Hostname: page-component-cd9895bd7-fscjk Total loading time: 0 Render date: 2024-12-28T21:56:06.293Z Has data issue: false hasContentIssue false
  • English
  • Français

Heat transfer characteristic modelling and the effect of operating conditions on re-cooled cycle for a scramjet

Published online by Cambridge University Press:  27 January 2016

W. Bao ,
J. Qin  and
W. X. Zhou
W. Bao
Affiliation:
Harbin Institute of Technology, Heilongjiang, China
J. Qin
Affiliation:
Harbin Institute of Technology, Heilongjiang, China
W. X. Zhou
Affiliation:
Harbin Institute of Technology, Heilongjiang, China
Get access Rights & Permissions [Opens in a new window]

Abstract

A re-cooled cycle has been proposed for a regeneratively cooled scramjet to reduce the hydrogen fuel flow for cooling. Upon the completion of the first cooling, fuel can be used for secondary cooling by transferring the enthalpy from fuel to work. Fuel heat sink (cooling capacity) is thus repeatedly used and fuel heat sink is indirectly increased. Instead of carrying excess fuel for cooling or seeking for any new coolant, the cooling fuel flow is reduced, and fuel onboard is adequate to satisfy the cooling requirement for the whole hypersonic vehicle. A performance model considering flow and heat transfer is build. A model sensitivity study of inlet temperature and pressure reveals that, for given exterior heating condition and cooling panel size, fuel heat sink can be obviously increased at moderate inlet temperature and pressure. Simultaneously the low-temperature heat transfer deterioration and Mach number constrains can also be avoided.

Type
Research Article
Information
The Aeronautical Journal , Volume 115 , Issue 1164 , February 2011 , pp. 83 - 90
Copyright
Copyright © Royal Aeronautical Society 2011

Access options

Get access to the full version of this content by using one of the access options below. (Log in options will check for institutional or personal access. Content may require purchase if you do not have access.)

References

1. Chang, J., Bao, W. and Yu, D. Hypersonic inlet control with pulse periodic energy addition, Proc IMechE Part G: J Aerospace Engineering, 2009, 223, (2), pp 85–94.Google Scholar
2. Mahapatra, D. and Jagadeesh, G. Shock tunnel studies on cowl/ramp shock interactions in a generic scramjet inlet, Proc IMechE Part G: J Aerospace Engineering, 2008, 222, (8), pp 1183–1191.Google Scholar
3. Kontis, K. Flow control effectiveness of jets, strakes, and flares at hypersonic speeds, Proc. IMechE Part G: J Aerospace Engineering, 2008, 222, (5), pp 585–603.Google Scholar
4. Gascoin, N., Gillard, P., Dufour, E. and Toure, Y. Validation of transient cooling modelling for hypersonic application, J Thermophysics and Heat Transfer, 2007, 21, (1), pp 86–94.CrossRefGoogle Scholar
5. Chang, J. and Bao, W. Effects of wall cooling on performance parameters of hypersonic inlets, Acta Astronautica, 2009, 65, (3-4), pp 467–476.10.1016/j.actaastro.2009.02.005CrossRefGoogle Scholar
6. Kanda, T., Masuya, G. and Wakamatsu, Y. Propellant feed system of a regeneratively cooled scramjet, J Propulsion and Power, 1991, 7, (2), pp 299–301.10.2514/3.23325CrossRefGoogle Scholar
7. Roudakov, A.S. and Semenov, V.L. Recent flight test results of the joint CIAM-NASA Mach 6.5 scramjet flight program, AIAA Paper 1998-164, 1998.CrossRefGoogle Scholar
8. Qin, J., Zhou, W., Bao, W. and Yu, D. Thermodynamic analysis and parametric study of a closed Brayton cycle thermal management system for scramjet, Int J Hydrogen Energy, 2010, 35, (1), pp 356–364.10.1016/j.ijhydene.2009.09.025CrossRefGoogle Scholar
9. Sobel, D.R. and Spadaccini, L.J. Hydrocarbon fuel cooling technologies for advanced propulsion, J Engineering for Gas Turbines and Power, 1997, 119, pp 344–351.CrossRefGoogle Scholar
10. Boudreau, A.H. Hypersonic air-breathing propulsion efforts in the Air Force Research Laboratory, AIAA Paper 2005-3255, 2005.CrossRefGoogle Scholar
11. Gasner, J.A. and Fujimura, C. Evaluation of thermal management for a Mach 5.5 hypersonic vehicle, AIAA Paper 92-372, 1992.10.2514/6.1992-3721CrossRefGoogle Scholar
12. Qin, J., Bao, W., Zhou, W. and Yu, D. Performance cycle analysis of an open cooling cycle for scramjet, Proc. IMechE Part G: J Aerospace Engineering, 2009, 223, (6), pp 599–607.Google Scholar
13. Bao, W., Qin, J., Zhou, W. and Yu, D. Parametric performance analysis of multiple re-cooled cycle for hydrogen fueled scramjet, Int J hydrogen energy, 2009, 34, (17), pp 7334–7341.CrossRefGoogle Scholar
14. Bao, W., Qin, J., Zhou, W. and Yu, D. Performance limit analysis of recooled cycle for regenerative cooling systems, Energy Conversion and Management, 2009, 50, (8), pp 1908–1914.10.1016/j.enconman.2009.04.023CrossRefGoogle Scholar
15. Youn, B and Millst, A.F. Cooling panel optimization for The active cooling system of a hHypersonic aircraft, J Thermophysics and Heat Transfer, 1995, 9, (1), pp 136–143.CrossRefGoogle Scholar
16. Lemmon, E.W., Peskin, A.P. and Friend, D.G. NIST 12: Thermodynamic and Transport Properties of Pure Fluids. NIST Standard Reference Database Number 12, Version 5.0, National Institute of Standards and Technology, Boulder, CO, 2000.Google Scholar
17. Schuff, R., Maier, M., Sindiy, O., Ulrich, C. and Fugger, S. Integrated modelling and analysis for a LOX/Methane expander cycle engine: Focusing on regenerative cooling jacket design, AIAA Paper 2006-4534, July 2006.CrossRefGoogle Scholar
18. Taylor, M.F. Correlation of local heat-transfer coefficients for singlephase turbulent flow of hydrogen in tubes with temperature ratios to 23, NASA TN D-4332, January 1968.Google Scholar
19. Peet, Y., Sagaut, P. and Charron, Y. Pressure loss reduction in hydrogen pipelines by surface restructuring, Int J Hydrogen Energy, 2009, 34, (21), pp 8964–8973.CrossRefGoogle Scholar
20. Daniel, K., Parris, D. and Landrum, B. Effect of tube geometry on regenerative cooling performance, AIAA Paper 2005-430, July 2005.CrossRefGoogle Scholar
21. Kanda, T., Masuya, G., Wakamatsu, Y., Chinzei, N. and Kanmuri, A. Parametric study of airframe-Integrated scramjet cooling requirement, J Propulsion and Power, 1991, 7, (3), pp 431–436.CrossRefGoogle Scholar
22. Locke, J.M. and Landrum, D.B. Study of heat transfer correlations for supercritical hydrogen in regenerative cooling channels, J Propulsion and Power, 2008, 24, (1), pp 94–103.CrossRefGoogle Scholar
23. Cengel, Y.A. and Boles, M.A. Thermodynamics, 4th ed New York, US, McGraw-Hill, 2002.Google Scholar
24. Buchmann, O.A. et al Advanced fabrication techniques for hydrogen cooled engine structures, NASA CR 3949, November 1985.Google Scholar
25. Dziedzic, W.H., Jonest, S.C., Gould, D.C. and Petley, D.H. Analytical comparison of convective heat transfer correlations in supercritical hydrogen, J Thermophysics And Heat Transfer, 1993, 7, (1), pp 68–73.CrossRefGoogle Scholar
26. Scotti, S.J., Martin, C.J. and Lucas, S.H. Active cooling design for scramjet engines using optimization methods. 1988; NASA TM-100581.CrossRefGoogle Scholar
27. Wieting, A.R. and Guy, R.W. Thermal-structural design/analysis of an airframe-integrated hydrogen-cooled scramjet, J Aircr, 1976, 13, (3), pp 192–197.CrossRefGoogle Scholar
28. Bao, W., Qin, J., Zhou, W.X. and Yu, D.R. Effect of cooling channel geometry on re-cooled cycle performance for hydrogen fueled scramjet, Int J Hydrogen Energy, 2010, 35, (13), pp 7002–7011.CrossRefGoogle Scholar
30. Sorato, S., Pascovici, D.S. and Ogaji, S.T. Investigating the emissions and performance of high bypass ratio aero-engines, Proc IMechE Part G: J Aerospace Engineering , 2008, 222, (4), pp 463–471.Google Scholar
31. Yang, J.C. and Huber, M.L. Analysis of thermodynamic processes involving hydrogen, Int J Hydrogen Energy, 2008, 33, (16), pp 4413–4418.CrossRefGoogle Scholar
32. Balta, M.T., Dincer, I. and Hepbasli, A. Thermodynamic assessment of geothermal energy use in hydrogen production, Int J Hydrogen Energy, 2009, 34, (7), pp 2875–2880.Google Scholar
33. Rossi, C.C.R.S., Alonso, C.G. and Antunes, O.A.C. Thermodynamic analysis of steam reforming of ethanol and glycerine for hydrogen production, 2009, Int J Hydrogen Energy, 34, (1), pp 323–332.CrossRefGoogle Scholar
34. Qin, J., Zhou, W., Bao, W. and Yu, D. Thermodynamic optimization for a scramjet with Re-cooled Cycle, Acta Astronautica, 2010, 66, (9-10), pp 1449–1457.CrossRefGoogle Scholar
35. Qin, J., Zhou, W., Bao, W. and Yu, D. Irreversible cycle analysis of Re-Cooled Cycle for a Scramjet, Proc IMechE Part G: J Aerospace Engineering, 2009, 224, (8), pp 912–926.Google Scholar
36. Yanovskiy, L.S., Baykov, A.V. and Martynenko, C.E. Cooling Character of hydrocarbon fuel in supercritical pressure, V nationwide aviation congress, Moscow, 2006 (In Russian).Google Scholar