高真空多层绝热低温容器完全真空丧失后传热及绝热夹层内温度分布规律实验

在搭建了高真空多层绝热低温容器完全真空丧失传热研究实验台的基础上,分别利用干燥氮气、二氧化碳、氧气、氦气及空气为破空介质,进行了高真空多层绝热低温容器发生完全真空丧失事故后的传热实验研究.实验中通过流量计和温度采集系统测得了高真空多层绝热低温容器在发生完全真空丧失事故后的排放率和绝热夹层内的温度分布规律.实验结果表明,...     

高真空多层绝热低温容器真空丧失后的传热试验

利用一个工业化的高真空多层绝热低温量热器,以液氮为介质研究了真空突然丧失对高真空多层绝热低温容器漏热量的影响.主要研究了低温量热器绝热层的变化及破空气体(空气和干燥氮气)的不同对真空丧失后低温容器漏热量的影响,指出绝热层数和破空气体种类都是影响真空丧失后低温容器漏热量的重要因素.     

不同种类破空气体对高真空多层绝热低温容器真空丧失后传热的影响

通过实验,分别利用氮气、空气、氧气和氦气作为破空气体,对高真空多层绝热低温容器在真空完全丧失后的漏热进行了研究。结果表明,多层绝热结构对于绝热真空完全丧失后的低温容器能够起到一定的保护作用,初始和最终漏热和渗入到绝热真空夹层中气体的性质密切相关。     

Experimental investigation of the influence of different leaking gases on the heat transfer in a HVMLI cryogenic tank after SCLIV

This paper presented an experimental investigation of the influence of different leaking gases on the heat transfer process in a high-vacuum-multilayer-insulation (HVMLI) cryogenic tank after sudden catastrophic loss of insulation vacuum (SCLIV). The experiments were conducted with the breakdown of the insulation vacuum with nitrogen, air, helium, oxygen, argon, carbon dioxide and the gas mixture of argon and carbon dioxide. The maximum value of the venting rate and heat flux could be ordered as following: CO₂ > O₂ > Ar > the gas mixture > He > Air > N₂, while the average value of the venting rate and heat flux could be ordered as following: O₂ > Ar > He > the gas mixture > CO₂ > Air > N₂. The temperature distribution indicated that phase change heat transfer happened in the insulation jacket after the five different gases including air, argon, the gas mixture of argon and carbon dioxide, oxygen and carbon dioxide were introduced into the insulation jacket.     

用于低温存储系统的多层绝热性能分析

真空多层绝热的性能好坏直接影响到低温贮箱的安全性。根据修正的Lockheed模型,计算冷边界温度、热边界温度、层密度等对均匀层密度多层绝热性能影响,并对三区域变密度的多层绝热性能进行分析,最后针对在轨、地面状态时对低温贮箱漏热方面的要求提出采用复合多层绝热的概念,得出复合多层绝热具有优良的隔热性能。     

Wrapped multilayer insulation design and testing

New vehicles need improved cryogenic propellant storage and transfer capabilities for long duration missions. Multilayer insulation (MLI) for cryogenic propellant feedlines is much less effective than MLI tank insulation, with heat leak into spiral wrapped MLI on pipes 3–10 times higher than conventional tank MLI. Better insulation for cryogenic feed lines is an important enabling technology that could help NASA reach cryogenic propellant storage and transfer requirements. Improved insulation for Ground Support Equipment could reduce cryogen losses during launch vehicle loading. Wrapped-MLI (WMLI) is a high performance multilayer insulation using innovative discrete spacer technology specifically designed for cryogenic transfer lines and Vacuum Jacketed Pipe (VJP) to reduce heat flux.The poor performance of traditional MLI wrapped on feed lines is due in part to compression of the MLI layers, with increased interlayer contact and heat conduction. WMLI uses discrete spacers that maintain precise layer spacing, with a unique design to reduce heat leak. A Triple Orthogonal Disk spacer was engineered to minimize contact area/length ratio and reduce solid heat conduction for use in concentric MLI configurations.A new insulation, WMLI, was developed and tested. Novel polymer spacers were designed, analyzed and fabricated; different installation techniques were examined; and rapid prototype nested shell components to speed installation on real world piping were designed and tested. Prototypes were installed on tubing set test fixtures and heat flux measured via calorimetry. WMLI offered superior performance to traditional MLI installed on cryogenic pipe, with 2.2 W/m² heat flux compared to 26.6 W/m² for traditional spiral wrapped MLI (5 layers, 77–295 K). WMLI as inner insulation in VJP can offer heat leaks as low as 0.09 W/m, compared to industry standard products with 0.31 W/m. WMLI could enable improved spacecraft cryogenic feedlines and industrial hot/cold transfer lines.     

B型LNG模拟舱内低温流体两相流动与相变传热数值研究

本文以内容积为40 m3，绝热层厚度为400 mm的新型独立B型液化天然气船模拟舱为研究对象，对模拟舱内低温流体的两相流动及相变传热问题进行了非稳态三维CFD模拟。采用流体体积函数（VOF）模型追踪气液相界面，利用Lee模型作为相变模型，在相变模型中考虑了静压的影响，对模拟舱的温度分布及静态BOG生成速率进行了计算。研究了在不同液位以及绝热层存在破损的情况下模拟舱的温度分布及静态BOG生成速率的变化，同时研究了当模拟舱密闭时的增压特性。对比模拟结果与实验结果，偏差在10%以内，模型对模拟舱内的低温液体的蒸发过程模拟较好，可为新型独立B型液化天然气实船的设计和改进提供参考。     

Three-dimensional analysis for liquid hydrogen in a cryogenic storage tank with heat pipe–pump system

This paper presents a study on fluid flow and heat transfer of liquid hydrogen in a zero boil-off cryogenic storage tank in a microgravity environment. The storage tank is equipped with an active cooling system consisting of a heat pipe and a pump–nozzle unit. The pump collects cryogen at its inlet and discharges it through its nozzle onto the evaporator section of the heat pipe in order to prevent the cryogen from boiling off due to the heat leaking through the tank wall from the surroundings. A three-dimensional (3-D) finite element model is employed in a set of numerical simulations to solve for velocity and temperature fields of liquid hydrogen in steady state. Complex structures of 3-D velocity and temperature distributions determined from the model are presented. Simulations with an axisymmetric model were also performed for comparison. Parametric study results from both models predict that as the speed of the cryogenic fluid discharged from the nozzle increases, the mean or bulk cryogenic fluid speed increases linearly and the maximum temperature within the cryogenic fluid decreases.     

有效导热系数对低温容器日蒸发率的影响

低温容器是气体液化分离加工工业中的重要设备，绝热设计是低温容器设计的重要组成部分，它直接影响低温容器的日蒸发率。在不同的绝热材料和一定漏热温差的条件下，给出了普通绝热和真空粉末绝热型低温容器的日蒸发率与热材料的有效导热系数以及绝热层厚度之间的关系曲线。为简化设计和比较低温容器的特性提供方法和依据。     

Cryogenic propellant liquefaction and storage for a precursor to a human Mars mission

An analysis of cryogenic liquefaction and storage methods for in-situ produced propellants (oxygen and methane) on Mars is presented. The application is to a subscale precursor sample return mission, intended to demonstrate critical cryogenic technologies prior to a human mission. A heat transfer analysis is included, resulting in predicted cryogenic tank surface temperatures and heat leak values for different conditions. Insulation thickness is traded off against cryocooler capacity to find optimum combinations for various insulation configurations, including multilayer insulation and microspheres. Microsphere insulation is shown to have promise, and further development is recommended.     

低温容器在水蒸气膜态凝结前后的绝热效果分析

绝热失效严重影响了低温容器的经济和安全运行。膜态凝结的出现是绝热失效最直接的表现。提出了用低温容器表面温度与空气露点温度的比较来判别低温容器的绝热是否失效的方法。理论上,分析了低温容器表面水蒸气膜态凝结出现前后的换热机理。在一个高真空多层绝热低温容器上进行了实验,测量并分析了水蒸气膜态凝结前后低温容器表面温度和液氮蒸发速度的变化。理论分析和实验均验证该方法对于判别绝热效果的有效性和可行性。     

Numerical modeling of self-pressurization and pressure control by a thermodynamic vent system in a cryogenic tank

This paper presents a numerical model of a system-level test bed—the multipurpose hydrogen test bed (MHTB) using the Generalized Fluid System Simulation Program (GFSSP). MHTB is representative in size and shape of a space transportation vehicle liquid hydrogen propellant tank, and ground-based testing was performed at NASA Marshall Space Flight Center (MSFC) to generate data for cryogenic storage. GFSSP is a finite volume-based network flow analysis software developed at MSFC and used for thermofluid analysis of propulsion systems. GFSSP has been used to model the self-pressurization and ullage pressure control by the Thermodynamic Vent System (TVS). A TVS typically includes a Joule–Thompson (J–T) expansion device, a two-phase heat exchanger (HEX), and a mixing pump and liquid injector to extract thermal energy from the tank without significant loss of liquid propellant. For the MHTB tank, the HEX and liquid injector are combined into a vertical spray bar assembly. Two GFSSP models (Self-Pressurization and TVS) were separately developed and tested and then integrated to simulate the entire system. The Self-Pressurization model consists of multiple ullage nodes, a propellant node, and solid nodes; it computes the heat transfer through multilayer insulation blankets and calculates heat and mass transfer between the ullage and liquid propellant and the ullage and tank wall. A TVS model calculates the flow through a J–T valve, HEX, and spray and vent systems. Two models are integrated by exchanging data through User Subroutines of both models. Results of the integrated models have been compared with MHTB test data at a 50% fill level. Satisfactory comparison was observed between tests and numerical predictions.     

卧式高真空多层绝热低温容器无损贮存规律

介绍了卧式低温容器的传热特点,以及低温液体无损贮存的传热模型.通过2m3卧式高真空多层绝热低温容器在90%、85%和80%初始充满率下的静态无损贮存试验,拟合现有的传热模型,对升压过程中不同规律的3个阶段进行了分析,得到了第一、第三阶段升压的初步规律.     

变密度多层绝热的理论分析

讨论了一种新型的多层绝热结构,针对径向内外侧不同层间辐射阻断的强弱比例特征、材料重量、以及结构强度,对多层材料的布置进行了优化设计.主要分析多层绝热的绝热性能随层密度分布的变化规律,寻找特定条件下最优化层密度的分布方式,并研究了最优化层密度分布方式与绝热系统各参数之间的关系.     

Short-time heat impulse intensification of heat transfer in liquid nitrogen

The cryogenic technology deals with fluids produced from gases after liquefaction. Boiling of cryogenic fluids is frequently characterized by a hysteresis of their boiling curve. The present experimental work demonstrates an opportunity to intensify heat transfer in those fluids by means of short-term heat impulsion from a heater. The intensification takes place due to the impulse-induced transition of heat transfer regime from natural convection towards nucleate boiling. The process takes place when the impulse magnitude overcomes certain minimum value that was quantified experimentally. We also propose a theoretical expression for the minimum energy that is in agreement with the experimental data.     

低温液体容器无损存储传热模型

分析了低温液体容器无损存储时的传热规律,并建立了传热模型,得出了反映储罐绝热层温度变化的微分方程式。采用数值差分法可以求解出绝热层内部温度变化规律,从而推出储罐内液体的温度和压力的变化规律。     

低温推进剂贮箱增压过程的传热传质数学模拟

针对火箭发动机地面试验中低温液氧贮箱的预增压和增压过程建立了气相空间的传热、传质数学模型.运用实际气体的状态方程、连续性方程、能量守恒方程以及推进剂与气相空间的传热、传质方程等组成了关于气相空间参数的微分方程组,并运用四阶Runge-Kutta算法对其进行求解.获得了气相空间的压力、温度、增压气体流量、液氧挥发速率以及贮箱壁温等参数的变化规律.结果表明,在发动机启动前的预增压过程中,气相空间的温度和压力急剧增加,液氧的挥发速率也增加很快;发动机启动后的保持增压阶段,由于气相空间的体积不断发生变化,气相空间参数的变化趋于平缓,液氧表面向气相空间的传质速率也趋于稳定.     

Experimental study of the influences of degraded vacuum on multilayer insulation blankets

The paper presented experimental investigation on the heat transfer of MLI with different rarefied gases at different pressures. The investigations were carried out using an innovative static liquid nitrogen boil-off rate measurement system in the case of the small temperature perturbations of cold and warm boundaries. The heat fluxes for a number of inert and some polyatomic gases have been analyzed at different heat transfer conditions ranging from molecular to continuum regime, apparent thermal conductivities of the multilayer insulation were measured over a wide range of temperature (77 K–300 K) and pressure (10⁻³–10⁵ Pa) using the apparatus. The experimental results indicated that under degraded vacuum condition, the influences of rarefied gas on the MLI thermal performance very depend on the gas rarefaction degree which impacted by the MLI vacuum degree. Under the condition of molecular regime heat transfer, the MLI thermal performance was greatly influenced by gas energy accommodation coefficients (EAC), when under the continuum regime, the performances depend on the thermal conductivity of rarefied gas itself. Compared to the results of N₂, Ar, CO₂, Air and He as interstitial gases in the MLI, Ar was the better selection as space gas because of its low EAC and thermal conductivity characteristics on the different vacuum condition ranging from high pressure to vacuum. So different residual gases can be utilized according to the vacuum level and gas energy accommodation coefficient, in order to improve the insulation performance of low vacuum MLI.     

Electric field effects on boiling heat transfer of liquid nitrogen

This paper describes an experimental study into the influence of a d.c. uniform electric field on boiling heat transfer characteristics of liquid nitrogen. The electric field effect on the onset of boiling, nucleate boiling curve, hysteresis phenomenon and critical heat transfer were quantitatively investigated using a mesh-plane electrode system. For this purpose, a novel copper block electrode with temperature measurement and vacuum heat insulation was designed and manufactured. Moreover, a heat transfer model based on this electrode geometry has been developed in order to provide some useful data for the electrode design and assist temperature calculations. Detailed heat transfer processes appearing on the copper surface were observed and monitored using a high-speed camera. The experimental results show that electric fields have an obvious effect on boiling heat transfer of liquid nitrogen.     

Spray-on foam insulations for launch vehicle cryogenic tanks

Spray-on foam insulation (SOFI) has been developed for use on the cryogenic tanks of space launch vehicles beginning in the 1960s with the Apollo program. The use of SOFI was further developed for the Space Shuttle program. The External Tank (ET) of the Space Shuttle, consisting of a forward liquid oxygen tank in line with an aft liquid hydrogen tank, requires thermal insulation over its outer surface to prevent ice formation and avoid in-flight damage to the ceramic tile thermal protection system on the adjacent Orbiter. The insulation also provides system control and stability throughout the lengthy process of cooldown, loading, and replenishing the tank. There are two main types of SOFI used on the ET: acreage (with the rind) and closeout (machined surface). The thermal performance of the seemingly simple SOFI system is a complex array of many variables starting with the large temperature difference of 200–260 K through the typical 25-mm thickness. Environmental factors include air temperature and humidity, wind speed, solar exposure, and aging or weathering history. Additional factors include manufacturing details, launch processing operations, and number of cryogenic thermal cycles. The study of the cryogenic thermal performance of SOFI under large temperature differentials is the subject of this article. The amount of moisture taken into the foam during the cold soak phase, termed Cryogenic Moisture Uptake, must also be considered. The heat leakage rates through these foams were measured under representative conditions using laboratory standard liquid nitrogen boiloff apparatus. Test articles included baseline, aged, and weathered specimens. Testing was performed over the entire pressure range from high vacuum to ambient pressure. Values for apparent thermal conductivity and heat flux were calculated and compared with prior data. As the prior data of record was obtained for small temperature differentials on non-weathered foams, analysis of the different methods is provided. Recent advancements and applications of SOFI systems on future launch vehicles and spacecraft are also addressed.