INVESTIGATION OF A RESONANT COMBUSTOR CONCEPT
Abstract
The project is concerned with an attempt to take advantage of the pressure rise that occurs during resonant combustion, but to avoid the losses that have plagued the majority of resonant combustion systems during the blowback or flow reversal portion of the cycle. In order to avoid flow reversal losses, as well as to take advantage of a ram pressure rise (or compressor pressure rise), the resonant combustor was placed inside a ram shroud or duct which permits a bypass flow around the combustor. A large number of combustor air inlets were provided (between 80 and 100 inlets), which permitted submerging the inlets into the combustor shell, and thus reducing the external drag around the combustor and improving the combustor air inflow coefficient. The use of a large number of air inlets also contributed to a reduction of burning time, which was reflected in an unusually high operating frequency. Fuel was injected into each air inlet, in a jet pump arrangement. This feature permitted static (zero airspeed) starting and operation of the combustor when using gaseous fuels such as propane.
Document Details
- Document Type
- Technical Report
- Publication Date
- Jan 30, 1960
- Accession Number
- AD0629951
Entities
People
- George E. Heuer
- Raymond M. Lockwood