SCRAMJET COMBUSTOR
Assignee
Filed
Oct 15, 1990
Granted
Jan 21, 1992
Location
FOREST PARK OH US
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. Additionally, the fuel injector is positioned proximate the step and includes a condition responsive mechanism for varying the angle the fuel injector makes with the combustor's longitudinal axis during supersonic flight.
Source: Google Patents
35 USC §181 Secrecy Order
Imposed
Jan 31, 1991
Rescinded
Jun 4, 1991
Duration
4 months
Inventor
- 1DANIEL L. HARSHMAN
Record Details
- Patent number
- US 5081831
- Application
- 07597133
- Aerospace match
- Yes
- Dataset source
- 35 USC §181 SO records
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