Safran Aircraft Engines

Benjamin Franklin François Gillot

Sebastien Jean Laurent Prestel

Simon Nicolas Morliere

Sébastien Jean Laurent Prestel

Julian Nicolas Girardeau

Ghislain Hervé Abadie

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 ().

Growing community of inventors

Moissy-Cramayel, France

Benjamin Franklin François Gillot