COMBUSTOR AND COMBUSTION NOZZLE THEREOF FOR HYDROGEN GAS TURBINE
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United States of America Patent
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Issued Date -
Jul 18, 2024
app pub date -
Nov 7, 2023
filing date -
Jan 18, 2023
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Abstract
A combustion nozzle injects compressed air and fuel for combustion into a combustion chamber of a combustor for a gas turbine. The combustion nozzle includes a first air injection hole through which a first air flow of the compressed air is injected into the combustion chamber, a second air injection hole through which a second air flow of the compressed air is injected adjacent to the first air flow into the combustion chamber, and a fuel injection hole through which a fuel flow of the fuel is injected into the combustion chamber at a flow velocity different from a flow velocity of the first air flow and a flow velocity of the second air flow in a state where the fuel flow is sandwiched between the first air flow and the second air flow. The fuel injection hole has an inner diameter smaller than a quenching distance of the fuel.
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