Abstract: An axial flow compressor for a gas turbine engine is disclosed having a casing treatment that includes a shrouded rotor and an airflow member disposed in a passage between a casing and the shrouded rotor. In one form the airflow member is stationary with the casing and in another the airflow member is coupled to rotate with the shrouded rotor. The airflow member can have an airfoil shape in some embodiments. A passage inlet that extracts working fluid and provides it to the passage can be formed between a leading edge of the rotor and a trailing edge. A passage outlet can be formed upstream of the leading edge of the rotor.

Abstract: An inlet case for a small gas turbine engine, where the inlet case is formed as a hybrid piece with a metallic inner shroud cylinder and plastic guide vanes and plastic outer shroud molded around the metallic inner shroud cylinder. The metallic inner shroud cylinder carries an electric generator and provides for a good convective heat transfer surface to carry heat away from the electric generator and into the inlet air flow entering the engine. The plastic guide vanes and outer shroud allow for a light weight inlet case assembly that is also much easier to form the airfoil shapes than a machined metallic inlet case. The plastic guide vanes and outer shroud are injection molded around the metallic inner shroud cylinder to produce a rigid single inlet case. The metallic cylinder includes axial extending slots that receive the lower ends of the guide vanes during the injection molding process.

Abstract: A turbine nozzle for an air cycle machine includes a disk section 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 0.745-0.769.

Abstract: A blade for use in a fluid-flow machine, where at least one of the meridional flow line profile sections MSLi and MSLo is provided at a distance of max. 35% of the main flow path width from the respective inner and outer main flow path boundaries. The blade has in at least parts of a central area a multi-profile configuration such that at least two partial profiles (7, 9, 10) arranged one behind the other in the flow direction are provided, of which each has substantially the shape of a blade profile, where a passage (8) is provided between each two partial profiles and is passed through by fluid from the blade pressure side to the blade suction side.

Abstract: An axial-flow gas turbine engine includes a plurality of inlet guide vanes (V) which are radially disposed in an annular gas passage defined between an inner peripheral wall (Ch) and an outer peripheral wall (Ct) of a turbine. The inner peripheral wall (Ch) of the gas passage includes inner peripheral concave portions (Cc1 and Cc3) on an upstream side, and inner peripheral convex portions (Cv1 and Cv3) on a downstream side. The outer peripheral wall (Ct) of the gas passage includes outer peripheral convex portions (Cv2 and Cv4) on an upstream side, and outer peripheral concave portions (Cc2 and Cc4) on a downstream side. Therefore, a pressure difference in a radial direction of the inlet guide vane V is reduced or partially reversed, and a secondary flow toward an inner side in the radial direction can be suppressed to reduce pressure loss.

Abstract: A multi-stage radial turbine that is capable of reducing the number of bearings and of improving the conversion efficiency is provided.

Abstract: A vane assembly for a gas turbine engine where each vane is connected to at least one adjacent portion of at least one of the inner and the outer shrouds through a melt-weld connection. The melt-weld connection includes non-metallic heat-meltable material with a metal wire mesh layer trapped therein, the metal wire mesh being heatable to melt the heat-meltable material for formation and breakdown of the melt-weld connection.

Abstract: A gas turbine engine is provided having an annular duct having an inner duct wall and an outer duct wall. At least one strut extends between the inner duct wall and the outer duct wall. The strut has an aerodynamic shape. At least one vane located circumferentially adjacent the strut and axially behind a leading edge of the strut, and an aerodynamic deflector located circumferentially between each strut and each vane. The aerodynamic deflector may positioned axially upstream of a flow separation point which would otherwise be caused by the strut.

Abstract: A turbine power generation system, comprising a stator including a shroud and a rotor rotatably situated within the shroud, wherein the shroud is structured such that the inner diameter of the inner surface of the shroud reduces when the inner surface is exposed to a thermal load. The reduction of the inner diameter allows a minimum blade-casing clearance to be achieved during steady-state operation instead of during transient operations. Blade-casing clearance is configured to be greatest at when the engine is in a cold, stationary position. The clearance is further configured to decrease as thermal load increases until a steady-state, thermal equilibrium is achieved. The clearance grows during shutdown as the stator and rotor begin to cool.

Abstract: An article of manufacture having a nominal profile substantially in accordance with Cartesian coordinate values of X, Y and Z set forth in TABLE A. X and Y are distances in inches which, when connected by smooth continuing arcs, define airfoil profile sections at each distance Z in inches. The profile sections at the Z distances can be joined smoothly with one another to form a complete airfoil shape.

Abstract: A two-stage high pressure turbine includes a second stage blade having an airfoil with a profile substantially in accordance with at least an intermediate portion of the Cartesian coordinate values of X, Y and Z set forth in Table 2. The X and Y values are distances, which when smoothly connected by an appropriate continuing curve, define airfoil profile sections at each distance Z. The profile sections at each distance Z are joined smoothly to one another to form a complete airfoil shape.

Abstract: A core case section for a gas turbine engine a multitude of discreet radial extending 2.5 bleed ducts defined in part by a rear structural wall.

Abstract: An inter-turbine casing for a turbofan is disclosed. The casing includes an outer ring, an inner ring, and an intermediate ring between the inner ring and the outer ring. The inner and intermediate rings have respective openings for the passage of cooling air. The casing includes at least one sealing device, arranged between the outer ring and the intermediate ring, with a base, provided with at least one orifice for the passage of cooling air, and a peripheral skirt which is able to be compressed and expanded elastically. The base bears against the outer ring and the peripheral skirt bears against the intermediate ring.

Abstract: A blade for a stator in a torque converter including a first face, which includes a first step, and a second face located substantially circumferentially opposite the first face. In one embodiment, the first face includes first and second disjointed or misaligned segments, and the first step connects the first and second segments. In another embodiment, the second face includes a second step. In yet another embodiment, the second face includes third and fourth disjointed or misaligned segments, and the second step connects the first and second segments.

Abstract: An axial flow fan according to the present invention comprises an impeller which rotates about a central axis and including a plurality of blades, a hollow member accommodating therein the impeller, a base portion which is arranged at the hollow member and supports the base portion in a rotatable manner, a plurality of inner air guide members each connected to the base portion, and a plurality of outer air guide members each connected to the hollow member. The inner air guide members and the outer air guide members each include a first edge member and a second edge portion. A length of the first edge member and that of the second edge member of the outer air guide member are greater than those of the first edge member and the second edge member of the inner air guide member.

Abstract: In a transonic region with a Reynolds number not more than a critical Reynolds number, a flow velocity distribution on an extrados of an airfoil has a single supersonic maximum value within a range of up to 6% from a leading edge on a chord, or a shape factor has a maximum value in a region of 6 to 15% from the leading edge on the chord, the value being nearly constant in a region of 30 to 60% and gradually can increase up to 2.5 in a region downstream of 60% of chord. A pressure loss in a low Reynolds number region can be drastically reduced, while conventionally keeping low the pressure loss in a high Reynolds number region. Moreover, this pressure-loss reduction effect in the low Reynolds number region is exerted even if an inflow angle is changed in a wide range.

Abstract: A guide vane for a gas turbine includes a vane body having a leading edge and a trailing edge and a shroud extending at least between the leading edge and the trailing edge. The shroud has a first side wall and a second side wall extending essentially radially and in a longitudinal direction of the gas turbine. The first side wall has a groove disposed in a region of the trailing edge extending in a longitudinal direction of the shroud and is configured to receive a sealing plate. The first side wall also has a clearance extending from the groove in a region of the trailing edge, wherein a depth of the clearance in a circumferential direction of the gas turbine is equal to a depth of the groove, and wherein a width of the clearance in the longitudinal direction of the shroud is between one to three times the depth of the clearance.

Abstract: A stator vane for a gas turbine includes a vane airfoil which extends in the longitudinal direction of the vane and which is delimited by a leading edge and a trailing edge, and also an outer platform, the inner side of which is exposed to the hot gas which flows through the gas turbine, and on which provision is made for a hook-like fastening element, projecting outwards in the region of the trailing edge, for fastening the stator vane on a casing of the gas turbine, which fastening element, on its side facing the trailing edge, has a locating slot above the trailing edge for the fixing of a heat shield which adjoins the outer platform of the stator vane in the flow direction of the hot gas. Provision is made on the outer platform of the stator vane between the locating slot and the trailing edge of a structure for reducing the thermal and mechanical stresses in the region of the transition between trailing edge and outer platform.

Abstract: A gas turbine transition duct apparatus is provided comprising first and second turbine transition ducts and a strip seal. The strip seal may comprise a sealing element and a spring structure.

Abstract: A turbomachine includes a housing, and a plurality of turbomachine nozzles. At least one of the plurality of turbomachine nozzles includes a body having a first surface and an opposing second surface that extend between a first end and a second end. At least one of the first and second surfaces includes a profile having an angle of between about 3° and about 8° between a first line passing through the first end and a first position located between about 28% and about 38% from the first end and a second line passing through the first position and a second position located between about 53% and about 63% from the first end, and an angle of between about 10° and about 20° between the second line and a third line passing through the second position and a third position located between about 74% and about 84% from the first end.

Abstract: There is disclosed an improved hydro turbine assembly (1) that offers high productivity, high operating versatility and minimal and/or no cavitation for an improved efficiency. The present invention proposes a new hydro turbine assembly having substantially higher energy conversion process as well as versatile range of capability from low to high head applications. The hydro turbine assembly (1) comprises of at least an inlet connection (2), an inboard casing (3) and an outboard casing (4) and a turbine runner (6) arranged internally toward the end of the inlet connection (2), the turbine runner (6) is mechanically connected to a turbine shaft (7) arranged with means to generate mechanical energy by the rotation of the turbine shaft (7); characterized in that the inlet connection (2) and the turbine runner (6) are arranged such that water enters into the turbine in the same axis as of the turbine shaft (7) but from the opposite end and leaves it in a radial direction through the turbine runner (6).

Abstract: A rotor blade is disclosed herein. The rotor blade comprises a nominal surface profile substantially in accordance with Cartesian coordinates X, Y and Z as set forth in TABLE 1. Wherein X and Y are distances in millimeters which, when connected by smooth, continuing arcs, define airfoil profile sections at each distance Z in millimeters. The airfoil profile sections at the Z distances being joined smoothly with one another to form a complete airfoil shape.

Abstract: A turbine nozzle includes an array of turbine vanes between inner and outer bands. Each vane includes opposed pressure and suction sides extending between opposed leading and trailing edges. The vanes define a plurality of flow passages each of which is bounded between the inner band, the outer band, and adjacent first and second vanes. A surface of the inner band in each of the passages is contoured in a non-axisymmetric shape including a peak of relatively higher radial height adjoining the pressure side of the first vane adjacent its leading edge, and a trough of relatively lower radial height is disposed parallel to and spaced-away from the suction side of the second vane aft of its leading edge. The peak and trough define cooperatively define an arcuate channel extending axially along the inner band between the first and second vanes.

Abstract: An article of manufacture having a nominal profile substantially in accordance with Cartesian coordinate values of X, Y and Z set forth in TABLE A. X and Y are distances in inches which, when connected by smooth continuing arcs, define airfoil profile sections at each distance Z in inches. The profile sections at the Z distances can be joined smoothly with one another to form a complete airfoil shape.

Abstract: The disclosure relates to a multi-stage low-pressure steam turbine and a method for operating thereof. The steam turbine includes a last stage in which the leading edge of each vane of the last stage is skewed so as to form a W shaped K-distribution across the span of the vanes. This shape allows for efficient last stage operation at low last stage exit velocities. The disclosure includes a method for operating such a steam turbine at a last stage exit velocity between 125 m/s and 150 m/s.

Abstract: A housing for an axial-flow fan includes a frame, a seat and a plurality of stationary blades. The frame has an air inlet and an air outlet. The seat is received in the frame and at a position where the air outlet is formed. Two ends of each stationary blade are respectively fixed to an outer periphery of the seat and an inner periphery of the frame. Furthermore, extending directions of any two adjacent stationary blades jointly define an included angle, and all of the included angles formed by all of the stationary blades are of more than two values in degrees, so that the stationary blades are not spaced with equal intervals. Consequently, while sucked air passes by the stationary blades, noises with the same tone can be suppressed effectively.

Abstract: A wedge-type diffuser includes a diffuser floor and a plurality of wedge-shaped vanes. The wedge-shaped vanes extend from the diffuser floor and have a top surface, a leading edge and a trailing edge. Each of the wedge-shaped vanes has a slot extending from the trailing edge toward the leading edge.

Abstract: Diffusion in the vane island passages of a centrifugal compressor diffuser is in part controlled by contouring the diffuser passage wall with low profile surface variations. The surface variations can be provided in the form of flow boundary disrupting protrusions disposed within the downstream portion of the vane island passages to prevent flow separation.

Abstract: A system, in certain embodiments, includes a plurality of detachable, three-dimensional diffuser vanes attached to a diffuser plate of a centrifugal compressor. In certain embodiments, the detachable, three-dimensional diffuser vanes may be attached to the diffuser plate using threaded fasteners. In addition, dowel pins may be used to align the detachable, three-dimensional diffuser vanes with respect to the diffuser plate. However, in other embodiments, the detachable, three-dimensional diffuser vanes may include a tab configured to fit securely within a groove in the diffuser plate. In addition, the tabs of the detachable, three-dimensional diffuser vanes may include indentions that mate with extensions extending from the diffuser plate, wherein the tabs may slide into slots between the extensions and the grooves of the diffuser plate.

Abstract: A centrifugal air blower guides returning air from a fan rotated by a rotational drive source out of interference with air delivered by a fan. The centrifugal air blower includes a rotational drive source having a rotational drive shaft, a housing including a holder which holds the rotational drive source in surrounding relation thereto, and a fan coupled to the rotational drive shaft of the rotational drive source. The housing has a disk-shaped flange extending from the holder, and the flange has a plurality of air guides disposed on a surface thereof and extending toward a peripheral edge of the flange.

Abstract: A powerless diversion plate of a ceiling air-conditioning circulation machine includes a bearing block and a bearing within a circular inflow/outflow hole for installing a diversion disc having a plurality of radial separation pieces. A plurality of conic and ring-shaped diversion pieces are positioned around the connection shaft. The diversion disc is separated by the ring-shaped diversion pieces and the radial separation pieces to create air inflow/outflow zones. The diversion disc has a downward protruding middle part and a staged structure at the rim thereof to form a predetermined shape. This obviates a powered motor, as the radial separation pieces of the diversion disc serve as a working surface, and respond to forced air for causing the diversion disc to be driven in 360° rotation to diffuse air downward or suck air upward in a flowing way, thereby enhancing air-outflowing and convection efficiency and reducing energy consumption and carbon release.

Abstract: A heat dissipating fan structure of a dual motor includes: a base device, having a fan base, and the fan base having a fan motor; a fan, connected and rotated by the fan motor, and the fan having a plurality of vanes; a support frame device, installed at the fan base, and having a frame-fan motor; a frame-fan device, connected and rotated by the frame-fan motor, and having a frame-fan frame, and a plurality wing plates disposed around the frame-fan frame, and the wing plates being disposed around the external periphery of the fan and perpendicular to the vane, so that the plurality wing plates on the frame-fan base can produce an auxiliary airflow to increase the airflow of the fan and give a better heat dissipating effect.

Abstract: An axial fan apparatus including an axial-flow impeller, a drive unit, and a housing. The axial-flow impeller is capable of rotating and includes a plurality of blades inclined with respect to a rotational axis direction. The drive unit rotates the axial-flow impeller. The housing is mounted with the drive unit, and includes a sidewall, and a plurality of slits that circulate gas. The sidewall is provided around the axial-flow impeller. The plurality of slits are provided to the sidewall and inclined with respect to the rotational axis direction in a direction opposed to a direction in which the plurality of blades incline.

Abstract: An air guide apparatus includes a body installed at a discharge side of a rotary fan for sucking air, a plurality of first vanes arranged at one surface of the body to guide air sucked by the rotary fan toward the outer circumferential surface of the body, and a plurality of second vanes arranged on the other side of the body to guide air which has been guided by the first vanes from the outer circumferential surface of the body toward a central portion, formed in a spiral shape from the central portion of the body toward the outer circumferential surface of the body, and having disconnected portions formed at middle portions thereof.

Abstract: An airflow-cooling apparatus of a ceiling air-conditioning circulation machine, and more particularly a structure permitting a smooth flow of the indoor air, wherein the drawn current of air passes through a cooling apparatus and then is guided indoors for reducing the temperature. A base frame includes a base frame having a rectangular positioning frame of the rim thereof. A plurality of radial supports are extended from the periphery of the positioning frame inwards. A circular frame is positioned at the center of the base frame. The rim of the circular frame is attached to the radial supports. A fan base is positioned within the circular hole of the circular frame and supported by a plurality of ribs. A plurality of conic and ring-shaped air outflow/inflow channels are concentrically and outwardly interposed between the circular frame and the positioning frame.

Abstract: A shrouded fluid turbine includes an impeller for generating power from a fluid stream and a shroud surrounding the impeller. The impeller and/or the shroud have a moveable member for controlling power generation in the fluid turbine. The shroud has a plurality of mixing lobes on a trailing edge thereof, the trailing edge having a circular crenellated shape. The power generation is controlled by reducing loads and/or controlling impeller speed. Various moveable components are described for the stator vanes and the rotor blades.

Abstract: A diffuser for a gas turbine system having a longitudinal axis is disclosed. The diffuser includes a plurality of diffuser ducts. Each of the plurality of diffuser ducts is disposed annularly about the longitudinal axis and has an inlet, an outlet, and a passage extending between the inlet and the outlet. The outlet of each of the plurality of diffuser ducts is tangentially offset from the inlet of the respective diffuser duct. Each of the plurality of diffuser ducts is configured to flow a gas flow therethrough, reducing the gas flow velocity.

Abstract: A centrifugal pump with a volute and at least one stage with an associated impeller and removable diffuser assembly comprises: multiple diffuser segments, each diffuser segment comprising a central passage from an inner curvilinear surface to an outer curvilinear surface and a curvilinear leading engagement surface between a leading end of its curvilinear inner surface and its curvilinear outer surface; multiple curvilinear volute mounting surfaces within the volute, each curvilinear mounting surface receiving a corresponding diffuser segment to mount the diffuser segments in a generally annular pattern about the impeller to form the removable diffuser assembly, with the curvilinear inner surface of each diffuser segment proximate an outer periphery of the impeller and the curvilinear leading engagement surface of each diffuser segment engaging a trailing portion of the curvilinear outer surface of an adjacent one of the diffuser segments; and a volute connecting passage within the volute for coupling the cen

Abstract: A fluid turbine comprises a turbine shroud and an optional ejector shroud. The turbine shroud and/or the ejector shroud are formed from a hard shell and a membrane. The hard shell forms a leading edge, a trailing edge, and an interior surface of the shroud. The membrane forms an exterior surface of the shroud. The resulting construction is lighter than previous turbine shrouds.

Abstract: A stationary vane assembly of a turbine engine including an inner casing and a high-pressure turbine guide vane assembly including at least two angular sectors including blades, the angular sectors being fixed on the casing, each angular sector including a platform and a fastening tab. The fastening tab protrudes from the platform radially inwardly. The casing includes a first annular groove receiving the fastening tabs, radial retaining pins for the angular sectors being introduced into bores made in the casing and the fastening tabs, the axial retaining pins being axially stopped by a ring mounted in a second annular groove of the casing.

Abstract: A turbine airfoil (31) with an end portion (42) that tapers (44) toward the end (43) of the airfoil. A ridge (46) extends around the end portion. It has proximal (66) and distal (67) sides. A shroud platform (50) is bi-cast onto the end portion around the ridge without bonding. Cooling shrinks the platform into compression (62) on the end portion (42) of the airfoil. Gaps between the airfoil and platform are formed using a fugitive material (56) in the bi-casting stage. These gaps are designed in combination with the taper angle (44) to accommodate differential thermal expansion while maintaining a gas seal along the contact surfaces. The taper angle (44) may vary from lesser on the pressure side (36) to greater on the suction side (38) of the airfoil. A collar portion (52) of the platform provides sufficient contact area for connection stability.

Abstract: A radial exhaust gas turbine apparatus has a gas turbine engine that includes a radial exhaust diffuser section and a casing apparatus consisting essentially of polygonal walls, substantially straight plates, and substantially straight sidewalls. The casing apparatus encloses the radial exhaust diffuser section and is configured to direct at least a substantial portion of the gas exiting the radial exhaust diffuser section to an exit in the casing apparatus via an approximately involute path.

Abstract: A fluid turbine comprises a turbine shroud, an ejector shroud, and a means for extracting energy from a fluid stream. The means for extracting energy is located in the annulus between the turbine shroud and the ejector shroud. High-energy fluid can flow through the turbine shroud to bypass the means for extracting energy. Energy is extracted from the fluid passing through the means to form a low-energy fluid stream. The high-energy fluid and the low-energy fluid can then be mixed. The turbine shroud and/or the ejector shroud has mixing lobes to increase the mixing of the two fluid streams.

Abstract: A system for forming a seal slot in a shroud assembly has a first element having a longitudinally extending slot and a second element having a longitudinally extending slot for receiving a portion of the first element. The first element has a pair of opposed surfaces and the second element has a pair of opposed surfaces which are oriented at an angle to the surfaces of the first element. The second element may have a planar portion and a curved portion adjacent the planar portion for forming a slot which allows a flow of fluid to exit the slot at a desired angle.

Abstract: In exemplary embodiments, a nozzle can include a first flow wall, a second flow wall and a vane disposed between the first and second flow walls, wherein the vane is mechanically coupled to the first flow wall and in contact with the second flow wall.

Abstract: A row of stator blades in a compressor of a combustion turbine engine, the combustion turbine engine including a diffuser located downstream of the compressor, and the row of stator blades disposed in close proximity to the diffuser; the row of stator blades comprising: a plurality of stator blades that include at least one of an inboard forward notch and an outboard forward notch.

Abstract: A compressor of a turbine engine, the compressor including stator blades with shrouds, the shrouds being surrounded, at least in part, by rotating structure and forming a shroud cavity therebetween, the compressor including: a plurality of tangential flow inducers disposed within the shroud cavity; wherein each tangential flow inducer comprises a surface disposed on the rotating structure that is configured such that, when rotated, induces a tangential directional component to and/or increases the velocity of a flow of leakage exiting the shroud cavity.

Abstract: A fan section of a gas turbine engine having an axially extending centerline is provided. The fan section includes a fan assembly, a fan containment case, and a plurality of structural exit guide vanes. The fan assembly includes a fan rotor hub centered on and rotatable about the centerline, and a plurality of fan blades that are attached to and extend radially out from the fan rotor hub. The fan containment case is disposed radially outside of and circumferentially around the fan assembly. The fan containment case includes a shell and an integral flange ring that extends around the circumference of the shell, a circumferentially extending blade outer air seal disposed between the fan blades and the shell. The structural exit guide vanes are mechanically attached to the fan containment case at a position aligned with the integral flange ring.

Abstract: A fluid turbine comprises a turbine shroud and an ejector shroud. The turbine shroud has an axial length LM. The ejector shroud has an axial length LE. The ratio of LM to LE is from 0.05 to 2.5. In particular embodiments, the ejector shroud has an axial length LE, an outer diameter DI at the inlet end, and an outer diameter DE at the exhaust end. The ratio of LE to DI is from 0.05 to 3; and the ratio of LE to DE is from 0.05 to 3. The resulting ejector shroud is 30%-50% shorter than ejector shrouds of previous designs.

Abstract: A stage for a gas turbine engine, having a plurality of circumferentially spaced apart radially extending aerofoils, includes a plurality of annulus fillers to bridge the spaces between adjacent aerofoils to define an inner wall of a flow annulus through the stage. Each annulus filler has opposing side faces which are spaced circumferentially from the adjacent blades and which correspond in profile therewith, and resilient seal strips each including a stiffener are mounted adjacent the opposing side faces of the annulus fillers to seal the gaps between the annulus fillers and the aerofoils. The stiffeners have three-dimensional curvature.