Brennstoffversorgungseinrichtung für Turbo-Strahltriebwerke mit Nachbrenner

摘要

A fuel supply device 1 for a turbo jet engine with afterburner 2 has pipes 9 and 10 bifurcating from a main fuel pipe 7 for the supplying of fuel to the afterburner 2 and the combustion chamber 3. To deliver the fuel at the required rate of flow and at the required pressure, provision is made in the main fuel pipe 7 for a first fuel delivery pump 6, and for a second fuel pump 11 and respectively an afterburner pump 18 in the fuel pipes 9 and 10. In order also to be able to supply the afterburner 2 via the second fuel pump 11 when a suitably free pump capacity exists, downstream of the afterburner pump 18 and the second fuel pump 11 provision is made for a connecting pipe 19 between the two fuel pipes 9 and 10. When operating the turbo jet engine with afterburner, the afterburner 2 can be supplied by the second fuel pump 11 via the connecting pipe 19 when the fuel requirement of the turbo-combustion chamber 3 is reduced, so that its delivered quantity of fuel is high. An undesirably high fuel temperature downstream of the second fuel pump 11 can thus be prevented. An oil cooler 14 may be provided (various positions of correction being disclosed) as well as a 2/4 directional control valve in the connecting pipe (figure 2). <IMAGE>