A gas turbine engine (1) has a burner chamber (4) with a number of fuel (B) and air (V) burner units (10). Some of the fuel is supplied to the burner through a ring pipe (24) which is discharged into the burner chamber in opposition to the direction taken ...

A combustor (40) for a gas turbine engine is provided with a premix pilot fuel stage (42) in order to reduce the emission of oxides of nitrogen from the engine. An in-service engine may be modified to add the premix pilot fuel stage by delivering premix pi...