A fuel nozzle assembly and a gas turbine having the fuel nozzle assembly includes a fuel nozzle guide disposed in a compressed air channel formed between a body and a housing of a gas turbine and includes a nozzle body disposed in the housing, a shroud mounted on an outer side of the nozzle body, and two or more flow guides arranged at predetermined distances from each other between the shroud and the outer side of the nozzle body and formed to correspond to the shape of an end of the shroud and the shape of the outer surface of the nozzle body.

The present invention relates to an axial swirler, in particular for premixing of oxidizer and fuel in gas turbines. The axial swirler for a gas turbine burner includes a plurality of swirl vanes with a streamline cross-section being arranged around a swirler axis and extending in radial direction between an inner radius R.sub.min and an outer radius R.sub.max. Each swirl vane has a leading edge, a trailing edge, and a suction side and a pressure side extending each between the leading and trailing edges. A discharge flow angle between a tangent to the swirl vane camber line at its trailing edge and the swirler axis is first function of radial distance R from the swirler axis. A position of maximum camber of the swirl vane is second function of radial distance R from the swirler axis. At least one swirl vane of the first and second functions include each a respective local maximum and local minimum values along said radial distance from R.sub.min to R.sub.max. The invention also relates to a burner with such a swirler.

The present invention discloses a novel apparatus and way for reducing the recirculation zone at the inlet end of a combustor. The recirculation zone is reduced by altering the geometry of the inlet end through a tapering of the liner wall thickness and a tapering of the thermal barrier coating to reduce the bluff body effect at the combustion liner inlet end.

A premixed dual fuel burner includes a burner head, a burner interior elongated along a main axis and having an upstream side enclosed by a swirler and a downstream side enclosed by a premixing section, and an injection component. The burner head and sides are serially arranged. The swirler includes an inlet section for introducing air and a main gas fuel. The injection component has a tapering structure positioned along the main axis which extends from the burner head into the burner interior. The injection component tapers from a burner head side and an injection side along the main axis. At the injection side a liquid fuel outlet introduces a main liquid fuel into the burner interior. The injection side is disposed in the burner interior. At least one of the at least one liquid fuel outlet is at a side of the injection side of the injection component.

A burner having an air supply and a premix channel having an essentially annular cross-section, through which air and fuel flow during operation, and which is formed of an outer shell (5) and a hub (6). A plurality of swirl blades (7) arranged in the burner extend from the hub (6) to the outer shell (7) in a radial direction. Each blade's surface (11) is provided with a deflection in a radial outer region of the swirl blade (7), a downstream flow angle () to a main flow direction (13) increases at least once and decreases at least once in a radial direction at an outflow end (12) of the deflection surface (11).

An injector device is disclosed which includes an elongated body with a leading edge and a trailing edge, gas nozzles and oil nozzles, an oil supply duct housed within the elongated body and connected to the oil nozzles, and a gas supply duct housed within the elongated body and connected to the gas nozzles. The oil supply duct is connected to the gas supply duct only between one or more oil nozzles and one gas nozzles, and the gas supply duct is connected to the elongated body only via bridges.

A swirler for use in a combustor of a gas turbine engine, having a plurality of generally radially inwardly extending passages arranged circumferentially staggered in a circle, each passage having a radially outer inlet end, a radially inner outlet end, first and second generally radially inwardly extending lateral surfaces, and a base surface and top surface, in use of the swirler fuel and air travelling along the passages from their inlet ends to their outlet ends so as to create adjacent to the outlet ends a swirling fuel/air mixture. At least one surface of at least one passage has at least one gas fuel injection hole, wherein the surface, having the gas fuel injection hole, has at least one counterbore radially surrounding the gas fuel injection hole, wherein the gas fuel injection hole is arranged at a base of the counterbore.

An injector for a combustor of a gas turbine engine is provided with a plurality of first vanes radially arrayed about a central axis of the injector and a plurality of second vanes radially arrayed about the central axis of the injector and disposed radially inward of the plurality of first vanes. A plurality of fuel injection holes are disposed nearer to a trailing edge than to a leading edge of the second vanes for injecting fuel into compressed air passing through over the second vanes. The trailing edge of each of the second vanes includes a non-planar profile configured to induce turbulence in the compressed air to thereby mix the fuel with the compressed air and reduce the surfaces on which undesirable flame anchoring may occur.

A method for premixing air with a gaseous fuel for being burned in a combustion chamber includes: guiding the air in an air stream along a burner axis through a coaxial air tube into a combustion chamber arranged at an end of said air tube; and impressing a swirl on the air stream by passing it through a first swirl device concentrically arranged within the air tube and comprising a plurality of radially oriented first blades. The method further includes: injecting gaseous fuel into the air stream at the first swirl device; and mixing said air in said air stream with the injected gaseous fuel in a first mixing zone arranged just after said first swirl device.

The present invention discloses a novel apparatus and way for controlling a velocity of a fuel-air mixture entering a gas turbine combustion system. The apparatus comprises a hemispherical dome assembly which directs a fuel-air mixture along a portion of the outer wall of a combustion liner and turns the fuel-air mixture to enter the combustion liner in a manner coaxial to the combustor axis and radially outward of a pilot fuel nozzle so as to regulate the velocity of the fuel-air mixture.