A turbine engine ignition system comprising a spark plug having excitation and return terminals, and a spark plug exciter connected to the excitation terminal. The return terminal is connected to an equipotential reference-forming structure, the exciter device is connected to a command line for a signal to supply an excitation signal to the spark plug. The ignition system comprises a control device comprising current and voltage sensors, a first voltage comparator, a second current comparator, and a microcontroller receiving output from the two comparators. The first comparator compares the voltage sensor signal to a first reference value and the second comparator compares the current sensor signal to a second reference value. The microcontroller generates a signal indicating a malfunction of the ignition system if the current sensor signal is lower than the second reference value while the voltage sensor signal is higher than the first reference value.

An apparatus and a method for a circuit can include a voltage divider having a first and a second impedance in series, and having a voltage divider output. A switchable element is arranged in parallel with the first impedance and connected with the voltage divider output. The switchable element has an open state and a closed state. A spark gap device is configured to not generate a spark when the switchable element is in the open state and generate a spark when the switchable element is in the closed state.

A device for cooling of an annular wall of a turbomachine combustion chamber provided with micro-perforations, and in particular the cooling of a region of the wall facing a wake induced by an ignition plug, the device includes, a deflector designed to divert air immersing the ignition plug towards a median plane of the wake and towards the annular wall of the combustion chamber, so as to increase the air pressure within the wake in proximity to the annular wall.

A control device for an internal combustion engine is programmed, during a catalyst warm-up control, to perform first fuel injection by an injector in an intake stroke, control an ignition device so as to generate a discharge spark in a predetermined period in an expansion stroke, and perform second fuel injection, at a timing retarded from a compression top dead center, such that its injection period overlaps with at least a part of the predetermined period and an end timing of the injection period is advanced from an end timing of the predetermined period. Further, the control device is programmed, during the catalyst warm-up control, to control an actual tumble ratio depending on a result of determination using a first index value representing a speed of initial combustion accompanying an ignition by the ignition device and a second index value representing a speed of main combustion accompanying the ignition.

A device for igniting an aircraft engine, comprising at least two spark plugs, the device comprising a power supply, a first path for supplying a first spark plug with power and a second path for supplying a second spark plug with power, said paths being connected to the power supply by distribution means of the power supply which are controlled by a FADEC-type control system, wherein said distribution means comprise a first circuit that is configured to alternately supply said first path or said second path with power, and a second circuit for simultaneously supplying said first and second paths with power, the device being configured to use either the first circuit or the second circuit during start-up.

A spark gap assembly includes a sealed chamber, at least two discharge electrodes, and a non-radioactive gas fill within the sealed chamber. The sealed chamber includes first and second end plugs and a vitreous tube having opposite ends, each end being sealed by one of said end plugs. The discharge electrodes extend through the first and second end plugs, respectively, from an exposed portion outside of the sealed chamber to an enclosed portion inside the sealed chamber. The discharge electrodes each have a discharge portion that includes a surface from which electrons of a spark discharge exit or are received, with the discharge surfaces of the discharge portions facing each other to thereby define a spark discharge gap between the discharge surfaces of the two discharge electrodes. The gas fill within the sealed chamber includes one or more non-radioactive isotopes of one or more noble gases.

A gas turbine engine comprises an electronic control unit adapted to control functions of the gas turbine engine and having a DC power input unit coupled to receive DC supply power and an ignition igniter coupled thereto. The ignition exciter includes an AC power input unit adapted to receive AC power from an AC power source within the gas turbine engine, a power rectification unit coupled to receive the AC power from the AC power source and configured, upon receipt thereof, to rectify the AC power into DC power, and a DC power output unit coupled to receive the DC power from the power rectification unit and configured to supply the DC power to the DC power input unit of the electronic control unit as DC supply power and/or the ignition igniter.

A solid state spark device that operates as a two terminal spark gap in a CDI exciter of an aircraft ignition system. The device includes a triggering transformer, a triggering circuit, and a control circuit. The triggering circuit is electrically connected to a first coil of the transformer and includes circuit elements connected to supply current to the first coil upon charging of the triggering circuit up to a triggering voltage. This current through the first coil of the triggering transformer induces an output in a second coil of the transformer. The control circuit is electrically connected to the second coil and includes a switch controlled by the output from the second coil. The switch, when activated by the triggering circuit, discharges energy from the exciter into an igniter of the aircraft ignition system.

An ignition unit for a turbojet engine, including: an electrical power supply, a single control channel to receive a control signal from a computer, a main sparkplug ignition channel to energize at least one main sparkplug of a main combustion chamber, and an afterburner sparkplug ignition channel to energize at least one afterburner sparkplug of an afterburner chamber. The ignition unit is configured, in response to pulsed controls on the single control channel, to selectively activate the main sparkplug ignition channel or the afterburner sparkplug ignition channel.

A solid state spark device that operates as a two terminal spark gap in a CDI exciter of an aircraft ignition system. The device includes a triggering transformer, a triggering circuit, and a control circuit. The triggering circuit is electrically connected to a first coil of the transformer and includes circuit elements connected to supply current to the first coil upon charging of the triggering circuit up to a triggering voltage. This current through the first coil of the triggering transformer induces an output in a second coil of the transformer. The control circuit is electrically connected to the second coil and includes a switch controlled by the output from the second coil. The switch, when activated by the triggering circuit, discharges energy from the exciter into an igniter of the aircraft ignition system.