Recoup turbojet engine

Details Recoup turbojet engine Recoup turbojet engine

1996-12-24

1998-07-14

Casaregola, Louis J.

Power plants

Reaction motor

Method of operation

60261, 60266, F02K 310

Patent

active

057786585

ABSTRACT:
A turbojet engine includes a compressor and turbine, with a combustor disposed therebetween for generating exhaust gas. An afterburner includes an annular casing and liner spaced radially inwardly therefrom to define a cooling duct therebetween. A recoup duct is disposed in flow communication with the compressor for receiving a portion of compressed air therefrom as recoup air. A plenum is disposed at an upstream end of the afterburner casing, and includes an inlet disposed in flow communication with the recoup duct for receiving the recoup air, and an outlet disposed in flow communication with the afterburner cooling duct for discharging the recoup air therein.

REFERENCES:
patent: 2794319 (1957-06-01), Stockdale
patent: 2846841 (1958-08-01), Jordan
patent: 3394543 (1968-07-01), Slattery
Treager, Irwin E. Aircraft Gas Turbine Engine Technology McGraw-Hill, New York; 1979. pp. 175-177, 390-401.
General Electric Company. J85 Engine Manual Figures 1-39 and 1-57.

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