Nozzles for a reaction drive blade tip with turning vanes
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United States of America Patent
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Aug 13, 2019
Grant Date -
Jul 13, 2017
app pub date -
Jan 27, 2017
filing date -
Jun 20, 2014
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Abstract
A nozzle for use with a rotor blade for a reaction drive type helicopter includes a first wall, a second wall opposing the first wall, and sidewalls extending between the first wall and the second wall enclosing a cavity having an upstream end and a downstream end. The nozzle includes an inlet section for receiving a gasflow at the upstream end. The distance between the first wall and the second wall reduces to a throat downstream of the inlet section. An expansion section extending from the throat, downstream thereof.
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