Safran Aircraft Engines

Laurent Patrick Robert Coudert

Erwan Daniel Botrel

Kevin Yannick Garles

A turbine blade, including a root, a vane including a leading edge and a trailing edge and a pressure-side wall and a suction-side wall, and including cooling vents at the trailing edge, this vane also including first and second serpentine circuits; each serpentine circuit including several ducts extending in the span direction, being connected to each other by angled portions; each serpentine circuit being supplied with air by its duct that is closest to the leading edge; and wherein the vents are supplied by the first and by the second serpentine circuit.

Turbine engine blade with improved cooling

A turbomachine blade including a hollow body defining a cavity, and including a downstream trailing edge. The blade further includes at least one hole which communicates with the cavity and which opens downstream onto the trailing edge. The trailing edge extends along the main radial direction of the blade, and including a downstream convex face. The blade is characterised in that each hole opens onto a planar rear face of a flat region formed in the trailing edge.

Turbine blade comprising an improved trailing-edge

A turbine vane of a turbine engine such as a turbojet. The vane includes a base supporting a blade that extends in a spanwise direction and ends in an apex. The blade includes a pressure-side wall and a suction-side wall, each ending at an end edge at the apex of the blade. The blade includes, at the apex thereof, a closed wall extending from the pressure-side wall to the suction-side wall so as to define, with the end edges, a tub shape. The pressure-side wall is curved inward so as to deviate from the spanwise direction in the region of the blade apex preceding the tub, between the base and the pressure-side end edge.

Turbine vane comprising a blade with a tub including a curved pressure side in a blade apex region

The invention relates to a turbomachine vane comprising a root and a blade including a median main plane having a longitudinal and radial main orientation, which is carried by the root, the blade including a leading edge located at an upstream longitudinal end, a trailing edge located at a longitudinal end downstream of the leading edge with respect to a gas stream flowing around the blade, a lower surface wall and an upper surface wall which are located laterally remote from each other and each connecting the leading edge to the trailing edge, and a top located at the free outer radial end of the blade, the blade further including a fin having a longitudinal main orientation which is carried by the lower surface side, which is located at the top of the blade, wherein the fin is radially inwardly offset with respect to the top of the blade.

Growing community of inventors

Nandy, France

Laurent Patrick Robert Coudert