The present disclosure relates generally to a fan blade spacer including a conduit disposed within a fan blade spacer composed of an elastically deformable material.

A method for mounting rotor blades on a rotor disk along a predetermined pitch circle diameter in such a way that adjacent rotor blades, when properly mounted on the rotor disk and in the cold state, are clamped against each other with a predetermined preload. A clamping device which performs such a method has a plurality of clamping elements which are arranged in a uniformly distributed manner around a central axis, the number of which corresponds to the number of rotor blades to be mounted on the rotor disk and which in each case are designed for the locating of a rotor blade, wherein the clamping elements are moveable radially, exerting a radially inwardly directed force.

The present invention relates to a system and method for joining adjacent sections of a compressor diaphragm. A splitline jumper is positioned within a recessed portion of a seal ring segment of the adjacent compressor diaphragms. The splitline jumper is sized and oriented so as to prevent axial movement of the compressor diaphragms relative to each other and also to prevent rotational movement of the seal ring relative to the diaphragm.

The present invention relates to a system and method for joining adjacent sections of a compressor diaphragm. A splitline jumper is positioned within a recessed portion of a seal ring segment of the adjacent compressor diaphragms. The splitline jumper is sized and oriented so as to prevent axial movement of the compressor diaphragms relative to each other and also to prevent rotational movement of the seal ring relative to the diaphragm.

The present application provides a steam turbine. The steam turbine may include a number of rotor wheel slots, a number of buckets positioned in the rotor wheel slots, and a radial support assembly positioned between each of the buckets and each of the rotor wheel slots. The radial support assembly may include one or springs and one or more shims.

A nozzle assembly includes at least one stationary nozzle and an outer ring having a predefined shape. The outer ring includes at least one groove defined therein configured to receive at least a portion of the at least one stationary nozzle. The nozzle assembly also includes an attachment member coupled between the stationary nozzle and the outer ring. The attachment member has a first configuration at a first nozzle assembly operating temperature a second configuration at a second nozzle assembly operating temperature.

A nozzle assembly includes at least one stationary nozzle and an outer ring having a predefined shape. The outer ring includes at least one groove defined therein configured to receive at least a portion of the at least one stationary nozzle. The nozzle assembly also includes an attachment member coupled between the stationary nozzle and the outer ring. The attachment member has a first configuration at a first nozzle assembly operating temperature a second configuration at a second nozzle assembly operating temperature.

According to an aspect of the present invention, a turbine apparatus includes a shaft; a turbine disk provided on the shaft and having a plurality of protrusions protruding in a direction of the shaft; blades provided on the turbine disk; a support plate provided on the turbine disk and having a plurality of latching portions engaged with the plurality of protrusions; a plurality of first fixing blocks located between the plurality of latching portions; and a second fixing block located between the plurality of protrusions and fixed to the plurality of first fixing blocks, wherein a width of a space where the second fixing block is located, from among spaces between the plurality of protrusions, is less than a width of a space where the plurality of first fixing blocks are located, from among spaces between the plurality of latching portions.

According to an aspect of the present invention, a turbine apparatus includes a shaft; a turbine disk provided on the shaft and having a plurality of protrusions protruding in a direction of the shaft; blades provided on the turbine disk; a support plate provided on the turbine disk and having a plurality of latching portions engaged with the plurality of protrusions; a plurality of first fixing blocks located between the plurality of latching portions; and a second fixing block located between the plurality of protrusions and fixed to the plurality of first fixing blocks, wherein a width of a space where the second fixing block is located, from among spaces between the plurality of protrusions, is less than a width of a space where the plurality of first fixing blocks are located, from among spaces between the plurality of latching portions.

The present invention relates to a rotor (1) of a turbomachine turbine, comprising a rotor disc (2) and a plurality of blades (3) distributed at its periphery, said rotor disc (2) comprising a plurality of mainly axial cells (23), each blade (3) comprising a root (32), retained in one of the cells (23) of said rotor disc, each root being dimensioned so as to form a space (4) between the bottom of the cell (23) and the radially inner face (324) of the root. This rotor is remarkable in that said root comprises a mainly axial blind hole (5) opening onto the upstream face of the root and a plurality of mainly radial air ejection orifices (6), each air ejection orifice (6) opening into said blind hole (5) and onto the radially inner face (324) of the root located facing the bottom of the cell (23).