EP2513488A2 - Turbocompresseur - Google Patents

Turbocompresseur

Info

Publication number
EP2513488A2
EP2513488A2 EP10795284A EP10795284A EP2513488A2 EP 2513488 A2 EP2513488 A2 EP 2513488A2 EP 10795284 A EP10795284 A EP 10795284A EP 10795284 A EP10795284 A EP 10795284A EP 2513488 A2 EP2513488 A2 EP 2513488A2
Authority
EP
European Patent Office
Prior art keywords
flow
impeller
side opening
inlet
channel
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Granted
Application number
EP10795284A
Other languages
German (de)
English (en)
Other versions
EP2513488B1 (fr
Inventor
Hans-Joachim Ring
Joel Kofi Adomako
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Piller Blowers and Compressors GmbH
Original Assignee
Piller Industrieventilatoren GmbH
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Piller Industrieventilatoren GmbH filed Critical Piller Industrieventilatoren GmbH
Publication of EP2513488A2 publication Critical patent/EP2513488A2/fr
Application granted granted Critical
Publication of EP2513488B1 publication Critical patent/EP2513488B1/fr
Active legal-status Critical Current
Anticipated expiration legal-status Critical

Links

Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/40—Casings; Connections of working fluid
    • F04D29/42—Casings; Connections of working fluid for radial or helico-centrifugal pumps
    • F04D29/4206—Casings; Connections of working fluid for radial or helico-centrifugal pumps especially adapted for elastic fluid pumps
    • F04D29/4213—Casings; Connections of working fluid for radial or helico-centrifugal pumps especially adapted for elastic fluid pumps suction ports
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D27/00—Control, e.g. regulation, of pumps, pumping installations or pumping systems specially adapted for elastic fluids
    • F04D27/02—Surge control
    • F04D27/0207—Surge control by bleeding, bypassing or recycling fluids
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D27/00—Control, e.g. regulation, of pumps, pumping installations or pumping systems specially adapted for elastic fluids
    • F04D27/02—Surge control
    • F04D27/0207—Surge control by bleeding, bypassing or recycling fluids
    • F04D27/0215—Arrangements therefor, e.g. bleed or by-pass valves
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/40—Casings; Connections of working fluid
    • F04D29/42—Casings; Connections of working fluid for radial or helico-centrifugal pumps
    • F04D29/44—Fluid-guiding means, e.g. diffusers
    • F04D29/441—Fluid-guiding means, e.g. diffusers especially adapted for elastic fluid pumps
    • F04D29/444—Bladed diffusers
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/66—Combating cavitation, whirls, noise, vibration or the like; Balancing
    • F04D29/68—Combating cavitation, whirls, noise, vibration or the like; Balancing by influencing boundary layers
    • F04D29/681—Combating cavitation, whirls, noise, vibration or the like; Balancing by influencing boundary layers especially adapted for elastic fluid pumps
    • F04D29/685—Inducing localised fluid recirculation in the stator-rotor interface
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2250/00—Geometry
    • F05D2250/50—Inlet or outlet
    • F05D2250/51—Inlet

Definitions

  • the invention relates to a turbocompressor comprising a compressor housing, in which an incoming gas volume flow through an inlet channel is fed to an impeller passage, is compressed in the impeller passage by an impeller and is discharged from the impeller passage via an outlet passage, and provided with a compressor housing, outside the impeller passage and the Inlet passage extending flow bypass channel, which opens with an inlet side opening in the inlet channel and with an impeller-side opening in the impeller channel and which leads in response to a pressure difference between the openings a bypass volumetric flow.
  • Such a turbocompressor is known, for example, from EP 0 913 585 B1.
  • Such a turbocompressor is not designed with a view to the best possible operation in volume flows, which are far below the intended for the design point volume flow.
  • the invention is therefore an object of the invention to improve a turbocompressor of the generic type such that it can be optimally operated at flow rates that are far below the intended for the design point volume flow.
  • the flow cross-sectional area of the flow diversion channel increases steadily as it extends from the impeller-side opening to the inlet-side opening in order to obtain a favorable design of a bypass volumetric flow from the impeller-side opening to the inlet-side opening for flow stabilization in part-load operation.
  • a particularly advantageous solution of a turbocompressor according to the invention provides that a flow cross-sectional area of the inlet-side opening is in the range between 2.5 times and 3 times the flow cross-sectional area of the impeller-side opening.
  • the above-mentioned object is also achieved in a turbocompressor of the type described above in that the flow bypass channel is formed by with respect to an impeller axis in a circumferential direction juxtaposed channel segments, that is, the flow diversion channel itself does not extend continuously in the direction of rotation around the impeller channel, but is divided into such individual channel segments.
  • the channel segments are separated from one another in the direction of rotation, so that a swirl arising in the region of the impeller is not transmitted through the flow diversion channel, but is decelerated in the flow diversion channel, so that in particular from the inlet-side opening the Strömungsumieitungskanais exits a spin-free bypass flow.
  • the intake-side opening of the flow-bypass duct lies in the region between inlet-side ends of long impeller blades and inlet-side ends of short impeller blades.
  • the impeller-side opening of the Strömungsumieitungskanais lies in a surface which is continuous to a current flow upstream of this opening and a flow guide located downstream of this opening flow guide surface.
  • the Iaufrad capablee opening of the Strömungsumieitungskanais is formed in a circumferential direction around the impeller axis, that is, that the Iaufrad capablee opening of the Strömungsumieitungskanais extends around the entire impeller channel and thus over the entire circumference of the gas volume flow in the impeller passage allows the bypass volume flow to flow out.
  • the opening of the flow diversion channel is interrupted by ribs or webs which divide the flow diversion channel into individual successive segments in the direction of rotation.
  • an advantageous solution provides that the inlet-side opening of the flow diversion channel is upstream of the impeller.
  • Strömungsumtechnischskanals is arranged at a distance from the impeller blades, which corresponds to at least one extension of the impeller blades in the direction of the impeller axis.
  • the inlet-side opening of the flow-bypass channel is arranged not to interfere with the gas volume flow in the inlet channel but due to its substantially parallel orientation to the inlet channel
  • Flow diversion channel is located in an area which is continuous to flow guide surfaces in the inlet channel upstream of the opening and flow guide surfaces downstream of the opening. This ensures the flow guide surfaces guide the gas volume flow past the inlet-side opening so that it undergoes substantially no disturbance.
  • the inlet channel-side opening of the flow diversion channel is located in a cylindrical surface to the impeller axis.
  • a particularly favorable solution further provides that the inlet channel-side opening of the flow bypass channel is formed circumferentially with respect to an impeller axis, that is completely circulates around the inlet channel and thus is able to supply a bypass flow on all outer sides of the outlet channel the gas flow or remove it.
  • an advantageous solution provides that the flow diversion channel in the region of the inlet-side opening deflects a bypass volume flow coming from the impeller-side opening so far that it exits into the inlet channel with a flow direction transverse to the flow direction of the entering gas volume flow. This ensures that the diversion volume flow is supplied with the least possible disturbance to the gas volume flow entering the inlet duct.
  • the flow diversion channel has flow deflection surfaces which deflect the bypass volumetric flow exiting from the flow diversion channel in a direction transverse to the gas volume flow entering the inlet duct.
  • the flow diversion channel of the turbocompressor is configured in such a way that it promotes a bypass volumetric flow from the impeller-side opening to the inlet-side opening in the partial load range.
  • the flow diversion channel is designed so that it is able to carry more than 20% of the gas volume flow flowing to the impeller in the partial load operation.
  • a solution according to the invention of the aforementioned object provides, as an alternative or in addition to the solutions described so far, that the flow diversion channel allows a partial load operation of the turbocompressor in gas flow rates that lie between 40% of the gas volume flow provided in the design point and the gas volume flow in the design point.
  • bypass flow rate and in particular the direction of the bypass volumetric flow set according to a pressure difference between the impeller-side opening and the inlet-side opening in the flow-diversion duct and that only this pressure difference for the direction and the thickness of the Diverting flow is responsible.
  • the object according to the invention can be advantageously achieved in a further exemplary embodiment in that the flow diversion channel can be closed by a closure unit.
  • a closure unit makes it possible to influence both the occurrence of a diversion volume flow and its strength and, indirectly, its direction.
  • this creates the possibility to prevent a bypass flow from the inlet-side opening to the impeller-side opening, as may occur especially at Studentslasszuexn above the design point or at the design point or near the design point, depending on how in detail the pressure conditions in the Turbo compressor are set.
  • the closure unit can be designed in various ways.
  • a solution provides that the closure unit has a spring-loaded valve element, so that the closure unit acts independently and thus acts, for example, to always allow a diversion volume flow from the impeller-side opening to the inlet-side opening, but a bypass volume flow from the inlet-side opening to the impeller-side opening, regardless of what the pressure difference between the inlet-side opening and the impeller-side opening is.
  • the spring-loaded valve element is designed as a so-called flutter valve, that is formed by thin metal plates, which can bend to open, but remain when closing in its unbent state and rest for example on correspondingly provided surfaces.
  • closure unit has a controllable closure element.
  • Such a controllable closure element is thus not designed so that it automatically closes when a bypass flow which is to be suppressed, but formed so that this is controlled.
  • controllable closure element can be formed in a variety of ways and in the turbocompressor, for example, either in Strömungsum glaciskanal itself or one of the openings of the
  • the controller can not only provide that this closure element is either open or closed, but can also advantageously provide that the closure element, the strength of the bypass volume flow, if this is even allowed, additionally controls ,
  • controllable closure element can then be controlled in such a way that it allows a diversion flow when it improves or favors the operation of the turbocompressor, but suppresses a bypass flow in all other cases.
  • flow instabilities in the turbocompressor can also be detected by suitable pressure measurements, and it is also possible to detect the occurrence of flow instabilities by means of such pressure measurements and then to control the bypass volume flow accordingly.
  • FIG. 1 shows a longitudinal section through a first embodiment of a turbocompressor according to the invention.
  • Fig. 2 is a side view of an impeller of the invention
  • FIG. 3 is an enlarged longitudinal section of FIG. 1 in the region of an inlet housing and an impeller housing;
  • Fig. 4 shows a schematic representation of a compressor characteristic in a turbocompressor according to the invention
  • Fig. 5 is a further enlarged view of a portion of
  • Impeller housing and the inlet housing in particular in the region of a flow diversion channel
  • Fig. 6 is a section along line 6-6 in Fig. 3;
  • Fig. 7 is a section along line 7-7 in Fig. 3;
  • Fig. 8 is a section along line 8-8 in FIG. 3;
  • Fig. 9 is a section along line 9-9 in FIG. 3;
  • Fig. 10 is a section similar to FIG. 5 through a second embodiment of a turbocompressor according to the invention.
  • FIG. 11 is a further enlarged section of FIG. 10 in the
  • FIG. 12 is a section similar to FIG. 11 through a third embodiment of a turbocompressor according to the invention.
  • FIG. 13 is a section similar to FIG. 9 through the third embodiment.
  • FIG. 14 is a section similar to FIG. 10 through a fourth embodiment of a turbocompressor according to the invention.
  • FIG. 15 is a section similar to FIG. 11 through the fourth embodiment.
  • An in Fig. 1 illustrated embodiment of a turbocompressor according to the invention comprises a designated as a whole by 10 compressor housing, which comprises an inlet housing 12, an impeller housing 14 and an outlet housing 16.
  • the inlet housing 10 forms at least in part an inlet channel 22, which merges into an impeller channel 24 in the impeller housing 14 and this in turn merges into an outlet channel 26 in the outlet housing 16.
  • an impeller channel 24 in the impeller housing 14 and this in turn merges into an outlet channel 26 in the outlet housing 16.
  • the impeller 24 a designated as a whole with 30 impeller is provided which, as shown in FIG. 2, a hub body 32 on which impeller vanes 34 and 36 are disposed, the impeller vanes 34 being so-called long impeller vanes, whose inlet passage side ends 38 extend in the direction parallel to an impeller axis 40 further upstream toward the intake passage 22 inlet-side ends 42 of the so-called short impeller blades 36.
  • the impeller 30 is driven by a drive motor 50, on the motor shaft 52, the impeller 30 is seated with its hub body 32, the hub body 32 is connected to the impeller blades 34, 36 opposite bottom with the motor shaft 52 and carried and guided by the motor shaft 52 ,
  • the drive motor 50 is a typical high-revving drive motor for a turbocompressor, which has, for example, magnetic bearings for the motor shaft 52.
  • the inlet channel 22 leads to a gas volume flow 58 which, due to the narrowing inlet channel cross-sectional area, propagates with increasing speed towards the impeller 30 and through whose impeller blades 34 and 36 the gas volume flow 58 in the impeller channel 24 is increasingly compressed
  • Turbo compressor according to the in Fig. 4 compressor characteristic is shown, which represents the pressure increase above the gas flow.
  • the design of the turbocompressor that is to say in particular also of the impeller 30 and the inlet duct 22, of the impeller duct 24 and of the outlet duct 26 takes place with reference to a design point A of the embodiment shown in FIG. 4
  • the turbocompressor according to the invention should not only be operated in the region of the design point A, but also be operated at lower gas flow rates 58, where, as is apparent from the compressor curve, the pressure increase is greater than in the design point A and the gas flow 58, however, also noteworthy is lower.
  • a flow diversion channel 60 extending in both the impeller housing 14 and in the inlet housing 12 is provided, which is arranged around a portion of the inlet channel 22 and around a portion of the impeller 24 in each case radially around the latter and, as shown in FIG , 3, extends from an impeller-side opening 62 to an inlet-side opening 64, wherein a bypass volumetric flow 66 is formed in the flow-diversion channel 60, the direction and magnitude of which is dependent on the pressure difference between the impeller-side opening 62 and the inlet-side opening 64. If, for example, as shown in FIG.
  • the turbocompressor is operated with a gas flow 58 which is lower than the gas flow 58 at design point A, that is, at part-load operation, at the impeller-side opening 62 of the flow bypass duct 60, a higher pressure than at the inlet-side opening 64 exists and thus, a bypass flow 66a is formed through the flow bypass passage 60 such that the bypass flow 66a flows from the impeller side opening 62 to the inlet side opening 64, thereby passing therethrough to enter the inlet passage 22.
  • the flow diversion channel 60 is thereby limited by a radially inner wall 72 of the impeller housing 14 and the inlet housing 12 with respect to the impeller axis 40 and a radially outer wall 74 of the impeller housing 14 and the inlet housing 12, wherein the radially inner wall 72 at the same time an end portion 76 of the Inlet duct 22 forms, which merges into the impeller 24.
  • the end section 76 preferably lies between the inlet-side opening 64 of the flow-diversion channel 60 and the hub body 32 of the impeller 30.
  • the end portion 76 of the inlet channel 22 is in the region of a plane El, which is perpendicular to the impeller axis 40 and the hub body 32 contacts at its inlet-side upper portion 78, in the impeller passage 24 via.
  • end portion 76 preferably lies between the inlet-side opening 64 of the flow-bypass channel 60 and the plane El, and has a flow-guiding surface 78 which continuously merges into a surface 80 in which the inlet-side opening 64 lies.
  • the inlet channel 22 comprises a flow guide surface 81 of the up to the inlet-side opening 64 of the flow diversion channel 60 is guided.
  • the arranged in the radially inner wall 72 impeller-side opening 62 of the flow diversion channel 60 lies in a surface 82 which is continuous in an upstream of the impeller-side opening 62
  • Flow guide surface 84 of the impeller 24 and downstream adjacent flow guide surface 86 of the impeller 24 passes.
  • the impeller side opening 62 is arranged to lie in the direction of the impeller shaft 40 between the inlet side end 38 of the long impeller blades 34 and the inlet side end 42 of the shorter impeller blades 36 (FIG. 5).
  • Impeller side opening 62 is provided in the above-mentioned area to provide the possibility that, at a gas flow rate lower than the gas volume flow at the design point A, these forming vortices will not pass through Impeller channel 24
  • a bypass flow 66 exiting through the impeller-side opening 62 strikes a deflection surface 90 formed by the radially outer wall 74, which deflects the bypass flow 66a in the direction of the inlet-side opening 64, so that this between the radially inner wall 72 and the radial outer wall 74 in the direction of the inlet-side opening 64 flows and before reaching the inlet-side opening 64 by a deflection surface 92, also in turn formed by the radially outer wall 74, so deflected is that the exiting deflection volume flow 66a has a flow direction 96 which is transverse to a flow direction 100, with which the incoming gas volume flow 58 flows in the inlet channel 22 in the direction of the impeller 30.
  • Such a bypass volumetric flow 66a occurs when the pressure at the impeller-side opening 62 is greater than at the inlet-side opening 64, so that due to the pressure difference in the inlet channel 22 entering gas volume flow 58 enters a part as bypass flow 66a in the impeller-side opening 62 and flows into the inlet side opening 64 via the flow bypass passage 60.
  • the inlet-side opening 64 is in particular arranged such that it lies in a geometrical surface 102 which is continuously adjacent to an upstream surface 104 and a downstream surface 106 and thus does not cause a gas volume flow 58 entering the inlet duct 22.
  • surfaces 102, 104, and 106 are cylindrical surfaces that are coaxial with impeller axis 40.
  • bypass volumetric flow 66a in particular in operating states with lower gas volume flows 58 than provided for the design point, is favored by the arrangement of the inlet-side openings 64 of the flow diversion channel 60, since the gas volume flow 58 entering via the inlet channel 22 is characterized by the arrangement of the inlet side Opening 64 in the coaxial with the impeller axis 40 cylindrical surface 80 causes no congestion and thus no pressure increase in the inlet-side opening 64, so that in the region of the inlet-side opening 64, the bypass flow 66 counteracting effects occur.
  • bypass volumetric flow 66a passes through the inlet-side opening 64 with a flow direction 96 that extends transversely to the impeller axis 40 causes this bypass volumetric flow 66a to be mixed with the gas volumetric flow 58 entering through the inlet channel 22, so that the two together enter the impeller duct 24 enter, possibly even accelerated by the narrowing in its cross-section end portion 76 of the inlet channel 22nd
  • such a diversion volume flow 66a is further facilitated by the fact that the flow diversion channel 60 at its inlet-side opening 64 provides a flow cross-sectional area which is more than 2.5 times the flow cross-section of the impeller-side opening 62 and in that In addition, the Strömungsumtechnischskanal 60 from the impeller-side opening 62 to the inlet-side opening 64 is steadily increased.
  • deceleration of the bypass volumetric flow 66a as it flows through the flow bypass passage 60 from the impeller side opening 62 to the inlet side opening 64 occurs such that the flow rate of the bypass volumetric flow 66a exiting the inlet side port 64 is approximately equal to the flow rate of the gas volumetric flow entering the inlet duct 22.
  • Such a design of the flow diversion channel 60 results in that the turbo compressor from the in FIG. 4 can be operated at partial load operation still at a gas flow rate 58, which is significantly below the design point A.
  • the compressor without a pump that is Vibrations due to flow instabilities in the gas flow, occurring, can be operated up to a gas volume flow which is up to 60% below the design for the design point A gas volume flow.
  • the flow redirecting channel 60 is divided in the direction of rotation 110 by ribs 112 extending in radial planes 111 to the rotor axis 40, such that the flow redirecting channel 60 is characterized by a sum in the circumferential direction 110 consecutive channel segments 114 is formed, which are closed on both sides by the ribs 112, whereby the bypass flow 66a in the region of the inlet-side opening 64 with its flow direction 96 has substantially no component in the circumferential direction 110 and thus substantially transverse to the impeller axis 40,
  • the turbocompressor according to the invention can also, as shown in FIG. 4, are operated in the overload range at gas flow rates that are above the design point A, in these cases, with increasing relative to the design point A larger gas flow 58, the pressure at the impeller-side opening 62 is lower and thus raises a pressure difference between the impeller-side opening 62 and the inlet-side opening 64, which causes the flow bypass passage 60 is flowed through by a bypass volumetric flow 66 b, which flows from the inlet-side opening 64 to the impeller-side opening 62, that is from the gas volume flow 58 entering through the inlet channel 22 in the region of the inlet-side opening 64th is branched, flows through the flow diversion channel 60 and enters via the impeller-side opening 62 in the impeller 24 and there is further compressed by the impeller 30.
  • bypass volumetric flow 66 b is not favored by the orientation of the inlet-side opening 64, but rather impeded, since such a bypass volumetric flow 66 b transverse to the impeller axis 40 Inlet passage 22 must leave in the region of the inlet-side opening 64 to enter the flow bypass channel 60.
  • turbocompressor according to the invention at the design point A is designed so that there is no pressure difference at this between the inlet-side opening 64 and the impeller-side opening 62, so that no diversion volume flow 66 is formed.
  • a diversion volume flow 66a begins with reducing the gas flow rate 58, based on the gas flow rate 58 at the design point slowly and increases with increasing reduction of the gas flow rate 58, so that the turbo-compressor can still be operated at a gas flow rate 58 without pumping at Values of 40% of the gas flow rate 58 at the operating point A. In this case, the diverting flow will account for approximately 30% of the
  • the flow diversion channel 60 is associated with a closure unit 120, which is designed as a flutter valve 122.
  • Flutter valve 122 includes a fin element 124 held in inlet housing 12, with fin element 124 closing flow diversion channel 60 (drawn solid line) when in flight Diverting flow 66b would occur due to the pressure difference, so that a bypass flow 66b can not occur.
  • the fin element 124 opens and leaves such
  • undesirable bypass flow 66b would occur due to the pressure difference, however, is prevented automatically by the flutter valve 122 and only in the partial load range of the desired bypass flow 66a may occur.
  • closure unit 120 comprises two superimposed
  • Lock rings 132 and 134 each having a plurality of ring segments, with closure segments 136 and breakaway segments 138 alternating.
  • the locking rings 132, 134 can be, for example, by turning the
  • Locking ring 134 are rotated to each other so that the closure segments 136 of a closure ring 134, the breakthrough segments 138 of the other closure ring 132 covers, or are rotated to each other so that the closure segments 136 and the breakthrough segments 138 of both closure rings 132, 134 are superimposed, so that through one breakthrough volume flow 66 can pass through one another lying breakthrough segments.
  • Allow bypass flow 66 or prohibit In particular, a diverting volume flow 66a will be permitted in partial load operation and a diversion flow 66b will be prevented in operation near design point A or above design point A.
  • the position of the closure ring 134 relative to the closure ring 132 with a controller 140 and an actuator 142 is controllable, so that, for example, depending on the controller 140, for example via sensors detected pressure difference between the inlet side opening 64 and the impeller side opening 62, a control of the bypass flow 66 also can still be done in terms of its strength according to the pressure and flow conditions and flow instabilities and optionally the speed of the impeller.
  • a sliding sleeve 150 is provided in the inlet housing 12, for example guided on the cylindrical surface 104, as a closure unit 120 ", which - as in FIG. 14
  • the sliding sleeve 150 is also preferably controllable by the actuator 142 'and the controller 140' as a function of pressure and flow conditions in turbocompressors, as described in connection with the third embodiment.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Life Sciences & Earth Sciences (AREA)
  • Sustainable Development (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)

Abstract

L'invention concerne un turbocompresseur comportant un boîtier de compresseur dans lequel un flux volumique de gaz entrant est acheminé vers un canal de roue à aubes à travers un canal d'entrée, est comprimé dans le canal de roue à aubes par la roue à aubes et est évacué du canal de roue à aubes par un canal de sortie, et un canal de déviation de flux prévu dans le boîtier de compresseur, s'étendant en dehors du canal de roue à aubes et du canal d'entrée, aboutissant avec une ouverture côté entrée dans le canal d'entrée et avec une ouverture côté roue à aubes dans le canal de roue à aubes, et guidant un flux volumique de déviation en fonction d'une différence de pression entre les ouvertures. L'invention vise à améliorer un tel turbocompresseur de telle manière qu'il fonctionne de façon optimale avec des flux volumiques nettement inférieurs au flux volumique pour lequel le turbocompresseur à été conçu. A cet effet, le canal de déviation de flux présente une surface de section transversale de flux qui augmente de l'ouverture côté roue à aubes jusqu'à l'ouverture côté entrée.
EP10795284.8A 2009-12-16 2010-12-09 Turbocompresseur Active EP2513488B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE102009054771A DE102009054771A1 (de) 2009-12-16 2009-12-16 Turboverdichter
PCT/EP2010/069320 WO2011082942A2 (fr) 2009-12-16 2010-12-09 Turbocompresseur

Publications (2)

Publication Number Publication Date
EP2513488A2 true EP2513488A2 (fr) 2012-10-24
EP2513488B1 EP2513488B1 (fr) 2016-07-20

Family

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Family Applications (1)

Application Number Title Priority Date Filing Date
EP10795284.8A Active EP2513488B1 (fr) 2009-12-16 2010-12-09 Turbocompresseur

Country Status (6)

Country Link
US (1) US8926264B2 (fr)
EP (1) EP2513488B1 (fr)
CN (1) CN102695881B (fr)
DE (1) DE102009054771A1 (fr)
HK (1) HK1171491A1 (fr)
WO (1) WO2011082942A2 (fr)

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US10309417B2 (en) 2017-05-12 2019-06-04 Borgwarner Inc. Turbocharger having improved ported shroud compressor housing
US10316859B2 (en) 2017-05-12 2019-06-11 Borgwarner Inc. Turbocharger having improved ported shroud compressor housing
DE102017221717A1 (de) * 2017-12-01 2019-06-06 Man Energy Solutions Se Radialverdichter
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Publication number Publication date
US8926264B2 (en) 2015-01-06
WO2011082942A2 (fr) 2011-07-14
EP2513488B1 (fr) 2016-07-20
CN102695881B (zh) 2016-03-09
WO2011082942A3 (fr) 2011-12-01
CN102695881A (zh) 2012-09-26
HK1171491A1 (zh) 2013-03-28
US20130058762A1 (en) 2013-03-07
DE102009054771A1 (de) 2011-06-22

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