Power plants – Reaction motor – Method of operation
Patent
1990-10-15
1992-04-14
Carone, Michael J.
Power plants
Reaction motor
Method of operation
F02K 710, F02K 714
Patent
active
051036339
ABSTRACT:
A scramjet combustor for a hypersonic (Mach number greater than about 5.5) flight vehicle. The combustor housing has two spaced-apart, generally opposing, and longitudinally extending walls. Each wall has an aft-facing step. Fuel (such as hydrogen) is injected at the step into the shear zone along the separation line for better fuel-air mixing. The longitudinal distance between the steps is controlled to take advantage of aerothermo compression provided by the forward step's shock. The back portion of each wall is positioned transversely inward toward the combustor's longitudinal axis to improve mixing effectiveness for more efficient combustion.
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patent: 3974648 (1976-08-01), Kepler
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Short Course in Hypersonics, Aug. 19-22, 1986, State University of New York at Buffalo.
Preliminary Results of Arc Tunnel Testing of Two-Dimensional Supersonic Combustors, by D. E. Nieser and M. J. Kenworthy, General Electric Flight Propulsion Division's Feb. 1966 Report No. R66FPD57.
Experimental Performance of the CIM II Scramjet Engine at Mach 7, by W. Hoelmer and R. C. King, General Electric Aircraft Engine Group's May 1968 Report No. R68AEG257.
Combustion in a Supersonic Flow, by V. K. Bayed et al., Guarana v Sverkhzvukovom Potke, Publishing House "Hauka", Novosibirsk, USSR.
Carone Michael J.
Erickson Douglas E.
General Electric Company
Squillaro Jerome C.
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