Snecma

Gregory Pierre Lafarge

Philippe Picot

Erwan Daniel Botrel

Christophe Bernard Texier

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.

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Choisy en Brie, France

Gregory Pierre Lafarge