Accession Number : ADD004115

Title :   Vortex Flow Particle Accelerator.

Descriptive Note : Patent,

Corporate Author : DEPARTMENT OF THE AIR FORCE WASHINGTON D C

Personal Author(s) : Cramer,Kenneth R

Report Date : 28 Jun 1977

Pagination or Media Count : 6

Abstract : A particle accelerator having a tapered tubular vortex flow channel with a zero taper entrance portion. A high pressure low molecular weight gas, such as helium or hydrogen, is supplied tangentially into the zero taper portion of the flow channel. The particles to be accelerated are also supplied into the zero taper portion of the flow channel. An axial gas exit is provided at the end of the flow channel remote from the gas inlet. A tangential particle exit tube is tilted in the direction of flow at an angle of approximately 60 degrees with respect to the longitudinal axis of the flow channel. (Author)

Descriptors :   *Patents, *Particle accelerators, *Vortices, Boundary layer, Hydrogen, Helium

Subject Categories : Particle Accelerators

Distribution Statement : APPROVED FOR PUBLIC RELEASE