Apparatus for reducing aerodynamic drag in system for air coolin

Electric lamp and discharge devices – With temperature modifier – Using liquids or fluid flow directing means

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313 36, 313 22, 313 24, 313 45, 313 46, H01J 726, H01J 6152

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active

044423730

ABSTRACT:
A high power vacuum tube 10 has a cylindrical body 16 and a plurality of radially extending fins 18. A cylindrical wall 20 is co-axially disposed about the body and the fins, thus defining an air channel between the body and the wall. To cool the tube, air is forced into the channel from an entry port, and leaves the channel through an exit port. The cooling capacity of the system is optimized by contouring the entry and exit ports to minimize aerodynamic drag. In one embodiment, the entry into the channel is flared outward and a cone assembly 42 is provided adjacent the longitudinal end of the body 16 nearest the exit port. This cone assembly thus forms a continuation of the body 16 which tapers to a smaller cross section in the direction of air flow. The cone assembly may be formed of a stack of discs 70 of successively smaller diameter. The exit port, which may have either rigid or flexible sidewalls, has a venturi shape to further reduce drag.

REFERENCES:
patent: 2324034 (1943-07-01), Skene
patent: 2476647 (1949-07-01), Weschler et al.
patent: 2829290 (1958-01-01), Van Warmerdam
patent: 3343019 (1967-09-01), Wolf et al.
patent: 4180763 (1979-12-01), Anderson
Mair, W. H., "The Effect of a Rear Mounted Disc on the Drag of a Blunt-Based Body of Revolution," The Aeronautical Quarterly, 11/65, pp. 350-360.
Little, Jr., B. H. et al., "Locked Vortex Afterbodies", American Inst. of Aeronautics and Astronautics, Inc., 1978, pp. 296-302.

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