Noise attenuating supersonic nozzle
AssigneeCold Jet, Inc.
InventorsDaniel L. Lloyd, Richard J. Madlener
Life of this patent
Estimating the term…
Abstract
A sound attenuating supersonic nozzle has an exit to throat ratio in the range of 2.5 to 6.0, with longitudinal grooves formed in the interior wall of the supersonic passageway of the nozzle body. A shield is disposed about the exterior surface of the nozzle body, forming an exit cavity and an exit opening, and has a gill cavity through which auxiliary air flows into the exit cavity and mixes with the supersonic flow. 572
Claims42
A sound attenuating supersonic nozzle connectable to a flow of compressible fluid, said nozzle comprising:
- (a) a nozzle body having an exterior surface;
- (b) a supersonic passageway having an interior wall, said supersonic passageway formed in said nozzle body and having an inlet, a throat, and an exit, said supersonic passageway having a converging section between said inlet and said throat, said supersonic passageway having a diverging section between said throat and said exit, said supersonic passageway adapted for producing sonic flow at said throat and supersonic flow in said diverging section;
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- (c) means for reducing the coalescence of sound waves, said means comprising a plurality of longitudinal grooves formed in said internal wall adjacent said exit.
A sound attenuating supersonic nozzle connectable to a flow of compressible fluid, said nozzle comprising:
- (a) a nozzle body having an exterior surface;
- (b) a supersonic passageway having an interior wall, said supersonic passageway formed in said nozzle body and having an inlet, a throat, and an exit, said supersonic passageway having a converging section between said inlet and said throat, said supersonic passageway having a diverging section between said throat and said exit, said supersonic passageway adapted for producing sonic flow at said throat and supersonic flow in said diverging section;
- and
- (c) means for attenuating sound, said means comprising a plurality of cavities formed in said exterior surface of said nozzle body.
A sound attenuating supersonic nozzle connectable to a flow of compressible fluid, said nozzle comprising:
- (a) a nozzle body having an exterior surface;
- (b) a supersonic passageway having an interior wall, said supersonic passageway formed in said nozzle body and having an inlet, a throat, and an ext, said supersonic passageway having a converging section between said inlet and said throat, said supersonic passageway having a diverging section between said throat and said exit, said supersonic passageway adapted for producing sonic flow at said throat and supersonic flow in said diverging section;
- (c) a plurality of longitudinal grooves formed in said interior wall adjacent said exit;
- (d) a plurality of longitudinal cavities formed in said exterior surface;
- and
- (e) a plurality of inserts, said inserts having complimentary shapes to said longitudinal cavities, said inserts being disposed in said cavities.
A sound attenuating supersonic nozzle connectable to a flow of compressible fluid, comprising:
- (a) a nozzle body having an exterior surface;
- (b) a supersonic passageway having an interior wall, said supersonic passageway formed in said nozzle body and having an inlet, a throat, and an exit, said supersonic passageway having a converging section between said inlet and said throat and a diverging section between said throat and said exit, said supersonic passageway adapted for producing sonic flow at said throat and supersonic flow in said diverging section;
- (c) a shield disposed about said exterior surface of said nozzle body and extending in the direction of flow beyond said exit;
- (d) an exit opening formed by said shield, said exit opening being aligned with said exit of said supersonic passageway, said exit opening being of a complimentary shape to said exit and having a cross-sectional area at least as large as the cross-sectional area of said exit, said exit opening having a perimeter;
- (e) an exit cavity defined by said exit of said supersonic passageway, said shield and said exit opening of said shield;
- and
- (f) a gill angle formed between said exterior surface and said perimeter, said gill angle being no greater than 90.degree..
Dependencies are inferred from the claim text.