Convective heat transfer coefficients for near-horizontal two-phase flow of nitrogen and hydrogen at low mass and heat flux

Correlations for convective heat transfer coefficients are reported for two-phase flow of nitrogen and hydrogen under low mass and heat flux conditions. The range of flowrates, heat flux and tube diameter are representative of thermodynamic vent systems (TVSs) planned for propellant tank pressure control in spacecraft operating over long durations in microgravity environments. Experiments were conducted in normal gravity with a 1.5° upflow configuration. The Nusselt number exhibits peak values near transition from laminar to turbulent flow based on the vapor Reynolds number. This transition closely coincides with a flow pattern transition from plug to slug flow. The Nusselt number was correlated using components of the Martinelli parameter and a liquid-only Froude number. Separate correlating equations were fitted to the laminar liquid/laminar vapor and laminar liquid/turbulent vapor flow data. The correlations give root-mean-squared (rms) prediction errors within 15%.     

Cryogenic heat pipe for cooling high temperature superconductors

The research in this paper investigates a consumable-free method of operating a high temperature superconducting (HTS) coil in space. The HTS wire resides inside a cryogenic heat pipe which is used for isothermalization. This paper presents the design, implementation, and testing of a cryogenic heat pipe for cooling high temperature superconductors. As a proof-of-concept, an 86 cm long straight heat pipe was constructed and enclosed two straight lengths of HTS wire. The working fluid, at saturation condition, maintains a constant temperature below the HTS wire critical temperature. Testing of the heat pipe in a vacuum chamber was conducted to verify the drop in HTS resistance correlating to the wire operating in a superconducting state.     

Operational performance of a cryogenic loop heat pipe with insufficient working fluid inventory

A cryogenic loop heat pipe (CLHP) has been developed for future aerospace applications at the Technical Institute of Physics and Chemistry (TIPC). It has been demonstrated that this CLHP, when placed horizontally, can operate in liquid-nitrogen temperature range and have a heat transfer capability of up to 12 W with proper working fluid inventory. This paper presents some particular characteristics of the CLHP when the compensation chamber is half-filled with liquid-phase working fluid before startup. The device has been tested at different orientations using nitrogen as the working fluid in order to compare its thermal behavior, specially related to the heat transfer capability, the operation temperature and the thermal resistance, as well as to investigate its operational characteristics under power level as low as 1 W. Tests were performed for the CLHP at horizontal position and with the liquid line 3.4 and 6.4 cm below the vapor line, respectively. The experimental results show the operationability of the CLHP tested at three orientations and tests with the liquid line 6.4 cm below the vapor line show lower operation temperatures and higher heat transfer capability.     

Analysis of helium II thermal links for instrument cooling in low gravity

The Low Temperature Microgravity Physics Facility (LTMPF) is a reusable, cryogenic facility that will accommodate a series of low temperature experiments to be conducted at the International Space Station. The facility will use a He II cryostat to cool the instruments. Some configurations of the science instruments in the cryostat will require an enhanced thermal link between the He II bath and parts of the instruments. Such an enhanced link can be made with plumbing filled with He II. This paper reports the results of analysis that was performed using the BATC proprietary helium flow software called SUPERFLO, on four different concepts for this link. The four concepts analyzed were: a simple tube with the heated end closed, a closed end tube with a porous plug at its entrance, a closed end tube filled with capillary tubes, and a porous plug driven flow loop. It was found that the concepts that used a porous plug were more robust since they were much less prone to boiling. This is due to the low gravity which causes all of the liquid in helium tank and plumbing to be very close to saturated conditions unless a porous plug is used to create a thermomechanical pressure. The effects of varying system parameters such as a acceleration, heat flux, pore size and tube size were also investigated and the results are reported.     

Feed system thermal integration for a cryogenic Lunar ascent stage

Cryogenic liquid acquisition devices (LADs) for space-based propulsion interface directly with the feed system, a significant heat leak source. The gradual accumulation of thermal energy within a representative capillary LAD during long-term storage periods (up to 210 days) on the Lunar surface is the main issue addressed. The ongoing program consists of experimental and analytical facets that include: (a) thermal modeling of LAD interior temperatures, (b) computational fluid dynamics (CFD) analyses to define bulk liquid conditions surrounding the LAD, (c) testing and analyses of condensation conditioning techniques for stabilizing LAD liquid retention, and (d) low-cost fluid systems thermal integration testing.     

A simple and efficient thermal link assembly for cryocoolers

The thermal connection between a cryocooler cold tip and any object to be cooled (the thermal load) is very often a technical challenge. The allowed mechanical load on the cooler cold finger is generally strongly restricted. It is therefore difficult to design a mechanically anchored thermal link with low induced mechanical load and high thermal conductance. The proposed heat link concept is based on an evaporation/condensation process between the cooler cold tip and the thermal load.     

Prediction of heat transfer during boiling of cryogenic fluids flowing in tubes

Data from eleven sources for nitrogen, neon, helium, and argon boiling in horizontal and vertical tubes were compared with the correlations of Shah and Klimenko as well as the superposition correlation of Rohsenow. Best agreement was found with the Shah correlation which agrees with nine of the data sets. Each of the other two correlations gives satisfactory agreement with only four of the twelve data sets. The results of data analysis are presented and discussed.     

微通道冷凝器低温回路热管的实验研究

设计了一套以乙烷作为工质,使用微通道冷凝器的低温回路热管原理样机,并对样机的降温过程、传热性能以及再启动特性进行了实验研究。结果表明:在5 W的驱动功率下该低温回路热管可实现快速降温,在降温过程中通过增大蒸发器的加热功率可以加速回路热管的降温;该样机可以在200 K时能够稳定传输50 W的热量,并且随着加热功率的增大,回路热管的热阻不断减小;在回路热管停止工作后,重新施加热量,该样机仍能够正常启动;该样机在本实验中的最大传热功率为54W,此时的热阻为0.46 K/W。     

乙烷温区低温环路热管设计与实验

为了研究低温环路热管在乙烷温区的启动及运行特征,通过自行设计的样机进行了实验.实验表明,在0.7W的驱动功率下,低温环路热管可顺利实现降温启动;运行时,可传递12W的冷量,并且在9W时,传热热阻最小,为1.14 K/W.     

深冷环路热管超临界启动实验研究

深冷环路热管(CLHP)在正常工作之前,整个回路内工质处于超临界状态.通过对毛细芯在液体工质中良好的浸润,保证主蒸发器顺利启动.研究了从储气室位置、副蒸发器功率以及充装压力等影响超临界启动的因素对CLHP超临界启动过程的影响.结果表明:储气室的两种接入位置均能实现超临界启动过程;漏热量一定时,为了使主蒸发器达到启动条件,副蒸发器存在一个最小启动功率,且副蒸发器功率越大主蒸发器降温越迅速;对于回路结构一定的CLHP,当副蒸发器功率一定时,其存在一个最佳充装压力,在该充装条件下能使得启动过程最为迅速.     

Thermal characterisation of a tungsten magnetoresistive heat switch

A magnetoresistive heat switch has been developed to improve the performance of our flight-worthy cryogen-free ADR. We have characterised the switch’s thermal conductivity in the temperature range 0.3-4 K under an applied magnetic field of 1.8 T for two tungsten samples of different purity. The results are discussed relating to the key aspects of semi-classical magnetoresistance theory. We show that crystal purity has a strong effect on switch performance and magnetoresistive effect. Our findings are verified by comparison to results obtained by other authors. The measured switching ratio for our best sample is 1.75 × 10⁴ at 1.5 K and 1.51 × 10⁴ at 4.26 K. The lattice conductivity remains dominated by the electronic conductivity in the investigated range of temperatures under an applied magnetic field of 1.8 T. In order for the lattice conductivity to dominate a purity of >99.999% would be required.     

Thermal design of the CFRP support struts for the spatial framework of the Herschel Space Observatory

Thermal finite element (FE) models, of low thermal conductance struts which are required to provide support for the low temperature components of the Herschel Space Observatory, have been validated by measurements at temperatures below 20 K. The Herschel Space Observatory structure is introduced. FE modelling of two designs of support strut is briefly discussed and the final designs presented. Validation of the design models was made in two experiments. The first of these provided specific thermal conductivity data for component CFRP materials, whose composition was initially designed on the basis of data available in the literature. The second experiment was performed to confirm the thermal conductance (Q′/ΔT), of the completed struts. The validation test rigs are described together with details of the experimental methods employed. Values of conductance were at the level of 5 × 10⁻⁵ W/K at a mean temperature of 6 K. The measured data are presented and discussed with reference to the thermal models. Sources of measurement inaccuracy, are also discussed.     

Neon gas-gap heat switch

A self-contained neon gas-gap heat switch featuring an internal charcoal adsorption pump has been developed and tested. This heat switch can be used with cold base temperature ranging from 17 K to 40 K offering an extension to sorption based helium gas-gap heat switch limited to below 20 K. For this prototype, an ON conductance about 74 mW/K and an OFF resistance about 3000 K/W were obtained, giving an ON/OFF conductance ratio about 220 at 20 K in agreement with calculations obtained from a simple model. These characteristics can be further optimized working on the geometry.     

基于SINDA/FLUINT的低温回路热管整机仿真分析

基于热流分析软件SINDA/FLUINT,对低温回路热管进行了仿真模型分析,得到了它的工作温度、漏热、压降等随热负载的变化关系.将计算结果与实验进行对比,在一定的热负载范围内,仿真结果与实验结果吻合,验证了仿真模型的正确性.通过分析模型的计算结果,可为以后低温回路热管的设计和实验提供参考.     

液氮温区重力辅助深冷回路热管的实验研究

给出了液氮温区重力辅助深冷回路热管结构设计方案,建立了实验系统,对其启动特性和工作性能进行了实验研究.深冷回路热管以高纯氮作为工作液体,工作温区为90 K～126 K.实验结果表明,深冷回路热管能在重力作用下快速启动,在气体管线高于液体管线20 mm的情况下,最大可传送的功率为11W.     

GaAs cryogenic readout electronics for high impedance detector arrays for far-infrared and submillimeter wavelength region

We have been developing cryogenic readout integrate circuits (ROICs) for high impedance submillimeter and far-infrared detectors: Our ROICs are constructed from SONY GaAs-JFETs, which have excellent performance even at less than 1 K. We designed ROICs consisting of analog readouts and digital circuits for 32-element SIS photon detectors fabricated in RIKEN. The analog readout is ac-coupled capacitive transimpedance amplifier (CTIA), which is composed of the two-stage amplifier. Some initial test results of the ac-coupled CTIA gave us the following performance; open loop gain of >740, power consumption ≈1.4 μW. The input referred noise is ≈4 μV/ at 1 Hz. These results suggest that low power and high sensitive cryogenic readout electronics are successfully developed for high impedance detectors.     

Transient thermodynamic behavior of cryogenic mixed fluid thermosiphon and its cool-down time estimation

Thermosiphon is an efficient heat transfer device by utilizing latent heat of fluid at liquid-vapor phase change. One of the disadvantages of thermosiphon, however, is that the operational temperature range is fundamentally limited from the critical point to the triple point of the working fluid to maintain two phase state. Nitrogen (N₂) and tetrafluoromethane (CF₄) were selected as the mixed working fluid to widen their original operational temperature range. Thermodynamic behavior of mixture and its effect on the cool-down time were investigated. A simple calculation model was proposed to estimate the cool-down time of the thermosiphon evaporator prior to experiments. The calculated results agreed well with the experimental results within 5% error. The cool-down time reduction was not achieved by mixing two components at once due to the separation of mixture. One idea to avoid this problem was suggested in this paper where the estimated cool-down time was reduced 17.8% compared to pure N₂.     

Development of double-stage ADR for future space missions

We report a development of a portable dewar with a double-stage ADR in it, and its cooling test results. The purpose of this system is to establish a cooling cycle of double-stage adiabatic demagnetization from 4.2 K to 50 mK, which is strongly desired for future space science missions. In our test dewar, two units of ADR are installed in parallel at the bottom of a liquid He tank. We used 600 g of GGG (Gadolinium Gallium Garnet) for the higher temperature stage (4 Tesla) and ∼90 g of CPA (Chromic Potassium Alum) for the lower temperature stage (3 Tesla). A passive gas-gap heat switch (PGGHS) is used between these two stages, while a mechanical heat switch between the He tank and the GGG stage. Using this system, 50 mK was achieved, and various kinds of cooling cycles with different operating temperatures and different sequences of magnetization were tested. We also evaluated the performance of the PGGHS, and interference of the magnetic field with each other during a stable temperature control.     

Measurement of the heat transfer characteristics of gas flow in fine channel heat exchangers used for microminiature refrigerators

The heat transfer characteristics have been measured for the flow of gas in the fine channels of the heat exchangers used for microminiature J-T refrigerators. The test channels were fabricated using a photolithographic technique similar to that used for the fabrication of the refrigerators. The unique features of such channels are their asymmetric roughness, their large relative roughness and a large variation of the heat flux and temperature over the walls of the channels. The tests involved both laminar and turbulent flow regimes. The results we have obtained are useful for designing heat exchangers in microminiature refrigerators.