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 spray nozzle includes a fuel circuit having in series a gallery, circumferentially spaced passages arranged in a row around the nozzle, and an annular spin chamber. Each passage has an inlet for receiving a respective portion of the fuel from the gallery and a metering orifice for discharging its portion of the fuel. The passages are configured such that, when the flow of liquid fuel to the inlet port is shut off, a respective differential static pressure develops across stagnant liquid fuel remaining between the inlet and the metering orifice of each passage, and the passages are further configured such that one or more selected passages develop a different differential static pressure to the remaining passages causing a flow of purging air to enter the gallery from the combustor through the selected passages and exit through the remaining passages, thereby purging the gallery and the passages of fuel.

The current invention discloses a method of controlling the flow rate of a heavy fuel oil in a fluid transfer apparatus having a point of use outlet to a boiler. It not only controls the flow rate of the fuel oil directly, but also indirectly control the viscosity of the fuel oil without measuring its viscosity. It relies on combustion curves established during the commissioning period using a typical fuel oil at a predetermined trim heater temperature. During normal operation, it sets the flow control valve according to the combustion curves, measures the flow rate and compares to the flow rate target. Instead of using the flow rate measurement feedback to control the flow control vale, it modulates the trim heater to vary the viscosity to arrive at the desired flow rate.

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.

A fuel nozzle for a combustor of a gas turbine engine includes an outer air swirler along an axis, said outer air swirler defines an outer annular air passage between an outer wall and an inner wall, the outer wall defines a convergent-divergent nozzle. An inner air swirler along the axis to define an annular liquid passage therebetween, the annular liquid passage terminates upstream of the convergent-divergent nozzle and an annular fuel gas passage around the axis between the outer air swirler and the inner air swirler.

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 combustion system for a gas turbine engine includes a combustor dome. The combustor dome includes a fuel manifold with an inlet and nozzle components of a plurality of nozzles circumferentially spaced around the combustor dome. The fuel manifold and nozzle components are integrated with the combustor dome for fluid communication from the inlet to the nozzle components.

Provided is a burner of double tube structure including an outer tube and an inner tube. The inner tube includes a tip-side support portion fixed on the outer tube, a base-side support portion fixed on the outer tube, a main body portion supported by the tip-side support portion, bellows interposed between the main body portion and the base-side support portion, and a bulkhead member attached at a position between the tip-side support portion and the base-side support portion. Between an outer peripheral surface of the bulkhead member and an inner peripheral surface of the outer tube, a second gap smaller than a first gap between an outermost peripheral surface of the bellows and the inner peripheral surface of the outer tube is interposed.

A burner having an air intake, a premix manifold, a blast tube, a rich fuel manifold, and a pilot. The blast tube includes a diffuser, an auxiliary passage, and a shutter. The shutter has at least an open position allowing air and fuel mixtures to flow through the auxiliary passage and the diffuser, and a closed position allowing flow through only the diffuser. Air moves from the air intake to the premix manifold where it mixes with a first fuel. The mixture moves through the blast tube and is ignited by the pilot, forming a lean center flame. A second fuel moves through the rich fuel manifold and ignites via the lean center flame, forming a rich secondary flame. The lean center flame and rich secondary flame combine to form a first flame.