Turbomachine hollow blade
AssigneeSafran Helicopter Engines
InventorsLaurence Vial, Bruno Frelon, Jérôme Beugniez, Yann Bellot
Life of this patent
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Abstract
Turbomachine hollow blade (11) comprising at least one vane (14) having lateral walls (15) which are intended to guide a flow in a flow path around the vane and which are fixed to a first platform (12) at a first longitudinal end of the vane (14), the vane (14) further comprising an internal cavity between the lateral walls (15), which cavity is intended for passing a vane-cooling fluid, with a fluid inlet opening (19) opening through said first platform (12), characterized in that a gyroid surface network (18) fills at least part of the cavity, being arranged therein so as to guide the cooling fluid, and is in contact with at least part of the lateral walls (15).
Claims14
A turbomachine hollow vane, comprising at least one blade having lateral walls which are intended to guide a flow in a duct around the vane and which are attached on a first platform at a first longitudinal end of the at least one blade,
- the at least one blade further comprising:
- an internal cavity between the lateral walls, the internal cavity is intended for passing a cooling fluid of the at least one blade,
- an opening for an inlet of the cooling fluid opening through said first platform,
- characterised in that a gyroid surface array fills at least one portion of the internal cavity and is arranged to guide the cooling fluid into the internal cavity, and the gyroid surface array is in contact with at least one portion of the lateral walls.
A turbomachine hollow vane, comprising at least one blade having lateral walls which are intended to guide a flow in a duct around the vane and which are attached on a first platform at a first longitudinal end of the at least one blade, the at least one blade further comprising an internal cavity between the lateral walls, the internal cavity is intended for passing a cooling fluid of the at least one blade, with an opening for an inlet of the cooling fluid opening through said first platform, characterised in that a gyroid surface array fills at least one portion of the internal cavity and is arranged to guide the cooling fluid therein and is in contact with at least one portion of the lateral walls,
- wherein the gyroid surface array separating a space of the internal cavity into two separate channels through which the cooling fluid can flow, the lateral walls of the at least one blade form a portion of walls of said two separate channels by intersecting the gyroid surface array.
A turbomachine hollow vane, comprising at least one blade having lateral walls which are intended to guide a flow in a duct around the vane and which are attached on a first platform at a first longitudinal end of the at least one blade, the at least one blade further comprising an internal cavity between the lateral walls, the internal cavity is intended for passing a cooling fluid of the at least one blade, with an opening for an inlet of the cooling fluid opening through said first platform, characterised in that a gyroid surface array fills at least one portion of the internal cavity and is arranged to guide the cooling fluid therein and is in contact with at least one portion of the lateral walls,
- wherein the vane comprises an insert in the cavity and that the gyroid surface array occupies a space located between the insert and the lateral walls of the at least one blade.
Dependencies are inferred from the claim text.