Snecma

Safran Aircraft Engines

David Gino Stifanic

Francois Leglaye

Luc Henri Chatenet

Pierre-François Simon Paul Pireyre

Bertrand Boedot

Joël Yvan Marcel Robert Berton

Jean-Francois Cabre

Thomas Gérard Daniel Riviere

Denis Robert Gaston Haussaire

Guillaume Thierry Richen

Christian Schaeffer

The invention relates to a semiconductor body revolving around a main axis (A) for a spark plug of a turbine engine, the semiconductor body comprising a baseplate and an upper portion extending from the baseplate along the main axis, the baseplate comprising a bottom surface substantially defined in a plane perpendicular to the main axis and a first conical surface intended to cooperate by form-fitting at least partially with a contact surface of an outer electrode of the spark plug. According to the invention, the upper portion comprises an interface located opposite the bottom surface along the main axis (A) and featuring a profile that is at least partially corrugated.

Semiconductor body for a spark plug of a turbine engine

In order to test a semiconductor spark plug, a test method comprises a step consisting of depositing water on the head of the spark plug, between the two electrodes of same, so that the water forms a water meniscus covering the semiconductor element of the head, a step consisting of applying, between the first terminal and the second terminal of the spark plug, a voltage equal to the operating voltage of the spark plug, a step consisting of identifying at least a first characteristic of electric arcs induced between the electrodes during the application of the voltage, and a step consisting of determining the operational or defective character of the spark plug according to the first characteristic of the electric arcs. This test method is particularly reliable and does not require constraining provisions in order to ensure the safety of the operators implementing the method.

Method for testing a semiconductor spark plug

Assembly comprising, on a turbomachine:&#x2014;a combustion chamber () having a longitudinal axis () and comprising: internal and external longitudinal walls () having a first opening () substantially transverse to said axis (), an outer casing () having a second opening () likewise substantially transverse to said axis (),&#x2014;a turbomachine sparkplug (),&#x2014;a device () for radially securing the sparkplug (), which device () comprises a sparkplug adapter () fixed toward a first end to the outer casing (), facing the second opening () and through which adapter and casing the sparkplug () in question passes, and a sparkplug guide () kept in contact with the external longitudinal wall (), facing the first opening () and through which the sparkplug () passes to emerge in the combustion chamber (), the sparkplug () and the sparkplug guide () each having a screw thread (), the screw threads () being screwed together so as to stabilize the sparkplug () radially to the axis () of the combustion chamber () with respect to said external longitudinal wall (), and&#x2014;in this condition, the sparkplug () and the sparkplug guide () are mounted freely with respect to the outer casing () in a direction substantially radial to the axis of the second opening ().

Turbomachine sparkplug fixing assembly

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.

Ignition unit for turbojet engine

A spark plug for combustion chamber of a gas turbine engine including: an external body forming ground electrode, intended to be received mainly in a bypass of the combustion chamber; an internal central electrode; and an interposed insulator with clearance between the external body and the internal electrode, is provided. The spark plug terminates in a nose forming portion to be received in the flame tube of the chamber of the combustion chamber, and a semi-conductor element being interposed between the central electrode and the ground electrode at the level of said nose forming portion. The external body includes at least one cooling air inlet which communicates inside the spark plug with at least one outlet arranged at the level of the nose forming portion.

Spark plug for combustion chamber of a gas turbine engine

A method for determining an optimum positioning zone of an ignition plug fitted with a semiconductor element in a combustion chamber is provided. The method includes: determining, using a test ignition plug, of an optimum fuel flow rate value intended to ensure optimum long-term operation of the ignition plug; successively measuring quantities of fuel collected at the surface of one end of a test tool positioned in the combustion chamber in successive test ignition tests; determining the fuel flow rate values corresponding to the measured quantities of fuel; comparing the fuel flow rate values and of the optimum fuel flow rate value, and determining the optimum positioning zone following the comparing.

Growing community of inventors

Moissy-Cramayel, France

David Gino Stifanic