초록

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.

대표청구항 ▼

1. 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 transve

1. 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; andwherein 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; andwherein 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. 2. A gas turbine combustor according to claim 1, wherein said plurality of fuel nozzles are partitioned into a plurality of fuel supply systems and a control system is provided so as to individually control the flow rate of fuel for each fuel supply system according to a load on the gas turbine. 3. A gas turbine combustor according to claim 2, wherein, a swirling angle which provides a swirling component around the axis of the combustor chamber is given to a part or all of said plurality of fuel nozzles and corresponding air holes. 4. A gas turbine combustor according to claim 2, wherein a fuel hole of the fuel nozzle is disposed coaxially or almost coaxially with the air hole, a fuel jet being injected toward the vicinity of the center of the air hole inlet, and a fuel jet and a circular flow of the air enveloping the fuel jet being injected into the combustion chamber as a coaxial jet from an outlet of the air hole, anda plurality of modules, each module consisting of the fuel nozzle and the air hole, are combined to form a combustor. 5. A gas turbine combustor according to claim 1, wherein said plurality of fuel nozzles are partitioned in a plurality of fuel supply systems, and a control system is provided for controlling independently a fuel flow rate in each of said plurality of fuel supply systems according to a load on the gas turbine. 6. 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; anda 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. 7. 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 cham ber as a plurality of coaxial jet flows; andimparting 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.