초록 ▼

A method of operating a gas turbine engine combustion system at lower load conditions while maintaining required emissions levels is disclosed. The present invention includes multiple embodiments of axial, radial, and circumferential fuel staging within a can-type combustor having alternate ignitio

A method of operating a gas turbine engine combustion system at lower load conditions while maintaining required emissions levels is disclosed. The present invention includes multiple embodiments of axial, radial, and circumferential fuel staging within a can-type combustor having alternate ignition techniques of spark ignition or torch ignition.

대표청구항 ▼

What is claimed is: 1. A method of operating a combustion system of a gas turbine engine, said method comprising: a). providing a combustion system comprising a plurality of first stage injectors arranged in a first array about a center axis, a plurality of second stage injectors arranged in a seco

What is claimed is: 1. A method of operating a combustion system of a gas turbine engine, said method comprising: a). providing a combustion system comprising a plurality of first stage injectors arranged in a first array about a center axis, a plurality of second stage injectors arranged in a second array radially outward of said first injectors proximate a first swirler, an aft injector assembly comprising a manifold having a plurality of third stage injectors and a plurality of fourth stage injectors, said plurality of third stage and fourth stage injectors arranged in sectors of said aft injector assembly, and a spark ignition source located within said combustion system; b). supplying a fuel to said plurality of first stage injectors and said plurality of second stage injectors at a fuel flow split and injecting said fuel into a surrounding air flow to form a mixture, and igniting said mixture with said spark ignition source; c). gradually increasing fuel flow split to said plurality of first stage injectors while gradually decreasing fuel flow split to said plurality of second stage injectors until all fuel to said combustion system is flowing through said plurality of first stage injectors at engine full speed no load condition; d). maintaining said fuel flow split to said plurality of first stage injectors until a first part-load condition; e). at said first part-load condition, gradually decreasing said fuel flow split to said plurality of first stage injectors while gradually increasing said fuel flow split to said plurality of second stage injectors until all fuel to said combustion system is flowing through said plurality of second stage injectors at a second part-load condition; f). maintaining said fuel flow split to said plurality of second stage injectors until a third part-load condition; g). at said third part-load condition, reducing said fuel flow split to said plurality of second stage injectors while increasing fuel flow split to said plurality of third stage injectors; h). gradually decreasing said fuel flow split to said plurality of second stage injectors while gradually increasing said fuel flow split to said plurality of third stage injectors until a fourth part load condition; i). At said fourth part load condition, reducing said fuel flow split to both said plurality of second stage injectors and said plurality of third stage injectors while increasing fuel flow split to said plurality of fourth stage injectors; and, j). maintaining said fuel flow split to said plurality of second stage, third stage, and fourth stage injectors until said gas turbine engine reaches a full load condition. 2. The method of claim 1 wherein NOx emissions are controlled as total combustor fuel flow increases by reducing fuel flow split to the previously activated injector. 3. The method of claim 1 wherein said gas turbine combustion system further comprises a second swirler adjacent said aft injector assembly. 4. The method of claim 1 wherein said plurality of third stage injectors is oriented in a sector encompassing approximately one third of said aft injector assembly manifold. 5. The method of claim 4 wherein said plurality of fourth stage injectors is oriented in a sector encompassing approximately two thirds of said aft injector assembly manifold. 6. A method of operating a combustion system of a gas turbine engine, said method comprising: a). providing a combustion system comprising a plurality of second stage injectors arranged in an array about a center axis proximate a first swirler, an aft injector assembly comprising a manifold having a plurality of first stage injectors, a plurality of third stage injectors, and a plurality of fourth stage injectors, said plurality of first stage, third stage, and fourth stage injectors arranged in sectors of said aft injector assembly, and a torch ignition source located within said combustion system; b). supplying a fuel to said plurality of first stage injectors and said plurality of second stage injectors at a fuel flow split and injecting said fuel into a surrounding air flow to form a mixture, and igniting said mixture with said torch ignition source; c). gradually increasing fuel flow split to said plurality of first stage injectors while gradually decreasing fuel flow split to said plurality of second stage injectors until all fuel to said combustion system is flowing through said plurality of first stage injectors at engine full speed no load condition; d). maintaining said fuel flow split to said plurality of first stage injectors until a first part-load condition; e). at said first part-load condition, gradually decreasing said fuel flow split to said plurality of first stage injectors while gradually increasing said fuel flow split to said plurality of second stage injectors until all fuel to said combustion system is flowing through said plurality of second stage injectors at a second part-load condition; f). maintaining said fuel flow split to said plurality of second stage injectors until a third part-load condition; g). at said third part-load condition, reducing said fuel flow split to said plurality of second stage injectors while increasing fuel flow split to said plurality of third stage injectors; h). gradually decreasing said fuel flow split to said plurality of second stage injectors while gradually increasing said fuel flow split to said plurality of third stage injectors until a fourth part load condition; i). At said fourth part load condition, reducing said fuel flow split to both said plurality of second stage injectors and said plurality of third stage injectors while increasing fuel flow split to said plurality of fourth stage injectors; and, j). maintaining said fuel flow split to said plurality of second stage, third stage, and fourth stage injectors until said gas turbine engine reaches a full load condition. 7. The method of claim 6 wherein NOx emissions are controlled as total combustor fuel flow increases by reducing fuel flow split to the previously activated injector. 8. The method of claim 6 wherein said gas turbine combustion system further comprises a second swirler adjacent said aft injector assembly. 9. The method of claim 6 wherein said plurality of first stage injectors is oriented in a sector encompassing approximately one third of said aft injector assembly manifold. 10. The method of claim 9 wherein said plurality of third stage injectors is oriented in a sector encompassing approximately one third of said aft injector assembly manifold. 11. The method of claim 10 wherein said plurality of fourth stage injectors is oriented in a sector encompassing approximately one third of said aft injector assembly manifold.