Journal article
Plenum pressure behavior in transiently heat loaded transpiration cooling system
- Abstract:
- In this paper, the behavior of the plenum pressure behind a transpiration-cooled porous material sample after an incident surface heat flux to the sample is analyzed in experiment and theory. Two porous materials, zirconium diboride and carbon/carbon, were characterized using the pressure-based noninteger system identification method. The resulting impulse responses are analyzed based on two numerical models. One model calculates a plenum pressure impulse response by modeling the porous sample’s heat conduction. A second model considers an additional plenum behind the sample and allows a changing mass flow rate through the sample. The experimentally obtained impulse responses show a stronger response for increasing coolant mass flow rates. Both models cover this trend, essentially depending on the volumetric heat transfer coefficient. However, only the second model allows the entire rebuilding of the experimental data. The plenum pressure impulse response for a transpiration-cooled system depends not only on the material parameters of the porous sample, but also on the volume of the plenum. The reason is that the flow rate changes through the porous sample although the mass flow rate at the controller always stays constant.
- Publication status:
- Published
- Peer review status:
- Peer reviewed
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- Files:
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(Preview, Accepted manuscript, pdf, 4.4MB, Terms of use)
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- Publisher copy:
- 10.2514/1.t6089
Authors
- Publisher:
- American Institute of Aeronautics and Astronautics
- Journal:
- Journal of Thermophysics and Heat Transfer More from this journal
- Volume:
- 35
- Issue:
- 2
- Pages:
- 256-267
- Publication date:
- 2020-12-29
- Acceptance date:
- 2020-09-29
- DOI:
- EISSN:
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1533-6808
- ISSN:
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0887-8722
- Language:
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English
- Keywords:
- Pubs id:
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1159635
- Local pid:
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pubs:1159635
- Deposit date:
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2021-02-01
- ARK identifier:
Terms of use
- Copyright holder:
- Hufgard et al.
- Copyright date:
- 2020
- Rights statement:
- Copyright © 2020 by the authors. Published by the American Institute of Aeronautics and Astronautics, Inc., with permission.
- Notes:
-
This is the accepted manuscript version of the article. The final version is available from American Institute of Aeronautics and Astronautics at https://doi.org/10.2514/1.T6089
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