Expander-cycle, turbine-drive, regenerative rocket engine

Details Expander-cycle, turbine-drive, regenerative rocket engine Expander-cycle, turbine-drive, regenerative rocket engine

1985-04-22

1986-04-22

Casaregola, Louis J.

Power plants

Reaction motor

Liquid oxidizer

60260, 60267, F02K 900

Patent

active

045833621

ABSTRACT:
A heat-regenerative, expander-cycle, turbine-drive rocket engine 26 in which heated oxidizer gas is used to drive the fuel and oxidizer turbines 16 and 20. The hot exhaust gas from the oxidizer turbine 20 is passed through a heat-donor coil 36 of a heat exchanger 24 where it passes heat to the oxidizer flowing through a donee coil 34 to preheat the oxidizer liquid and gasify it before it is passed through the cooling jacket 28 of the rocket engine 26 where it cools the engine 26 and is itself heated to a higher temperature. The oxidizer, e.g., N.sub.2 O.sub.4, is brought to higher temperature and pressure than its supercritical temperature and pressure so that flashing and boiling of the oxidizer are avoided.

REFERENCES:
patent: 2763126 (1956-09-01), Halford et al.
patent: 2906091 (1959-09-01), Kretschmer
patent: 3017745 (1962-01-01), Shirley et al.
patent: 3028729 (1962-04-01), Ledwith
patent: 3048966 (1962-08-01), Feraud et al.
patent: 3049870 (1962-08-01), Chamberlain
patent: 3561217 (1971-02-01), Hall
patent: 3613375 (1971-10-01), Abild
patent: 4073138 (1978-02-01), Beichel
patent: 4369920 (1983-01-01), Schmidt
patent: 4379679 (1983-04-01), Guile
Beichel, "Propulsion Systems for Single-Stage Shuttles" Astronautics & Aeronautics, Nov. 1974, pp. 32-39, see pp. 37 & 36.

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