Rotating Detonation Engine Fundamental Physics Investigation
Abstract
The objective of the proposed research is to advance the nascent rotating detonation engine (RDE) concept toward the launch of a liquid bi-propellant rocket. In the RDE, detonation waves spin within an annular chamber, which itself remains stationary. Across the detonation waves, not only does static pressure increase, so does total pressure in the frame of reference fixed to the annular chamber, which is the reason why the RDE is referred to as a Pressure Gain Combustor (PGC) technology.The main advantages of the RDE applied to rockets are twofold: (a) the spinning detonation waves could overpower acoustic instabilities which have plagued conventional rocket engine operation and (b) pressure gain in a combustion chamber could reduce the feed pressure, resulting in smaller, less mechanically complicated turbo-pumps. In addition, since RDE can accelerate combustion products to supersonic exit velocities without a convergent-divergent nozzle, it can eliminate a throat, reducing overall length and weight.
Document Details
- Document Type
- DoD Grant Award
- Publication Date
- Apr 09, 2018
- Source ID
- FA95501810076
Entities
People
- Carl Knowlen
Organizations
- Air Force Office of Scientific Research
- United States Air Force
- University of Washington