Abstract: A turbine blade 10a which is a stop blade is provided with a cutout portion 50 which is formed in one circumferential side surface 22a of a shank portion 22 at the center in the axial direction of a turbine rotor 100, a cutout portion 60 which is formed in one circumferential side surface 22a of the shank portion 22 from one end portion 22b to the cutout portion 50 in the axial direction of the turbine rotor 100, and a through passage 70 which is formed to pass from the cutout portion 50 to an effective blade part and in which a moving member 170, which moves a stopper member 160 to the effective blade part in the cutout portion 50, is inserted.

Abstract: The invention relates to an axial fan (1) for conveying cooling air for a cooling device of a motor vehicle, wherein the axial fan (1) has axial vanes (4) each having a front edge (4a) and a rear edge (4b), a van tip (4c) and a circumferential ring (5) which is connected to the vane tips (4c) and has an approach edge (5a) and a dispersing edge (5b). It is proposed that the approach edge (5a) of the circumferential rind (5) is set back in the flow direction (L) in relation to the front edges (4a) of the axial vanes (4).

Abstract: An axial blower includes a moving vane generating air flow by rotation, a casing accommodating said moving vane, and an adapter detachably attached to the casing. The adapter includes a fitting part to be fit to an inner surface of the casing. The adapter forms a protrusion or a step on the inner surface of the casing.

Abstract: The invention relates to a fan comprising a housing and a fan wheel arranged on a motor shaft and being drivable by a motor. According to the invention, the fan is designed as a mixing fan for transporting and mixing a combustible medium with air, wherein at least the fan wheel is designed in an insulating manner.

Abstract: A gas turbine engine includes a low pressure compressor section and a high pressure compressor section. A low pressure turbine drives the low pressure compressor section. A gear arrangement is driven by the low pressure turbine to in turn drive a fan section. A pressure ratio across the low pressure compressor section is between about 4-8, and a pressure ratio across the high pressure compressor section is between about 8-15. In a separate feature, a compressor case includes a front compressor case portion and a rear compressor case portion, with the rear compressor case portion being axially further from an inlet case than the front compressor case portion. A support member extends between the fan section and the front compressor case portion.

Abstract: A nacelle inlet for an aircraft engine of a type having an engine fan case with a forward flange includes an acoustic inner barrel having a forward edge and an aft edge, an outer shell having a nose lip portion with a trailing inner edge, and an outer barrel portion having an aft portion. The nacelle inlet also includes an aft attachment flange configured to attach the inlet to the forward flange of the engine fan case, and an aft bulkhead having an aft end and connecting the outer barrel portion of the outer shell to the aft attachment flange. The forward edge of the acoustic inner barrel is connected to the trailing inner edge of the nose lip portion, and the aft portion of the inner barrel is attached to the aft attachment flange.

Abstract: A comfort system outdoor unit with a heat exchanger coil and a fan in its top opening has an orifice structure and an insert registerable with the orifice structure to streamline the inward flow of air that passes over a lower end of the orifice structure. The insert may be fastened directly to the orifice structure lower end, or it may be installed so as to extend substantially from an upper edge of the coil to the orifice structure lower end.

Abstract: A casing (2) includes at least one casing structure (casing treatment) for stabilizing a flow in an area of blade tips of rotor blades (4) in a fluid-flow machine, with the casing structure (casing treatment) being provided in at least one stage on an inner circumference of the casing (2). To provide a casing which improves compressor stability, is simply designed, features low weight and operates reliably without heating-up fluid in the fluid-flow machine, the casing structure is designed as a duct (20) which includes a first end (21) and a second end (22), with the first end (21) issuing into the interior of the casing (2) in the area of the blade tips of a rotor blade row and with the second end (22) being closed.

Abstract: A pump for a dishwasher has an impeller for conveying fluid, wherein it is formed as a centrifugal pump with the fluid to be conveyed being sucked-in in a central axial manner and flowing out in a radial manner. The impeller extends on a bottom surface above a pump base, wherein several fixed flow directing blades are arranged radially outside the impeller, said flow directing blades extending in a helicoidal manner with the pitch extending in the rotational direction of the impeller away from the pump base. At least one flow directing blade extends as far as up to the bottom surface of the impeller for picking up a circulating funnel or tube produced of fluid with air bubbles therein.

Abstract: A method of repairing an engine case for a gas turbine engine includes the steps of identifying a damaged flange on an engine case, removing the damaged flange down to a surface of the engine case to receive a replacement flange. The replacement flange is placed on the surface, and welded to the surface utilizing cold metal transfer.

Abstract: A wind energy systems includes a shroud for each turbine. The shroud is adapted to direct and accelerate wind towards the turbine. A strong adaptable support assembly is provided for securing turbines to a structure. An air glide yaw assembly facilitates rotational movement of the structure allowing the turbines to face oncoming wind. The turbine blades are optimized for use with a shroud.

Abstract: An axial fan and a fan rotor are provided as well as a method of manufacturing same, wherein the rotor hub includes an outer shell having on its outside a hub surface which is essentially rotational-symmetrical about the centre axis of the rotor hub; and wherein the rotor hub has a front end and a rear end and a diverging section there between, where the radius of the hub surface in the diverging section is increased by the distance to the front end on the hub; and wherein the rotor hub and the blades are made as separate metal parts; and wherein the rotor blades are securely mounted to the diverging section on the hub surface.

Abstract: A hub cone (20, 30, 40) is provided for an aircraft engine having a propeller (2, 32, 42) or a blower (fan) (3) enveloped by a casing (5). To reduce flow losses of the hub cone and increase efficiency of the engine, a contour of the hub cone is described by the following equation: S(x)=Rmax*{1?[(x?Lmax)/Lmax]2}1/M; where: S(x) is a shape of the cone defined along the machine axis x; Rmax is a maximum extension (26) of the cone in the radial direction; Lmax is a maximum extension (25) of the cone in the direction of the machine axis x and M is a quantity describing the shape S(x).

Abstract: A fan and a frame with a sensor-supporting structure are disclosed. The fan includes a frame with an inlet, a connecting portion disposed on the frame, a stator, and a rotor having blades and disposed in the frame. The frame includes a main body and a sensor-supporting structure. The sensor-supporting structure extending from the main body toward the inlet is utilized to support a sensor.

Abstract: The invention relates to a blower (99), in particular for an engine cooling blower in a motor vehicle, comprising a N housing (10) having a cooling air guide device (200), wherein the housing (10) is designed for mounting a drive unit (102, 103) and the cooling air guide device (200) in the motor vehicle, and for guiding a cooling air flow (20, 30, 31, 32) to the drive unit (102, 103), wherein the cooling air guide device (200) is designed as one piece with the housing (10).

Abstract: A portable hydroelectric generator that carries its own water supply. A tube with a first opening at one end for receiving fluid from a trough and a second opening at the other end for discharging the received fluid. The tube has an inverted U shape having a side A which extends from the first opening toward the top of the inverted U and a side B which includes a turbine coupled to a generator extends from the top of the inverted U to the second end. Side A has a volume which is smaller than the volume of side B and the second opening is located above the level of the fluid in the trough. When fluid is in the tube, its weight in side B is greater than its weight in side A which causes the fluid to flow from the first opening through the tube and out of the second opening.

Abstract: A casing treatment for a fan or compressor stage 10 of a gas turbine engine comprises circumferential grooves 16A, 16B, 16C, 16D and 16E which extend in a series disposed between the leading edges 20 and trailing edges 22 of blades 6 of a fan or compressor stage 10. The grooves 16 vary in depth d in order to optimise the stall margin of the fan or compressor stage 10 while preserving peak efficiency.

Abstract: A cooling fan includes a fan housing (30) having a central tube (34) extending upwardly therefrom, a bearing (60) being received in the central tube, a stator (20) being mounted around the central tube, and a rotor (10) having a shaft (18) extending through the bearing. At least one notch (180, 184) is defined in an end of the shaft. A balance structure (62) is mounted around the shaft, and has a portion facing and surrounding an upper portion of the at least one notch of the shaft. The balance structure is made of magnetic material, which can attract the shaft downward to thereby counter the upward force generated by the rotor when it is driven to rotate. Accordingly, the noise problem incurred by the floating of the rotating rotor can be resolved by the present invention.

Abstract: A fan unit has a fan (10). Associated with the fan is an air-guiding tube (22) through which the fan (10) transports air, during operation. The air-guiding tube (22) is connected to at least one carrier tube (23) for suspension of the fan (10). The fan includes a carrier part (25). A damping member (30) is arranged between the carrier part (25) and the carrier tube (23) to reduce any structure-borne sound which occurs during operation of the fan (10).

Abstract: Provided is an axial fan apparatus including a housing and an axial-flow impeller. The axial-flow impeller is capable of rotating inside the housing and includes a plurality of axial-flow wings each having a negative pressure generation surface for generating a negative pressure, and an auxiliary vane standing on the negative pressure generation surface at an end portion of each of the plurality of axial-flow wings.

Abstract: An axial flow turbine includes in axial flow series a low pressure turbine section and a turbine exhaust system. The low pressure turbine section includes a final low pressure turbine stage having a circumferential row of static aerofoil blades followed in axial succession by a circumferential row of rotating aerofoil blades. Each aerofoil blade has a radially inner hub region and a radially outer tip region. The K value, being equal to the ratio of the throat dimension (t) to the pitch dimension (p), of each static aerofoil blade of the final low pressure turbine stage varies along the height of the static aerofoil blade, between the hub region and the tip region, according to a substantially W-shaped distribution.

Abstract: A jet streamer turbine comprises a top housing, a center housing, a bottom housing, a plurality of vacuum fan housing, a nose propeller housing and an exit air housing. The plurality of vacuum fan housing comprise a first vacuum fan housing and a second vacuum fan housing. The top housing and the bottom housing is connected to the center housing from top and bottom respectively. The first vacuum fan housing and the second fan vacuum fan housing are positioned behind the top housing. The exit air housing is positioned behind the first vacuum fan housing and the second fan vacuum fan housing. A plurality of backward extenders is connected to the exit air housing. The nose propeller housing is connected to the front side of the top housing with a plurality of forward inward extenders.

Abstract: A fan apparatus includes a casing and a fan unit. The casing is a hollow member having an inlet and an outlet. The fan unit has an inlet and an outlet, and includes a plurality of axial fans. The fan unit is disposed on the inside of the casing, and the inlet of the fan unit is disposed in the vicinity of the inlet of the casing. The position of the fan unit within the casing can be varied in order to alter the air flow and static pressure of the air discharged by the fan apparatus.

Abstract: An exhaust system for a steam turbine provided with an improved annular flow guide in a high or intermediate turbine. The improved flow guide reduces flow turbulence in an exhaust hood and reduces pressure loss to thereby improve turbine plant efficiency. The shape (vertically symmetric) of a flow guide 5A according to a conventional technology was modified into the shape (vertically asymmetric) of a flow guide 5 such that the length of a downstream flow guide portion 5d is greater than that of a upstream flow guide portion 5u. Numerical analyses were performed to find the optimum flow guide occupation ratio of the conventional technology and the corresponding total pressure loss coefficient. The obtained values were used as reference values. Further, the flow guide occupation ratio of the upstream flow guide portion 5u was set at 0.4 and the flow guide occupation ratio of the downstream flow guide portion 5d was set at 0.

Abstract: An arrangement and method adapted for providing a stiffened lower exhaust hood for a steam turbine. Sidewalls of the lower exhaust hood may taper inward between a horizontal joint and an inlet to a condenser for the steam turbine, providing an enhanced flow path for the exhaust steam. Stiffening of the sidewalls may be provided by stiffening bends, stiffening curvature, and external stiffening beams on the wall plate of the sidewalls of the lower exhaust hood, permitting reduction or elimination of structural supports within the exhaust hood, which degrade exhaust steam flow.

Abstract: An arrangement and method adapted for providing a reinforced lower exhaust hood for a steam turbine. Double-wall sidewalls and endwalls for a lower exhaust hood include an outer corrugated wall joined to an inner plate wall. The enhanced strength provided by the corrugation provides reduced deformation of the lower exhaust hood and allows reduction of structural complexity and improved aero-performance within the lower exhaust hood.

Abstract: A shroud assembly for an engine cooling fan positioned between an engine and a radiator includes a ring shroud, a radiator shroud, and a flexible boot. The ring shroud is mounted adjacent to the fan and includes a locking feature. The radiator shroud, which is mounted to the rear of the radiator, has a first end with a first aperture for receiving air flowing rearwardly through the radiator, and a second end with a second aperture for discharging air received by the first aperture. A first end of the flexible boot engages the locking feature of the ring shroud to secure the flexible boot to the ring shroud. A second end of the flexible boot contacts the radiator shroud so that the boot provides fluid communication between the ring shroud and the radiator shroud.

Abstract: A gas turbine engine includes a fan section, a gear arrangement configured to drive the fan section, a compressor section and a turbine section. The compressor section includes a low pressure compressor section and a high pressure compressor section. The turbine section is configured to drive compressor section and the gear arrangement. An overall pressure ratio, which is provided by a combination of a pressure ratio across said low pressure compressor section and a pressure ratio across said high pressure compressor section, is greater than about 35. The pressure ratio across the low pressure compressor section is between about 3 and about 8 whereas the pressure ratio across the high pressure compressor section is between about 7 and about 15.

Abstract: A compressor which includes: an inner casing arranged so as to cover a rotor shaft; an outer casing arranged so as to cover the inner casing and forming a fluid flow path around the rotor shaft; and a plurality of struts mounted in the entrance of the fluid flow path and between the inner casing and the outer casing; in which the plurality of struts are arranged in a radial pattern centered on the rotor shaft, and the spacings between the adjacent struts in the circumferential direction of the rotor shaft are unequal.

Abstract: A fan assembly includes a fan, two mounting members fixed to two opposite sides of the fan, and a fixing plate. Each of the mounting members includes an inner wall facing the fan and an outer wall away from the fan. The outer wall of each of the mounting members defines a recess and forms a block adjacent to a bottom of the mounting member. The blocks of the mounting members are adjacent to a first end of the fan. The fixing plate includes two engaging members respectively engaging in the recesses of the mounting members, a stop plate engaging with a second end opposite to the first end of the fan, and two resilient tabs respectively resisting against the blocks of the mounting members to sandwich the fan between the resilient tabs and the stop plate.

Abstract: A fan frame structure includes a plastic frame and a metal fixing frame, in which at least two support arms are disposed on the rim of the fixing frame and extended outwardly therefrom, the outwardly extended distance of each support arm shall be beyond the range of an accommodation space of the frame, the portion of the support arm beyond the accommodation space in integrally enclosed by the plastic material of the frame.

Abstract: A filter frame is removably attachable to a box fan. The filter frame is adapted for receiving a standard HVAC-style filter for removing contaminants from air flow induced by the fan. In this manner, a cost-effective means for filtering a flow of air is provided for residential and commercial settings. The filter frame is adaptable to a variety of standard box fan types of different styles and dimensions. The frame is configured to accommodate standard filters, such as those readily available from retail hardware stores and home centers.

Abstract: A plug for an inspection hole of a gas turbine engine is disclosed. The plug may have a stem including a first shaft, wherein a first seal is located circumferentially about the first shaft. The plug may have a swivel seal including a second seal spaced from a ball by a second shaft, and the swivel seal may be rotatably connected to the stem by the ball. The ball and the second seal may be fixed to the second shaft.

Abstract: An axial flow fan is configured to allow leakage flows in regions near rear edges of bent portions formed by bending outer peripheries of blades towards negative pressure surfaces to smoothly flow out to reduce the vortex scale of the leakage flows themselves and to be able to effectively control turbulence of the flows. The axial flow fan includes a bellmouth and blades, with outer peripheries of the blades being bent towards negative pressure surfaces, wherein in regions near rear edges of bent portions that are bent towards the negative pressure surfaces, there are disposed second bent portions formed by bending part of the bent portions further towards the negative pressure surfaces.

Abstract: A nacelle inlet for an aircraft engine of a type having an engine fan case with a forward flange includes an acoustic inner barrel having a forward edge and an aft edge, an outer shell having a nose lip portion with a trailing inner edge, and an outer barrel portion having an aft portion. The nacelle inlet also includes an aft attachment flange configured to attach the inlet to the forward flange of the engine fan case, and an aft bulkhead having an aft end and connecting the outer barrel portion of the outer shell to the aft attachment flange. The forward edge of the acoustic inner barrel is connected to the trailing inner edge of the nose lip portion, and the aft portion of the inner barrel is attached to the aft attachment flange.

Abstract: A method for increasing the total-to-static pressure ratio across a Ram Air Turbine (RAT) has designed and experimentally tested. The invention develops a localized accelerated flow of free-stream air near the discharge of the turbine rotor exhaust. This localized accelerated flow decreases the static pressure at the exit of the turbine and allows for additional power generation for a given free-stream flight condition. Full-scale wind tunnel experimenting testing shows that creating this low static pressure region behind the turbine resulted in significant increases in turbine output power when compared to a turbine that is not subjected to this invention. The invention showed the ability to increase the total-to-static pressure ratio across the turbine.

Abstract: A cylindrical wind-turbine has an intake opening set in a known direction of oncoming wind (such as towards the direction of an expected oncoming train). A central plunger acts as a valve to regulate airflow, and may seal the intake opening. Exit valves are situated near the rear of the device and/or at the rear in embodiments of the disclosed technology. The intake opening and exit valves may be opened or closed depending on readings from wind and water sensors. Generally speaking, when there is sufficient wind and low threat of water, the openings and valves are open, collecting wind energy. When there is a lack of wind or presence of water, the openings and valves are sealed to protect the interior components of the device from the elements and unnecessary wear and tear, prolonging the life of the device.

Abstract: A connector device for coupling a turbomolecular pump to an apparatus to be pumped. The connector device can suppress transmission of vibrations of relatively low frequencies. The pump has a rotor, a casing accommodating the rotor therein, and an intake port and an outlet port formed in the casing. The pump operates to suck gas from the intake port and to expel the gas from the outlet port by rotating the rotor within the casing at high speed. The connecting device has a connecting exhaust tube for connecting the intake port of the turbomolecular pump with the outlet port of the apparatus (such as a vacuum vessel) to be pumped. An annular weight is disposed around the outer periphery of the connecting exhaust tube. A viscoelastic member is interposed between the connecting exhaust tube and the weight to form a vibration absorber.

Abstract: An airflow passage structure is applied to a fan. The airflow passage structure includes a sidewall and an airflow channel. The sidewall has uneven thickness. The airflow channel is defined by an inner surface of the sidewall, and includes a channel entrance and a channel exit. The channel exit is in communication with an airflow inlet of the fan. The diameter of the airflow channel is non-uniformly distributed.

Abstract: A kinetically modulated fan structure is provided. The fan structure comprises a housing, a plurality of blades and an equilibrating structure, wherein the equilibrating structure is disposed on the inner side of the housing, and formed integrally with the housing and the blades. Thereby, the fan structure is adapted to be kinetically equilibrated during the manufacturing process. As a result, the modulation of the kinetic equilibrium with respect to the fan structure is eliminated since all of the yielded fan structures are uniform in quality. The simplified production is both time efficient and cost efficient, while producing a durable product.

Abstract: A fan assembly includes a casing, which is substantially cylindrical in shape with a fan motor and fan blades located therein, so that air can be drawn into the casing and delivered therefrom. A grille extends over an open end of the casing and has a plurality of angular curved blades extending from a central portion thereof to the periphery. These curved blades are, preferably, at an angle to the normal plane through the grille, so that air in the casing is caused to move to the fan blades at an angle permitting efficient operation of the fan.

Abstract: A fan shroud assembly includes a fixed fan shroud and a removable fan shroud. An upper retention system integral with the fixed and removable fan shrouds secures the two circumferential ends of the removable fan shroud to the fixed fan shroud. A lower retention system integral with the fixed and removable fan shroud secures the center of the removable fan shroud to the fixed fan shroud. No additional fasteners are required to connect the removable fan shroud to the fixed fan shroud because of the integral nature of the upper and lower retention systems.

Abstract: A round axial fan with balancing structure includes a hub; a ring-shaped band located around an outer side of the hub to thereby define an annular flow passage between the hub and the ring-shaped band; a plurality of blades located in the annular flow passage; and a plurality of recesses circumferentially spaced on and along the ring-shaped band, each of the recesses internally defining a receiving space for at least one balancing element to fit therein. With these arrangements, it is able to achieve weight balance of the round axial fan for the latter to rotate in a balanced state and to avoid any vibration due to unbalanced rotation of the round axial fan.

Abstract: A gas turbine engine includes a spool along an engine centerline axis which drives a gear train, said spool includes a low pressure compressor with four (4) stages.

Abstract: A service tube apparatus for a gas turbine engine includes a service tube assembly having: (a) an elongated, hollow service tube; and (b) a service tube baffle surrounding the service tube which is pierced with a plurality of impingement cooling holes.

Abstract: A gas turbine engine includes a low pressure compressor section and a high pressure compressor section. A low pressure turbine drives the low pressure compressor section. A gear arrangement is driven by the low pressure turbine to in turn drive a fan section. A pressure ratio across the low pressure compressor section is between about 4-8, and a pressure ratio across the high pressure compressor section is between about 8-15. In a separate feature, a compressor case includes a front compressor case portion and a rear compressor case portion, with the rear compressor case portion being axially further from an inlet case than the front compressor case portion. A support member extends between the fan section and the front compressor case portion.

Abstract: One aspect of the present invention provides a steam turbine comprising a rotor and a casing that installs the rotor inside, wherein the casing comprises an upper-half section and a lower-half section, which are coupled with each other by an upper-half flange and a lower-half flange thereof, wherein the upper-half section includes: a semi-cylindrical wrapper plate extending in an axial direction of the rotor, end plates coupled with the wrapper plate, each of the end plate is disposed perpendicular to the rotor, wherein at least one of axial ends of the wrapper plate includes a wrapper plate projecting portion that projects from the corresponding end plates in the axial direction, and a first end plate reinforcing rib disposed on the outside surfaces of the end plates in a peripheral direction of the inner periphery of the wrapper plate; and a plurality of second end plates reinforcing ribs disposed radially on the outside surfaces of the end plates, wherein the second end plates reinforcing ribs couple the w

Abstract: A support frame portion is divided into a first support-frame half-portion and a second support-frame half-portion along a virtual reference dividing plane. A raised portion is integrally formed with each of side walls in a pair of the first web half-portion, projecting toward the second web half-portion beyond the virtual reference dividing plane. A raised portion is integrally formed with each of side walls in a pair of the second web half-portion, projecting toward the first web half-portion beyond the virtual reference dividing plane. A recessed portion is formed in each of the side walls in the pair of the first web half-portion, and is fitted with the raised portion corresponding thereto of the second web half-portion. A recessed portion is formed in each of the side walls in the pair of the second web half-portion, and is fitted with the raised portion corresponding thereto of the first web half-portion.

Abstract: A fan includes an impeller rotatable about a rotation axis and having a plurality of rotating vanes, and a plurality of stationary vanes connecting an outer casing to a supporting body which supports a motor rotating the impeller. At least in a portion of each stationary vane in a radial direction, an axial distance between that stationary vane and one of the rotating vanes closest thereto and a slant angle of that stationary vane with respect to an axial direction increase as that stationary vane moves outwardly in the radial direction.

Abstract: A system, including a rotary machine including: a stator, a rotor configured to rotate relative to the stator, wherein the rotor comprises a plurality of blades having a non-uniform spacing about a circumference of the rotor.