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 method may include: in a used metal turbomachine blade including a root including a shank, a platform coupled to the shank and an airfoil coupled to the platform, removing the airfoil, leaving a remaining base including the platform, the shank and the root. The method may also form a radially extending opening through the platform into the shank, and insert a ceramic shank nub extending from a ceramic airfoil into the radially extending opening of the remaining base. The ceramic airfoil is fixedly attached to the remaining base. The method allows reuse of the metal shank while providing the lower cooling requirements of a ceramic airfoil.

To provide an axial flow turbine that can reduce circumferential pressure differences to reduce loss. The axial flow turbine includes: stator blades arrayed in the circumferential direction; and a diaphragm inner ring having an outer circumferential surface that interconnects the stator blades on their inner-circumference side and constitutes a wall surface of a main flow path. The outer circumferential surface of the diaphragm inner ring has depressed portions. Each depressed portion is formed in an area that is on the downstream side of a throat where the distance between a suction surface of one stator blade of a pair of adjacent blades and a pressure surface of other stator blade of the pair of adjacent blades becomes the shortest, and that lies in the circumferential direction within a range of a throat position on the suction surface of the one stator blade to a downstream edge position of the one stator blade. The area includes a downstream edge position of the outer circumferential surface in the axial direction.

A rotor of a steam turbine includes a plurality of rotor blades attached to a disk portion and a key configured to restrict movement of each of the plurality of rotor blades in an axial direction. The disk portion includes a blade embedding groove and a circumferential groove. The plurality of rotor blades include a first rotor blade and a second rotor blade adjacent to the first rotor blade on one side in a circumferential direction. A platform of the first rotor blade includes an access groove communicating with the circumferential groove, and a platform of the second rotor blade includes a second side surface facing a first side surface in the circumferential direction and a key accommodating groove communicating with the access groove in the circumferential direction. A key is arranged in the circumferential groove and the key accommodating groove.

A compressor disc for a compressor of a gas turbine engine includes a circumferentially extending groove for receiving blade roots of a plurality of compressor blades. The circumferentially extending groove includes a planar surface offset into the groove.

The present invention describes a ring fastener (10) comprising a discontinuous band (11) having a first end (14) and a second end (16). The first end (14) comprises a pair of spaced-apart elongate finger members (15a,15b) (having a first finger member (15a) and a second finger member (15b)), and the second end (16) comprises an elongate tongue member (17). The finger members (15a,15b) and the tongue member (17) are interlockable, such that when interlocked, the band (11) comprises a continuous circumference. The ring fastener (10) further comprises a closed configuration wherein the finger members (15a,15b) and the tongue member (17) are substantially aligned with a circumferential surface (13) of the band (11); and an open configuration wherein the first finger member (15a) is radially and/or axially deflected from its substantially aligned position, so that it is angled with respect to the circumferential surface (13) of the band (11). The invention also describes a method of assembling a bore (40) and a component (42), and the use of such an assembly.

A blade has an airfoil extending radially outwardly of a dovetail. The dovetail has edges that will be at circumferential sides of the blade when the blade is mounted within a rotor. A bottom surface of the dovetail will be radially inward when the rotor blade is mounted in a rotor, and is formed such that a circumferentially central portion of the bottom surface is radially thicker than are circumferential edges. A fan and a gas turbine engine are also described.

A rotor disk assembly for a gas turbine engine includes a rotor disk that defines an axis, the rotor disk comprising a slot within a rim of the disk and a spacer within the slot, the spacer having a clearance feature sized to permit rotation of a rotor blade from an insertion position to an installed position.

The present invention describes a ring fastener (10) comprising a discontinuous band (11) having a first end (14) and a second end (16). The first end (14) comprises a pair of spaced-apart elongate finger members (15a,15b) (having a first finger member (15a) and a second finger member (15b)), and the second end (16) comprises an elongate tongue member (17). The finger members (15a,15b) and the tongue member (17) are interlockable, such that when interlocked, the band (11) comprises a continuous circumference. The ring fastener (10) further comprises a closed configuration wherein the finger members (15a,15b) and the tongue member (17) are substantially aligned with a circumferential surface (13) of the band (11); and an open configuration wherein the first finger member (15a) is radially and/or axially deflected from its substantially aligned position, so that it is angled with respect to the circumferential surface (13) of the band (11). The invention also describes a method of assembling a bore (40) and a component (42), and the use of such an assembly.

A rotor for a contrarotating turbine comprising a drum and a blading mounted inside, the drum comprising a hook delimiting a housing having an outer wall and an inner wall, the blading comprising a blade and an outer platform provided with spoiler placed inside the housing, wherein the rotor comprises a foil comprising an elastic inner wing and an outer wing, the outer wing being arranged radially between the spoiler and the outer wall, the inner wing having a first support with the inner wall and a second support with the spoiler, the inner wing being arranged in the housing so as to exert a force on the spoiler so as to press the spoiler against the outer wall via the outer wing.