Hexagonal cluster nozzle for a rocket engine

Details Hexagonal cluster nozzle for a rocket engine Hexagonal cluster nozzle for a rocket engine

1993-04-28

1994-09-06

Bertsch, Richard A.

Power plants

Internal combustion engine with treatment or handling of...

Material from exhaust structure fed to engine intake

60263, 60224, 23926511, F02K 100

Patent

active

053436989

ABSTRACT:
A rocket engine thrust nozzle assembly is disclosed wherein combustion products from a plurality of rocket engines having hexagonally-shaped exhaust areas flow to the inlet of a main nozzle that transitions the flow of the combustion products from a non-circular flow area to a circular flow area.

REFERENCES:
patent: 2573697 (1951-11-01), Dunbar et al.
patent: 3115747 (1963-12-01), Yu
patent: 3817029 (1974-06-01), Frisch

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