The gas turbine, especially an aviation jet engine (10), has at least one ancillary unit (14) fastened to it and receiving signals from at least one sub-unit of the gas turbine. The ancillary unit has a base element (21) and a housing element (22), with th...

A fuel ratio control method and a device therefor in a gas turbine combustor are provided in which supply ratio of pilot fuel to main fuel is appropriately maintained to thereby avoid unstable combustion, such as combustion vibration or misfire, and to rea...

A method of detecting an amount of a contaminant in an enclosure, the method comprising: detecting (S7) a first amplitude of energy within a first wavelength band of a first width centered about an emission wavelength of the contaminant, the method charact...

A fuel control system for a gas turbine engine includes logic that is used to facilitate enhanced compressor stall margin when the engine is operating in potential icing conditions is described. The fuel control system is coupled to at least one fuel regul...