Disclosed are example efficient circuits that produce spark discharges for hydrocarbon conversion (or treatment of other mixtures) using a high-voltage rectified DC supply to discharge a capacitor (either internal or external) across a two-electrode gap, optimized to minimize waste energy by operating in a constant current, approximately-constant current, or constant power mode. The circuits may operate off of a standard electrical supply line (e.g. 120 VAC or 240 V AC, 60 Hz, single-phase or multi-phase). The disclosed approach is scalable to any number of discharge gaps while maintaining similar pulse characteristics and electrical efficiency.

The present invention discloses a mobile power system, the whole mobile power system is assigned onto two transport vehicles, achieving effective integration to reduce transport vehicle and transport cost; the two transport vehicles are connected at the side to enable quick and convenient connection in working state, greatly saving installation time; a gas turbine starter is disposed on an exhaust auxiliary transportation unit so that the mobile power system can be started by a gas turbine in totally power failure conditions.

The present invention discloses a mobile power system, the whole mobile power system is assigned onto two transport vehicles, achieving effective integration to reduce transport vehicle and transport cost; the two transport vehicles are connected at the side to enable quick and convenient connection in working state, greatly saving installation time; a gas turbine starter is disposed on an exhaust auxiliary transportation unit so that the mobile power system can be started by a gas turbine in totally power failure conditions.

A method of servicing a gas turbine engine having an igniter socket, the method comprising: inserting a glow plug into the igniter socket of the gas turbine engine until a rod end of a glow plug heater rod of the glow plug is exposed to a combustion chamber of the gas turbine engine; and blocking a gap between the glow plug heater rod and an aperture defined in a combustor liner of the gas turbine engine to block fluid communication between the combustion chamber and an environment outside the combustion chamber via the aperture.

A method of servicing a gas turbine engine having an igniter socket, the method comprising: inserting a glow plug into the igniter socket of the gas turbine engine until a rod end of a glow plug heater rod of the glow plug is exposed to a combustion chamber of the gas turbine engine; and blocking a gap between the glow plug heater rod and an aperture defined in a combustor liner of the gas turbine engine to block fluid communication between the combustion chamber and an environment outside the combustion chamber via the aperture.

There is described a method and system for in-flight start of an engine. The method comprises rotating a propeller; generating electrical power at an electric generator embedded inside a propeller hub from rotation of the propeller; transmitting the electrical power from the electric generator to an engine starter mounted on a core of the engine via an electric power link; and driving the engine with the engine starter to a sufficient speed while providing fuel to a combustor to light the engine to achieve self-sustaining operation of the engine.

There is described a method and system for in-flight start of an engine. The method comprises rotating a propeller; generating electrical power at an electric generator embedded inside a propeller hub from rotation of the propeller; transmitting the electrical power from the electric generator to an engine starter mounted on a core of the engine via an electric power link; and driving the engine with the engine starter to a sufficient speed while providing fuel to a combustor to light the engine to achieve self-sustaining operation of the engine.

An igniter for a combustor of a turbomachine includes a fuel inlet in fluid communication with a mixing plenum. The mixing plenum is positioned upstream of a mixing channel. An air inlet is in fluid communication with the mixing plenum and an ignition source is in operative communication with the mixing channel. The igniter may include a mounting flange configured for coupling the igniter to the combustor. The ignition source may be positioned proximate to a downstream end of the mixing channel and upstream of the mounting flange. The mixing channel may define a venturi shape. The venturi shape includes a converging section between an upstream end of the mixing channel and a venturi throat.

An igniter for a combustor of a turbomachine includes a fuel inlet in fluid communication with a mixing plenum. The mixing plenum is positioned upstream of a mixing channel. An air inlet is in fluid communication with the mixing plenum and an ignition source is in operative communication with the mixing channel. The igniter may include a mounting flange configured for coupling the igniter to the combustor. The ignition source may be positioned proximate to a downstream end of the mixing channel and upstream of the mounting flange. The mixing channel may define a venturi shape. The venturi shape includes a converging section between an upstream end of the mixing channel and a venturi throat.

An ignition system for igniting fuel in a gas turbine engine includes a power supply and an energy storage network electrically connected to the power supply. The energy storage network includes a first stage having a first capacitor and a second stage having a second capacitor. The ignition system further includes an engine igniter electrically coupled to the energy storage network.