Gas-fed hybrid propulsion system

Details Gas-fed hybrid propulsion system Gas-fed hybrid propulsion system

1989-11-07

1991-04-30

Casaregola, Louis J.

Power plants

Reaction motor

Turborocket

60251, 60262, 60263, F02K 500

Patent

active

050107305

ABSTRACT:
Self-contained hybrid propulsion systems have long been recognized as a class of propulsion systems that combine a liquid propellant and a solid propellant into a single system. The propellants are stored separately and the liquid propellant is delivered to the motor casing that holds the solid propellant. The present invention contemplates gasifying the liquid propellant prior to introduction into the motor casing in order to enhance system performance. The solid propellant grain is ignited and partially burned generating heat to evaporate the remaining solid propellant grain at a controlled rate. The resulting mixture is then passed to a secondary combustion region where it is mixed with additional gasified liquid propellant to complete the combustion. An integrated turbopump assembly including a pump portion, a preburner portion and a turbine portion is provided to pressurize and gasify the liquid propellant.

REFERENCES:
patent: 3158992 (1964-12-01), Hodgson
patent: 3158994 (1964-12-01), Hodgson
patent: 3334489 (1967-08-01), Vilet
patent: 3613583 (1971-10-01), Lai et al.
patent: 3709652 (1973-01-01), Iwanciow et al.
patent: 3782112 (1974-01-01), Muzzy
patent: 3943706 (1976-03-01), Grafwallner et al.
patent: 4424679 (1984-01-01), Holzman
patent: 4589253 (1986-05-01), Wagner
Merrifield, John T., "Aerojet TechSystems Develops Hypersonic Aircraft Engine", Aeronautical Engineering, pp. 57-60, Oct. 14, 1985.

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