초록 ▼

Improvement to the starting characteristics of an annular combustor for a gas turbine engine that employs dual fuel nozzles (primary and secondary fuel flow systems) by redistributing the total fuel admitted to the nozzles in an asymmetrical pattern to deliver the requisite amount of fuel to the ign

Improvement to the starting characteristics of an annular combustor for a gas turbine engine that employs dual fuel nozzles (primary and secondary fuel flow systems) by redistributing the total fuel admitted to the nozzles in an asymmetrical pattern to deliver the requisite amount of fuel to the igniter by the primary flow system feeding fuel to that igniter.

대표청구항 ▼

1. The method of starting a gas turbine engine of the type that includes an annular combustor that receives a predetermined total amount of fuel during said starting condition, a plurality of dual fuel nozzles symmetrically disposed about the circumference of the annular combustor, and an igniter ad

1. The method of starting a gas turbine engine of the type that includes an annular combustor that receives a predetermined total amount of fuel during said starting condition, a plurality of dual fuel nozzles symmetrically disposed about the circumference of the annular combustor, and an igniter adjacent to at least one of said dual fuel nozzles, and each dual fuel nozzle includes a primary fuel system and a secondary fuel system being supplied a given amount of fuel, including the steps of: calculating the amount of fuel to be supplied to the igniter fuel nozzle from data established from said gas turbine engine to achieve starting, and the amount of fuel to be supplied to the remaining dual fuel nozzles, redistributing said given amount of fuel for said starting condition to all of the primary fuel systems of all of said duel fuel nozzles to provide the amount of fuel ascertained from the above previous step, so that the calculated amount of fuel to the igniter fuel nozzle is greater than the calculated amount delivered to each of the adjacent dual fuel nozzles, and initiating starting of the gas turbine engine with the preascertained amount of fuel. 2. The method as in claim 1 including the step of flowing the fuel to each of the primary fuel nozzles not associated with the igniter through a fixed restrictor.