Pre-regenerated staged-combustion rocket engine

Details Pre-regenerated staged-combustion rocket engine Pre-regenerated staged-combustion rocket engine

1984-04-16

1986-05-20

Croyle, Carlton R.

Power plants

Reaction motor

Method of operation

60259, 60260, 60266, 60736, F02K 948

Patent

active

045892539

ABSTRACT:
An improvement in the design of a staged-combustion-cycle rocket engine. The preburner 16 (or preburners) is operated at a higher temperature than that above which turbine blades will be damaged. A heat-exchanger unit 40 through which the output flow of the cooling jacket 18 of the engine is passed is placed inside the preburners 16, or in close proximity to its output flow, so that heat energy is transferred from the output flow of the preburners 16 to the output flow of the cooling jacket 18. This lowers the preburners output flow to a temperature which will not damage turbine blades and raises the cooling-jacket output flow temperature. Since the output flow of the cooling jacket 18 is fed to the low-pressure turbines 22, the increased temperature raises the pressure of the low-pressure turbines 22 so that their output of flow rate is increased and the flow rate to the engine is increased, thereby increasing engine output power and efficiency.

REFERENCES:
patent: 3046734 (1962-07-01), Abild
patent: 3524319 (1970-08-01), Stockel
patent: 3561217 (1971-02-01), Hall
patent: 3577735 (1971-05-01), Schmidt
patent: 3636712 (1972-01-01), Kaufmann
patent: 3828551 (1974-08-01), Schmidt
patent: 4073138 (1978-02-01), Beichel
patent: 4171615 (1979-10-01), Stewart et al.
patent: 4328020 (1982-05-01), Hughes

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