Supersonic Flow Diffuser with Energy Redistribution.
Abstract
According to the patent application, a blade system is provided in a non-axisymmetrical supersonic diffuser. It was found that flow energy redistribution within the ducts can overcome the adverse flow conditions associated with the ingestion of a boundary layer into the flow ducts along the wall of a supersonic diffuser channel. These improved results are obtained when the upstream end of the blades are bent in a direction away from the wall having the boundary layer. It was found that the best results are obtained when the blades closest to the wall have the greatest amount of bend with the amount of bending being decreased as the distance from this wall increases. Also, the pressure recovery can be further improved by providing internal energy redistribution in the diffuser channel. This is accomplished by providing an internal injection of flow from the duct next to the duct having the boundary layer into the duct having the boundary layer.
Document Details
- Document Type
- Technical Report
- Publication Date
- Aug 20, 1975
- Accession Number
- ADD001457
Entities
People
- Siefried H. Hasinger
Organizations
- United States Department of the Air Force