Accession Number : ADD004476

Title :   Supersonic Flow Diffuser with Energy Redistribution.

Descriptive Note : Patent,

Corporate Author : DEPARTMENT OF THE AIR FORCE WASHINGTON D C

Personal Author(s) : Hasinger,Siegfried H ; Miller,David K

Report Date : 15 Nov 1977

Pagination or Media Count : 6

Abstract : This patent describes a supersonic diffuser having a plurality of blades therin for dividing the diffuser channel into a plurality of approximately axisymmetric ducts wherein a portion of said ducts ingest a boundary layer along at least one of the walls of the supersonic diffuser. The blades in the diffuser channel have their upstream ends bent away from the wall having the boundary layer to redirect the flow into the ducts. In one embodiment the wall between the duct having the boundary layer and the duct adjacent to the duct having the boundary layer is made in two sections with both sections being bent away from the wall having the boundary layer, to provide internal redistribution between the two ducts. (Author)

Descriptors :   *Patents, *Supersonic diffusers, Blades, Curvature, Ducts, Boundary layer flow, Flow fields, Directional, Walls

Subject Categories : Jet and Gas Turbine Engines

Distribution Statement : APPROVED FOR PUBLIC RELEASE