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US 6,813,889 B2Granted
Gas turbine combustor and operating method thereof
AssigneeHitachi, Ltd.
InventorsHiroshi Inoue, Tomomi Koganezawa, Nariyoshi Kobayashi, Isao Takehara
Life of this patent
Estimating the term…
Abstract
A gas turbine combustor has a combustion chamber into which fuel and air are supplied, wherein the fuel and the air are supplied into said combustion chamber as a plurality of coaxial jets.
Claims7
A gas turbine combustor comprising:
- a combustion chamber;
- a member arranged at a upstream side of said combustion chamber and having a plurality of air holes formed therein, said air holes having inlets and outlets, respectively, said outlets of said air holes being dispersed in a direction transverse to an axis of said combustion chamber and opened to said combustion chamber;
- a plurality of fuel nozzles for injecting fuel into said combustion chamber through said air holes, respectively;
- and
- wherein said air holes and said plurality of fuel nozzles are arranged so that fuel and air are jetted as a plurality of coaxial jet flows from said outlets of air holes into said combustion chamber;
- and
- wherein fuel holes of the fuel nozzles are disposed coaxially or almost coaxially with said air holes, respectively, and said fuel nozzles and said air holes are arranged so that a fuel jet from each of said fuel nozzles is injected toward the vicinity of the center of said inlet of each of said air holes, and a fuel jet and a circular flow of the air enveloping the fuel jet is injected into the combustion chamber as a coaxial jet from each of said air hole outlets.
4 more elements
A gas turbine combustor comprising:
- a combustion chamber;
- a member having a plurality of air holes formed therein, said air holes each opened to said combustion chamber;
- a plurality of fuel nozzles corresponding to said air holes, and having fuel jet holes arranged coaxially or nearly coaxially with said air holes, respectively;
- wherein said plurality of fuel nozzles and said air holes are arranged so that fuel jet flows from said fuel nozzles are directed to central portions of inlets of said air holes to form fuel jet flows enclosed by annular air flows which are jetted from outlets of said air holes as a plurality of coaxial jet flows into said combustion chamber;
- and
- a swirling means provided in at least a part of said plurality of fuel nozzles and the corresponding air holes, for imparting swirling components to the jet flows swirling around an axis of said combustion chamber.
3 more elements
A method of operating a gas turbine combustor having a plurality of fuel nozzles, air holes and a combustion chamber, said method comprising the steps of:
- arranging fuel jet holes of said fuel nozzles to be coaxial or nearly coaxial with said air holes;
- flowing air into said combustion chamber through said air holes;
- jetting fuel from said fuel nozzles to central portions of inlets of said air holes so that fuel jet flows from said fuel nozzles and annular air flows enclosing said fuel jet flows are jetted from an outlet of said air holes into said combustion chamber as a plurality of coaxial jet flows;
- and
- imparting swirling components swirling around an axis of said combustion chamber to jet flows from at least part of said plurality of fuel nozzles and the corresponding air holes.
2 more elements
Dependencies are inferred from the claim text.