Device for attaching a stator vane to a turbomachine annular casing, turbojet engine incorporating the device and method for mounting the vane

2:

• The device as claimed in claim 1, the fastening means of which consists of a screw.

3:

• The device as claimed in claim 1, the fastening means of which consists of two screws.

4:

• The device as claimed in claim 1, comprising a layer of elastomeric material between the downstream edge of the platform and the bottom of said slot.

5:

• A bypass turbojet engine with upstream fan comprising a set of stator vanes which straighten the stream downstream of the fan rotor and the vanes of which are held inside the fan casing by a device as claimed in claim 1.

6:

• The turbojet engine as claimed in claim 5, the vanes of which are positioned between the fan casing and the main stream casing, the root of the vanes being engaged with clearance in openings formed in said main stream casing and a seal being used to fill said clearance.

7:

• The turbojet engine as claimed in claim 5, in which the vanes and the main stream casing are made of a metal or of a composite.

8:

• A method of mounting a stator vane in a turbojet engine as claimed in claim 5, whereby the vane is engaged via the root in said opening, the vane is tilted in such a way as to engage the downstream edge of the platform in the downstream slot of the circumferential groove, the vane is pivoted about the slot, returning the vane upstream until the upstream edge of the platform enters the groove, and the platform is secured to the casing using the fastening means.

The method as claimed in claim 8, whereby the seal is fitted around the airfoil near the root beforehand.

10:

• The method as claimed in claim 8, whereby a layer of elastomeric material is positioned between the downstream edge of the platform and the bottom of the slot.