Snecma

Snecma Moteurs

Safran Aircraft Engines

Philippe Picot

Patrice Eneau

Gregory Pierre Lafarge

Sébastien Serge Francis Congratel

Erwan Daniel Botrel

Charlotte Marie Dujol

Son Le Hong

Didier Fabre

Christophe Bernard Texier

Isabelle Bourriaud

Gael Frédéric Claude Cyrille Evain

A turbine blade including a root bearing an aerofoil extending in a direction of span and ending in a tip, this aerofoil including a leading edge and a trailing edge which are connected by a pressure face wall and a suction face wall, the trailing edge including on the pressure face side cooling slots. The trailing edge includes one or more first slots close to the root, which are supplied via a lower cavity; one or more last slots near the tip which are supplied via an upper cavity; intermediate slots situated between the first slots and the last slots supplied with air via a downstream line set; and wherein the lower cavities and upper cavities and the downstream line set are supplied distinctly at the level of the root.

Blade comprising a trailing edge having three distinct cooling regions

A turbine or compressor stage for a turbine engine is provided. The stage includes a disk including a metal material configured to be coupled to a shaft of the turbine engine, an airfoil including a ceramic matrix composite material, and an interface part that is distinct from the airfoil and that is configured to be fastened to the disk and to fasten the airfoil. The interface part includes a ceramic or a ceramic matrix composite material.

Turbine or compressor stage including an interface part made of ceramic material

When cold and in the uncoated state, the aerodynamic airfoil is substantially identical to a nominal airfoil determined by the Cartesian coordinates X, Y, Z' given in Table 1, in which the coordinate Z&#x2032; is the ratio D/H where D is the distance from the point in question to a reference plane P, located at the base of the nominal airfoil, and H is the height of this airfoil, measured from said reference plane up to the tip of the blade. The D and H measurements being taken radially with respect to the axis of the turbine whereas the X coordinate is measured in the axial direction of the turbine.

Optimized aerodynamic airfoil for a turbine blade

When cold and in the non-coated state, the aerodynamic profile is substantially identical to a nominal profile determined by the rectangular coordinates X,Y,Z' given in Table 1, in which the X coordinate is measured in the axial direction of the turbine, and the Z&#x2032; coordinate is the quotient D/H, where D is the distance of the point in question from a reference plane Psituated at the base of the nominal profile and H is the height of the profile measured from said reference plane to the tip of the blade, the measurements D and H being taken radially relative to the axis of the turbine.

Optimized aerodynamic profile for a turbine blade

A gas turbine blade for an airplane engine, comprising in its central portion at least a first central cooling circuit comprising at least first and second cavities extending radially on the concave side of the blade, at least one cavity extending on the convex side of the blade, an air admission opening at a radial end of the first concave side cavity for feeding the first central cooling circuit with cooling air, a first passage putting the other radial end of the first concave side cavity into communication with an adjacent radial end of the convex side cavity, a second passage putting the other radial end of the convex side cavity into communication with an adjacent radial end of the second concave side cavity, and outlet orifices opening out into the second concave side cavity and through the concave face of the blade.

Cooling circuits for a gas turbine blade

A gas turbine blade for an airplane engine, the blade comprising at least a first cooling circuit comprising at least a concave side cavity extending radially beside the concave face of the blade, at least a second cooling circuit comprising at least one convex side cavity extending radially beside the convex face of the blade, and at least one third cooling circuit comprising at least one central cavity situated in the central portion of the blade between the concave side cavity and the convex side cavity, at least one leading edge cavity situated in the vicinity of the leading edge of the blade, communication orifices opening out into the central cavity and into the leading edge cavity, and outlet orifices opening out into the leading edge cavity and through the leading edge of the blade.

Growing community of inventors

Le Chatelet en Brie, France

Philippe Picot