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 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.

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 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 along a first fuel injector axis and at least one secondary plain jet fuel injector axially forward of the primary fuel injector.

A system is provided for an aerial vehicle. This system includes a splash plate, a fuel nozzle and a gas circuit. 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. The gas circuit includes a gas passage and a gas outlet. At least a portion of the gas passage is formed by and embedded within the splash plate. The gas passage extends through the splash plate to the gas outlet.

A nozzle for injecting liquid includes a nozzle body defining a plurality of injection point orifices and an annular prefilmer positioned downstream of the injection point orifices for prefilming impingement of spray from the injection point orifices on the prefilmer. A swirl antechamber can be defined upstream of the injection point orifices for supplying a swirling liquid flow to the injection point orifices for impingement of a swirling flow on the prefilmer.

A system is provided for an aerial vehicle. This system includes a splash plate, a fuel nozzle and a gas circuit. 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. The gas circuit includes a gas passage and a gas outlet. At least a portion of the gas passage is formed by and embedded within the splash plate. The gas passage extends through the splash plate to the gas outlet.

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.

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.