초록 ▼

A method for distributing a flow of fuel over the gas flow area of a gas turbine engine includes the steps of dividing the gas flow area into a plurality of sector shaped sub-areas (48), (50), (52), (54) disposed within a surrounding, annular sub-area (46) which is in turn disposed adjacent the augm

A method for distributing a flow of fuel over the gas flow area of a gas turbine engine includes the steps of dividing the gas flow area into a plurality of sector shaped sub-areas (48), (50), (52), (54) disposed within a surrounding, annular sub-area (46) which is in turn disposed adjacent the augmentor wall (12). During operation, the method according to the present invention distributes the fuel over one or more of the sub-areas (46-54) in response to the current rate of fuel flow. At the lowest and intermediate fuel flow rates, fuel is distributed only over one or more of the sector shaped sub-areas (48-54). Only at the very highest rates of augmentor fuel flow is fuel distributed finally in the outer annular sub-area (46).

대표청구항 ▼

A method for distributing a flow of fuel over a circular flow area in a gas turbine engine augmentor, the flow of fuel having a current flow rate variable over a range of flow rates, comprising the steps of: dividing the augmentor flow area into a plurality of sub-areas, one sub-area being annular i

A method for distributing a flow of fuel over a circular flow area in a gas turbine engine augmentor, the flow of fuel having a current flow rate variable over a range of flow rates, comprising the steps of: dividing the augmentor flow area into a plurality of sub-areas, one sub-area being annular in shape and disposed adjacent the augmentor interior surface, and the other sub-areas being sectors of the circular area remaining within the one annular sub-area; dividing the range of flow rates into a series of sub-ranges, the series comprising a pilot sub-range including the initial and lowest augmentor fuel flow rates, a full thrust sub-range including the highest and maximum augmentor fuel flow rates, and one or more intermediate sub-ranges including all augmentor fuel flow rates between the pilot and full thrust sub-ranges; allocating one or more sub-areas to each fuel flow rate sub-range, the sector sub-areas being sub-ranges, and the annular sub-area being allocated to only the full thrust sub-range; and distributing the flow of fuel to those sub-areas allocated to sub-ranges corresponding to fuel flow rates up to and including the current rate of fuel flow.