A low-pollution combustor and a combustion control method therefor. The low-pollution combustor includes a combustor head including a primary combustion stage and a precombustion stage, the primary combustion stage including a primary-combustion-stage channel and a primary-combustion-stage swirler disposed in the primary-combustion-stage channel. The primary combustion stage includes a pre-film plate disposed in the primary-combustion-stage channel, and the pre-film plate is radially divided into an outer-layer pre-film plate and an inner-layer pre-film plate. The positions and injection directions of fuel jet points of the primary combustion stage control fuel of the primary combustion stage to be injected into the primary-combustion-stage channel through primary-combustion-stage fuel jet orifices; and part of the fuel directly forms primary-combustion-stage direct-injection fuel spray, and the other part is hit on the pre-film plate close to an inner side of the primary-combustion-stage channel, or the two parts are respectively hit on the two layers of pre-film plates.

An apparatus is provided for a turbine engine. This turbine engine apparatus includes a monolithic body. The monolithic body includes a splash plate and a fuel nozzle. The splash plate includes a splash plate surface. The fuel nozzle includes a nozzle orifice. The fuel nozzle is configured to direct fuel out of the nozzle orifice to impinge against the splash plate surface.

Apparatus and method for a combustion turbine engine are provided. The apparatus may include a fuel-injecting lance (12) to convey a liquid fuel to a downstream end (16) of the lance. At least one jet in cross-flow injector (18) may be disposed at the downstream end of the lance, and includes an ejection orifice (20) responsive to eject a liquid jet (22) of the fuel. A plurality of surface irregularities (28, 29, 30, 50, 52, 54) is disposed at least on a portion of a wall (32) of the fuel-injecting lance exposed to the flow of air and proximate to the ejection orifice (20). The plurality of surface irregularities may be arranged to interact (e.g., turbulent interaction) with the flow of air to promote breakage of the ejected liquid jet of fuel compared to an injector lacking such surface irregularities.

An apparatus is provided for a turbine engine. This turbine engine apparatus includes a monolithic body. The monolithic body includes a splash plate and a fuel nozzle. The splash plate includes a splash plate surface. The fuel nozzle includes a nozzle orifice. The fuel nozzle is configured to direct fuel out of the nozzle orifice to impinge against the splash plate surface.

A combustor assembly for a gas turbine engine according to an example of the present disclosure includes, among other things, a combustion chamber, and a fuel injector assembly in communication with the combustion chamber that has a swirler body situated about a nozzle to define an injector passage that converges to a throat. The throat is defined at a distance from the combustion chamber. The nozzle includes a primary fuel injector and an array of secondary plain jet fuel injectors.

A fuel spray nozzle, for atomising liquid fuel in gas, including: an gas passage; a liquid fuel passage; a swirler provided in the gas passage and including vanes such that, when gas passes through the gas passage, the swirler produces a jet flow of gas from between adjacent vanes and a turbulent flow of gas in the wake of each vane; a prefilming surface for receiving liquid fuel from the liquid fuel passage, and gas from the gas passage, wherein the prefilming surface includes areas that receive jet flow of gas from the gas passage, in use; wherein the fuel spray nozzle is configured to direct the liquid fuel passing through the liquid fuel passage to the areas on the prefilming surface that receive a jet flow of gas from the gas passage.

A combustor assembly for a gas turbine engine according to an example of the present disclosure includes, among other things, a combustion chamber, and a fuel injector assembly in communication with the combustion chamber that has a swirler body situated about a nozzle to define an injector passage that converges to a throat. The throat is defined at a distance from the combustion chamber. The nozzle includes a primary fuel injector and an array of secondary plain jet fuel injectors.

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 low-pollution combustor and a combustion control method therefor. The low-pollution combustor includes a combustor head including a primary combustion stage and a precombustion stage, the primary combustion stage including a primary-combustion-stage channel and a primary-combustion-stage swirler disposed in the primary-combustion-stage channel. The primary combustion stage includes a pre-film plate disposed in the primary-combustion-stage channel, and the pre-film plate is radially divided into an outer-layer pre-film plate and an inner-layer pre-film plate. The positions and injection directions of fuel jet points of the primary combustion stage control fuel of the primary combustion stage to be injected into the primary-combustion-stage channel through primary-combustion-stage fuel jet orifices; and part of the fuel directly forms primary-combustion-stage direct-injection fuel spray, and the other part is hit on the pre-film plate close to an inner side of the primary-combustion-stage channel, or the two parts are respectively hit on the two layers of pre-film plates.

A combustor assembly for a gas turbine engine according to an example of the present disclosure includes, among other things, a combustion chamber, and a fuel injector assembly in communication with the combustion chamber that has a swirler body situated about a nozzle to define an injector passage that converges to a throat. The throat is defined at a distance from the combustion chamber. The nozzle includes a primary fuel injector along a first fuel injector axis and at least one secondary plain jet fuel injector axially forward of the primary fuel injector.