Accession Number : ADD001457
Title : Supersonic Flow Diffuser with Energy Redistribution.
Descriptive Note : Patent Application,
Corporate Author : DEPARTMENT OF THE AIR FORCE WASHINGTON D C
Personal Author(s) : Hasinger,Siefried H
Report Date : 20 Aug 1975
Pagination or Media Count : 11
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.
Descriptors : *Supersonic diffusers, *Ramjet inlets, Ramjet engines, Channel flow, Blades, Ducts, Fluid flow, Boundary layer flow, Walls, Shock waves, Geometric forms, Patents
Subject Categories : Test Facilities, Equipment and Methods
Jet and Gas Turbine Engines
Distribution Statement : APPROVED FOR PUBLIC RELEASE