Safran Aircraft Engines

Snecma

Sébastien Jean Laurent Prestel

Olivier Belmonte

Jean-Luc Soupizon

Alain Dominique Gendraud

Olivier Renon

Guillaume Sevi

Patrick Jean Laurent Sultana

Bertrand Guillaume Robin Pellaton

Baptiste Marie Aubin Pierre Jouy

Simon Nicolas Morliere

Philippe Jean-Pierre Pabion

Julian Nicolas Girardeau

Benjamin Franklin François Gillot

Patrick Sultana

Simon Jean-Marie Bernard Cousseau

Nicolas Contini

Patrice Jean-Marc Rosset

Cyril Verbrugge

Patrick Joseph Marie Girard

Ghislain Hervé Abadie

Benoit Argémiro Matthieu Debray

Hélène Myriam Condat

Aurélien René-Pierre Massot

Fabrice Marcel Noël Garin

Cyril Loiseau

Denis Aydin

Rémi Blanc

Alice Pages

Alberto Martin-Matos

Vincent Millier

Gilles Jeannin

Vincent Dubois Dorogi

Arnaud Doublier

Florent Pierre Antoine Luneau

Godefroy Francis Frédéric Drelon

Jean-Pierre Pabion

A cooling device () for a turbine of a turbomachine extending along an axis includes at least one radially inner metal sheet () and one radially outer metal sheet () that are joined to one another and delimit, between them, cooling air circulation channels () extending circumferentially from a connection region (). Each channel () includes at least one air inlet and air ejection orifices (), that are designed to be oriented toward a region to be cooled. The cooling device also includes at least one cooling duct () intended for the circulation of cooling air, the duct () located radially outside said metal sheets () and close to or in contact with the metal sheets so as to cool said metal sheets using the cooling air circulating in the duct (), the cooling duct () extending axially and arranged toward the circumferential end regions of the channels ().

Cooling device for a turbine of a turbomachine

A connecting assembly comprising an air distribution housing, between an air inlet passage and at least one duct connected with the housing by at least one bush mounted on an orifice of a wall of the housing. The wall of the housing and an inner wall of the bush are connected by a fillet having a radius which is maximum over an angular sector.

Connecting assembly for cooling the turbine of a turbine engine

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 () 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 ().

The invention relates to an inter-turbine casing () comprising: an inner shell (), an outer shell (), and an assembly of arms () extending radially between the timer () and outer () shells; and an assembly of splitter blades () positioned between the arms (), each splitter blade () comprising an inner platform () and an outer platform (). The inner shell () comprises at least one inner groove () for slidably receiving one or more inter platforms (). The outer shell () comprises at least one outer groove () for slidably receiving one or more outer platforms (). The inter-turbine casing further comprises locking means () for locking the splitter blades () in the inner () and outer () grooves. The splitter blades are arranged using multiple tenons () that extend in corresponding ribs ().

Inter-turbine casing comprising mounted splitter blades

A support system () for a structural casing of a turbomachine (), which comprises:

Handling fitting with movable jaws for a turbomachine casing

A holding device of a cooling tube for a turbojet casing, the holding device including a first plate configured to be arranged in integral contact with a turbojet casing; a second plate, the first and second plates having a gap therebetween; a first spacer and the second spacer which are arranged between the first plate and the second plate and defining the gap between the first and second plates, the first and second spacers having a spacing therebetween suitable for passing the cooling tube.

Holding device of a cooling tube for a turbojet casing

A nozzle sector of an aircraft turbo-machine, including a hooking member () having a projection () radially extending towards the outside of the sector, a recess () being provided through at least one part of a distal end of the projection (), the recess () being configured to accommodate a shoulder member () forming a stop for a surface of an adjacent sector ().

Anti-rotation nozzle sector and method for manufacturing such a sector

Growing community of inventors

Moissy-Cramayel, France

Sébastien Jean Laurent Prestel