A premixer injector assembly in a gas turbine engine includes at least one premixer injector. The premixer injector includes a fuel tube having a fuel feed passage enclosed by an outer surface, a plurality of fins coupled to the fuel tube extending from the outer surface of the fuel feed passage, the outer surface of the fuel feed passage between adjacent fins having a concave shape, a plurality of mixing channels defined between adjacent fins, a plurality of fuel injection apertures disposed along the fuel feed passage to direct fuel from the fuel feed passage to the mixing channels, an air tube coupled to the fuel tube to at least partially enclose the fuel tube, and a plurality of air injection openings arranged along the air tube to inject air to the mixing channels.

A fuel injector has a body extending in an axial direction. The body includes: an axial passage formed so as to extend in the axial direction; a radial passage formed so as to communicate at one end with the axial passage and to open at another end to an outer surface of the body; and an internal passage including a first opening and a second opening open to the outer surface, and formed so as to extend inside the body from the first opening to the second opening. The first opening and the second opening are located opposite to each other across a third opening, through which the radial passage opens to the outer surface, in a circumferential direction centered on an axis of the body.

Disclosed is a fuel mixed injection method for a gas turbine. The method includes the following steps: arranging a secondary fuel injection nozzle and a secondary air injection nozzle on a secondary combustion section, wherein the secondary fuel injection nozzles is closer to a main combustion section than the secondary air injection nozzle; and injecting secondary fuel and secondary primary air in sequence through the secondary fuel injection nozzle and the secondary air injection nozzle, respectively, thus enabling the secondary fuel to spontaneously combust in a mainstream high-temperature flue gas atmosphere to form a transverse jet flame and increase the flame lift-off height.

A turbine engine can include a compressor section, a combustion section, and a turbine section in serial flow arrangement. A combustor in the combustion section can include a combustion chamber, a fuel supply fluidly coupled to the combustion chamber, and a fuel nozzle assembly. The fuel nozzle assembly can include an air flow passage and a fuel flow passage.

A combustor nozzle, a combustor, and a gas turbine including the same are proposed. The combustor nozzle includes a nozzle module. The nozzle module includes a fuel supply pipe supplying fuel from the front side to the rear side, a fuel plenum having an internal fuel flow path through which the fuel flows and communicating with the fuel supply pipe, an air inlet formed in front of the fuel plenum, a plurality of tubes disposed through a rear side of the fuel plenum, wherein a front end of each tube communicates with the air inlet, and a fuel port communicating with the fuel flow path is formed on a lateral side of each tube, and a swirler provided with a plurality of swirling guides disposed obliquely in axial and circumferential directions on an inner circumferential surface of each of the plurality of tubes to swirl fluid, with a central portion thereof opened when viewed from the axial direction of the tube.

A combustor nozzle, a combustor, and a gas turbine including the same are provided. The combustor nozzle includes a nozzle module. The nozzle module includes a central tube having an air flow path, through which air flows from a front-to-rear direction, and an opening hole at a rear end thereof, a shroud into which at least a part of the central tube is inserted, and having an air inlet at a front end thereof, wherein a mixing flow path is formed between the shroud and the central tube so that the air and injected fuel flow therethrough, and a plurality of cooling channels, each of the plurality of cooling channels extending rearward from an inlet communicating with the air flow path to an outlet communicating with the mixing flow path while passing through a sidewall portion of the central tube.

Fuel nozzle assemblies are provided. For example, a fuel nozzle assembly for a combustor system comprises a fuel nozzle having a pilot swirler and an outlet defined in an outlet end, as well as a main mixer attached to the outlet end and extending about the outlet. A total combustor airflow through the combustor system comprises a pilot swirler airflow that is greater than about 14% and a main mixer airflow that is less than about 50% of the total combustor airflow. In further embodiments, the fuel nozzle also comprises main and pilot fuel injectors that each are configured to receive a portion of a fuel flow to the fuel nozzle. The fuel nozzle provides less than about 80% of the fuel flow to the main fuel injector at a high power operating condition of a gas turbine engine in which the fuel nozzle assembly is installed.

A swirler assembly for use in a combustor includes a first air swirler having a first swirler vane assembly, a second air swirler adjacent the first air swirler and having a second swirler vane assembly, and a ferrule coupled to the first air swirler and the second air swirler. The ferrule includes a ferrule swirler having a plurality of vanes. The first swirler vane assembly is configured to generate a first radial rotating airflow, and the second swirler vane assembly is configured to generate a second radial rotating airflow. The plurality of vanes of the ferrule swirler are configured to generate a ferrule axial airflow to interact with and mix to with the first radial rotating airflow and the second radial rotating airflow.

A burner arrangement has a plurality of mixing channels which extend parallel to the main axis of the burner arrangement and are arranged in at least two concentric circles, in which mixing channels fuel and discharge air from the compressor are mixed during the operation of the burner arrangement. The mixing channels are grouped together into fuel stages so as to produce an irregular staging in the peripheral direction of the burner arrangement.

A gas turbine combustor includes a burner composed of a fuel nozzle group having a plurality of fuel nozzles for fuel supply, a fuel nozzle plate structurally supporting the fuel nozzles and serving to distribute the fuel flowing from an upstream side to the fuel nozzles, and a perforated plate located downstream of the fuel nozzles and having nozzle holes corresponding to the fuel nozzles. The fuel nozzle group includes outer circumferential fuel nozzles and inner circumferential fuel nozzles. Each outer diameter of at least a proximal end of the outer circumferential fuel nozzles is larger than that of the inner circumferential fuel nozzles.