Abstract: The turbomachine subassembly comprises:—at least one tow-pressure nozzle ring, the nozzle ring comprising a root (38) integral with the nozzle ring;—a clamp (40) configured so as to fasten the root to a casing of the turbomachine; and—at least two pads (150) interposed between the root and the clamp, each pad being assembled in a form-fitting manner with one of either the root or the clamp.

Abstract: A method for refitting blade shrouds of a rotor wheel in an aircraft turbomachine is described. The rotor wheel has a disc bearing blades that each have an airfoil extending between a root and a shroud, the shroud of each blade having lateral edges comprising including shapes complementary to the lateral edges of the shrouds of the adjacent blades. The lateral edges of the shrouds are interlocked in engagement with one another such that anti-Wear coatings of these edges are in contact With one another in a desired interlocking engagement position, and at least one of the lateral edges of at least one of the shrouds being able to be disengaged from the lateral edge of an adjacent shroud in an undesired disengagement position. The method includes, when an undesired disengagement position is detected, a step of inserting a re-engagement device into the turbomachine.

Abstract: A turbomachine rotor blade includes a radially outer end equipped with a heel, the heel being provided with at least one sealing wiper, the or each sealing wiper projecting beyond the heel along a first axis, the first axis being at ±15° with respect to a radial direction, and extending along a second axis, substantially perpendicular to the first axis, between a first upper-surface end and a second lower-surface end, the or each sealing wiper having a first upstream side and a second downstream side as well as a radially outer surface, wherein the or each sealing wiper includes a base attached to the heel and an end piece removably interlocked with the base.

Abstract: The invention relates to a movable blade made of aluminum and titanium alloy, for a turbojet engine turbine comprising a vane and at least one root at a distal end of the vane. The root has at least one azimuthal contact surface with another directly adjacent blade. A hard abrasion-resistant material, called wear-resistant material, is deposited onto the at least one azimuthal contact surface. A cavity is produced in said at least one azimuthal contact surface, the wear-resistant material being deposited in the cavity.

Abstract: An assembly includes: a movable blade for a turbomachine including a tip; and a removable part including an anti-wear material, configured to be attached removably to an edge of the tip to limit wear of the tip.

Abstract: A turbomachine rotor blade includes a radially outer end equipped with a heel, the heel being provided with at least one sealing wiper, the or each sealing wiper projecting beyond the heel along a first axis, the first axis being at ±15° with respect to a radial direction, and extending along a second axis, substantially perpendicular to the first axis, between a first upper-surface end and a second lower-surface end, the or each sealing wiper having a first upstream side and a second downstream side as well as a radially outer surface, wherein the or each sealing wiper includes a base attached to the heel and an end piece removably interlocked with the base.

Abstract: The invention relates to an assembly comprising: a movable blade (100) for a turbomachine comprising a root (130), a removable part (300) comprising an anti-wear material, configured to be attached removably to an edge of the root (130) to limit wear of the root (130).