Abstract: A centrifugal pump for delivering hot fluids, having a contacting shaft seal, a seal housing (13) for the shaft seal (14), and a return line (8) for a partial flow of the delivered fluid, in which no delivered fluid is discharged out of the seal housing (13); a separate housing cover (9) is disposed between the seal housing (13) and the pump housing (1); there is a contact surface which minimizes heat transfer between the seal housing (13) and the housing cover (9); and the return line (8) is connected to the housing cover (9) and/or to the pump housing (1).

Abstract: A centrifugal pump (1, 110) includes an apparatus for the removal of particles, wherein the centrifugal pump includes an impeller (6, 106). A fluid (2, 102) can be conveyed by means of the impeller (6, 106) through a suction passage (5, 105) from a suction stub (3, 103) to a pressure stub (4, 104). The impeller (6, 106) is rotatable in a stator (7, 107). A gap (9, 19, 109) is arranged between the stator (7, 107) and the impeller (6, 106), wherein the gap (9, 19, 109) opens into a storage space (11, 21, 111) for particles. The storage space (11, 21, 111) communicates with the suction passage (5, 105) via a return line (12, 112) running through the stator (7, 107).

Abstract: A compressor typically for use in a turbocharger comprises a downstream radial compressor impeller wheel, an upstream axial compressor impeller wheel and an intermediate stator. The compressor housing has an inlet with inner and outer walls that define between them an MWE gas flow passage. An upstream opening defined by the flow passage provides communication between the passage and the intake and at least one first slot downstream of the upstream opening provides communication between the passage and the inner surface of the inner wall. The stator comprises a plurality of fixed vanes and is disposed in the inner wall of the inlet between the radial and axial impeller wheels. The position of the slot can be at one of several positions along the gas flow passage, in other embodiments there are second and third slots and the flow passage is divided into two parts. All the arrangements are designed to improve the compressor map width.

Abstract: In one exemplary embodiment of the present invention, a compressor housing for a forced induction system of an internal combustion engine is provided. The compressor housing includes a compressor inlet passage in fluid communication with a compressor volute configured to house a compressor wheel, the compressor inlet passage comprising a wall that is shared with the compressor volute. The compressor also includes a compressor outlet in fluid communication with the compressor volute, the compressor outlet being configured to direct a compressed gas to an intake manifold of the internal combustion engine.

Abstract: A compressor comprises an impeller wheel mounted within a housing defining an inlet and an outlet. The wheel has a plurality of vanes and is rotatable about an axis. The housing has an inner wall defining a surface located in close proximity to radially outer edges of the impeller vanes which sweep across said surface as the impeller wheel rotates about its axis. The inlet comprises a tubular wall extending away from the impeller wheel in an upstream direction. An enclosed chamber is defined between said inner wall and an outer wall and in communication with at least one opening in said in said inner wall. The outer wall is penetrated by at least one ventilation aperture that is designed to be connected via a conduit to a location upstream of the inlet and downstream of an air filter.

Abstract: Provided is a centrifugal compressor having improved operation performance to improve durability. The centrifugal compressor includes an impeller connected to a rotary shaft and configured to radially eject a fluid suctioned in an axial direction upon rotation thereof; a shroud configured to cover front and rear sides of the impeller and having a suction port formed to face one surface of the impeller at a center of one side thereof; a volute chamber formed at an outer periphery of the shroud in a circumferential direction thereof and configured to guide the fluid ejected by the impeller to an ejection port; and a regulator installed at one side of the shroud and configured to selectively communicate a space formed at the other surface of the impeller with the outside.

Abstract: A compressor typically for use in a turbocharger comprises a downstream radial compressor impeller wheel, an upstream axial compressor impeller wheel and an intermediate stator. The compressor housing has an inlet with inner and outer walls that define between them an MWE gas flow passage. An upstream opening defined by the flow passage provides communication between the passage and the intake and at least one first slot downstream of the upstream opening provides communication between the passage and the inner surface of the inner wall. The stator comprises a plurality of fixed vanes and is disposed in the inner wall of the inlet between the radial and axial impeller wheels. The position of the slot can be at one of several positions along the gas flow passage, hi other embodiments there are second and third slots and the flow passage is divided into two parts. All the arrangements are designed to improve the compressor map width.

Abstract: A compressor (1) of an exhaust-gas turbocharger (ATL), having a compressor wheel (2) and a compressor housing (3) which has a housing longitudinal axis (A). The compressor wheel (2) is arranged in the housing. An inlet duct (5) runs from a compressor inlet (4) to the compressor wheel (2). A recirculation duct (6) has a compressor-wheel-side inflow opening (7) and a compressor-inlet-side return flow opening (8). The inflow opening (7) and the return flow opening (8) can be opened and closed.

Abstract: Apparatus for reducing air mass flow through the compressor in a single shaft gas turbine engine having an extended operating range including part load conditions, to provide low emissions combustion. The apparatus includes one or more nozzles positioned for injecting compressed air into the inlet region of the compressor. The nozzles are oriented to direct the compressed air tangentially to, and in the same angular direction as, the direction of rotation to create a swirl in the inlet air flow to the compressor inducer. The apparatus also includes conduits in flow communication between the compressor diffuser and the nozzles, one or more valves operatively connected to control the flow of compressed air from the diffuser to the nozzles, and a controller operatively connected to the valves to cause compressed air flow to the nozzles during operation at part load conditions.

Abstract: A diffuser for a centrifugal impeller assembly of a gas turbine engine includes a diffuser case having a plurality of vanes extending therein defining a plurality of circumferentially distributed angled passages in communication with an inlet space. Each vane includes a bleed port defined in a suction surface thereof, in proximity of the leading edge. The diffuser case includes a passive fluid communication defined at least partially through each one of the vanes between each bleed port and the inlet space upstream of the leading edge, such that air bled through the bleed ports is recirculated upstream of the leading edges to the inlet space to increase a surge margin of the diffuser.

Abstract: In a radial compressor, particularly of an exhaust gas turbocharger of an internal combustion engine, having a compressor housing within which a compressor wheel is disposed for compressing air from an inflow channel of the compressor housing and directing the air to an outflow channel of the compressor housing, the compressor housing comprising a bypass channel having a first flow opening upstream of an axial compressor wheel inlet and a second flow opening downstream of the compressor wheel inlet, the compressor housing is configured at least in a flow region upstream of the second flow opening in an asymmetric manner with regard to a rotational axis of the compressor wheel.

Abstract: In one example, a turbocharger for an internal combustion engine is described. The turbocharger comprises a casing containing an impeller having a full blade coupled to a hub that rotates about an axis of rotation. The casing includes a bleed port and an injection port. The full blade includes a hub edge, a casing edge, and a first distribution of angles, each angle measured between the axis of rotation and a mean line at the hub edge at a meridional distance along the hub edge. The full blade includes a second distribution of angles, each angle measured between the axis of rotation and a mean line at the casing edge at a meridional distance along the casing edge. Further, various systems are described for affecting the aerodynamic properties of the compressor and turbine components in a way that may extend the operating range of the turbocharger.

Abstract: A supersonic gas compressor with bleed gas collectors, and a method of starting the compressor. The compressor includes aerodynamic duct(s) situated for rotary movement in a casing. The aerodynamic duct(s) generate a plurality of oblique shock waves for efficiently compressing a gas at supersonic conditions. A convergent inlet is provided adjacent to a bleed gas collector, and during startup of the compressor, bypass gas is removed from the convergent inlet via the bleed gas collector, to enable supersonic shock stabilization. Once the oblique shocks are stabilized at a selected inlet relative Mach number and pressure ratio, the bleed of bypass gas from the convergent inlet via the bypass gas collectors is effectively eliminated.

Abstract: There is provided a compressor device in which resonance in a circulating channel is reduced so that an increase in noise generated from the compressor device is prevented. The compressor device includes: a plurality of blades rotated about a rotation axis; an air inlet extending along the rotation axis and introducing air to the blades; a circulating channel disposed on a circumference centered on the rotation axis and communicating between the air inlet and the shroud of the blades; and a strut extending radially centered on the rotation axis and dividing the circulating channel. Resonance frequencies determined from circumferential lengths in the circulating channels divided by the strut are higher than a noise frequency determined from the rotational speed of the blades and the number of blades.

Abstract: A compressor typically for use in a turbocharger comprises a downstream radial compressor impeller wheel, an upstream axial compressor impeller wheel and an intermediate stator. The compressor housing has an inlet with inner and outer walls that define between them an MWE gas flow passage. An upstream opening defined by the flow passage provides communication between said passage and the intake and at least one first slot downstream of the upstream opening provides communication between the passage and the inner surface of the inner wall. The stator comprises a plurality of fixed vanes and is disposed in the inner wall of the inlet between the radial and axial impeller wheels. The position of the slot can be at one of several positions along the gas flow passage, hi other embodiments there are second and third slots and the flow passage is divided into two parts. All the arrangements are designed to improve the compressor map width.

Abstract: A radial compressor includes an impeller which is rotatively driven, axially introduces air taken in through an air inlet passage formed in a housing, pressurizes the introduced air, and discharges the pressurized air in a radial direction, wherein an annular concave groove is formed in a peripheral wall of the air inlet passage of the housing, a rear end portion of an opening of the annular concave groove, which rear end portion meets the housing peripheral wall, is provided in the vicinity of a blade front end surface of the impeller, and the rear end portion of the opening of the annular concave groove is formed such that an axial projecting amount X thereof relative to the blade front end surface of the impeller is set to ?1T?X?1.5T (where T denotes the thickness of the distal portion of a blade).

Abstract: A turbocharger housing has a valve device. The valve device is formed with at least one first duct section and a second duct section. The two duct sections are arranged with their longitudinal axes parallel to one another and they are formed without any undercuts.

Abstract: A compressor typically for use in a turbocharger comprises a downstream radial compressor impeller wheel, an upstream axial compressor impeller wheel and an intermediate stator. The compressor housing has an inlet with inner and outer walls that define between them an MWE gas flow passage. An upstream opening defined by the flow passage provides communication between the passage and the intake and at least one first slot downstream of the upstream opening provides communication between the passage and the inner surface of the inner wall. The stator comprises a plurality of fixed vanes and is disposed in the inner wall of the inlet between the radial and axial impeller wheels. The position of the slot can be at one of several positions along the gas flow passage, in other embodiments there are second and third slots and the flow passage is divided into two parts. All the arrangements are designed to improve the compressor map width.

Abstract: A compressor (8) of an exhaust-gas turbocharger (1), having a compressor wheel (11) which can be driven in a compressor wheel direction of rotation (VR); having a compressor housing (10) in which the compressor wheel (11) is arranged, as viewed in the flow direction of the inducted air, between a preferably tubular compressor inlet (12) and a compressor outlet (13), and having an overrun air recirculation valve inflow duct (14, 15) which runs in the compressor housing (10) from the compressor outlet (13) to the compressor inlet (12), wherein the inflow duct (14, 15) opens into the compressor inlet (12) substantially in the circumferential direction with respect to the inner diameter (DI) of said compressor inlet (12).

Abstract: A centrifugal compressor includes an asymmetric self-recirculating casing treatment that includes, on an inner face of a casing 10, a suction ring groove 1, a ring guide channel 2 and a back-flow ring groove 3 to form a self-recirculating channel. An axial distance Sr from an upstream end face of the suction ring groove 1 to an impeller full blade leading edge 4 or a width br of the suction ring groove 1 is represented as A·sin(?+?0)+A0 and is distributed in a sinusoidal shape in a circumferential direction, an initial phase angle ?0 is in a range of 0°??0?360°, and a circumferential angle ? of the casing 10 has a definition range of ?0????0+360°. In the expression, A denotes amplitude of distribution of the axial distance Sr or the width br, and A0 denotes an average of the axial distance Sr or the width br.

Abstract: A centrifugal compressor has a casing 7. In the casing 7 is formed a back-flow channel 9 to return fluid from a downstream position of an impeller full blade leading edge 6a to an upstream position of the impeller full blade leading edge 6a. The back-flow channel 9 includes a suction ring groove 9a and a back-flow ring groove 9b. The suction ring groove opens at the downstream position on the inner face 7a of the casing 7, and extends in the circumferential direction. The back-flow ring groove opens at the upstream position on the inner face 7a, and extends in the circumferential direction. Distribution in the circumferential direction of the axial-direction position of the suction ring groove 9a or a width of the suction ring groove 9a is asymmetric with reference to the rotation axis.

Abstract: In a compressor of a turbocharger of an internal combustion engine comprising a housing with an inflow channel; a compressor impeller arranged in the inflow channel; and a bypass channel which has a first flow opening upstream of the compressor impeller inlet, a second flow opening downstream of the compressor impeller inlet and an axial annular chamber which connects the first and the second flow openings. An axial vane structure is provided in the axial annular chamber of the bypass channel, which imparts a swirl direction corresponding to that of the air mass flow in the inflow channel to the air mass flowing through the bypass channel from the second to the first flow opening.

Abstract: An exemplary port (180, 180?) includes a first port opening (182, 182?) positioned at a location downstream from a compressor wheel (140), a second port opening (184, 184?) positioned at a location adjacent to a blade (144) of the compressor wheel (140), and a third port opening (186, 186?) positioned at a location upstream from the compressor wheel (140) wherein the first port opening and the third port opening define a first flow path and wherein a second flow path extending from the second port opening meets the first flow path at a confluence (188, 188?). The first flow path optionally includes a venturi section, for example, wherein the confluence coincides at least in part with the venturi section. Other exemplary ports, compressor shrouds, systems and methods are also disclosed.

Abstract: A centrifugal compressor for compressing a fluid comprises a compressor wheel having a plurality of circumferentially spaced blades, and a compressor housing in which the compressor wheel is mounted. The compressor housing includes an inlet duct through which the fluid enters in an axial direction and is led by the inlet duct into the compressor wheel, and an inner surface located radially adjacent the tips of the blades. A bleed port is defined in the inner surface of the compressor housing at a location intermediate the leading and trailing edges of the blades, for bleeding off a bleed portion of the fluid, the bleed port leading to a recirculation flow channel that feeds the bleed portion back into the inlet duct. Highly cambered vanes are disposed in the recirculation flow channel for turning the bleed portion to take out and in some cases reverse the swirl in the bleed portion.

Abstract: A compressor comprises an impeller wheel mounted within a housing defining an inlet and an outlet. The wheel has a plurality of vanes and is rotatable about an axis. The housing has an inner wall defining a surface located in close proximity to radially outer edges of the impeller vanes which sweep across said surface as the impeller wheel rotates about its axis. The inlet comprises a tubular wall extending away from the impeller wheel in an upstream direction. An enclosed chamber is defined between said inner wall and an outer wall and in communication with at least one opening in said in said inner wall. The outer wall is penetrated by at least one ventilation aperture that is designed to be connected via a conduit to a location upstream of the inlet and downstream of an air filter. The arrangement maintains the advantages of a conventional MWE structure and further improves the surge margin. In addition, the risk of debris being drawn into the compressor via the opening is eliminated.

Abstract: A method for cooling a component of a turbine is provided, wherein a fluid with a pressure below 1 bar is guided away from the component. Moreover, a turbine is described comprising a component, a conduit which is connected to the component so that a fluid can be guided away from the component, and a fluid discharge which is connected to the conduit. The fluid discharge is constructed so that it removes a fluid with a pressure below 1 bar.

Abstract: A diffuser for a centrifugal impeller assembly of a gas turbine engine includes a diffuser case having a plurality of vanes extending therein defining a plurality of circumferentially distributed angled passages in communication with an inlet space. Each vane includes a bleed port defined in a suction surface thereof, in proximity of the leading edge. The diffuser case includes a passive fluid communication defined at least partially through each one of the vanes between each bleed port and the inlet space upstream of the leading edge, such that air bled through the bleed ports is recirculated upstream of the leading edges to the inlet space to increase a surge margin of the diffuser.

Abstract: A compressor includes a housing, a rotor, an impeller, and a ported shroud. The rotor is mounted within the housing, and has a first leading edge and a first trailing edge. The rotor is operable, upon rotation thereof, to compress air and to discharge the air in an approximately axial direction. The impeller is mounted within the housing, and has a second leading edge and a second trailing edge. The impeller is operable, upon rotation thereof, to receive the air discharged from the rotor, to further compress the air, and to discharge the air in an approximately radial direction. The shroud at least partially surrounds the impeller. The shroud has an opening therein to at least facilitate allowing the air to travel upstream of the opening.

Abstract: A gas turbine engine includes a housing with a duct wall that defines a generally annular and axially elongated hot gas flow path for passage of combustion gas. The engine further includes a contoured shroud mounted within the internal engine cavity and defining a hot gas recirculation pocket for receiving hot gas ingested from the hot gas flow path through the annular space and for recirculating the ingested hot gas back through the annular space to the hot gas flow path. The contoured shroud includes a base wall extending radially inwardly from the duct wall, an inboard wall extending from the base wall in an axial direction toward the rotor, and an end wall extending from the inboard wall in a radially outward direction. The end wall terminates in a circumferentially extending free edge disposed in proximity to the annular space. The end wall defines an opening.

Abstract: An axial tip turbine driven pump in which a first fluid pumped by an inducer is driven by a second fluid that reacts with a turbine blade extending from a shroud on the inducer. The inducer includes a set of screw thread blades and a second set of partial blades that are covered by a shroud in the aft section of the inducer. A row of turbine blades extends from the shroud and into a manifold that forms the outer casing for the pump. The fluid flow through the manifold reacts with the turbine blades and drives the inducer to pump the fluid from the inlet and through guide vanes downstream from the inducer. Fluid from a pre-burner or a gas generator used to drive a main turbine is bled off and used to drive the low pressure turbine blades and the inducer.

Abstract: A multistage compressor for a gas turbine, having a compressor housing, guide vanes, impeller vanes, a hub area, discharge ports, and injection ports for stabilizing the compressor flow, wherein the discharge ports are situated at least one stage downstream from the injection ports, the injection ports being fashioned as nozzles, and the geometry of these nozzles is designed such that the flow speed of the injected air stream is significantly greater than the speed of the flow in a critical cross-section.

Abstract: A fuel pump has substantially coaxial outer and inner pump chambers. An impeller has partition walls correspondingly to the inner pump chamber to define inner vane grooves. A rear surface is located at a rear side in a rotative direction of each inner vane groove. At least a radially inner side of the rear surface inclines rearward in the rotative direction from the radially inner side to a radially outer side. A first line connects a radially inner end of the rear surface with a radially outer end of the rear surface. A second line radially extends from the radially inner end of the rear surface. The first line and the second line therebetween define a backward tilt angle ?2, which satisfies a relationship of 30°??2?80°.

Abstract: An apparatus (1) includes a housing (2), an air feed duct (21) a volute (5), an impeller (4), and a motor (3) for driving the rotation of the impeller (4) so as to generate a centrifugal air flow in the volute (5). The housing (2) has a first part (18a) where wall is intended, after assembly, to extend around the motor (3), espousing the shape of this motor (3) in such a way as to lie at a substantially constant distance from this motor (3); and a second part (18b, 19) where wall is intended, after assembly, to extend around the volute (5), espousing the shape of this volute (5) so as to lie at a substantially constant distance from this volute (5). The housing (2) internally forms a salient axial lump (20) which, after assembly, sits close to the hub (10) of the impeller (4).

Abstract: An internal heating arrangement for a centrifugal impeller for a gas turbine engine is provided having at least one heating passage extending through into the rotor for directing air bled from the rotor exit along the backface and forwardly through the impeller.

Abstract: A turbocharger (10) for an internal combustion engine includes a compressor (12) having an impellor (16) disposed in a compressor chamber (18). The compressor chamber (18) receives fluid flow. A flow regulation mechanism (30) is disposed in the compressor (12) and includes a diffuser cover (32) and a recirculation gate (36). The diffuser cover (32) is moveably disposed in a diffuser passage (34) from a first position permitting fluid flow through the diffuser passage to a second position at least partially impeding the fluid flow. The recirculation gate (36) is moveably disposed in the compressor chamber (18) from a first position closing a recirculation groove (48) to a second position opening the recirculation groove to fluid communication with the compressor chamber.

Abstract: A compressor having a variable-geometry ported shroud includes a compressor housing defining an inlet duct, a shroud, and a bypass passage. A variable-geometry port extends through the shroud into the bypass passage, and includes an adjustable mechanism that is selectively configurable to adjust the meridional location of the port between at least first and second meridional locations. In one embodiment an opening extends through the shroud, and the adjustable mechanism includes a bypass control device that is disposed within the opening and is axially movable therein. The bypass control device has an axial length less than that of the opening such that there is always a portion of the opening that remains unblocked by the bypass control device and forms a port through the shroud. The bypass control device is axially movable between at least first and second positions to place the port at the first and second meridional locations.

Abstract: There is provided a compressor (10) and associated method for providing a flow of recirculated air to control surging in the compressor. The compressor includes a housing (12) with a compressor wheel (16) rotably mounted therein. The housing defines at least one injection port (36) configured to receive compressed air from the compressor wheel and recirculate the compressed air to an inlet passage (20) of the compressor. In particular, each injection port defines an outlet (38) proximate to the leading edges (32) of the blades (18) of the compressor wheel such that the compressed air is delivered to the leading edges and reduces the occurence of surging.

Abstract: A housing is incorporated as part of a compressor having blades that impart to a fluid a momentum along a main gas flow direction and a swirl. The housing includes a channel that has at least one channel wall and defines an axis substantially aligned with the main gas flow direction. The channel is configured to duct at least some of the fluid. The channel wall defines an internal cavity that extends axially within the channel wall. A bleed passage connects and provides fluid communication between the channel and the cavity. The channel wall defines a plurality of injection passages providing fluid communication between the cavity and the channel at a location spaced in a direction opposite the main gas flow direction from both the bleed passage and the blades. The injection passages have a portion configured to direct fluid from the cavity into the channel with a component along the main gas flow direction and a component opposed to the swirl.

Abstract: A housing is disclosed for a compressor having a duct defining a main gas flow axis and blades that draw a fluid through the duct. The blades impart to the fluid a momentum along a main gas flow direction and a swirl. The housing includes a volute configured to extend substantially circumferentially around and fluidly communicate with the duct (at a first location). The volute may be configured to direct a fluid portion flowing thereinto from the duct to have a velocity with a component in a first circumferential direction generally aligned with the swirl. The housing may also include at least one conduit, such as a pipe, in fluid communication with the first volute. The conduit may be configured to redirect the fluid portion to have a velocity with a first component along the main gas flow axis in a direction opposite the main gas flow direction and a second component in a second circumferential direction opposite to the first circumferential direction.

Abstract: A fuel pump includes a bearing element disposed in proximity to an impeller. The bearing element is configured to form a fuel seal with the impeller and to drain fuel leaked from the pump chamber back into the pump chamber. The bearing element minimizes leakage of fuel from the pump chamber into an engine coupled to the impeller. The fuel pump also includes redundant lip seals configured to provide redundant sealing relative to a shaft of the impeller within the fuel pump in order to minimize engine oil from entering the pump chamber and to minimize fuel from entering the engine. Integration of both the bearing element and the redundant lip seals as part of the fuel pump results in the fuel pump having a relatively compact size.

Abstract: A rotational axis multi-phased wind turbine power generating system is disclosed. A differential pressure is created by utilizing the prevailing wind, and air from the prevailing wind is directed into air blades for the creation of power. Optimally, the air blades directly utilize the prevailing wind in combination with the created differential pressure to create power. An adjustable air scoop, adjustable exit drag curtain or barrier, orienting systems, and air flow directing dampers are disclosed.

Abstract: A centrifugal compressor for compressing a fluid comprises a compressor wheel having a plurality of circumferentially spaced blades, and a compressor housing in which the compressor wheel is mounted. The compressor housing includes an inlet duct through which the fluid enters in an axial direction and is led by the inlet duct into the compressor wheel, and a wheel shroud located radially adjacent the tips of the blades. A bleed port is defined in the wheel shroud at a location intermediate the leading and trailing edges of the blades for bleeding off a bleed portion of the fluid being compressed by the compressor wheel. A converging injection nozzle is defined in the duct wall upstream of the leading edges of the blades for injecting the bleed portion of the fluid back into the main fluid flow stream approaching the compressor wheel.

Abstract: A radial compressor is capable of preventing the occurrence of separation caused by a flow which goes beyond the front end of a blade and turns onto a negative pressure plane from a pressure plane, thereby reducing a surging flow rate to a smaller flow rate. The radial compressor includes an impeller which is rotatively driven, axially introduces air taken in through an air inlet passage formed in a housing, pressurizes the introduced air, and discharges the pressurized air in a radial direction, wherein an annular concave groove is formed in a peripheral wall of the air inlet passage of the housing, a rear end portion of an opening of the annular concave groove, which rear end portion meets the housing peripheral wall, is provided in the vicinity of a blade front end surface of the impeller, and the rear end portion of the opening of the annular concave groove is formed such that an axial projecting amount X thereof relative to the blade front end surface of the impeller is set to ?1T?X?1.

Abstract: A Multi or single-stage turbo compressor with at least one compressor wheel fastened to a shaft. the shaft is mounted in a turbocompressor housing which is separated by a hub disc a front interior housing region in front of the hub disc of the compressor wheel. The driven compressor wheel delivers a fluid from an inlet channel (10) to an outlet channel. The front interior housing region comprises a wheel lateral space from which an extraction channel for the extraction of fluid is provided.

Abstract: To provide a pump comprising an impeller which sucks and discharges liquid, a motor unit which drives the impeller, a parting plate which is disposed between the impeller and the motor unit and which partitions the impeller and the motor unit, a case formed with a pump chamber in which the impeller is accommodated, a suction port which is connected to the case and which sucks liquid and a discharge port which discharges liquid, wherein the case is provided with a discharge passage which discharges liquid introduced into the pump chamber from the suction port, the discharge passage has a predetermined diameter, the discharge passage is provided along an outer periphery of the pump chamber at a location at a predetermined distance from the outer periphery of the pump chamber, the pump further comprises at least one reflow passage which brings the discharge passage and the pump chamber into communication with each other and through which liquid flowing through the discharge passage flows back to the pump chamber

Abstract: A gas turbine transition duct apparatus is provided comprising first and second turbine transition ducts and a strip seal. The strip seal may comprise a sealing element and a spring structure.

Abstract: A fan unit for an agricultural machine includes a fan housing configured to define a plurality of fan chambers. Each fan chamber of the plurality of fan chambers has a respective air inlet port and a respective air outlet port. A shaft is rotatably mounted to the fan housing. The shaft has an axis of rotation that intersects the plurality of fan chambers. A plurality of fans is attached to the shaft for rotation with the shaft. Each fan of the plurality of fans is located in a separate respective fan chamber of the plurality of fan chambers.

Abstract: A centrifugal compressor for compressing a fluid comprises a compressor wheel having a plurality of circumferentially spaced blades, and a compressor housing in which the compressor wheel is mounted. The compressor housing includes an inlet duct through which the fluid enters in an axial direction and is led by the inlet duct into the compressor wheel, and an inner surface located radially adjacent the tips of the blades. A bleed port is defined in the inner surface of the compressor housing at a location intermediate the leading and trailing edges of the blades, for bleeding off a bleed portion of the fluid, the bleed port leading to a recirculation flow channel that feeds the bleed portion back into the inlet duct. Highly cambered vanes are disposed in the recirculation flow channel for turning the bleed portion to take out and in some cases reverse the swirl in the bleed portion.

Abstract: An improved diffuser apparatus for use in connection with gas turbines that will markedly increase the fuel efficiency of the turbine. The improved diffuser apparatus improves the performance of the diffuser apparatus by insuring that the gas flow supplied by the turbine is free from unnecessary energy losses due to improperly located mechanical structures. More particularly, the prior art turbine is modified in a manner to incorporate into the diffuser itself certain of the mechanical structures that previously formed a part of the structure of the turbine.

Abstract: Fluid transfer controllers (FTCs) having a rotor assembly with multiple rotor blade sets coupled to a hub component of the rotor assembly and further having barrier components forming passages for routing fluid through the multiple rotor blade sets are provided. More specifically, the FTCs include passages for routing fluid along one side of a dividing structure to which a first set of rotor blades is attached and subsequently along the opposite side of the dividing structure to which a second set of rotor blades is attached. The dividing structure may be the hub component of the rotor assembly or a partition separating different levels of rotor blades within the rotor assembly. In some cases, the FTCs may be configured to route fluid from the first rotor blade set to a thermal energy alteration device and further route fluid from the thermal energy alteration device to the second rotor blade set.