Seal for a platform in the rotor of a turbine engine
View Patent ↗A seal for an intermediate platform provided between two adjacent blades in the rotor of a turbine engine, the seal having an elongate shape with an upstream end and a downstream end, and including transversally, in the direction of the width thereof, a contact portion, an attachment portion, and a flexible portion between the attachment portion and the contact portion. The cross section of the seal has an open-ended shape between the two ends thereof.
1. A seal for an intermediate platform between two adjacent blades in a rotor of a turbine engine, the seal being of elongate shape with an upstream end and a downstream end, the seal comprising:
transversely, widthwise, a contact portion, an attachment portion, and a flexible portion between the attachment portion and the contact portion,
wherein a cross section of the seal has a changing shape between the upstream end and the downstream end,
wherein the seal presents an upstream zone and a downstream zone between the upstream end and the downstream end,
wherein a profile of the cross section of the seal is constant throughout the upstream zone, and
wherein a cross section of the contact portion presents a bulbous shape, and
wherein a profile of the cross section of the seal is not constant in the downstream zone, a width of the flexible portion in the downstream zone being less than a width of the flexible portion in the upstream zone, and a surface area of the contact portion in the downstream zone being less than a surface area of the contact portion in the upstream zone.
2. The seal as claimed in claim 1 , wherein the cross section of the contact portion has a circular shape.
3. The seal as claimed in claim 1 , wherein at least one of the upstream end or the downstream end is tapered.
4. An intermediate platform of a turbine-engine rotor comprising a seal as claimed in claim 1 at least along one longitudinal lateral edge.
5. A platform arranged so as to be mounted axially onto a rim of a rotor, the platform presenting a diameter that is greater at first axial end than at a second axial end and including a seal at least along one longitudinal lateral edge as claimed in claim 1 , a smallest cross section of the seal being provided on a side of the platform having the larger diameter.
6. The platform as claimed in claim 5 , with an upstream axial end and a downstream axial end with a diameter greater than that of the upstream axial end, and the upstream zone of the seal having a length of between half and two thirds of a total length of the seal, the cross section of the seal in the downstream zone reducing in the downstream direction.
7. The platform as claimed in claim 6 , arranged to be mounted on a fan rotor of a turbojet.
8. A turbine-engine rotor comprising intermediate platforms as claimed in claim 6 .
9. A rotor of a fan of a turbojet comprising intermediate platforms according to claim 6 .
10. The seal as claimed in claim 1 , wherein the upstream zone of the seal has a length of between one half and two thirds of a total length of the seal.
11. The seal as claimed in claim 1 , wherein a shape and dimension of the attachment portion in the downstream zone is the same as a shape and dimension of the attachment portion in the upstream zone.