Fuel-distribution system for a gas turbine engine

Power plants – Combustion products used as motive fluid – Combustion products generator

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137 38, F02C 7228

Patent

active

054129494

ABSTRACT:
A fuel distribution system for a gas-turbine engine is disclosed which ensures homogenous fuel supply to all fuel injectors in order to avoid local fuel oversupplies that might cause local overheating of the turbine blades. The fuel system compensates for the deleterious load factors experienced by the aircraft and the gas turbine engine that affect the fuel distribution to the fuel injectors. The system supplies fuel to a plurality of fuel injectors arranged in an annular array so as to inject fuel into an annular combustion chamber of the gas turbine engine. The system has a closed loop, generally annular fuel connector line and a plurality of fuel distributors connected in parallel to the fuel connector line so that fuel passes into a central chamber of each of the distributors. Each fuel distributor has end chambers on opposite ends of the central chamber in which are movably located pistons whose positions within the end chambers open or close a fuel outlet in communication with each of the end chambers. Each fuel injector is connected to one fuel outlet of a pair of fuel distributors. Also, the two fuel outlets of each fuel distributor are connected to different fuel injectors. The fuel distributor is oriented such that central axis of the central and end chambers extends substantially parallel to a line drawn between the ends of the fuel injectors served by that fuel distributor.

REFERENCES:
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patent: 3249145 (1966-05-01), Alberani et al.
patent: 3348560 (1967-10-01), Stearns
patent: 3738104 (1973-06-01), Rosa
patent: 3774851 (1973-11-01), Simmons

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