Safran Helicopter Engines

Baptiste Hallouin

Jean-Luc Breining

Alexandre Montpellaz

Damien Laberny

Jean-Maurice Casaux-Bic

Yann Danis

Lionel Renault

Sylvain Pierre Votie

Fabrice Iparaguirre

A stator vane of a turbine of a gas turbine engine, including an outer platform and an inner platform between which there extends an outer wall forming an outer skin, wherein it includes an inner wall, forming an inner skin, facing the outer wall so as to define an inter-skin cavity between the outer wall and the inner wall, the inner wall including a plurality of cooling orifices for impingement cooling of the outer wall, the outer wall and inner wall being produced by additive manufacturing.

Turbine stator vane comprising an inner cooling wall produced by additive manufacturing

A turbomachine blade formed of a hollow airfoil having a leading edge and a trailing edge opposed to each other and connected by an intrados wall and an extrados wall each extending along a radial axis of the blade, between a blade root and a blade tip, and including a cooling circuit supplied with air and delivering air jets ensuring through multiple perforations of the cooling circuit an impingement cooling of the inner surface of the airfoil, the cooling circuit includes superimposed cooling channels over the height of the blade, each integrated into the inner surface of the airfoil while matching its contour, the multiple perforations being drilled in the cooling channels terminating in a purge cavity of the airfoil are able to ensure a purge of the air having impinged the inner surface of the airfoil after its passage through the perforations.

Turbine stator blade cooled by air-jet impacts

An assembly for a turbomachine including an annular channel designed to form a flow duct for a flow of gas between two turbine stages of the turbomachine. The channel is bounded by a radially inner annular wall and a radially outer annular wall. The walls are connected by hollow arms that extend radially, a support having a radially outer annular part that is located radially outside the outer annular wall of the annular channel, and a radially inner annular part that is located radially inside the inner annular wall of the annular channel. The outer and inner parts of the support are connected by connecting parts that extend radially and pass through one of the hollow arms of the annular channel. The connecting parts may be connected by a connecting partition having a frangible part that ruptures when the mechanical stresses in the connecting partition are above a threshold.

Assembly for a turbomachine

The present disclosure relates to a blade of a guide vane assembly of a turbomachine fitted with a cooling system, generally including an insert arranged inside an internal cavity of said blade, connected to a cooling air inlet of the blade and designed to cool the surface of the internal cavity of the blade, and a bleed device configured to bleed some of the cooling air inside the insert and designed to send this bled cooling air to a central hub of the turbomachine. The bleed device of the blade may further include a bleed head arranged in the internal cavity of the blade and passing through an opening of the insert, and configured to bleed some of the cooling air inside the insert.

Growing community of inventors

Moissy-Cramayel, France

Baptiste Hallouin