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LIQUID FUEL COMBUSTOR HAVING AN OXYGEN-DEPLETED GAS (ODG) INJECTION SYSTEM FOR A GAS TURBOMACHINE
LIQUID FUEL COMBUSTOR HAVING AN OXYGEN-DEPLETED GAS (ODG) INJECTION SYSTEM FOR A GAS TURBOMACHINE
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机译:具有用于燃气轮机的贫氧(ODG)喷射系统的液体燃料燃烧器
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摘要
A liquid fuel combustor for a gas turbomachine includes a combustor body, a combustor liner arranged in the combustor body defining a combustion chamber extending from a head end to a combustor discharge. The combustor liner is spaced from the combustor body forming a compressor discharge casing (CDC) airflow passage. A nozzle is arranged at the head end of the combustor liner. The nozzle includes a first inlet, a second inlet and an outlet configured and disposed to establish a flame zone. The first inlet is configured to receive a first fluid and the second inlet is configured to receive a second fluid. The second fluid includes a liquid fuel. An oxygen-depleted gas (ODG) injection system is arranged radially outwardly of the nozzle. The ODG injection system is configured and disposed to deliver an oxygen-depleted gas stream into the combustion chamber to vaporize a portion of the second fluid.
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