A Calculation Method for Heat Transfer Process of Porous Pyrolysis Materials

A calculation method and technology of heat transfer process, which is applied in the field of calculation of heat transfer process of porous pyrolysis materials, can solve the problem that the three-dimensional temperature distribution of materials cannot be obtained, such as pyrolysis gas

Active Publication Date: 2014-08-20
NAT UNIV OF DEFENSE TECH
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Problems solved by technology

In order to solve existing pyrolysis material heat transfer process calculation can't obtain material internal three-dimensional temperature distribution and pyrolysis gas
To dea

Method used

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  • A Calculation Method for Heat Transfer Process of Porous Pyrolysis Materials
  • A Calculation Method for Heat Transfer Process of Porous Pyrolysis Materials
  • A Calculation Method for Heat Transfer Process of Porous Pyrolysis Materials

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Embodiment Construction

[0045]

[0048] In addition to the existence of carbide residues in the carbide layer, pyrolysis gas generated by decomposition flows through, which belongs to porous media.

[0049] In the carbonized layer, a micro-element control body is arbitrarily taken, and the control body contains both solid and decomposed gas.

[0052]

[0055]

[0059]

[0062]

[0065]

[0068]

[0071]

[0073] There is no thermal decomposition process in the carbonized layer, and there is no thermal decomposition heat absorption; but there is heat of chemical reaction. Therefore, the internal heat source

[0074]

[0076]

[0078]

[0079] This is the final expression of the solid phase energy conservation equation.

[0081]

[0084]

[0086] Since the temperature in the carbonized layer is relatively low, the influence of radiation is ignored.

[0090]

[0092]

[0094]

[0097]

[0099]

[0101]

[0104]

[0106]

[0108]

[0109] Since the unsteady phase time at the beginning of the ablation is shor...

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Abstract

A calculation method for the heat transfer process of porous pyrolysis materials, including deriving the mass, momentum and energy conservation equations of each layer inside the composite material, realizing the solution of the mass, momentum and energy equations of the solid phase and gas phase inside the porous medium structure, and obtaining the solid phase temperature T, density ρ, thermal conductivity ks, gas phase density ρf, thermal conductivity kf, porosity φ, pyrolysis gas pressure p, decomposition gas overflow velocity un. The invention can analyze the heat transfer process of different kinds of carbonized pyrolysis materials, can display the pyrolysis process of the pyrolysis gas inside the material in three dimensions, obtain the pressure and velocity distribution of the pyrolysis gas, and the cloud map of the temperature distribution of the porous medium structure formed after pyrolysis . By calculating the heat transfer process of porous pyrolysis materials, it solves the problem that it is difficult to accurately calculate the temperature of composite materials and the ambient temperature in the cabin of hypersonic aircraft.

Description

A method for calculating the heat transfer process of porous pyrolysis materials Technical field The present invention relates to a kind of porous pyrolysis material heat transfer process calculation method, especially a kind of complex based on fluent Calculation method for heat transfer process of composite material porous media structure. Background technique In rocket engine internal thermal protection or hypersonic vehicle external aerodynamic thermal protection, silicon-based composite material or Carbon-based composites are commonly used thermal protection materials, which can accurately predict the temperature distribution during the ablation process of such insulation materials. Engine and aircraft structure design is of great significance. There are many kinds of production processes, SIO2 glass fiber can be impregnated with phenolic resin Resin winding curing, or cloth made of glass fiber impregnated with phenolic resin lamination curing, or mixed with rand...

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Application Information

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IPC IPC(8): G06F19/00B01J20/02
Inventor 王德全李大鹏刘冰柳军金亮隆清贤梁文鹏杨阳夏智勋王中伟罗世彬
Owner NAT UNIV OF DEFENSE TECH
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