Safran Aircraft Engines

Simon Nicolas Morliere

Alain Dominique Gendraud

Vincent François Georges Millier

Olivier Renon

Sebastien Jean Laurent Prestel

Nicolas Jean-Marc Marcel Beauquin

Stéphane Pierre Guillaume Blanchard

Sébastien Jean Laurent Prestel

Julian Nicolas Girardeau

Ghislain Hervé Abadie

Benjamin Franklin François Gillot

Renaud James Martet

Thierry Fachat

Gaëlle Inès Méganne Moreaux

Sébastien Philippe Edith Bourgeois

Stéphane Sylvain Bois

The invention proposes an aeronautical turbine engine assembly comprising an upstream casing () to which guide blading () is fastened, and a downstream casing () to which a sealing element () provided with an abradable material for rotor blading is fastened. This assembly further comprises a shroud ring () placed between the upstream casing and the downstream casing and fastening means () for detachably fastening the shroud ring. In order to be fastened to the upstream casing, the guide blading () of the turbine engine is mounted on a downstream hook () of the upstream casing, without being hooked onto the shroud ring (), and the downstream casing () has an upstream hook with which the sealing element () is engaged in order to be fastened to the downstream casing, or the shroud ring has an upstream hook on which the sealing element () is mounted so as to be fastened to the downstream casing.

Mounting of a sealing ring on an aeronautical turbine engine

The invention relates to an assembly () for a turbomachine turbine comprising a casing () including an annular wall () extending about an axis, and means of cooling the casing (), the said means of cooling comprising a collector housing () and at least one tube () extending circumferentially around the annular wall () of the casing () and connected to the housing (), with the tube () comprising cooling-air ejection orifices.

Assembly for a turbomachine turbine

A turbine for a turbine engine extending along an axis includes an annular casing and at least one turbine stage having a nozzle and a rotor impeller wheel surrounded by a sealing ring with an abradable element. The impeller wheel and the sealing ring are located downstream of the nozzle, and the sealing ring has an upstream end held on the casing by locking means. The turbine includes elastic sealing means in contact with the locking means as well as with the nozzle or the casing so as to press the locking means against the sealing ring. The locking means includes a radially outer portion with a C-shaped cross-section and a radial portion extending radially inwards from the outer portion. The sealing means include two elastic seals bearing on the radial portion, respectively, on either side of the radial portion.

Turbine for a turbine engine

The present invention relates to a device for cooling, using air jets, an external casing of a turbomachine, comprising a housing for supplying air to cooling tubes of said casing, the housing being provided with an attachment device on the external casing. According to the invention, said attachment device comprises two upstream ball joint retention devices which each connect the housing to the external casing.

Device for cooling an outer casing of a turbomachine and turbomachine provided with such a device

A device for holding () at least one cooling tube () of a turbomachine casing () cooling system (), the holding device including a fixing frame (), a holding member () being configured to hold two cooling tubes (), and a connection assembly () between the holding member () and a fixing frame (), extending on either side of the frame, the connection assembly () comprising a connection part () extending through an opening () of the fixing frame from an outer portion () to the inner portion () of the connection assembly, the inner portion () being disposed between two cooling tubes () and secured to the holding member () while the outer portion () comprises a resilient return member () urged in compression towards the fixing frame by the connection part ().

Device for holding a cooling tube for a turbomachine casing

The invention relates to a cooling device () extending circumferentially around a turbine engine casing (), such as, for example, a turbine casing (), comprising a support () extending axially and intended to be attached to the casing (), at least one cooling tube () extending circumferentially, at least one attachment member () comprising a radially inner portion () at least partially surrounding the tube (), and a radially outer portion () attached to the support (), the radially outer portion () of the attachment member () being attached to the support () through connecting means () formed by L-shaped sheets.

Cooling device for a turbine of a turbomachine

Cooling device () extending circumferentially around a turbomachine casing, such as a turbine casing, comprising a support () extending axially and designed to be secured to the casing, at least one cooling tube extending circumferentially, at least one securing member (), comprising a radially inner portion () at least partially surrounding the tube, and a radially outer portion () secured to the support (), the radially outer portion () of the securing member () being secured to the support () via the intermediary of a connection member () comprising a central portion () having a circumferential end portion () and a second circumferential end portion () which are circumferentially opposite, the first end portion () and the second end portion () each extending in an opposite axial direction, the first and second end portions () each being secured to the support (), the radially outer portion () of the securing member () being secured to the central portion () of the connection member ().

Turbine engine turbine sealing module extending about an axis and including a distributor fixed to a casing, and at least one blade connected to an outer platform. The turbine module further includes an impeller mounted rotating inside the casing and surrounded by a sealing ring fastened to this casing. The sealing ring includes an annular row of ring sectors arranged such that the circumferential end edges of two adjacent sectors are facing one another. Each sector includes a body configured to engage with at least one seal lip carried by the impeller and a hook which extends circumferentially which is configured to engage with a fastening rail of the casing. Each ring sector further includes a deflector which extends radially inwards and upstream with respect to the axis, such that the radially inward end thereof extends around a downstream end of the outer platform of the distributor.

Aircraft turbine engine sealing module

A sealing assembly for a turbine is provided. The turbine includes stages each including a nozzle blade extending between radially inner and outer platforms, the outer platform including a spoiler which delimits a groove. The assembly includes a ring, a tab, and an anti-wear foil. The ring is to be attached to an outer casing of the turbine. A part of the sealing tab is engaged in a first housing of a ring sector of the ring and another part in a second housing of an adjacent ring sector. The anti-wear foil, open upstream, is mounted in the groove. The downstream end of the ring sectors are to be engaged in the anti-wear foil. Each of the first and second housings is formed by a slot. The tab is bent and disposed in the slots so that a downstream end of the tab extends out of the slots.

Growing community of inventors

Moissy-Cramayel, France

Simon Nicolas Morliere