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Research Papers: Radiative Heat Transfer

Improved MSMGFSK Models Apply to Gas Radiation Heat Transfer Calculation of Exhaust System of TBCC

[+] Author and Article Information
Haiyang Hu

School of Energy and Power Engineering,
Beihang University,
Beijing 100191, China
e-mail: 09451@buaa.edu.cn

Qiang Wang

School of Energy and Power Engineering,
Beihang University,
Beijing 100191, China;
Collaborative Innovation Center
for Advanced Aero-Engine,
Beijing 100191, China

Contributed by the Heat Transfer Division of ASME for publication in the JOURNAL OF HEAT TRANSFER. Manuscript received September 23, 2015; final manuscript received August 10, 2016; published online September 20, 2016. Assoc. Editor: Zhuomin Zhang.

J. Heat Transfer 139(1), 012702 (Sep 20, 2016) (11 pages) Paper No: HT-15-1617; doi: 10.1115/1.4034485 History: Received September 23, 2015; Revised August 10, 2016

The multiscale multigroup full-spectrum k-distribution (MSMGFSK) model was improved to adapt to radiation heat transfer calculations of combustion gas flow field with large temperature and pressure gradient. The improvements in calculation accuracy resulting from new sorting strategy of the spectral absorption coefficients were validated using a series of semi-1D problem in which strong temperature, pressure, and mole fraction inhomogeneities were present. A simpler method to attain compatibility between the MSMGFSK model and the gray-wall radiation emission has been established and validated. Finally, estimates are given for the calculation of wall radiation heat transfer characteristics and thermal emission imaging of the exhaust system of the parallel turbine-based combined cycle (TBCC) engine, using finite volume method (FVM) and ray trace method (RT), respectively.

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Figures

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Fig. 1

Contributions of spectral lines to the spectral absorption coefficient at different pressures

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Fig. 2

Temperature dependence of the line strengths (left) and 1692.616 cm−1 spectral absorption coefficient (right)

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Fig. 3

Hemispherical radiative heat flux distribution of low temperature (left) and high temperature (right) H2O-CO2-N2 mixture slab

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Fig. 4

Radiation heat flux leaving normal pressure (left) or low pressure (right) H2O-N2 mixture slab with step changes in temperature

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Fig. 5

Radiation heat flux leaving H2O-N2 mixture slab with step changes in temperature under different pressure

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Fig. 6

Radiation heat flux leaving H2O-N2 mixture slab with step changes in pressure

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Fig. 7

Radiation heat flux leaving H2O-N2 mixture slab with step changes in pressure and temperature

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Fig. 8

Radiation heat flux leaving the high pressure H2O-CO2-N2 mixture slab with step changes in the temperature and species mole fraction (cases 11–13) or in temperature, species mole fraction, and pressure (case 14)

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Fig. 9

Sketch of the exhaust system of TBCC

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Fig. 10

Inner–outer wall computation grids of the exhaust system of TBCC

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Fig. 11

Pressure (p), temperature (T), Mach number (Ma), and water vapor mass fraction (yH2O) distributions on the symmetry plane of the exhaust system of TBCC

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Fig. 12

Normalized convective heat flux (Ch) distribution calculated on different grids (left) and absolute and normalized radiation heat flux distribution (right) along the outer expansion ramp of the exhaust system of TBCC

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Fig. 13

400 × 160 pixel full-spectrum radiation image, obtained from the LBL model, of the TBCC exhaust system

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Fig. 14

Full spectrum radiation imaging calculation error of TBCC exhaust system using different models

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