Power plants – Reaction motor – Method of operation
Patent
1986-08-28
1988-08-23
Casaregola, Louis J.
Power plants
Reaction motor
Method of operation
60253, F02K 972
Patent
active
047651342
ABSTRACT:
The periodic shedding of vortices produced in a highly sheared gas flow, such as that encountered at the grain transition boundary in a solid propellant rocket motor or at the combustor inlet to a ramjet engine, is a significant source of acoustic instability which may result in unstarting of the ramjet engine or excessive vibration of the rocket motor. By restricting the transition boundary or combustor inlet at the sudden expansion dump plane (5), such as by locating an orifice plate (13) at the dump plane, the gas flow is separated upstream and produces a vena contracta downstream of the orifice, inhibiting the feedback of acoustic pressure to the point of flow separation and preventing the formation of organized oscillations. Incorporation of such a simple thin plate orifice at the dump plane reduces the periodic acoustic oscillations and thereby controls the detrimental oscillatory pressure fluctuations.
REFERENCES:
patent: 3315472 (1967-04-01), Moutet et al.
patent: 3407736 (1968-10-01), Beuschet
patent: 3656304 (1972-04-01), McCullough
patent: 4047483 (1977-09-01), Williams
patent: 4075832 (1978-02-01), Diesinger et al.
Brown Robert S.
Dunlap Roger
Casaregola Louis J.
Sapone William J.
United Technologies Corporation
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