Fuel supply system for a staged combustor

Power plants – Combustion products used as motive fluid

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Details

60734, 60747, F02C 722

Patent

active

054026342

ABSTRACT:
A fuel supply system for a gas turbine engine having a multi-stage combustor provides responsiveness by blocking the drainage of fuel within the fuel lines during pilot only operation. In a particular embodiment, the fuel supply system includes a fuel source, a flow splitter valve, a main flow divider valve interconnected with a plurality of main fuel injectors, a pilot flow divider valve interconnected with a plurality of fuel injectors, and check valves disposed in the fuel lines connecting the main flow divider and the main fuel injectors. The check valves block the flow of fuel to the plurality of main fuel injectors during pilot only operation. A method of operating the fuel supply system includes built in hysteresis. The method includes the steps of switching from pilot to staged at a first thrust level TL.sub.1, and switching from staged to pilot at a second thrust level TL.sub.2 <TL.sub.1.

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