Annular premix section for dry low-NO.sub.x combustors
First Claim
1. A gas turbine combustor, comprising:
- a nozzle housing, said nozzle housing having a nozzle housing base, a main combustion zone located adjacent to said nozzle housing;
a main fuel nozzle, said main fuel nozzle having a main fuel injection port and a tip, said main fuel nozzle extending through said nozzle housing and attached to the nozzle housing base, the tip of said main fuel nozzle located downstream of the nozzle housing base; and
a main fuel swirler, said main fuel swirler having an axis, swirler vanes, and a downstream end, the axis of said main fuel swirler substantially parallel to said main fuel nozzle, said main fuel swirler surrounding a portion of said main fuel nozzle, the downstream end of said main fuel swirler located downstream of said main fuel injection port and upstream of said main fuel nozzle tip; and
the main fuel injection port located downstream of the swirler vanes.
5 Assignments
0 Petitions
Accused Products
Abstract
An annular premix section that reduces NOx and CO emissions of a gas turbine combustor by providing a more homogeneous fuel/air mixture for main stage combustion is provided. A gas turbine combustor according to the present invention includes a nozzle housing, a main fuel nozzle, and a main fuel swirler. A main combustion zone is located adjacent to the nozzle housing. The main fuel nozzle extends through the nozzle housing and is attached to a nozzle housing base. The tip of the main fuel nozzle is located downstream of the nozzle housing base. The main fuel swirler surrounds a portion of the main fuel nozzle, with a downstream end of the main fuel swirler located downstream of a main fuel injection port and upstream of the main fuel nozzle tip. The main fuel swirler is adapted to receive a flow of compressed air and to mix a fuel with the flow of compressed air to form a fuel/air mixture flow. An annular premix section, adjacent to the downstream end of the main fuel swirler, is adapted to receive and expand the fuel/air mixture flow. A contraction zone is located downstream of the premix section and upstream of the main combustion zone. The contraction zone is adapted to increase the velocity of the fuel/air mixture flow into the main combustion zone.
150 Citations
9 Claims
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1. A gas turbine combustor, comprising:
- a nozzle housing, said nozzle housing having a nozzle housing base, a main combustion zone located adjacent to said nozzle housing;
a main fuel nozzle, said main fuel nozzle having a main fuel injection port and a tip, said main fuel nozzle extending through said nozzle housing and attached to the nozzle housing base, the tip of said main fuel nozzle located downstream of the nozzle housing base; and
a main fuel swirler, said main fuel swirler having an axis, swirler vanes, and a downstream end, the axis of said main fuel swirler substantially parallel to said main fuel nozzle, said main fuel swirler surrounding a portion of said main fuel nozzle, the downstream end of said main fuel swirler located downstream of said main fuel injection port and upstream of said main fuel nozzle tip; and
the main fuel injection port located downstream of the swirler vanes. - View Dependent Claims (2, 3, 4)
- a nozzle housing, said nozzle housing having a nozzle housing base, a main combustion zone located adjacent to said nozzle housing;
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5. A gas turbine combustor comprising:
- a nozzle housing, said nozzle housing having a nozzle housing base, a main combustion zone located adjacent to said nozzle housing;
a main fuel nozzle, said main fuel nozzle having a main fuel injection port and a tip, said main fuel nozzle extending through said nozzle housing and attached to the nozzle housing base, the tip of said main fuel nozzle located downstream of the nozzle housing base; and
a main fuel swirler having swirler vanes and a downstream end, said main fuel swirler surrounding a portion of said main fuel nozzle, the downstream end of said main fuel swirler located downstream of the main fuel injection port of said main fuel nozzle and upstream of the tip of said main fuel nozzle, the main fuel injection port located downstream of the swirler vanes, said main fuel swirler adapted to receive a flow of compressed air, said main fuel swirler adapted to mix a fuel with the flow of compressed air to form a fuel/air mixture flow; and
a premix section adjacent to the downstream end of said main fuel swirler, said premix section adapted to receive and expand said fuel/air mixture flow. - View Dependent Claims (6, 7, 8, 9)
- a nozzle housing, said nozzle housing having a nozzle housing base, a main combustion zone located adjacent to said nozzle housing;
Specification