Turbojet engine with combustor bypass

Details Turbojet engine with combustor bypass Turbojet engine with combustor bypass

1978-01-10

1980-01-29

Croyle, Carlton R.

Power plants

Reaction motor

Liquid oxidizer

60262, 60 3923, F02K 310, F02K 102

Patent

active

041854616

ABSTRACT:
A propulsion system having an afterburning turbojet with the fuel supplied at the inlet to the turbojet compressor. The turbojet combustor has a bypass with a flow control connected at the inlets to the combustor and the bypass to control the amount of fuel-air mixture from the compressor that enters the combustor.

REFERENCES:
patent: 2693674 (1954-11-01), Anxionnaz et al.
patent: 2946185 (1960-07-01), Bayer
patent: 3045425 (1962-07-01), Seifferlein
patent: 3486338 (1969-12-01), Haussmann et al.
Hill et al., Mechanics and Thermodynamics of Propulsion, 1965, pp. 216-217.

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