Vane for aircraft turbine engine receiver, provided with two hollow cores lodged in one another
View Patent ↗The invention relates to a vane ( 200 ) for an aircraft turbine engine receiver. The vane is a blade ( 14 ) having an aerodynamic shell ( 24 ) enveloping a principal hollow structure core ( 34 ) extending in the direction of wingspan of the blade. The vane further has a secondary structural assembly ( 34 ′) enveloped by the hollow core ( 34 ) and extending also in the direction of wingspan, as well as a first coating made of shock-absorbing material ( 50 ) arranged between a longeron ( 44 ) of the core ( 34 ) and the assembly ( 34 ′), and a second coating made of shocking-absorbing material ( 52 ) arranged between another longeron ( 38 ) of the core ( 34 ) and this same assembly ( 34 ′).
1. A vane for an aircraft turbine engine receiver comprising a blade part having an aerodynamic shell forming the intrados and the extrados of the blade, said shell enveloping a principal hollow structural core extending in the direction of wingspan of the blade and formed by means of a first longeron oriented towards a leading edge of the shell, a second longeron oriented towards a trailing edge of the shell, a third longeron oriented towards the intrados and a fourth longeron oriented towards the extrados,
characterised in that it further comprises a secondary structural assembly enveloped by said principal hollow structural core and extending also in the direction of wingspan of the blade, as well as a first coating made of shock-absorbing material arranged between the fourth longeron and said secondary structural assembly, and a second coating made of shock-absorbing material arranged between said first longeron and this same assembly.
2. The vane as claimed in claim 1 , characterised in that said secondary structural assembly at least partially forms a secondary hollow structural core.
3. The vane as claimed in claim 2 , characterised in that said structural assembly fully forms said secondary hollow structural core by means of a first longeron oriented towards the leading edge of the shell, a second longeron oriented towards a trailing edge of the shell, a third longeron oriented towards the intrados and a fourth longeron oriented towards the extrados.
4. The vane as claimed in claim 3 , characterised in that said principal and secondary cores are arranged in contact with one another, at the level of their second and third longerons.
5. The vane as claimed in claim 1 , characterised in that said shock-absorbing material is foam, or a material with a honeycomb structure.
6. The vane as claimed in claim 1 , characterised in that it comprises also a coating made of shock-absorbing material arranged on said fourth longeron of the principal core, externally to the latter, as well as a coating made of shock-absorbing material arranged on said first longeron of the principal core, externally to the latter.
7. The vane as claimed in claim 1 , characterised in that said hollow principal core and said secondary structural assembly are each made in a single piece, preferably of composite material.
8. A turbine engine for an aircraft comprising a receiver equipped with a plurality of vanes as claimed in claim 1 .
9. The turbine engine as claimed in claim 8 , characterised in that it is a turbojet, a propjet engine, or an open-rotor.
10. An aircraft comprising a plurality of turbine engines as claimed in any one of claims 8 and 9 .