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 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: 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: Disclosed herein is a stator assembly for a steam turbine. The stator assembly includes a stacked stator section and a retention device. The stacked stator section has a plurality of adjacently disposed stator plates. The retention device retains the adjacent stator plates proximate to each other.

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 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: A compressor includes a stator having a plurality of vane sectors each with an outer shroud having a forward and a rearward guide vane extending there form, the vane sector being mounted in an annular slot of the casing, the guide vanes forming a gap between the tips and an inner shroud, and a spring member located on the outer shroud in the rearward portion to bias the rearward shroud in a radial direction, where a space is formed in the slot to allow for the outer shroud to move in the radial direction when the rearward guide vane tip makes contact with the inner shroud due to thermal growth of the stator components. This arrangement allows for the rearward guide vane tip to maintain contact with the inner shroud without inducing high compressive stresses in the stator components due to the thermal growth.

Abstract: A hydrocarbon well pump has impellers and diffusers configured with inner and outer sections. The central section contains impeller passages configured for pumping liquid. The outer section contains turbine blades for compressing gas. A cylindrical sidewall separates the two sections. A driven shaft rotates the central and outer sections in unison.

Abstract: A stay ring of a hydraulic turbine has: a ring-shaped upper wall, a ring-shaped lower wall arranged below the upper wall forming a ring-shaped flow channel between the upper wall and the lower wall; and stay vanes arranged in array with spaces in a peripheral direction in the ring-shaped flow channel and rigidly secured to the upper and lower walls. The upper wall and the lower wall are inclined so as to reduce height of the ring-shaped flow channel toward outlet at least near inlet end thereof. The straightening bodies are arranged along inner surfaces of the upper wall and the lower wall at least near inlet end to reduce inclination of water flow in the stay ring.

Abstract: Systems and methods for absorbing acoustic noise generated by computer cabinet cooling fans are described herein. In one embodiment, an acoustic absorber for use with a fan carried by a computer cabinet in a room includes a first acoustic panel spaced apart from a second acoustic panel. The first acoustic panel is configured to be positioned proximate to an outlet of the fan and at least approximately parallel to a flow of cooling air discharging from the outlet. The second acoustic panel is also configured to be positioned proximate to the outlet of the fan and at least approximately parallel to the flow of cooling air discharging from the outlet. The first and second acoustic panels together form an opening configured to direct the flow of cooling air away from the fan outlet and into the surrounding room. In a further embodiment, the opening formed by the first and second acoustic panels can be configured to extend at least approximately 360 degrees around the fan.

Abstract: A turbomolecular pump includes a plurality of rotor and stator discs arranged alternatively one behind another and producing together a pumping effect, a plurality of spacer rings for retaining the stator discs at a distance from each other; and connection elements for fixedly connecting adjacent spacer rings with each other, so that the spacer rings together provide for securing and centering of the stator discs, taking over the function of a pump housing that is eliminated.

Abstract: A nozzle box includes a torus, bridge ring and nozzle ring portions wherein steam flowing generally circumferentially in the torus portion is redirected for flow generally axially by the bridge ring portion. The steam exiting the bridge ring portion flows into nozzles formed by adjacent partitions of the nozzle ring portion. Bridges in the bridge ring portion are tangentially leaned to exactly match the angle of inclination of the leading edges of the axially adjacent partitions at like circumferential locations. For strength purposes, there are two bridges for each partition. Every other bridge axially registers with the leading edge of the axially downstream partition matching its angle while remaining bridges are equally spaced between the aligned bridges. In this manner, the steam flow is straightened by the bridges to match the angle of the leading edge of the nozzle partitions with consequent reduction of passage area loss.

Abstract: A stator vane assembly for a turbomachine comprising a plurality of circumferentially arranged stator vanes (32), the axial position of the stator vanes (32) and/or the pitch angle circumferentially between adjacent stator vanes (32) is varied circumferentially around the stator vane assembly. The stator vane assembly reduces the pressure distortion upstream of the fan outlet stator vanes (32), reduces the circumferential pressure variation and this reduces blade forced response excitation, noise generation and aerodynamic losses.

Abstract: A gas path flow blocker comprising a plurality of vanes each comprising a forward portion and an aft portion defining a plurality of gas paths, a forward ring comprising a central axis about which is circumferentially disposed the plurality of forward portions, and an aft ring disposed about the central axis about which is circumferentially disposed the plurality of aft portions wherein the forward ring and the aft ring are moveable with respect to each other to at least partially block the flow of a gas through the gas paths.

Abstract: A gas turbine engine diffuser comprises a bowl-shaped diffuser casing and a cover nested into the bowl-shaped diffuser casing and cooperating therewith in defining a diffuser passage having a channeled entry portion in fluid flow communication with a vaned exit portion via a vaneless intermediate portion. The channeled entry portion is divided into an array of inlet flowpaths by a first set of vanes. Likewise, the vaned exit portion is divided into an array of outlet flowpaths by a second set of vanes.

Abstract: A vane unit system having a plurality of vane units having at least one air foil projecting from a base. The base has a hole which receives a pin which extends between adjacent bases of vane units therein forming a rigid ring of vanes that are less susceptible to vane motion caused by pressure fluctuations within the compressor of a gas turbine. A blade assembly tool having a shape to fit within the slot in a casing that receives the vane units allows for the installation of vane units with interlocking pins without the necessity of having to remove the rotor from the casing.

Abstract: A resilient ring for sealing between an inner housing surface of revolution and a coaxial outer housing surface of revolution, one of the housing surfaces being a sloped surface with a sloped profile intersecting an axially extending plane and the other housing surface being an axial abutment surface in a substantially radially extending plane. The ring has a circumferential sealing surface for sealing engagement of the ring with the sloped housing surface, and a planar abutment surface for sealing engagement of the ring with the axial abutment housing surface.

Abstract: A method of assembling a gas turbine engine includes coupling an inner engine casing to an outer engine casing such that an annular flow path is defined therebetween, coupling a plurality of circumferentially-spaced support struts between the inner and outer casings, and coupling a plurality of circumferentially-spaced outlet guide vanes within the flow path upstream from the support struts, such that a first circumferential spacing is defined between a first guide vane and a second guide vane, and a second circumferential spacing is defined between the second guide vane and a third guide vane. The guide vanes are arranged such that the second guide vane is between the first and third guide vanes and the second circumferential spacing is different from the first circumferential spacing.

Abstract: A heat dissipation apparatus has an enclosure, in which a lateral fan seat is integrally formed with the enclosure. The lateral fan seat divides the interior space of the enclosure into an upper chamber and a lower chamber. An axis is installed across the upper and the lower chambers through a center of the fan seat. A coil set, a magnetic element and a plurality of blades are mounted about the axis in each of the upper and lower chambers. Thereby, two sets of fans are formed in a single enclosure to increase the heat dissipation effect while the assembly convenience is improved.

Abstract: The third stage nozzle has an airfoil profile substantially in accordance with Cartesian coordinate values of X, Y and Z set forth in Table I wherein X and Y values are in inches and define airfoil profile sections at each distance Z and Z are non-dimensional values within a range from 0.1 to 0.9 convertible to Z distances in inches by multiplying the Z values of Table I within the range by a height of the airfoil in inches. The profile sections at the Z distances are joined smoothly with one another to form the nozzle airfoil shape. The X and Y distances may be scalable to provide a scaled-up or scaled-down airfoil for the nozzle. The nominal airfoil given by the X, Y and Z distances lies within an envelope of ±0.160 inches.

Abstract: An axial-flow turbine has an exhaust diffuser including a hub-side tube and a tip-side tube. In the exhaust diffuser, front struts and rear struts are placed to cross a flow of working fluid. A wake generated behind the front strut diverts from the rear strut and passes through a gap between a pair of the rear struts. Otherwise, a wake generated behind the front strut hits against the front face of the rear strut. The front struts are equal to or multiple of the rear struts in number.

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 heat-dissipating module including a first fan unit, a second fan unit, and a connecting arrangement for connecting the first fan unit and the second fan unit in a serial manner. The first fan unit is located on an air inlet side and includes a casing and a fan wheel received in the casing of the first fan unit. The second fan unit is located on an air outlet side and includes a casing and a fan wheel received in the casing of the second fan unit. At least one side air inlet is defined between the casing of the first fan unit and the casing of the second fan unit for increasing an air inlet amount and an air outlet amount of the second fan unit.

Abstract: A composite fan consists of a first fan and a second fan located on the air outlet side of the first fan. The first fan has a plurality of first rotary vanes and a plurality of first guide vanes located on the air outlet side of the first rotary vanes. The second fan has a plurality of second rotary vanes and a plurality of second guide vanes located on the air inlet side of the second rotary vanes. Each of the second guide vanes corresponds to and is coupled with each of the first guide vanes to form a continuous curved surface.

Abstract: The first stage nozzles have airfoil profiles substantially in accordance with Cartesian coordinate values of X, Y and Z set forth Table 1. The X and Y values are in inches and the Z value is non-dimensional along the nozzle-stacking axis coincident with a turbine radius and convertible to a Z distance in inches from the turbine axis by multiplying the Z value by the height of the airfoil and adding the root radius to the result. 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: An internal combustion engine includes a coolant pump having an axially directed rotary pumping element which is functionally housed between upstream and downstream stators which function to straighten the flow and recover fluid velocity, both before and after work has been performed on the fluid by the rotary pumping element.

Abstract: Disclosed is a composite heat-dissipating system and its used fan guard which can impart a supercharging function to the heat-dissipating fans of the composite heat-dissipating system for efficient heat dissipation and reduces the noise generated when the heat-dissipating fans are operated. The fan guard includes a frame and a set of guard blades arranged inside and fixed onto an inner surface of the frame. The fan guard can be arranged upstream or downstream of the rotor blades of the heat-dissipating fans and assembled with the heat-dissipating fans in series or in parallel to supercharge the airflow out of the heat-dissipating fans.

Abstract: An axial flow fan includes a first rotor having first blades and a second rotor having second blades. The first rotor is axially connected to the second rotor, and both of the first rotor and the second rotor are received in a first stator which has third blades extending from radially inward from an inner periphery thereof. A second stator is connected to the first stator and has fourth blades extending radially inward from an inner periphery thereof.

Abstract: A turbomolecular pump capable of maintaining a maximum discharge rate even in a higher pressure has rotor blades or stator blades formed such that surface angles on a first surface of the blades facing the direction of rotation differ between an inlet port side of the blades and an outlet port side. The surface closer to the inlet port has a larger angle than on a side closer to the outlet port. One side of the blades has a plurality of surface portions each with different angles. The angles of the surfaces are in the range of 20° to 50° on the inlet port side, 10° to 40° on an intermediate portion, and 10° to 90° on the outlet port side. The angles of the first and second surface portions are larger than that of the intermediate surface portion.

Abstract: A combination airflow straightener and finger guard straightens airflow and minimize the chance of fingers or other objects coming into contact with rotating blades of a fan, and includes a plurality of vanes that extend radially outward from a hub to an outer frame of the combination airflow straightener and finger guard. Each vane can be considered as having three portions. The first portion is closest to the fan and is parallel to the airflow leaving the fan. The second portion is farthest from the fan and is aligned with the axis of rotation of the fan (or some other desired exhaust vector). The third portion is curved to link the first portion to the second portion to straighten the airflow to the desired exhaust vector, with the space between each pair of vanes forming a plenum that straightens the airflow by removing the rotational components from the airflow.

Abstract: A gas turbine has circumferential arrays of nozzles and shrouds and a plurality of combustors for flowing hot gases of combustion through respective sets of adjacent nozzles and shrouds. First and second nozzles of each set of nozzles are subject to different known inlet conditions of the hot gases of combustion flowing from the associated combustor and transition piece. The first nozzle in each set is preferentially located relative to the second nozzle of that set at a circumferential location relative to the associated combustor based on the known different inlet conditions. The first and second nozzles are therefore qualitatively different from one another dependent on those different inlet conditions. Similarly, the shrouds are subject to different inlet conditions and are preferentially designed and located based on those known inlet conditions.

Abstract: A low pressure fuel system for a gaseous fuel internal combustion engine in which the source of gaseous fuel is at a pressure lower than the intake manifold pressure of the internal combustion engine. The gaseous fuel is inducted into the interstage duct of a multi-compressor combustion air turbocharger associated with the internal combustion engine. The combined flow of air and gaseous fuel is further compressed in the second compressor stage of the turbocharger.

Abstract: A turbine includes three rows of airfoils which receive in sequence hot combustion gases during operation. The third row airfoils are clocked circumferentially relative to the first row airfoils for bathing the third row airfoils with relatively cool wakes discharged from the first row airfoils during the hottest running condition of the gas turbine engine being powered. The third row airfoils therefore avoid the hottest temperature of the combustion gases for reducing the cooling requirements thereof.

Abstract: An axial flow power tool turbine motor for operation with an elastic fluid, like pressured air, includes a housing (12), a rotor (11) rotatively journalled in the housing (12) and formed in one piece with drive blades (24) arranged in axially spaced circumferential rows (C, A, C, E, G, I, K), and a stator (10) in the form of a tubular body (22) which is immovably supported in the housing (12) and which carries internal guide vanes (23) arranged in circumferential rows (B, D, F, H, J), wherein the tubular stator body (22) is divided into three longitudinal sections (22a, 22b, 22c) with which the guide vanes (23) are integrally formed, and a retainer (27, 29) for fixing and mounting the longitudinal sections (22a, 22b, 22c) in accurately defined relative positions to form the tubular stator body (22).

Abstract: A two stage jointed stationary blade of a high pressure or intermediate pressure steam turbine is formed with a bolt joint in place of a welded joint so as to make detachment and disassembly possible, and thereby facilitating maintenance and inspection work and reducing assembling man-hours. A stationary blade (front stage)(2), outer ring front portion (1) and inner ring front portion (3) are welded into an integral structure. A stationary blade (rear stage) 22, outer ring rear portion (21) and inner ring rear portion (23) are also welded into an integral structure. The outer ring front portion 1, outer ring center portion 10 and the outer ring rear portion 21 are mutually engaged via engaging portions (4, 11 and 12, 24) with precise positioning and then jointed together integrally by bolt (30).

Abstract: A turbocharger includes a rotor having coaxial turbine and compressor wheels. In a preferred embodiment, a turbine inlet scroll conducts exhaust gas toward the turbine wheel and an exhaust duct carries exhaust gas away from the turbine wheel. A turbine nozzle ring coupled between the inlet scroll and the exhaust duct defines an annular passage including angled stator blades and vanes that direct gas angularly against energy converting blades of the turbine wheel. Ring seals at outer and inner edges of the nozzle ring inlet end seal the inlet end against loss of gas pressure. They may also form springs that axially bias the nozzle ring against a stop to fix the axial position of the nozzle ring. The nozzle ring is centered by radial guides at the outlet end which may include at least three radial keys on the nozzle ring engaging mating guide slots connected with the exhaust duct.

Abstract: A fan guard has a function of supercharging a fan in addition to supporting a rotor device is disclosed. The fan guard is to be mounted beside the rotor device for supporting the rotor device, and additionally, the fan guard interacts with an airflow generated by the revolution of the rotor blades to supercharge the fan. The fan guard essentially includes a main frame, and a set of guard blades radially arranged inside the main frame and fixed onto an inner surface of the main frame by each one end thereof. Each of the guard blades is preferred to have a shape similar to the shape of the rotor blades, and the set of guard blades can be arranged either upstream or downstream of the rotor blades.

Abstract: A stator device for an axial flow fan has a plurality of first stator elements and a corresponding plurality of second stator elements, the first stator elements being disposed axially rearwardly of the second stator elements so as to define an air flow slot therebetween.

Abstract: A fan guard has a function of supercharging a fan in addition to supporting a rotor device is disclosed. The fan guard is to be mounted beside the rotor device for supporting the rotor device, and additionally, the fan guard interacts with an airflow generated by the revolution of the rotor blades to supercharge the fan. The fan guard essentially includes a main frame, and a set of guard blades radially arranged inside the main frame and fixed onto an inner surface of the main frame by each one end thereof. Each of the guard blades is preferred to have a shape similar to the shape of the rotor blades, and the set of guard blades can be arranged either upstream or downstream of the rotor blades.