| 摘要 |
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. |
