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Abstract
Experiments were carried out on a scaled down model of scramjet engine with gaseous hydrogen as fuel in 1meter combustion driven shock tunnel at VSSC. The tests were carried out at an enthalpy of 2.6 MJ/kg, at a free stream Mach number of 6.8 with stagnation pressures varying from 11-19MPa, dynamic pressure varying from 72-130 kPa and fuel to air equivalence ratio varying between 0.34-1.16. Experiments were carried out with air and nitrogen as a test gas with H2 injection to bring out the difference between reactive and non-reactive cases. For the current model scale, it was found that when combustion chamber inlet pressure (Pc) is greater than 0.1 MPa, a sharp increase in pressure downstream of fuel injection struts is observed, whereas when Pc is < 0.1 MPa, marked rise in pressure just downstream of the strut is not observed. The pressure rise at the location immediately downstream of fuel injection struts due to supersonic combustion is approximately three to four times as compared to without combustion case. Scramjet flight test data are compared with Shock tunnel pressure measurements for with and without combustion cases and reasonable match of peak combustion pressures and over all trends is observed.
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References
- Francois Falempin., "Ramjet and Dual Mode Operation", Advances on Propulsion Technology for HighSpeed Aircraft, pp.7-1 to 7-36, 2008, Educational notes RTO-EN-AVT-150, Paper 7.
- Michael Smart., "Scramjets", Advances on Propulsion Technology for High-Speed Aircraft, pp.9-1 to 9-38, Educational Notes RTO-EN-AVT-150.
- Curran, E. T. and Murthy, S. N. B., "Scramjet propulsion", Progress in Astronautics and Aeronautics, 189, Reston, VA AIAA 2000, ISBN: 1 56347 322 4.
- Stalker, R. J, et al., "Scramjets and Shock Tunnels The Queensland Experience", Progress in Aerospace Sciences, 41, 2005, pp.471-513.
- Osgerby, I.T., Smithson, H. K. and Wagner, D. A., "Development of a Double-Oblique Shock Scramjet Model in a Shock Tunnel", Journal of Aircraft, Vol.8, No.4. April 1971, pp.258-263.
- Rogers, R. C., Shih, A. T. and Hass, N. E., "Scramjet Development Tests Supporting the Mach 10 Flight of the X-43", AIAA Paper 2005-3351.
- Gardner, A. D., Hannemann, K., Paull, A. and Steelant, J., "Post Flight Analysis of the HYSHOT Supersonic Combustion Flight Experiment in HEG", Proceedings of the Fifth European Symposium of Aerothermodynamics for Space Vehicles, November 8-11, 2005, Cologne, Germany, ESA SP-563, February 2005.
- Tanno, H., Itoh, K., Ueda, S, et al., "Scramjet Testing in High Enthalpy Shock Tunel (HIEST)", JAXA Document, pp.120-124.
- Ratan, J. and Jagadeesh, G., "Investigations on Supersonic Combustion in a Combustion-driven Shock
- Tunnel", Proceedings of the Institution of Mechanical Engineers, Vol.226, Part G: Journal of Aerospace
- Engineering, 2012, pp.1183-1191.
- Charles E Wittliff, et al., "The Tailored-Interface Hypersonic Shock Tunnel", Journal of the AeroSpace Sciences, Vol.26, No.4, April 1959, pp.219- 228.
- Bogdanoff, D. W., Zambrana, H. A., Cavolowsky, J. A, et al., "Reactivation and Upgrade of the NASA
- Ames 16 Inch Shock Tunnel: Status Report", AIAA Paper 92-0327.
- Srinivasan, K., Maurya, P. K, et al., "Effect of Sphere Truncation on the Stagnation Point Heat Flux", CP245, Symposium on Applied Aerodynamics and Design of Aerospace Vehicle (SAROD 2015),
- December 3-5, Vikram Sarabhai Space Centre (VSSC), Thiruvananthapuram, India.
- Robinson, M. J., Mee, D. J. and Paull, A., "Scramjet Lift, Thrust and Pitching-Moment Characteristics
- Measured in a Shock Tunnel", Journal of Propulsion and Power, Vol.22, No.1, 2006, pp.85-95.
- Desikan, S. L. N., Suresh, K., Srinivasan, K. and Raveendran, P. G., "Fast Response Co-axial Thermocouple for Short Duration Impulse Facilities", Applied Thermal Engineering, Vol.96, 2016,
- pp.48-56.
- Coward, H. F. and Jones, G. W., "Limits of Flammability of Gases and Vapors", U.S. Bureau of Mines,
- Bulletin 503.
- Gnanasekar, S., Ashok, V., Dipankar Das and Lazar T Chitilappilly., "Effect of Connected Pipe Test Conditions on Scramjet Combustor Performance", International Journal on Aerospace Innovations, Vol.1,
- No.4, 2009, pp.159-173.
- Mee David, J., "Uncertainty Analysis of Conditions in the Test Section of the T4 Shock Tunnel", Report
- No.4/93, Department of Mechanical Engineering, The University of Queensland.
References
Francois Falempin., "Ramjet and Dual Mode Operation", Advances on Propulsion Technology for HighSpeed Aircraft, pp.7-1 to 7-36, 2008, Educational notes RTO-EN-AVT-150, Paper 7.
Michael Smart., "Scramjets", Advances on Propulsion Technology for High-Speed Aircraft, pp.9-1 to 9-38, Educational Notes RTO-EN-AVT-150.
Curran, E. T. and Murthy, S. N. B., "Scramjet propulsion", Progress in Astronautics and Aeronautics, 189, Reston, VA AIAA 2000, ISBN: 1 56347 322 4.
Stalker, R. J, et al., "Scramjets and Shock Tunnels The Queensland Experience", Progress in Aerospace Sciences, 41, 2005, pp.471-513.
Osgerby, I.T., Smithson, H. K. and Wagner, D. A., "Development of a Double-Oblique Shock Scramjet Model in a Shock Tunnel", Journal of Aircraft, Vol.8, No.4. April 1971, pp.258-263.
Rogers, R. C., Shih, A. T. and Hass, N. E., "Scramjet Development Tests Supporting the Mach 10 Flight of the X-43", AIAA Paper 2005-3351.
Gardner, A. D., Hannemann, K., Paull, A. and Steelant, J., "Post Flight Analysis of the HYSHOT Supersonic Combustion Flight Experiment in HEG", Proceedings of the Fifth European Symposium of Aerothermodynamics for Space Vehicles, November 8-11, 2005, Cologne, Germany, ESA SP-563, February 2005.
Tanno, H., Itoh, K., Ueda, S, et al., "Scramjet Testing in High Enthalpy Shock Tunel (HIEST)", JAXA Document, pp.120-124.
Ratan, J. and Jagadeesh, G., "Investigations on Supersonic Combustion in a Combustion-driven Shock
Tunnel", Proceedings of the Institution of Mechanical Engineers, Vol.226, Part G: Journal of Aerospace
Engineering, 2012, pp.1183-1191.
Charles E Wittliff, et al., "The Tailored-Interface Hypersonic Shock Tunnel", Journal of the AeroSpace Sciences, Vol.26, No.4, April 1959, pp.219- 228.
Bogdanoff, D. W., Zambrana, H. A., Cavolowsky, J. A, et al., "Reactivation and Upgrade of the NASA
Ames 16 Inch Shock Tunnel: Status Report", AIAA Paper 92-0327.
Srinivasan, K., Maurya, P. K, et al., "Effect of Sphere Truncation on the Stagnation Point Heat Flux", CP245, Symposium on Applied Aerodynamics and Design of Aerospace Vehicle (SAROD 2015),
December 3-5, Vikram Sarabhai Space Centre (VSSC), Thiruvananthapuram, India.
Robinson, M. J., Mee, D. J. and Paull, A., "Scramjet Lift, Thrust and Pitching-Moment Characteristics
Measured in a Shock Tunnel", Journal of Propulsion and Power, Vol.22, No.1, 2006, pp.85-95.
Desikan, S. L. N., Suresh, K., Srinivasan, K. and Raveendran, P. G., "Fast Response Co-axial Thermocouple for Short Duration Impulse Facilities", Applied Thermal Engineering, Vol.96, 2016,
pp.48-56.
Coward, H. F. and Jones, G. W., "Limits of Flammability of Gases and Vapors", U.S. Bureau of Mines,
Bulletin 503.
Gnanasekar, S., Ashok, V., Dipankar Das and Lazar T Chitilappilly., "Effect of Connected Pipe Test Conditions on Scramjet Combustor Performance", International Journal on Aerospace Innovations, Vol.1,
No.4, 2009, pp.159-173.
Mee David, J., "Uncertainty Analysis of Conditions in the Test Section of the T4 Shock Tunnel", Report
No.4/93, Department of Mechanical Engineering, The University of Queensland.