Abstract: A turbine exhaust diffuser system includes a plurality of manways. The plurality of manways each extend between an outer wall of the turbine exhaust diffuser system and an interior access tunnel of the turbine exhaust diffuser system. The plurality of manways extend between the outer wall and the access tunnel at an angle that is not perpendicular to a central axis of the turbine exhaust diffuser system.

Abstract: A housing-side structure of a turbomachine, in particular of a gas turbine, including an in particular segmented jacket ring (16), which carries an abradable lining for radially outer ends of rotor-side moving blades of a moving blade ring, wherein the jacket ring (16) carrying the abradable lining is connected by means of at least one constriction (18) to a stator-side housing part (19), which is radially adjacent to the jacket ring (16) on the outside and the jacket ring is thermally decoupled from said stator-side housing.

Abstract: A gas turbine engine includes a flow control mechanism operable to direct at least a portion of a fan airflow from a secondary flow path into a core flow path.

Abstract: A casing for an aircraft turbofan bypass engine includes an outer ring, an inner hub and a plurality of struts radially extending therebetween. An annular portion of an engine core casing having an outer wall and an inner wall, is disposed between the outer ring and inner hub, forming an annular splitter supporting an upstream splitter tip structure. The annular splitter further includes an intermediate wall disposed in the annular splitter fixed to the outer wall and the struts, to distribute loads from the annular splitter box to the struts.

Abstract: The invention relates to a rotor for a pump, having at least one blade, the rotor being able to be actuated to rotate about an axis of rotation in order to convey a fluid in the axial or radial direction, the rotor being able to be deformed reversibly elastically in the radial direction between a first, radially compressed state and a second, radially expanded state which the rotor adopts without the effect of external forces, and a third state of the rotor being provided in which, in pumping operation under fluid loading, the rotor is deformed from the first state to beyond the second state.

Abstract: A VTG cartridge (1, 2) of an exhaust-gas turbocharger (2), with a blade bearing ring (3), and a disk (4), which is spaced apart from the blade bearing ring (3) and together with the latter delimits a hot-gas passage (5). The disk (4) is constructed from at least two layers (6, 7, 6?, 7?), which bear loosely against one another in the assembled state of the disk (4).

Abstract: The present application provides a turbine nozzle. The turbine nozzle may include an airfoil with a leading edge and a trailing edge and a flow groove extending from the leading edge to the trailing edge.

Abstract: A pumping element includes a blade (20) having a first section proximate a hub and a second section proximate a tip, a cavity height distribution based on a selected incidence angle distribution and a selected blade thickness distribution based on a structural requirement. The resulting cavity height distribution matches the blade thickness at the first section and the second section and is greater than the blade thickness along the blade.

Abstract: A fan may be provided. The fan may comprise a first plurality of vanes and a second plurality of vanes. The first plurality of vanes may be arranged substantially parallel to an axis of rotation and positioned along a first arc substantially centered on the axis of rotation. Vanes in the first plurality of vanes may be being positioned at a first angle relative to the first arc. The second plurality of vanes may be arranged substantially parallel to the axis of rotation and positioned along a second arc substantially centered on the axis of rotation. Vanes in the second plurality of vanes may be positioned at a second angle relative to the second arc. The first angle may be different than the second angle.

Abstract: A mixing system includes a pipe having a longitudinal axis, in which exhaust gases can flow in a flow direction, a nozzle designed to inject a fluid inside the pipe from an injection inlet arranged in the pipe wall, according to an injection direction, a first mixing device positioned inside the pipe upstream from the injection inlet, the first mixing device including a peripheral portion including blades capable of creating a peripheral swirl along the pipe wall, and a central portion designed to create substantially no turbulence, and a second mixing device positioned inside the pipe downstream from the injection inlet, the second mixing device including a central portion including blades capable of creating a swirl inside the pipe.

Abstract: Wind turbines and energy capturing assemblies for capturing fluid energy are provided. The wind turbines includes a plurality of helical air foil blades mounted for rotation about an axis, and a cylindrical airfoil mounted along the axis and shaped to direct a flow of fluid, such as, air or water, toward the plurality of helical airfoil blades. Incorporating photovoltaic devices within the turbines can enhance the energy capturing capacity of some turbines. The energy capturing assemblies include a plurality of airfoil blades mounted for rotation about an axis, a structure having an outer surface shaped to direct a flow of fluid toward the plurality of airfoil blades; and an electrical generator operatively connected to the plurality of airfoil blades. The structure may be a building, a residence, a tower, a tank, or a vessel. Methods and devices for capturing fluid energy are also included.

Abstract: The present invention relates to a fixed vane-type turbocharger provided with a fixed vane (15) in a conduit (9) between a bearing housing and a turbine housing (4). The fixed vane (15) is configured by a movable member (11) which is disposed on one of the mutually opposing front faces of the bearing housing and the turbine housing (4) so as to be capable of forward and backward movement, and by vanes (14) which are fixed to the front face of the movable member (11). A pressing means (16) is provided which presses the movable member (11) so that the distal ends of the vanes (14) are brought into pressure contact between the rear face of the movable member (11) and either the bearing housing or the turbine housing (4) with the other opposing front face of these. The pressing means (16) contacts the rear face of the movable means (11) within a range in the radial direction where the vanes (14) are disposed, and conducts pressing within this range.

Abstract: An airfoil and method of fabricating an airfoil including a first and a second side coupled together at a leading and a trailing edge and extending there between. The airfoil includes a plurality of first chord sections having a first chord length and extending outward from one of the first side or second side of the airfoil at the leading edge and a plurality of second chord sections having a second chord length and extending outward from the one of the first side or the second side of the airfoil at the leading edge. The leading edge including spaced-apart wave-shaped projections defining a waveform. The configuration defining a three-dimensional crenulated airfoil configured to facilitate desensitization of an airfoil unsteady pressure response to at least one impinging upstream generated wake or vortex by decorrelating spatially and temporally and reducing in amplitude an unsteady pressure caused by interaction of the airfoil with the upstream generated wake or vortex.

Abstract: A fan assembly includes a device for creating an air flow and an air outlet for emitting the air flow. The air outlet is mounted on a stand for conveying the air flow to the air outlet. The fan assembly also includes a tilt mechanism for tilting the air outlet relative to at least part of the stand. The tilt mechanism comprises a flexible hose defining, at least in part, an air passage through the tilt mechanism.

Abstract: A fan case of a gas turbine engine includes a fan blade containment section defined about an engine axis and a plurality of helical ribs adjacent to the fan blade containment section.

Abstract: A wind collection apparatus includes an outer tube and an inner tube assembly. The outer tube has a front end and a rear end. The inner tube assembly is installed in the outer tube and has an inner channel and an outer channel. An air-guiding channel is formed between an outer circumferential wall of the inner tube assembly and an inner circumferential wall of the outer tube. The inner channel has two openings. One of the openings is located at the front end and the other one of the openings is located at the rear end. The outer channel is in communication with the inner channel and the air-guiding channel at two ends of the outer channel.

Abstract: An apparatus for driving a load is provided. The apparatus comprises a multiple-shaft gas turbine comprising a high pressure compressor and a high pressure turbine drivingly connected to one another by a first gas turbine shaft and a low pressure compressor and a power turbine drivingly connected to one another by a second gas turbine shaft extending coaxial with the first gas turbine shaft, the high pressure compressor and the high pressure turbine. The apparatus also comprises a load coupling drivingly connecting the power turbine to the load and a dual-speed turning gear with an output shaft drivingly engageable to and disengageable from the load, the dual-speed turning gear comprising a low speed turning motor and a high speed turning motor, wherein the low speed turning motor and the high speed turning motor are configured to selectively drive the load.

Abstract: A turbomachine casing assembly including a casing adapted to encase an aerofoil structure, the aerofoil structure having a tip, a leading edge and a trailing edge, the casing substantially surrounding the tip of the aerofoil structure, wherein the casing has a set-back portion extending from a position in the region of the leading edge or the trailing edge of the aerofoil structure part way towards a position in the region of the respective other edge and set back from the remainder of the casing away from the aerofoil structure, such that the set-back portion permits a flow over a corresponding portion of the tip of the aerofoil structure.

Abstract: A fan hub frame comprises a circular hub having an opening extending axially wherein an engine core is capable of being positioned, the circular hub having a radially outer surface, the radial outer surface having a plurality of cradles, each of the cradles having a lower surface and fillets disposed between the lower surface and upwardly extending sidewalls, the cradles capable of receiving a double outlet guide vane.

Abstract: An exhaust nozzle 9 has nozzle vanes 15 interposed between front and rear exhaust introduction walls 10 and 51. A space 19 is between the wall 51 and a turbine housing 1. A sealing device 25 is arranged upstream, in a direction of exhaust gas, of each through hole 24 provided in the wall 51 for penetration of a vane shaft 16a to prevent exhaust gas in a scroll passage 8 from leaking through the space 19 to a turbine impeller 4. Each of the walls 10 and 51 is disk-shaped, the turbine housing 1 being formed with a shoulder 50 to which the wall 51 is fitted with the space 19.

Abstract: An example stator vane assembly of a turbomachine includes a shroud having a leading edge, a trailing edge, and at least one circumferential edge. The leading edge is circumferentially offset relative to the trailing edge when installed within the turbomachine.

Abstract: A surround for housing a wind turbine directs and concentrates wind from any direction toward the wind turbine. The surround can be formed from an upper apron and a lower apron, each having three or more sides, typically four sides. A fin can be disposed between the upper and lower aprons and extend from a corner thereof toward a central region. The wind turbine can be disposed in the central region. Openings formed on each side of the surround are defined by the upper and lower aprons and the two fins extending from each corner on that side. The openings can deliver wind, from any direction, toward the wind turbine. The upper and lower aprons may angle inward to further concentrate and direct wind toward the wind turbine.

Abstract: A structural platform comprises a first end, a second end, a first side wall and a second side wall, a platform body extending between the first end and the second end and further between the first side wall and the second side wall, a first fillet joining the first side wall and the platform body, a second fillet joining the second side wall and the platform body, the sidewalls being curved.

Abstract: A method is provided for reconditioning a turbomachine vane cover plate, by a forming apparatus. The vane having a mounting portion, an airfoil extending radially outward therefrom and a vane head connected to the airfoil. The vane also having a cover plate connected to the vane head, bulged in a direction opposite to the root. In a first analysis step, dimensions of the vane in relation to the cover plate are determined in respect of predefined reference points. If, thereafter, forming of the cover plate seems necessary and possible based on comparison of measurement values from the analysis step with predefined dimension values, the bulged cover plate is formed, at least essentially pressed smooth, by pressing by the forming apparatus in a forming step. After the forming step, the cover plate is re-treated in one or more follow-up steps. An apparatus is also provided for carrying out the method.

Abstract: A turbine nozzle is provided including a nozzle airfoil having an airfoil shape, the nozzle airfoil having a nominal profile substantially in accordance with Cartesian coordinate values of X, Y and Z set forth in Table 1 wherein the Cartesian coordinate values of X, Y and Z are non-dimensional values from 0% to 100% convertible to dimensional distances in inches by multiplying the Cartesian coordinate values of X, Y and Z by a height of the airfoil in inches, and wherein X and Y are distances in inches which, when connected by smooth continuing arcs, define airfoil profile sections at each distance Z, the airfoil profile sections at Z distances being joined smoothly with one another to form a complete airfoil shape.

Abstract: The invention relates to an exhaust-gas turbocharger (1) having a turbine (2) which has the following parts: a turbine wheel (3); a turbine housing (4) in which is arranged at least one turbine channel (5, 5?) which has a passage opening (6, 6?) arranged upstream of the turbine wheel (3) as viewed in the exhaust-gas flow direction; and a shut-off device (7), which is arranged downstream of the turbine channel (5, 5?) and upstream of the turbine wheel (3), for opening and closing the passage opening (6, 6?), wherein the shut-off device (7) has a shut-off sleeve (12) which is guided in a translatorially movable fashion in a groove (13) formed directly into the turbine housing (4).

Abstract: A sealing device includes a housing rotatably accommodating a rotary shaft, guide parts extending along a radial direction and an axial direction of the rotary shaft, and arranged side-by-side in a circumferential direction of the rotary shaft, a partition part that is a partition between spaces between the guide parts and an outside space, a first seal part that is an annular protrusion, forming a first gap with respect to the rotary shaft or the partition part, and blocking a flow of fluid passing through the outside space, and a second seal part that is an annular protrusion extending in the radial direction, forming a second gap with respect to the rotary shaft or the housing, and blocking a flow of fluid that has passed through the spaces between guide parts and a flow of fluid that has passed through the first seal part.

Abstract: A fluid movement system that includes an impeller having a blade with a leading edge blade tip angle determined as a function of an increase in mass flow rate due to reinjection of flow from a flow stability device located proximate to the leading edge tip of the blade. In an exemplary method, the leading edge blade tip angle can be determined based on selecting a blade incidence level based on a mass flow gain versus flow coefficient curve. Blade leading edge tip angles determined in accordance with a method of the present invention are typically greater than blade leading edge tip angles determined using traditional methods. The greater blade leading edge tip angles can lead to more robust blades designs.

Abstract: An anti-relief fan frame body structure includes a frame body and multiple anti-relief sections. The frame body has a receiving space and a shaft seat received in the receiving space. The frame body further has multiple flow guide members extending from a circumference of shaft seat to an inner circumference of the frame body to connect with the inner circumference of the frame body. The anti-relief sections are disposed on the inner circumference of the frame body between the flow guide members to increase the performance of the fan.

Abstract: A hypereutectic chromium alloy consisting of 9 to 12 at % tantalum, 4 to 15 at % silicon, 0 to 7 at % molybdenum, 0 to 7 at % aluminium, 0 to 7 at % titanium, 0 to 5 at % rhenium, 0 to 2 at % silver, 0 to 2 at % hafnium, 0 to 2 at % lanthanum, 0 to 2 at % cerium, 0 to 2 at % yttrium and the balance chromium and incidental impurities. The hypereutectic chromium alloy has good oxidation resistance and good fracture toughness. The chromium alloy may be used to make gas turbine engine turbine blades, turbine vanes, turbine seals, combustion chamber tiles, exhaust nozzle segments or steam turbine components.

Abstract: A compressor diffuser for a gas turbine includes: a compressor diffuser having an upstream end and a downstream end, the downstream end defined by a peripheral annular edge, the annular edge formed with a plurality of substantially axially-oriented slots extending from an opening at the downstream edge in an upstream direction.

Abstract: For a wind turbine, an electromagnetically shielding nacelle cover is formed of a composite material which can comprise, for example, an outer layer made of a fiber material or fiber mats such as glass fiber mats and an interposed foam layer. A conductor layer, for example a mesh, a woven fabric or a coating made of conductive material is integrated between the fiber layers of the composite material to provide electromagnetic shielding of the nacelle. The conductor layer is also connected, or can be connected, directly or indirectly, to at least one conductive structure that is applied to the outside of the nacelle cover.

Abstract: In an exemplary embodiment, a high temperature oxidation and hot corrosion resistant MCrAlX alloy is disclosed, wherein M comprises cobalt and X comprises, by weight of the alloy, from about 0.001 percent to less than 0.19 percent yttrium. In these alloys, X may also optionally include silicon, including, by weight of the alloy, up to about 1.5 percent. In another exemplary embodiment, a coated article is disclosed. The coated article includes a substrate having a surface. The article also includes a bond coat disposed on the surface. The bond coat comprises a high temperature oxidation and hot corrosion resistant MCrAlX alloy, wherein M comprises cobalt and X comprises, by weight of the alloy, from about 0.001 percent to less than 0.19 percent yttrium.

Abstract: An airflow-straightening structure for an aircraft engine is provided that includes a hoop inside which there are arranged a plurality of flow-straightening vanes bearing a hub of a fan. Also includes is a clevis for connecting to a suspension strut, the clevis being fixed to said hoop. The structure has at least two elements chosen from the group of the hoop, the plurality of vanes, the hub and the clevis, which are formed in one piece, that is to say without any assembly operation. Additionally, at least one of the elements chosen from the group is at least partially formed of a composite material.

Abstract: A vane segment for a gas turbine engine includes an airfoil disposed between an outer platform and an inner platform. A slot for receiving a seal is defined within the outer platform and includes closed first and second ends and an upper surface spaced apart from a lower surface with a spacing between the upper surface and the lower surfaces that varies along a length of the slot.

Abstract: An airfoil comprises pressure and suction surfaces extending axially from a leading edge to a trailing edge and radially from a root section to a tip section, defining a mean span therebetween. An inner endwall defines an inner endwall contour extending axially and circumferentially from the root section, and an outer endwall defines an outer endwall contour extending axially and circumferentially from the tip section. The inner and outer endwall contours are defined by varying radial deviations from circumferentially uniform nominal inner and outer radii, where one of the radial deviations varies axially and circumferentially by at least three percent of a mean span of the airfoil.

Abstract: A fan assembly includes a rack, a shield, and a fan. The rack defines a first vent opening and a second vent opening aligned with the first vent opening. The shield is mounted in the rack and aligned with the first vent opening. The shield defines a frame opening corresponding to the first vent opening. A plurality of shielding pieces are pivotally mounted in the frame opening, and rotate to shield the frame opening because of gravity. The shield includes a plurality of guarding bars to guard the plurality of shielding pieces from being damaged. The fan is mounted in the rack and aligned with the second vent opening and the shield. The fan generates air flow flowing through an air passage between each adjacent two of the plurality of shielding pieces, and the plurality of shielding pieces are rotated by the air flow.

Abstract: A fan assembly for creating an air current includes a nozzle mounted on a base. The base includes an outer casing, a silencing member housed within the outer casing, an impeller housing located within the outer casing, the impeller housing having an air inlet and an air outlet, an impeller located within the impeller housing and a motor for driving the impeller about an axis to create an air flow through the impeller housing. The nozzle includes an interior passage for receiving the air flow from the air outlet of the impeller housing and a mouth through which the air flow is emitted from the fan assembly. The silencing member is located beneath the air inlet of the impeller housing and is spaced from the air inlet along said axis by a distance in the range from 5 to 60 mm.

Abstract: An impulse wind machine comprises the following: A funnel configured to capture air from the wind. A turbine housing configured to direct the air to the center (eye) of the housing where the air passes through directional vanes. A rotor configured to rotate within the eye of the turbine housing and configured with impulse blades along the longitudinal periphery. Air from the directional vanes impinges the impulse blades to cause rotor rotation. An exhaust deflector configured inside the cavity of the rotor to deflect exhaust air from the impulse blades axially out the ends of the rotor. Spokes on the rotor configured to provide a fan action during rotor rotation aiding removal of the exhaust air. A generator and a gearbox driven by a shaft connected to the rotor for generating electrical power.

Abstract: A cooling apparatus comprising an impeller, a housing that encloses the impeller, an inlet opening formed between the hosing and impeller and a projection formed on the housing that extends from the housing towards the impeller.

Abstract: A static structure of a gas turbine engine according to an exemplary aspect of the present disclosure includes a multiple of airfoil sections between an outer ring and an inner ring. A spring biased tie-rod assembly is mounted through at least one of the multiple of airfoil sections.

Abstract: A turbine airfoil assembly for installation in a gas turbine engine. The airfoil assembly includes an endwall and an airfoil extending radially outwardly from the endwall. The airfoil includes pressure and suction sidewalls defining chordally spaced apart leading and trailing edges of the airfoil. An airfoil mean line is defined located centrally between the pressure and suction sidewalls. An angle between the mean line and a line parallel to the engine axis at the leading and trailing edges defines gas flow entry angles, ?, and exit angles, ?. Airfoil inlet and exit angles are substantially in accordance with pairs of inlet angle values, ?, and exit angle values, ?, set forth in one of Tables 1, 3, 5 and 7.

Abstract: A reinforced structural guide vane system includes an outer casing; a center body within the outer casing; a plurality of structural guide vanes extending between and connected to the center body and the outer casing; and a plurality of strut rods extended between and connected to the outer casing and to the center body.

Abstract: A stator for a progressive cavity pump or motor includes a stator housing and a stator thread made of a material moulded within the housing. The stator housing includes an outer tube and an inner anchor element within. The anchor element has radially disposed apertures and is spaced from outer tube. To fix the anchor element in the outer tube, the axial end faces of the anchor element each have a first set of protrusions and indentations around the circumference thereof. Two end caps of the housing are fixed at the end faces of the outer tube. Each end cap is provided with an interconnecting part having a second set of protrusions and indentations. The first and second sets of protrusions and indentations interengage to mechanically fix the anchor element axially and radially within the outer tube.

Abstract: A section of a gas turbine engine including a radial spoke is provided. The spoke includes an aerodynamic shape with a leading side and a trailing side and, extending from the leading side to the trailing side, a first side and a second side, opposite the first side. The spoke also includes at least one flow guiding element arranged on at least the first side.

Abstract: A turbine nozzle for an air cycle machine includes a base with a multiple turbine vanes which each extend for a vane height H, a throat width W defined between each of the multiple of turbine vanes, wherein a ratio W/H is 0.101-0.112.

Abstract: This invention relates to a stator aerofoil for a gas turbine engine, comprising: a body portion; at least one panel which forms at least part of one of either the pressure or section surface of the aerofoil; at least one internal chamber which is bounded by the body portion and panel; and, at least one elastomeric component within the at least one internal chamber, wherein the elastomeric component at least partially defines a cell within the internal chamber, wherein the cell is in fluid communication with the exterior of the aerofoil.

Abstract: A catcher ring assembly (170) configured to limit axial movement of a turbomachine shaft assembly (132, 132?) during a failure mode, the catcher ring assembly comprising a catcher ring (172) disposable about and connectable to the shaft assembly, wherein one of the shaft assembly and the catcher ring comprises a protrusion (194, 182) and the other of the shaft assembly and the catcher ring comprises a recess (192, 184), the recess corresponding in shape to the protrusion, wherein the protrusion and recess are circumferentially disposed about a longitudinal axis of the shaft assembly and the protrusion extends in an axial direction.

Abstract: The invention provides a wind direction cover of an electric fan, comprising a central cap, an external circular frame, a plurality of wind guiding blades between the central cap and the external circular frame which are concentric with the central cap, and a plurality of anchor plates of the wind guiding blades. The exterior side of the most internal wind guiding blade is parallel to the flank of the central cap, and the exterior sides of external wind guiding blades slant toward the external circular frame, angulating the exterior sides of the wind guiding blades with the parallel plane of the flank of the central cap, and the more external the wind guiding blade is, the larger its angle slanting toward the external circular frame is.

Abstract: A diffuser plate for a centrifugal compressor includes an inner edge disposed at an inner diameter about a central axis; an outer edge disposed at an outer diameter, the outer edge displaced an axial distance from the inner edge; a deformable section that includes a substantially S-shaped cross-section, the deformable section disposed between the inner edge and the outer edge; and a spring constant for forced axial displacement of the outer edge with respect to the inner edge, the spring constant characterized, at least in part, by the deformable section. Various other examples of devices, assemblies, systems, methods, etc., are also disclosed.