CPC F01D 5/3023 (2013.01) [F01D 1/26 (2013.01); F01D 5/08 (2013.01); F01D 5/3053 (2013.01); F02C 3/067 (2013.01); F05D 2240/15 (2013.01)] | 8 Claims |
1. A turbine rotor wheel for an aircraft turbomachine, comprising:
a rotor disc extending about an axis X,
an annular shroud extending about said axis X and said disc, and
vanes arranged between said disc and said shroud and comprising roots attached to said disc, and summits attached to said shroud,
wherein the root of each of the vanes comprises two tabs for attachment to the disc, the tabs being arranged respectively upstream and downstream of a wall of the disc, with respect to said axis, each tab arranged upstream being engaged in a first recess of an upstream face of the disc and being configured to cooperate by abutment with a peripheral edge of this first recess, each tab arranged downstream being engaged in a second recess of a downstream face of the disc and being configured to cooperate by abutment with a peripheral edge of this second recess, said first and second recesses being located on two sides of said wall, said wall comprising orifices oriented parallel to said axis X and aligned with orifices of said tabs, attachment elements passing through the orifices of the tabs and of the wall, and at least some of the orifices of the tabs and of the wall have an elongated or oblong shape and comprise a longest dimension oriented in a radial direction with respect to said axis X.
|