logo

SCIENCE CHINA Technological Sciences, Volume 61 , Issue 7 : 994-1002(2018) https://doi.org/10.1007/s11431-017-9250-x

Design and heat transfer analysis of a compound multi-layer insulations for use in high temperature cylinder thermal protection systems

More info
  • ReceivedDec 23, 2017
  • AcceptedApr 8, 2018
  • PublishedMay 30, 2018

Abstract

Thermal protection systems are very essential for high temperature thermal conductivity measurement system to reduce the heat loss to environment at the range of 600–1800 K. A compound multi-layer insulations structure which composed of inner carbon fibrous materials and outer alternately arranged alumina fibrous materials and high reflectivity foils is proposed for use in high temperature cylinder thermal protection systems. A coupled conductive and radiation governing equations is presented for heat transfer analysis of the structure. The finite volume method and the discrete ordinate method are used to solve the governing equations. The optimization structure of the compound multi-layer insulations is investigated by considering the pressure of the gas, the density of the carbon fibrous materials, the density of the alumina fibrous materials, the number of reflective foil layers and the emissivity of reflective foils. The results show that the compound structure has the best thermal insulation performance when the pressure of the gas is below 0.01 kPa, the density of carbon fibrous materials is 180 kg m−3, the density of alumina fibrous materials is 256 kg m−3 and the number of reflective foil layers is 39. In addition, the thermal insulation performance is much better when the emissivity of reflective foils is lower.


Funded by

the National Natural Science Foundation of China(Grant,No.,51225602)


Acknowledgment

This work was supported by the National Natural Science Foundation of China (Grant No. 51225602).


References

[1] Daryabeigi K, Miller S, Cunnington G. Heat transfer in high-temperature multilayer insulation. In: Thermal Protection Systems and Hot Structures. Noordwijk, 2006, 631. Google Scholar

[2] Li P, Cheng H. Thermal analysis and performance study for multilayer perforated insulation material used in space. Appl Therm Eng, 2006, 26: 2020-2026 CrossRef Google Scholar

[3] Ferraiuolo M, Manca O. Heat transfer in a multi-layered thermal protection system under aerodynamic heating. Int J Therm Sci, 2012, 53: 56-70 CrossRef Google Scholar

[4] Xie G, Qi W, Zhang W, et al. Optimization design and analysis of multilayer lightweight thermal protection structures under aerodynamic heating conditions. J Therm Sci Eng Appl, 2013, 5: 011011 CrossRef Google Scholar

[5] Huang C, Zhang Y. Calculation of high-temperature insulation parameters and heat transfer behaviors of multilayer insulation by inverse problems method. Chin J Aeronautics, 2014, 27: 791-796 CrossRef Google Scholar

[6] Ji T, Zhang R, Sunden B, et al. Investigation on thermal performance of high temperature multilayer insulations for hypersonic vehicles under aerodynamic heating condition. Appl Therm Eng, 2014, 70: 957-965 CrossRef Google Scholar

[7] Zhang R, Zhang X, Lorenzini G, et al. Material combinations and parametric study of thermal and mechanical performance of pyramidal core sandwich panels used for hypersonic aircrafts. Continuum Mech Thermodyn, 2016, 28: 1905-1924 CrossRef ADS Google Scholar

[8] Xie G, Zhang R, Manca O. Thermal and thermomechanical performances of pyramidal core sandwich panels under aerodynamic heating. J Therm Sci Eng Appl, 2017, 9: 014503 CrossRef Google Scholar

[9] Hurd J A, Van Sciver S W. Measurements of the apparent thermal conductivity of multi-layer insulation between 20 K and 90 K. In: Weisend II J G, Breon S, Demko J, et al. AIP Conference Proceedings. Tallahassee, 2014. 694–700. Google Scholar

[10] Smith C, Mckinley I, Ramsey P, et al. Performance of multi-layer insulation for spacecraft instruments at cryogenic temperatures. In: 46th International Conference on Environmental Systems. Vienna, 2016. Google Scholar

[11] Liu Z, Li Y, Xie F, et al. Thermal performance of foam/MLI for cryogenic liquid hydrogen tank during the ascent and on orbit period. Appl Therm Eng, 2016, 98: 430-439 CrossRef Google Scholar

[12] Spinnler M, R.F. Winter E, Viskanta R, et al. Theoretical studies of high-temperature multilayer thermal insulations using radiation scaling. J Quant Spectr Radiative Transfer, 2004, 84: 477-491 CrossRef ADS Google Scholar

[13] Spinnler M, Winter E R F, Viskanta R. Studies on high-temperature multilayer thermal insulations. Int J Heat Mass Transfer, 2004, 47: 1305-1312 CrossRef Google Scholar

[14] Pasztory Z, Peralta P N, Peszlen I. Multi-layer heat insulation system for frame construction buildings. Energy Buildings, 2011, 43: 713-717 CrossRef Google Scholar

[15] Mavromatidis L E, Bykalyuk A, El Mankibi M, et al. Numerical estimation of air gaps’ influence on the insulating performance of multilayer thermal insulation. Building Environ, 2012, 49: 227-237 CrossRef Google Scholar

[16] Jensen C, Xing C, Folsom C, et al. Design and validation of a high-temperature comparative thermal-conductivity measurement system. Int J Thermophys, 2012, 33: 311-329 CrossRef ADS Google Scholar

[17] Scoarnec V, Hameury J, Hay B. A new guarded hot plate designed for thermal-conductivity measurements at high temperature. Int J Thermophys, 2015, 36: 540-556 CrossRef ADS Google Scholar

[18] Pillai C G S, George A M. An improved comparative thermal conductivity apparatus for measurements at high temperatures. Int J Thermophys, 1991, 12: 563-576 CrossRef ADS Google Scholar

[19] Chen Q, Wang Y F. Differences and relations of objectives, constraints, and decision parameters in the optimization of individual heat exchangers and thermal systems. Sci China Tech Sci, 2016, 59: 1071-1079 CrossRef Google Scholar

[20] Baxter R I, Iwashita N, Sawada Y. Effect of halogen purification and heat treatment on thermal conductivity of high porosity carbon/carbon composite thermal insulation. J Mater Sci, 2000, 35: 2749-2756 CrossRef ADS Google Scholar

[21] Daryabeigi K. Design of high-temperature multi-layer insulation for reusable launch vehicles. Doctoral Dissertation. Charlattesville: University of Virginia, 2000. Google Scholar

[22] Stark C, Fricke J. Improved heat-transfer models for fibrous insulations. Int J Heat Mass Transfer, 1993, 36: 617-625 CrossRef Google Scholar

[23] Modest M F. Radiative Heat Transfer. London: Academic Press, 2013. 26–27. Google Scholar

[24] Stauffer T, Jog M, Ayyaswamy P. The effective thermal conductivity of multi foil insulation as a function of temperature and pressure. AIAA Paper, 1992. 2992–2939. Google Scholar

[25] Lee S C, Cunnington G R. Conduction and radiation heat transfer in high-porosity fiber thermal insulation. J Thermophys Heat Transfer, 2000, 14: 121-136 CrossRef Google Scholar

[26] Zhang B M, Zhao S Y, He X D. Experimental and theoretical studies on high-temperature thermal properties of fibrous insulation. J Quant Spectr Radiative Transfer, 2008, 109: 1309-1324 CrossRef ADS Google Scholar

[27] Daryabeigi K. Thermal analysis and design optimization of multilayer insulation for reentry aerodynamic heating. J Spacecraft Rockets, 2002, 39: 509-514 CrossRef ADS Google Scholar

[28] Baxter R I, Rawlings R D, Iwashita N, et al. Effect of chemical vapor infiltration on erosion and thermal properties of porous carbon/carbon composite thermal insulation. Carbon, 2000, 38: 441-449 CrossRef Google Scholar

[29] Kingery W D, Francl J, Coble R L, et al. Thermal conductivity: X, data for several pure oxide materials corrected to zero porosity. J Am Ceramic Soc, 1954, 37: 107-110 CrossRef Google Scholar

[30] Ho C Y, Powell R W, Liley P E. Thermal conductivity of the elements. J Phys Chem Reference Data, 1972, 1: 279-421 CrossRef ADS Google Scholar

[31] Shao W, Cui Z, Wang N H, et al. Numerical simulation of heat transfer process in cement grate cooler based on dynamic mesh technique. Sci China Tech Sci, 2016, 59: 1065-1070 CrossRef Google Scholar

[32] Wang J S, Dong Y W. The numerical investigation of flow and heat transfer characteristics of flow past a slit-cylinder. Sci China Tech Sci, 2017, 60: 602-612 CrossRef Google Scholar

[33] Sun P J, Wu J Y, Zhang P, et al. Experimental study of the influences of degraded vacuum on multilayer insulation blankets. Cryogenics, 2009, 49: 719-726 CrossRef ADS Google Scholar

  • Figure 1

    (Color online) Schematic of the compound multi-layer insulations for high temperature cylinder heating system. The dimension is given in millimeter.

  • Figure 2

    (Color online) The heat transfer model of the compound multi-layer insulation.

  • Figure 3

    (Color online) Grid independent study for different hot boundary temperature.

  • Figure 4

    (Color online) Steady state temperature distribution of the compound multi-layer insulation for hot boundary temperature of 1800 K.

  • Figure 5

    (Color online) Comparison of effective thermal conductivity of multi-layer insulations between numerical results and experimental data from ref. [31].

  • Figure 6

    (Color online) External surface temperature of the compound MLIs varied with hot boundary temperature under different gas pressure.

  • Figure 7

    (Color online) External temperature of the compound MLIs varied with hot boundary temperature under different density of carbon fibrous materials.

  • Figure 8

    (Color online) External temperature of the compound MLIs varied with hot boundary temperature under different density of alumina fibrous materials.

  • Figure 9

    (Color online) External temperature of the compound MLIs varied with hot boundary temperature under different number of the reflective foil layers.

  • Figure 10

    (Color online) External temperature of the compound MLI varied with hot boundary temperature under different emissivity of metal screen layer.

  • Table 1   Thermal properties at and single layer dimension

    Material

    Density (kg m−3)

    Thermal conductivity (W m−1 K−1)

    Thickness (mm)

    Carbon fibrous insulations

    180

    0.34

    40

    Alumina fibrous insulations

    128

    0.08

    20

    Gold-coated

    ceramic foils

    1343

    100

    0.5

  • Table 2   Thermal properties of the materials used in present work

    Property

    Value

    Alumina thermal conductivitykf1(W m−1k−1)

    93.81362−0.26631T+3.19292×10−4T2−1.75732×10−7T3+3.67188×10−11T4[29]

    Gas thermal conductivity at atmospheric pressurekg*(W m−1 k−1)

    2.76793×10−4+9.87534×10−5T−5.15535×10−8T2+1.54272×10−11T4[30]

    Amorphous carbon thermal conductivitykf2(W m−1 k−1)

    −0.08043+0.00847T−1.16882×10−5T2+7.37644×10−9T3−1.52747×10−12T4[30]

    Alumina fibrous albedo of scattering ω (N A-1)

    0.939+5.564×10−6T[27]

    Alumina fibrous specific extinction coefficient e (m2 kg−1)

    (41.92+0.0188T)[27]

Copyright 2020 Science China Press Co., Ltd. 《中国科学》杂志社有限责任公司 版权所有

京ICP备17057255号       京公网安备11010102003388号