Abstract: A ceramic matrix composite nozzle assembly. The ceramic matrix composite nozzle assembly may include a ceramic matrix composite vane, a number of metallic components positioned about the ceramic matrix composite vane, and a number of metallic seals positioned between the ceramic matrix composite vane and one or more of the metallic components.

Abstract: A method is provided for attaching a shim to at least one of a base of a stator vane unit and a ring segment of a ring segment assembly in a gas turbine compressor. The method includes providing a shim shaped to conform to an engaging face of the base of the stator vane unit or the segment ring of the segment ring assembly, with a predetermined thickness dimension; boring at least one hole, normal to the face of the shim and extending fully through the thickness dimension of the shim; positioning the shim on the engaging face of the at least one of the base of the stator vane unit and the segment ring of the segment ring assembly; and welding the shim to the engaging face of the at least one of the base of the stator vane unit and the ring segment of the stator ring assembly.

Abstract: An air handling blower for HVAC equipment includes a blower housing adapted to accommodate centrifugal impellers of selected inside and outside diameters of the impeller blades wherein the inside diameter of the largest diameter impeller accommodated by the housing is not less than the outside diameter of the smallest diameter impeller accommodated by the housing without loss of performance. The blower housing preferably has a continuously increasing cross-sectional airflow area for air being discharged from the blower and extending from a cutoff edge to an outlet.

Abstract: A cooling fan for a vehicle. Many engine compartments of motor vehicles are small in size, and contain numerous components. Electric cooling fans are used to draw air through a radiator. Given the cramped conditions within the engine compartment, the exhaust of the fan cannot be directed into open air, but must impinge on one or more of the components within the compartment. This situation reduces velocity in the exhaust, and also reduces efficiency of the fan. The invention provides a collection of generally co-axial stators which divert the exhaust around the components, while retaining much of the velocity of the exhaust.

Abstract: A fan includes a fan frame and an impeller. The fan frame includes a frame body and a base, and the impeller is accommodated in the main body and is disposed on the base. The frame body has a column-shaped passage, an airflow outlet and an airflow inlet. The main body further has two expansion portions respectively disposed adjacent to the outlet and inlet. The expansion portions extend from the column-shaped passage to the outlet and the inlet, respectively. The main body has at least two planar sides so as to allow parts of the expansion portions to respectively form straight-cut lines where the planar sides are located, respectively. The base has several straight-cut planes, and each of the straight-cut planes is located with respect to the straight-cut line.

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 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 low-restriction turbine outlet device (200) includes a housing (202) having an internal volume (208). The internal volume (208) includes an inlet transition portion (230) and an outlet transition portion (232). An inlet port (204) that is formed in the housing (202) is in fluid communication with an outlet port (206) that is also formed in the housing (202). A mounting flange (216) is connected to the housing (202), a first set of stiffening ribs (218) and a second set of stiffening ribs (220) each connect the mounting flange (216) to the housing (202).

Abstract: A guiding device (2) includes a base (21), a cover (23) and a sidewall (22) cooperatively defining an annular space therein and a passage therethrough. An air inlet (221) is defined in the sidewall communicating with the space for an airflow flowing into the space. A plurality of guiding plates (24) are arranged in the space around the passage. An air outlet (29) is defined between two neighboring guiding plates for the airflow flowing out the space into the passage. The airflow is distributed into a plurality of even streams by the guiding plates. An atomizer (4) is connected with the space via the air inlet. The atomizer produces a high-pressured water vapor which is taken by the airflow to cool an aluminum profile produced by an extrusions press (6) and moving through the passage.

Abstract: A flow structure of a gas turbine, in particular for an aircraft engine, in a transitional channel between two compressors or in a transitional channel between two turbines or in a transitional channel of a turbine outlet housing downstream from a low-pressure turbine is disclosed. Supporting ribs are positioned in the transitional channel and spaced a distance apart in the circumferential direction of the transitional channel. At least one guide vane and/or guide rib is positioned between two supporting ribs spaced a distance apart from one another. The flow outlet edge of the guide rib or each guide rib runs upstream from the flow outlet edges of the supporting ribs.

Abstract: A fan module, particularly for cooling motor vehicle engines allows for improved cooling of the fan motor. The fan housing (101) in which the fan motor (105) is arranged has fixed air-channeling elements (109) which are arranged in the region of a fan hub (2) of the fan wheel (1) driven by the fan motor (105) and which only partially cover an outlet cross section (102, 118) defined by the fan housing (101).

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 method for assembling an exhaust hood for a turbine is provided. The method includes providing a bearing cone that substantially circumscribes a rotor of the turbine; and positioning a guide radially outward from the bearing cone. The guide and the bearing cone are configured to channel fluid from the turbine. The method also includes extending a guide cap from the guide. The guide cap is oriented to facilitate preventing the generation of fluid vortexes within the exhaust hood.

Abstract: A conformal seal (20) for sealing air flow between a cooling airflow path and a hot gas flow path within a combustion turbine engine. The conformal seal (20) may be fitted within cooperating side slots of adjacent vane segments (10) within the combustion turbine engine. The conformal seal (20) may include an elongated metallic substrate (22, 40) forming an upper surface and a lower surface. A conformal coating (26, 44) may be deposited over one or both surfaces of the substrate (22, 40). The conformal coating (26, 44) may be deposited to a depth so that a point contact between the conformal coating (26, 44) and respective interior walls of the side slots wears the conformal coating (26, 44) to establish surface area contact there between. The surface area contact improves a sealing function between the conformal coating (26, 44) and the respective interior walls during operation of the combustion turbine engine.

Abstract: A heat dissipation module includes a first heat dissipation apparatus, a second heat dissipation apparatus, and a flow direction controlling structure. The first heat dissipation apparatus and the second heat dissipation apparatus are symmetrically disposed. The flow direction controlling structure has several rotatable elements disposed between the first heat dissipation apparatus and the second heat dissipation apparatus. Each of the rotatable elements has a fixed end and a correspondingly movable end for guiding airflow. The rotatable elements can be sheet-shaped, wing-shaped, arc-shaped or nonlinear in cross section. The thickness of the rotatable elements varies or decreases from the fixed end to the movable end. The rotatable elements overlap an adjacent rotatable element so as to selectively seal the heat dissipation apparatuses.

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 Invention is a swimming machine operated by a hydraulic pump and hydraulic motor. A first and a second tubular rail support the swimming machine in a swimming pool and are configured to resemble a swimming pool ladder and thus disguise the swimming machine. The configuration of the tubular rails substantially prevents use of the swimming machine as a ladder. A radio-operated remote control proportional relief valve selectably bleeds hydraulic fluid from the high pressure side to the low pressure side of the hydraulic pump, allowing remote control of the velocity of water in the pool.

Abstract: A compressor includes a compressor wheel, a diffuser and a device for the wet cleaning of the diffuser of a compressor, the diffuser being arranged downstream of the compressor wheel in the flow direction of the medium to be compressed. The device includes an arrangement for injecting a liquid, which is arranged in such a way that the liquid can be introduced, downstream of the compressor wheel, to the diffuser. The diffuser has at least partially a non-stick coating. A device of this type is suitable for removing deep-seated deposits from the surface of the diffuser.

Abstract: A turbine nozzle guide vane 10 with passages 28 leading from a hollow core 32 to respective seal strip slots 20, to deliver cooling air to abutment faces 18 on each end of the vane 10.

Abstract: Some embodiments of the present invention provide a pump including a pump housing having an inlet adapted to fluidly couple with an inlet conduit, and an outlet adapted to fluidly couple with an outlet conduit. The pump also includes a pump shaft rotatably supported in the pump housing and a plurality of impellers coupled for rotation with the pump shaft. The pump further includes a motor removably coupled to the pump housing. The motor has an output shaft drivably coupled to the pump shaft. The pump also includes a spacer positioned between the plurality of impellers and the motor. The spacer includes at least one aperture to access and de-couple the output shaft and the pump shaft. The motor, spacer, pump shaft, and the plurality of impellers are removable from the pump housing as a single unit without disconnecting the inlet conduit and the outlet conduit from the pump housing.

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: A modular ceiling fan housing unit designed to create a focused column or columns of downwardly moving air such that there is little deflection when the column or columns of downwardly moving air arrives at the ground level. The modular ceiling fan housing includes an elongated body element having a fluid impelling device to create the downwardly moving air. At least one plate disposed within the elongated body element directs the downwardly moving air into columns. The modular ceiling fan housing unit may be coupled to another modular ceiling fan housing unit to provide additional columns of downwardly moving air. The modular ceiling fan housing units may be coupled in various configurations, depending on the type of application. Furthermore, the modular ceiling fan housing unit or multiple modular fan housing units may be coupled to an elevated structure located either above or below the housing units.

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 invention is an Exit Stay Apparatus with Intermediate Flange for Francis and propeller hydraulic turbines. The purpose of the invention is to improve the effectiveness of known Exit Stay Apparatus (U.S. Pat. No. 6,918,744, July 2005, for Hydraulic Turbine and Exit Stay Apparatus therefor) in eliminating the axial central vortex and, therefore, in increasing the efficiency and decreasing the flow pressure pulsations in draft tube cone at off optimum operating regimes. The new Exit Stay Apparatus has an intermediate flange between exit stay crown and periphery and two sets of exit stay vanes: crown exit stay vanes secured to the exit stay crown and the intermediate flange and peripheral exit stay vanes secured to the intermediate flange and following to the periphery. When installed in the turbine the peripheral exit stay vanes are secured at the periphery.

Abstract: An exhaust system for a turbine includes an annular diffuser and a collector. The annular diffuser is positioned adjacent to a final stage of the turbine and includes a hub portion surrounding a turbine shaft and an outer cone having a substantially frusto-conical shape that is radially symmetrical about a central longitudinal axis thereof that is tilted relative to the turbine shaft. The collector has an inlet extending from the annular diffuser and an outlet. The collector is configured to include a turn that causes the collector to turn exhaust gases approximately 90° from the longitudinal axis of the turbine shaft. The outer cone of the annular diffuser is tilted in a direction of the turn of the collector.

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 turbomachine comprising: an annular combustion chamber (40) with injection orifices (44); a centrifugal compressor (10) having a centrifugal downstream stage; and an annular diffuser (20) comprising: a radially-oriented upstream portion (21) with diffusion passages (22) connected to the outlet of the compressor; an elbow-shaped intermediate portion (24); and a downstream portion (25) comprising a series of flow-straightening vanes (26) and inclined relative to the axis (A) of the turbomachine. In the section plane containing the axis (A) of the turbomachine and passing via the center (C) of one of said injection orifices (44), the curvilinear abscissa distance along a flow line (L) between the middle (O) of the flow path at the trailing edges of the flow-straightening vanes (26) and said center (C) is greater than or equal to three times the height (h) of said flow path.

Abstract: A wind driven vertical axis power generating system is disclosed. An air scoop directs air from the prevailing wind into an air turbine. An exit drag curtain provides for an efficient re-entrainment of the power generating air back into the prevailing wind. The design provides for an efficient method of utilizing the energy from a prevailing wind. The air scoop and exit drag curtain may be rotated to be suitably oriented to the prevailing wind direction. The invention is visually pleasing in shape, as well as efficient in the production of useful power.

Abstract: Exhaust apparatus for exhausting “dirty” exhaust gases accept a core flow of such exhaust gases and combine that with an annularly-surrounding “rooftop” flow of ambient air for diluting the exhaust gases as well as expelling the diluted flow in a forcibly expelled plume in order to ensure that the “effective” expulsion distance of the expelled diluted flow is at least the physical length of the exhaust apparatus plus the gains gotten from efflux velocity and flowrate.

Abstract: Appropriate location of components such as vanes in gas turbine engines is important. These components are located between tangs held in interference engagement. There are four relatively rigid mounting points constituted by the tangs engaging respective opposed slots in a casing or a mounting ring. Only three point limitation with respect to displacement and rotation is adequate so provision of a fourth locator causes unnecessary constraint. A relatively resilient or compliant locator means it is possible to reduce the amount of constraint upon the component mounting whilst the other locators are adequate for positioning of the component.

Abstract: A heat-dissipating device includes a housing having at least one air inlet and at least one air outlet, and a rotor disposed in the housing, wherein the housing has a first extending part extending along an axial direction of the heat-dissipating device to form an axially compressed air passage inside the housing for enabling the airflow to smoothly flow in the air passage inside the frame thereof so as to enhance its performance.

Abstract: A cooling fan for an engine in a vehicle. Ordinarily, a fan rotates within a shroud, which surrounds the fan. Leakage can occur between the tips of the fan blades and the shroud, wherein fan exhaust moves forward, and then passes through the fan again. The invention reduces leakage by placing a surface downstream of the fan. The surface employs the Coanda Effect, to urge fan exhaust to continue in the downstream direction, and not move forward as leakage air.

Abstract: In an axial flow fan, for reducing fluid noise and further reducing the noise by suppressing solid-conveyed noise (structure-borne noise) generated by the vibration of an electric motor or the like, the axial flow fan is equipped with a propeller, a motor for driving the propeller, and a venturi portion disposed on the outer circumference side of the propeller and provided on its inner circumferential side with a bellmouth through which an air flow generated by the revolution of the propeller passes, wherein the bellmouth has an intake portion whose diameter contracts in a curved shape in the direction of the air flow, a cylindrical portion having a cylindrical shape, and a discharge portion whose diameter slantingly expands in the direction of the air flow.

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: An axial flow fan with a plurality of segment blades is described. The axial flow fan has a base, a hub and a plurality of blade units. The hub is mounted on, or pivots on, the base and supports the blade units. Each of the blade units is connected to a periphery of the hub and extends radially outward from the base has a plurality of segment blades. A segment space between the segment blades reforms a boundary layer of fluid passing over the segment blades and reduces the thickness of the boundary layer on the blade surfaces. As a result, the separation between the blade surfaces and fluid is avoided to maintain a laminar flow of the fluid adjacent to the segment blades.

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 fan includes a fan housing located on an axis. The apparatus has axially front and rear sections that together define a chamber. Air can enter the chamber through an inlet in the front section. An impeller in the chamber is configured to rotate about the axis to drive the air radially outward. A trough-shaped channel in the rear section extends circumferentially about the axis from a first end of the channel to a second end of the channel. The channel is configured to channel the air away from the first end circumferentially toward the second end. The axially extending depth of the channel increases from the first end toward the second end such that, over a 90° range, an increase in the depth is more than twice an increase in the radially extending width of the channel.

Abstract: A low solidity vaned airfoil diffuser for a centrifugal compressor wherein each blade has a lean angle greater than zero and wherein the hub stagger angle may be the same as or may be different from the shroud stagger angle for each blade.

Abstract: Within an intake for a gas turbine engine provision is provided through stator vanes 25, 45 in the stator whereby back pressure from a necessary obstruction 34, 46 can be utilised to balance forward pressure variations caused by intake droop or crosswinds in order to reduce those forward pressure detriments for more efficient engine operation according to a desired objective regime. Typically the flow through the intake 20 is analysed and then an appropriate positioning of the stator vanes 25, 45 determined in order to provide approximate balance between the forward pressures and back pressures. Normally, a combination of camber variation of stator vanes 45a and stagger variation of stator vanes 45b are utilised in order to achieve a desired momentum balance around the circumference of the intake 20. It will be understood that both the forward pressures and the back pressures are differentially variable about the circumference such that one opposes the other.

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: According to some embodiments, systems for improved blower fans are provided. In some embodiments, systems may include a casing comprising an inlet to accept a fluid and an outlet to evacuate the fluid. The systems may further comprise an impeller disposed within the casing, comprising a hub and one or more impeller blades coupled to the hub. In some embodiments, the inlet of the casing may be shaped to reduce the amount of fluid that evacuates the casing via the inlet due to pressure within the casing.

Abstract: A cooling fan comprising a housing that connects to a chassis that is operable to support an electronic component. An axial duct runs through the housing. A blade assembly is rotatably disposed within the duct and comprises a plurality of fan blades that extend radially from a hub to a fan diameter. The axial duct has a chord length at least equal to the fan diameter. A motor assembly is disposed within the axial duct and coupled to said blade assembly. The cooling fan provides a cooling capacity of at least 1.5 air horsepower per cubic inch volume of the cooling fan.

Abstract: An integrated assembly is provided for a centrifugal compressor, which integrates selected static portions of the centrifugal compressor into a monolithic structure to allow a small deflection of the inner flow path at assembly. The integrated assembly may include a machined compressor shroud casting having integral diffuser vanes, an aft sheet metal inner flow ring having a radially extending rim with slots in the inner flow ring for receiving diffuser vanes and slots in the rim for receiving deswirler vanes, an outer deswirler band surrounding the inner flow ring and having slots opposing those in the rim, and a plurality of deswirler vanes for fabrication between the inner flow ring and the deswirler band within the respective slots.

Abstract: A heat dissipation fan includes a fan frame, a stator mounted to the frame, and a rotor rotatably disposed around the stator. The fan frame includes a bracket, a central tube for positioning the stator, and a supporting member. The supporting member is made of a material having a higher bending strength than a plastic material used to form the bracket and the central tube. The supporting member includes a main body connected to the central tube, a plurality of ribs extending radially outwardly from the main body, and a plurality of engaging units formed at free ends of the ribs, respectively. The engaging units are embedded in the bracket for integrally connecting the central tube to the bracket.

Abstract: A fan housing and a fan have stationary blades for guiding airflow. Each stationary blade has at least one airflow-guiding element extending therefrom along the circumference of the fan. The side wall of the airflow-guiding element changes the direction of the airflow so that the airflow at the outlet is fully introduced toward the heat source. Furthermore, the airflow-guiding element regulates the airflow, restrains the turbulent flow at the outlet and on the curved surface of the stationary blade, decreases the noise arising from the turbulent flow, and prevents foreign matter from entering the fan housing so as to protect the inside elements thereof.

Abstract: A blade for a turbine engine is described, having a base body, made from a titanium alloy, with a first and a second component piece, which are connected in the connection region by means of a bonding process. A groove with a groove wall runs through the connection region, to prevent local concentration of tension, such that the above borders directly on the second component piece and forms therewith a connection angle greater than 70 degrees.

Abstract: A fan has an air conveying conduit (16) and a fan wheel (22) arranged therein, which wheel is rotatable about a central axis (25) and is formed with a central hub (20; 120) having an outer periphery (27) on which fan blades (26) are mounted. These extend with their radially outer rims (40) as far as a surface (17) that is substantially coaxial with the central axis (25) and delimits the air conveying conduit (16) externally. The blades (26) have a profile similar to an airfoil profile. A flow element (42) is provided along the radial outer edge (40) of a fan blade and serves as an obstacle to a compensating flow proceeding around that radial outer edge (40) from the delivery side to the intake side, and likewise has, in cross section, an airfoil profile.

Abstract: A system for improved power generation through movement of water having a turbine with a generally cylindrical housing, where the turbine is positioned to receive kinetic energy from moving water, and a member positioned circumferentially about the housing for inducing a pressure drop across the turbine. The member may be a rotating blade, cantilevered duct, circumferential flange, radial eductor, and air tube for injection of ambient air into said water source.