Gas turbine engine

A method for determining clocking positions for a combustor and turbine of a gas turbine engine, the method comprising the steps of:

• (a) providing, in axial flow sequence, a compressor assembly, a combustor assembly, a turbine assembly, and an exhaust assembly;
• (b) arranging the combustor assembly to comprise a first circumferential array of NBURN burner assemblies;
• (c) arranging the turbine assembly to comprise, in axial flow sequence, a second circumferential array of NNGV nozzle guide vanes, a turbine assembly, a third circumferential array of NOGV outlet guide vanes, and a fourth circumferential array of temperature measurement rakes, each temperature measurement rake comprising a plurality of temperature measurement sensors;
• (d) defining a clocking position as a relative circumferential orientation of the first circumferential array with the fourth circumferential array, in which a one temperature measurement rake in the fourth circumferential array, is aligned directly with a one burner in the first circumferential array, and
• (e) positioning the quantity of burner assemblies (NBURN) in the first circumferential array, and the respective quantity of temperature measurement rakes in the fourth circumferential array, such that there is a minimum quantity of five (5) clocking positions between the fourth circumferential array, and the first circumferential array.