Abstract: To provide a jet engine booster structure capable of obtaining a desired pressure ratio with fewer stages. The moving blade of a booster is a boundary layer control tandem moving blade.

Abstract: A streamlined body has oppositely facing external pressure and suction surfaces that meet to form a leading edge region. Passageways within the body direct pressurized fluid from passageway outlets over the pressure surface toward the leading edge region at a shallow angle with respect to the pressure surface. The pressurized fluid travels around the leading edge region to the suction surface, energizing the boundary layer on the suction surface.

Abstract: The present invention provides a blower that improves the P-Q characteristic and reduces noise. The apparatus is a blower that sucks air inside through slits (6) provided in an annular wall (2), wherein the blade thickness near a blade end s is progressively reduced toward the front end, and the location F of the maximum thickness gradually moves back toward a blade trailing edge side u2 so as to make the blade advance angle near the front end larger than in other locations. In addition, the width of a slit is made wider in sections near a spacer than in other sections. Alternatively, notches are provided in the outer perimeter of annular plates near the spacers so as to reduce the radial length of the annular plates. This arrangement improves the P-Q characteristic and reduces noise.

Abstract: The end wall of the compressor adjacent the stator vanes and compressor blades is configured so that the annular region between the vanes and blades is held at a constant area and that the flow path convergence of the stator is increased to compensate for the loss of convergence due to the reduction of convergence in the annular region between vanes and blades.

Abstract: An aerofoil (22,24), preferably of a high lift, highly loaded design, for an axial flow turbo machine (10). The aerofoil having a span, a leading edge (LE), a trailing edge (TE) and a cambered sectional profile comprising a pressure surface (30,72) and a suction surface (28,70) extending between the leading edge (LE) and trailing edge (TE). The aerofoil (22,24) having at least one aerofoil cross bleed passage (36,37,78,80) defined in the aerofoil (22,24) which extends from the pressure surface (30,72) through the aerofoil (22,24) to the suction surface (28,70). The at least one passage (36,37,78,80) preferably disposed generally at a location on the suction surface (28,70) at which boundary layer separation from the suction surface (28,70) would normally occur.

Abstract: An air moving device in the form of an axial flow fan is provided that is adapted for use in substantially enclosed high-density electrical systems, e.g. computers and the like. The fan includes an annular wall extending about the blades thereof and in which pressure equalizing openings are formed for increasing the maximum pressure in the preferred operating area of the fan and just before the stall effect occurs due to increasing system pressure resistance. A method is also provided for optimizing the number and size of the slots to obtain a desired maximum pressure increase. The slots are optimized so that there is no appreciable airflow loss in early stages of the preferred operating area while providing the desired increase in maximum pressure. The slots preferably have an elongated shape, e.g. rectangular or oval, with a major dimension extending generally axially and parallel to the axis of rotation of the blades, and are spaced from each other circumferentially about the annular wall.

Abstract: For improving characteristic uprising at the right-hand side of head-flow rate characteristic of a turbo machine, as well as for suppressing increase of vibration and/or noises thereof, a plurality of first grooves 24 in direction of gradient in pressure of fluid are formed on an inner flow surface of a casing, for connecting an inlet side of blades of an impeller and an area on the inner flow surface of the casing where the impeller blades reside in, over an inner circumference of the casing. Also, second grooves 25 in a circumferential direction are formed in an area on the inner flow surface of the casing where the impeller blades reside in, for communicating the first grooves in the circumferential direction of the casing.

Abstract: An axial flow turbomachine has at least one circumferential row of aerofoil members in which at least one of the two end walls (33) between successive blades (30) is given a non-axisymmetric profile to modify the boundary layer flow at the wall. In one form of the profile, a convex region (33) adjacent each member pressure surface (35) and a complementary concave region (34) adjacent each member suction surface (34) extend over at least a major part of the blade chord lengths to reduce the transverse pressure gradient and thereby reduce vortical energy losses. In another form of the profile, at least one end wall (33) has complementary convex and concave regions (50,51) extending through the zone of the trailing edges of the members (30) on the suction end pressure surface sides (34,35) respectively of each member, thereby to reduce over turning of the flow. Both forms of profiling can be employed in combination.

Abstract: A gas turbine engine variable vane having a winglet integrally formed therewith. In one embodiment, the variable vane includes a winglet attached to one end so as to reduce endwall losses resulting from air leakage from the high-pressure side to the low-pressure side of the airfoil. The winglet substantially increases the width of the endwall gap thereby reducing the loss associated with the vortex flow caused by leakage of gas from the pressure side to the section side of the airfoil. In another aspect the winglet runs along the airfoil thereby increasing stiffness and acting as a bracing strut to increase the resonant frequency of the airfoil.

Abstract: A fan system, such as a turbofan, marine propeller, or a cooling fan, includes a fan noise control system for reducing noise generated by the fan system. The noise control system may be configured to reduce either broadband noise, blade-passage noise, or both. In particular, the fan noise control system suitably includes a pre-swirl generator configured to provide a layer of fluid upstream from the fan blades. The layer swirls in the direction of the fan's rotation, reducing the angular velocity differential between the fan blades and the incident fluid. In addition, the fan noise control system may also include a fluid seal generator configured to create a fluid barrier between the fan blade tips and the interior surface of the fluid flow channel. The fluid seal inhibits leakage flow between the fan blade tips and the interior surface as well as the formation of blade vortices. By minimizing the blade wake and the blade tip vortices without adding solid surfaces, noise tends to diminish.

Abstract: A compressor casing is configured to surround blade tips in a compressor stage. The casing includes stall grooves with adjoining lands defining respective local gaps with the blade tips. At least one of the lands is offset to locally increase a corresponding one of the gaps larger than the nominal gap for the casing to reduce tip rubbing thereat.

Abstract: An axial flow or centrifugal flow compressor having arrays of blades (16) extending across a working medium flowpath (18) includes a casing treatment for enhancing the compressor's fluid dynamic stability. In one variant of the invention the casing treatment comprises one or more circumferentially extending grooves (40) that each receive indigenous fluid from the compressor flowpath at a fluid extraction site (56) and discharge indigenous fluid into the flowpath at a fluid injection site (58), circumferentially offset from the extraction site, where the migrated fluid is better able to advance against an adverse pressure gradient in the flowpath. Each groove is oriented so that the discharged fluid enters the flowpath with a streamwise directional component that promotes efficient and reliable integration of the introduced fluid into the flowpath fluid stream (20).

Abstract: A turbine casing supports a row of nozzle vanes through which are flowable hot combustion gases. A baffle surrounds the casing to define a cooling duct. A nacelle surrounds the turbine casing to define a bay having an inlet for receiving bay air, and an outlet for discharging the air. The cooling duct includes an inlet which receives the bay air for flow along the turbine casing for selective cooling thereof.

Abstract: An apparatus comprises a longitudinally extending housing having a fluid inlet port and a fluid outlet port; a plurality of spaced apart members rotatably mounted in the housing to transmit motive force between fluid introduced through the fluid inlet port and the members; each member having a pair of smooth opposed surfaces, each surface having an inner portion and an outer portion; and, at least one of the members having a width that is increased at at least one discrete location to alter the fluid flow over the surface of that member.

Abstract: The invention relates to a steam turbine (1) which has a flow duct (2) with a wall (3). Blading (5) is arranged in blading rings (55) in the flow duct (2). The wall (3) of the flow duct (2) has a grooved structure (6) which purposefully influences the flow of an active fluid (13) through the flow duct (2). In particular, a spacing surface (31) with a grooved structure (6) is located between each two blades or vanes (5) of a blading ring (55). The invention also relates to a blade or vane for a steam turbine.

Abstract: Blades, including helicopter rotor blades, gas turbine engine fan blades, air moving machinery fan blades, and the like, have an air inlet near the hub of the blade, which may be on the pressure side of the blade and/or near the leading edge or trailing edge nearer the tip of the blades, with an air plenum between the air inlet and the slots, whereby air is forced into the inlet, through the plenum and out of the slots into the flow adjacent the blades. The slots may be through the suction surface of the blade, typically near the boundary layer separation point, so that air flowing out of the slots into the boundary layer of the suction surface of the blade, thereby delay or prevent the onset of boundary layer separation, or to reduce supersonic shock. The inlet may be near the trailing edge of the blade, near the root, adjacent to the air inlet of the core of a jet engine, to suction off air and reduce fan wake blockage at the core inlet.

Abstract: A wave augmented diffuser for a centrifugal compressor surrounds the outlet of an impeller that rotates on a drive shaft having an axis of rotation. The impeller brings flow in in an axial direction and imparts kinetic energy to the flow discharging it in radial and tangential directions. The flow is discharged into a plurality of circumferentially disposed wave chambers. The wave chambers are periodically opened and closed by a rotary valve such that the flow through the diffuser is unsteady. The valve includes a plurality of valve openings that are periodically brought into and out of fluid communication with the wave chambers. When the wave chambers are closed, a reflected compression wave moves upstream towards the diffuser bringing the flow into the wave chamber to rest. This action recovers the kinetic energy from the flow and limits any boundary layer growth. The flow is then discharged in an axial direction through an opening in the valve plate when the valve plate is rotated to an open position.

Abstract: An MWE compressor comprising a housing defining an inlet and an outlet, and an impeller wheel rotatably mounted in the housing such that on rotation of the wheel gas within the inlet is moved to the outlet. The housing has an inner wall defining a surface located in close proximity to radially outer edges of vanes supported by the wheel. The inlet is defined by a first tubular portion an inner surface of which is an extension of the said surface of the inner wall of the housing, a second tubular portion located radially outside the first portion to define an annular passage between the first and second portions, a wall extending across the annular passage between the first and second portions, and a conical wall located upstream of the first portion and extending in the radially outwards and upstream directions from adjacent the upstream end of the first portion to the upstream end of the second portion.

Abstract: In a blower in which air is sucked to the inside through slits formed in an annular wall, the width w and the number of slits are so set that an air flow of 20 to 40% of the maximum air flow is sucked through the slits in a state in which the static pressure is zero. By this configuration, the fan stall inhibiting effect due to the air flow through the slits and the energy loss due to the viscosity of air yielded in the slits are balanced, whereby the efficiency of the blower can be improved.

Abstract: A structure and a method to form the structure are provided for an impeller bleed passage of a compressor for a gas turbine engine. The compressor has an impeller assembly which includes an impeller rotor rotatably supported within an annular shroud having an inlet and an outlet. The shroud is made of two separate annular segments which are axially spaced apart. Each of the segments is supported separately and independently in a cantilevered manner. Such that a circumferentially continuous, uninterrupted annular slot is formed between the two segments and air passes through the slot without causing a dynamic component to affect the impeller rotor. The width of the slot is adjustable for different engines depending on the requirements of use of a particular engine. The width of the slot is also self-regulating in response to changes in the air pressure within the shroud because of the deformation of the segments. The structure is relatively simple and inexpensive to manufacture.

Abstract: An airfoil with a reduced heat load for use in either a turbine or a compressor of a gas turbine engine comprises having at least one heat reducing dimple on the body of the airfoil or on the associated endwall of the airfoil. The body of the airfoil is comprised of a leading edge, a trailing edge, a pressure side and a suction side. The length of the heat reducing dimple in the expected direction of hot gas stream flow is at least equal to or greater than the width transverse to such direction. The heat reducing dimple is located on the airfoil or endwall so as to reduce the heat load as the hot gas stream flow passes from the leading edge to the trailing edge.

Abstract: A blower comprising an annular wall (2) formed to be spaced from blade tips of a fan (1), the annular wall having slits (6) formed at a portion opposed to the blade tips to establish communication between inner and outer peripheral portions of the annular wall, so that air is sucked into the inner peripheral portion of the annular wall through the slits as the fan rotates, characterized in that the width w of a gap of the slit is changed in radial and circumferential directions thereof, whereby the quantity of air flowing into the inner peripheral portion of the annular wall through the slits is made substantially equal over the entire circumference. By this configuration, leakage vortexes flowing from the pressure side to the suction side at the blade tips are restrained, and the P-Q characteristics are improved. At the same time, noise produced in the annular wall having slits can be restrained, so that a low-noise blower can be realized.

Abstract: Structure with elements includes a main body of the element used in gas stream and a plurality of fluid passage. Each outlet of the fluid passage is opened on surface of the main body. Coolant fluid flows from each outlet through the passage to cover the surface as a film-like fluid. The plurality of fluid passages include first fluid passages and second fluid passages. The coolant fluid flows from the outlet of the first fluid passage along the direction of the gas stream on the surface. On the other hand, the coolant fluid also flows from the outlet of the second fluid passage toward the gas stream neighbored on each outlet of the first fluid passage.

Abstract: A compressor for a gas turbine engine, comprising a casing having an inner surface defining a plurality of circumferentially spaced-apart grooves adjacent the tips of a row of rotor blades. Each groove as a depth which is less than half the width thereof in order to increase surge margin at off design points without affecting the performance of the compressor under normal operating conditions.

Abstract: When a turbine engine is operated near the ground, for example on a stationary static test stand, the ground effect as well as excessive lateral wind effects can lead to instabilities and unacceptable flow conditions of the air flow entering the air intake of the engine. A method for stabilizing or preventing such instabilities in the engine intake air flow involves preventing the generation or full development of a spiral vortex extending between the ground and the engine air intake. Specifically, by positively introducing air into the vortex core of any spiral vortex being formed, the vortex is destroyed and full development of the vortex is prevented. An apparatus for carrying out the method includes an air permeable element arranged between the ground and the engine air intake, such that a flow of air is provided through the air permeable element into the core of any spiral vortex being formed on the surface of the air permeable element.

Abstract: The removal of cooling air from the diffuser part of a radial end stage of a compressor of a gas turbine is provided. Compressed air is removed via a cooling air discharge (10) from a radial compressor stage, which comprises a rotor disk (2) and a bladed diffuser (20). The removal of cooling air may be brought about such that the cooling air is removed on one side through openings (6) on the housing side (20.1) of the diffuser (20) and is fed through cooling air channels (10) to the parts in contact with hot gas, including the outer wall of the bifurcated tube (17). The compressed air is guided to the diffuser outside (20.2) through cooling air holes (19) in the diffuser blade (3).

Abstract: A turbine shroud includes a panel having inner and outer surfaces extending between forward and aft opposite ends. The panel includes forward and aft hooks for supporting the panel radially atop a row of turbine rotor blades. The panel includes a plurality of recesses in the inner surface thereof which face tips of the blades. The recesses extend only in part into the panel for reducing surface area exposed to the blade tips.

Abstract: A centrifugal blower assembly for a heat exchanger system of an automotive vehicle is described. The centrifugal blower assembly includes a diffuser section interposed between the centrifugal blower housing and a heat exchanger housing in the heat exchanger system. The diffuser section has a pair of non-linear, curved side walls which allow for expansion of the air flowing therethrough to minimize air flow separation against the side walls of the diffuser.

Abstract: An unshrouded turbine rotor blade 24 for use particularly in gas turbine engines comprising an aerofoil 30 having a leading edge 32 and a trailing edge 34. The radially outer extremity of the aerofoil 30 having a passage 42 defined by a peripheral wall 44. An aperture is formed within the wall 44 in the proximity of the trailing edge 32 of the aerofoil portion 30. The walled passage 42 is provided to capture and retain air or gas flowing over the tip of the aerofoil 30 and redirect the flow through the aperture 46 at the trailing edge of the aerofoil 30.

Abstract: A turbine blade having an extensible tail is described. The extensible tail is selectively positionable during engine operation, enabling fine-tuning for maximum power and efficiency during engine operation. During periods of operation exhibiting low Reynolds number flows, the extensible tail is projected out from the trailing edge of the turbine blade, into the gas path. As Reynolds number flows increase, the extensible tail is retracted back into the turbine blade, maximizing turbine engine efficiency.

Abstract: A stator assembly for a fan has a passage member which defines a passage for air flow due to the fan, a fan mount for the fan and at least one support arm extending between the passage member and the fan mount. A plurality of air flow directing members extend between the passage member and the fan mount. The passage member is preferably ring shaped and the fan mount is concentric with the ring. The air flow directing members may be straight, or skewed with respect to the direction of rotation of the fan. Different forms of the air flow directing members are described.

Abstract: A heat transfer structure for the efficient cooling of a heated surface such as the combustor wall of a gas turbine has a high heat transfer coefficient and can therefore operate at a relatively low pressure loss. A cooling jacket is formed around the heated surface by means of an apertured wall parallel to and spaced from the heated surface. Cooling fluid such as air flows into the cooling jacket through the apertures and impinges as air jets on the heated surface. The heat transfer coefficient is greatly increased by flow diversion features associated with the apertures which act as Coanda surfaces to divert the air jets so that they impinge obliquely and turbulently on the heated surface and establish subsequent turbulent sinuous cross-flows of the cooling air on the heated surface.

Abstract: A tandem blade lattice having characteristics enhanced is provided. In a high pressure ratio blade lattice, inevitable generation of an shock wave is shifted, as much as possible, toward a rear portion of an upper surface of a front blade to inhibit separation from a blade surface from being caused by interference of the shock wave and a boundary layer, and boundary layer control is performed such that a speed, a momentum and the like of a jet flowing from a trailing edge of a lower surface of the front blade onto an upper surface of a rear blade are regulated to obtain a flow along the upper surface of the rear blade, so that separation of the boundary layer on the upper surface of the rear blade is restricted to a vicinity of a trailing edge.

Abstract: Structure with elements includes a main body of the element used in gas stream and a plurality of fluid passage. Each outlet of the fluid passage is opened on surface of the main body. Coolant fluid flows from each outlet through the passage to cover the surface as a film-like fluid. The plurality of fluid passages include first fluid passages and second fluid passages. The coolant fluid flows from the outlet of the first fluid passage along the direction of the gas stream on the surface. On the other hand, the coolant fluid also flows from the outlet of the second fluid passage toward the gas stream neighbored on each outlet of the first fluid passage.

Abstract: A blade for an axial fluid machine comprises an effective blade portion having a root portion and a tip portion and projecting blade portions. The projecting blade portions are defined by axis reference lines extending to an upstream side with respect to a fluid flow from at least one of the root portion and the tip portion of the effective blade portion and by axes obliquely extending from ends of the axis reference lines toward a leading edge of the effective blade portion. The projecting blade portions are formed continuously to and integrally with the leading edge of the effective blade portion so that the effective blade portion and the projecting blade portions have substantially the same maximum blade thickness.

Abstract: A deflector for redirecting cooling air leakage to improve the efficiency of a gas turbine engine rotors. Adjacent rotor blades have a radially extending gap between each adjacent rotor blade and cooling air leaks into the gaps resulting in engine inefficiency. A deflector, disposed circumferentially on a forward face of the coverplate, deflects cooling air leakage, flowing from the running seal through the cooling air leakage path, away from the gaps between the blades, onto the outward surface of the blade platform, and into the gaspath at an acute angle relative to rearwardly axial flow. A forwardly extending flange deflects cooling air leakage forwardly around the blade platform lip.

Abstract: An optimum axial distance is secured by varying the distance between a nozzle blade and a moving blade along the length of a nozzle blade (11). The nozzle blades (11) are curved so that a middle portion of each nozzle blade has a section (b2) dislocated in the flowing direction of a fluid which flows through the fluid passage relative to the root section (b3) and the tip section (b1) of the blade with respect to a circumferential direction and an axial direction. Outlet flow angle of the nozzle is varied with distance along the blade length to vary optimum axial distance properly.

Abstract: A stator apparatus for mounting upstream of an intake to a rotating machine which blows pressurized air, or other media, from discharge orifices at a pressure and velocity to minimize velocity defects or turbulence in the wake of the stator prior to the plane of rotation of a rotating member of the machine. The rotating member then encounters a substantially uniform velocity medium at the plane of incidence, which substantially reduces uneven loading on the rotating member, thereby reducing noise and reducing high-cycle failure of that rotating element. The distribution and size of the orifices is determinable by placing the stator apparatus in a wind tunnel, or on the intake of a apparatus simulating the intake of the rotating machine, measuring the turbulence or velocity defects in the stator wake, and modifying the distribution and size of the orifices until the turbulence is minimized.

Abstract: A rotary turbomachine, and particularly a turbojet engine, has a compressor stage that is especially adapted for operation in the transonic region. The compressor stage includes a rotor (1) having a hub (2) and a plurality of compressor blades (3) extending radially therefrom, and a stator having a plurality of compressor blades extending radially between a stator hub and a housing. The hub (2) of the rotor (1), and/or the hub of the stator, and/or the housing of the stator, have a circumferential surface contour that is not continuously rotationally symmetrical. Namely, a concave contour (K) is provided in the circumferential surface of the hub near the base of each blade (3) on the pressure side (PS) thereof, while the circumferential surface on the suction side (SS) of the base of each blade has a contour that is linear, slightly convex, convex/concave, or slightly concave to a lesser degree than the concave contour (K) on the pressure side of each blade.

Abstract: In the invention, propagating broad band and tonal acoustic components of noise characteristic of interaction of a turbomachine blade wake, produced by a turbomachine blade as the blade rotates, with a turbomachine component downstream of the rotating blade, are reduced. This is accomplished by injection of fluid into the blade wake through a port in the rotor blade. The mass flow rate of the fluid injected into the blade wake is selected to reduce the momentum deficit of the wake to correspondingly increase the time-mean velocity of the wake and decrease the turbulent velocity fluctuations of the wake. With this fluid injection, reduction of both propagating broad band and tonal acoustic components of noise produced by interaction of the blade wake with a turbomachine component downstream of the rotating blade is achieved.

Abstract: A compressor is disclosed having a characteristic modifier, such as air injection, adapted to modify an operating characteristic of the compressor in order to reduce the bandwidth and rate limit requirements of the compressor. The compressor includes an actuator, such as a bleed valve, whose bandwidth and rate limit parameters meet the corresponding reduced requirements of the compressor. The actuator is adapted to stabilize the compressor with respect to a likely condition in the compressor which would tend to make the compressor operate in a less stable manner. This makes it possible to stabilize the compressor using a more readily available actuator having lower bandwidth and rate limit parameters.

Abstract: A fan shroud for an outdoor unit of an air conditioner is positioned between an axial fan and a grill. The axial fan has multiple fan blades and is designed to pull air through a heat exchanger toward the grill. The fan shroud includes an inflow portion and an outflow portion diverging outwardly. The inflow portion has substantially an inwardly U-bent section for generating a primary vortex. The U-bent section has two generally parallel legs connected at one end to define a closed end further from the grill and disconnected at another end to define an open end closer to the grill. The U-bent section extends along the entire circumference of the inflow portion. The open end and the closed end of the U-bent section are positioned between a front edge and a rear edge of each fan blade.

Abstract: For obtaining a highly compressed air in an axial compressor, a load per blade row must be reduced and blade rows must be increased in number by so much that the apparatus becomes unavoidably larger. The present invention provides an axial compressor stationary blade wherein a blade portion near an end wall face is twisted so as to coincide with a direction of a boundary layer flow occurring in the vicinity of the blade portion. This blade portion and a blade portion for the main flow are turned differently from each other over a distortion or twist angle, and thereby growth of the boundary layer flow is suppressed, an increase of losses is prevented, and the apparatus can be made compact.

Abstract: Improved performance of counter-rotating turbo machines and compressors. An increase in the thermodynamic efficiency of the compression process is obtained by removing the boundary layer in locations where separation is likely to occur.

Abstract: A sleeve slidable along an axial direction of the impeller shaft produces a variable width of the channels leading into and out of the bypass. The sleeve can be a single unit, a telescopic slide, or a slide of two relatively movable parts.

Abstract: A strut bridges inner and outer walls of a frame defining a flow channel for channeling a fluid therethrough. The strut has leading and trailing edges, and a root and tip, and is tapered between the root and tip for varying frequency and amplitude of vortex shedding.

Abstract: A turbo-machine comprises a housing. The housing has internal surfaces which come into contact with fluid flowing through the turbo-machine. The surfaces have an ordered, fine, sharp-edged groove structure that is affixed to the surfaces, such that the groove structure extends predominantly in the flow direction.

Abstract: In a conduit constituting the outlet from turbo machinery such as a turbine or compressor, stall gas having high static pressure and low velocity is collected. This stall gas is then routed through struts--preferably teardrop shaped--to more central low static pressure and high velocity gas flow areas. At these areas, the gas is discharged, preferably through multiple manifold openings. Mixing of the collected high static pressure, low velocity stall gas with the low static pressure, high velocity main stream gas occurs. Turbine noise, vibration, and back pressure are decreased with resulting improvements of efficiency. Variations are illustrated including adaptation of gas flow transfer utilizing turning vanes, fairings, rectangular duct turns, and struts for placement in turbine turbo machine outlets having high turbulence or variable swirl.

Abstract: A multi-stage blade system of an axial flow turbo machine includes a wall (10, 11), which is on either the rotor side, the stator side, or both, which bounds the flow through the channel through which flow passes. The wall is provided, immediately at the outlet of the rotor blades (La1, La2, La3), with a kink angle (A, AA). This kink angle (A, AA) is dimensioned such that the outlet flow from the rotor blades is homogenized in terms of the total pressure and outlet flow angle. The wall (10, 11) is also provided with an opposing kink angle (B, BB) at least approximately in the inlet region of the stator blades (Le2, Le3) of the following stage. This allows the labyrinth mass flow to be reduced in blade systems having covering strip sealing.

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.