| 摘要 |
PROBLEM TO BE SOLVED: To provide a gas turbine combustor and its fuel supply method capable of preventing backfire, while reducing an NOx generation quantity. SOLUTION: This combustor 2 for mixing a fuel with combustion air introduced from a compressor 1 and burning it, and supplying generated combustion gas to a gas turbine 3 is equipped with a liquid fuel nozzle 13 for blowing out the fuel; a mixing chamber wall 5 equipped with the liquid fuel nozzle 13 in the center, having a hollow circular-cone shape enlarged toward the blowout direction, and forming a mixing chamber 4 inside; a plurality of air introduction holes 14, 15, 16 bored on the mixing chamber wall 5 so that the combustion air is introduced into the mixing chamber 4, and that simultaneously its introduction angle is deflected at least toward the circumferential direction of the mixing chamber wall 5; and each gas fuel nozzle 17 provided respectively oppositely to the plurality of air introduction holes 14, 15, 16 on the peripheral side of the mixing chamber wall 5, for blowing out the fuel approximately in the same axial direction as axial lines L1, L2, L3 of the air introduction holes 14, 15, 16. COPYRIGHT: (C)2007,JPO&INPIT
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