Abstract: A mixer having a unitary construction is disclosed comprising an annular housing having an axis and at least a first swirler having a plurality of vanes arranged circumferentially around the axis such that circumferentially adjacent vanes form at least one flow passage that is oriented at least partially in an axial direction with respect to the axis. In another exemplary embodiment, a mixer having a unitary construction is disclosed comprising a swirler having a plurality of radial vanes arranged circumferentially around the axis and oriented at least partially in a radial direction.

Abstract: A wind power installation module comprising wind turbines arranged on a support body, each of the wind turbines comprises a rotor with a certain number of blades, a stator supporting the rotor in such a way that the rotor may rotate on the turbine axis for generating electric energy and a shroud extending circumferentially around the stator and the rotor and supporting the stator so as to define an air channel of a certain air channel diameter at an inlet portion of the shroud. The shroud has a maximum outer diameter such that the air channel diameter is comprised in the range from 0.82 to 0.9 times the maximum outer diameter. Furthermore, the shroud has a length in direction of the turbine axis that is comprised in the range from 0.1 to 0.25 times the outer diameter.

Abstract: A blower for providing a supply of air at positive pressure in the range of approximately 2 cm H2O to 30 cm H2O includes a motor, at least one impeller, and a stationary component. The stationary component includes an inlet and an outlet. The motor, the impeller, the inlet and outlet are co-axial.

Abstract: A variable geometry inlet guide vane assembly that reduces stress placed on downstream compressor blades in gas turbine engines. The invention circumferential leans upstream guide vanes, pushing engine core air flow radially. This allows for aerodynamic stresses on the downstream blades to be reduced. The invention overcomes the difference in movement between a unison ring and a vane arm by providing a hinge in conjunction with a spherical bearing that couples to the unison ring.

Abstract: A gas-turbine axial compressor has a casing 3 and a rotatable shaft 5, which form an annular duct, in which at least one stator 2 and one rotor 4 are arranged. A shroud 21 is arranged at a free end of the stator 2 vanes, which extends over part of the axial length of the stator 2. A further part of the axial length of the stator 2, at which no shroud 21 is arranged, radially adjoins a rotor platform 28 formed by a rotor hub 8.

Abstract: A tip turbine engine according to the present invention includes a plurality of independently variable inlet guide vanes for the fan and/or for the compressor. An actuator is operatively coupled to each of the flaps, such that each actuator can selectively vary the flap of its associated inlet guide vane. In one embodiment, the inlet guide vanes each include a pivotably mounted flap that is variable independently of the flaps of at least some of the other inlet guide vanes. In another embodiment, the inlet guide vanes each include at least one fluid outlet or nozzle directing pressurized air, as controlled by the associated actuator, to control inlet distortion.

Abstract: A diffuser for use in a centrifugal compressor that includes an impeller that discharges a high-velocity flow of fluid. The diffuser includes a platform having a blade portion and defining a substantially circular aperture. The impeller is disposed at least partially within the aperture such that the high-velocity fluid exits the impeller in directions that are substantially tangent to the blade portion. A vane extends from the platform and includes a suction side, a pressure side, and a leading edge having a platform portion and a shroud portion. A majority of the shroud portion is disposed on the suction side of a line normal to the platform that passes through a center of the platform portion of the leading edge. A shroud is coupled to the shroud portion of the vane such that the vane, the platform, and the shroud cooperate to at least partially define two flow paths.

Abstract: A diaphragm for an axial flow turbomachine, in which outer shrouds of adjacent fixed blades in a row of blades contact each other circumferentially to form a circumferentially continuous load path. Inner shrouds of the blades only contact each other on contact faces oriented to transmit loads in the radial and/or axial directions of the turbomachine.

Abstract: A single stage high pressure turbine vane includes an airfoil having 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 diffuser augmented wind turbine assembly comprising an inlet wind suppressor and a shroud disposed within said inlet wind suppressor. The assembly contains a wind turbine; the wind turbine is disposed within the shroud; and the shroud is connected to a diffuser.

Abstract: This invention involves a hydroelectric turbine system that is capable of producing electricity while sustaining a majority of the fluid flow or hydraulic pressure within the pipe line or pipe network driving the system. The system's objective is to shave as little pressure as possible from an enclosed pipe system that requires pressure to operate and function properly. More particularly, this invention relates to a hydroelectric turbine generator system wherein the system is specially designed and configured with an unique impeller and fluted turbine housing that enable a generator device to produce a particular amount of electric current and voltage, while yet minimizing flow restriction and pressure loss to the fluid pressure driving the system.

Abstract: A blower motor assembly for use in a heating, ventilation and air-conditioning system of a vehicle and a method of diverting water are disclosed. The blower motor assembly may include a motor housing, configured to surround internal components of the blower motor assembly, and including a cooling channel/air intake opening. The blower motor assembly may also include a motor support flange extending radially outward from the motor housing and having an upward facing surface, and at least one water diversion vane extending upward from the upward facing surface and extending radially outward in an arcuate shape to divert water off of the flange.

Abstract: A prewhirl type inlet casing for inducing a spiral stream in fluid has a suction passage arranged on an upstream side, being orthogonal to a rotary shaft of fluid machinery, and an internal passage connected to the suction passage, the internal passage being formed in a spiral shape so as to induce a swirl stream orthogonal to the rotary shaft in the fluid. A guide vane provided in the fluid passage in the inlet casing has a rectifying function capable of distributing flow rates in the swirl stream of the fluid in the internal passage between the swirl center side and the swirl outer peripheral side, and causing the fluid to deflect into the swirling direction of the swirl stream induced by the internal passage.

Abstract: A method of selecting an arrangement of sectors for a turbomachine nozzle, the method comprising the following steps: A) creating a database of three-dimensional numerical models of the sectors by digitizing; B) setting a criterion for selecting an arrangement of sectors and setting a desired value for said criterion, the criterion being a function of the shapes and the relative positions of the sectors; C) for the various arrangements that are evaluated, determining the relative positions of the sectors when assembled together by performing a virtual assembly, and as a function of said positions, determining the value of the selection criterion for the arrangement under evaluation; and D) retaining the arrangement for which the selection criterion has the value closest to the desired value. This method serves to optimize selecting sectors in a nozzle.

Abstract: A turbine nozzle includes a row of vanes extending radially in span between inner and outer bands. The vanes include opposite pressure and suction sidewalls and opposite leading and trailing edges. Each vane includes an inner pattern of inner cooling holes and an outer pattern of outer cooling holes distributed along the leading edge. The inner and outer holes diverge toward the corresponding inner and outer bands to preferentially discharge cooling air.

Abstract: A nonlinearly stacked low noise turbofan stator vane having a characteristic curve that is characterized by a nonlinear sweep and a nonlinear lean is provided. The stator is in an axial fan or compressor turbomachinery stage that is comprised of a collection of vanes whose highly three-dimensional shape is selected to reduce rotor-stator and rotor-strut interaction noise while maintaining the aerodynamic and mechanical performance of the vane.

Abstract: A turbine section of a gas turbine engine includes an arcuate vane platform segment having a substantially flat surface over which a rotational turbine vane may swing.

Abstract: A steam turbine is provided having a rotor which rotates around a machine axis, and a stator which concentrically encompasses the rotor with clearance, between which an annular passage is formed which is exposed to throughflow by steam in the axial direction and in which a multiplicity of rotor blades, which are fastened on the rotor, and fixed stator blades are arranged in a plurality of stages, wherein the stator blades of the last stage have a sweep with a sweep angle which changes in sign over the relative blade height.

Abstract: To improve the assembling efficiency of a urbo-molecular pump having a structure in which the outside diameter of a rotor blade on the exhaust port side is smaller than the outside diameter of a rotor blade on the intake port side. Spacer rings 31f to 31h are set to a threadedly grooved spacer 3. Next, a moving section is inserted along the inner wall of a beanng section of a base 24 from the upside and is fixed. Thereafter, the spacer ring 31f to 31h are raised to provide a clearance between the spacer ring 31h and the threadedly grooved spacer 3. A halved stator blade 30 is inserted between rotor blades 9 via this clearance. After insertion, the spacer ring 31h is lowered, and the stator blade 30 is held by the threadedly grooved spacer 3 and the spacer ring 31h and is fixed. In the same way, the stator blade 30 is inserted between the rotor blades 9 via a clearance between the spacer ring 31h and the spacer ring 31g and a clearanoe between the spacer ring 31g and the spacer ring 31f.

Abstract: The first stage nozzles have airfoil profiles substantially in accordance with Cartesian coordinate values of X, Y and Z set forth Table I. The X and Y values are in inches and the Z value is in inches along the nozzle stacking axis coincident with a turbine radius. The X and Y 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±0.160 inches.

Abstract: The present invention provides an axial flow fan including an impeller that has a plurality of rotor vanes and is rotatable about a central axis, a motor that rotary drives the impeller, a base portion that supports the motor, a housing that has an intake vent, an exhaust vent, and an inner peripheral surface to surround the impeller and the motor, and a plurality of stator vanes that respectively connects the base portion and the housing, wherein the inner peripheral surface has a first inner peripheral surface formed to increase a distance from the central axis toward the intake vent or the exhaust vent in an axial direction, and there is formed a recess between the first inner peripheral surface and a stator vane that is included in the plurality of stator vanes and faces the first inner peripheral surface. According to the above described configuration, airflow is allowed to smoothly pass through the housing, resulting in a decrease in noise generated in the axial flow fan.

Abstract: The shape, of a vane for use in a variable nozzle assembly of a turbocharger was designed, including a step of defining a camberline curve and a thickness curve by means of two Bézier curves having a certain number of control points, and a step of applying computational fluid dynamics analysis and a Design of Experiments methodology for optimizing the setting of the control points to improve performance of the vane. As result, a distinct vane shape as shown in the drawings was obtained.

Abstract: The invention relates to a radial compressor having a suction-side opening and a pressure side. A swirl generator is placed upstream of the radial compressor. The swirl generator, has an inlet portion which is angularly configured relative to the outlet opening, the outlet opening facing the suction-side opening of the swirl generator. The swirl generator further has adjustable baffle plates arranged concentrically around the outlet opening.

Abstract: A Mixer/Ejector Wind Turbine (“MEWT”) system is disclosed which routinely exceeds the efficiencies of prior wind turbines. In the preferred embodiment, Applicants' MEWT incorporates advanced flow mixing technology, ejector technology, aircraft and propulsion aerodynamics and noise abatement technologies in a unique manner to fluid-dynamically improve the operational effectiveness and efficiency of prior wind turbines, so that its operating efficiency routinely exceeds the Betz limit. Applicants' preferred MEWT embodiment comprises: a turbine shroud with a flared inlet; a ring of stator vanes; a ring of rotating blades (i.e., an impeller) in line with the stator vanes; and a mixer/ejector pump to increase the flow volume through the turbine while rapidly mixing the low energy turbine exit flow with high energy bypass wind flow. Unlike gas turbine mixers and ejectors which also mix with hot core exhaust gases, Applicants' preferred apparatus mixes only two air streams (i.e.

Abstract: An inner shell for a rotating machine including at least one segment; and at least one complementary segment in operable communication with the at least one segment, the segments forming a support structure for a shroud ring; wherein the at least one segment and the at least one complementary segment are individually moved to change a set of dimensions defined by the at least one segment and the at least one complementary segment. A method for controlling a dimension of the shroud ring in a rotating machine is also disclosed.

Abstract: An article of manufacture having a nominal profile substantially in accordance with Cartesian coordinate values of X, Y and Z set forth in a TABLE 1. Wherein 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 being joined smoothly with one another to form a complete airfoil shape.

Abstract: An article of manufacture having a nominal profile substantially in accordance with Cartesian coordinate values of X, Y and Z set forth in a TABLE 1. Wherein 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 being joined smoothly with one another to form a complete airfoil shape.

Abstract: An article of manufacture having a nominal profile substantially in accordance with Cartesian coordinate values of X, Y and Z set forth in a TABLE 1. Wherein 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 being joined smoothly with one another to form a complete airfoil shape.

Abstract: An article of manufacture having a nominal profile substantially in accordance with Cartesian coordinate values of X, Y and Z set forth in a TABLE 1. Wherein 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 being joined smoothly with one another to form a complete airfoil shape.

Abstract: The present invention relates to a device for transducing and/or converting of wind power into another power, for example electric power, comprising a rotor which is rotary in a tunnel tube which is mounted on the upper end of a tower the rotor having an outer ring, an inner ring and a number of blades or vanes, which extend between the rings, the outer ring having a depression extending between the edges for a belt or the like which extends to a shaft on the underside of the tunnel tube for rotation thereof on rotation of the rotor.

Abstract: A screw-centrifugal pump (1) comprises a pump housing (3) having an inlet opening (3c) and also an impeller (2) arranged within the pump housing (3) and rotatable about an axis of rotation (2d) in a direction of rotation (4a). The impeller (2) has a spirally extending blade entry edge (2a) and a guide vane (5) projects into the interior space of the impeller (2) and is disposed in the region of the inlet opening (3c). A method of conveying a liquid permeated with solid additions using such a pump is also described and claimed.

Abstract: A vapor compressor for use with a distillation system, the compressor including a housing defining an interior volume. The housing includes an inlet and an outlet. A shaft has a first end and a second end and extends along a longitudinal axis of the housing. A first compression stage includes a first impeller and a first stator, the first impeller including a first plurality of impeller blades having a first dimension. The first stator includes a first plurality of stator blades having a second dimension. A second compression stage includes a second impeller and a second stator, the second impeller including a second plurality of impeller blades having a third dimension. The second stator includes a second plurality of stator blades having a fourth dimension. The first dimension and the third dimension are measured along corresponding portions of the first plurality of impeller blades and the second plurality of impeller blades, and the first dimension is greater than the third dimension.

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 he 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: A stator shell for a hydrodynamic torque converter (1), wherein said stator shell (2) comprises a plurality of blades (32, 34), wherein said stator shell (2) comprises plural components (20, 22), produced separately from one another and respectively comprising one or plural blades (32, 34) of said stator shell (2), wherein said components (20, 22) are fixated to one another and disposed relative to one another, so that blades (32, 34) of several of said components (20, 22) are disposed respectively offset relative to one another in a circumferential direction forming gaps provided in said circumferential direction extending about a central axis of the stator shell (2), wherein each of said blades (32, 34) is configured from an integral component between its respective leading edge and its respective trailing edge, so that each of the blades (32, 34) is respectively configured integrally from one of the components (20 or 22).

Abstract: A centrifugal fan includes a spiral-shaped housing with a driving mechanism and multiple internally mounted centrifugal impellers. The driving mechanism is mounted on a circular base. At least two support brackets links the circular base to the spiral-shaped housing, wherein profiles of the support brackets are involute curves based upon the circular base. The multiple centrifugal impellers, driven by the driving mechanism, suck airflow into the spiral-shaped housing through void spaces among the support brackets. The centrifugal impellers are perpendicular to the support bracket profiles.

Abstract: A seal assembly (60) for sealing first and second static parts (40A, 40B) with opposed slots (44A, 44B) together forming a pocket (46). The seal assembly (60) comprises a floor strip (70) positioned adjacent the pocket's floor (48) and a ceiling strip (80) positioned adjacent the pocket's ceiling (50). A connection (90) of the strips' central portions (72, 82) provides a flat hinge between cooperating hinge portions (76, 86). A first set of the hinge portions (76A-86A) converge for insertion into the first slot (44A) and a second set of hinge portions (76B-96B) converge for insertion into the second slot (44B). After such slot insertion and pocket installation, the converged hinge portions (76A-86A, 76B-86B) resiliently diverge within the pocket to seat the floor strip's end portions (74A, 74B) against the pocket's floor (48) and to seat the ceiling strip's end portions (84A, 84B) against the pocket's ceiling (50).

Abstract: Disclosed is a swirler for use in a burner of a gas turbine engine, the swirler comprising a plurality of vanes arranged in a circle, flow slots being defined between adjacent vanes in the circle, each flow slot having an inlet end and an outlet end, in use of the swirler a flow of fuel and air travelling along each flow slot from its inlet end to its outlet end such that the swirler provides a swirling mix of the fuel and air, at least one vane having an edge adjacent an inlet end of a flow slot configured to generate within the flow slot one or more flow vortices that extend along the slot thereby to enhance mixing of the fuel and air travelling along the slot.

Abstract: The first stage nozzles and buckets have nominal airfoil profiles substantially in accordance with Cartesian coordinate values of X, Y and R set forth in Tables I and II, respectively, and second stage nozzles and buckets have nominal airfoil profiles substantially in accordance with Cartesian coordinate values set forth in Tables III and IV, respectively. The X, Y and R values are in millimeters. R represents distances along a radius from an axis of rotation of the turbine. For each airfoil, X and Y are distances which, when connected by smooth continuous arcs, define airfoil profile sections in planes normal to the radius at each distance R. The profile sections at the R distances for each airfoil are joined smoothly with one another to form the airfoil shape. The airfoil shapes given by the X, Y and R distances lie within envelopes of ±4.064 millimeters in a direction normal to any airfoil surface location therealong.

Abstract: A turbomachine exhaust casing with connection roots between the structural arms of the casing and the annular endplates of the hub of the casing, each of said the roots having a profile that is optimized so as to reduce the level of stress in the connection portions, and thus increase the lifetime of the exhaust casing.

Abstract: The invention relates to a slotted bleed deflector for a gas turbine engine. The bleed deflector comprises an inlet portion for receiving bleed air from the engine and a body for distributing the bleed air into a fan bypass duct. The body includes a leading edge section, a trailing edge section and a flow compartment section where the flow compartment distributes the bleed air above an inner wall of the bypass duct.

Abstract: A first motor 25 rotates, in one of two rotating directions, the first impeller 7 including a plurality of front blades 28 in a suction opening portion 15 of a housing 59. The second motor 49 rotates, in the other rotating direction opposite to the one rotating direction, the second impeller 35 including a plurality of rear blades 51 in a discharge opening portion 57 of the housing 59. A plurality of stationary blades 61 are arranged between the first impeller 7 and the second impeller 35 in the housing 59. When the number of the front blades 28 is N, that of the stationary blades 61 is M, and that of the rear blades 51 is P, their relationship is defined as N>P>M. A length L1 of the front blades 28 measured in an axial direction is set longer than a length L2 of the rear blades 51 measured in the axial direction.

Abstract: The invention relates to a turbocharger comprising a turbine casing (2) which has an exhaust-gas inlet opening (3) and an exhaust-gas outlet opening (4); comprising a turbine wheel (5) which is fastened to a shaft (6) and is arranged in the turbine casing (2); comprising a plurality of blades (7; T) which are arranged in the turbine casing (2) between the exhaust-gas inlet opening (3) and the turbine wheel (5), wherein each blade has the following: a profile underside (8; 8?) and a profile top side (9; 9?) which determine the blade thickness, a blade leading edge (10; 10?) at a first intersection of the blade underside (8; 8?) and the blade top side (9; 9?), a blade trailing edge (11; 11?) at a second intersection of the blade underside (8; 8?) and the blade top side (9; 9?), a profile centre line (12; 12?) which is defined by the blade underside (8; 8?) and the blade top side (9; 9?) and runs between them from the blade leading edge (10; 11?) to the blade trailing edge (11; 11?), wherein the profile centre l

Abstract: A gas turbine engine vane has first and second members. The first member has a first surface section forming a suction side of an airfoil of the vane. The second surface section forms leading and trailing portions of a pressure side of the airfoil. The third surface section forms a recess between the leading and trailing portions. The second member is secured to the first member and has a first surface section forming an intermediate portion of the pressure side. a leading protrusion of the second member may be captured by a recess below a lip of the first member.

Abstract: An air intake with at least one inlet port area and one outlet port area, in which there is arranged at least one structure which may be flowed through and around, comprises an opening and modifies the clear cross-section only slightly, in particular serving as a fresh air/recirculated air housing for a motor vehicle heating, ventilation and/or air-conditioning system.

Abstract: An intermediate casing for use in a gas turbine engine comprises inner and outer casing walls 2, 4, a support plate 6, supporting an axial end of each of the casing walls 2, 4, a splitter 8, and an array of vanes 10. At least one of the casing walls 2, 4, the support plate 6, the splitter 8 and the array of vanes 10 is formed from at least one blank of sheet material, such as steel. The formation of one or more components of the assembly from a flat blank of material provides a significant reduction in manufacturing cost.

Abstract: External shroud for a turbomachine turbine wheel, this shroud being formed of ring sectors (120) positioned circumferentially end to end, and each comprising a circumferentially directed plate (136) bearing a block (138) of abradable material, the plate and the block of each ring sector being offset one with respect to the other in the circumferential direction so that a circumferential end part of the plate of each ring sector overlaps a corresponding end part of the block of an adjacent ring sector.

Abstract: A turbine unit of a turbocompressor comprises a turbine wheel having blades and a flow channel for directing exhaust gas onto the turbine wheel. The turbine unit additionally comprises injection means for injecting carbon build-up preventing substance into the flow channel.

Abstract: A centrifugal impeller having an inlet and a plurality of outlets the outlets including at least one outlet in a forward direction of the Impeller and at least one outlet in a rearward direction of the impeller. A flow path distance of the outlet in the forward direction can be greater than a flow path distance of the outlet in the rearward direction in order to provide a greater pressure in the outlet having the greater flow path distance. In another embodiment, the flow path volume in the forward direction can be greater than the flow path volume in the rearward direction in order to provide a greater flow volume in the forward direction In another embodiment, the number of flow paths in the forward direction can be greater than the number of flow paths in the rearward direction in order to provide a greater flow volume in the forward direction.

Abstract: A motor-driven fan assembly includes a bracket which couples to a motor assembly and includes an outlet port. A shroud assembly defines a chamber and includes an inlet port. The shroud assembly is received on a bracket and a bearing-supported shaft is driven by the motor assembly and extends through the bracket and into the shroud assembly. At least one fan is coupled to the shaft and received in the chamber. The fan includes a plurality of curved blades positioned between a frustoconical lower cap and an opposed frustoconical upper cap. Rotation of the fan by the shaft results in turbulent air flow through the fan assembly. Dust is generally prevented from settling on the fan blades during operation, thereby preventing non-uniform dust buildup or breakup which may cause excessive vibration and reduce bearing and brush life.

Abstract: A method for assembling a turbine nozzle for a gas turbine engine facilitates improving cooling efficiency of the turbine nozzle. The method includes providing a hollow doublet including a leading airfoil and a trailing airfoil coupled by at least one platform, wherein each airfoil includes a first sidewall and a second sidewall that extend between a respective leading and trailing edge. The method also includes inserting an insert into at least one of the airfoils, wherein the insert includes a first sidewall including a first plurality of cooling openings that extending therethrough, and a second sidewall including a second plurality of cooling openings extending therethrough, and wherein the first plurality of cooling openings facilitate more cooling of the airfoil than the second plurality of cooling openings.