Abstract: In an axial flow fan, a line extending from a center axis and passing a corner where a following edge and a radially outer edge of a blade of an impeller meet is arranged forwardly in a rotational direction from an another corner where a leading edge of the blade and a radially outer surface of a hub meet. Furthermore, a camber ratio of the blade, which is minimum at a joint with the hub across the blade, monotonically increases to be maximum at the radially outer edge of the blade.

Abstract: A method for assembling turbomachinery having combined particle separation device and flow regulating device is provided. The turbomachinery includes a casing; a compressor attached to an inside of the casing, the compressor having a shaft supported by bearings; and a cooling system mounted inside the casing and configured to cool the bearings of the compressor with a cooling fluid. The cooling system includes a particle separation device configured to separate particles from the cooling fluid, and a flow regulation device that fluidly communicates with the particle separation device without contacting the particle separation device. The flow regulation device is disposed adjacent to the particle separation device within a wall of the casing.

Abstract: A turbine component has an airfoil extending between a leading edge and a trailing edge, and has an outer surface. A coating includes at least two discontinuous areas that are spaced from each other such that there is an area of uncoated surface between the discontinuous areas of coating. In addition, a method of providing such a coating is disclosed.

Abstract: A compressor component having a non-linear thickness distribution along the span length is disclosed. By altering the thickness distribution to a non-linear arrangement so as to locally increase airfoil thickness proximate a mid-span location, the natural frequency of the airfoil is increased so as to not coincide with a critical engine order of the compressor. Further, the present invention provides a novel airfoil profile in accordance with the coordinates of Table 1. The present invention also includes a carrier segment or disk fabricated from a material so as to eliminate corrosion with the compressor component.

Abstract: A gas turbine engine combustion chamber including at least one deflector mounted on the chamber end wall and including an opening for a carburetted air supply device. The deflector includes an opening, corresponding to the chamber end wall opening, with an annular cylindrical part for attachment to the wall, the cylindrical part including a mechanical attachment mechanism collaborating with a complementary attachment mechanism on a metal sleeve secured to the wall and a cylindrical centering cup fixed by one end to the sleeve and housed inside the cylindrical part of the deflector.

Abstract: A blower fan includes a housing having a lateral wall defining a compartment. The housing includes an air inlet and an air outlet both in communication with the compartment. An impeller mounted in the compartment includes a hub and blades mounted on the hub. A first plane including opposite first and second end edges in the air outlet is parallel to and spaced from a second plane including a center of the hub. The compartment of the housing includes an air outlet section and a pressure accumulating section on opposite sides of the second plane. The air outlet section is located between the first and second planes. The lateral wall of the housing includes at least one air guiding hole located in the pressure accumulating section. At least one air guiding tube includes an outlet end and an inlet end coupled to the at least one air guiding hole.

Abstract: A one piece axial flow turbine case with an inlet volute and an outlet volute with an axial flow turbine positioned between the inlet and outlet volutes, in which the turbine vanes and blades can be installed or removed from one side of the case without disassembling the two volutes. The one piece turbine case eliminates the mating flange, the flange seal, and the flange bolts required in the two piece turbine volute case. The one piece axial flow turbine case reduces the part count, reduces the weight of the turbine, improves the reliability of the turbine, and improved the performance of the turbine. The annular guide vane assembly with an annular outer shroud having guide vanes extending from the shroud is inserted through an opening of the turbine case. The vane outer shroud extends aft to form an outer shroud for the turbine blades.

Abstract: In a turbine housing for an exhaust gas turbocharger of an internal combustion engine with at least one spiral channel, which can be coupled into an exhaust gas flow of an exhaust tract of the internal combustion engine, and a receiving space for a turbine wheel which is disposed downstream of the at least one spiral channel and can be acted upon by the exhaust gas of the internal combustion engine passing through the at least one spiral channel of the turbine housing, there is at least one partial housing including the at least one spiral channel, and a housing module which is fastened to the partial housing and has a vane structure disposed upstream of the receiving space which also includes an attachment surface for a bearing section of the exhaust gas turbocharger. The invention also resides in an exhaust gas turbocharger with such a turbine housing as well as to a method for producing such a turbine housing.

Abstract: A shrouded wind turbine comprises an impeller and a turbine shroud surrounding the impeller. The shroud includes alternating inward and outward curving elements that form mixing elements on a trailing edge of the turbine shroud. The inward and outward curving elements have exposed lateral surfaces, or in other words do not have sidewalls joining the inward and outward curving elements. This allows for both transverse mixing and radial mixing of air flow through the turbine shroud with air flow passing along the exterior of the turbine shroud.

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. The table selected from the TABLE. 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 gas turbine (1) includes a combustion chamber (2) followed by a stator airfoil row (4) defining a plurality of guide vanes and separated by the combustion chamber (2) by a first gap (5), and a rotor airfoil row (6) separated by the stator airfoil row (4) by a second gap (7). The stator airfoils (15) of the stator airfoil row (4) are connected to guide vane boxes (17) collecting a cooling fluid (A) and injecting it through nozzles (20) in the second gap (7) to make it to enter rotor airfoil inlets (23). The guide vane boxes (23) are provided with passages (30) connecting a zone (31) upstream of the guide vane boxes (17) to a zone (32) of the second gap (7) downstream of the guide vane boxes (32). Moreover, the mouths (3) of the passages (30) facing the rotor airfoil row (6) are closer to a hot gases path than the nozzles (20).

Abstract: A plenum fan comprising a fan wheel disposed within a box-like enclosure includes a secondary inlet cone, a primary inlet cone, and a flexible duct. The two inlet cones convey air to the mouth of the fan wheel. A frame supports the fan wheel and the primary inlet cone such that the frame, the fan wheel and the primary inlet cone comprise a fan assembly. If the fan assembly shifts due to fan thrust or vibration, the fan assembly moves as a unit. The flexible duct connects the primary inlet cone to an inlet of the enclosure while isolating the fan assembly's vibration from the enclosure. The secondary inlet cone extends from the inlet of the enclosure, protrudes into or toward the primary inlet cone and provides a smooth airflow path over the abrupt shape of the flexible duct.

Abstract: An airfoil (30) and fabrication process for turbine blades with cooling channels (26). Tapered tubes (32A-32D) are bonded together in a parallel sequence, forming a leading edge (21), a trailing edge (22), and pressure and suction side walls (23, 24) connected by internal ribs (25). The tapered tubes may be extruded without camber to simplify the extrusion process, then bonded along matching surfaces (34), forming a non-cambered airfoil (28), which may be cambered in a hot forming process and cut (48) to length. The tubes may have tapered walls that are thinner at the blade tip (T1) than at the base (T2), reducing mass. A cap (50) may be attached to the blade tip. A mounting lug (58) may be forged (60) on the airfoil base and then machined, completing the blade for mounting in a turbine rotor disk.

Abstract: An exhaust diffuser system and method for a turbine engine includes an inner boundary and an outer boundary with a flow path defined therebetween. The inner boundary is defined at least in part by a hub structure that has an upstream end and a downstream end. The outer boundary may include a region in which the outer boundary extends radially inward toward the hub structure and may direct at least a portion of an exhaust flow in the diffuser toward the hub structure. The hub structure includes at least one jet exit located on the hub structure adjacent to the upstream end of the tail cone. The jet exit discharges a flow of gas substantially tangential to an outer surface of the tail cone to produce a Coanda effect and direct a portion of the exhaust flow in the diffuser toward the inner boundary.

Abstract: A method for depositing material on a turbine airfoil having a tip wall extending past a tip cap, wherein the tip wall includes a first alloy with a single crystal microstructure. The method includes: depositing a second alloy on at least a portion of the tip wall to form a repair structure, wherein a high temperature oxidation resistance of the second alloy is greater than a high temperature oxidation resistance of the first alloy, and wherein the repair structure has a crystallographic orientation that is substantially the same as a crystallographic orientation of the tip wall.

Abstract: Turbine blade assemblies of a turbine include airfoils that are mounted on bases. The leading and/or trailing edges of the bases are provided with curved portions. Likewise, curved portions may be provided on leading and/or trailing edges of the angle wings of a turbine blade assembly. Also, curved portions may be provided on the leading and/or trailing edges of nozzle assemblies of a turbine.

Abstract: A fluid machine includes a non-streamline casing capable of forming a stable vortex street on a downstream side by internal and external flows, and an impeller disposed inside the casing. The casing has a vortex generator configured to form the vortex street on the downstream side. The vortex generator is provided with a phase control structure which regulates a phase of a vortex formation that fluctuates along a circumferential direction in a plane including a rear face of the casing and which clarifies a cell structure to be formed along the circumferential direction of the casing to fix, on a surface of the casing, respective positions of cells into a plurality of segmented regions arranged in the circumferential direction. The velocity of the internal flow is increased by the phase control structure.

Abstract: A two-stage, omnidirectional vertical axis wind turbine includes a first chamber in which a plurality of angularly spaced horns guide wind from any side of the wind turbine into a chamber to rotate a first rotor. Wind exiting the first rotor passes through a diverter to produce laminar flow. A fan attached to the shaft intercepts this laminar flow to add additional torque to the shaft.

Abstract: A bypass-type motor protecting device includes: a casing fitted into a bypass opening in a body housing of a vacuum cleaner and having an inner abutment wall; a seat body having a bypass entry port; a valve body unit movable within the casing relative to the bypass entry port and including a valve disc to be engaged with and disengaged from the seat body, a plunger body having an externally accessible operated head and an axially extending threaded shank, and an abutment member threadedly engaged with the shank such that rotation of the operated head results in a change of an axial distance between the abutment member and the inner abutment wall; and a biasing member disposed to bias the abutment member and the inner abutment wall such that a biasing force thereof is varied in strength by the change of the axial distance.

Abstract: A turbocharger turbine containing a separate insert affixed within the housing. The insert is of a stamped metal configuration, and forms at least a portion of inlet passageway outer wall. An axial discontinuity is machined into the inlet passageway outer wall, the axial discontinuity being characterized by a size and location to direct airflow away from the blade-gap zone over at least part of the range of flow conditions. The inlet passageway may be either larger or smaller upstream of the axial discontinuity.

Abstract: A support frame includes a rail engaging a hook of a composite article having plys. The rail included a rail contact surface generally conformal to and contacting a hook contact surface of the hook. The rail and hook contact surfaces being substantially normal to the plys beneath the hook contact surface. One embodiment of the article is a composite nozzle segment including one or more airfoils extending radially between arcuate radially outer and inner band segments having plys curved about a centerline axis and the rail engages a hook of the radially inner band segment. The hook and the rail may be straight or arcuate. The frame includes a central body extending axially aftwardly from the rail to an aft frame flange. A frame pin may be mounted on the frame, engage the inner band segment or one of the airfoils, and may extend into a cavity in the airfoil.

Abstract: The present invention provides an axial flow fan capable of increasing an air volume and static pressure more than conventional axial flow fans. A plurality of rotary blades 5 are disposed in a circumferential direction of a rotary shaft 8 at equidistant intervals. A plurality of stationary blades 11 are disposed in the vicinity of a discharge opening 16 of an air channel portion 19 of a housing 3. The stationary blades are disposed in the circumferential direction of the rotary shaft 8 at equidistant intervals. The number of the rotary blades is seven (7) and the number of the stationary blades 11 is eight (8).

Abstract: A heated guide vane for turbomachinery includes a guide vane having two major surfaces joined about their periphery by edges and an electric heater element, wherein the electric heater element is secured to at least one major surface of the guide vane.

Abstract: A fan shroud with modular vane members for a cooling system. A plurality of modular vane set members are positioned around the inner surface of the fan shroud ring, each of the modular vane set members having a plurality of vane members. The modularity provides flexibility and versatility for the fan shroud and corresponding efficiencies in costs and manufacturing.

Abstract: The CWE Concepts are designed to extract the maximum possible wind energy passing through a given square footage area of influencing machine interface at given calculated velocities, to deliver that energy to two power take off shafts for end user's useful work (electrical power generation and other requirements). A multi-bucket “S” rotor, airfoils, baffles and cowling combined, utilize one hundred percent of that moving air volume most efficiently. Our strategies are to use smaller units, yielding more power than existing designs while being installed at much lower levels, urban friendly, less visible, nearly-enclosed rotating machinery, quieter, and safer for indigenous wildlife populations. We plan to market for commercial and residential customers, in turn providing HVAC and electrical power augmentation to utility companies—a reliable and robust addition to the national power grid. Our goals—reduce dependency on foreign oil and provide a clean alternative.

Abstract: On a two-shaft gas turbine, on at least one of an inner peripheral side or an outer peripheral side of a main flow passage, an outlet of a high-pressure turbine is lower than an inlet of a low-pressure turbine, an outer periphery of a flow channel that connects the outlet of the high-pressure turbine and the inlet of the low-pressure turbine includes a first casing shroud that is supported by a casing and located on an outer peripheral side of a final-stage rotor vane of the high-pressure turbine, and an initial-stage stator vane of the low-pressure turbine, and a connection position of the first casing shroud and the initial-stage stator vane of the low-pressure turbine is closer to the inlet of the initial-stage stator vane of the low-pressure turbine than the outlet of the final-stage rotor vane of the high-pressure turbine.

Abstract: A wind power generating system that is a technology for converting wind energy to electrical energy is provided. The system blocks flow of air inside the impeller, so that a high speed jet pressure on an I.G.V. (inlet guide vane) is converted to a constant pressure between the blades disposed downstream of the flow which has passed through the inlet guide vane, thus generating a large amount of torque.

Abstract: A guide vane, particularly for a turbocharger, has a line of curvature with at least one or more sectors having a discontinuous course.

Abstract: A wind turbine comprises an impeller and a turbine shroud disposed about the impeller. The impeller surrounds a center body having a central passageway through which air can flow through the center body to bypass the impeller. The impeller comprises a central ring and a plurality of impeller blades extending therefrom. When air passes through the impeller blades, some of its energy is used to turn the blades. The reduced-energy air is then mixed with the air flowing through the central passageway. This mixing allows the operating efficiency of the turbines to routinely exceed the Betz limit.

Abstract: A multistage radial compressor (1) with at least two compressor stages for compressing a fluid has a compressor housing (16) in which a flow channel (2) is formed for the fluid to be compressed; an impeller (4) with a plurality of impeller vanes (5) which are arranged in the flow channel (2) and are rotatable with the impeller (4) around a driveshaft (A), and a 3D return blading (8) with a plurality of return vanes (9) which are fixed with respect to rotation relative to the compressor housing (16). The flow channel (2) has a curved deflecting channel (7) which is arranged in front of the return vanes (9) in the flow direction. A vane base (11) and/or, axially downstream thereof, a vane head (12) of the return vanes (9) of the 3D return blading (8) have/has a curvature, and/or the return vanes (9) have a first vane angle distribution (17) at the vane base (11) and a second vane angle distribution (18) differing from this at the vane head (12).

Abstract: A two-stage high pressure turbine includes a second stage vane having an airfoil with 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: Blowing devices (100) have many uses; for example, they can be used to dry, cool, clean, or move objects. These functions are often performed by human beings with limited carrying capacity and endurance; therefore, a lightweight blower (100) is desired to perform the above tasks more easily. In accordance with the example uses, the present disclosure includes a lightweight blower (100) having an upper scroll (11), a lower scroll (10), and a joint (15) where the two scrolls (10, 11) are welded together to form a strong, lightweight joint (15).

Abstract: A wind turbine system includes a kite positioned upstream to a turbine to direct wind to the turbine, thereby increasing revolutions per minutes and power output of the turbine.

Abstract: The present invention relates to a vertical shaft aero-generator. An aero-generator has the advantage that it is not influenced by the wind direction, but the resistance in the reverse direction of rotation is a disadvantage thereof. For figuring out this disadvantage, a plurality of dimple panel wind guide apparatuses are mounted around the outer surface of a cylindrical vertical shaft windmill as well as on top and bottom thereof in order to maximally guide the wind coming from various directions including above and below to the rotational direction of the windmill, thereby the efficiency of the vertical shaft aero-generator is increased. The dimple panel wind guide apparatus includes a feature that a great number of dimples are formed on both entire lateral surfaces of the dimple panel so that the resistance may be minimized.

Abstract: A helical turbine configured to rotate transversely within a cylindrical pipe under the power of fluid flowing either direction therethrough is operatively coupled with a rotating machine or generator to produce work or electricity. The twisted blades of the turbine define a right circular cylinder when the shaft mounting them rotates under the influence of fluid flow through the pipe. In one embodiment, baffles are provided at least upstream of the cylindrical turbine and within the cylindrical pipe to control flow through the cylindrical turbine. The twisted blades of the helical turbine are airfoil in cross section, as are the radial struts or spokes that mount the twisted blades to the rotatable shaft, thereby to optimize hydrodynamic flow, to minimize cavitation, and to maximize conversion from axial to rotating energy.

Abstract: A nozzle assembly for a turbine including an airfoil, inner and outer sidewalls, and inner and outer rings is provided. The sidewalls and rings are coupled together using a weld and mechanical interconnection, including axial and radial mechanical stops to allow for an accurate assembly, to ensure correct radial and axial positions of the parts during welding, to minimize weld shrinkage and to control an axial weld length. The configuration may further include one or more surfaces at an interface between a ring and a sidewall angled away from the interface to form a narrow groove. The configuration further may include a ring with a consumable root portion to facilitate the weld, and to provide a fixturing stop to further ensure that the parts remain in the correct position.

Abstract: A nozzle box 10 includes: a lead-in pipe 20; a bent pipe 30 connected to the lead-in pipe 20 and formed so as to change a direction of a channel center line 50 to an axial direction of a turbine rotor 212; and an annular pipe 40 connected to the bent pipe 30 and leading steam to a first-stage nozzle 213a while spreading the steam in a circumferential direction of the turbine rotor 212. In the steam channel lead-in part structure 10, from an inlet of the lead-in pipe 20 toward an outlet of the annular pipe 40, steam channel widths Sa-1 to Sn-1 in a first direction intersecting with the channel center line 50 gradually increases and steam channel widths Sa-2 to Sn-2 in a second direction intersecting with the channel center line 50 and perpendicular to the first direction gradually decreases.

Abstract: A cooling apparatus for a motor vehicle with an internal combustion engine is provided that includes at least one heat exchanger through which air can pass, at least one axial fan that is located behind the at least one heat exchanger in a direction of air flow and has a circumferential ring with which ring is associated a stationary baffle ring, and a fan shroud adjoining the at least one heat exchanger. At least one motion compensating element with a sealing function is provided between the baffle ring and the at least one fan shroud.

Abstract: A blower fan includes a housing having a compartment. A stator and an impeller are mounted in the compartment. The housing further includes an air inlet and an air outlet both communicated with the compartment. The impeller has a hub and a plurality of vanes coupled to the hub. Each vane includes an upper edge whose end is an air input portion adjacent to the air inlet of the housing, and an air gap is formed between the upper edge of each vane and a top of the housing, with various widths of the air gap ranging from 0.3 mm to 2.0 mm, while a shortest width of the air gap is formed between the air input portion of the upper edge and the top of the housing for providing reduced turbulence and noises.

Abstract: A bladeless fan assembly includes a nozzle mounted on a base housing a motor and an impeller driven by the motor for creating an air flow. The nozzle includes an interior passage for receiving the air flow, a mouth for emitting the air flow, and a plurality of stationary guide vanes located within the interior passage and each for directing a portion of the air flow towards the mouth. The nozzle defines an opening through which air from outside the fan assembly is drawn by the air flow emitted from the mouth.

Abstract: The axial-flow turbine includes an extraction chamber 15 disposed on the outer circumference of a turbine blade chamber 12 and an extraction opening 16. An outer diaphragm 8 forming the downstream-side wall surface of the extraction chamber 15 is provided with a projection 21 formed more radially inwardly than the downstream-side edge on the outer circumference of an adjacent bucket 2 on the upstream side of the extraction opening 16 to form the downstream-side wall surface of the extraction opening 16. The projection 21 forms an upstream-side wall surface 18 of the outer diaphragm 8 for leading a part of the working fluid to the extraction chamber 15, and an inner wall surface 19 of the outer diaphragm 8 for leading the remaining working fluid to a bucket 11 on the downstream side of the extraction opening 16.

Abstract: A pump apparatus comprising a series of stacked impellers rotating about a common axis, for pumping a viscous fluid mixture upwardly from an underground location. The pump apparatus comprises a generally cylindrical housing having an intake at or near its suction end. A plurality of impellers are mounted in the housing to rotate about a shaft, which each induce flow of the mixture toward the discharge end of the pump. Each impeller has a series of radially outwardly extending vanes, one or more of such vanes having a radially-extending horizontal slot and arranged to generate an upwardly moving column of fluid. Without being limited to the theory of operation, the horizontal slot in the vanes assists in creating laminar flow and reducing turbulent flow.

Abstract: An inlet system, including for an auxiliary power unit includes an inlet louver mounted to an inlet duct, the inlet louver defines a multiple of vanes positioned to shield the inlet duct from fluids which fall in direction generally transverse to a free stream airflow.

Abstract: A nozzle assembly for a turbine that may include: (1) a nozzle-blade having inner and outer sidewalls and, in part, defining a flowpath upon assembly into the turbine; (2) an outer ring; (3) a flowsplitter having a horizontal extension; (4) an interface between the outer ring and the outer sidewall having at least one of (i) a male/female interface or (ii) a radial interlock; and (5) an interface between the horizontal extension and the inner sidewall having at least one of (i) the male/female interface or (ii) the radial interlock. In some embodiments, one of the interface between the outer ring and the outer sidewall and the interface between the horizontal extension and the inner sidewall comprises a weld and one of the interface between the outer ring and the outer sidewall and the interface between the horizontal extension and the inner sidewall is weld free.

Abstract: An energy conversion system for converting energy of naturally occurring fluid flow into output power. The energy conversion system includes an accelerator plate that has a leading edge and an upper surface that is substantially linearly inclined from the leading edge and transitions into a gradually increasing inclined shape so as to receive a fluid flow and form a vortex at a rear portion of the accelerator plate, a turbine positioned at the rear of the accelerator to rotate in the vortex created by the accelerator plate, and a deflector plate position down stream of the accelerator plate and adjacent the turbine. The cross-sectional shape of the accelerator plate has a duckbill shape which causes the fluid flow to increase up to five times and before turbulence is created and directs the increased air flow onto the blades of the turbine. The deflector plate can also have a duckbill cross-sectional shape.

Abstract: An energy conversion system for converting energy of naturally occurring fluid flow into output power. The energy conversion system includes an accelerator plate that has a leading edge and an upper surface that is substantially linearly inclined from the leading edge and transitions into a gradually increasing inclined shape so as to receive a fluid flow and form a vortex at a rear portion of the accelerator plate and a turbine positioned at the rear of the accelerator to rotate in the vortex created by the accelerator plate. The cross-sectional shape of the accelerator plate has a duckbill shape which causes the fluid flow to increase up to five times and before turbulence is created and directs the increased air flow onto the blades of the turbine.

Abstract: A fixed convergent collecting concentrator is provided. The concentrator contains two spaced-apart, co-axial, approximately horizontal, concentric plates with approximately circular shape centered on a vertical axis. The space between said plates is separated by vertical partition walls radially disposed about the axis thereof. The walls connect to the plates to form several sectors such that, irrespective of the direction of the wind, certain sectors collect and concentrate the air flow which enters the respective sectors. Each sector is connected to an intermediate tube which is in fluid communication with an accumulating tube, thus forming a system of tubes which is oriented in a common direction, optionally towards the ground. A turbine or other engine adapted for energy conversion being placed inside the concentrator or tubes.

Abstract: A power generation system that includes a heat source loop that supplies heat to a turbine loop. The heat can be waste heat from a steam turbine, industrial process or refrigeration or air-conditioning system, solar heat collectors or geothermal sources. The heat source loop may also include a heat storage medium to allow continuous operation even when the source of heat is intermittent. In the turbine loop a working fluid is boiled, injected into the turbine, recovered condensed and recycled. The power generation system further includes a heat reclaiming loop having a fluid that extracts heat from the turbine loop. The fluid of the heat claiming loop is then raised to a higher temperature and then placed in heat exchange relationship with the working fluid of the turbine loop. The turbine includes one or more blades mounted on a rotating member.

Abstract: A multiblade air blower has a multiblade impeller, a casing, an orifice, an axially overlaid portion, and an airflow collision prevention device. The multiblade impeller includes a main plate and a blade. The blade has a blade end face, and is provided at the main plate to form a blade inner periphery. The casing houses the multiblade impeller. The orifice has an open end and an orifice inner periphery. The open end is positioned toward the main plate from the blade end face. The orifice inner periphery has an inner diameter larger than that of the blade inner periphery, and guides air to the multiblade impeller. The axially overlaid portion is a part where the orifice and the blades are overlaid. The airflow collision prevention device is provided at the blade and at an inner side of the orifice inner periphery. With this structure, backflow of air and airflow disturbance at high air volume can be suppressed.

Abstract: A vane for use in a duct, such as an exhaust duct in a gas turbine engine, comprises a shear web arranged to extend substantially across the duct and to be fixedly attached to at least one wall thereof, and one or more vane plates removably mountable on the web. On each side of the web three retaining plates are secured to the web by bolts 18. A plurality of mounting brackets, are permanently fixed to the vane plates by riveting with countersunk-head rivets. Mounting brackets have tangs which are arranged for slidable engagement with the retaining plates in a direction opposite to arrow A. Thus, the vane plates may be slid along the web from a trailing edge of the vane to a leading edge, and back. Once the vane plates are in the required position on the web they may be secured against further sliding movement by a pair of limiting brackets, one on each side of the web.