Abstract: A fan assembly in which all of the major structural components of the assembly are mechanically fastened together by non-welding means, such as mechanical fasteners, is disclosed. The disclosure also relates to a fan assembly in which the major structural components have planar segments separated by bend lines that approximate a curved shape, and that can be formed, for example, by a press brake machine. Such a construction can eliminate the necessity for rolling, welding, and painting of the structural components of the fan assembly.

Abstract: A turbine engine turbine including a nozzle stage made of ceramic matrix composite material and including a plurality of annular sectors forming an annulus presenting an inner shroud and an outer shroud, each sector having an inner platform forming a portion of the inner shroud, an outer platform forming a portion of the outer shroud, and at least one airfoil extending between the outer and inner platforms and secured thereto. A metal ring includes at least one annular sector, and presents an outer surface in contact with the surface of the inner shroud opposite from the surface from which the airfoils extend, the metal ring presenting an outside diameter at its outer surface that is greater than the diameter of the inner shroud such that the nozzle stage is held in compression between a casing and the metal ring.

Abstract: A diffuser for a radial compressor of a turbomachine is provided. The diffuser has a plurality of diffuser channels, wherein the diffuser channels extend across a radial area of the diffuser across a bent area into an axial area of the diffuser, wherein, in the radial area of the diffuser, the diffuser channels have diffuser walls in particular at v-shaped blades that are bent in the movement direction of the radial compressor or are straight.

Abstract: A rotor blade for a wind turbine is provided. The rotor blade includes a pressure side, a suction side, a leading edge section with a leading edge, and a trailing edge section with a trailing edge. An airflow flows along the surface of the rotor blade from the leading edge section to the trailing edge section and builds up a boundary layer in close proximity to the surface of the rotor blade. The rotor blade includes a noise reduction device for reducing noise which is generated by interaction of the airflow and the rotor blade. The noise reduction device is located within the boundary layer of the rotor blade. The noise reduction device includes a cover and connection device for connecting the cover to the surface of the rotor blade. The cover spans at least over a part of the surface of the rotor blade.

Abstract: Platforms for airfoils in gas turbine engines are provided. The platforms include an aero-structure defining a gaspath surface and a non-gaspath surface, a first securing element arranged to receive a locking pin and secure the aero-structure to a rotor disk, and a first securing element structure extending between the non-gaspath surface and the first securing element, wherein the first securing element structure comprises at least two legs defining a hollow space between the two legs and the non-gaspath surface.

Abstract: A rotary converter of wind energy with a vertical axis of rotation includes a rotor with a vertical axis of rotation 4, which has two or more shovels 6 connected to a central body 5 and/or to each other. The shovels called “working” shovels have wind-permeable structure 2. On one side of the shovels is formed a working surface. It is formed on same side of all working shovels by a flag or flags 1 of which the structure limits the capability to take the direction of the air flow, meeting with this side of the shovels. By this surface, the shovels catch the wind energy and convert it to a rotational motion of the rotor. The shovel's load and the rotor speed can be regulated.

Abstract: A lead-lag damper arranged inside a blade of a rotor of a rotary wing aircraft. The lead-lag damper comprises an inner strength member provided with a cage in which a ball-joint connection is arranged, an outer strength member for securing to the blade, and an elastomer material member arranged between the two strength members. The two strength members and the elastomer material member extending beyond the zone around the cage so that the relative movements between two strength members resulting from the movements of the blade are damped by deformations of the elastomer material member, at least a portion of the lead-lag damper being designed to occupy a portion of the inside of the blade that is conventionally filled with foam.

Abstract: A fan includes an impeller including a boss serving as a center of rotation and a plurality of blades provided on an outer circumferential surface of the boss, and a structure member installed on an upstream side of the impeller in an airflow direction. The plurality of blades each have a plurality of recesses disposed only on a side of a suction surface of a leading edge. The plurality of recesses each have a rectangular shape having two longitudinal sides. Consequently, it is possible to reduce fluctuations of lift on the plurality of blades and thereby reduce discrete frequency noise.

Abstract: A bearing assembly for a centrifugal pump is configured to accommodate both forward and reverse axial thrust, and to be lubricated by process fluid. A pump incorporating a dual acting bearing assembly that is lubricated by process fluid and that is located between the final two impeller stages of the pump. A desalination system comprises a pump with an inlet for receiving seawater at a first end, an outlet for discharging high pressure seawater at a second end, one or more impellers coupled to a rotatable shaft between the first end and the second end for increasing a pressure of the seawater, and a bearing assembly lubricated by the seawater for absorbing axial thrust in both directions along the shaft.

Abstract: A wind turbine uses a series of airfoils/vanes that rotate in a vertical plane within a specifically designed housing. The housing has several adjustable surfaces that control airflow patterns within the housing to increase wind velocity through a vortex effect.

Abstract: An apparatus and method for cooling a fluid within a turbine engine. A fan casing assembly for the turbine engine can include an annular fan casing with a peripheral wall having a flow path defined through the casing. A fan casing cooler includes a body to confront the peripheral wall with at least one conduit configured to carry a flow of heated fluid to convectively cool the heated fluid with a flow of air through the flow path.

Abstract: The present application provides a rotor for use in a turbine engine. The rotor may include a first rotor disc, a second rotor disc adjacent to the first rotor disc, and a belly band seal positioned between the first rotor disc and the second rotor disc. The belly band seal may include a band seal with a locking tab brazed thereon.

Abstract: The present disclosure relates generally to blades used in gas turbine engines. More specifically designs in accordance with the present disclosure include turbine blades comprising ceramic matrix composite materials with abrasive tips coupled thereto.

Abstract: A fan blade for a fan impeller is coupled to a front endring and a rear endring. The fan blade includes a first portion, a second portion, a third portion, a leading edge, and a trailing edge. The second portion is positioned on a first side of the first portion. The third portion is positioned on a second side of the first portion. The leading edge defines a leading edge blade angle and the trailing edge defines a trailing edge blade angle. The leading edge blade angle and the trailing edge blade angle are constant within the first portion and the leading edge blade angle and the trailing edge blade angle vary within the second portion and the third portion.

Abstract: A movable-blade operation system for a hydraulic machine according to an embodiment includes an oil hydraulic cylinder installed within a rotational shaft, a bidirectional pump, a pump drive motor, a control unit, and an oil head installed in the hydraulic machine. The bidirectional pump selectively feeds pressurized hydraulic oil to one of a first cylinder chamber and a second cylinder chamber. The oil head couples the rotational shaft rotatably, and the hydraulic oil fed from the bidirectional pump to the first cylinder chamber and the second cylinder chamber flows through the oil head. The bidirectional pump, the pump drive motor, and the control unit are installed outside the hydraulic machine.

Abstract: A fan nose cone is disclosed for impeding icing and recovering momentum in a gas turbine engine. The fan nose cone comprises: an axially symmetric shell having a convex external surface and an internal surface, the shell having an opening in a forward end of the shell for communication with a source of heated pressurized air; and an axially symmetric deflector disposed forward of the opening, the deflector being configured to direct heated pressurized air exiting from the opening radially outwardly to flow in a downstream direction over the convex external surface of the shell during operation. The shell of the fan nose cone may have a rearward circumferential vent in communication with the source of heated pressurized air for directing heated pressurized from the vent in a radially outward and downstream direction toward the fan blade platforms.

Abstract: A turbo engine rotor disc that has a rotation axis and includes, at the periphery thereof, a plurality of slots regularly distributed around the rotation axis, wherein at least one slot of the plurality of slots has a base that has a plurality of plates arranged in staggered rows and protruding from the base, each plate extending mainly along a direction perpendicular to a radial direction.

Abstract: Radial turbomachine includes fixed case; one rotor disc installed in case and having rotor blades mounted on front face thereof; plurality of elements projecting from case and terminating proximity to rotor disc, wherein projecting elements include seal elements acting against rotor disc are operatively active on rear face of rotor disc or stator blades radially interposed between rotor blades of rotor disc; and one support plate bearing projecting elements and installed in case. Support plate is radially extended across from rotor disc and includes plurality of first circular portions concentric with rotation axis of rotor disc and plurality of second circular portions radially interposed between first circular portions.

Abstract: The invention relates to a method (100) for manufacturing a turbomachine fan comprising a plurality of blades mounted on a disc extending along a longitudinal axis, said method comprising the following steps of: —measuring (102) at least one structural parameter of each of the blades in the cold state, and, for each of the blades, estimating (103) at least one structural parameter in operation relating to a blade from the structural parameter(s) measured on said blade in the cold state, —determining (104) an optimal sequence of the blades around the disc from the structural parameters estimated in operation for each of the blades, and —mounting (105) the blades on the disc in the optimal sequence thus determined.

Abstract: A set of turbomachine guide vanes including plural vanes arranged around an annulus, each vane having a leading edge extending between root and tip ends, the leading edge offset between these two ends being greater than 10% of the blade height. A tangential stacking of the guide vanes towards the suction face side, the curve of tangential stacking, of the position, in the direction tangential to the annulus, of centers of gravity of successive vane cross sections along the vane height, is a curve that increases constantly towards the suction face side. The curve, near the vane tip end, has an accentuated gradient towards the suction face side compared with the rest of the curve, and has a mean gradient near the vane tip end that is greater than at least 1.2 times the mean gradient of the curve over the portion between 30% and 90% of the vane height.