Snecma

Safran Aircraft Engines

Francois Leglaye

David Gino Stifanic

Christophe Pieussergues

Olivier Baptiste Bidart

Pierre-François Simon Paul Pireyre

Emeric D'Herbigny

Patrick Lutz

Jean-Francois Cabre

Pierre-Francois Pireyre

Sylvain Oblaza

Olivier Bidart

Emeric D'herbigny

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.

Turbomachine combustion chamber provided with air deflection means for reducing the wake created by an ignition plug

A turbine engine, a turbojet, or a turboprop engine, including an annular combustion chamber defined by an inner shell and an outer shell, a turbine distributor arranged downstream of the combustion chamber, with a downstream end of the outer shell and/or of the inner shell of the chamber including a radial rim arranged opposite a radial rim of an upstream end of the distributor, a sealing mechanism including at least one strip extending between the rims to provide a seal between the combustion chamber and the distributor. The sealing strip extends axially and circumferentially between the rims and bears sealingly against free ends of the rims.

Turbine engine, such as a turbojet or a turboprop engine

A turbine engine wall having a cold side and a hot side and including a plurality of cooling orifices for enabling air flowing on the cold side of the wall to penetrate to the hot side at least some of the cooling orifices being plugged by a plugging material so as to define a minimum level of porosity for the wall corresponding to putting the turbine engine into service, and the plugged cooling orifices being suitable for being unplugged progressively throughout the lifetime of the turbine engine in order to define a maximum level of porosity for the wall corresponding to an end of lifetime for the turbine engine, the plugging being performed by alternating at least one of the following rows or lines: circumferential rows, axial rows, diagonal lines, so as to lie in the range one-third to one-half of the maximum porosity.

Turbine engine wall having at least some cooling orifices that are plugged

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

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.

Growing community of inventors

Vaux Le Penil, France

Francois Leglaye