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. The wheel shroud has a port for bleeding off a portion of air flowing through the compressor. The bleed air enters an annular space, flows forward, and is injected back into the inlet flow through a plurality of circumferentially spaced slots defined through the wheel shroud. The slots are open at a leading edge of the wheel shroud.

Abstract: A casing treatment 4 including a recirculation passage 41 and a mixing piping 6 are provided. The recirculation passage 41 has a first recirculation opening 42 and a second recirculation opening 43 that are in communication with each other, the first recirculation opening 42 being formed inside a compressor housing 11 of an exhaust gas turbocharger and opening to an air passage 15 upstream of a compressor impeller 3, the second recirculation opening 43 being formed at the outer circumferential section of the compressor impeller 3. The mixing pipe 6 opens to the recirculation passage 41 and has a return opening 14 for introducing EGR gas and blow-by gas to the recirculation passage 41.

Abstract: A compressor of an exhaust gas turbocharger has a compressor housing of a divided type that forms an inlet slit, an outlet slit and a recirculation passage at the same time when the compressor housing is assembled. In the compressor of the exhaust gas turbocharger, mating surfaces of compressor housing members 9a and 9b are formed in the neighborhood of the inlet part of the impeller 5 in the compressor housing 9 that is divided into the compressor housing members 9a and 9b in the direction of the rotation axis of the impeller; and, a space forming the recirculation passage 29, an inlet slit 25 and an outlet slit 27 are formed between the mating compressor housing members 9a and 9b.

Abstract: A turbomachine or high pressure compressor including a stator casing housing a plurality of compression stages that are spaced apart in an axial direction along the central axis of the turbomachine, each compression stage including a row of rotor blades followed by a row of stator vanes. The compressor further includes an air injection system including at least one air injection passage through the casing and including an outlet segment that opens out in an inclined manner upstream from and directed towards a row of rotor blades into a set-back zone of the inside face of the casing.

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 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 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 method for determining a preferred circumferential groove arrangement for a casing treatment of an axial flow compressor is disclosed. The method includes using the results from a three dimensional steady state computational fluid dynamic analysis to generate a flow field between a blade tip of a rotating blade and a compressor casing to determine the preferred circumferential groove arrangement. A stall margin for the axial flow compressor will be increased with the method.

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: There is provided a compressor (10) and an associated method for controlling a recirculation flow to control surging in the compressor. The compressor includes a housing (12) and a compressor wheel (16) mounted therein. A recirculation passage (41) receives compressed air from the compressor and recirculates the compressed air to an inlet passage (20) of the housing and, in particular, to leading edges (32) of blades (18) of the compressor wheel. An adjustable flow control device (60) is configured to control the flow of the compressed air through the recirculation passage to control a surge characteristic of the compressor. For example, the flow control device can include one or more valves (V1, V2, V3), each of which can be adjusted by an actuator (64).

Abstract: A turbomachine includes at least one rotor 1 featuring a hub and one stator 2, with a casing 5 confining the flow through the rotor 1 and the stator 2 to the outside. It also includes running-gap adjacent hub and casing surfaces LNGO, with openings being provided along the circumference on at least one running-gap adjacent hub and casing surface LNGO which form at least one dynamically operating supply point DAV which is connected via a least one line 6 to at least one opening on a blade-passage confining surface SKO.

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 fuel pump includes an impeller and a casing member. The impeller defines a plurality of vane grooves arranged in a circumferential direction. The casing member receives the impeller, and the casing member defines therein a pump passage configured to have an arcuate shape along the vane grooves. The discharge passage is provided downstream of the pressurizing passage. The discharge passage has a width narrower than a width of the pressurizing passage, and the discharge passage is positioned toward a radially outer wall of the pressurizing passage. The pressurizing passage includes a throttle part that extends from a starting point to an inlet of the discharge passage. The throttle part has a first width at the starting point, which corresponds to the width of the pressurizing passage, and a second width at the inlet, which corresponds to the width of the discharge passage.

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: The nozzles are in the form of blowing-in openings in the housing wall which bounds the flow channel. The blowing-in openings are fed directly by means of air which is extracted from the flow channel downstream from the diffusor. This air is at a higher pressure than the flow in the flow channel upstream of the diffusor. This results in a passive, dynamic stabilization system for a compressor stage in the high pressure-ratio range, which does not require any additional control or actuating elements.

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.

Abstract: A turbocompressor flow structure comprises a ring chamber which is arranged concentrically to an axis of a turbocompressor in an area of free blade/vane ends of a rotor blade ring/vane ring and is adjacent radially to a main flow channel. A ring chamber is provided which is bordered by a front upstream wall, a rear downstream wall and a wall that runs essentially axially. Baffle elements are arranged in the ring chamber and the ring chamber permits flow penetration in a circumferential direction in a front and/or rear area. At least one opening is provided in the area of the wall that runs essentially axially or in the area of the upstream wall and permits flow penetration out of the ring chamber, at least one compressor chamber being provided to accommodate this outgoing flow.

Abstract: A compressor assembly (404) includes a compressor housing (412) having a main inlet bore (424) and a secondary inlet passage (422) that has an increasing flow cross-sectional area. The secondary inlet passage (422) is positioned in the compressor housing (412) and around the main inlet bore (424). A secondary inlet slot (426) and an outlet slot (420) fluidly connect the secondary inlet passage (422) with the main inlet bore (424). A compressor wheel (418) is in the compressor housing (412) and has a stepped portion (518) formed by at least one plurality of vanes (506). The stepped portion (518) is located adjacent to the outlet slot (420) of the housing (412).

Abstract: A compressor for compressing a gas comprises an impeller wheel (1) mounted within a housing (2) defining an inlet and an outlet (6). The inlet comprises an outer tubular wall (7) extending away from the impeller wheel in an upstream direction and forming a gas intake portion (8) of the inlet, and an inner tubular wall (9) of diameter D extending away from the impeller wheel in an upstream direction within the outer tubular wall (7) and defining an inducer portion (10) of the inlet. An annular gas flow passage (11) is defined between the inner and outer tubular walls (9, 7) and has an upstream end and a downstream end separated by a length L1 measured along its axis. The upstream end of the annular passage (11) communicates with the intake or inducer portions of the inlet through at least one upstream aperture and at least one downstream aperture (13) communicates between a downstream portion of the annular flow passage (11) and the impeller.

Abstract: A recirculation structure for turbo-compressors has an annular chamber that is positioned in the area of the free blade ends of a rotating blade ring and that radially borders the main flow channel, and has a multitude of guide vanes arranged in the annular chamber and distributed around its circumference. The annular chamber enables the passage of air flow in the forward and/or rear areas, and the guide vanes are firmly fixed to at least one wall of the annular chamber and otherwise are designed to be free-standing. The tips of the guide vanes that face the annular chamber extend along and/or near the contour of the main flow channel, and axially overlap the free blade ends or axially border the area of the free blade ends.

Abstract: An apparatus and method is provided for improving efficiency of a transonic gas turbine engine compressor by bleeding off a shockwave-induced boundary layer from the gas flow passage of the compressor using an array of bleed holes having a downstream edge aligned with a foot of an oblique shock wave which originates on the leading edge of an adjacent transonic rotor blade tip.

Abstract: This invention provides a single cascade multistage turbine that has a compact turbine structure having only a single cascade, and enables power to be extracted efficiently in the same way as a multistage turbine having multistage rotor vanes. The working fluid supplied through the supply duct 3 flows on one side of the single cascade of rotor vanes 2 to one part of the circumference direction of the rotor vanes 2, and after passing through the rotor vanes 2 it passes through the circulation ducts 4a and 4b and returns to the former side of the rotor vanes 2. The circulation ducts 4a and 4b consist of exhaust duct members 6a and 6b, return duct members 7a and 7b, and inflow duct members 8a and 8b. Using the circulation ducts 4a and 4b this circulation process is repeated at least once whereby the working fluid is again passed through the rotor vanes 2 at a slightly different position in the circumferential direction of the rotor vanes 2.

Abstract: In an exhaust turbocharger for an internal combustion engine including a turbine and a compressor, which is driven by the turbine, wherein the compressor comprises a compressor impeller in a flow duct, a transfer component with flow passages extends radially around the compressor impeller in the axial direction of the impeller and provides for communication with the flow duct. To provide for variable adjustment of the effective flow cross-section of the transfer duct, a transfer ring is provided which comprises two component rings, which are rotatable relative to one another.

Abstract: A centrifugal pump for a gas turbine engine, including a housing having a fluid inlet port for receiving fluid at an initial pressure and an interior chamber defining a central axis. An impeller disk disposed within the interior chamber of the housing and mounted for rotation about the central axis. The impeller disk defines first and second inlet areas and has a plurality of circumferentially spaced apart channels formed therein which extend from the inlet areas for conducting fluid from the inlet areas in a radially outward direction upon rotation of the impeller disk so as to increase the pressure of the fluid. A first collector is formed by the housing for receiving the fluid from the first inlet area via the channels at a first elevated pressure relative to the initial pressure and a second collector is formed by the housing for receiving fluid from the second inlet area via the channels at a second elevated pressure relative to the first elevated pressure.