Safran Aircraft Engines

Snecma

Esteban Bernardos-Chamagne

Matthieu Jean Luc Vollebregt

Benjamin Lukowski

Matthieu Jean Vollebregt

The present invention relates to a turbomachine component () or collection of components comprising at least a first and a second blade (I,E) and a platform () from which the blades (I,E) extend, characterized in that the platform () has a non-axisymmetric surface (S) bounded by a first and a second end plane (PS, PR) and defined by at least two class C construction curves each one representing the value of a radius of said surface (S) as a function of a position between the pressure face of the first blade (I) and the suction face of the second blade (E) in a plane substantially parallel to the end planes (PS, PR), these including at least one upstream curve and one downstream curve; each construction curve being defined by at least one pressure face control end point and one suction face control end point such that: &#x2014;the tangent to the downstream curve at the suction face control end pointis inclined by at most 5&#xb0;; &#x2014;any other tangent to a construction curve at a control end point is inclined by at least 5&#xb0;.

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Moissy-Cramayel, France

Esteban Bernardos-Chamagne