Abstract: A rotary assembly includes a fan disk including a tooth with an upstream face; a platform mounted on the tooth; and a shroud mounted at the upstream end of the disk. The platform, at its upstream end, includes a step with a radial portion that is extended by an axial portion to form a substantially L-shaped longitudinal section. The axial portion radially retains the platform against the tooth. The radial portion extends along the upstream face of the tooth and includes an opening for having a fastener element passing axially therethrough to mount the shroud on the disk. A face of the shroud includes an element that projects and passes through the opening and comes into contact with the upstream face. The element extends from the face of the shroud over a length that is longer than a thickness of the radial portion of the step of the platform.

Abstract: The embodiments of the present invention disclose a rotor driving system, wherein at least three first actuators can drive a nonrotating lower-rotor swashplate to tilt towards a specific direction by cooperating with each other such that a rotating lower-rotor swashplate, lower tilted-arm pull rods and blade-clamp tilted arms of the lower rotor are all in motion, thereby driving first blade clamping bodies to be twisted relative to a lower rotor hub; at least three second actuators can drive a nonrotating upper-rotor swashplate towards a specific direction by cooperating with each other such that a rotating upper-rotor swashplate, upper-rotor steering rod—L arms, lower upper-rotor steering rods, pull rods, upper upper-rotor steering rods, upper tilted-arm pull rods, blade-clamp tilted arms 42 of the upper rotor are all in motion, thereby driving a second blade clamping body to be twisted relative to an upper rotor hub.

Abstract: A holding device of a cooling tube for a turbojet casing, the holding device including a first plate configured to be arranged in integral contact with a turbojet casing; a second plate, the first and second plates having a gap therebetween; a first spacer and the second spacer which are arranged between the first plate and the second plate and defining the gap between the first and second plates, the first and second spacers having a spacing therebetween suitable for passing the cooling tube.

Abstract: A rotor disk includes a ring shaped rotor body defining a radially inward opening, rims protrude radially outward from the rotor body, and outwardly facing rotor blade retention slots are defined between circumferentially adjacent rims. Each slot is operable to receive and retain a corresponding rotor blade, and each rim of the rims includes an anti-vibratory feature. The anti-vibratory feature includes a structure defining an isogrid pattern intruding into a surface of the rim.

Abstract: A bearing load sharing system comprising: first and second rotors extending in an axial direction; a first thrust bearing having an inner race and an outer race, the inner race connected to the first rotor; a second thrust bearing having an inner race and an outer race, the inner race connected to the second rotor; and an inter-rotor bearing having an inner race and an outer race, the inner race connected to one of the first and second rotor and the outer race connected to the other of the first and second rotor; wherein the outer race of the first bearing and/or the outer race of the second bearing is movable to vary the axial spacing between the outer races.

Abstract: The present invention relates to a turbomachine blade (100; 200) with a base element, which has a blade part (1) for flow diversion and a blade root (2), a first guide (110; 210), fixed on the base element, in which a first element (111; 211) is movably guided, and a second guide (120; 220), fixed on the base element, in which a second element (121; 221) is movably guided, wherein a dynamic of the first element in the first guide and a dynamic of the second element in the second guide are designed differently, and the first guide (110; 210) is arranged in a half, nearer to the base root, of a radial height (H) of the base element, and the second guide is arranged in a half, more remote from the blade root, of the radial height of the base element.

Abstract: Aspects of the disclosure are directed to a gas turbine engine, comprising a sealing assembly that includes a non-contacting HALO seal, a ring constructed as a full ring and configured as a carrier of the seal, a sealing land configured to rotate and interface to the seal. In some embodiments, the engine further comprises a vane, where the ring is coupled to the vane.

Abstract: A method for reducing the noise level generated by a fan of a turbomachine including a plurality of vanes, said method further including, when the turbomachine is operating and under given flight conditions, the following steps measuring an operational pitch angle for each of the vanes, calculating an offset between the operational pitch angle of each of the vanes and a predetermined reference pitch angle for the given flight conditions so as to produce a controlled noise level at multiple rotation frequencies of the fan, correcting the orientation of the vanes so as to compensate their operational pitch angles depending on the offsets thus calculated.

Abstract: An exemplary gas turbine engine includes a radially stacked intershaft bearing assembly. The assembly includes an outer stubshaft having outer and inner diameter surface portions disposed concentrically with respect to one another. The outer diameter surface portion is rotatably connected to a body of the engine, and the inner diameter surface portion is rotatably connected to an inner stubshaft of the engine, so as to provide a stacked configuration of the inner stubshaft, the outer stubshaft, and the body along a radial direction orthogonal to a longitudinal axis of the engine.

Abstract: A vertical axis windmill comprises three or more frames rotatable in unison about a substantially vertical axis and a plurality of airfoils hingedly affixed to each frame. Each airfoil is able to swing away from its respective frame in a first direction from a closed position to an open position and not able to swing away from its respective frame in a second direction from the closed position.

Abstract: A mid-turbine frame for a gas turbine engine includes a CMC outer ring, a CMC inner ring, and a multiple of CMC airfoils between the CMC outer ring and the CMC inner ring. Each of the CMC airfoils includes at least one hollow tube and a shell of a multiple of CMC plies surrounding the hollow tube. The hollow tube reinforces the shell. A spring biased tie-rod assembly is mounted through at least one of the multiple of CMC airfoils.

Abstract: A turbomachine blade having a main body (10) that includes a plane, first attachment surface (100) having a first rim contour (110), a cover (20; 21, 22) that has a plane, second attachment surface (200) having a second rim contour (210) that is welded to the first attachment surface, and a tuning body configuration having at least one tuning body (30; 31-33) for contacting an inner wall (220) of the cover by impact therewith, a gap (s) being formed between the first and the second rim contour.

Abstract: A turbine nozzle disposed in a turbine includes a suction side having a bulge, and a pressure side. The suction side and the pressure side extend opposite one another between a leading edge and a trailing edge in an axial direction transverse to a longitudinal axis of the turbine nozzle, and extends a radial direction along the longitudinal axis. The bulge is disposed on the suction side protruding relative to the other portion of the suction side in a direction transverse to both the radial and axial directions. The turbine nozzle has a first periphery defined at a first cross-section at a first location along the height of the turbine nozzle by selected coordinate sets listed in Table 1.

Abstract: A turbomachine includes a sealing segment ring that is provided between a front guide vane row and a back guide vane row for sealing a radial gap between a casing section and a rotor blade row rotating between the guide vane rows, wherein the sealing segment ring has a plurality of identical sealing segments and at least one of the guide vane rows has a plurality of identical guide vane segments, wherein the sealing segments each have a plurality of engagement sites lying adjacent to one another in the peripheral direction for interaction with securing elements of this guide vane row, wherein the engagement sites and securing elements are distributed uniformly over the periphery and the engagement sites are a multiple of the securing elements, a sealing element, and a guide vane segment.

Abstract: A fan assembly and a fan frame thereof are disclosed. The fan assembly includes a fan frame and an impeller disposed in the fan frame. The fan frame has an air inlet end and an air outlet end, and includes a sidewall, a top portion and a bottom portion. The top portion is disposed close to the air inlet end and connected to one end of the sidewall. The bottom portion is disposed close to the air outlet end and connected to the other end of the sidewall. The bottom portion has at least one silencing structure.

Abstract: A connection assembly for securing a fan drive gear system module within a gas turbine engine includes first and second members removably secured to one another by radially extending fasteners.

Abstract: The present application relates to a stator of an axial turbomachine compressor. The stator includes a circular wall, such as an internal shroud, with a guiding surface in order to guide the primary flow of the turbomachine. The stator further includes a circular row of stator vanes, each of them including an airfoil which extends radially in the primary flow of the turbomachine, and a securing portion. The securing portion of the vane includes a lattice which has rods and which is secured and/or sealed in the shroud in order to fix the vanes to the shroud via the lattices. The stator includes a joint of abradable material which is arranged inside the internal shroud, and in which the lattice is secured in order to ensure retention, a fixing between the vane and the internal shroud. The vane is produced by means of additive production.

Abstract: Disclosed herein is a gas turbine with a plurality of tie rods. The gas turbine includes a compressor section having a plurality of compressor-side rotor disks, a turbine section having a plurality of turbine-side rotor disks arranged downstream of the compressor-side rotor disks, a first tie rod penetrating central portions of the rotor disks provided in the compressor section to press the compressor-side rotor disks against each other, a plurality of second tie rods penetrating vicinities of edges of the rotor disks provided in the turbine section to press the turbine-side rotor disks against each other, and a torque transfer member coupled to the first and second tie rods so as to transfer rotational torque generated by the turbine section to the compressor section.

Abstract: A fan assembly and a method of assembling a diffuser collar in the fan assembly are disclosed. The fan assembly includes an impeller including a plurality of blades. The impeller has an impeller diameter. A duct is configured to receive an outflow provided by the impeller. The duct has a duct exit diameter that is larger than the impeller diameter. The fan assembly further includes a diffuser collar extending from the impeller toward a duct exit. The diffuser collar is configured and arranged to radially expand the outflow provided by the impeller. The diffuser collar has a first diameter at a first edge disposed a first distance from the impeller. A contour extends from the first edge toward a second edge having a second diameter. The second edge is disposed a second distance from the impeller. The first distance is smaller than the second distance, the first diameter is smaller than the second diameter, and the first and second diameters are smaller than the duct exit diameter.

Abstract: A gas turbine engine is provided including a shaft coupling a compressor of a compressor section to a turbine of a turbine section. An aft bearing assembly, including at least two bearings, is positioned at least partially in an aft sump and supports the shaft within the turbine section. The aft sump is configured to receive lubrication oil from a lubrication oil supply extending through at least a portion of a turbine center frame of the turbine section, and provide such lubrication to the at least two bearings of the aft bearing assembly.