Importance

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Abstract

A control method for a gas turbine combustor including an air-hole plate having a plurality of air holes formed therein, and a plurality of fuel nozzles corresponding to respective ones of the plurality of air holes. The gas turbine combustor is operable to combust a hydrogen fuel and a fuel other than the hydrogen fuel. The air holes include: first air holes having, among passageways from an entry end to an exit end, an inclined passageway extending in a direction inclined with respect to the central axis of the air-hole plate in a region including at least the exit end; and second air holes extending in parallel to the central axis. The fuel nozzles include first fuel nozzles corresponding to respective first air holes, and second fuel nozzles corresponding to respective second air holes. During hydrogen fuel firing, the hydrogen fuel is not supplied to the first fuel nozzles.

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First Claim