The present disclosure describes a recovery boiler startup burner assembly that can mitigate the harmful effects of smelt fouling, airflow interference, and operator exposure to hot air from the furnace and win box through use of an extractable startup burner and an isolation chamber engaged to a windbox. The present disclosure also describes a method for safely extracting a startup burner from an active recovery boiler as has method for inserting an extractable startup burner into a recovery boiler during operation.

The present disclosure describes a recovery boiler startup burner assembly that can mitigate the harmful effects of smelt fouling, airflow interference, and operator exposure to hot air from the furnace and win box through use of an extractable startup burner and an isolation chamber engaged to a windbox. The present disclosure also describes a method for safely extracting a startup burner from an active recovery boiler as has method for inserting an extractable startup burner into a recovery boiler during operation.

An oxy-combustor is provided which comprises a combustion vessel including at least one solid fuel slurry inlet port, at least one oxygen inlet port and at least one supercritical fluid inlet port, wherein the combustion vessel is operable at an operating pressure of at least 1,100 psi; an interior of the combustion vessel comprises a combustion chamber and a supercritical fluid infusion chamber surrounding at least a part of the combustion chamber, the supercritical fluid infusion chamber and the combustion chamber are separated by a porous liner surrounding the combustion chamber, and the supercritical infusion chamber is located between the porous liner and an outer casing of the combustion vessel.

An oxy-combustor is provided which comprises a combustion vessel including at least one solid fuel slurry inlet port, at least one oxygen inlet port and at least one supercritical fluid inlet port, wherein the combustion vessel is operable at an operating pressure of at least 1,100 psi; an interior of the combustion vessel comprises a combustion chamber and a supercritical fluid infusion chamber surrounding at least a part of the combustion chamber, the supercritical fluid infusion chamber and the combustion chamber are separated by a porous liner surrounding the combustion chamber, and the supercritical infusion chamber is located between the porous liner and an outer casing of the combustion vessel.

A preheat burner assembly and method for preheating forming dies includes a frame, a burner manifold and a link assembly. The burner manifold as a plurality of burner orifices for preheating the forming dies. The burner manifold is connected to a fuel source. The link assembly mounts the burner manifold to the frame for movement between a stowed position and a deployed position. The burner is moved via the link assembly to a deployed position for preheating the forming dies. The forming dies are preheated. The burner manifold is subsequently moved via the link assembly from the deployed position to an upright stowed position.

A preheat burner assembly and method for preheating forming dies includes a frame, a burner manifold and a link assembly. The burner manifold as a plurality of burner orifices for preheating the forming dies. The burner manifold is connected to a fuel source. The link assembly mounts the burner manifold to the frame for movement between a stowed position and a deployed position. The burner is moved via the link assembly to a deployed position for preheating the forming dies. The forming dies are preheated. The burner manifold is subsequently moved via the link assembly from the deployed position to an upright stowed position.

The present application provides a variable volume combustor for use with a gas turbine engine. The variable volume combustor may include a liner, a number of micro-mixer fuel nozzles positioned within the liner, and a linear actuator so as to maneuver the micro-mixer fuel nozzles axially along the liner.

The present application provides a variable volume combustor for use with a gas turbine engine. The variable volume combustor may include a liner, a number of micro-mixer fuel nozzles positioned within the liner, and a linear actuator so as to maneuver the micro-mixer fuel nozzles axially along the liner.

A system includes a combustor for a gas turbine defining a main axis extending in an upstream-downstream direction, the combustor including a combustor dome bounding an upstream portion of the combustor, wherein a plurality of injector openings are defined through the combustor dome. An injector defines a spray axis aligned with one of the plurality of injector openings for issuing a spray into the combustor along the spray axis. An actuator is operatively connected to the injector for movement of the injector relative combustor dome to adjust a relative position of the spray axis relative to the main axis to alter the position and/or direction of the spray injector during operation of the gas turbine engine.

A system includes a combustor for a gas turbine defining a main axis extending in an upstream-downstream direction, the combustor including a combustor dome bounding an upstream portion of the combustor, wherein a plurality of injector openings are defined through the combustor dome. An injector defines a spray axis aligned with one of the plurality of injector openings for issuing a spray into the combustor along the spray axis. An actuator is operatively connected to the injector for movement of the injector relative combustor dome to adjust a relative position of the spray axis relative to the main axis to alter the position and/or direction of the spray injector during operation of the gas turbine engine.