Vortex flow particle accelerator

Details Vortex flow particle accelerator Vortex flow particle accelerator

1976-05-11

1977-06-28

Queisser, Richard C.

Measuring and testing

Wind tunnel: aerodynamic wing and propeller study

G01M 900

Patent

active

040317480

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.

REFERENCES:
patent: 2532655 (1950-12-01), Backer
patent: 2801133 (1957-07-01), Ridley

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