| 摘要 |
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.
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