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公开(公告)号:US11054135B2
公开(公告)日:2021-07-06
申请号:US15576036
申请日:2016-05-23
摘要: A gas turbine fuel nozzle for a combustor of a gas turbine engine comprises a sleeve with an internal duct for premixed fuel gas flow; it further comprises a flame ionization sensor located on the sleeve externally to the duct; typically, the combustor has a single annular-shaped chamber.