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US 2019/0240725 A1Published application
Turbomachine blade cooling circuit
AssigneeSafran Aircraft Engines
InventorsCoralie Cinthia Guerard, Vincent Marc Herb, Jun Ni, Joseph Toussaint Tami Lizuzu, Matthieu Jean Luc Vollebregt
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Abstract
The present disclosure is generally directed to a core configured for the manufacturing of a turbine engine blade by lost-wax casting. The core includes a first convex curved outer face and a second concave curved outer face. The first and second faces have a plurality of recesses, each recess including a spherical portion.
Claims9
A core configured for manufacturing a turbine engine blade by lost-wax casting, the core comprising:
- a first convex curved outer face having a plurality of recesses, each recess comprising a spherical portion;
- and
- a second concave curved outer face having a plurality of recesses, each recess comprising a spherical portion,
- wherein each recess of each face is defined at least partially by an axis of symmetry, the axes of symmetry of the spherical portions of the first face being parallel to a first direction defined, in a transversal plane, by the bisector of the angle formed by the intersection of:
- a first tangent to the first face at the first point of junction between the first face and a first connection between the first and second faces;
- and
- a second tangent to the first face at the second point of junction between the first face and a second connection between the first and second faces,
- wherein the first and second tangents are defined in the transversal plane, and wherein the first and second points of junction are opposite one another.
5 more elements
Dependencies are inferred from the claim text.