Supersonic flow diffuser with energy redistribution
AssigneeThe United States of America as represented by the Secretary of the Air Force
InventorsSiegfried H. Hasinger, David K. Miller
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Abstract
A supersonic diffuser having a plurality of blades therein 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.
Claims6
A supersonic diffuser, comprising:
- at least four walls forming a non-axisymmetric diffuser flow channel;
- means forming a converging inlet and throat section in said channel;
- a wall extending forward of the flow channel and forming a continuous surface together with one wall of said flow channel;
- whereby in response to a flow of air along said continuous surface and into the diffuser flow channel a boundary layer forms along the wall extending forward of the flow channel and enters the diffuser flow channel;
- a plurality of blade members positioned within the diffuser channel downstream of the throat section;
- said blade members dividing the flow channel into a plurality of flow ducts which are substantially symmetrical around their own axis;
- means, on at least a portion of said plurality of blade members, for redirecting the flow in the diffuser channel in a direction toward the wall of said flow channel, which forms the continuous surface with the wall which extends forward of the flow channel.
Dependencies are inferred from the claim text.