Abstract: A rotor includes: a hub; and a plurality of blades disposed on the hub. Each of the plurality of blades has a suction surface, a pressure surface, a leading edge, a trailing edge, a tip-side edge, and a hub-side edge. The suction surface has a first curved surface portion curved convexly toward the trailing edge such that the trailing edge is inclined to a pressure surface side in a first region which is a partial region, in a blade height direction of the blade, of a region connected to the trailing edge.

Abstract: A vacuum pump includes a rotor that has a rotor central portion and a plurality of stages of rotor blade portions extending from the rotor central portion and having a predetermined elevation angle, and a casing that houses the rotor therein. The rotor further includes a rotor fin. The rotor fin includes a fin shaft portion connected to an end of the rotor central portion, and a transfer blade that extends from the fin shaft portion and causes particles to bounce back in a direction toward an outer periphery of the rotor, the particles falling onto the abovementioned end through an inlet port. The height of the transfer blade and the number of transfer blades are set based on the fall velocity of the particles and the rotation speed of the rotor, such that the particles are prevented from falling onto the abovementioned end without colliding with the transfer blade.

Abstract: A turbine for a turbo-machine is proposed in which, at a gas inlet for a turbine wheel, vanes extend from a nozzle ring though slots in a shroud. The nozzle ring and shroud are relatively rotatable about a rotational axis of the turbine by at least 0.1 degrees. In use, the nozzle ring and shroud are relatively rotated to bring one side of the vane into close contact with one surface of the slot, to inhibit leakage of gas between the vane and the slot surface. For this purpose the respective surfaces of the nozzle and slot can be configured to closely conform to each other. If there is differential thermal expansion of the shroud and nozzle ring, the nozzle ring and shroud can relatively rotate, to withdraw the vane from the edge of the slot to relieve the pressure between them.

Abstract: A turbine rotor blade according to at least one embodiment to be connected to a rotational shaft so as to be rotatable around an axis includes a hub having a hub surface inclined with respect to the axis in a cross-section along the axis; and a plurality of rotor blades disposed on the hub surface. In a throat portion where a blade-to-blade distance between two adjacent rotor blades is smallest, a value (Lt/r) obtained by dividing the blade-to-blade Lt at a given radial position by a distance r from the axis to the radial position is maximum at a position where a dimensionless span length is in a range of 0.2 to 0.65, assuming that the dimensionless span length is 0 at a position of a root end portion on a hub side and is 1 at a position of a tip end portion opposite to the hub side.

Abstract: Provided is an aerodynamic structure for mounting to a surface of a wind turbine rotor blade, which aerodynamic structure includes a plurality of rectangular comb elements and/or a plurality of angular comb elements, wherein a comb element includes comb teeth arranged in a comb plane that subtends an angle to the surface of the rotor blade. The embodiments further describe a wind turbine rotor blade including such an aerodynamic structure.

Abstract: A cooled turbine component in a turbine engine is provided. The cooled turbine component includes a brazed in heat transfer feature, the brazed in heat transfer feature including a thin film including a heat transfer feature incorporated into a surface of the film. The thin film is capable of conforming to a surface of the cooled turbine component and is attached to the surface of the cooled turbine component via a braze material. A method for cooling a turbine component in a turbine engine is also provided.

Abstract: A nozzle segment for a gas turbine engine comprises an outer band having a cooling air inlet, an inner band having a first cooling air outlet, and a nozzle airfoil comprising a cooling flow passage arranged to receive the cooling air as a cooling air stream. A first channel and a second channel are arranged within the cooling flow passage. A deflector is arranged to divide the cooling air stream into a first cooling air stream in the first channel and a second cooling air stream in the second channel, respectively. The deflector deflects the first cooling air stream obliquely to a suction sidewall in the first channel, wherein the first channel is configured to transport the first cooling air stream along the first channel in a swirly flow.

Abstract: A turbine wheel (100) for a turbocharger includes a hub (110) and blades (120). The hub includes a primary outer surface (116), a back wall surface (115), a peripheral edge (119) extending between the primary outer surface and the back wall surface, and a central axis (111). The hub has a back wall thickness measured parallel to the central axis from the primary outer surface to the back wall surface. The blades (120) extend from the primary outer surface of the hub and are integrally formed with the hub by casting. Each blade has a blade thickness measured tangential to the central axis between opposed surfaces of the blade. A maximum diameter of the peripheral edge is 60 mm or more. Over a majority of a radially outer region (117), a thickness ratio of the blade thickness to the back wall thickness varies by 25% or less. The radially outer region extends from the peripheral edge to a 25% meridional.

Abstract: A rotor of a gas turbine, having two adjacent rotor disks having a plurality of blade-holding grooves for receiving rotor blades, distributed around the periphery thereof, and having an axially extending peripheral ring projection radially beneath the blade-holding grooves. A peripheral rotor component is fixed to the ring projections, between the rotor disks. In order to protect the periphery, the rotor disk or the rotor component includes at least two recesses arranged on the periphery in a distributed manner, in each of which engaging shoulders of the rotor component or the rotor disk engage.

Abstract: High performance wedge diffusers utilized within compression systems, such as centrifugal and mixed-flow compression systems employed within gas turbine engines, are provided. In embodiments, the wedge diffuser includes a diffuser flowbody and tapered diffuser vanes, which are contained in the diffuser flowbody and which partition or separate diffuser flow passages or channels extending through the flowbody. The diffuser flow channels include, in turn, flow channel inlets formed in an inner peripheral portion of the diffuser flowbody, flow channel outlets formed in an outer peripheral portion of the diffuser flowbody, and flow channel throats fluidly coupled between the flow channel inlets and the flow channel outlets. The diffuser vanes include a first plurality of vane sidewalls, which transition from linear sidewall geometries to non-linear sidewall geometries at locations between the flow channel inlets and the flow channel outlets.

Abstract: A system for coupling a shroud to a case associated with a gas turbine engine and a gas turbine engine including such a system includes the case defining a bore and the shroud retained within the case. The shroud defines a pocket. The system includes a pin received through the bore and at least partially positioned within the pocket. The pin has a perimeter. The system includes a load spreader including a first side and a second side opposite the first side. The first side is interconnected to the second side by a flexible portion. The first side, the second side and the flexible portion are received about a portion of the perimeter of the pin, and the load spreader is configured to transmit at least one of an axial point load and a circumferential point load from the pin over a surface of the shroud.

Abstract: A rotor has a rotor body having: a flange with a circumferential array of discontiguous apertures; and a surface spaced apart from the flange. One or more rotor balance weight assemblies each have a weight and a fastener. The weight has: a passageway having a first end and a second end; an internal thread along the passageway; and a boss at the first end of the passageway. The boss is in a respective one of the apertures. The fastener has: a shank having a first end and a second end and an external thread engaged to the passageway internal thread; an engagement feature at the shank first end for engagement by a tool to turn the fastener; and a head at the second end contacts the surface.

Abstract: A rotor for a gas turbine having a rotor disk on which there are a plurality of rotor components distributed around the circumference. The rotor disk has a circumferential securing shoulder with a contact face. Retaining faces come to bear against the contact face, each of the retaining faces have a retaining shoulder of the respective rotor component and are designed with a form that complements the contact face. In order to optimize the bearing stresses between the retaining shoulder and the securing shoulder, the retaining face has a smaller radius than the contact face, namely the retaining radius is at least 0.99 times and at most 0.995 times the contact radius. Also provided is an axially extending aperture in the rotor component, the width of which in the circumferential direction is 25% to 75% of the rotor component width in the circumferential direction.

Abstract: A powertrain for a wind turbine (100) comprises at least a first powertrain component (21, 22, 23, 26) and a second powertrain component (21, 22, 23, 26). A rotating output of the first powertrain component (21, 22, 23, 26) is coupled to a rotating input of the second powertrain component (21, 22, 23, 26) and a powertrain housing enclosing the powertrain components (21, 22, 23, 26), the powertrain housing comprising at least a first powertrain housing section (211, 221, 231, 261) enclosing at least part of the first powertrain component (21, 22, 23, 26) and a second powertrain housing section (211, 221, 231, 261) enclosing at least part of the second powertrain component (21, 22, 23, 26).

Abstract: An airfoil includes an airfoil section that has an airfoil wall that surrounds a cavity. The airfoil wall includes an exterior monolithic ceramic shell and an interior CMC liner that has CMC plies. An outermost ply of the CMC plies forms tabs that are raised from an underlying ply so as to define a slot. The exterior monolithic ceramic shell includes an underlapping shell piece and an overlapping shell piece. The underlapping shell piece has a portion disposed in the slot and bonded with the tabs. The overlapping shell piece extends over the tabs and is bonded to the tabs. There are channels bounded by adjacent ones of the tabs, the underlapping shell piece, and the overlapping shell piece. Channel orifices through the CMC liner connect the cavity and the channels.

Abstract: An oil passage of a centrifugal compressor includes a first oil passage that communicates with an oil pan and a speed increaser chamber to supply oil to a speed increaser and the seal. A second oil passage communicates with the speed increaser chamber. A third oil passage extends upward in a gravitational direction from an end of the second oil passage. A fourth oil passage extends in a horizontal direction and causes the oil pan and an end of the third oil passage to communicate with each other. A pressure relief passage that communicates with an outside is arranged in at least one of a portion of the fourth oil passage through which a gas layer passes and a portion of the oil pan in which the gas layer is stored.

Abstract: A vane for a gas turbine engine includes an airfoil section that has an airfoil wall defining a leading edge, a trailing edge, a pressure side, and a suction side that bound an internal cavity. The airfoil section has associated characteristics including a center of pressure and an aerodynamic load vector through the center of pressure. The airfoil wall has a single rib connecting the pressure side and the suction side. The single rib is aligned with the aerodynamic load vector.

Abstract: The present invention relates to a wind tower (10) for delivering wind flow to a turbine. The wind tower (10) including includes a support structure (12) mounted to a support surface (14) and a wind intake section 16 rotatably mounted to the support structure (12) and elevated with respect to the support surface (14). The intake section (16) includes a plurality of internal passageways (32) extending between a plurality of wind-facing inlets (22) and a plurality of outlets (34). The plurality of inlets (22) are orientated for concurrently receiving an oncoming wind-flow W. Each of the inlets (22) are in fluid communication with one of the outlets 34 via one of the passageways (32). The wind tower (10) further includes an output passageway (42) for collecting wind flow W from the plurality of outlets (34).

Abstract: An assembly adapted for use in a gas turbine engine includes a carrier and a blade track segment that is supported by the carrier relative to a high temperature zone. The blade track segment provides a heat shield for use in high temperature applications protecting the carrier and other components.

Abstract: A seal assembly for a gas turbine engine according to an example of the present disclosure includes, among other things, a rotatable shaft defining a longitudinal axis, and a bearing housing extending along the longitudinal axis to define a bearing compartment. The bearing housing has a first seal land defined along an inner diameter of the bearing housing, a seal carrier fixedly attached to an outer periphery of the shaft, and a seal member extending outwardly from the seal carrier. The seal member defines a plurality of helical grooves facing radially outward to establish a first sealing relationship with the first seal land, and each one of the helical grooves has a major component extending in an axial direction relative to the longitudinal axis. A method of sealing for a gas turbine engine is also disclosed.