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Journal of Thermal Analysis and Calorimetry

, Volume 134, Issue 3, pp 2147–2156 | Cite as

Thermal analysis of high viscosity deicing fluid in the heating system

  • Mengli WuEmail author
  • Chiyu Wang
  • Qi Nie
  • Yunpeng Li
  • Rui Zhou
Article

Abstract

Aircraft ground deicing is a crucial certification to civil flight safety in cold winter. Thermal analysis of high viscosity deicing fluid in Chinese ground heating system is carried out for promoting efficiency and flight punctuality. The structure of the system is asymmetrical, which is mainly composed of combustion chamber and heat exchange tube. Combustion releases energy to heat the deicing fluid in the exchange tube. Firstly, because of the formidable asymmetric structure, the grids of system need to be meshed separately to analyze the distribution of combustion temperature field. Secondly, due to the complex properties of deicing fluid, its main component ethylene glycol is selected as the working medium to examine the heat transfer performance. Then, the variation rules of thermo-physical parameters of ethylene glycol are compared with those of ideal fluid water. The results show that the asymmetric structure leads to the temperature field shifting to the gas outlet. The central area of the combustion chamber burns more fully than the edge area. Both dynamic viscosity coefficient and Prandtl number of ethylene glycol demonstrate similar nonlinear relationships when heating. Concerning thermal conductivity, Nusselt number and convection heat transfer coefficient, the variation rules of the two fluids are approximate, but the magnitudes of ethylene glycol are obviously less than those of water. Therefore, the high viscosity of fluid shows significant effect on heat transfer performance. Finally, a heating experiment is conducted to verify the reliability of the simulation. The research is beneficial to further explore the basic mechanism of combustion and heat transfer in the system, which is of great theoretical significance for optimizing and improving the existing Chinese deicing heating system.

Keywords

Aircraft ground heating system High viscosity Heat transfer Asymmetric combustion chamber structure 

List of symbols

\( \rho \)

Density of fluid \( ( {\text{kg}}\,{\text{m}}^{ - 3} ) \)

\( \vec{v} \)

Velocity vector

\( S_{\text{m}} \)

Mass entering a microelement in unit time

\( p \)

Static pressure (Pa)

\( \bar{\bar{\tau }} \)

Stress tensor

\( \rho \vec{g} \)

Gravity term

\( \vec{F} \)

Force on the microelement except the gravity

\( k_{\text{eff}} \)

Effective thermal conductivity \( ( {\text{W}}\, ( {\text{m}}\,{\text{k)}}^{ - 1} ) \)

\( J_{\text{j}} \)

Diffusion flow of component \( j \)

\( S_{\text{h}} \)

Heat of formation or other forms of heat produced within a microelement

\( G_{\text{k}} \)

Turbulent kinetic energy due to mean velocity gradients

\( G_{\text{b}} \)

Turbulent kinetic energy due to buoyancy

\( Y_{\text{M}} \)

Fluctuating dilatation in compressible turbulence to the overall dissipation rate

\( S_{\text{k}} ,S_{\upvarepsilon} \)

User defined source term

\( C_{{1\upvarepsilon}} ,C_{{2\upvarepsilon}} ,C_{{3\upvarepsilon}} \)

Empirical constants

\( \sigma_{\text{k}} \)

Prandtl number related to the turbulent kinetic energy

\( \sigma_{\upvarepsilon} \)

Prandtl number related to the turbulent kinetic energy dissipation ratio

\( \alpha \)

Absorption coefficient

\( \sigma_{\text{s}} \)

Scattering coefficient

\( G \)

Incident radiation

\( C \)

Functional relation of anisotropic phases

\( Z_{\text{i}} \)

Mass fraction of component \( i \)

\( Z_{\text{i,ox}} \)

Mass fraction of component \( i \) at the inlet of the oxidant flow

\( Z_{\text{i,fuel}} \)

Mass fraction of component \( i \) at the inlet of the fuel flow

\( Nu \)

Nusselt number

\( Pr \)

Prandtl number

\( c \)

Specific heat capacity \( ( {\text{J}}\, ( {\text{kg}}\,{\text{K)}}^{ - 1} ) \)

\( \mu \)

Dynamic viscosity coefficient

\( \lambda \)

Thermal conductivity \( ( {\text{W}}\, ( {\text{m}}\,{\text{k)}}^{ - 1} ) \)

\( \nu \)

Kinematic viscosity coefficient

\( h \)

Heat transfer coefficient

\( L \)

Characteristic length (mm)

\( T \)

Temperature (K)

\( T_{\exp } \)

The outlet temperature of the heating experiment (K)

\( T_{\text{s}} \)

The outlet temperature of the simulation (K)

\( \delta \)

The error between experiment and simulation (%)

Notes

Acknowledgements

This research is supported by the Natural Science Foundation of Tianjin (15JCQNJC42900), National Natural Science Foundation of China (51505483), and the Fundamental Research Funds for the Central Universities (3122013C012), China.

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Copyright information

© Akadémiai Kiadó, Budapest, Hungary 2018

Authors and Affiliations

  1. 1.College of Aeronautical EngineeringCivil Aviation University of ChinaTianjinChina

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