Safran Aircraft Engines

Snecma

Pierre-François Simon Paul Pireyre

Laurent Bernard Cameriano

Brice Le Pannerer

David Gino Stifanic

Francois Leglaye

The invention relates to an annular combustion chamber in a turbine engine, comprising two coaxial walls of revolution, one an internal wall () and the other an external wall (), between which emerge fuel injectors () each engaged in centring means () which are moveable in the radial direction in support means (), the chamber also comprising means () of axial retention in the upstream direction of the centring means. According to the invention, the means of axial retention in the upstream direction are removably fixed to at least one of the internal () or external () walls of revolution.

Combustion chamber in a turbine engine

The invention relates to a device for supporting and centring a fuel injector in a turbine engine combustion chamber, which includes means for centring a fuel injector along an axis, which are movable in a plane that is radial to the centring axis () in supporting means intended for being attached to the bottom of an annular chamber (). According to the invention, the centring means include at least two radially external tabs () each inserted respectively in a circumferential recess () of the supporting means, the device including circumferential abutment means () of the radial tabs () of the centring means in the circumferential recesses (), the circumferential abutment means being configured such as to enable a greater angular displacement of a first () one of the radial tabs in a first circumferential recess () relative to a second () one of the radial tabs in a second circumferential recess ().

Annular combustion chamber in a turbine engine

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 ().

Growing community of inventors

Moissy Cramayel, France

Pierre-François Simon Paul Pireyre