| CPC F02C 9/32 (2013.01) [F02C 7/222 (2013.01); F02C 7/228 (2013.01); F05D 2220/32 (2013.01); F05D 2240/35 (2013.01)] | 12 Claims |
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1. A fuel system for an aircraft engine that burns gaseous fuel, the fuel system comprising:
a gaseous fuel supply configured to provide the gaseous fuel;
a main inlet feed conduit fluidly connecting the gaseous fuel supply to a primary manifold feed conduit and to a secondary manifold feed conduit;
a primary manifold fluidly connecting the primary manifold feed conduit to a plurality of primary fuel injectors;
a secondary manifold fluidly connecting the secondary manifold feed conduit to a plurality of secondary fuel injectors;
a fuel regulator disposed in the main inlet feed conduit upstream of the primary manifold and the secondary manifold, the fuel regulator operable to regulate flow through at least the main inlet feed conduit and the primary manifold;
a primary fuel flow valve disposed in the primary manifold feed conduit downstream of the fuel regulator, the primary fuel flow valve being a first pulse width modulation (PWM) valve, wherein the primary fuel flow valve has an open condition operative to permit flow of fuel through the primary manifold feed conduit and a closed condition operative to inhibit flow of fuel through the primary manifold feed conduit;
a secondary fuel flow valve disposed in the secondary manifold feed conduit downstream of the fuel regulator, wherein the secondary fuel flow valve has an open condition operative to permit flow of fuel through the secondary manifold feed conduit and a closed condition operative to inhibit flow of fuel through the secondary manifold feed conduit; and
a controller operatively connected to the first PWM valve, wherein the controller is configured to control the first PWM valve, when in the open condition, to pulse a flow of the gaseous fuel fed to the primary fuel injectors to regulate a fuel flow exiting the primary fuel injectors.
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