A pilot pre-mixer for a gas turbine engine has a pilot body that includes an internal mixing chamber, a first end on an upstream side of the internal mixing chamber, a second end on a downstream side of the internal mixing chamber, a fuel injector at the first end and communicable with the internal mixing chamber, a plurality of first oxidizer inlet ports arranged to provide an oxidizer agent from outside of the pilot body to the internal mixing chamber, and a plurality of pilot outlet ports at the second end and communicable with the internal mixing chamber, each of the plurality of pilot outlet ports having an outlet on the second end for dispensing a pilot fluid mixture into a combustion zone of a combustor.

A gas cavity burner, wherein the present invention discloses a burner applied to ovens, more specifically, the present invention discloses a tubular burner composed by two half-shells disposed superposed conforming an inner mixture and diffusion chamber the receives a comburent and a combustible in order to generate a pilot and primary flames, said two half-shells comprising substantially symmetrical perimetral surfaces wherein one said shell comprises a corrugated perimeter surface while the other comprises a flat perimeter surface, the burner of the present invention also presenting a spacer between both half-shells, in that said spacer reduces deformation issues caused by the heating, while it also brings more control to the pilot flame and aggregates a reduction of material thickness in the manufacturing of the burner.

A gas cavity burner, wherein the present invention discloses a burner applied to ovens, more specifically, the present invention discloses a tubular burner composed by two half-shells disposed superposed conforming an inner mixture and diffusion chamber the receives a comburent and a combustible in order to generate a pilot and primary flames, said two half-shells comprising substantially symmetrical perimetral surfaces wherein one said shell comprises a corrugated perimeter surface while the other comprises a flat perimeter surface, the burner of the present invention also presenting a spacer between both half-shells, in that said spacer reduces deformation issues caused by the heating, while it also brings more control to the pilot flame and aggregates a reduction of material thickness in the manufacturing of the burner.

A combustion system includes a fuel and oxidant source and a flame holder. The flame holder includes a plurality of discrete slats arranged in parallel defining combustion channels between adjacent slats. Pairs of adjacent slats may be oriented to operate substantially as a V-gutter. The fuel and oxidant source outputs fuel and oxidant into the combustion channels. The flame holder holds a combustion reaction of the fuel and oxidant in the combustion channels.

A combustion system includes a fuel and oxidant source and a flame holder. The flame holder includes a plurality of discrete slats arranged in parallel defining combustion channels between adjacent slats. Pairs of adjacent slats may be oriented to operate substantially as a V-gutter. The fuel and oxidant source outputs fuel and oxidant into the combustion channels. The flame holder holds a combustion reaction of the fuel and oxidant in the combustion channels.

Provided is a surface combustion burner which solves the passage blocking in a combustion part caused by dust, and enables stable combustion for a long term. The surface combustion burner comprises: a nozzle configured to discharge fuel gas and air for combustion; and a laminate, provided on a tip of the nozzle, in which a plurality of mesh plates is laminated, wherein the laminate includes a portion having an offset arrangement between at least any adjacent ones of the mesh plates.

A supercritical hydrothermal combustion device comprises a main enclosure and a top cap. A partition is mounted in the main enclosure and divides the interior of the main enclosure into a main combustion space and a mixing space. The top cap is provided with a primary fuel inlet, an oxidant inlet and a secondary fuel inlet. A high-temperature ignition bar sleeve, having a high-temperature ignition bar arranged therein, is disposed in the top cap. A combustion sleeve, having a stable combustion space formed therein, is mounted at a bottom of the top cap, and has a top communicated with the high-temperature ignition bar sleeve and the oxidant inlet, as well as a bottom communicated with the main combustion space. The secondary fuel inlet and a secondary oxidant inlet are communicated with the main combustion space. Supercritical hydrothermal combustion is realized to generate a hybrid thermal fluid or treat organic wastes.

A supercritical hydrothermal combustion device comprises a main enclosure and a top cap. A partition is mounted in the main enclosure and divides the interior of the main enclosure into a main combustion space and a mixing space. The top cap is provided with a primary fuel inlet, an oxidant inlet and a secondary fuel inlet. A high-temperature ignition bar sleeve, having a high-temperature ignition bar arranged therein, is disposed in the top cap. A combustion sleeve, having a stable combustion space formed therein, is mounted at a bottom of the top cap, and has a top communicated with the high-temperature ignition bar sleeve and the oxidant inlet, as well as a bottom communicated with the main combustion space. The secondary fuel inlet and a secondary oxidant inlet are communicated with the main combustion space. Supercritical hydrothermal combustion is realized to generate a hybrid thermal fluid or treat organic wastes.

Known micromixers for fuel injection (e.g., in a gas turbine engine) experience early burning or have limited operability. Accordingly, a micromixer is disclosed that utilizes an air nozzle, in combination with one or more fuel jets, to produce short flames that minimize the emission of nitrogen oxides, while providing additional benefits, such as mechanical robustness, aerodynamic efficiency, resistance to flame damage, suitability for additive manufacturing, wider operating ranges, operation with a variety of gaseous fuels, and/or amenability to control using conventional mechanisms.

Known micromixers for fuel injection (e.g., in a gas turbine engine) experience early burning or have limited operability. Accordingly, a micromixer is disclosed that utilizes an air nozzle, in combination with one or more fuel jets, to produce short flames that minimize the emission of nitrogen oxides, while providing additional benefits, such as mechanical robustness, aerodynamic efficiency, resistance to flame damage, suitability for additive manufacturing, wider operating ranges, operation with a variety of gaseous fuels, and/or amenability to control using conventional mechanisms.