Abstract: The invention relates to a guide blade segment of a thermal turbomachine, in particular a gas turbine, comprising a number of profiled blades which are arranged on a platform. A plurality of securing elements for securing the guide blade segment to an associated guide blade support are arranged on the side of the platform which is oriented away from the blade. The aim of the invention is to provide a guide blade segment which can be produced in a simple and economical manner avoiding casting problem areas enabling the guide blade segment to be attached in a particularly reliable and secure manner to the associated guide blade support. According to the invention, at least one section of at least one of the securing elements is a separately produced component which is rigidly connected to the platform or to an additional section of the securing element.

Abstract: A pond pump comprising an impeller (2) which rotates about an axis of rotation (X) within a pump housing (1). The pump housing (1) comprises a suction inlet (11) that is coaxial to the impeller (2), a pressure outlet (14) for the water that is to be conducted, the pressure outlet (14) being disposed in a radial to tangential direction relative to the impeller (2), and a counterflow plate (12) between the suction inlet (11) and the pressure outlet (14). The impeller (2) is fitted with a radially disposed disk (22) with vanes (21) that are arranged on one side thereof. The counterflow plate (12) is on the impeller side encompassing the vanes (21) while channels (23) that are formed between the vanes (21) have a cross-section which tapers from the inner radial face to the outer face.

Abstract: Apparatuses and methods are provided for a wind diverter at least partially encircling a wind turbine support column to direct the wind from an area around a wind turbine to the rotor blades of the wind turbine. The wind diverter may also reduce turbulence and increases the laminar flow of the airstream delivered to the rotor blades. Additionally, the wind diverter increases both the volume of air and the velocity of the airstream reaching the rotor so as to increase the rotor speed. Increasing the rotor speed increases the energy available to the wind turbine. Energy increases as the cube of the rotor speed and the increased energy produces an increase in the power generated by the wind turbine. The wind diverter also allows a wind turbine to begin producing energy at lower initial wind speeds due to the concentration of air.

Abstract: A rotor for driving, or being driven by, a fluid has rotor blades that follow a screw thread shape, all portions of all blades having the same screw pitch. This enables the rotor, or a molding pattern for use in making a mold, to be withdrawn from a mold part by a screw motion without damage to the mold part. This helps to make it economically viable to manufacture the rotor by a molding or casting process in which the mold parts are not destroyed to release the rotor, such as injection molding, for example with reinforced plastics. Additionally, in the case of manufacturing methods in which the mold is destroyed to release the rotor, the process of making or assembling the mold may be improved. In some molding processes, the ability to remove the rotor or the pattern by screw motion improves the economic viability of the process by reducing the number of mold parts required.

Abstract: A diffuser is provided that includes a first wall, a second wall, and a first plasma actuator. The first wall has a radially-extending section and a curved section. The second wall has a radially-extending section and a curved section that are spaced apart from the radially-extending section and the curved section of the first wall such that the curved section of the second wall is disposed radially inwardly from the curved section of the first wall and a flow path is defined therebetween. The first plasma actuator is disposed on the curved section of the second wall, and the first plasma actuator is adapted to generate a first electric field to ionize a first portion of air flowing along the flow path to form a plurality of ionized species capable of inducing a second portion of air to flow in a desired direction.

Abstract: The flow of fluid into energy capture machines is crucial for determining the amount of energy extracted, particularly in the field of renewable energy resources. The current invention describes devices and methods for applying the physics of flow to energy capture machines, most commonly wind and water turbines, by enhancing the flow into the energy capture component by the appropriate placement of various objects called flow deflection devices (FDD). FDDs can make a highs significant improvement in power output.

Abstract: Embodiments for a compressor stator vane assembly in a gas turbine engine are disclosed. In an embodiment of the present invention a stator vane assembly is provided having a plurality of vanes each with an attachment and channels machined into the forward and aft walls of the attachment. A forward hook ring segment is pressfit into the channel in the forward wall of the attachment and an aft hook ring is pressfit into the channel in the aft wall of the attachment. The hook ring segments join a plurality of vanes together so as to provide a uniform engagement of mounting slots in the compressor case. Such an arrangement increases the contact area between the hook rings and the compressor case such that damping of individual vane vibrations are improved and operating stresses are reduced.

Abstract: A multi-functional air circulation system includes a bottom base, a flow-splitting base, a filter and a main engine. The bottom base has a lower flow-guiding surface, a net, and a space used to contain diverse improving agents. The flow-splitting base is fixed on the bottom base, including an inner flow-guiding surface to rush air flow generated by a blade member down to the bottom base. The filter is laid at an exit of the inner flow-guiding surface, composed of two filter bases forming a room between them for containing aromatic powder, etc. The main engine includes a motor having its shaft fixed with a blade member, and a control system. The motor is installed in a rear shell combined with a front shell. Air is sucked in through the rear shell to run through an ornamental shell and the flow-splitting base to enter a room. The main engine and the bottom base can also be assembled to work independently.

Abstract: A fan variable area nozzle (FVAN) includes a flexible adaptive segment which defines the fan nozzle exit area. The flexible adaptive segment generally includes a multiple of flexible sections, a linkage and an actuator system to morph the flexible adaptive segment between a converged shape and a diverged shape. The flexible adaptive segments seal an interface between sectors to provide an asymmetrical fan nozzle exit area.

Abstract: The invention relates to a stator blade (4) of a turbomachine, especially of a steam turbine, which has the following geometric features. A lean curvature, a swept curvature, a twist in the radial direction of the respective blade (4), a hub-side circumferential step (14) which in the direction of flow (15) falls away inwards and radially to the rotational axis (8) of the turbomachine, a chord length (s) of the blade which varies over the radial extent of the stator blade (4), and also a cross-sectional profile of the blade (4) which varies over the radial extent of the stator blade (4).

Abstract: The invention relates to a turbine, in particular of an exhaust-gas turbocharger, comprising a turbine rotor which is supported rotatable in a housing, and to which at least one guide vane apparatus forming a radial inlet channel for a medium driving the turbine rotor is allocated, wherein the guide vane apparatus comprises a guide vane mounting ring with a plurality of guide vanes which radially surround the turbine rotor and which are located within the inlet channel, as well as a guide vane cover ring, and wherein the inlet channel is axially bounded by the guide vane mounting ring and the guide vane cover ring, and the guide vane cover ring abuts with a front side facing away from the inlet channel against a support area of the housing. The invention provides that the housing (5) comprises in the support area (15) at least one recess (17) which is open-edged towards the guide vane cover ring (9), and through which the medium can flow.

Abstract: The invention relates to a workpiece (1), in particular a rotor disc, an impeller or guide wheel for a turbine, for a pump or for a compressor, including a base body (2) with a guide vane (3), wherein the guide vane (3) is welded in notch-free manner to the base body (2) and/or to a cover part (4). Furthermore, the invention relates to a welding method for the manufacture of a workpiece (1).

Abstract: A reaction mount system that provides support for the stator vane for a gas turbine engine is described comprising a stator hanger located on an outer band at a first location and a stator stopper located at a second location that is located circumferentially apart from the first location. A stator assembly for a gas turbine engine is described, the stator assembly comprising a stator vane having an airfoil, an outer band located on a radially outer end of the airfoil, a shroud hanger located axially adjacent to the outer band, the shroud hanger comprising a post wherein at least a portion of the post extends in an axial direction over a portion of the outer band, and a reaction mount system located on the outer band wherein the reaction mount system engages with the post to provide support for the stator vane.

Abstract: A turbine component includes a flow path surface and a trench disposed in the flow path surface. At least one cooling through hole is located in the trench and is capable of injecting a cooling flow onto the flow path surface of the turbine component. The cooling flow forms a cooling film on the flow path surface. A method of cooling a turbine component includes injecting a cooling flow onto a flow path surface of the turbine component through at least one cooling through hole disposed in a trench in the turbine component. A cooling film is formed by the cooling flow between the flow path surface and a hot gas flow.

Abstract: A method and system of supporting removable static components in a turbine engine stator assembly is described. The method comprises the steps of engaging a stator hanger located at a first location on a first static component with a post located on a first static structure whereby the post supports at least a part of the weight of the first static component, engaging a stator stopper located at a second location on the first static component that is located circumferentially apart from the first location with the stator hanger that is located on a second static component, and engaging a hook located at a third location on the first static component with a second static structure whereby the second static structure supports at least a part of the weight of the first static component.

Abstract: Subassemblies are arranged in the interior of a closed housing. The housing has an air inlet via which air-conditioning air is guided into the interior of the housing. The housing contains a fan via which the air used for the air conditioning of the subassemblies is guided to the outside from the interior of the housing. In addition to a fan input opening, the fan has at least two fan output openings wherein a rotatably mounted screen is arranged in the interior of the fan. By variably adjusting the position of the screen, the air sucked in via the fan input openings is optically guided via at least one of the fan output openings.

Abstract: A power plant includes a first turbine having a plurality of turbine stages. The first turbine discharges a first fluid flow. A second turbine is operatively coupled to the first turbine. The second turbine receives the first fluid flow from the first turbine and a second fluid flow. An interface member is mounted between the first and second turbines. The interface member includes a main body portion having an inner surface, an inlet portion and an outlet portion that combine to form a fluid flow path that extends between the first and second turbines. The interface member further includes an input member having an input passage that leads the second fluid into the fluid flow path. The interface member also includes a baffle plate that extends toward the fluid flow path. The baffle plate establishes a flow gap between the input passage and the inlet and outlet portions.

Abstract: Kinetic energy contained in oceans, rivers and channels can be converted to power using kinetic hydro turbines. These turbines can be tethered to the ocean floor, riverbed and channel bottom and their vertical position within the water column controlled. A method is disclosed that permits to increase the power extracted by the turbine by modifying the boundary layer using a shaped object located upstream of the turbine to increase the flow velocity through the turbine. The object also provides protection during climatic events like spring ice breakup, logs and storms that could damage the turbine. Additionally the shaped object can allow the turbine to be tethered to it. The shaped object can be made symmetric to allow operating in tidal conditions where the flow direction changes periodically. On site manufacturing can also alleviate overall costs.

Abstract: For the rotor and stator blades of turbomachines, more particularly of gas-turbine engines, an airfoil design is provided with a defined area of a skeleton line angle distribution for skeleton lines of airfoil sections near the gap. With the distribution of the dimensionless skeleton line angles (?) over the chord length (I) in a certain area between two limiting curves (7, 8) according to the present invention, and the corresponding course of the skeleton lines in a blade portion extending up to 30 percent of the blade height, a uniformed pressure distribution is ensured, minimizing disturbances and losses due to the influence of the gap.

Abstract: A method for repairing a cantilevered stator vane includes removing a damaged portion leaving a remaining vane portion. A supplemental airfoil portion is then selected and is attached to the remaining vane portion to provide a repaired cantilevered stator vane.

Abstract: A vane ring damper for a small turbomachine, the vane ring having a plurality of vanes extending between an inner ring and an outer ring and forming a gas flow path, where one of the inner and the outer rings have cuts formed between adjacent vanes to form separate ring segments. In one embodiment, a frictional damper is positioned between the ring segments to provide frictional damping for the vane assembly. in another embodiment, the cuts are formed at about a 45 degree angle and the space is narrow such that adjacent segments rub during vibration and provide the frictional damping for the vane assembly. Inner or outer bands are used to secure the ring segments together and to hold the frictional damper within the space formed between adjacent ring segments. Cuts can be formed between every vane to form a ring segment for each vane, or cuts can be formed in an alternating series such that two or more adjacent vanes extend from a common ring segment.

Abstract: An inlet guide vane is turnably installed about an axis line at a suction port into which a fluid is drawn by rotation of an impeller in order to adjust a suction amount and flow direction of the fluid, the inlet guide vane, and includes: a shaft that is turnably supported by inserting a round bar-shaped shaft main body portion thereof in a bearing sleeve; and a plate-shaped vane main body that is joined with the shaft and projects from an inner periphery surface of the suction port to a central portion of the suction port, the shaft including a flange portion that is provided at a distal end side in a direction of the axis line to join with the vane main body and that extends to an outside in a direction perpendicular to the axis line so as to be extended outward in a radial direction of the bearing sleeve.

Abstract: Use of the stator blade platforms for the deposition of a track of adjacent abradable material inside an external turbomachine shell. The stator blades (13) are attached to the shell (11) so as to define an annular edge (33) that is substantially continuous and the abradable material is deposited using this edge to delimit a boundary of said track of abradable material (15).

Abstract: The invention concerns a novel type of turbomachine. According to the invention, the stator of the turbomachine comprises a plurality P of profiled members forming stiffeners arranged on the blade stage while being distributed uniformly at its periphery and individually between two consecutive blades, the stiffeners being fixed to the internal and external ferrules of the stator in order to uniformly increase the axial and radial stiffness of the stator in normal operation of the turbomachine and to allow to the internal ferrules to have. The invention makes it possible to reduce the axial sizing of the turbomachine, and consequently its mass. Application to aircraft engines, such as jet engines.

Abstract: A centrifugal blower (10) includes a bottom housing (12), a top cover (14) covering the bottom housing, and an impeller (16) and a stator accommodated in a space formed between the bottom housing and the top cover. The bottom housing includes a base plate (121), and a sidewall (122) surrounding the base plate. The sidewall includes a tongue (126) extending from the sidewall towards an inner space enclosed by an inner surface of the sidewall. The tongue is slantingly arranged with respect to a top surface (121a) of the base plate and size of a transverse section of tongue is variable changing along a height direction of the tongue.

Abstract: A nacelle assembly for a turbine engine has a cowl. The cowl extends along an axis and has an exterior surface spaced from an interior surface. The interior surface forms an air inlet for directing airflow to the turbine engine. A turbulator for creating turbulence is disposed on one of the interior surface and the exterior surface.

Abstract: An axial turbine includes a plurality of stages, each of the plurality of stages having stationary blades adjacent to each other along the turbine circumferential direction and corresponding moving blades adjacent to each other along the circumferential direction, each of the moving blade being located downstream of a corresponding one of the stationary blades along a flow direction of a working fluid, so as to be opposed to the corresponding stationary blade. In this axial turbine, each of the stationary blades is formed so that the intersection line between the outer periphery of the stationary blade constituting a stage having moving blades longer than moving blades in a preceding stage and a plane containing the central axis of the turbine, has a flow path constant diameter portion that includes at least an outlet outer periphery of the stationary blade and that is parallel to the central axis of the turbine.

Abstract: A portable-blower duct has a bendable portion whose inner peripheral surface is a cylindrical surface without any protrusions or recesses in a normal state or in an expanded state, that is, unless it is greatly curved. With this construction, no turbulence is generated in air passing through a tube, thereby making it possible to suppress pressure loss. Thus, the flow velocity of air guided through the duct is not reduced, thereby suppressing a deterioration in air blowing efficiency. Even when the tube is curved, the outer side of the curved portion is expanded, and the corresponding portion of the inner peripheral surface remains a smooth surface, thus making it possible to minimize the air pressure loss.

Abstract: This invention relates to a nacelle for bypass engine with a high bypass ratio comprising an interior flow channel for a secondary flow generated by the bypass engine and having an external structure provided with a reverse thrust device capable of alternately shifting from a closed position in which it enables circulation of the direct-jet secondary flow inside the interior channel, to an open position in which it uncovers an opening in the external structure so as to enable reorientation of the secondary flow in an angled flow via activation of the reverse thrust means; in open position, the reverse thrust device partially blocks the interior channel so as to provide a leakage section therein, enabling circulation of a controlled leakage flow, said nacelle being characterized in that, when the thrust reversal device is in open position and has an angled-jet reversal section and a leakage section through the interior channel the sum of which is substantially equal to a direct-jet secondary flow discharge sec

Abstract: An air conditioner includes a fan and a rear guide which guides air to the fan. A recess is formed in a side surface of the rear guide which faces the fan.

Abstract: A flow structure is for a gas turbine, e.g., for an aircraft engine, in a transition channel between two compressors or in a transition channel between two turbines or in a transition channel of a turbine outlet housing downstream from a low-pressure turbine, having support ribs positioned in the transition channel spaced apart from one another around the circumference of the transition channel. A channel wall which delimits the transition channel radially on the inside and/or a channel wall which delimits the transition channel radially on the outside may be drawn inwardly into the transition channel in the area of the outflow edges of the support ribs.

Abstract: A fan inlet flow distributor comprises a skewed elliptical cone or equivalent body installed between an inlet opening of a centrifugal blower and an adjacent wall that faces the inlet. When all of the incoming airflow approaches the blower from the same general direction parallel to the wall and then makes a right turn to enter the blower's inlet, the unique shape of the flow distributor promotes a circumferentially uniform flow pattern as the air enters the fan's inlet. In some embodiments, the flow distributor comprises a skewed elliptical hyperboloid near its base and a skewed elliptical paraboloid near its vertex. The flow distributor is preferably attached to the wall and spaced apart from the fan's housing to ensure an unobstructed flow path between the distributor and the fan housing.

Abstract: A compressor case support arrangement for a gas turbine engine includes a fan section having a central axis and a compressor case for housing a compressor. An inlet case guides air to the compressor. The compressor case is positioned axially further from the fan section than the inlet case. A support member extends between the fan section and the compressor case. The support member restricts movement of the compressor case relative to the inlet case. The support member is positioned axially further from the fan section than the plumbing access area.

Abstract: The present invention provides a vane structure of an airflow generator. The plate of predefined thickness and width has a locating portion and a swinging end. The swinging end of the vane is wider than the locating portion. There is an oblique section placed between the swinging end and locating portion for linking purposes. A better wind guide effect can be obtained from the expanded swinging end, and the oblique section is employed to reduce inlet stagnation, thus greatly improving the smoothness of air flow and the operating performance of the vane with better applicability.

Abstract: A method of repairing a turbine engine component involves offering two repair options to a customer. A first repair option is based on an operating environment of the turbine engine component and the second repair option is based on cost. The first repair option is priced higher than the second repair option. The turbine engine component is examined. The turbine engine component is then repaired according to the selected repair option.

Abstract: An article of manufacture having a nominal profile substantially in accordance with Cartesian coordinate values of X, Y and Z set forth TABLE I. The X and Y values are distances in inches, which when connected by smooth continuing arcs define airfoil profile sections at each distance Z in inches The X, Y and Z distances may be scalable as a function of the same constant or number to provide a scaled up or scaled down airfoil section for the nozzle. The nominal airfoil given by the X, Y and Z distances lies within an envelope of +0.130 inch to ?0.030 inch.

Abstract: A serial fan module includes a first fan, a second fan and a plurality of guide elements. The first fan has a first frame body and a first impeller disposed within the first frame body. The second fan has a second frame body and a second impeller disposed within the second frame body. The guide elements are disposed between the first impeller and the second impeller, wherein the guide elements guide airflow from the first fan to the second fan. Each of the guide elements has an axial extended part and an inclined part and the inclined part meets the axial extended part at a camber angle. Each of the inclined part has an inner edge toward the first impeller and each of the axial extended part has an outer edge toward the second impeller.

Abstract: A heat-dissipating device includes a housing having an air inlet and an air outlet, and a rotor disposed in the housing and having a first set of blades, wherein the housing has a sidewall extending inward from the air inlet to define an air-gathering chamber in the housing, and a plurality of air-guiding members disposed along the sidewall for increasing and stabilizing a blast pressure of airflow passing through the heat-dissipating device.

Abstract: Disclosed is a leakage reducing venturi for a dry low nitric oxides (NOx) emissions combustor, the venturi including a substantially annular outer liner, a substantially annular inner liner, a venturi channel defined by the annular inner liner and the annular outer liner, the venturi channel including a forward end and an aft end, a forward weld disposed in proximity to the forward end of the venturi channel, the forward weld being configured to connect the annular outer liner with the annular inner liner, and an aft weld disposed in proximity to the aft end of the venturi channel, the aft weld being configured to connect the annular outer liner with the annular inner liner.

Abstract: The present invention provides an improvement in a new structure of a regenerative pump, including a cross section structure of the flow channel of a pump casing and closed type impeller, whereby to improve a better flow model for pump performance to solve problems of noise, and to increase the outflow capacity and higher efficiency.

Abstract: Flow energy installation with at least one in particular roller-like rotor (1) which rotates about an axis (A1) and has a plurality of rotor blades (2), wherein one, a plurality or all rotor blades (2) have associated with them at least one efficiency-improving air conducting fin (3) which in the direction of rotation is arranged upstream or downstream of the rotor blade (2) and/or the rotor is at least partly surrounded by at least one efficiency-improving diffuser element, and wherein the flow energy installation can be operated with liquid and/or gaseous media at any desired orientation of the axis (A1).

Abstract: Systems and methods involving struts are provided. In this regard, a representative system includes a gas turbine engine defining a gas flow path. The gas turbine engine comprises a strut extending into the gas flow path. The strut has an interior operative to receive pressurized air, an outer surface, and ports communicating between the outer surface and the interior of the strut, the ports are operative to receive the pressurized air from the interior and emit the pressurized air into the gas flow path such that an effective aerodynamic length of the strut along the gas flow path is increased.

Abstract: A fluid dynamic device including a shroud disposed about a central axis and having an upstream fluid intake region and a downstream fluid exit region, the shroud directing fluid flow between the upstream fluid intake region and the downstream fluid exit region. The shroud is configured so that, at least during some operating conditions of the fluid dynamic device, at least a portion of fluid exiting the fluid exit region is directed towards the central axis.

Abstract: A blower assembly 10? includes a housing 18? having an inlet 19 and an outlet 20. The housing includes an inlet ring 22? at the inlet. A blower wheel 12? is mounted for rotation in the housing. An electric motor 16 includes a shaft 14 having an axis B. The shaft is coupled to the blower wheel so that rotation of the shaft causes rotation of the blower wheel that causes air to flow from the inlet to the outlet. The inlet ring has an annular extension 24 extending linearly in the same direction as the shaft axis B. An end 26 of the blower wheel 12? is within bounds of the extension 24.

Abstract: A novel three-vaned, drag-type wind turbine, wherein air, when it exits a first vane, is split into two flow paths. A first path is directed to a second vane, while a second path is directed to a third vane. The air, then, impinges on a plurality of vanes wherein the momentum of the air is altered, thus providing the force needed to drive the wind turbine. In a first embodiment, a wind shield is used to deflect a portion of the wind from entering the wind turbine, this portion being in a region where the vanes are rotating into the wind. In second embodiment, the wind shield is not used.

Abstract: A vane has an airfoil shell and a spar within the shell. The vane has an outboard shroud at an outboard end of the shell and an inboard platform at an inboard end of the shell. The shell includes a region having a depth-wise coefficient of thermal expansion and a second coefficient of thermal expansion transverse thereto, the depth-wise coefficient of thermal expansion being greater than the second coefficient of thermal expansion.

Abstract: Disclosed is a method of producing a stator blade for use in a turbo-molecular pump. The method includes subjecting a metal plate to a slitting process to form a blade element having an upstream edge surface and a downstream edge surface, wherein a laser beam is emitted onto the metal plate at an incident angle oblique to a principal surface of the metal plate. Thus, the upstream edge surface and/or the downstream edge surface can be formed to extend obliquely relative to the principal surface of the metal plate, in a simple manner, while eliminating a need for a burr removal operation which would otherwise be necessary in a punching-based slitting process.

Abstract: An assembly including a metal piece, a piece made of ceramic material, and at least one intermediate connection element assembled to each of the pieces by brazing. The intermediate connection element includes a deformable sheet presenting at least two flat zones brazed to respective ones of the pieces, the two flat zones being interconnected by a deformable zone presenting at least two free undulations oriented in alternation towards the metal piece and towards the piece made of ceramic material.

Abstract: A containment system comprises at least one passage obstructer extending from a housing inlet cover through a diffuser passage and into a housing back cover. The passage obstructer includes a fastener portion, such as a bolt, and an obstructing portion extending from and integral to a shaft of the fastener portion. The diameter of the obstructing portion is less than the diameter of the shaft, allowing the obstructing portion to bend upon impact with a burst impeller fragment.

Abstract: A novel and useful improvement to vane pumps, both variable displacement vane pumps and fixed displacement vane pumps, provides a supply of pressurized fluid to the region within the diameter of the pump rotor which would otherwise be a region of reduced pressure wherein air could be ingested by the pump. By reducing or preventing the ingestion of air, operating noise and damage to the pump can be reduced and wear in an engine or other system supplied from the pump can be reduced. The supply of pressurized working fluid also can be used to lubricate auxiliary components and/or accessories as well. Further, a portion of the supply of pressurized working fluid to this region can act to supercharge the pump, reducing the occurrence of cavitation at higher operating speeds.