US20160238012A1 - Adjustable-inlet radial-radial compressor - Google Patents

Adjustable-inlet radial-radial compressor Download PDF

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Publication number
US20160238012A1
US20160238012A1 US14/624,618 US201514624618A US2016238012A1 US 20160238012 A1 US20160238012 A1 US 20160238012A1 US 201514624618 A US201514624618 A US 201514624618A US 2016238012 A1 US2016238012 A1 US 2016238012A1
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US
United States
Prior art keywords
radial
compressor
tubular sleeve
compressor wheel
inlet
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.)
Abandoned
Application number
US14/624,618
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English (en)
Inventor
Milan Nejedly
Vit Houst
Daniel Turecek
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.)
Honeywell International Inc
Original Assignee
Honeywell International Inc
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 Honeywell International Inc filed Critical Honeywell International Inc
Priority to US14/624,618 priority Critical patent/US20160238012A1/en
Assigned to HONEYWELL INTERNATIONAL INC. reassignment HONEYWELL INTERNATIONAL INC. ASSIGNMENT OF ASSIGNORS INTEREST (SEE DOCUMENT FOR DETAILS). Assignors: Houst, Vit, Nejedly, Milan, Turecek, Daniel
Priority to EP16155122.1A priority patent/EP3059452A1/fr
Priority to CN201610088446.3A priority patent/CN105889085A/zh
Publication of US20160238012A1 publication Critical patent/US20160238012A1/en
Abandoned legal-status Critical Current

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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
    • F04D27/00—Control, e.g. regulation, of pumps, pumping installations or pumping systems specially adapted for elastic fluids
    • F04D27/002—Control, e.g. regulation, of pumps, pumping installations or pumping systems specially adapted for elastic fluids by varying geometry within the pumps, e.g. by adjusting vanes
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D17/00—Regulating or controlling by varying flow
    • F01D17/10—Final actuators
    • F01D17/12—Final actuators arranged in stator parts
    • F01D17/14—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits
    • F01D17/141—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits by means of shiftable members or valves obturating part of the flow path
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
    • F02C7/04—Air intakes for gas-turbine plants or jet-propulsion plants
    • F02C7/042—Air intakes for gas-turbine plants or jet-propulsion plants having variable geometry
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D17/00—Radial-flow pumps, e.g. centrifugal pumps; Helico-centrifugal pumps
    • F04D17/08—Centrifugal pumps
    • F04D17/10—Centrifugal pumps for compressing or evacuating
    • 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
    • F04D27/0246—Surge control by varying geometry within the pumps, e.g. by adjusting vanes
    • 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
    • F04D27/0253—Surge control by throttling
    • 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
    • F04D29/05—Shafts or bearings, or assemblies thereof, specially adapted for elastic fluid pumps
    • F04D29/053—Shafts
    • 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
    • F04D29/26—Rotors specially for elastic fluids
    • F04D29/28—Rotors specially for elastic fluids for centrifugal or helico-centrifugal pumps for radial-flow or helico-centrifugal pumps
    • F04D29/284—Rotors specially for elastic fluids for centrifugal or helico-centrifugal pumps for radial-flow or helico-centrifugal pumps for compressors
    • 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
    • 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
    • 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
    • F04D29/46—Fluid-guiding means, e.g. diffusers adjustable
    • F04D29/462—Fluid-guiding means, e.g. diffusers adjustable especially adapted for elastic fluid pumps
    • F04D29/464—Fluid-guiding means, e.g. diffusers adjustable especially adapted for elastic fluid pumps adjusting flow cross-section, otherwise than by using adjustable stator blades
    • 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
    • F05D2220/00—Application
    • F05D2220/40—Application in turbochargers
    • 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
    • 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
    • F05D2260/00—Function
    • F05D2260/50—Kinematic linkage, i.e. transmission of position
    • F05D2260/53—Kinematic linkage, i.e. transmission of position using gears
    • 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
    • F05D2270/00—Control
    • F05D2270/01—Purpose of the control system
    • F05D2270/10—Purpose of the control system to cope with, or avoid, compressor flow instabilities
    • F05D2270/101—Compressor surge or stall
    • 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
    • F05D2270/00—Control
    • F05D2270/60—Control system actuates means
    • F05D2270/66—Mechanical actuators

Definitions

  • the present disclosure relates to radial-radial compressors, such as used in turbochargers, and more particularly relates to radial-radial compressors in which the effective inlet area can be adjusted for different operating conditions.
  • An exhaust gas-driven turbocharger is a device used in conjunction with an internal combustion engine for increasing the power output of the engine by compressing the air that is delivered to the air intake of the engine to be mixed with fuel and burned in the engine.
  • a turbocharger comprises a compressor wheel mounted on one end of a shaft in a compressor housing and a turbine wheel mounted on the other end of the shaft in a turbine housing.
  • the turbine housing is formed separately from the compressor housing, and there is yet another center housing connected between the turbine and compressor housings for containing bearings for the shaft.
  • the turbine housing defines a generally annular chamber that surrounds the turbine wheel and that receives exhaust gas from an engine.
  • the turbine assembly includes a nozzle that leads from the chamber into the turbine wheel.
  • the exhaust gas flows from the chamber through the nozzle to the turbine wheel and the turbine wheel is driven by the exhaust gas.
  • the turbine thus extracts power from the exhaust gas and drives the compressor.
  • the compressor receives ambient air through an inlet of the compressor housing and the air is compressed by the compressor wheel and is then discharged from the housing to the engine air intake.
  • Turbochargers can employ a compressor wheel of the radial-radial type because radial-radial compressors can achieve relatively high pressure ratios in a compact arrangement.
  • Intake air for a radial-radial compressor is received in a generally axial direction approaching the wheel but before the air reaches the inducer portion of the wheel the air is turned substantially 90 degrees to proceed generally radially outwardly into the inducer portion.
  • the air passes through the blades of the compressor and is compressed, and is then discharged in a generally radial direction from an exducer portion of the wheel.
  • the compressed air from the wheel is delivered to a volute, and from the volute the air is supplied to the intake of an internal combustion engine.
  • the operating range of the compressor is an important aspect of the overall performance of the turbocharger.
  • the operating range is generally delimited by a surge line and a choke line on an operating map for the compressor.
  • the compressor map is typically presented as pressure ratio (discharge pressure P out divided by inlet pressure P in ) on the vertical axis, versus corrected mass flow rate on the horizontal axis.
  • the choke line on the compressor map is located at high flow rates and represents the locus of maximum mass-flow-rate points over a range of pressure ratios; that is, for a given point on the choke line, it is not possible to increase the flow rate while maintaining the same pressure ratio because a choked-flow condition occurs in the compressor.
  • the surge line is located at low flow rates and represents the locus of minimum mass-flow-rate points without surge, over a range of pressure ratios; that is, for a given point on the surge line, reducing the flow rate without changing the pressure ratio, or increasing the pressure ratio without changing the flow rate, would lead to surge occurring.
  • Surge is a flow instability that typically occurs when the compressor blade incidence angles become so large that substantial flow separation arises on the compressor blades. Pressure fluctuation and flow reversal can happen during surge.
  • compressor surge may occur when the engine is operating at high load or torque and low engine speed, or when the engine is operating at a low speed and there is a high level of exhaust gas recirculation (EGR). Surge can also arise when an engine is suddenly decelerated from a high-speed condition. Expanding the surge-free operation range of a compressor to lower flow rates is a goal often sought in compressor design.
  • EGR exhaust gas recirculation
  • the present disclosure describes mechanisms and methods for a radial-radial compressor that can enable the surge line for the compressor to selectively be shifted to the left (i.e., surge is delayed to a lower flow rate at a given pressure ratio), by adjusting the effective area at the inducer portion of the wheel.
  • One embodiment described herein comprises a radial-radial compressor having the following features:
  • the compressor housing defining an air inlet for leading air in a generally axial direction toward the radial-radial compressor wheel and defining a shroud surface that is adjacent to the outer tips of the blades, the hub of the radial-radial compressor wheel being configured to cooperate with the shroud surface to cause air proceeding through the air inlet to be turned substantially 90 degrees toward a generally radially outward direction relative to a rotational axis of the radial-radial compressor wheel, the blades defining an inducer portion arranged to receive air proceeding in the generally radially outward direction, the compressor housing further defining a volute for receiving compressed air discharged generally radially outwardly from the radial-radial compressor wheel; and
  • an inlet-adjustment mechanism disposed in the air inlet upstream of the radial-radial compressor wheel and movable between an open or “on” position and a closed or “off” position for adjusting an effective area at the inducer portion of the radial-radial compressor wheel.
  • the inlet-adjustment mechanism comprises a tubular sleeve that is movable within the air inlet with an axial component of movement.
  • the tubular sleeve has a trailing edge spaced by a spacing distance upstream from the compressor wheel.
  • the axial movement of the tubular sleeve adjusts the spacing distance of the trailing edge from the compressor wheel. In the closed or “off” position of the inlet-adjustment mechanism, the spacing distance is relatively smaller; in the open or “on” position, the spacing distance is relatively greater.
  • the spacing distance in the “on” position is such that an effective inlet area into the inducer portion of the compressor wheel is defined by the hub of the compressor wheel and the shroud surface of the compressor housing—i.e., the tubular sleeve does not prevent the air from following the shroud surface and thus does not have an effect on the effective inlet area, or has a relatively minor effect.
  • the spacing distance in the “off” position is such that the effective inlet area into the inducer portion of the compressor wheel is reduced relative to that in the “on” position—i.e., the tubular sleeve extends into the flow path at the point where the air turns to proceed generally radially outwardly, so as to prevent the air from following the shroud surface of the compressor housing, and hence the effective inlet area is defined between the hub and the trailing edge of the tubular sleeve.
  • the tubular sleeve of the inlet-adjustment mechanism can be actuated in any of various ways, and the present invention is not limited to any particular actuation system.
  • the tubular sleeve defines an external helical first thread.
  • the actuation system includes a drive cog having a helical drive thread that is meshed with the first thread of the sleeve.
  • the drive cog is rotatable about its axis but is constrained against axial movement, such that rotation of the drive cog imparts a screw motion (i.e., combined rotational and axial motion) to the tubular sleeve.
  • the tubular sleeve also defines an external helical second thread axially spaced from the first thread, and the sleeve is threaded into a nut having a corresponding internal thread that is meshed with the second thread of the sleeve.
  • the internal thread of the nut is substantially coaxial with the compressor wheel. The nut helps to guide the motion of the sleeve and keep the sleeve substantially coaxial with the compressor wheel.
  • a linear axially extending rack is defined by or secured on the tubular sleeve, the rack defining axially spaced teeth.
  • the actuation system includes a drive pinion whose rotational axis extends perpendicular to the axial direction, the drive pinion having teeth meshed with the teeth of the rack. Rotation of the drive pinion imparts a purely axial motion to the tubular sleeve. Thus, rotation of the drive pinion in one direction moves the tubular sleeve toward the “off” position and rotation in the opposite direction moves the tubular sleeve toward the “on” position.
  • actuation systems that work on different principles can also be used.
  • a pneumatic or hydraulic actuation system can be used.
  • FIG. 1 is a perspective view of a radial-radial compressor in accordance with a first embodiment of the invention, with a portion of the compressor housing cut away to show internal details, wherein the inlet-adjustment mechanism is in the “off” position;
  • FIG. 2 is an axial cross-sectional view of the radial-radial compressor of FIG. 1 , with the inlet-adjustment mechanism in the “off” position;
  • FIG. 3 is a view similar to FIG. 1 , but with the inlet-adjustment mechanism in the “on” position;
  • FIG. 4 is a perspective view of a radial-radial compressor in accordance with a second embodiment of the invention.
  • FIG. 5 is an axial cross-sectional view of the compressor of FIG. 4 , with the inlet-adjustment mechanism in the “off” position;
  • FIG. 6 is a view similar to FIG. 5 , but with the inlet-adjustment mechanism in the “on” position.
  • a radial-radial compressor 10 in accordance with one embodiment of the invention is illustrated in perspective view in FIG. 1 , and in cross-sectional view in FIGS. 2 and 3 .
  • the turbocharger comprises a radial-radial compressor wheel 14 mounted in a compressor housing 16 on one end of a rotatable shaft (not shown).
  • the compressor housing defines an air inlet 17 for leading air generally axially toward the compressor wheel 14 .
  • the shaft of the compressor wheel is supported in bearings (not shown) and the shaft is rotated by a turbine wheel or an electric motor or other means (not shown) coupled to the shaft, thereby rotatably driving the compressor wheel, which compresses air drawn in through the compressor inlet and discharges the compressed air generally radially outwardly from the compressor wheel into a volute 21 for receiving the compressed air.
  • the air can be used for any of various purposes, such as being supplied to the intake of an internal combustion engine (not shown) for boosting the performance of the engine.
  • the compressor wheel 14 includes a hub 14 h and a plurality of blades 14 b joined to the hub and extending therefrom and terminating at outer tips of the blades.
  • the compressor housing 16 defines a shroud surface 16 s that is closely adjacent to the outer tips of the compressor blades.
  • the shroud surface 16 s defines a curved contour that is generally parallel to the curved contour of the compressor wheel.
  • the wheel hub 14 h and the shroud surface 16 s cooperate to define a flow path between them, which flow path is configured so as to lead air in a generally radially outward direction as the air encounters the inducer portion 14 i of the compressor wheel.
  • the air proceeds radially outwardly and is compressed as it progresses through the passages defined between the blades 14 b , the air then being discharged outwardly into the volute 21 .
  • the compressor of the turbocharger includes an inlet-adjustment mechanism disposed in the air inlet 17 of the compressor housing just upstream of the shroud surface 16 s and inducer portion 14 i .
  • the inlet-adjustment mechanism comprises a tubular sleeve 30 having an inside diameter selected with reference to the inducer portion 14 i of the compressor wheel 14 .
  • the mechanism 30 is movable, with an axial component of movement, between a closed or “off” position ( FIGS. 1 and 2 ) and an open or “on” position ( FIG. 3 ) for adjusting the effective inlet area at the inducer portion of the radial-radial compressor.
  • the sleeve 30 can move purely axially (i.e., with no rotational component of movement) or can move both axially and rotationally (i.e., like a screw). In the particular embodiment of FIGS. 1-3 , the motion of the sleeve is a screw motion, but a second embodiment is described below that undergoes purely axial motion.
  • the sleeve 30 has a trailing edge 30 t spaced by a spacing distance upstream from the compressor wheel 14 . The axial movement of the sleeve is effective to adjust the spacing distance of the trailing edge 30 t from the compressor wheel.
  • the spacing distance 30 t is relatively smaller as shown in FIG. 2 .
  • the spacing distance in the “off” position is such that an effective inlet area A eff,off into the inducer portion 14 i of the compressor wheel is reduced relative to that in the “on” position by virtue of the sleeve 30 extending into the flow path at a point where the air in the “on” position would turn to proceed generally radially outwardly, so as to prevent the air from following the shroud surface 16 s of the compressor housing, such that the effective inlet area A eff,off is defined between the hub 14 h and the trailing edge 30 t of the sleeve 30 .
  • the spacing distance between the wheel 14 and the sleeve trailing edge 30 t is relatively greater.
  • the spacing distance in the “on” position is such that the air is generally able to turn toward the radially outward direction and follow the shroud surface 16 s .
  • an effective inlet area A eff,on into the inducer portion 14 i of the compressor wheel is defined by the hub 14 h of the compressor wheel and the shroud surface 16 s of the compressor housing.
  • the inlet-adjustment sleeve 30 can be positioned in the “off” position for setting the effective inlet area into the compressor wheel at a minimum value.
  • the sleeve 30 can be positioned in the “on” position for increasing the effective inlet area.
  • the sleeve 30 can also be positioned at any of various intermediate positions between the “off” and “on” positions, if so desired (e.g., for intermediate flow rates), in order to permit a range of inlet area adjustments for the radial-radial compressor.
  • the tubular sleeve 30 is actuated by a lead-screw type actuation system.
  • the tubular sleeve 30 defines an external helical first thread 32 .
  • the actuation system includes a drive cog 40 having a helical drive thread 42 that is meshed with the first thread 32 of the sleeve.
  • the drive cog 40 is rotatable about its axis but is constrained against axial movement, such that rotation of the drive cog imparts a screw motion (i.e., combined rotational and axial motion) to the tubular sleeve 30 .
  • rotation of the drive cog 40 in one direction moves the tubular sleeve 30 toward the “off” position ( FIGS. 1 and 2 ) and rotation in the opposite direction moves the tubular sleeve toward the “on” position ( FIG. 3 ).
  • the tubular sleeve 30 also defines an external helical second thread 34 axially spaced from the first thread 32 , and the sleeve is threaded into a nut 50 having a corresponding internal thread 54 that is meshed with the second thread 34 of the sleeve.
  • the internal thread 54 of the nut is substantially coaxial with the compressor wheel 14 .
  • the nut 50 helps to guide the motion of the sleeve and keep the sleeve substantially coaxial with the compressor wheel.
  • the actuation system comprises a rack-and-pinion system.
  • a linear rack 60 is provided or defined on the tubular sleeve 30 , extending axially along the sleeve.
  • the rack defines axially spaced teeth 62 .
  • the actuation system includes a drive pinion 70 whose rotational axis extends perpendicular to the axial direction, the drive pinion having teeth 72 meshed with the teeth 62 of the rack.
  • Rotation of the drive pinion 70 imparts a purely axial motion to the tubular sleeve 30 .
  • rotation of the drive pinion in one direction moves the tubular sleeve toward the “off” position ( FIGS. 4 and 5 ) and rotation in the opposite direction moves the tubular sleeve toward the “on” position ( FIG. 6 ).
  • the effective inlet area A eff into the inducer portion 14 i of the compressor wheel is variable by positioning the tubular sleeve 30 in various axial positions having different spacing distances between the sleeve's trailing edge 30 t and the compressor wheel 14 . In this manner, the effective inlet area of the compressor can be adjusted depending on operating conditions substantially as in the first embodiment.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Physics & Mathematics (AREA)
  • Geometry (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
US14/624,618 2015-02-18 2015-02-18 Adjustable-inlet radial-radial compressor Abandoned US20160238012A1 (en)

Priority Applications (3)

Application Number Priority Date Filing Date Title
US14/624,618 US20160238012A1 (en) 2015-02-18 2015-02-18 Adjustable-inlet radial-radial compressor
EP16155122.1A EP3059452A1 (fr) 2015-02-18 2016-02-10 Compresseur radial-radial à entrée réglable
CN201610088446.3A CN105889085A (zh) 2015-02-18 2016-02-17 可调入口的径向-径向压缩机

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US14/624,618 US20160238012A1 (en) 2015-02-18 2015-02-18 Adjustable-inlet radial-radial compressor

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US20160238012A1 true US20160238012A1 (en) 2016-08-18

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US14/624,618 Abandoned US20160238012A1 (en) 2015-02-18 2015-02-18 Adjustable-inlet radial-radial compressor

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US (1) US20160238012A1 (fr)
EP (1) EP3059452A1 (fr)
CN (1) CN105889085A (fr)

Cited By (5)

* Cited by examiner, † Cited by third party
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US20160222875A1 (en) * 2015-02-04 2016-08-04 Bullseye Power, LLC Tunable turbocharger compressor cover
US20170292441A1 (en) * 2016-04-11 2017-10-12 Hyundai Motor Company Device for variably controlling flow rate of intake air of turbocharger compressor
CN112524050A (zh) * 2020-11-04 2021-03-19 浙江工业大学 一种水动力推进装置
US11708841B2 (en) * 2019-09-18 2023-07-25 Massachusetts Institute Of Technology Adaptive volutes for centrifugal pumps
US11841173B2 (en) * 2018-06-28 2023-12-12 Danfoss A/S Variable stage compressors

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* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US10502126B2 (en) * 2017-03-10 2019-12-10 Garrett Transportation I Inc. Adjustable-trim centrifugal compressor for a turbocharger
CN111503027A (zh) * 2020-04-15 2020-08-07 广东广顺新能源动力科技有限公司 一种空压机内壁间隙的圆轨智能调节系统
CN111503015A (zh) * 2020-04-16 2020-08-07 广东广顺新能源动力科技有限公司 一种空压机内壁间隙的智能螺杆节流调节机构
CN111486106A (zh) * 2020-04-16 2020-08-04 广东广顺新能源动力科技有限公司 一种空压机内壁间隙的齿轮齿条智能调节机构
CN111503014A (zh) * 2020-04-16 2020-08-07 广东广顺新能源动力科技有限公司 一种空压机内壁间隙的智能凸轮节流调节机构

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