Abstract: In at least one implementation, a method of making a turbine blade may include providing a preform having a hollow cross-section, hydroforming the preform to form a turbine blade body comprising a shell that includes a continuous hollow portion along its interior, and providing a mounting portion attached to the body to mount the turbine blade to a hub. In one or more implementations of the method, the mounting portion may be provided during the step of hydroforming the preform and the mounting portion may be formed from the same preform as the turbine blade body.

Abstract: A turbine rotor blade with a three-pass serpentine flow cooling circuit for a mid-chord region and a triple metering and impingement cooling circuit for a trailing edge region of the blade. The triple rows of metering holes each includes regular sized metering holes in an upper span and a lower span section of the row, and a middle span metering holes having a larger flow area in order to pass more cooling air to the middle span section of the trailing edge region of the blade. The three rows of metering holes are separated by an upper continuous cooling channel and a lower continuous cooling channel.

Abstract: A wheel member includes a body having a first surface that extends to a second surface through an intermediate portion. The body includes an outer diametric surface and a central bore. A first plurality of purge circuits are formed in the body. The first plurality of purge circuits extend from a first end to a second end through the body. The first plurality of purge circuits are arranged to direct a first purge flow in a first direction. A second plurality of purge circuits are formed in the body and fluidly isolated from the first plurality of purge circuits. The second plurality of purge circuits extend from a first end portion to a second end portion through the body and are arranged to direct a second purge flow in a second direction, that is distinct from the first direction, to establish a cross-over purge flow system.

Abstract: In a turbomolecular pump, in connection with a dimensionless number X that is the ratio of an inter-vane distance S to a chord length C for moving vane blades of rotor impeller (4B) and stationary vane blades of stator impeller (2B), with dimensionless numbers at the outer circumferential portion and the inner circumferential portion of a first vane stage being termed Xo(R) and Xi(R) and dimensionless numbers at the outer circumferential portion and the inner circumferential portion of a second vane stage being termed Xo(S) and Xi(S), and with respect to vane stages that are adjacent along the direction of the rotational shaft, at least one vane stage is provided that satisfies a first relational equation “Xo(R)>Xo(S)” and a second relational equation “Xi(R)<Xi(S)”.

Abstract: An aggregate vane assembly is disclosed herein. The aggregate vane assembly includes a core vane assembly encircling a central longitudinal axis. The core vane assembly has a plurality of core vanes each extending radially between an inner hub and an outer band. The core vane assembly extends along the central longitudinal axis between a first forward end and a first aft end. The aggregate vane assembly also includes a bypass vane assembly disposed on a radially opposite side of the outer band relative to the plurality of core vanes. The bypass vane assembly includes at least one bypass vane extending radially outward from a platform. The bypass vane assembly extends along the central longitudinal axis between a second forward end and a second aft end. The aggregate vane assembly also includes at least one boss fixed with the outer band and operable to engage the bypass vane assembly proximate to the second forward end.

Abstract: A multipart bladed rotor (1) for a flow machine, particularly a gas turbine or steam turbine or an axial compressor, has at least two disks (2) whose front sides, which face one another, are connected to one another, particularly by positive engagement, in a separating plane (7) so as to be fixed with respect to rotation relative to one another, wherein a groove (10) for receiving a blade root (14) of at least one rotor blade is formed in the separating plane.

Abstract: A cooling system of ring segment is provided with: a collision plate that has a plurality of small holes; a cooling space that is enclosed by the collision plate and a main body of the segment body; a first cavity that arranged is the upstream end portion of the segment body in the flow direction of the combustion gas so as to be perpendicular to the axial direction of a rotating shaft; a first cooling passage that communicates from the cooling space to the first cavity; and a second cooling passage that communicates from the first cavity to a fire combustion gas d gas space in the downstream end portion of the segment body in the flow direction of the combustion gas.

Abstract: A platform is provided for use between adjacent fan blades joined to a rotor disk to provide an inner flowpath boundary. The platform includes: a metallic arcuate body with opposed forward and aft ends and opposed lateral edges; and a pair of frangible wings that extend from the lateral edges laterally and radially beyond the body.

Abstract: A turbine blade or vane includes at least one internal radial channel for the circulation of cooling medium bordered on a pressure side by a pressure side wall and on a suction side by a suction side wall joined at a upstream side at a leading edge and at and downstream side at the trailing edge. At least one exit hole extends through at least one of the pressure side wall or the suction side wall for blowing out of cooling medium from the internal radial channel to a medium surrounding the blade or vane. At least one trailing edge exit hole along the trailing edge has a surfacial exit opening disposed at the pressure side of the trailing edge.

Abstract: A blade section for a wind turbine blade, the blade section extending along a longitudinal axis and having at least a first end, the blade section comprising a main blade section with a contour having an outer surface. The main blade section at the first end is provided with a number of connection elements, each connection element being pivotally engaged with the main blade section about a rotational axis. Each of the connection elements being provided with a joining means for anchoring each of the connection element to another blade section. The joining means of each of the number of connection elements is arranged in a distance from the rotational axis.

Abstract: An example shaft support includes a cylindrical body establishing a bore extending along an axis. The bore is configured to receive a shaft. Openings are provided in the cylindrical body and distributed circumferentially about the axis. The openings are positioned radially outward of the bore. Each of the openings has a cross-sectional area. The ratio of a total cross sectional area of the openings to a diameter of the cylindrical body is between 0.0963 and 0.0964.

Abstract: The present invention relates to an arrangement (1) for cable guiding, comprising a first guide member (40) adapted to enclose a first cable (10) along at least a part of the length of said first cable. The first guide member (40) has an outside surface adapted to form at least one first guide surface (41) supporting at least one second cable (20) along at least a part of the length of said first cable. The present invention further relates to a wind turbine comprising such an arrangement and to the use of such an arrangement.

Abstract: The invention relates to a charging device, more preferably an exhaust gas turbocharger for a motor vehicle with a variable turbine/compressor geometry (1) with a plurality of adjustable guide blades, which are each engaged with an adjusting ring (2) via a corresponding lever (3, 3?) and which are preferentially jointly adjustable through said adjusting ring. Through a reinforcement (10) of a plurality of engagement regions (7, 7?) of the adjusting ring (2) which are in contact with an adjusting lever (3, 3?) each, higher force transmission from the adjusting ring (2) to the adjusting levers (3, 3?) is made possible without disadvantageous plastic deformation of the adjusting ring (2) or of the adjusting levers (3, 3?).

Abstract: A two-layer wind-guiding shroud includes a base. The interior of the base includes a first wind-guiding channel and a second wind-guiding channel longitudinally overlapped with each other. The first wind-guiding channel has a first wind entrance and a first wind exit. The second wind-guiding channel has a second wind entrance and a second wind exit. The first wind exit and the second wind exit are staggered. By this arrangement, the airflow generated by a fan can be guided into different wind-guiding channels toward different locations, thereby increasing the heat-dissipating efficiency of the fan.

Abstract: The invention relates to a nozzle stage for a turbomachine compressor, the stage comprising two coaxial shrouds, a radially inner shroud and a radially outer shroud, and radial vanes extending between the shrouds and being connected via their ends to the shrouds, together with a support for abradable material that is mounted by crimping onto the upstream and downstream edges of the inner shroud, the inner shroud presenting openings in which the radially inner ends of the vanes are inserted and fastened. The radially inner ends of the vanes are plane and do not have any projecting tenons.

Abstract: One embodiment of the present invention is a vane assembly for a gas turbine engine. Another embodiment of the present invention is a damper seal that may be employed in conjunction with a vane assembly of a gas turbine engine. Other embodiments include apparatuses, systems, devices, hardware, methods and combinations for vane assemblies and the sealing and damping thereof. Further embodiments, forms, features, aspects, benefits and advantages of the present application shall become apparent from the description and figures provided herewith.

Abstract: In one embodiment, a system includes a sight tube configured to optically communicate with an interior of a rotary machine via insertion within an inspection port. The sight tube includes a window and multiple openings configured to direct purge air across the window. The system also includes a curtain tube disposed about the sight tube and configured to direct purge air from a first air source to the openings via a first passage formed between an inner surface of the curtain tube and an outer surface of the sight tube. The curtain tube includes multiple outlets configured to direct curtain air around the window, and the curtain tube is configured to direct the curtain air from a second air source to the outlets via a second passage formed between an outer surface of the curtain tube and an inner surface of the inspection port.

Abstract: A fan shroud with modular vane members for a cooling system. A plurality of modular vane set members are positioned around the inner surface of the fan shroud ring, each of the modular vane set members having a plurality of vane members. The modularity provides flexibility and versatility for the fan shroud and corresponding efficiencies in costs and manufacturing.

Abstract: A counter-rotating axial flow fan in which the shape of stationary blades of a middle stationary portion is optimized to reduce noise is provided. Defining the maximum axial chord length of front blades as Lf, the maximum axial chord length of rear blades as Lr, and the maximum axial chord length of stationary blades as Lm, a relationship of Lm/(Lf+Lr)<0.14 is satisfied. Defining the maximum dimension between the blade chord for lower surfaces of the stationary blades and the lower surfaces as K1, the maximum axial chord length Lm of the stationary blades satisfies a relationship of Lm/K1>5.8.

Abstract: A nozzle box 10 includes: a lead-in pipe 20; a bent pipe 30 connected to the lead-in pipe 20 and formed so as to change a direction of a channel center line 50 to an axial direction of a turbine rotor 212; and an annular pipe 40 connected to the bent pipe 30 and leading steam to a first-stage nozzle 213a while spreading the steam in a circumferential direction of the turbine rotor 212. In the steam channel lead-in part structure 10, from an inlet of the lead-in pipe 20 toward an outlet of the annular pipe 40, steam channel widths Sa-1 to Sn-1 in a first direction intersecting with the channel center line 50 gradually increases and steam channel widths Sa-2 to Sn-2 in a second direction intersecting with the channel center line 50 and perpendicular to the first direction gradually decreases.