Abstract: A turbine blade includes a base and an airfoil. The airfoil includes a skin extending from the base and defining a leading edge and a trailing edge opposite the leading edge. The trailing edge includes an inner edge disposed proximate to the base, an outer edge disposed distal the inner edge, and a tuning region edge disposed between the inner edge and the outer edge. The tuning region edge includes an upper transition edge, a middle transition edge, a lower transition edge, an upper tuning edge, and a middle tuning edge. The upper transition edge extends from the outer edge towards the inner edge. The middle transition edge is disposed between the upper transition edge and the inner edge. The lower transition edge is disposed between the middle transition edge and the inner edge. The upper tuning edge is disposed between the upper transition edge and the middle transition edge, being at least partially closer to the leading edge than the middle transition edge.

Abstract: A turbine includes a stator and a movable rotor, rotating around an axis, in relation to the stator. The rotor comprises at least one disc, the radially outer periphery of which comprises cavities. The rotor further includes blades, each having a blade root axially engaged in a cavity of the disc so as to radially hold the blade on the disc. At least one of the blade roots has an axially flaring shape, with the corresponding cavity having a matching shape so as to axially lock the blade root in the cavity in a first axially oriented direction. Locking means lock the blade root in the cavity in a second axially oriented direction, opposite the first direction.

Abstract: A pump rotor includes a hub, a back plate and a plurality of blades extending from the hub and disposed on the back plate. Each of the plurality of blades has an outer surface essentially parallel to a rotational axis of the hub, and a first end adjacent the hub and a second end distal from the hub, the first end having a height from the planar surface that is less than a height from the planar surface of the second end. The plurality of blades is configured to cause a synchronized central column of flow.

Abstract: There is disclosed a vane segment for a gas turbine engine. The vane segment includes vanes extending radially from inner ends to outer ends. The vanes have leading edges, trailing edges, and chords extending from the leading edges to the trailing edges. A platform circumferentially extends around the central axis. The platform has an inner face facing the central axis and an opposed outer face. The inner face of the platform is connected to the outer ends of the vanes. Ribs protrude away from the outer face and have lengths extending along the outer face.

Abstract: There is provided a rotary machine including a rotary shaft configured to rotate around an axis; rotor blades; a casing surrounding the rotor blades radially outside the rotor blades, and in which a recessed portion accommodates tips of the rotor blades; a sealing portion extending from one of a bottom portion of the recessed portion and the tip of the rotor blade, and having a clearance with the other; and a variable breaker installed in the casing and is capable of being displaced between a protrusion position where the variable breaker protrudes into the recessed portion and an accommodation position where the variable breaker is accommodated in the casing.

Abstract: An annular shroud assembly for a gas turbine engine is provided. The annular shroud assembly includes a plurality of first shroud segments having a same first arcuate length within a tolerance, at least one second shroud segment having a second arcuate length different than the first arcuate length and outside the tolerance, a plurality of first intersegment gaps between adjacent first segments, the first intersegment gaps having a circumferential dimension within a desired controlled range of dimensions, and at least two second intersegment gaps between opposed ends of the second segment and adjacent first segment. The first and second intersegment gaps are within the desired controlled range. Methods for controlling intersegment gaps between a plurality of shroud segments forming an annular shroud assembly and for forming such annular shroud assembly are also provided.

Abstract: A fluid machine including a rotating shaft that extends parallel to a power generation shaft of a power generation unit, and that has an end coupled to the power generation shaft; a multiple rotors that are provided on the rotating shaft so as to be able to rotate in a circumferential direction of the rotating shaft, and that are arranged so as to be spaced in a rotational axis direction parallel to the axis of the rotating shaft; and a differential mechanism that is provided between a pair of rotors lying adjacent to each other in the rotational axis direction, and that combines the rotational force from each of the pair of rotors and transmits the rotational force to the rotating shaft.

Abstract: A compressor diffuser for a gas turbine engine includes a plurality of diffuser passages including a first portion having a radial component, a second portion having an axial component, and a curved portion fluidly connecting the first portion and the second portion. The diffuser passages having a throat located within the first portion thereof, and including a first subset of passages and a second subset of passages. The throats of the first subset of passages have a first throat area that is different than a throat area of the throats of the second subset of passages.

Abstract: A tip sealing structure for a blade includes a casing having an inner circumferential surface facing the blade; a blocking groove formed in the inner circumferential surface of the casing; and a movable seal provided on a tip of the blade and configured to move in a depth direction of the blocking groove. Since the seal is configured to move into the blocking groove, tighter sealing at the tip of the blade can be accomplished. A seal bracket of the moveable seal encloses a movement space open at one end and includes a seal stop formed at the open end. A brush body including top and bottom crossbars is disposed partially within the seal bracket, such that movement of the moveable seal is limited by the bottom crossbar being stopped by the seal stop. A first brush seal is mounted on the brush body and positioned in the blocking groove.

Abstract: An assembly including a sector of fixed blades for turbomachine distributor including at one circumferential end a protuberance and at another circumferential end a contact surface, such that the protuberance of a sector arrives opposite the contact surface of another adjacent sector, a detachable cap including a surface with anti-wear material, configured to be engaged detachably on the protuberance of the sector, such that the anti-wear material is in contact with the contact surface of the other sector.

Abstract: Baffles for gas turbine engines are provided. The baffles include a baffle body extending between a first end and a second end, a chamfered surface formed at at least one corner of the baffle body, wherein the chamfered surface extends from the first end to the second end, and a plurality of baffle holes formed in the chamfered surface.

Abstract: Centralizer apparatuses attached around a unison ring include rub buttons at inner ends of stud attached to and spaced apart from the unison ring and include rolling bearings. Each rolling bearing rotatably trapped within bearing chamber in bearing receptacle at inner end of stud. Tip cap includes bearing aperture trapping rolling bearing within bearing chamber. Rolling bearing extends partially through bearing aperture. Rolling bearing may be spring loaded within chamber by spring between the bearing receptacle and the rolling bearing. Stud may extend through and may be threaded into mounting aperture in unison ring and nut may be threaded onto outer end of stud. Variable stator vanes rotatably mounted to a casing and connected to vane crank arms connected to the unison ring mounted exterior to casing.

Abstract: In an axial turbomachine low-pressure compressor, the compressor, or booster, includes a first vane with an intrados surface, a second vane with an extrados surface, an inter-vane passage with a guiding surface, which connects the intrados surface to the extrados surface delimiting an annular vein, and which has a bulge and a recess forming a so-called 3D contouring geometry, or non-axisymmetric surface. The guiding surface includes an axially symmetrical or substantially flat zone, which axially extends through the inter-vane passage so as to separate the recess from the bulge.

Abstract: A rotor blade locking assembly for locking a rotor blade in a deployed position. The rotor blade locking assembly comprises a locking mechanism configured to be coupled to a blade grip. The locking mechanism comprises a latch and an actuator configured to cause the latch to move between an unlocked position and a locked position. The assembly comprises a locking plate configured to be coupled to the rotor blade. The locking plate comprises a bearing surface configured to bear against a contact surface of the latch, when the latch is in the locked position.

Abstract: A rotary machine includes a first impeller which rotates about an axis integrally with a rotating shaft, and a casing which covers the rotating shaft and the first impeller. The first impeller includes a circular-disk-shaped first disk part centered on the axis, a plurality of blade parts which extend from a surface facing a first side of the first disk part in an axial direction toward the first side in the axial direction and disposed at intervals in a circumferential direction, and an extension shaft which extends from a surface facing a second side of the first disk part in the axial direction toward the second side in the axial direction centered on the axis. An end portion of the extension shaft on the second side in the axial direction is connectable to an end portion of the rotating shaft on the first side in the axial direction.

Abstract: An airfoil assembly for a turbo machine, the airfoil assembly including an airfoil defining a leading edge and a trailing edge, and further defining ends separated along a span of the airfoil; a shaft extended from the end of the airfoil; and a button surrounding at least a portion of the end of the airfoil, the button comprising a composite material.

Abstract: A wheel assembly for a gas turbine engine includes a disk, a blade-attachment system, and a plurality of blades. The disk is configured to rotate about an axis during operation of the gas turbine engine. The blade-attachment system is configured to couple the plurality of blades with the disk for rotation therewith.

Abstract: An aerofoil having a leading edge and a trailing edge, the leading edge including a plurality of slits extending toward the trailing edge, such that the leading edge is defined by alternating peaks and troughs. Each peak extends in a generally spanwise direction and defines a peak width, each peak being separated from an adjacent peak in the spanwise direction by a trough. Each trough extends in the generally spanwise direction and is spaced in a chordwise direction from the peak, each trough defining a trough width. A ratio of the peak width to the trough width is between 4:1 and 10:1.

Abstract: A gas turbine includes a housing; a rotor rotatably provided in the housing; a turbine blade to receive rotating force from combustion gas and rotate the rotor; a turbine vane to guide a flow of the combustion gas toward the turbine blade, the turbine vane having a turbine vane cooling passage for delivering cooling fluid to an inner wall of the turbine vane; and an impingement plate installed in the turbine vane cooling passage, the impingement plate having a plurality of injection holes through which the cooling fluid is injected onto the inner wall of the turbine vane, the injection holes formed at predetermined locations of the impingement plate, wherein the injection holes are formed differently depending on locations of the injection holes. A temperature gradient or thermal stress may be prevented from occurring in the turbine vane that is cooled by cooling fluid ejected from the impingement plate.