A fuel spray nozzle provided with: a liquid fuel channel (15), which is a channel for liquid fuel; a liquid fuel injection hole (19), which is a hole for communicating the liquid fuel channel (15) and the inside of a combustion burner, and injecting the liquid fuel into the combustion burner; an additive channel (14), which is a channel for an additive; and an additive injection hole (18a), which is a hole for communicating the additive channel (14) and the inside of the combustion burner, and injecting the additive into the combustion burner at an angle at which the additive collides with the liquid fuel injected from the liquid fuel injection hole (19).

The invention relates to a central burner for multi-fuel multiple lance burner systems having a central lance with an inner pipe and an outer pipe. The inner pipe and the outer pipe form an annular clearance duct. A plurality of outer lances are arranged around the central lance. A funnel-like mixing device is provided in the extension of the annular clearance duct in the region of the end of the inner pipe. This funnel-like mixing device has openings in its wall for combustion media to flow through. The outer lances each have a nozzle which has openings along the lateral circumferential area, said openings being arranged asymmetrically.

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 combustion chamber assembly of a gas turbine, for combusting a fuel in the presence of combustion air, is configured as a dual-fuel combustion chamber assembly. In a gas fuel operating mode a mixture of a gaseous fuel and combustion air is supplied to the combustion chamber via a swirl body. In a liquid fuel operating mode liquid fuel is fed to the combustion chamber via a fuel lance and combustion air is fed to the combustion chamber via the swirl body. The fuel lance is surrounded by an adjoining lance cap to form a radial clearance therebetween such that the combustion chamber is feedable with combustion air via the radial clearance, bypassing the swirl body.

A burner assembly of a gas turbine comprising: a tubular body defining the flow path for the hot gas of the combustion during the turbine operation; an aperture for a fuel lance; a wearing ring of a sacrificial material configured to correspond to the edge of the aperture; a contacting leg extending from the wearing ring on the tubular body; a pre-tension system configured to contact the contacting leg in order to provide a pre-tension force on the ring.

A burner includes an oxidant feed passage, a fuel feed passage surrounding the oxidant feed passage, an air feed surrounding the fuel feed passage, a movable air flow diverter and, optionally, a flame nozzle. The movable air flow diverter and/or flame nozzle are independently configured to create one or a plurality of gas recirculation regions adjacent the downstream tip of the burner to improve the mixing and reaction of the fuel and oxidant, and overall combustion process efficiency. A related furnace and method for generating a stable flame with the burner are also provided.

A method of generating a flame from combustion of a fuel, includes moving an oxidant feed through an oxidant feed passage; moving a fuel feed through a fuel feed passage surrounding the oxidant feed passage; moving an air feed containing oxidant within an air feed region surrounding the fuel feed passage along the fuel feed passage; creating a gas recirculation region immediately downstream from the air feed and the fuel feed passage; diverting the air feed for proportioning the air feed around the fuel feed passage for controlling flame stabilization in the gas recirculation region; and igniting a resulting gas mixture.