Molecule Dynamics Study on Heat Transfer at Gas-Nanoparticle Interface

The molecular dynamics (MD) simulations were used to understand the heat transfer process between the gas phase and the solid skeleton in the nanoporous silica aerogels. The amorphous silica nanoparticles were generated by the MD simulations and the energy accommodation coefficient (EAC) between the gases and the nanoparticles was calculated based on the results of the nonequilibrium molecular dynamics (NEMD) simulations. The apparent thermal conductivity (ATC) of the gases between the heat source and heat sink was also obtained. The effects of the temperature, the particle diameter and the molecule type on the EAC and the ATC were investigated. The results indicate that the EAC decreases with the increase of temperature within the calculating range. When the preset temperature is constant, the EAC increases with the increasing of the particle diameter and eventually approaches a specific value. When the preset temperature is 300 K and the particle size is 4 nm, the obtained EAC for the N2 gas and the O2 gas is close to each other and both are less than that of the Ar gas. The results also indicate that the heat transferred through the gas-nanoparticle interface is far less than that through the neighbouring nanoparticles in silica aerogels.     

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.     

Heat flux from 277 to 77 K through a few layers of multilayer insulation

The insulating ability of a multilayer insulation (MLI) system, consisting of a few layers on an aluminium taped 77 K surface, was experimentally studied to understand quantitatively how thermal performance changes with the number of multilayers and vacuum level. This information can help to make design decisions trading-off the cost of material and installation manpower against liquid nitrogen consumption in many cryogenic applications. The ratios of the measured heat flux for different systems are: Q(_painted) : Q(_taped) : Q(_{5 layers}) : Q(_{10 layers}) : Q(_{20 layers}) Q(_{30 layers}) = 1 : 0.19 : 0.06 : 0.037 : 0.027 : 0.022. The effective thermal conductivity also increases with the number of layers so only a marginal benefit can be gained in excess of 30 layers; for large liquid vessels 30–40 layers are recommended. The heat flux and temperature distribution in the MLI were also measured as functions of vacuum pressure. The temperature of the last layer is closer to the temperature of the warm box than that of the first layer is to the cold surface, even if the last layer is separated from the warm box and the first layer is in contact with the cold surface. The results and heat transfer mechanisms through MLI are analysed and discussed.     

Techniques of vacuum pumping in multi-layer insulated cryogenic vessels

The improvement in heat transfer properties obtained by use of Multi-Layer Insulation (MLI) is reviewed. The introduction of many closely spaced layers of material increases considerably the surface exposed to vacuum and flow restrictions. Experiments have been made to demonstrate that by using correct pump-down procedures the inherent difficulties can be dealt with and the improved insulation properties of MLI can be used to full advantage in laboratory cryostats which are vented and re-pumped frequently. The test apparatus, procedure and calculation are shown in detail. Test results show that the heat losses of MLI at 10⁻⁴ torr are about 10 per cent of the losses of vacuum insulation only at 10⁻⁶ torr. Heat transfer of MLI remains constant at pressures below 10⁻³ … 10⁻⁴ torr. Recommended pump down procedures are given for equipment which is occasionally vented. The importance of cleanliness during installation of MLI, of the use of heating and getter materials is demonstrated. Pump down times to 10⁻⁴ torr of 5 … 6 h after venting were easily obtained in the test system.     

Measurements of the relative momentum accommodation coefficient for different gases with a viscosity vacuum gauge

The viscosity vacuum gauges are based on the gas momentum transfer phenomena between a moving part of the gauge and a stationary surface. Thus, they may be used for the study of the momentum accommodation coefficient for various combinations of gas species and surfaces. The aim of the present work is to determine the momentum accommodation coefficient by means of the viscosity vacuum gauge with vibrating metal ribbon. The relative accommodation coefficient was computed from the measurements for Xe, Ar, He and H₂ on the bronze ribbon of the gauge in the molecular conditions. The values of the relative coefficients were 0.90 for Xe, 0.95 for Ar, 1 for He (values were normalised to data obtained for He) and 0.94 for H₂.     

Investigations into the thermal performance of multilayer insulation (300-77 K) Part 2: Thermal analysis

Simple analytical methods have been employed for heat transfer analysis of experimental data obtained through calorimetric investigations on multilayer insulation (MLI). Sectional heat transfer analysis has shown that the effective thermal conductivity of the MLI varies from section to section of the insulation structure and it has a peak which lies between the middle and warm boundary regions of the MLI. This could be attributed to a peak in residual gas conduction in this region. The theoretical estimation of heat flux through MLI, using a simple analytical model, is also discussed in this paper. This model takes into consideration the non-linear temperature profile of the insulation. The computed heat flux using this model gives a lower (2 to 4 times) value in comparison with the heat flux estimated from calorimetric measurements. A refined model has been suggested which includes the residual gas conduction also in MLI.     

Novel load responsive multilayer insulation with high in-atmosphere and on-orbit thermal performance

Aerospace cryogenic systems require lightweight, high performance thermal insulation to preserve cryopropellants both pre-launch and on-orbit. Current technologies have difficulty meeting all requirements, and advances in insulation would benefit cryogenic upper stage launch vehicles, LH₂ fueled aircraft and ground vehicles, and provide capabilities for sub-cooled cryogens for space-borne instruments and orbital fuel depots. This paper reports the further development of load responsive multilayer insulation (LRMLI) that has a lightweight integrated vacuum shell and provides high thermal performance both in-air and on-orbit.LRMLI is being developed by Quest Product Development and Ball Aerospace under NASA contract, with prototypes designed, built, installed and successfully tested. A 3-layer LRMLI blanket (0.63 cm thick, 77 K cold, 295 K hot) had a measured heat leak of 6.6 W/m² in vacuum and 40.6 W/m² in air at one atmosphere. In-air LRMLI has an 18× advantage over Spray On Foam Insulation (SOFI) in heat leak per thickness and a 16× advantage over aerogel. On-orbit LRMLI has a 78× lower heat leak than SOFI per thickness and 6× lower heat leak than aerogel.The Phase II development of LRMLI is reported with a modular, flexible, thin vacuum shell and improved on-orbit performance. Structural and thermal analysis and testing results are presented. LRMLI mass and thermal performance is compared to SOFI, aerogel and MLI over SOFI.     

Study on the heat transfer of high-vacuum-multilayer-insulation tank after sudden, catastrophic loss of insulating vacuum

One of the worst accidents that may occur in a high-vacuum-multilayer-insulation (HVMLI) cryogenic tank is a sudden, catastrophic loss of insulating vacuum (SCLIV). There is no doubt that the gases leaking into the insulation jacket have some influence on the heat transfer process of it. However, this issue has not been thoroughly studied so far. In this paper, a test rig was built up and experiments were conducted using a SCLIV cryogenic tank and with nitrogen, helium and air as the working medium, respectively. The venting rates of the tank and temperature in the insulation jacket were measured respectively after the three different gases leaking into the jacket. A heat transfer model describing the heat transfer process of a SCLIV tank was also presented. The calculated results using this model were compared against the experimental data. It is found that the heat transfer performance of the HVMLI cryogenic tank after SCLIV is strong relevant to the type of gas leaking into the insulation jacket.     

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。     

A calorimeter for multilayer insulation (MLI) performance measurements at variable temperature

Here we describe a concentric cylindrical calorimeter with radiation guards developed to measure the thermal performance of multilayer insulation (MLI) for low temperature applications. One unique feature of this calorimeter is its ability to independently control the boundary temperatures between room temperature and about 15 K using two single-stage Gifford–McMahon cryocoolers. Also, unlike the existing calorimeters that use the evaporation rate of a liquid cryogen to measure the heat load, in the present system the total heat transfer through the MLI is measured by recording the temperature difference across a calibrated heat load support rod that connects the cold inner cylinder to the lower temperature cryocooler. This design allows the continuous mapping of MLI performance over a much wider temperature range with independently controlled boundary conditions. The calorimeter is also suitable for performing a variety of radiation heat transfer experiments including the determination of the temperature dependence of the total emissivity.     

Determination of tangential momentum accommodation coefficient and slip coefficients for rarefied gas flow in a microchannel

This paper presents an experimental study of rarefied gas flow in a trapezoidal microchannel with a constant depth of 103 µm, top width of 1143 µm, bottom width of 998 µm and length of 2 cm. The aim of the study is to verify the upper limit of the validity of the second-order slip boundary condition to model rarefied gas flows. The slip coefficients and the tangential momentum accommodation coefficient (TMAC) are determined for three different gases, viz. argon, nitrogen and oxygen, and it is observed that they compare well to the literature values. The range of mean Knudsen number (Kn_m) investigated is 0.007–1.2. The non-dimensional mass flow rate exhibits the well-known Knudsen minimum in the transition regime (Kn_m?~?1). It is seen that the Navier–Stokes equation with a second-order boundary condition fits the data satisfactorily with a high value of correlation coefficient (r²?>?99.95%) in the entire range of Kn_m investigated. This work contributes by extending the range of Knudsen number studied in the context of validity of the second-order slip boundary condition.     

Thermal performance of multilayer insulation around a horizontal cylinder

Thermal performance of multiplayer insulation (MLI) is affected by contact pressure between adjacent layers. In order to evaluate the thermal performance of the MLI fabricated in the horizontal cryostats of superconducting magnets, it is important to investigate the contact pressure in the MLI. In case of a horizontal cryostat, the MLI is wound around horizontal cylindrical surface and is compressed at the upper part of the cylinder due to the MLI self-weight. At first, a single thin film wound around the horizontal cylinder was analyzed to evaluate the contact pressure acting on the cylinder. The analysis has been extended to the multiply wound film around horizontal cylinder, in order to investigate the distribution of contact pressure between adjacent layers. By using experimental data obtained with a flat panel calorimeter, the results of this analysis have been applied to evaluate the thermal performance of MLI around a horizontal cylinder. And the non-dimensional contact pressure parameter P^* has been introduced as a useful parameter to evaluate and compare the thermal performance among different kinds of MLI.     

Carbon Aerogel-Based High-Temperature Thermal Insulation

Carbon aerogels, monolithic porous carbons derived via pyrolysis of porous organic precursors synthesized via the sol–gel route, are excellent materials for high-temperature thermal insulation applications both in vacuum and inert gas atmospheres. Measurements at 1773K reveal for the aerogels investigated thermal conductivities of 0.09W · m⁻¹ · K⁻¹ in vacuum and 0.12W · m⁻¹ · K⁻¹ in 0.1MPa argon atmosphere. Analysis of the different contributions to the overall thermal transport in the carbon aerogels shows that the heat transfer via the solid phase dominates the thermal conductivity even at high temperatures. This is due to the fact that the radiative heat transfer is strongly suppressed as a consequence of a high infrared extinction coefficient and the gaseous contribution is reduced since the average pore diameter of about 600nm is limiting the mean free path of the gas molecules in the pores at high temperatures. Based on the thermal conductivity data detected up to 1773K as well as specific extinction coefficients determined via infrared-optical measurements, the thermal conductivity can be extrapolated to 2773K yielding a value of only 0.14W· m⁻¹ · K⁻¹ in vacuum.     

Thermal accommodation coefficient of gases on controlled solid surfaces: Argon-tungsten system

The knowledge of the thermal accommodation coefficient for gases on well-controlled surfaces as a function of temperature is imperative to understanding the mechanism of interphase heat transfer on the microscopic level. With this goal in view, a heat transfer column instrument is designed, fabricated, assembled, and tested for the specific case a argon—tungsten system. With 99.9999%, pure argon, six sets of data are taken in the rarefied gas region in the maximum temperature range of 500–1500 K. Four sets of these measurements are in the temperature-jump region and are analyzed by the constant-power method to compute the thermal accommodation coefficient of argon on a controlled tungsten surface. The other two sets are taken under free-molecular flow conditions and are interpreted in accordance with the man-free-path kinetic theory for the low-pressure regime. These data are compared and discussed in the context of reported data in the literature and interpreted in the light of the surface condition and finish of the tungsten wire.Nomenclature A area of the solid surface - C _j constants in Eq. (3); j=0, 1, 2, 3, and 4 - E _i incident energy flux - E _r reflected energy flux - E _s reflected energy flux when the interaction between the gas and the solid atoms is complete - g temperature-jump distance - L half-length of the metal wire - M molecular weight of the gas - P gas pressure - Q _H total thermal energy conducted by the gas per unit time from the hot surface - Q_KT total thermal energy conducted by the gas per unit time if the striking gas molecules were to attain thermal equilibrium with the hot surface - R molar gas constant - r radial coordinate - r _f radius of the hot wire - S sticking coefficient - S_o initial sticking coefficient - T temperature - T _e linearly extrapolated gas temperature on the hot-wire surface - T _g temperature of the impinging gas molecules - T _H temperature of the hot surface - T _i temperature of the incident gas stream - T _r temperature of the gas molecules receding after collision with the solid surface - T _s temperature of the solid surface Greek Symbols thermal accommodation coefficient for the gas—solid surface - resistivity of the metal wire - gas coverage on the solid surface For an explanation of symbols, see Nomenclature.     

Calculation of Heat Transfer and Drag in Tubes under Conditions of Laminar Flow of Gases with Varying Properties

A numerical investigation is performed of the problem on heat transfer and hydraulic drag in the hydrodynamic and thermal initial sections of a round tube heated by the q _w = const law, under conditions of laminar flow of gases with varying physical properties. Monatomic, diatomic, and polyatomic gases and gas mixtures are treated, as well as the range of heat loads Q ⁺ _in up to 20. The obtained results are used to analyze disagreement between the available literature data; methods are suggested for improving the engineering procedure of thermohydraulic design under laminar flow of gases and the known model of stabilized flow and heat transfer.     

Effect of welding procedure on wear behaviour of a modified martensitic tool steel hardfacing deposit

In the last years hardfacing became an issue of intense development related to wear resistant applications. Welding deposits can functionalize surfaces and reclaim components extending their service life. Tool steels are widely used in hardfacing deposits to provide improved wear properties. Nevertheless systematic studies of wear behaviour of new alloys deposited by hardfacing, under different service conditions are scarce. In this work the effects of shielding gas, heat input and post-weld heat treatment on the microstructural evolution and wear resistance of a modified AISI H13 martensitic tool steel deposited by semi-automatic gas shielded arc welding process using a tubular metal-cored wire, were studied. Four coupons were welded with different welding parameters. The shielding gases used were Ar–2% CO₂ and Ar–20% CO₂ mixtures and two levels of heat input were selected: 2 and 3 kJ/mm. The as welded and 550 °C–2 h post-weld heat treated conditions were considered. From these coupons, samples were extracted for testing metal–metal wear under condition of pure sliding with a load of 500 N. Chemical compositions were determined; microstructure and microhardness were assessed. It was found that content of retained austenite in the microstructure varied with the welding condition and that heat-treated samples showed secondary hardening, associated with precipitation phenomena. Nevertheless, as welded samples showed higher wear resistance than heat treated specimens. Under these test conditions post-weld heat treatment led to a reduction in wear resistance. The best wear behaviour was observed in samples welded with low heat input and under the lowest oxygen potential shielding gas used here, in the as welded condition. The intervening mechanism was mild oxidative. These results were explained in terms of the relative oxidation resistance stemming from different welding conditions.     

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.     

Physical simulation of the interaction effects of <Emphasis Type="Italic">Magnetized</Emphasis> bodies and the Earth’s atmosphere in a hypersonic rarefied plasma flow

It is shown that, in a hypersonic rarefied plasma flow with the met MHD approximation conditions, it is possible to partially physically simulate effects that characterize the interaction of magnetized dielectric bodies and hypersonic gas flow in the continuum regime for a wide Stewart number range of 1 < Q _B ≤ 10³.     

Systematic study to reduce the effects of cracks in multilayer insulation Part 2: experimental results

A series of cracks with different widths and shapes was cut in a multilayer insulation (MLI) blanket. The measured data shows that the incremental heat load per unit slot area has a maximum of ≈ 135 W m⁻². The heat load increment is essentially independent of the preparation of the cold surface under the crack, i.e. its emissivity, if the slot width is sufficiently small. The temperature distribution and the equivalent thermal conductivity near the cracks are quite different from that in a system without cracks. The dependence of the heat load and temperature distribution on the vacuum pressure was also observed. A systematic study of a crack-covering ‘patch’ method to reduce the heat load to a 77 K surface through cracks in a MLI blanket was conducted. The following patch materials were used to determine the optimum distribution of the patches in a 30 layer blanket: 300 ų single aluminized crinkled Mylar (NRC-2) and 1000 Å double aluminized flat Mylar. The experimental results indicated that the use of a patch every few layers is almost as effective as using a patch every layer. Placing the patches in the upper half of the blanket is much better than in the lower half and can reduce the heat load essentially to that without cracks. Putting the same number of patches on top of a crack is much less effective. The data suggest that 1000 Å material is preferable for patches. All of the experimental results are generally in agreement with the enhanced black cavity model.     

Concept for thermal insulation arrangement within a flexible cryostat for HTS power cables

The successful application of high temperature superconducting power cables requires improved flexible cryostats with respect to their thermal heat load between environment (300 K) and LN₂ (77 K) operating temperature. Heat transfer through the thermal insulation consists of thermal radiation, solid and residual gas conduction. Considering this heat load contributions, a new concept for the thermal insulation arrangement is presented in this paper. The main advantage of this concept consists in a separation of the thermal insulation and the supporting structure. This separation protects the thermal insulation from degradation by mechanical load. The fraction of solid heat conduction through this support structure is minimised by small contact areas and high heat conduction lengths. Heat transfer due to residual gas conduction is reduced by improved evacuation conditions close to the cold wall. Finally the structure allows subdivision of the multilayer insulation ensuring an optimal number of layers with respect to their insulation thickness, i.e. an optimal layer density.