The present disclosure relates to a liquid fuel self-sustaining combustion burner for flame synthesis, including a swirl-flow cylinder and a stable combustion cylinder. A swirl-flow plate is disposed at an open end of the swirl-flow cylinder and defines swirl-flow outlets. A tangential inlet tube is mounted on the swirl-flow cylinder and in fluid communication with the swirl-flow chamber. An open end of the swirl-flow cylinder extends into the stable combustion chamber. The fuel can be atomized by an atomizer and sprayed into the stable combustion chamber for combustion. Air introduced from the tangential inlet tube can flow into the swirl-flow chamber and advance spirally around the central stabilizing column to reach the swirl-flow plate. The airflow is partially injected into the stable combustion chamber through the swirl-flow outlets, and then continues to spirally advance. An atomizing nozzle of the atomizer is located inside the swirling airflow.

An atomizer includes an endcap having a nozzle; an annular sidewall extending outward from a surface of the endcap and situated radially outward from the nozzle; and a plurality of vanes extending radially inward from the sidewall and axially outward from the endcap, the vanes being set at a non-zero angle of incidence to the sidewall. The annular sidewall and endcap define an fluid chamber between an inlet and the nozzle, and flow from the inlet to the nozzle is at least partially directed through passageways between the vanes, and the flow is imparted with swirling motion from the vanes.

An atomizer includes an atomizer body with a plurality of air passages defined therethrough from an upstream end of the atomizer body to a downstream end thereof. The air passages together define an air circuit through the atomizer body. A fuel circuit is defined in the atomizer body extending from a fuel inlet to a respective fuel outlet opening into each air passage. The air passages can be arranged circumferentially about a central axis defined by the atomizer body. The fuel circuit can include a manifold extending circumferentially about the atomizer body in fluid communication with a fuel opening in each respective air passage.

A liquid fuel injector includes a cylindrical center body including a center axis, an annular shroud concentrically disposed outside the center body, an annular fuel injection body disposed between and concentrically with the center body and the shroud, and including a fuel passage formed therein, a plurality of inner swirl vanes that are arranged in an equal cycle in an inner air passage between the center body and the fuel injection body, and are provided with an inner swirl vane action surface on an upstream side, a plurality of outer swirl vanes that are arranged in an equal cycle in an outer air passage between the fuel injection body and the shroud, and an outer swirl vane action surface on the upstream side.

A liquid fuel injector includes a cylindrical center body including a center axis, an annular shroud concentrically disposed outside the center body, an annular fuel injection body disposed between and concentrically with the center body and the shroud, and including a fuel passage formed therein, a plurality of inner swirl vanes that are arranged in an equal cycle in an inner air passage between the center body and the fuel injection body, and are provided with an inner swirl vane action surface on an upstream side, a plurality of outer swirl vanes that are arranged in an equal cycle in an outer air passage between the fuel injection body and the shroud, and an outer swirl vane action surface on the upstream side.

A torch igniter and a method of igniting a torch flame. An example embodiment includes a body including an oxidizer inlet configured to facilitate oxidizer flow through the body toward an output end of the body. The body includes a group of fuel inlet passages configured to distribute fuel in a direction tangential to the oxidizer flow through the body to create a swirling fuel-oxidizer mixture. A sparking element can be mounted on the body to produce a spark in the path of the swirling fuel-oxidizer mixture to ignite the mixture. The output end of the body is configured to emit a torch flame when the fuel-oxidizer mixture is ignited. Thus, a swirl torch igniter is configured for oxidizer and fuel flow through the igniter body to create an internal swirling fuel-oxidizer mixture to be ignited by a sparking element.

A combustion chamber for a gas turbine is provided. The combustion chamber has a pilot burner device, a fuel injector, an ignitor unit and an air blast injector. The pilot burner device has a pilot body with a pilot surface facing an inner volume of the combustion chamber. The fuel injector has a fuel outlet for injecting a fuel into the inner volume, wherein the fuel outlet is arranged at the pilot surface. The ignitor unit is arranged at the pilot surface such that fuel which passes the ignitor unit is ignitable. The air blast injector is adapted for injecting an air blast into the inner volume, wherein the air blast injector includes an air blast outlet arranged at the pilot surface such that the air blast is injectable in the direction to the fuel outlet and the ignitor unit for directing the fuel to the ignitor unit.

A burner capable of burning crude or other heavy oil. A combustion chamber is surrounded by a wall of thermal insulation. An air-fuel injector pipe extends through the wall and opens into the combustion chamber. An oil supply pipe extends along the interior of the air fuel injector pipe to an inner open end that is proximate the inner end of the air-fuel injector pipe. A venturi insert is fixed within the air-fuel injector pipe and has an orifice positioned outward of the open inner end of the oil supply pipe. A combustion air supply including a blower and a recuperator transfers heat from outgoing combusted exhaust gases to incoming combustion-supporting air being blown through the recuperator and the air fuel injector pipe into the combustion chamber.

Implementations of a combustor assembly yield low emissions, require low power, are suitable for alternate liquid fuels, including highly viscous fuels, and are scalable for various heat release rates. The combustor assembly includes a fuel injector and a swirler. The fuel injector may include a choke portion and a spacer. The choke portion is disposed just upstream of an outlet of a liquid fuel conduit and prevents atomizing gas from interrupting continuous flow of the liquid fuel through the liquid fuel conduit. The spacer is disposed downstream of the outlet to precisely control the gap and thus, bifurcation of atomizing gas flow, between the outlet of liquid fuel conduit and an inlet of an orifice plate. The swirler is disposed radially outwardly and adjacent the fuel injector and includes a plurality of angled vanes.

A fuel nozzle for a combustor of a gas turbine engine includes a body defining an axial direction and a radial direction, a primary air passageway centrally defined axially in the body, and a plurality of concentrically-arranged nozzle tip projections disposed at a downstream portion of the body. Each of the plurality of nozzle tip projections has a radially inwardly facing fuel filming surface communicating with respective fuel passages. The fuel filming surfaces are disposed radially outwardly of an outlet of the primary air passageway. A method for delivering fuel from a fuel nozzle of a combustor of a gas turbine engine is also presented.