F - Mech Eng,Light,Heat,Weapons – 02 – C
Patent
F - Mech Eng,Light,Heat,Weapons
02
C
F02C 9/34 (2006.01) F23R 3/34 (2006.01)
Patent
CA 2084176
A gas turbine combustor for a gas turbine power plant comprises a combustion liner connected to a turbine and provided with a main fuel nozzle assembly and a sub-fuel nozzle assembly for jetting fuel to an inside of the combustion liner through nozzle holes, a base fuel supply line, a main fuel line for supplying a fuel to the main nozzle assembly for premixing an air with the fuel jetted through the nozzle hole for carrying out a lean- burning in the combustion liner, and a plurality of sub-fuel lines for supplying the fuel to the sub-fuel nozzle assembly for mixing the fuel with a combustion air for carrying out an diffusion burning in the combustion liner. The main and sub-fuel lines are composed of by branching a front end of the base fuel supply line. Distributing valves are incorporated in the main fuel line and at least one of the sub-fuel lines for distributing the fuel into the main and sub-fuel lines and degree of openings of the distributing valves are controlled by a control unit for controlling a fuel distribution ratio. The sub-fuel nozzle assembly includes a swirler provided with swirling vanes at an end portion inserted in the combustion liner for swirling the fuel therein. The swirling vanes are provided with a combustion air passage to which the nozzle holes of the sub-fuel nozzle assembly are opened.
Itoh Masao
Izumi Atsuhiko
Kabushiki Kaisha Toshiba
Ogilvy Renault Llp/s.e.n.c.r.l.,s.r.l.
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