Abstract: A turbine blade for a turbine engine, including an aerofoil and a platform. The platform includes an internal channel having a suction opening which opens on a first surface of an upstream portion of the platform, this first surface defining a primary duct. The internal channel includes an ejection opening which opens on a second surface of a downstream portion of the platform, this second surface defining a purge cavity. The internal channel makes it possible to suck in a part of a fluid circulating in the primary duct so as to reduce the intensity of secondary flows which result from friction of the fluid on the first surface.

Abstract: 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.

Abstract: The invention relates to a turbine blade (1) of a turbine engine including an upper surface (11), a lower surface (12), a leading edge (13), a trailing edge (14), and a squealer tip (2) at the top thereof, wherein said squealer tip (2) is defined by a rim (2a) and comprises at least one inner rib (3) that is spaced apart from the rim (2a) defining the squealer tip (2). The invention is characterized in that said inner rib (3) is shaped to define, inside the squealer tip, a cavity (4) inside of which the passage of leak flows (5) is limited, wherein an upstream opening (131) is made in the rim (2a) at the leading edge (13), and a downstream opening (141) is made in the rim (2a) at the trailing edge (14).

Abstract: A turbomachine turbine blade includes a suction face, a pressure face, a leading edge and a trailing edge as well as a squealer at the tip thereof. The squealer tip includes at least one internal rib that extends from a point of attachment of the rim of the squealer on the suction-face side to a point of attachment of the rim of the squealer on the pressure-face side, and includes a portion for absorbing the load of leakage flows which extends from the suction face and a deflector-forming portion which extends the load absorber portion with an inflection and guides the leakage flows toward the pressure face.

Abstract: The invention relates to a turbine blade (1) of a turbine engine including an upper surface (11), a lower surface (12), a leading edge (13), a trailing edge (14), and a squealer tip (2) at the top thereof, wherein said squealer tip (2) is defined by a rim (2a) and comprises at least one inner rib (3) that is spaced apart from the rim (2a) defining the squealer tip (2). The invention is characterized in that said inner rib (3) is shaped to define, inside the squealer tip, a cavity (4) inside of which the passage of leak flows (5) is limited, wherein an upstream opening (131) is made in the rim (2a) at the leading edge (13), and a downstream opening (141) is made in the rim (2a) at the trailing edge (14).

Abstract: A turbomachine turbine blade includes a suction face, a pressure face, a leading edge and a trailing edge as well as a squealer at the tip thereof. The squealer tip includes at least one internal rib that extends from a point of attachment of the rim of the squealer on the suction-face side to a point of attachment of the rim of the squealer on the pressure-face side, and includes a portion for absorbing the load of leakage flows which extends from the suction face and a deflector-forming portion which extends the load absorber portion with an inflection and guides the leakage flows toward the pressure face.