Moving blade for a turbine of a turbine engine, comprising a stilt equipped with projections for radially retaining the blade
AssigneeSafran Aircraft Engines
InventorYannick Durand
Life of this patent
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Abstract
A blade for a turbine rotor wheel of an aircraft turbomachine, successively comprising a blade root, a stilt, a platform, as well as a vane, the blade root being intended to be housed in a blade housing groove provided on a peripheral portion of a turbine disc, the housing groove being defined between two directly consecutive disc teeth. According to the invention, on each of the two sides thereof, in the circumferential direction of the blade, the stilt is provided with a protrusion for radially retaining the blade, each protrusion comprising a stop surface which is radially inwardly directed and intended to cooperate with a radially outer surface of a disc tooth.
Claims8
A turbine rotor wheel of an aircraft turbomachine, comprising a turbine disc including a peripheral portion provided with grooves for housing blades, the grooves succeeding each other in a circumferential direction of the wheel, said wheel also comprising a plurality of the blades, a root of each respective blade being housed in a respective one of the grooves of the peripheral portion of the disc, each blade comprising successively, in a radial direction of a height of the blade relative to an axis of the wheel, the blade root, a stilt, a platform, as well as a vane, the blade root configured to be housed in the respective blade housing groove provided on the peripheral portion of the turbine disc of the rotor wheel, said housing groove being defined between two disc teeth which are directly consecutive in the circumferential direction about the axis,
- the platform comprising a first surface as well as a second surface which is opposite to the first surface in the radial direction, the first surface, from which the vane extends, configured to delimit a gas flow path, and the second surface, from which the stilt extends, partially delimiting a first and a second cavity arranged on either side of the stilt in the circumferential direction,
- wherein at each of the two sides thereof, in the circumferential direction, the stilt is provided with a protrusion for radially retaining the blade, each protrusion comprising a stop surface which is radially inwardly directed and configured to cooperate with a radially outer surface of one of the disc teeth, wherein each protrusion is positioned between a radially inner edge of one of a first and a second stiffening wall and the blade root of the respective blade, and
- wherein each stop surface defines a clearance with the radially outer surface of the associated disc tooth thereof, such that the protrusions do not contact the disc teeth in operation of the turbine rotor wheel.
Dependencies are inferred from the claim text.