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Research on head cooling of high-speed aircraft by liquid nitrogen

Published online by Cambridge University Press:  02 December 2020

H.X. Xiong Open the ORCID record for H.X. Xiong [Opens in a new window] ,
S.H. Yi Open the ORCID record for S.H. Yi [Opens in a new window] ,
H.L. Ding ,
L. Jin  and
J.J. Huo
H.X. Xiong
Affiliation:
College of Aerospace Science and Engineering, National University of Defense Technology, Changsha410073, China
S.H. Yi*
Affiliation:
College of Aerospace Science and Engineering, National University of Defense Technology, Changsha410073, China
H.L. Ding
Affiliation:
College of Aerospace Science and Engineering, National University of Defense Technology, Changsha410073, China
L. Jin
Affiliation:
College of Aerospace Science and Engineering, National University of Defense Technology, Changsha410073, China
J.J. Huo
Affiliation:
College of Aerospace Science and Engineering, National University of Defense Technology, Changsha410073, China
*
[email protected]
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Abstract

In the development process of high-speed aircraft, the head of the aircraft is subject to high temperatures and high speed flows, supporting the maximum heat flow and thus requiring a reliable cooling system. A new type of head cooling system is proposed herein. An internal flow channel model of the heat transfer in a ball head made from high-temperature alloy steel is constructed, then an experimental platform is built to carry out relevant experiments on the performance of this cooling system. Firstly, the influence of different experimental conditions on the cooling efficiency of the ball head is studied. For given liquid-nitrogen supply pressure, a higher heating heat flux density on the outer surface of the ball head corresponds to higher cooling efficiency. Then, the vaporisation effect under different experimental conditions is evaluated using temperature sensors at the inlet and outlet of the ball head heat exchange channel in combination with images of the visualised glass tube. It is found that liquid nitrogen can vaporise completely when flowing through the heat exchange channel. The characteristics of the heating effect and liquid nitrogen injection for the ball head were evaluated using an infrared camera. Finally, under different experimental conditions of liquid-nitrogen supply pressure, it is found that liquid nitrogen can vaporise completely in each case, and the total temperature of the vaporised nitrogen is about 300K. It can thus be collected as a secondary gas source.

Keywords

visualisationcooling efficiencyvaporisationinfrared effect
Type
Research Article
Information
The Aeronautical Journal , Volume 125 , Issue 1284 , February 2021 , pp. 389 - 409
Copyright
© The Author(s), 2020. Published by Cambridge University Press on behalf of Royal Aeronautical Society

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References

REFERENCES

Bouchez, M. and France, M. Ptah-socar fuel - cooled composite materials structure - status 2007 Single Stage to Orbit Two Stage to Orbit, October 3, 2007, 1–10.Google Scholar
Jackson, T.A., Eklund, D.R. and Fink, A.J. High speed propulsion: Performance advantage of advanced materials, J. Mater. Sci. 2004, 39, pp 5905–5913. https://doi.org/10.1023/B:JMSC.0000041687.37448.06.Google Scholar
Choit, S.H., Scottit, S.J., Song, K.D. and Ries, H. Transpiring cooling of a scram-jet engine combustion chamber, 32nd Thermophys. Conf. (1997). https://doi.org/10.2514/6.1997-2576.CrossRefGoogle Scholar
Liu, Y.Q., Jiang, P.X., Jin, S.S. and Sun, J.G. Transpiration cooling of a nose cone by various foreign gases, Int. J. Heat Mass Transf. 2010, 53, pp 5364–5372. https://doi.org/10.1016/j.ijheatmasstransfer.2010.07.019.CrossRefGoogle Scholar
Reimer, T., Kuhn, M., Esser, B., Sippel, M. and Van Foreest, A. Transpiration cooling tests of porous cmc in hypersonic flow, 17th AIAA Int. Sp. Planes Hypersonic Syst. Technol. Conf. 2011. 2011. https://doi.org/10.2514/6.2011-2251.Google Scholar
Wang, J.H., Messner, J. and Stetter, H. An Experimental Investigation of Transpiration Cooling. Part I: Application of an Infrared Measurement Technique, Int. J. Rotating Mach. 2003, 9, pp 153–161. https://doi.org/10.1155/s1023621x03000149.Google Scholar
Andoh, Y.H. and Lips, B. Prediction of porous walls thermal protection by effusion or transpiration cooling. An analytical approach, Appl. Therm. Eng. 2004, 23, pp 1947–1958. https://doi.org/10.1016/S1359-4311(03)00145-5.Google Scholar
Treviño, C and Medina, A. Analysis of the transpiration cooling of a thin porous plate in a hot laminar convective flow, Eur. J. Mech. B/Fluids. 1999, 18, pp 245–260. https://doi.org/10.1016/S0997-7546(99)80025-9.Google Scholar
Greuel, D., Herbertz, A., Haidn, O.J., Ortelt, M. and Hald, H. Transpiration cooling applied to C/C liners of cryogenic liquid rocket engines, 40th AIAA/ASME/SAE/ASEE Jt. Propuls. Conf. Exhib. 2004. https://doi.org/10.2514/6.2004-3682.CrossRefGoogle Scholar
Keener, D., Lenertz, J., Bowersox, R. and Bowman, J. Transpiration cooling effects on nozzle heat transfer and performance, J. Spacecr. Rockets. 1995, 32, pp 981–985. https://doi.org/10.2514/3.26718.CrossRefGoogle Scholar
Landis, J.A. and Bowman, W.J. Numerical study of a transpiration cooled rocket nozzle, 32nd Jt. Propuls. Conf. Exhib. 1996. https://doi.org/10.2514/6.1996-2580.Google Scholar
Weinbaum, S. and Wheeler, H.L. Heat transfer in sweat-cooled porous metals, J. Appl. Phys. 1944, 20, pp 113–122. https://doi.org/10.1063/1.1698226.CrossRefGoogle Scholar
Chauvin, L.T. and Carter, H.S. Exploratory Tests of Transpiration Cooling on a Porous 8 Cone at M = 2.05 Using Nitrogen Gas, Helium Gas, and Water as the Coolants, Naca Rm L55C29. 1955. http://naca.central.cranfield.ac.uk/reports/1955/naca-rm-l55c29.pdf.Google Scholar
Rashis, B. Exploratory Investigation of Transpiration Cooling of a 40 deg Double Wedge using Nitrogen and Helium as Coolants at Stagnation Temperatures from 1,295 deg F to 2,910 deg F, 1957.Google Scholar
Transpiration Cooling Using Liquid Water, 2007, 14.Google Scholar
Leontiev, A.I. Heat and mass transfer problems for film cooling, J. Heat Transfer. 2004, 121, pp 509–527. https://doi.org/10.1115/1.2826012.Google Scholar
Ding, L., Wei, K., Zhang, Q. and Wang, J. An experimental investigation on transpiration cooling of porous flat plate, 2011 Int. Conf. Remote Sensing, Environ. Transp. Eng. RSETE 2011 - Proc. 2011, 5692–5696. https://doi.org/10.1109/RSETE.2011.5965645.CrossRefGoogle Scholar
Wang, J.H., Messner, J. and Casey, M.V. Performance investigation of film and transpiration cooling, Proc. ASME Turbo Expo 2004. 3, 2004 895–907. https://doi.org/10.1115/gt2004-54132.CrossRefGoogle Scholar
Wang, J.H., Messner, J. and Stetter, H. An Experimental Investigation on Transpiration Cooling Part II: Comparison of Cooling Methods and Media, Int. J. Rotating Mach. 2004, 10, pp 355–363. https://doi.org/10.1155/s1023621x04000363.CrossRefGoogle Scholar
Shi, J.X. and Wang, J.H. A Numerical Investigation of Transpiration Cooling with Liquid Coolant Phase Change, Transp. Porous Media. 2011, 87, pp 703–716. https://doi.org/10.1007/s11242-010-9710-9.Google Scholar
Wei, K., Wang, J. and Mao, M. Model Discussion of Transpiration Cooling with Boiling, Transp. Porous Media. 2004, 94, pp 303–318. https://doi.org/10.1007/s11242-012-0006-0.CrossRefGoogle Scholar
Wang, J., Zhao, L., Wang, X., Ma, J. and Lin, J. An experimental investigation on transpiration cooling of wedge shaped nose cone with liquid coolant, Int. J. Heat Mass Transf. 2004, 75, pp 442–449. https://doi.org/10.1016/j.ijheatmasstransfer.2014.03.076.CrossRefGoogle Scholar