A gas turbine engine and a combustor are described herein. The combustor includes a fuel vaporizer coupled to a combustor wall, which extends into a combustion chamber. A fuel injector having a nozzle extends within a portion of the fuel vaporizer. A dome swirler is coupled to an upstream dome portion of the combustor wall. The swirler surrounds a heat shield, which may have a concaved body. The outlet end of the fuel vaporizer is disposed over the heat shield, which may be over the central zone of the heat shield, to face the heat shield. The fuel vaporizer may be coupled to the combustor wall and disposed outside the swirler. Fuel and air mixture exits the vaporizer and impinges against the heat shield and is then combined with the swirler air to become part of the primary zone recirculation.

A fuel-fired burner includes a combustion air inlet for receiving combustion air coupled to a combustion air nozzle at an input to a second chamber within a burner housing spaced apart from a third chamber within the second chamber. The combustion air nozzle directs the combustion air into the third chamber. A fuel inlet coupled to a burner nozzle secured to a burner mounting plate has a recycle port for receiving hot exhaust gas provided to an exhaust gas path. A jet pump located entirely inside the burner housing is configured to receive the hot exhaust gas from the exhaust gas path. The jet pump operates by flowing the combustion air through the combustion air nozzle which suctions in the hot exhaust gas through the recycle port into the exhaust gas path then into a gas mixing zone for mixing the hot exhaust gas and the combustion air.

A combustion system includes a fuel distributor configured to output a fuel, an oxidant source configured to output an oxidant, and a mixing tube defining a mixing volume aligned to receive the fuel and oxidant. The mixing tube is shaped to convey the fuel and the oxidant through the mixing volume at a bulk velocity higher than a flame propagation speed. The combustion system includes a flame holder aligned to receive the mixed fuel and oxidant and to support a combustion reaction of the fuel and the oxidant.

A gas turbine combustor assembly includes a primary combustion chamber in fluid communication with a primary fuel injector and a primary air inlet. A torch igniter is carried by the primary combustion chamber, and includes an auxiliary combustion chamber housing comprising a mixing chamber and a throat region converging downstream of the mixing chamber. An air swirler including a plurality of swirl openings surrounding an outlet of an auxiliary fuel injector is coupled to the auxiliary combustion chamber proximate the mixing chamber. An ignition source projects into the mixing chamber of the auxiliary combustion chamber.

A combustion system includes a fuel distributor configured to output a fuel, an oxidant source configured to output an oxidant, and a mixing tube defining a mixing volume aligned to receive the fuel and oxidant. The mixing tube is shaped to convey the fuel and the oxidant through the mixing volume at a bulk velocity higher than a flame propagation speed. The combustion system includes a flame holder aligned to receive the mixed fuel and oxidant and to support a combustion reaction of the fuel and the oxidant.

A method is provided for operating a gas turbine installation which has at least one compressor for compressing combustion air, at least one combustion chamber for combusting a supplied fuel, using the compressed combustion air, and also at least one turbine which is exposed to throughflow by the hot gases from the at least one combustion chamber. Both a first fuel on a carbon base, especially in the form of natural gas, and also a second fuel, in the form of a hydrogen-rich fuel or pure hydrogen, are used as fuel. A reduction of the CO.sub.2 emission without basic modifications to the installation is achieved by the first and the second fuels being intermixed and combusted together in the at least one combustion chamber.

The invention relates to a fuel injector for injecting an over-enriched fuel and air mixture to the combustion chamber of an internal combustion engine, is characterised in that it comprises: a hydrocarbon liquid fuel spray nozzle, at least one supply of a gaseous carrier, a fuel mixing and evaporation chamber and an injector nozzle to the engine combustion chamber (C.C.), configured such that, during operation, liquid fuel is supplied and heated and compressed gaseous carrier are supplied to the fuel mixing and evaporation chamber of this injector through the spray nozzle, where they are mixed and evaporated as a result of elevated temperature, and the mixture of evaporated fuel with a hot gaseous carrier with low oxygen content thus formed reaches the combustion chamber (C.C.), through the outlet, wherein the gaseous carrier is air or, alternatively, flue gas, at elevated pressure and temperature and having a composition that prevents the initiation of flame combustion, and the gaseous carrier has oxygen content low enough to prevent the initiation of combustion, even under conditions of elevated pressure and temperature.

A multistaged lean prevaporizing premixing fuel injector apparatus is provided. The fuel injector may be utilized with a turbogenerator. Preheated combustion air from the turbogenerator's recuperator may be utilized by the fuel injector to prevaporize liquid fuel. The injector may provide for premixing of multiple fuel streams and include multiple stages with a flow distributor plate separating adjacent stages. The injector may include multiple stages, with a pilot tube located in a final stage splitting the fuel stream into a premixed pilot stream and a premixed final fuel and air mixture stream.

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 mixer for separate streams of gas includes a center stream of a first gas and a co-axial stream of a second gas injected at an angle to the center stream and filling an annulus around the center stream. The mixer may further include a feed zone wherein the first gas is introduced into the mixer as the center stream and the second gas is introduced into the mixer as the co-axial stream filling the annulus around the center stream; a mixing zone wherein the first gas and the second gas mix with no recirculation zones to form a mixture; and a diffusion zone for advancing the mixture from the mixing zone. Corresponding or associated methods for mixing materials are also provided.