The invention relates to a turbomachine assembly (1) comprising a fan (2) and a booster drum-type part (3), the fan (2) comprising:—blades (20) comprising an airfoil (23) and an extension (30) mounted on and attached to the trailing edge (25) of the airfoil (23),—a fan (2) disc (10) and—a series of inter-blade platforms (16), the extension (30) of each blade (20) extending beyond the downstream face (14) of the fan (2) disc (10) in the direction of the upstream edge (4) of the part (3) and covering, at least partially, the cavity (6) between the fan (2) and the part (3).

When a combination of a vane type of a stator vane and a vane type of a stator vane for one straightening plate is the same as a combination of a vane type of a stator vane and a vane type of a stator vane for the other straightening plate, positions of the first straightening plate side connection portions and the second straightening plate side connection portions of the one straightening plate and the other straightening plate are the same as each other. When the combinations are different from each other, at least one of the positions of the first straightening plate side connection portions of the one straightening plate and the other straightening plate and the positions of the second straightening plate side connection portions of the one straightening plate and the other straightening plate are different from each other.

A seal member (7) is provided between a combustor disposed around a rotor axis and a vane disposed on the downstream side in an axial direction and defining a part of a combustion gas flow passage (Pg) through which combustion gas (G) flows, and seals a gap between the combustor and the vane. The seal member (7) has: an end face (71a) that faces the downstream side in the axial direction so as to face a lateral end face (461) of the vane facing the upstream side in the axial direction; cooling channels (80) through which cooling air is discharged from a plurality of openings (80a) provided in the end face (71a) in an array in a circumferential direction based on the rotor axis; and a clearance forming portion (71b) that protrudes further toward the downstream side in the axial direction than the end face (71a) in which the openings are formed.

An apparatus includes a body, a collar, a fastener and a retainer. The body extends between first and second sides. The collar sealingly engages the first side and extends into an aperture in the body. The fastener engages the second side and extends through the collar to a distal end. The retainer is mated with the fastener at the distal end. The collar and the fastener cooperate to limit rotation therebetween.

A gas turbine that having a flowpath having a rotor assembly that includes: a first rotor wheel supporting a first rotor blade having a platform that defines a first axial section of an inner boundary of the flowpath; a second rotor wheel supporting a second rotor blade having a platform that defines a second axial section of the inner boundary of the flowpath; and an annulus filler that includes an outboard surface that defines at least part of a third axial section of the inner boundary of the flowpath occurring between the first axial section and the second axial section of the inner boundary of the flowpath. The first rotor wheel may include an axial connector for axially engaging a mating surface formed on a radially innermost face of the first rotor blade and a mating surface formed on a radially innermost face of the annulus filler.

The present disclosure provides for a turbine wheel having a blade platform disposed to compliantly secure ceramic turbine blades to a rotatable disk. The platform includes opposing ends to engage a portion of an airfoil of each turbine blade and radial extensions to engage a portion of a root of each turbine blade.

A platform for use between adjacent propulsion rotor airfoils joined to a rotor disk to provide an inner flowpath boundary includes: an axially extending I-beam supporting a radially outer skin having a flowpath surface; the I-beam including an inner I-flange disposed at an inner edge of an axially extending I-web, and an outer I-flange disposed at an outer edge of the I-web; the I-beam including a laterally-extending forward end flange at a forward end of the I-web, and a laterally-extending aft end flange at an aft end of the I-web; and the radially outer skin disposed on top of and joined to the radially outer I-flange such that the forward end flange and the aft end flange abut the outer skin.

An annulus filler is provided for mounting to a rotor disc of a gas turbine engine and bridging the gap between two adjacent blades attached to the rotor disc. The annulus filler is substantially entirely formed from a polymer matrix composite material. It has an outer lid which defines an airflow surface for air being drawn through the engine in an axial airflow direction, and a support structure which is connectable to the rotor disc to support the lid on the rotor disc. The support structure has two support walls extending from opposing lateral sides of the lid to an attachment strap for receiving a hook on the rotor disc, the attachment strap bridging the support walls. In use, under centrifugal loads, the opposing support walls resiliently deform to allow outward radial movement of the lid. Each support wall is thickened in a region neighboring the attachment strap.

A modular turbine blade assembly (10) usable in a gas turbine engine (12) and formed from an airfoil (28) and an independent, modular platform (16) supported by one or more clevis arm supports (14) extending radially inward from the modular platform (16) to a disk is disclosed. The clevis arm support may support the modular platform while a separate dovetail attachment supports the generally hollow airfoil. The clevis arm support (14) may be formed from at least two arms (20, 22) designed to reduce stress from a pin receiving orifice (24) at a distal end (26) of the two arms (20, 22) to the platform (16). The independent arms (20, 22) minimize stress concentrations caused by centrifugal loading in the support. The arms (20, 22) may be modified independently of each other, such as thickness and support angle. The clevis arm support (14) enables use of a modular platform system for the modular turbine blade (10).

A rotor for a turbine engine includes a disk having cavities called primary cavities at its periphery; a plurality of blades each having a root of which the lower part is composed of a bulb locked axially in the primary cavities; a plurality of added platforms, each being arranged between two consecutive blades, wherein the platforms have: a substantially straight plate and a bulb extending radially under the plate, the bulb being locked axially in the secondary cavities arranged at the periphery of the disk, the secondary cavities being positioned between two consecutive primary cavities; a spoiler extending in the axial direction, the spoiler forming an annular sector facing at least two consecutive blades,