperatures.     

含二氧化碳和水蒸气的氮气增压输送液氮模拟试验

进行了低温液体火箭推进系统的液氧箱自生增压输送过程的模拟试验，专门设计加工了液氮箱增压输送模拟试验台，试验得出了液氮增压输送过程中温度、压力、流量的变化规律以及含饱和CO2、H2O的氮气通过过滤器时，对系统的流量和压降的影响。指出为保证低温流量计测量准确，必须重视在避免管路中出现两相流方面采取措施。试验结果表明，本试验装置能有效地进行含CO2、H2O(气)的氮气增压输送试验，保证了试验的圆满成功。     

基于AMESim的液氮可控传输性能分析

针对超低温冷却加工液氮可控传输难题,分析了热流量、管路压降等复杂因素对液氮可控传输的影响机制,提出了基于AMESim的液氮可控传输性能分析方法,建立了受热管道液氮两相流动传热数值模型,并在此基础上,研制出一套液氮可控传输原理性系统。通过对比实验表明,提高系统的输入压力能够增大低温流体的流量,缩短系统进入热平衡状态的时间,提高输出流体的干度和流型的稳定性;研制出的液氮可控传输原理性系统在输入压力为1.3 MPa时,在一定的开口范围内,能够稳定输出流量可控的低干度流体,且符合超低温冷却加工的要求。     

Two-phase cryogenic flow meters: Part I – Realization of the calorimetric method

While operating with multicomponent flows, one needs to determine such characteristics as temperature, pressure, mass flow rate and component composition – mass quality, and void fraction. The main attention is given to measurement of mass flow rate of the two-phase cryogenic flows which can be used for superconducting accelerators, refueling hydrogen system for space and liquid natural gas industry, in particular. On the one hand, a two-phase flow is one of the simplest cases of multi-component flows which can be observed in cryogenics. On the other hand, this is rather sophisticated problem in cryogenics to create two-phase flow meters and estimate their metrological characteristics. This problem is discussed. Two methods are suggested – calorimetric and pressure drop ones. Features of the calorimetric method are discussed in this part.     

An experimental study on flow patterns and heat transfer characteristics during cryogenic chilldown in a vertical pipe

In the present paper, the experimental results of a cryogenic chilldown process are reported. The physical phenomena involve unsteady two-phase vapor–liquid flow and intense boiling heat transfer of the cryogenic fluid that is coupled with the transient heat conduction inside pipe walls. The objective for the present study is to compare the chilldown rates and flow patterns between the upward flow and downward flow in a vertical pipe. Liquid nitrogen is employed as the working fluid and the test section is a vertical straight segment of a Pyrex glass pipe with an inner diameter of 8 mm. The effects of mass flow rate on the flow patterns, heat transfer characteristics and interface movement were determined through experiments performed under several different mass flow rates. Through flow visualization, measurement and analysis on the flow patterns and temperature variations, a physical explanation of the vertical chilldown is given. By observing the process and analyzing the results, it is concluded that pipe chilldown in a vertical flow is similar to that in microgravity to some extent.     

Free-surface flow of liquid oxygen under non-uniform magnetic field

The paramagnetic property of oxygen makes it possible to control the two-phase flow at cryogenic temperatures by non-uniform magnetic fields. The free-surface flow of vapor-liquid oxygen in a rectangular channel was numerically studied using the two-dimensional phase field method. The effects of magnetic flux density and inlet velocity on the interface deformation, flow pattern and pressure drop were systematically revealed. The liquid level near the high-magnetic channel center was lifted upward by the inhomogeneous magnetic field. The interface height difference increased almost linearly with the magnetic force. For all inlet velocities, pressure drop under 0.25 T was reduced by 7–9% due to the expanded local cross-sectional area, compared to that without magnetic field. This work demonstrates the effectiveness of employing non-uniform magnetic field to control the free-surface flow of liquid oxygen. This non-contact method may be used for promoting the interface renewal, reducing the flow resistance, and improving the flow uniformity in the cryogenic distillation column, which may provide a potential for enhancing the operating efficiency of cryogenic air separation.     

Investigation of helium injection cooling to liquid oxygen propellant chamber

Sub-cooling of cryogenic propellant by helium injection is one of the most effective methods for suppressing bulk boiling and keeping sub-cooled liquid oxygen before rocket launch. In order to design the cooling system, understanding of the limitations of heat and mass transfer is required. In this paper, an analytical model for the helium injection system is presented. This model’s main feature is the representation of bubbling system using finite-rate heat transfer and instantaneous mass transfer concept. With this simplified approach, the effect of helium injection to liquid oxygen system under several circumstances is examined. Experimental results along with simulations of single bubble rising in liquid oxygen and bubbling system are presented with various helium injection flow rates, helium temperatures, and injection methods. The overall cooling effect for rocket application is also discussed.     

Experimental study of cryogenic liquid turbine expander with closed-loop liquefied nitrogen system

A cryogenic liquid turbine expander is developed as a replacement for traditional Joule–Thomson valves used in the cryogenic systems for the purpose of energy saving. An experimental study was conducted to evaluate the performance of the turbine expander and is the subject of this paper. The test rig comprises a closed-loop liquefied nitrogen system, cryogenic liquid turbine expander unit, and its auxiliary and measuring systems. The test operating parameters of the turbine expander are determined on the basis of flow similarity rules. Pre-cooling of the liquid nitrogen system is first performed, and then the tests are conducted at different flow rates and speed ratios. The turbine expander flow rate, inlet and outlet pressure and temperature, rotational speed and shaft torque were measured. Experimental results and their uncertainties were analyzed and discussed. The following are demonstrated: (1) For both test cases, turbine expander peak isentropic efficiency is respectively 78.8% and 68.4% obtained at 89.6% and 92% of the design flow rate. The large uncertainties in isentropic efficiency are caused by the large enthalpy variations subjected to small measurement uncertainties in temperature and pressure. (2) Total efficiency and hydraulic efficiency of the turbine expander are obtained. They are essentially the same, since both include flow-related effects and also bearing losses. Comparisons of total efficiency and hydraulic efficiency were used to justify measurement uncertainties of different quantities, since the former involves the measured mass flow rate and enthalpy drop (being dependant on inlet and outlet temperature and pressure), while the latter involves the actual shaft power, volume flow rate, and inlet and outlet pressure. (3) Losses in flow passages and the shaft-bearing system have been inferred based on the measured turbine expander total efficiency, isentropic efficiency, and mechanical efficiency, which are respectively 57.6–74.8%, 62.1–78.8% and 89.5–96.4%. Uncertainty analysis is conducted for experimental isentropic efficiency, hydraulic efficiency, and total efficiency. The hydraulic efficiency seems to be the best measure for assessing the performance of cryogenic liquid turbine expander. (4) Isentropic efficiency versus speed ratio is obtained from the experimental data. The experimental isentropic efficiency increases with the speed ratio, and it reaches 78.8% at the largest experimental speed ratio. A higher efficiency would be achieved if the speed ratio could reach a larger value. This provides some guidance for an optimal operation of the turbine expander in the future.     

Wicking of liquid nitrogen into superheated porous structures

Evaporation in porous elements of liquid–vapor separation devices can affect the vapor-free cryogenic propellant delivery to spacecraft engines. On that account, the capillary transport of a cryogenic liquid subjected to evaporation needs to be understood and assessed. We investigate wicking of liquid nitrogen at saturation temperature into superheated porous media. A novel test facility was built to perform wicking experiments in a one-species system under non-isothermal conditions. A setup configuration enabled to define the sample superheat by its initial position in a stratified nitrogen vapor environment inside the cryostat. Simultaneous sample weight and temperature measurements indicated the wicking front velocity. The mass of the imbibed liquid nitrogen was determined varying the sample superheat, geometry and porous structure. To the author’s extent of knowledge, these are the first wicking experiments performed with cryogenic fluids subjected to evaporation using the weight–time measurement technique. A one-dimensional macroscopic model describes the process theoretically. Results revealed that the liquid loss due to evaporation at high sample superheats leads to only a slight imbibition rate decrease. However, the imbibition rate can be greatly affected by the vapor flow created due to evaporation that counteracts the wicking front propagation.