Abstract: A combustor is configured such that an outer liner defines a combustion chamber configured such that fuel and air are supplied thereto from an upstream end side, the fuel is subjected to combustion, and a combustion gas flows out to a downstream end side, an inner liner extends to be concentric with the outer liner inside the outer liner, a sub burner is defined between the outer liner and the inner liner, a main burner is defined on the downstream end side, the fuel is supplied at an equivalence ratio and is subjected to combustion in the sub burner, and the fuel and the air are supplied to the main burner through a region provided radially inward of the inner liner and are subjected to combustion while being mixed with a burnt gas.

Abstract: A combustor of a gas turbine engine includes a combustion chamber, pilot fuel supply unit configured to supply solely auxiliary fuel to a flame holding region in the combustion chamber, first auxiliary fuel amount adjustment unit configured to adjust an amount of the auxiliary fuel supplied from the pilot fuel supply unit, main fuel supply unit configured to supply unburned gas and the auxiliary fuel to an unburned gas combustion region in the combustion chamber continuous with the flame holding region, and second auxiliary fuel amount adjustment unit configured to adjust an amount of the auxiliary fuel, in which the first auxiliary fuel amount adjustment unit is configured to adjust the amount of the auxiliary fuel supplied from the pilot fuel supply unit to an amount for flame holding in the flame holding region throughout an operation of the gas turbine engine.

Abstract: A combuster (2) of a gas turbine engine (1) is fed with gaseous ammonia and that gaseous ammonia is burned to drive a turbine (3). Inside the exhaust passage of the gas turbine engine (1), an NOx selective reduction catalyst (10) is arranged. Inside one or both of the intake passage of the gas turbine engine (1) or the exhaust passage upstream of the NOx selective reduction catalyst (10), ammonia is fed. This ammonia is used to reduce the NOx which is contained in the exhaust gas at the NOx selective reduction catalyst (10).

Abstract: A combustor of a gas turbine engine is fed with liquid ammonia and that liquid ammonia is burned to drive a turbine. Inside the exhaust passage of the gas turbine engine, an NOX selective reduction catalyst is arranged. Inside the intake air which flows into the compressor, liquid ammonia is fed. This liquid ammonia is used to cool the intake air. The NOX which is contained in the exhaust gas is reduced by the unburned ammonia which is exhausted into the exhaust passage by the NOX selective reduction catalyst.

Abstract: A combuster (2) of a gas turbine engine (1) is fed with gaseous ammonia and that gaseous ammonia is burned to drive a turbine (3). Inside the exhaust passage of the gas turbine engine (1), an NOx selective reduction catalyst (10) is arranged. Inside one or both of the intake passage of the gas turbine engine (1) or the exhaust passage upstream of the NOx selective reduction catalyst (10), ammonia is fed. This ammonia is used to reduce the NOx which is contained in the exhaust gas at the NOx selective reduction catalyst (10).

Abstract: A combuster (2) of a gas turbine engine (1) is fed with liquid ammonia and that liquid ammonia is burned to drive a turbine (3). Inside the exhaust passage of the gas turbine engine (1), an NOX selective reduction catalyst (9) is arranged. Inside the intake air which flows into the compressor (4), liquid ammonia is fed. This liquid ammonia is used to cool the intake air. The NOX which is contained in the exhaust gas is reduced by the unburned ammonia which is exhausted into the exhaust passage by the NOX selective reduction catalyst (9).