Abstract: A centrifugal pump having a housing which includes an impeller mounted in the housing. At least one guide vane is mounted between a hub and the housing and in-line with the impeller. The guide vane has a leading guide. A recess is provided in proximity to the leading edge of the guide vane providing a connection between the spaces located on both sides of guide vane to prevent clogging of the impeller by fibrous components flowing in pump medium.

Abstract: The invention relates to the design of (particularly) a fixed blade in an axial flow steam turbine. A conventional blade is of prismatic form with an aerofoil cross-section and extends radially between annular end blocks. The inventive blade is curved in the radial (height) direction, being convex from root to tip on its pressure face. The setting angle relative to the corresponding prismatic blade is therefore fine at the root and tip and coarse at the blade mid-height. The throat opening is thus reduced at root and tip and increased at mid-height so displacing some mass flow away from both lossy end wall regions. A considerable gain in the stage efficiency results. A further improvement results from providing an optimum corner fillet between the blades and end walls at the root and tip.

Abstract: The invention is directed to a flow energizing system for turbomachinery including means for forming a plurality of rotating jet-sheet blades upstream of an impeller and a component for circumferentially varying the blade geometries of the plurality of rotating jet-sheet blades. The a component for forming a plurality of rotating jet-sheet blades includes: impeller shroud 26 having upstream-projecting axial extension 28 attached coaxially with and projecting upstream of shroud 26; recirculation chamber 30 surrounding shroud and axial extension, 26 and 28; recirculation flow inlet 32 formed by a gap between housing 12 and downstream ends, 20a and 26a, respectively, of impeller 20 and shroud 26, for allowing backflow to pressurize recirculation chamber 30; and a plurality of generally axially-extending jet-sheet slots 34 circumferentially distributed around a periphery of axial extension 28 and passing therethrough.

Abstract: An efficiency matching device and method. The efficiency matching device is utilized in combination with a centrifugal fan adapted to deliver an air mass flow through an air delivery system. The fan has a housing that defines an inlet port and an exit port. The fan additionally has an impeller disposed within the housing. The impeller draws air into the inlet port, accelerates the air, and discharges the air through the exit port. The efficiency matching device is shiftably carried within the exit port for selectively varying the area of the exit port such that the efficiency of the centrifugal fan can be varied to match the output efficiency of the fan to the desired air mass flow through the air delivery system.

Abstract: A shroud for the cooling fan of a motor vehicle engine provides a circumferential axial flow of air between the fan blade tips and the shroud to improve fan efficiency and engine cooling. The shroud may include a circumferentially extending Coanda surface and adjacent circular throat which directs air flow toward the annulus between the shroud and the fan blade tips. Adjustment of the air pressure and throat dimension allows accurate control of the velocity profile of the air flow through the annulus.

Abstract: To delay the onset of stall conditions at the tips of the blading an of axial-flow, mixed-flow and axial-centrifugal compressors, at the tips of the annular arrays of blading anti-stall tip treatment arrangement is provided at least at one of the arrays (2) comprising an annular cavity (3) communicating with the flow path through the compressor through slots (5) formed by an annular grid of ribs (4). The slots (5) provide communication between the cavity (3) and the flow path (7, 8) both upstream of and axially coincident with the array of blades (2). The ribs (4) are inclined relative to the radial direction at an angle (.phi..sub.r) of b 30.degree. to 50.degree.. The pitch (t) of the ribs and the slot width (.delta..sub.s) between the ribs are in the ratio of 1.5 to 2.0. The rib radial projection height (h) and the slot width are in the ratio of 1.1 to 1.8. The axial length (L) of the grating of ribs and the blade tip chord axial projection (b') of the array of blades (2) are in the ratio of 0.5 to 1.5.

Abstract: A radiator unit for an internal combustion engine of a vehicle is comprised of a radiator disposed in the vicinity of the engine. A fan shroud including stays is connected to the radiator and disposed between the radiator and the engine. A motor with a fan is installed to the stays so that the stays are located between the radiator and the fan. Therefore, the clearance between the radiator and the fan is increased without approaching the stays and the motor toward the engine to improve the heat transferring ability.

Abstract: A duct fixed to a vehicle propelled through an ambient fluid medium is innally provided with spaced channel passages from which the fluid medium is ejected under pressure tangentially of local duct surfaces through Coanda affected slots at the trailing edge of the duct from which only the ejection of the fluid medium occurs. The supply of the pressurized fluid medium under selective control is limited to different angular segments of the channel passages in order to modify the flow stream through the duct so as to perform certain functions such as thrust control and steerage control effects enhancing vehicle maneuverability.

Abstract: A method and device for collecting energy from wind includes an airfoil having an outer surface defining a leading edge, a central section of greatest breadth adjacent to which a Bernoulli effect reduced pressure region results as an air flow passes over the airfoil from the leading edge to a trailing edge, an air passage contained within the outer surface, and a plurality of edge nozzles penetrating the outer surface within the section of greatest breadth. The edge nozzles each have an outlet orifice oriented toward the trailing edge and an inlet orifice feeding into the air passage and being positioned to communicate between the air passage and the Bernoulli effect reduced pressure region. The airfoil is positioned in the wind with the leading edge facing substantially into the wind and with the wind passing over the edge nozzles. An airflow-driven turbine capable of converting an airflow into rotational mechanical energy is also provided, the turbine being in airflow communication with the air passage.

Abstract: A turbomachine having an impeller rotating within a casing of the machine and groove passages are formed in a wall of the casing between an upstream portion and a downstream portion of the impeller and high pressure fluid is injected into the groove passages for increasing the stall margin without lowering the peak efficiency of the machine and prevents generation of a positive slope in a head-capacity curve.

Abstract: An air moving device for improving P-Q characteristics and noise by suppressing the production of vortices. An annular wall spaced from blade tips, is formed of a plurality of annular plates and spacers with a slit defined between adjacent annular plates. The width of each slit is set to satisfy the formula W.ltoreq.(.nu..multidot.R.sub.ec /v) where .nu. is the kinematic viscosity of air, v is the peripheral speed of the blade tips, W is the width of the slits and R.sub.ec is the critical Reynold's number. Thus, as a fan is rotated, air is drawn in a laminar flow through the slits to the inner periphery of the annular wall. Thereby, it is possible to suppress the separation of air flow on the suction side of blade surfaces and the production of vortices, thus improving the air moving state.

Abstract: A cast and hot isostatically pressed gamma titanium aluminide turbine blade has an aerofoil portion including a concave pressure surface and a convex suction surface. The concave pressure surface has surface irregularities, produced by the action of the hot isostatic pressing process on voids located within the cast turbine blade, located in that region of the concave pressure surface where in operation aerodynamic separation occurs to minimise the aerodynamic effects of the surface irregularities upon the operation of the turbine blade. The remaining portion of the concave pressure surface and the whole of the convex suction surface are substantially free of surface irregularities.

Abstract: A diffuser apparatus for use in connection with gas turbines which will markedly increase the fuel efficiency of the turbine. The apparatus is specially designed for use with a gas turbine having both inner and outer walls on which a boundary layer develops and can become detached. The apparatus includes a strategically located capture scoop for capturing a portion of the high velocity gas stream of the gas turbine in the area of maximum velocity and redirecting it through a plurality of spaced-apart injector slots provided in both the inner and outer walls of a shroud which is positioned relative to the turbine in a manner to capture the high velocity gas stream generated by the blades of the turbine.

Abstract: A tip shroud assembly comprising a segmented annular shroud, each segment comprising a radially outer surface, and a radially inner surface including a plurality of first holes defining a first row and a plurality of second holes defining a second row, with each of the rows extending circumferentially along the length of the segment and the first row in spaced relation to the second row. Spaced radially outward from the radially inner surface is a circumferentially extending plenum, and a plurality of first passages extend from one of the first holes to the plenum, and a plurality of second passages extend from one of the second holes to said plenum. The plenum communicates with the radially inner surface through each of the first and second passages, and the length of each of the first passages is at least three times the diameter of the first hole from which it extends.

Abstract: A turbojet fan engine is disclosed having a fan or prop fan which blows air into a secondary channel and an external shroud for the turbine and the secondary channel, in which the front end of the shroud is formed with an inlet lip and the rear end of the shroud is formed in a nozzle-like, pointed manner and at least one end of the shroud is changed, with respect to its effective profile geometry, by means of air under pressure which is taken from the engine and blown out at the appropriate end of the shroud.

Abstract: The cantilevered stator vanes of the compressor section of the gas turbine engine are treated by including a rotating hub having a by-pass passage for removing the low momentum fluid from the main air stream adjacent to the tips of the stator vanes in the compressor and returning it back into the main air stream after having treated the air while avoiding penalties and excessive heating. A plurality of vanes are circumferentially spaced in the by-pass passage for removing vortices and streamlining the flow before injected the air back into the airstream. The vane passage hub treatment is fabricated in a single cast piece in one embodiment, in a three ring configuration in another embodiment and in a segmented ring configuration in still another embodiment.

Abstract: A turbulator for use with a fluid impelling device comprises a first side, a second side, and an apex toward which the first and second sides taper. The turbulator, circumferentially disposed about an inlet ring located adjacent the impelling device, is coaxially situated with an inlet passage of the inlet ring. The first side, second side, and apex define a triangular cross-section such that as laminar fluid flow from the second side moves over the apex of the turbulator, the laminar fluid flow is transitioned to a turbulent fluid flow on the first side prior to moving into the inlet passage. The turbulator also includes a plurality of evenly spaced slots for disrupting fluid flow symmetry within the inlet passage. The transition to turbulent flow and the disruption of fluid flow symmetry reduce acoustics as fluid is moved through the impelling device.

Abstract: A centrifugal pump (10) conveys a fluid from a rotor wheel inlet opening (8) via a rotor wheel outlet opening (9) into a pressure nozzle (4). The fluid has a velocity profile between the outer flow line (c) and the inner flow line (d). The method allows a fluid to be conveyed with a centrifugal pump (10) in such a manner that the velocity profile is continuously changed in dependence on the delivery flow (Q) which means that an abrupt change of the velocity profile when transferring from one load condition, e.g. at maximum efficiency, to another load condition, e.g. a partially loaded region, is avoided which results in a stable H/Q)-characteristic.

Abstract: The compressor section of an insert gas turbine engine contains a insert installed around the compressor blades that includes cells in a honeycomb configuration. Each cell is inclined at a compound angle to the blade tip to energize the tip air flow as the tip passes over the cell as the blade rotates, improving stall margin with minimum efficiency loss. Each cell is oriented in the direction of the blade chord and faces the advancing blades. As the blade rotates, it sweeps by each cell and high pressure airflow is first captured in the cell from the high pressure side of the blade and released to the low pressure side as the blade passes the cell in the form of a transient energizing jet of high velocity flow in the direction of the airflow across the blade thereby providing effective mixing of the endwall flows and enhancing the tip flow streamwise momentum.

Abstract: An axial flow compressor is disclosed. The axial flow compressor has a casing defining a compression passage therein. The casing has an inner surface and a center axis extending along the elongated direction of the casing. A plurality of rotor blades fixed to a disk rotate in the compression passage around the center axis. Each of the rotor blades has a tip, and the tip defines a rotation area having a width extending in the direction along the center axis. A circular concavity is formed on the inner surface of the casing extending completely around the inner surface. The circular concavity has a continuous curved shape in a sectional view, and the circular concavity is formed at a portion corresponding to a front part of the rotation area of the rotor blades.

Abstract: The invention provides a regulating system (23) for controlling the heating of the gases on the downstream side of the regulating system, attenuating the aerodynamic noise produced by the gyratory flow on the downstream side of the directing vanes (24) of the regulating system and facilitating the endoscopic inspection of the blades and vanes of a compressor (3) owing to the provision of a throughway passage (27) in the regulating system (23), and in particular a throughway opening in at least one directing vane (24).

Abstract: A tip shroud assembly comprising a segmented annular shroud, each segment comprising first, second and third arcuate members and a plurality of vane walls integral with the first second and third members, and each arcuate member has a radially inner surface, and the third arcuate member is in spaced relation to the first and second members, and each vane wall spans between the radially inner surface of the third arcuate member and the radially inner surfaces of the first and second members.

Abstract: A gas turbine engine turbine is provided with an annular array of nozzle guide vanes which define a radially inner annular platform. The radially outer surface of the platform is configured so as to define a plurality of convex and concave portions. These portions are so arranged as to vary the static pressure of the gases which operationally flow across the vanes in such a manner that the static pressure in the field immediately downstream of the vanes is substantially circumferentially uniform.

Abstract: Outer and inner endwall sections are so profiled that, essentially, the flowpath is straight or flat in the direction of flow. The profiles are defined by lines of revolution about a centerline of a turbine, and shaped as projections upstream from blade tips or bases, tangent to such blade tips or bases, axially, and radially, conforming to a mean obtaining between convex and concave surfaces of the nozzle.

Abstract: In a compressor, the stabilization device for extending the characteristic map consists of a co-rotating ring (2) rigidly connected to the runner blades (1), there being arranged between the ring (2) and the housing (3) of the compressor a recirculation duct (4) which has an opening to the impeller (5) at its rear end in the flow direction, only the previously customary narrow clearance existing subsequently at the rear end of this opening between impeller (5) and wall of the housing. The front edge of the ring (2) in the flow direction can terminate flush with the inlet edges of the runner blades (1), or be axially displaced.

Abstract: A flow directing assembly 24, 24a for a rotary machine 10 is disclosed. Various construction details are developed to decrease aerodynamic losses and promote the ease of design. In one particular embodiment, a concave region 58 of an end wall is employed to create convex wall regions 54, 56 upstream and downstream of the concave region.

Abstract: A cowl comprising, inter alia, a stationary part formed by a diffuser (10) which exhibits a fastening base (11), a nozzle-funnel (12), a connection zone (13), a cylindrical skirt (14), and a moving part (20) able to rotate about an axis (200), which moving part (21) exhibits a peripheral profiled annular hoop (20) which is intended to be rigidly connected to the blade (22) tips (221) of a helix and which is mounted coaxially in this skirt (14) so as to be able to rotate therein, is characterised in that, taking as references the direction of flow and the axis (200), this hoop (21) is delimited by an inner wall (2101), an outer wall (2102) and a rear section (2103), this connection zone (13) is delimited in particular by an inner surface (131) with an upstream limit (1310), and in that this rear section (2103) of the hoop (21) is situated in a plane (P) which is perpendicular to the axis (200) and which passes practically through the upstream limit (1310) of the inner surface (131) of the connection zone (13).

Abstract: As a device for stabilizing the performance characteristics, a radial compressor comprises a circulation chamber (31) which makes pressure equalization between the impeller and the intake region possible. The intake region has an intake ring (10) which makes it possible to influence the flow in the intake region so that the performance characteristics be stabilized without substantial losses. The compressor may be adapted to customer's requirements by changing the intake ring.

Abstract: To enhance stall margin without degrading engine performance the case of the fan of a fan-jet engine is treated by incorporating a passageway to remove flow from the main flow stream. The location and amount of the low momentum flow relative to the rotor being removed is critical. The flow is removed at a judicious location downstream of the leading edge of the rotor blade and returned at a judicious location upstream of the point of removal. The amount of removed flow must be no greater than 8% of the total flow in the fan rotor. Anti-swirl vanes in the passageway and discreetly sized inlet and outlet passages of the passageway return the flow to the main stream at an increased velocity. The intake is so designed that it selectively removes only the weak low momentum flow relative to the rotor and encourages the strong mainstream flow to remain in the main gas stream.

Abstract: A compressor assembly includes a housing, and a rotatable impeller within the housing which includes a hub and blades extending from the hub. A ring circumscribes the leading edge of the blades, and cooperates with a groove in the housing to define a clearance therebetween which is larger than the clearance between the connecting edge of the blades and a corresponding conforming portion of the housing. This permits free flow of gas around the ring to enhance the operating range of the compressor wheel. The ring also stiffens the blades, permitting the thickness of the hub to be reduced, thereby further enhancing the operating range of the compressor wheel.

Abstract: Rotating stall in an axial-flow compressor is suppressed by the positioning of a fixed inlet flow divider in the annular inlet flow passage upstream of the compressor. The inlet flow divider is aligned with the flow of fluid through the duct and acts to block or interfere with any rotating wave in the inlet and thereby suppresses rotating stall in the compressor.

Abstract: The present invention is directed to a method and apparatus for improving the flow range in centrifugal pumps and compressors. Bleed holes are introduced into a volute tongue of a centrifugal pump or compressor thereby providing a double acting means of boundary layer control at the volute tongue.

Abstract: The outer shroud of an axial flow compressor is treated to remove the low momentum flow adjacent the tips of the compressor blades in a judiciously located and sized passageway that removes the low momentum flow relative to the rotor blades at a location downstream of the blades' leading edge and returned at a location upstream of the point of removal. It being critical that no more than 12% of the total flow in the compressor rotor is removed for treatment. Anti-swirl vanes in the passageway serve to remove or reverse the swirl component from the removed low momentum flow. The intake is so designed that it selectively removes only the weak low momentum flow relative to the rotor and encourages the strong mainstream flow to remain in the main gas stream.

Abstract: A centrifugal compressor impeller for gas turbine engines designed to efficiently operate at both part-speed and full speed design points includes slanted vanes in a secondary air inlet to the impeller. The vanes are tangentially slanted in the direction of rotation of the impeller to preferentially augment airflow into the impeller at maximum speed, while at part-speed discouraging airflow out of its impeller through the secondary inlet.

Abstract: An axial flow transonic turbofan jet engine includes a hub (26) from which radiate a plurality of rotor blades (50). A casing (12) surrounds and shrouds the rotor blades (50). Part-span dampers (56) are located between adjacent rotor blades (50) in an annular pattern to stiffen the elongated rotor blades (50) during operation. The distal tips (54) of the rotor blades (50) are convexed and spin within a rub strip (62) embedded within the casing (12). The rub strip (62) includes an annularly troughed contour (60) to closely conform with the convex tips (54) of the rotor blades (50). The hub (26) may also include an annularly troughed contour (60) formed along the roots (52) of the rotor blades (50). The annularly troughed contours (60) in the hub (26) and in the casing (12) are radially aligned with the part-span dampers (56) to reduce drag between the casing (12) and the hub (26) caused by the part-span dampers (56) at transonic speeds.

Abstract: A water turbine is shown having a water transition member in the form of a partial cone which is positioned on the downstream side of the turbine runner. The cone is mounted independently of rotation of the turbine member and may be rotated by a motor. The partial cone may have ridges or blades which may be retractable.

Abstract: In a device for reducing resonant vibrations of rotor blades in turbomachines, cavities for the selective disturbance of the flow are arranged between the rotating blade tip and that wall of the casing which bounds the flow duct. These cavities are arranged in the casing wall in the region of the blade tips and comprise a plurality of cavities arranged over the circumference. Their open cross section facing the flow duct is arranged in the axial planes bounded by the inlet edges and outlet edges of the rotor blades.

Abstract: A variable pitch propeller mechanism includes a plurality of airfoil-shaped blades on three spaced apart blade arms. The airfoil-shaped blades are pivotally connected to the blade arms and are interconnected to each other by rigid connecting rods so these blades move in unison in response to changing wind conditions. Air flow across the airfoil-shaped blades is also controlled to improve the efficiency of the device.

Abstract: The profiled annular hoop for a fan helix blade tip exhibits a curved inlet collar whose convexity is directed towards the axis (100), and is characterized in that this collar (11) has a given axial length (l) and a meridian section (110) shaped approximately as a quarter ellipse whose eccentricity is of the order of 1.5 and whose major half-axis (a) lies between approximately one third and one half of this given axial length (l).Application to cooling motorized fans of vehicle radiators.

Abstract: A compressor casing defines an air inlet port, an air intake passage with an impeller accommodated therein, a diffuser and a scroll all communicated with each other in the order named. An annually extending chamber is formed between the passage and the scroll and has an opening opened sideways of the impeller in the passage, enhancing an ability of discharging a surging-occuring range to a lower flow rage. The compressor casing may be divided into a casing main body and an inner casing so as to decrease fabrication cost of the compressor casing.

Abstract: A blade array for turbomachines comprises blades disposed between an inner wall and an outer wall. The inner wall and/or the outer wall is provided with a suction port near at least some blades. This port has a first end situated along the upper surface in a region of the blade extending from the point of maximum curvature to the neck of the passage between said blade and the adjacent blade. The port enabling the efficiency to be increased is oriented along an isobar line. Its length is such that the second end is spaced from the upper surface of the blade by a distance between one quarter and one half the width of the neck of the inter-blade passage.

Abstract: An axial-flow blower of stator vane controllable pitch type has an upstream-side opening of an air separator on the upstream side of a controllable pitch type inlet guide vane so that the recirculating flow in the air separator can be joined smoothly with the axial main flow irrespective of the set angle of controllable pitch angle.

Abstract: In a turbomachine blade/vane for subsonic conditions with a convex curvature profile contour in the region of the leading edge and over the major part of the suction surface (S) and with a concave curvature profile contour in the region of the pressure surface (D), the profile contour in the suction-surface trailing edge region is designed to be concave (K). The momentum loss thickness mainly responsible for the profile loss is reduced in this region.

Abstract: A centrifugal pump has a casing which accommodates an impeller for conveying abrasive fluid in a predetermined flow direction. The casing has a peripheral wall which is provided with an outlet opening for the fluid. The upstream side and downstream side of the opening are flanked by wear elements which extend transversely of the flow direction and project into the interior of the casing.

Abstract: A cooling air pick up for use in a gas turbine engine includes a cooling air duct incorporating a diffuser to maximize the cooling air pressure. The entry orifice of the pick up duct is formed in the leading edge of a flow vane in the interior of a flow passage downstream of the engine compressor section.

Abstract: A steam turbine stationary blade diaphragm consisting of steam turbine blades with inner and outer rings which are integral with the blades to form a diaphragm structure of a particular design that avoids steam separation by selection of the blade parameters so as to cause a substantially continuous velocity increase over the major extent of the suction surface of the blade.

Abstract: A centrifugal impeller includes a hub formed about an axis of rotation with a plurality of substantially radially extending blades affixed to the hub, each blade having a suction surface, and a pressure surface formed on the adjacent blade facing the suction surface. The blades have a height being measured in a radial direction from the hub. A portion of the hub, having a hub configuration, extends between the pressure surface and the suction surface. An imaginary plane extending in a direction normal to the axis of rotation is used to define a cross-sectional view of the impeller. A first and a second concentric circle are formed in the plane with the center of the concentric circles being the axis of rotation. The first circle passes through a point on the hub located closest to the axis of rotation. The second circle has a radius greater than the first circle by an amount equal to five percent of the blade height, wherein a portion of the hub extends outside of the second circle.

Abstract: An axial fan has an impeller provided with vanes and mounted in a flow duct. In or on the wall of the duct at least one port is arranged adjacent to the vane tips. The duct side the port is provided with a covering means having passages therethrough.

Abstract: A housing for a propeller or axial flow fan. The housing comprises an orifice portion, a stator element portion and a motor mount portion, preferably made in a single piece by casting in metal. The single piece construction makes possible the positioning of the axis of rotation of the fan to be used with the housing precisely coincident with the axis of the orifice and thus permits very small fan blade tip to orifice wall clearances to be attained, increasing the efficiency of the fan assembly and reducing its radiated noise. The inlet of the orifice is elliptical to promote attached flow. In a preferred embodiment, the motor mount portion of the housing also is configured to serve as the motor shaft end cap of the electric motor used to drive the fan. The number of parts in a complete fan, housing and motor unit in such a configuration is reduced to two, the fan and the motor, reducing the time required to assemble and install the unit.

Abstract: A method and system for diverting leakage air back into the flow path of a turbine engine. A stator vane assembly is connected to a shroud assembly at the radially inner end of the stator vane assembly, the shroud assembly is provided with a scoop which is placed in the path of leakage air traversing in a forward direction from the high pressure static side of the stator vane to the low static pressure side of the stator vane. The leakage path is located between the stator vane assembly and a rotating member. The scoop intercepts the leakage air and re-directs the leakage air into an airflow path of the turbine engine with an aftward component of velocity.