| 摘要 |
PROBLEM TO BE SOLVED: To provide a gas turbine combustor having a reverse flow injection mechanism. SOLUTION: According to a specific embodiment, this system includes the reverse flow injection mechanism. The reverse flow injection mechanism includes fuel-air injection mechanisms 50, 150 having fuel and air passages to fuel and air injection openings 70, 72, 156, 157, 210, 211, and the fuel and air injection openings 70, 72, 156, 157, 210, 211 are disposed at off-center positions to the approximately longitudinal flow axis of a gas turbine combustor 30 approximately in the reverse flow direction. COPYRIGHT: (C)2008,JPO&INPIT
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