A fuel nozzle includes a main cylinder extending in one direction; an auxiliary cylinder surrounding the main cylinder and defining a fuel passage between the auxiliary cylinder and the main cylinder; a shroud spaced that is apart from the auxiliary cylinder and surrounds the auxiliary cylinder; a swirler vane that is disposed between the auxiliary cylinder and the shroud and defines a fuel cavity communicating with the fuel passage so that fuel flowing in the fuel passage flows into the fuel cavity; and a fuel flow guide disposed inside the fuel cavity to guide fuel that flows from the fuel passage and enters the fuel cavity and to distribute the guided fuel in the fuel cavity. A fuel aperture is formed in the swirler vane to communicate with the fuel passage and the fuel cavity so that the fuel flows into the fuel cavity via the fuel aperture.

A flare burner for burning combustible waste gases with a manifold, at least two arms, and a plurality of outlets disposed on the plurality of arms. The arms may be perpendicular to the manifold. The arms may also extend outwardly from the manifold. The arms may extend into annuli, to produce oppositely flowing exit gas. A curved dispersing surface may be disposed above the manifold. The arms may comprise a curvilinear shape, or include both a linear and a curvilinear portion. The arms are unequal in length and may curve in an opposite direction from each other. The outlets are configured and spaced such that flame is short relative to size of the flare burner.

A flame stabilization apparatus with fuel injection upstream of a torpedo, includes a flame stabilization plate that incorporates spokes that stabilize a flame over a range of operations of a burner. The spokes surrounds a fuel plenum with respect to the burner. A first group of fuel ports can be located in a fuel tube upstream of the torpedo and a second group of fuel ports can be located in the flame stabilization plate. A discharge cone includes a discharge zone for the burner, wherein the flame with respect to the flue gas is stabilized at an end of the burner in the discharge zone.

Disclosed are a pilot fuel injector, and a fuel nozzle and a gas turbine having the same. The pilot fuel injector is mounted on the fuel nozzle to uniformize the flow of the introduced air and to enable uniform mixing with the fuel, so that a fuel mixed air having a high mixing rate is provided to the combustion chamber. The mixing rate of the fuel mixed air directed to the combustion chamber is increased, thereby suppressing the generation of nitrogen oxides and preventing the flame stagnation.

A combustor arrangement for a gas turbine includes a first burner, a first combustion chamber, a mixer for admixing a dilution gas to the gases leaving the first combustion chamber during operation, a second burner, and a second combustion chamber arranged sequentially in a fluid flow connection. These elements of the combustor arrangement are arranged in a row to form a flow path extending between the first combustion chamber and the second burner. The arrangement includes a central lance body in the flow path, extending from the first burner into the second burner, which lance body includes at least one air duct for providing air for the mixer, wherein the air is injected into the combustor through air supply elements.

A combustor arrangement for a gas turbine includes a first burner, a first combustion chamber, a mixer for admixing a dilution gas to the gases leaving the first combustion chamber during operation, a second burner, and a second combustion chamber arranged sequentially in a fluid flow connection. These elements of the combustor arrangement are arranged in a row to form a flow path extending between the first combustion chamber and the second burner. The combustor arrangement includes acentral lance body arranged inside the flow path and extending from the first burner through the first combustion chamber into the mixer and into the second burner, wherein the lance body includes a fuel duct for providing fuel for the first burner and/or for the second burner.

A gas turbine combustor includes an external cylinder, an inner cylinder disposed in the external cylinder, a first fuel injecting unit disposed in the inner cylinder, an air passage provided between the external cylinder and the inner cylinder to cause compressed air to flow into the inner cylinder, and a second fuel injecting unit disposed in the air passage. The second fuel injecting unit is disposed at a curve communicating with the inner cylinder downstream in the air passage. The second fuel injecting unit is supported by a curved inner surface of the external cylinder in the inner cylinder. The second fuel injecting unit is disposed with a center line in a longitudinal direction inclined in a flow direction of the compressed air flowing through the air passage at a predetermined angle with respect to a perpendicular orthogonal to a tangent to the curved inner surface of the external cylinder.

A combustor includes: a first cylindrical body which is configured to hold a fuel nozzle extending in an axial line direction and through which air flows toward a downstream side thereof; a second cylindrical body that is connected to a downstream side of the first cylindrical body; and an outer shell that has an inner peripheral surface configured to define an air introduction channel through which air is introduced such that the air reverses course at an upstream end of the first cylindrical body and flows toward the downstream side together with an outer peripheral surface of the first cylindrical body. The inner peripheral surface has an outside narrowing surface that is formed to extend inward in a radial direction toward the upstream end of the first cylindrical body.

A fuel nozzle including vortex generating features for use in a combustion turbine engine is provided. An array of inner pre-mixing conduits (20) extends between an inlet end (14) and an outlet end (16) of the nozzle. An array of outer pre-mixing conduits (22) may be disposed radially outwardly relative to the inner pre-mixing conduits (20). A fuel-directing tube (24) includes fuel-directing arms (26) structured to direct fuel flow into the outer pre-mixing conduits (22) to be mixed with a flow of air. The fuel-directing arms include a bluff structural arrangement (30) that may be disposed upstream of fuel injection locations (32, 32) into the outer pre-mixing conduits (22). The proposed nozzle is believed to provide superior micro-mixing capability, such as by increasing the depth of penetration of jets of fuel in a cross-flow of air, and/or formation of vortices in a wake zone downstream from the vortex generating features.

The present disclosure is directed to a dual-fuel fuel nozzle that includes a center body having a tube shape and a gas fuel plenum defined within the center body. The duel-fuel fuel nozzle also includes a ring manifold defining a liquid fuel plenum disposed within the center body. The duel-fuel fuel nozzle further includes a plurality of radially oriented fuel injectors in fluid communication with the liquid fuel plenum. Additionally, the duel-fuel fuel nozzle includes an inner fuel tube extending axially within the center body. A portion of the inner fuel tube extends helically about an axial centerline of the center body. The inner fuel tube is in fluid communication with an axially oriented fuel injector. Furthermore, the duel-fuel fuel nozzle includes first fuel tube extending helically around a portion of the inner fuel tube within the center body. The first fuel tube is fluidly coupled to the fuel plenum.