A turbine rotor (50) for aircraft turbomachinery, in particular a counter rotating impeller, comprises:-The rotor disk (52),-The circovirus (54) extends around the disk, and-A blade (56) mounted between the disk and the virus,The utility model is characterized in that the bottom of each blade comprises two legs (66) fixed on the valve disc, and the legs are respectively arranged upstream and downstream of the valve disc wall (80) relative to the shaft, The upstream arranged pawl is engaged with the first convex part (70) of the disc, and the pawl is configured to fit with the peripheral edge (74) of the first convex part through a stop, The downstream disposed pawl is engaged with a second raised portion (72) of the disc, and the pawl is configured to mate with a peripheral edge (74) of the second raised portion by a stop device.Abstract figure: Figure 3
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