Safran Aircraft Engines

Cis Guy Monique De Maesschalck

Remi Philippe Oswald Olive

Sergio Lavagnoli

Guillermo Paniagua

A method for modeling at least one portion of a bathtub of a blade, the method including parametrizing a volume representing the bathtub portion as a set of markers extending from a reference transverse surface of the blade, the blade physically including the markers, and each marker associated with an elementary surface selected among a plurality of elementary surfaces forming a partition of at least one portion of the reference transverse surface; and defined by a marker height relative to the reference surface; determining optimized values of the marker heights relative to a given aerodynamic and/or thermal criterion; reproducing, on an interface of the device, the values thus determined.

Method for modelling a bathtub of a blade

The invention relates to a turbine blade () of a turbine engine including an upper surface (), a lower surface (), a leading edge (), a trailing edge (), and a squealer tip () at the top thereof, wherein said squealer tip () is defined by a rim () and comprises at least one inner rib () that is spaced apart from the rim () defining the squealer tip (). The invention is characterized in that said inner rib () is shaped to define, inside the squealer tip, a cavity () inside of which the passage of leak flows () is limited, wherein an upstream opening () is made in the rim () at the leading edge (), and a downstream opening () is made in the rim () at the trailing edge ().

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Kortrijk, Belgium

Cis Guy Monique De Maesschalck