Fuel distribution within a gas turbine engine combustor
AssigneeUnited Technologies Corporation
InventorsJames B. Hoke, Timothy S. Snyder, David Kwoka, Robert M. Sonntag
Life of this patent
Estimating the term…
Abstract
A fuel system for a gas turbine engine includes a plurality of duplex nozzles arranged on each side of top dead center and a plurality of simplex nozzles. A primary manifold is operable to communicate fuel to a primary flow jet in each of the plurality of duplex nozzles and a secondary manifold is operable to communicate fuel to a secondary flow jet in each of the plurality of duplex nozzles and a secondary flow jet in each of the plurality of simplex nozzles. An equalizer valve that is in communication with both the primary manifold and the secondary manifold distributes fuel at various pressures to both the primary and secondary manifolds.
Claims13
A method of noise control from a combustor of a gas turbine engine comprising:
- forming a plurality of alternating local circumferential zones about an engine longitudinal axis with different fuel-air ratios within the combustor including forming a high fuel-air ratio circumferential zone at a top center position and forming a low fuel-air ratio circumferential zone at a bottom center position relative to the engine longitudinal axis, wherein a high fuel-air ratio is generated by at least two duplex fuel nozzles disposed on either side of the top center position and a low fuel-air ratio is generated by at least two simplex fuel nozzles disposed on either side of a bottom center position.
A method of noise control from a combustor of a gas turbine engine comprising:
- selectively forming a plurality of local circumferential zones with different fuel-air ratios within the combustor including forming a high fuel-air ratio circumferential zone at a top dead center position and forming a low fuel-air ratio circumferential zone at a bottom dead center position;
- and
- alternating a plurality of duplex nozzles and a plurality of simplex nozzles to define the plurality of local circumferential zones wherein the plurality of duplex nozzles includes ten (10) duplex nozzles and the plurality of simplex nozzles includes six (6) simplex nozzles.
A method of noise control from a combustor of a gas turbine engine comprising:
- selectively forming a plurality of local circumferential zones with different fuel-air ratios within the combustor including forming a high fuel-air ratio circumferential zone at a top dead center position and forming a low fuel-air ratio circumferential zone at a bottom dead center position;
- and
- alternating a plurality of duplex nozzles and a plurality of simplex nozzles to define the plurality of local circumferential zones wherein the plurality of duplex nozzles includes ten (10) duplex nozzles and the plurality of simplex nozzles includes six (6) simplex nozzles;
- selectively dividing a fuel pressure between a primary manifold and a secondary manifold in response to a low power condition, the primary manifold in communication with a primary flow jet in each of the plurality of duplex nozzles and the secondary manifold in communication with a secondary flow jet in each of the plurality of duplex nozzles and a secondary flow jet in each of the plurality of simplex nozzles, wherein the low power condition comprises power required for approach conditions, wherein the power required for approach conditions is greater than power at a cruise condition.
Dependencies are inferred from the claim text.