Abstract: The coating of abradable material presents cavities opening out into the surface of the coating, the cavities extending over a fraction of the thickness of the coating and being defined by walls which form a plurality of continuous paths at the inside surface of the annular portion between the axial end faces thereof, and which form an angle of not less than 5° relative to the general direction of end portions of blades that might come into contact with the abradable material.

Abstract: A method of modifying a rotor blade, and a rotor blade are provided. The rotor blade is for a steam turbine and it is modified to facilitate altering a natural vibratory frequency of the rotor blade, the rotor blade includes a leading edge, a trailing edge, a first sidewall, and a second sidewall, wherein the first and second sidewalls are connected axially at the leading and trailing edges, and the sidewalls extending radially between a rotor blade root to a rotor blade tip. The method includes determining a vibratory resonance condition of the rotor blade and forming a blade extension between the rotor blade root and the rotor blade tip that alters the determined resonance condition.

Abstract: An axial flow gas turbine comprises a turbine and a turbine exhaust section. The turbine comprises a turbine nozzle containing a low pressure turbine stage having an annular row of stator vanes (V2) followed in axial succession by an annular row of rotor blades (B2). The low pressure turbine stage is characterized by the following parameters: the ratio of vane airfoil pitch to vane airfoil axial width (P/W) at the root end of the vane airfoil (V2) is in the region of 1.0 to 1.2, preferably about 1.12; the ratio of blade airfoil pitch to blade airfoil axial width (P/W)at the root end of the blade airfoil (B2) is in the region of 0.6; the ratio of blade diameter at the tip end of the blade airfoil to blade diameter at the root end of the blade airfoil (blade tip/hub diameter ratio) is in the region of 1.6-1.8, preferably about 1.72; and the ratio of the axial length of the exhaust section to the blade airfoil height (L/H) is no greater than a value in the region of 4:1, preferably 3:1.

Abstract: An axial-flow fan having a high fan efficiency and high performance is provided by improving a fluid flow on the rear edge side of a blade tip without deteriorating the fluid flow on the front side of the blade tip, and reducing loss of horsepower without causing a large influence on loadings. The blade has a warped portion on the side surface of the blade tip on the rear edge side thereof, being formed by bending the blade tip toward upstream at angles between 5 to 30 degrees with a smooth filet R along a line C connecting a position along the blade tip at the chord length A to 1/5 A from the rear edge of the blade tip toward the front edge of the blade tip and a position along the radial length B of the blade at 1/2B to 1/10B from the rear edge of the blade tip.

Abstract: A composite heat-dissipating device is provided for significantly increasing the number and size of blades so as to enhance the heat-dissipating performance. The composite heat-dissipating device is constructed by a plurality of impellers, each of which includes a plurality of blades. When the plurality of impellers are assembled together, the plurality of blades are arranged around the hub of the composite heat-dissipating device and there is an overlapped region formed between every two adjacent blades.

Abstract: The present invention describes an axial flow fan blade that presents innovation on its shape that results in a lower noise emission and in a higher efficiency. The axial flow fan blade, object of the present patent, has a lower vortex emission than the blades available on the previous art. This lower vortex emission is responsible for a lower level of pressure fluctuations, which results in a lower noise emission, and is also responsible for a lower energy expense on the vortex formation, which results in an efficiency increase. The present axial flow fan blade can be employed in various applications where it is necessary to move any gas.

Abstract: Small winglets placed at the outer end of each fan blade substantially reduce the vortices created in conventional fans by the pressure differential between the low pressure and high pressure sides of the blade. The winglet acts as a barrier, which substantially blocks leakage around the blade tip, thus suppressing vortices. Technical advantages include noise reduction, because there are no shedding vortices to create noise as the blades pass the struts; increased aerodynamic efficiency of the fan, providing higher air flow for the same fan speed, size, and power, because less energy is lost in vortices; and minimal cost impacts, because housings currently used for fans can still be used with standard finger guards and because winglets and blades can be formed integrally of injection molded plastic.

Abstract: In a fuel pump having a high pump efficiency, an annular portion is formed on an outer periphery of an impeller to let one- and opposite-side blade grooves be independent of each other. Then, various improvements are made such as tilting front and rear wall surfaces of the blade grooves in a predetermined direction, forming one- and opposite-side blade grooves in a zigzag fashion, forming a guide surface in a communicating passage of a pump housing, and forming communicating holes in an impeller.

Abstract: In an axial flow compressor, an apical angle at a leading edge of a stator blade progressively increases from a root end to a tip of the stator blade whereby the stator blade loss and noises caused by unsteady inter-blade airflow can be minimized. Preferably, the apical angle at the tip of the stator blade is 1.5 to 2.5 times of the apical angle at the root of the stator blade.

Abstract: Disclosed is an air blower apparatus comprising a hub (14) which is a center of rotation, and a plurality of blades (13, 13, 13) disposed along an outer peripheral surface of the hub (14) and having leading and trailing edges (13a) and (13b) wherein both an outer peripheral end of the leading edge (13a) and an outer peripheral end of the trailing edge (13b) lie ahead relative to the rotative direction. An outer peripheral part (13c) of the blade (13, 13, 13) is bent toward the suction side in such a way as to form a starting point at which an air flow starts leaking, and the radial-direction width, W, of the bent part gradually increases from the vicinity of the leading edge (13a) to the vicinity of the trailing edge (13b).

Abstract: A rotor blade for a fan, said rotor blade comprising a first blade zone having an airfoil cross-section and a second blade zone having a cross-section of reduced thickness, wherein the average thickness of the second blade zone is less than 50% of the average thickness of the first blade zone.

Abstract: A novel concept for a propeller blade configuration incorporates the model of the natural wave behavior. The leading edge of the propeller blade has a convex segment followed by a concave segment, as seen in a plan view. The leading and trailing edges are rounded so as to promote proper fluid sheet formation along the flat surfaces and to reduce undesirable vortice formation. Best results are obtained by modeling the surfaces along a sine or tangent function.

Abstract: The improvements are made in the turbine scroll and the turbine blades. The scroll structure for the radial turbines is characterized by the foregoing scroll having a scroll width ratio between the width in the radial direction (&Dgr;R) and the width in the direction of the rotation (B) ranging from &Dgr;R/B=0.3 to 0.7. It is further characterized by the configuration in which the turbine blades have cut-away areas at the blade corners by a prescribed amount, which are provided on the inlet edge at the shroud side and hub side where the operating gas flows.

Abstract: A blade part in a turbofan includes a hub coupled with a rotating axis of a driving part, a plurality of blades arranged radially at a circumferential part of the hub, and a shroud coupled with a plurality of the blades and arranged so as to confront the hub wherein the blades lie between the hub and the shroud, and wherein each of the blades form an airfoil constructed with a top camber line defined by an NACA 4-digit airfoil and a bottom camber line lying closer to the top camber line than a bottom camber line defined by the NACA 4-digit airfoil.

Abstract: A blade or wing configuration has a leading edge and a trailing edge, and an upper surface and a lower surface extending from the leading edge to the trailing edge. At least one of the upper surface and the lower surface is formed with a curved segment and a straight segment. The curved segment starts from a starting point on the upper surface or the lower surface between the leading edge and the trailing edge and ends at the leading edge. The straight segment extends from the starting point to the trailing edge. A tangent at the leading edge is substantially parallel to the direction of movement and the straight segment forms an angle &thgr; of approximately 30°-60° with respect to the direction of movement. The trailing edge can be formed with teeth.

Abstract: A turbofan engine includes a row of fan blades disposed upstream from a row of stator vanes, and is powered by a core engine. The fan blades are serrated for mixing wakes therefrom to attenuate fan noise.

Abstract: Rotor blades for wind power installations are known in many different forms. In a wind power installation the rotors or the rotor blades thereof represent the main source of sound. For reasons relating to acceptance and noise prevention laws, the aim should/must be that of minimizing the levels of sound emission as wind power installations are often also set up in the proximity of residential accommodation. The levels of sound emission which hitherto occur with a wind power installation or a wind power converter also mean that wind power installations are faced with resistance from populated areas because of the sound they produce and for that reason such installations can be accepted sometimes with difficulty or not at all as authorities responsible for planning permission refuse permission for wind power installations because of the existing environmental requirements, noise also being an environmentally polluting factor.

Abstract: A centrifugal fan mounted in a laptop computer is assembled to include a casing having an intake opening and a horn-shaped outlet opening for increasing the air outflow, an impeller rotatably mounted in the casing with a reduced diameter and bared inner space for increasing the air capacity, and fan blades attached to the impeller, wherein each of fan blades is chipped at the rim for lowering the noise.

Abstract: An improved impeller which facilitates greater linear movement of a media with less torque; and which accordingly, consumes less power. A blade portion of the impeller has a front media accelerating face and substantially varying slopes which increase from the leading to the trailing edge portions of a media-accelerating front face thereof, to facilitate a gradual acceleration of the media as the impeller rotates. The slope of the front face of the blade portion also gradually increases moving outwardly along the intermediate blade portion, from the hub to the peripheral edge portion thereof. The blade portions have increasing slope to accelerate the media more axially, and less radially, as the impeller rotates. The leading and trailing edge portions of the blade portion each have an elongated forwardly extended peripheral portion, which culminates in a tip portion, which is most preferably bulbuous, to facilitate efficient penetration of the media by the blade portion.

Abstract: A hollow blade for a ceiling fan is made from a selected material and has a hollow interior structure to result in a reduced weight for decreasing motor loading and saving electric power consumption, and saving material consumption for reducing costs.

Abstract: A rotor blade for a fan, said rotor blade comprising a first blade zone having an airfoil cross-section and a second blade zone having a cross-section of reduced thickness, wherein the average thickness of the second blade zone is less than 50% of the average thickness of the first blade zone.

Abstract: A blade for an axial-flow turbine includes an intrados producing a positive pressure between a leading edge and a trailing edge, and an extrados producing a negative pressure. The intrados is formed at its rear portion with a flat surface portion connected to the trailing edge, and the extrados has a curved surface portion formed at least at a portion corresponding to the flat surface portion. The trailing edge of the turbine blade is pointed at its end. The angle of intersection between the intrados and the extrados at the trailing edge is a right angle or an acute angle. Thus, it is possible to inhibit the flowing of a gas from the intrados at the trailing edge toward the extrados and to decrease the degree of curvature of the extrados at the trailing edge portion to reduce the flow speed, thereby minimizing a shock wave generated at the trailing edge portion to reduce the pressure loss and enhance the performance of the turbine.

Abstract: An improved impeller which facilitates greater linear movement of a media with less torque; and which accordingly, consumes less power. A blade portion of the impeller has a front media accelerating face and substantially varying slopes which increase from the leading to the trailing edge portions of a media-accelerating front face thereof, to facilitate a gradual acceleration of the media as the impeller rotates. The slope of the front face of the blade portion also gradually increases moving outwardly along the intermediate blade portion, from the hub to the peripheral edge portion thereof. The blade portions have increasing slope to accelerate the media more axially, and less radially, as the impeller rotates. The leading and trailing edge portions of the blade portion each have an elongated forwardly extended peripheral portion, which culminates in a tip portion, which is most preferably bulbuous, to facilitate efficient penetration of the media by the blade portion.

Abstract: An axial flow fan wherein an impeller having a plurality of blades is supported rotatably in the cylindrical cavity portion of a venturi case so that an outer peripheral edge of each of the blades faces to an inner peripheral surface of the cavity portion with a small air gap. The outer peripheral edge of the blade is increased in thickness gradually toward a discharge port side of the venturi case from a suction port side of the venturi case. An peripheral edge portion of the blade at a suction port side of the venturi case is bent in the circumferential direction from a negative pressure surface side of the blade, so that the edge is small in thickness. An outer peripheral edge portion of the blade at a discharge port side of the venturi case has a portion extending circumferentially from a positive pressure surface side of the blade.

Abstract: A vane structure for a propeller for engaging fluid and preventing cavitation or the rapid formation and collapse of low-pressure gas bubbles in a liquid. The vane structure for a propeller includes a plurality of spaced vanes that are mounted to and extend away from a hub. Each of the vanes has a leading edge, a trailing edge and an end. A lip is mounted on the end of each of the vanes for selectively engaging fluid and dispersing low-pressure gas bubbles positioned generally adjacent to the plurality of spaced vanes.

Abstract: The present invention relates to a moving blade (1), cast in one piece, for a turbomachine, in particular a turbine or compressor, comprising an aerodynamically shaped profile body (2) which has a shroud band (5). The shroud band (5) projects beyond the profile body (2) in the circumferential direction (6) and has a fin (12). The fin (12) possesses a base portion (14), a transitional portion (15) and a sealing portion (16). An axially measured wall thickness decreases in a transitional portion (15) from the base portion (14) to the sealing portion (16).

Abstract: A hollow blade for a ceiling fan is made from a selected material and has a hollow interior structure to result in a reduced weight for decreasing motor loading and saving electric power consumption, and saving material consumption for reducing costs.

Abstract: An impeller for generating an air flow, for use in a device such as a blower/vacuum, the impeller having a hub structure for mounting the impeller on a rotatable shaft of the blower/vac and a plurality of air-flow generating vanes coupled to the hub structure in a non-uniform manner wherein the spacing between adjacent vanes is irregular. An impeller having non-uniform spacing between adjacent vanes is provided. Additional features of the impeller may include a plurality of debris engaging structures or serrations for facilitating a finer mulch of air-entrained debris.

Abstract: A blade for an axial-flow turbine includes an intrados producing a positive pressure between a leading edge and a trailing edge, and an extrados producing a negative pressure. The intrados is formed at its rear portion with a flat surface portion connected to the trailing edge, and the extrados has a curved surface portion formed at least at a portion corresponding to the flat surface portion. The trailing edge of the turbine blade is pointed at its end. The angle of intersection between the intrados and the extrados at the trailing edge is a right angle or an acute angle. Thus, it is possible to inhibit the flowing of a gas from the intrados at the trailing edge toward the extrados and to decrease the degree of curvature of the extrados at the trailing edge portion to reduce the flow speed, thereby minimizing a shock wave generated at the trailing edge portion to reduce the pressure loss and enhance the performance of the turbine.

Abstract: A ventilation fan assembly (10) having a fan (22) mounted in a housing (12) and a shutter assembly (60). The housing has a square inlet portion (12C), a circular center portion (12E) and a conical outlet portion (12D) having rifling grooves (20). The shoulder (16) formed between the inlet portion and the center portion is radiused to reduce disruption of air flowing from the inlet portion to the center portion. The shape of the blades (32) of the propeller (28) is such that the axial velocity produced as the propeller rotates is essentially constant along the length of the blades. The shutter assembly has a large, radiused entrance and airfoil shaped blades which reduce air disruption. The blades have a flexible flap (68) along the trailing edges (64D) which form a seal between adjacent blades to prevent air from leaking from the housing through the shutter assembly.

Abstract: The present invention describes an axial flow fan blade that presents innovation on its shape that results in a lower noise emission and in a higher efficiency. The axial flow fan blade, object of the present patent, has a lower vortex emission than the blades available on the previous art. This lower vortex emission is responsible for a lower level of pressure fluctuations, which results in a lower noise emission, and is also responsible for a lower energy expense on the vortex formation, which results in an efficiency increase. The present axial flow fan blade can be employed in various applications where it is necessary to move any gas.

Abstract: An axial-flow fan having a high fan efficiency and high performance is provided by improving a fluid flow on the rear edge side of a blade tip without deteriorating the fluid flow on the front side of the blade tip, and reducing loss of horsepower without causing a large influence on loadings. The blade has a warped portion on the side surface of the blade tip on the rear edge side thereof, being formed by bending the blade tip toward upstream at angles between 5 to 30 degrees with a smooth filet R along a line C connecting a position along the blade tip at the chord length A to 1/5 A from the rear edge of the blade tip toward the front edge of the blade tip and a position along the radial length B of the blade at 1/2B to 1/10B from the rear edge of the blade tip.

Abstract: High efficiency and low noise is achieved in an automotive engine-cooling fan assembly by flaring the inlet to the shroud barrel, and shaping the tips of the fan blades to conform to the shape of the inlet. Separation of the flow entering the fan is reduced by extending the flare over the axial extent of the blade tip, and tip clearance losses are reduced by controlling recirculation along the entire blade tip. Blade rake is used to minimize fan deflection, thereby allowing the use of small tip clearances, which further enhance performance.

Abstract: The invention relates to an axial flow fan comprising a wheel having a plurality of blades (1) rotatably mounted within and at distance of at least a casing (4), each blade (1) being provided with an acoustic noise reducing means (10) at the vicinity of the casing (4), characterized in that the noise reducing means (10) are provided at the downstream face (I) of the blades (1) and made by a fold of material (10A) forming an outgrowth relatively to the surface of each blade (1) and whose external face (12) forming the outline is approximately tangential to the tip of each blade at its upper part.

Abstract: A set of fan blades comprises a plurality of blades evenly distributed around a hub case, wherein each of the blades has an outer edge from which a projection extends away at an angle.

Abstract: A cooling air blowing apparatus of a refrigerator includes: a driving motor fixed at a motor mount formed at a rear side of a freezing chamber; a blowing fan mounted on a rotational shaft of the driving motor and configured to blow cooling air in both an axial and a radial direction as the driving motor is driven; and a shroud positioned in a circumferential direction of the blowing fan. The blowing fan includes turbo blades for blowing cooling air in a radial direction in addition to the axial flow blade for blowing cooling air in an axial direction. The cooling air blown in the axial direction is sent to a freezing chamber, while the cooling air blown in the radial direction is sent to the cooling chamber. Thus, the blowing fan with the turbo blades ensures that in a refrigerator having a complicated and long cooling air passage structure, cooling air can be circulated smoothly and quickly.

Abstract: A high-performance propeller has one hub and a plurality of blades, characterized in that a double-side or a single-side arc brim is provided at the tip of each blade. The propeller of the invention can provide a small induced drag and convert the centrifugal force to the effective force so as is to increase the differential pressure near the tip of blades and thereby increase the acting force on blades. Under the condition of same power consumption, it has been tested for the large propeller in the type of lateral inclination that the amount of flow is increased about 12%˜17%, which is equivalent to save energy 40%˜70%. Since the fluid dynamic performance presents the aspect ratio approaching infinity, the width of the blades can be increased whereas the induced drag is not increased. Applying the method of increasing the area of the blades and decreasing the velocity of outflow fluid, the effect on saving of energy can be further improved greatly on the present basis.

Abstract: A windmill rotor of the front-runner type and airfoil type wind blades therefor in which the blade tips have a longitudinally forwardly curved configuration. The curvature solves the problem of inward flexure of the blade in strong wind conditions, without requiring modification of the manner in which the rotor as a whole is mounted in order to avoid having the blade strike the windmill tower under such strong wind conditions.

Abstract: A blade for a cooling fan is formed on an outer periphery of a rotor of the cooling fan and is curved. The blade has a convex outer surface and a concave inner surface. A curved angle of the blade between a line through the center of the rotor and a root of the convex outer surface and a line through the root and a tip of the convex outer surface is between 30° to 40°. A plane surface is formed on the concave inner surface and at a distal end of the blade. A first cutout is defined at a bottom side and a proximate end of the blade. A second cutout is defined at the upper side and the distal end of the blade.

Abstract: An aerofoil (34) for a gas turbine engine is substantially solid, including a concave pressure surface (42) and a convex suction surface (40). The pressure surface (42) is provided with a projection in the form of an elongate fin (44) which extends in the radial direction of the aerofoil.

Abstract: A method for the improvement of wind turbine rotor efficiency blades of a wind turbine rotor with serrated trailing edges each having a plurality of span-wise, periodic indentations, in the form of saw teeth having approximately 60 degrees included angles between adjacent vertices. The efficiency of an existing wind turbine rotor is improved by the attachment of an apparatus to at least part of the trailing edge of the wind turbine blades, the apparatus being in the form of a serrated panel that is fixed to the surface of the blade and has the serrations extending into the airflow behind the trailing edge of the existing blade. The efficiency of a new wind turbine blade is improved by manufacturing the blade with serrations of at least part of the trailing edge of the wind turbine blade.

Abstract: An impeller structure includes a hub provided with a rotation shaft that may be pivoted to rotate. The hub has a periphery provided with an annular plate connected with the hub. A plurality of blades each have one end fixed to the annular plate and connected with a top face and a bottom face of the annular plate. The blades are extended outward from the hub in a radiating manner.

Abstract: An airfoil for a gas turbine engine includes a leading edge, a trailing edge, a tip plate, a first sidewall, and a second sidewall. The first sidewall extends in radial span between an airfoil root and the tip plate. Furthermore, the first sidewall defines a pressure side of the airfoil. The second sidewall is connected to the first sidewall at the leading and trailing edges, and extends in radial span between the airfoil root and the tip plate. The second sidewall defines a suction side of the airfoil. The tip plate includes at least one groove that extends substantially between the first and second sidewalls.

Abstract: A turbine blade is provided with a bracket arranged in the tip region of the blade and projecting beyond the blade profile. The bracket is formed merely in a section of a surface region of the pressure side, the surface region being enclosed by an imaginary chord bearing against the pressure side of the blade body both in the region of the leading edge and in the region of the trailing edge.

Abstract: A rotatory pump has a housing (20) and an impeller wheel (40) which is mounted on a driving shaft (30) to rotate integrally therewith. The driving shaft is rotatably supported in the housing. The driving shaft also has a disk (44) disposed to be concentric with the driving shaft. Radially extending blades (46) are directed along the axial direction of the driving shaft (30) being provided on the disk, and the blades, together with the inner wall portions (22a) of the housing (20) which face the blades (46), form flow channels for the fluid to be pumped. At least one raised portion (48) is on each of the radially extending edges (46a) of preferably three blades (46), to bear against the inner wall portions (22a) of the housing (20) which face the blades (46) of the impeller wheel housing.

Abstract: A blade for a cooling fan is formed on an outer periphery of a rotor of the cooling fan and is curved. The blade has a convex outer surface and a concave inner surface. A curved angle of the blade between a line through the center of the rotor and a root of the convex outer surface and a line through the root and a tip of the convex outer surface is between 30° to 40°. A plane surface is formed on the concave inner surface and at a distal end of the blade. A first cutout is defined at a bottom side and a proximate end of the blade. A second cutout is defined at the upper side and the distal end of the blade.

Abstract: An airfoil for a gas turbine engine includes a leading edge, a trailing edge, a tip plate, a first sidewall, and a second sidewall. The first sidewall extends in radial span between an airfoil root and the tip plate. Furthermore, the first sidewall defines a pressure side of the airfoil. The second sidewall is connected to the first sidewall at the leading and trailing edges, and extends in radial span between the airfoil root and the tip plate. The second sidewall defines a suction side of the airfoil. The tip plate includes at least one groove that extends substantially between the first and second sidewalls.

Abstract: A compressor stator includes an outer casing supporting a row of stator vanes extending radially inwardly therefrom. Each vane includes pressure and suction sides extending axially between leading and trailing edges and radially between a root and a tip. The root and tip are twisted relative to a pitch section disposed therebetween. Each vane tip is radially convex adjacent a leading edge for defining an axially concave outer flowpath in the casing for reducing peak velocity of airflow for enhanced efficiency.

Abstract: Small winglets placed at the outer end of each fan blade substantially reduce the vortices created in conventional fans by the pressure differential between the low pressure and high pressure sides of the blade. The winglet acts as a barrier, which substantially blocks leakage around the blade tip, thus suppressing vortices. Technical advantages include noise reduction, because there are no shedding vortices to create noise as the blades pass the struts; increased aerodynamic efficiency of the fan, providing higher air flow for the same fan speed, size, and power, because less energy is lost in vortices; and minimal cost impacts, because housings currently used for fans can still be used with standard finger guards and because winglets and blades can be formed integrally of injection molded plastic.

Abstract: To remove moisture from the steam flow path of steam turbines, one or more grooves are located on the pressure or concave side of the steam turbine stationary and/or rotating airfoils. The grooves are oriented predominantly radially and are disposed close to the airfoil trailing or exit edge. Moisture deposited on the surface of the airfoil flows into the groove and, due to pressure and/or centrifugal forces, the moisture flows to the turbine inner or outer sidewall and, thus, is available for removal from the steam path in the same blade row in which it was first deposited. An advantage of removing moisture in the blade row in which it was first deposited is that it reduces efficiency losses associated with the chronology of the moisture downstream of the airfoil trailing edge.