Method for reducing the nonsteady side loads acting on a...

Details Method for reducing the nonsteady side loads acting on a... Method for reducing the nonsteady side loads acting on a...

2006-02-22

2009-10-20

Casaregola, Louis J (Department: 3741)

Power plants

Reaction motor

Method of operation

C060S233000, C239S265190

Reexamination Certificate

active

07603842

ABSTRACT:
A method for reducing the nonsteady side loads acting on a nozzle of a rocket engine during a startup phase of said engine. The nozzle comprises a combustion chamber (1) where exhaust gases are generated, a divergent portion (3) in which a supersonic flow of said exhaust gases occurs, and a throat (2) connecting the combustion chamber to the divergent portion, which method comprises the positioning of a body of rounded shape (5) inside the divergent portion (3) along its axis corresponding to an axial position such that, during at least part of the startup phase, a shock wave (8), induced by the distrubance of the flow of the exhaust gases by the body of rounded shape (5) is incident to the wall of the divergent portion (3) at an axial incidence position where it produces a jet separation or a separation in the form of a toroidal separation bulb.

REFERENCES:
patent: 2674088 (1954-04-01), Riedel et al.
patent: 3059425 (1962-10-01), McSherry et al.
patent: 5560559 (1996-10-01), Larsen
patent: 5607123 (1997-03-01), Larsen
patent: 2002/0157399 (2002-10-01), Dujarric
patent: 0 508 851 (1992-10-01), None
Frey M. et al., “Flow Separation and Side-Loads in Rocket Nozzles”,AIAA/SAE/ASME/ASEE Joint Propulsion Conference and Exhibit, Jun. 20, 1999, pp. 1-11.

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