Patent ID: 9133771
Filing Date: 2015-09-15
Classification: F02C,F23K,F23N,F23R,Y02T

Abstract:
1. A fuel supply device of a gas turbine engine, which supplies fuel to a combustor including a fuel injection unit including a pilot burner and a main burner; the fuel supply device comprising: a pilot fuel passage through which the fuel is supplied to the pilot burner; a main fuel passage through which the fuel is supplied to the main burner; a collecting fuel passage through which the fuel is supplied to the pilot fuel passage and to the main fuel passage; and a fuel divider which divides the fuel supplied from the collecting fuel passage to feed the fuel to the pilot fuel passage and to the main fuel passage; wherein the fuel divider includes: wherein when the fuel pressure at the fuel entrance is not higher than a predetermined value, the fuel is supplied only to the pilot fuel passage; wherein when the fuel pressure at the fuel entrance is higher than the predetermined value, the fuel is supplied to the pilot fuel passage and to the main fuel passage; wherein the pilot port of the fuel divider includes a plurality of pilot ports and the main port of the fuel divider includes a plurality of main ports; and wherein the number of the pilot ports which are open decreases and the number of the main ports which are closed decreases, as the fuel pressure at the fuel entrance increases.