초록 ▼

A fuel delivery system for a gas turbine engine combustor, the combustor having at least two fuel injectors of substantially the same design. All the fuel injectors are in flow communication with a first fuel supply via a first manifold, and some but not all of the injectors are in flow communicatio

A fuel delivery system for a gas turbine engine combustor, the combustor having at least two fuel injectors of substantially the same design. All the fuel injectors are in flow communication with a first fuel supply via a first manifold, and some but not all of the injectors are in flow communication with a second fuel supply via a second manifold. During normal operation of the gas turbine engine combustor fuel is supplied to all of the fuel injectors via the first manifold. However, during predetermined engine operating conditions a second fuel supply is used to supply fuel flow in those fuel injectors in flow communication with the second manifold.

대표청구항 ▼

1. A fuel delivery system for a gas turbine engine, comprising: a combustor, a fuel supply, a first manifold, a second manifold, and a plurality of fuel injectors of substantially the same design, whereby at least one of said fuel injectors is in direct flow communication with the first manifold and

1. A fuel delivery system for a gas turbine engine, comprising: a combustor, a fuel supply, a first manifold, a second manifold, and a plurality of fuel injectors of substantially the same design, whereby at least one of said fuel injectors is in direct flow communication with the first manifold and the remainder of said fuel injectors are in direct flow communication with the second manifold, the first manifold and the second manifold are in flow communication with the fuel supply through a first flow communication means which passes fuel under predetermined engine range, otherwise the second manifold is in flow communication with the fuel supply via a second flow communication means, wherein under predetermined engine range fuel is supplied to all of the fuel injectors and under predetermined engine conditions fuel is supplied to all the fuel injectors and additional fuel is supplied to the fuel injectors in direct flow communication with the second manifold.2. A fuel delivery system for a gas turbine engine as claimed in claim 1, wherein the first flow communication means comprises a pressure raising valve.3. A fuel delivery system for a gas turbine engine as claimed in claim 1, wherein the second flow communication means comprises a biased valve, a first flow restrictor and a second flow restrictor, arranged such that the second manifold is connected with the fuel supply via the second flow restrictor in series with the biased valve, said biased valve providing bypass means around the first flow restrictor such that in operation the fuel supply is used to supply fuel flow to the fuel injectors in direct flow communication with the second manifold.4. A fuel delivery system for a gas turbine engine as claimed in claim 1, wherein the first and second manifolds are fluidly connected.5. A fuel delivery system for a gas turbine engine as claimed in claim 4, wherein a further biased valve is connected between the first and second manifolds whereby the biased valve is operative to prevent reverse flow communication from the second manifold to the first manifold.6. A fuel delivery system for a gas turbine engine as claimed in claim 5, wherein a third flow restrictor is arranged in communication with the first and second manifolds to provide in operation bypass means around the biased valve such that during engine shut down fuel can be back purged from the second manifold into the first flow communication means.7. A fuel delivery system for a gas turbine engine as claimed in claim 2, wherein the second flow communication means comprises a biased valve, a first flow restrictor and a second flow restrictor, arranged such that the second manifold is connected with the fuel supply via the second flow restrictor in series with the biased valve, said biased valve providing bypass means around the first flow restrictor such that in operation the fuel supply is used to supply fuel flow to the fuel injectors in direct flow communication with the second manifold.8. A fuel delivery system for a gas turbine engine as claimed in claim 2, wherein the first and second manifolds are fluidly connected.9. A fuel delivery system for a gas turbine engine as claimed in claim 3, wherein the first and second manifolds are fluidly connected.10. A fuel delivery system for a gas turbine engine as claimed in claim 8, wherein a further biased valve is connected between the first and second manifolds whereby the biased valve is operative to prevent reverse flow communication from the second manifold to the first manifold.11. A fuel delivery system for a gas turbine engine as claimed in claim 9, wherein a further biased valve is connected between the first and second manifolds whereby the biased valve is operative to prevent reverse flow communication from the second manifold to the first manifold.12. A fuel delivery system for a gas turbine engine as claimed in claim 10, wherein a third flow restrictor is arranged in communication with the first and second manifolds to provide in operation bypass means around the biased valve such that during engine shut down fuel can be back purged from the second manifold into the first flow communication means.13. A fuel delivery system for a gas turbine engine as claimed in claim 11, wherein a third flow restrictor is arranged in communication with the first and second manifolds to provide in operation bypass means around the biased valve such that during engine shut down fuel can be back purged from the second manifold into the first flow communication means.