An assembly adapted for use in a gas turbine engine or other engine has a carrier component and a blade track segment. The assembly includes a mounting system for coupling the blade track segment to the carrier component. In an illustrative embodiment, the assembly is a turbine shroud segment for blocking gasses from passing over turbine blades included in the gas turbine engine.

A double ring axial seal for a disk and blade; the disk including an array of blade slots at a perimeter of the disk configured to receive a root portion of the blade, the blade includes a platform located between the root portion and an airfoil extending from the platform opposite the root portion, the platform including a receiver with an overhang proximate the root portion and the platform including a hook opposite the receiver proximate the root portion; a disk slot formed on a first side of the disk proximate the array of blade slots; a first axial seal ring coupled with the disk slot and the receiver; the first axial seal ring having a cutout proximate an outer perimeter of the first axial seal ring, the cutout sized to receive the overhang of the blade platform.

A rotor disc for a turbomachine, the disc extending circumferentially around an axis and including a plurality of cells configured to receive blade roots and each cell including an upstream radial wall configured to axially block the blade root in the cell, each cell being connected to an upstream surface of the disc by a ventilation channel of the cell, the ventilation channel including an inlet orifice which opens onto the upstream surface of the disc and an outlet orifice which opens into the cell. An assembly of such a disc, of a plurality of blades and of a downstream retaining ring and a turbomachine including such an assembly.

Turbomachine components and compressors are provided. The turbomachine component includes a platform and a mounting portion that extends from the platform. The mounting portion includes a dovetail received by a slot defined in the turbomachine. The slot includes a floor and a ceiling. The dovetail includes an inner surface and an outer surface. A hole is defined in the dovetail from an inlet at the inner surface to an end wall. The hole has a cylindrical portion and a tapered portion. A mechanical spring is disposed within the hole and in contact with the floor and the end wall such that the outer surface of the dovetail is forced into contact with the ceiling of the slot.

A propulsor fan array having reduced noise emission is disclosed. The propulsor fan array includes a plurality of propulsor fans that collectively generate thrust. Each of the propulsor fans include a blade fan having a plurality of blades. The plurality of blades are tensioned at tips of the plurality of blade fans such that a pitch of the blades during thrust generation is substantially the same as a pitch of the blades at rest. By tensioning the tips of the blades, an angle of the blades is maintained during operation of the propulsor fan thereby reducing noise that may result from changes in the angle of the blades.

A propulsor fan array having reduced noise emission is disclosed. The propulsor fan array includes a plurality of propulsor fans that collectively generate thrust. Each of the propulsor fans include a blade fan having a plurality of blades. The plurality of blades are tensioned at tips of the plurality of blade fans such that a pitch of the blades during thrust generation is substantially the same as a pitch of the blades at rest. By tensioning the tips of the blades, an angle of the blades is maintained during operation of the propulsor fan thereby reducing noise that may result from changes in the angle of the blades.

A rotor and a turbo machine including the same are provided. The rotor includes a disk including a disk slot, a blade including a root member inserted into the disk slot and an airfoil disposed outside the root member in a radial direction of the disk, a locking sheet disposed inside the root member in the radial direction, and a fixing portion disposed inside the root member in the radial direction and configured to fix the locking sheet to the root member.

A rotor and a turbo machine including the same are provided. The rotor includes a disk including a disk slot, a blade including a root member inserted into the disk slot and an airfoil disposed outside the root member in a radial direction of the disk, a locking sheet disposed inside the root member in the radial direction, and a fixing portion disposed inside the root member in the radial direction and configured to fix the locking sheet to the root member.

The invention relates to an assembly for a turbine engine blade, the assembly comprising a fastener (9) defining a well (10) for receiving a blade root (7), and a clamping device (32) for clamping the blade root (7) against the fastener (9) when the blade root (7) is received in the well (10), wherein the clamping device (32) comprises: at least one clamping member (34; 36) suitable for bearing simultaneously on the blade root (7) and on the fastener (9) in the well (10) so as to exert a clamping force on the blade root (7), the clamping member (34; 36) defining a threaded hole, and a resilient layer (44) arranged to bear in the well on the blade root, a rod (38) comprising a thread engaging with the threaded hole so that a rotation of the rod (38) with respect to the clamping member causes a variation in the clamping force exerted by the clamping member on the root.

A rotor and a turbo machine including the same are provided. The rotor includes a disk including a disk slot, a blade including a root member inserted into the disk slot and an airfoil disposed radially outside the root member, and configured to form a cooling cavity between an inner surface of the disk slot and the root member, a lifting part installed in the cooling cavity and configured to press the root member in a radially outward direction, and a supporting part installed in the cooling cavity, disposed in contact with the lifting part, and configured to support the lifting part.