A hot gas segment arrangement (20), especially for a combustion chamber of a gas turbine, comprises at least one hot gas segment (22), which is removably mounted on a carrier (21), and is subjected at its outside to hot gas and impingement-cooled at its in...

The disclosure relates combustor transition (24) adapted to guide combustion gases in a hot gas flow path (15) extending between a can combustor (2) and a first stage of turbine (3) in a gas turbine (9). The combustor transition (24) comprises a duct havin...

The disclosure relates combustor transition (24) adapted to guide combustion gases in a hot gas flow path (15) extending between a can combustor (2) and a first stage of turbine (3) in a gas turbine (9). The combustor transition (24) comprises a duct havin...

System and method for controlling a stuck nozzle system installed between first and second turbines connected in series to a compressor. The method includes determining whether the nozzle system is stuck; instructing the first turbine to increase a minimum...

The element has a supporting structure radially extended between inner and outer walls of a bypass duct and including a front edge part (7) and a rear edge part (8). A connecting rod (9) connects the front and rear edge parts to form a recess that extends ...