Device for axially retaining moving blades of an LP turbine in the slots of a rotor disc of the LP turbine and method for assembling said moving blades
AssigneeSafran Aircraft Engines
InventorSimon Jean-Marie Bernard Cousseau
Life of this patent
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Abstract
A device for axially retaining a moving blade of a low-pressure turbine in a recess of a rotor disc of axis of the turbine. This device includes a stop part intended to extend between an upstream face of a blade root of the moving blade and a downstream face of the root of the moving blade, the stop part including a first wall which forms an end stop for the upstream face of the blade root, a second wall which forms an end stop for the downstream face of the blade root, and a connection surface intended to extend between the first and the second wall along a radially inner end face of the blade root.
Claims10
A turbomachine rotor assembly comprising a rotor disc to rotate about an axis, the rotor disc having slots hollowed out at its periphery and moving blades mounted into the slots of the disc, two circumferentially adjacent slots around the disc each delimiting a tooth of the disc, and a plurality of stop pieces to be extended between an upstream face of a blade root of the moving blade and a downstream face of said blade root of the moving blade, said stop pieces including:
- a first wall which forms a stop for the upstream face of the blade root,
- a second wall which forms a stop for the downstream face of the blade root, and
- a connecting surface to be extended between the first and second walls along a radially inner end face of the blade root,
- each stop piece being for axially holding a moving blade in a corresponding slot of the disc, and,
- an annular piece for blocking the stop pieces against the disc,
- the first wall of each stop piece circumferentially extending so as to be in contact with at least one upstream face of a tooth of the rotor disc,
- a plurality of stop pieces each disposed in a slot of the disc and configured so that their first walls are circumferentially arranged end to end, about said axis, and
- a retaining ring attached to the disc and mounted to the entire circumference of the rotor disc against the first walls of the stop pieces so as to hold the stop pieces in position in the disc slots.
A method for mounting moving blades into slots of a rotor disc of a low pressure turbine of a turbomachine rotor assembly comprising the rotor disc to rotate about an axis, the rotor disc having slots hollowed out at its periphery and the moving blades mounted into the slots of the disc, two circumferentially adjacent slots around the disc each delimiting a tooth of the disc, and a plurality of stop pieces to be extended between an upstream face of a blade root of the moving blade and a downstream face of said blade root of the moving blade, said stop pieces including:
- a first wall which forms a stop for the upstream face of the blade root,
- a second wall which forms a stop for the downstream face of the blade root, and
- a connecting surface to be extended between the first and second walls along a radially inner end face of the blade root,
- each stop piece being for axially holding a moving blade in a corresponding slot of the disc, and,
- an annular piece for blocking the stop pieces against the disc,
- the first wall of each stop piece circumferentially extending so as to be in contact with at least one upstream face of a tooth of the rotor disc,
- a plurality of stop pieces each disposed in a slot of the disc and configured so that their first walls are circumferentially arranged end to end, about said axis, and
- a retaining ring attached to the disc and mounted to the entire circumference of the rotor disc against the first walls of the stop pieces so as to hold the stop pieces in position in the disc slots,
- the method comprising, for each moving blade:
- installing one of the stop pieces of the turbomachine rotor assembly against the radially inner end face of the blade root, and
- installing the moving blade equipped with the stop piece in the slot of the rotor disc.
Dependencies are inferred from the claim text.