In one aspect a pilot assembly is disclosed for use with a flare having a first flare stack and a second flare stack, each having discharge ends. The pilot assembly comprises a pilot nozzle assembly, a pilot inlet pipe having a pilot fuel inlet, and a pilot ignition system. The pilot nozzle assembly comprises a connecting member, a pilot nozzle inlet, a first pilot nozzle and a second pilot nozzle. The pilot nozzle assembly can direct a quantity of pilot gas received via the pilot inlet pipe out through the first and second pilot nozzles. The first and second pilot nozzles may both be positioned adjacent the discharge end of either one of the first or second flare stacks. Alternatively, the first pilot nozzle may be positioned adjacent the first flare stack's discharge, and the second pilot nozzle may be positioned adjacent the second flare stack's discharge end.

In one aspect a pilot assembly is disclosed for use with a flare having a first flare stack and a second flare stack, each having discharge ends. The pilot assembly comprises a pilot nozzle assembly, a pilot inlet pipe having a pilot fuel inlet, and a pilot ignition system. The pilot nozzle assembly comprises a connecting member, a pilot nozzle inlet, a first pilot nozzle and a second pilot nozzle. The pilot nozzle assembly can direct a quantity of pilot gas received via the pilot inlet pipe out through the first and second pilot nozzles. The first and second pilot nozzles may both be positioned adjacent the discharge end of either one of the first or second flare stacks. Alternatively, the first pilot nozzle may be positioned adjacent the first flare stack's discharge, and the second pilot nozzle may be positioned adjacent the second flare stack's discharge end.

A locally powered intermittent pilot combustion controller may include an igniter, a thermal electric and/or photoelectric device that produces an electrical signal having power when exposed to a flame, and a local power source for providing power when the thermal electric and/or photoelectric device is not exposed to a flame. In some cases, the intermittent pilot combustion controller may include a memory for storing information about an ignition sequence for igniting a pilot flame, and a controller coupled to the memory. The controller may be configured to initiate the ignition sequence of the pilot flame using information stored in the memory, determine whether the ignition was successful by monitoring the electrical signal produced by the thermal electric and/or photoelectric device, and adjust the information stored in the memory based on whether the ignition sequence completed successfully.

A locally powered intermittent pilot combustion controller may include an igniter, a thermal electric and/or photoelectric device that produces an electrical signal having power when exposed to a flame, and a local power source for providing power when the thermal electric and/or photoelectric device is not exposed to a flame. In some cases, the intermittent pilot combustion controller may include a memory for storing information about an ignition sequence for igniting a pilot flame, and a controller coupled to the memory. The controller may be configured to initiate the ignition sequence of the pilot flame using information stored in the memory, determine whether the ignition was successful by monitoring the electrical signal produced by the thermal electric and/or photoelectric device, and adjust the information stored in the memory based on whether the ignition sequence completed successfully.

An embodiment of a torch igniter for a combustor of a gas turbine engine includes a combustion chamber oriented about an axis, a cap defining the axially upstream end of the combustion chamber and situated on the axis, a tip defining the axially downstream end of the combustion chamber, an igniter wall extending from the cap to the tip and defining a radial extent of the combustion chamber, a structural wall coaxial with and surrounding the igniter wall, an outlet passage defined by the igniter wall within the tip, wherein the outlet passage fluidly connects the combustion chamber to the combustor of the gas turbine engine, and a cooling system. The cooling system has an air inlet, a cooling channel, and an aperture. The cooling channel forms a flow path having a first axial section, a second axial section, a radially inward section, and a radially outward section.

A pilot and burner apparatus is provided for use in firefighting training. The apparatus includes a main fuel conduit and a main fuel valve. The apparatus includes a pilot tube and a pilot fuel conduit configured to deliver fuel from the main fuel conduit to the pilot tube. The apparatus includes main and pilot fuel valves to respectively control a flow of fuel in the main and pilot fuel conduits. In a pilot phase, the valves direct fuel to the pilot tube. An ignition component is configured to ignite fuel in the pilot tube to generate a pilot flame. In a burn phase, the pilot flame generates a controllable flame out of a main burner pipe by igniting fuel exiting the main fuel conduit. The controllable flame can be delivered to a training structure for training purposes.

A pilot and burner apparatus is provided for use in firefighting training. The apparatus includes a main fuel conduit and a main fuel valve. The apparatus includes a pilot tube and a pilot fuel conduit configured to deliver fuel from the main fuel conduit to the pilot tube. The apparatus includes main and pilot fuel valves to respectively control a flow of fuel in the main and pilot fuel conduits. In a pilot phase, the valves direct fuel to the pilot tube. An ignition component is configured to ignite fuel in the pilot tube to generate a pilot flame. In a burn phase, the pilot flame generates a controllable flame out of a main burner pipe by igniting fuel exiting the main fuel conduit. The controllable flame can be delivered to a training structure for training purposes.

A fuel injector includes a fuel nozzle configured to issue a spray of fuel from a fuel outlet in a downstream direction along an injection axis. The fuel nozzle includes a nozzle body that defines a main flow passage therethrough. An injection fuel line is in fluid communication with the fuel nozzle to supply fuel to the fuel nozzle. A torch ignitor with a flame outlet opens into the main flow passage of the fuel nozzle for issuing flame into the main flow passage. The flame outlet meets the main flow passage at a position that is downstream of the fuel outlet with respect to the downstream direction along the injection axis.

An embodiment of a torch igniter for a combustor of a gas turbine engine includes a combustion chamber oriented about an axis, a cap defining the axially upstream end of the combustion chamber and situated on the axis, a tip defining the axially downstream end of the combustion chamber, an igniter wall extending from the cap to the tip and defining a radial extent of the combustion chamber, a structural wall coaxial with and surrounding the igniter wall, an outlet passage defined by the igniter wall within the tip, wherein the outlet passage fluidly connects the combustion chamber to the combustor of the gas turbine engine, and a cooling system. The cooling system has an air inlet, a cooling channel, and an aperture. The cooling channel forms a flow path having a first axial section, a second axial section, a radially inward section, and a radially outward section.

A system for use with a fired vessel of production/separators or dehydration equipment that includes a metal box, a main burner, a pilot burner, and a flame arrestor. The main burner and the pilot burner are within the metal box and the first flame arrestor is connected to the metal box.