Classifications

• • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
  • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
  • F02B—INTERNAL-COMBUSTION PISTON ENGINES; COMBUSTION ENGINES IN GENERAL
  • F02B37/00—Engines characterised by provision of pumps driven at least for part of the time by exhaust
  • F02B37/12—Control of the pumps
  • F02B37/24—Control of the pumps by using pumps or turbines with adjustable guide 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
  • 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
• • 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
  • F01D1/00—Non-positive-displacement machines or engines, e.g. steam turbines
  • F01D1/24—Non-positive-displacement machines or engines, e.g. steam turbines characterised by counter-rotating rotors subjected to same working fluid stream without intermediate stator blades or the like
• • 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
  • F01D17/143—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 the shiftable member being a wall, or part thereof of a radial diffuser
• • 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
  • F01D17/16—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits by means of nozzle vanes
  • F01D17/165—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits by means of nozzle vanes for radial flow, i.e. the vanes turning around axes which are essentially parallel to the rotor centre line
• • 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
  • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
  • F01D5/005—Repairing methods or devices
• • 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
  • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
  • F02B—INTERNAL-COMBUSTION PISTON ENGINES; COMBUSTION ENGINES IN GENERAL
  • F02B37/00—Engines characterised by provision of pumps driven at least for part of the time by exhaust
  • F02B37/12—Control of the pumps
  • F02B2037/125—Control for avoiding pump stall or surge
• • 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
  • F05D2250/52—Outlet
• • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
  • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
  • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
  • Y02T10/00—Road transport of goods or passengers
  • Y02T10/10—Internal combustion engine [ICE] based vehicles
  • Y02T10/12—Improving ICE efficiencies

Definitions

• This disclosure relates to a component for turbochargers for internal combustion engines. More particularly, this disclosure relates to a retractable vane diffuser system for a radial or mixed flow compressor stage of a turbocharger.
• turbocharging includes increased power output, lower fuel consumption and reduced pollutant emissions.
• the turbocharging of engines is no longer primarily seen from a high power performance perspective, but is rather viewed as a means of reducing fuel consumption and environmental pollution on account of lower carbon dioxide (CO2) emissions.
• CO2 carbon dioxide
• a primary reason for turbocharging is using the exhaust gas energy to reduce fuel consumption and emissions.
• the combustion air is pre-compressed before being supplied to the engine.
• the engine aspirates the same volume of air-fuel mixture as a naturally aspirated engine, but due to the higher pressure, thus higher density, more air and fuel mass is supplied into the combustion chamber. Consequently, more fuel can be burned, so that the engine's power output increases relative to the speed and swept volume.
• turbocharging In exhaust gas turbocharging, some of the exhaust gas energy, which would normally be wasted, is used to drive a turbine wheel mounted on a shaft.
• the turbocharger returns some of this normally wasted exhaust energy back into the engine, contributing to the engine's efficiency and saving fuel.
• a compressor impeller which is mounted on the same shaft as the turbine wheel, draws in filtered ambient air, compresses it, and then supplies it to the engine.
• a turbocharger is a type of forced induction system used with internal combustion engines. Turbochargers deliver compressed air to an engine intake, allowing more fuel to be combusted, thus boosting an engine's horsepower without significantly increasing engine weight. Thus, turbochargers permit the use of smaller engines that develop the same amount of horsepower as larger, naturally aspirated engines. Using a smaller engine in a vehicle has the desired effect of decreasing the mass of the vehicle and enhancing fuel economy. Moreover, the use of turbochargers permits more complete combustion of the fuel delivered to the engine, which contributes to the highly desirable goal of a cleaner environment. Turbochargers include a turbine stage and a compressor stage.
• turbochargers typically include a turbine housing connected to the engine's exhaust manifold, a compressor housing connected to the engine's intake manifold, and a center bearing housing coupling the turbine and compressor housings together.
• a turbine wheel in the turbine housing is rotatably driven by an inflow of exhaust gas supplied from the exhaust manifold.
• a shaft rotatably supported in the center bearing housing connects the turbine wheel to a compressor wheel (an impeller) in the compressor housing so that rotation of the turbine wheel causes rotation of the compressor impeller.
• the shaft connecting the turbine wheel and the compressor impeller defines an axis of rotation.
• the compressor stage is designed to help increase the intake manifold air pressure and density to allow the engine cylinders to ingest a greater mass of air during each intake stroke.
• the compressor stage specifically the compressor housing, preferably includes a diffuser.
• the diffuser converts high- velocity airflow leaving the compressor impeller to lower velocity, higher pressure airflow.
• the diffuser is defined by two walls. One is called a hub wall and is closest to the center bearing housing of the turbocharger. The other is called a shroud wall. These two walls form a flow path for air as it leaves the compressor impeller and guides the airflow into a volute.
• Vanes in diffusers are known. Providing vanes in the diffuser can improve efficiency. Full vanes that extend fully between the shroud wall and the hub wall have been utilized. Slotted wall type diffusers where full vanes are accepted by slots in one of the walls are also known. Ribbed vanes that do not extend fully between the walls of the diffuser are also known.
• Vanes help control airflow at lower mass airflow, and can slow the onset of diffuser stall and surge caused by flow reversal.
• Traditional movable vanes are known as pivoting vanes.
• the walls of the diffuser can move to adjust the airflow over the vanes.
• Vaneless diffusers are also known. At higher mass airflows, vanes can block airflow through the diffuser. This occurs because a leading edge of the vanes causes a sonic shock. Under certain operating conditions, vanes blocking any airflow is not preferred. At higher mass airflows, a vaneless diffuser is more effective than at lower mass airflows; whereas, a ribbed wall can be more effective at lower mass airflow conditions.
• a turbocharger has a compressor impeller and a turbine wheel connected by a rotating shaft.
• the compressor impeller is operably connected and adjacent to a retractable vane diffuser system with vanes that retract into a wall of a diffuser and selectively extend from the wall of the diffuser into a flow path of the diffuser based on activation of the retractable vane diffuser system.
• the vanes can be fully retracted with a vane ring into a cavity in the wall of the diffuser when operation as a vaneless diffuser is desired to maximize flow capacity.
• the vanes can extend from the wall of the diffuser when the efficiency of vanes is beneficial, such as at lower mass airfiow conditions to increase efficiency and pressure ratio and to slow the onset of diffuser stall or surge.
• the retractable vane diffuser system improves operating characteristics of the compressor stage of the turbocharger and effectively and efficiently controls airfiow from the compressor impeller with these retractable vanes.
• Figure 1 is a cross-sectional partial side view of a compressor stage of a turbocharger
• Figure 2 is a cross-sectional side view of the compressor stage of the turbocharger showing vanes in each wall of a diffuser;
• Figure 3 is an end view of a portion of a vane ring relative to a compressor impeller; and Figure 4 is an end view of a portion of a vane ring with separate vanes adjacent to a compressor impeller according to another embodiment.
• a turbocharger for an internal combustion engine is generally understood to include a compressor stage 12.
• the compressor stage 12 of the turbocharger can include a compressor impeller 14 and a compressor housing 16.
• a rotating shaft is driven by a turbine wheel such that rotation of the turbine wheel causes rotation of the compressor impeller 14.
• the compressor housing 16 includes a diffuser 18 leading to a volute 20.
• the compressor impeller 14 is mounted on one end of the shaft and is housed within the compressor housing 16.
• the turbine wheel is rotatably driven by an inflow of exhaust gas supplied from an exhaust manifold, which rotates the shaft, thereby causing the compressor impeller 14 to rotate.
• exhaust gas can be discharged or in some cases recirculated.
• the diffuser 18 and the volute 20 establish fluid communication between an impeller chamber 22 (containing a portion of the compressor impeller 14) and the engine.
• the volute 20 may be formed along an outer region of the compressor housing 16 and is radially remote from the compressor impeller 14.
• the volute 20 can be standard with an air passage 24 that gets larger as it approaches discharge for more static pressure.
• the diffuser 18 is associated with an entrance of the volute 20.
• the diffuser 18 has an inlet 26 in close proximity to the compressor impeller 14, preferably at a tip of the compressor impeller 14.
• the diffuser 18 includes an outlet 28 at an opposite end of the inlet 26.
• the diffuser 18 is confined by two walls called a hub wall 30 and a shroud wall 32 forming a flow path 34 for air as it leaves the compressor impeller 14.
• the shroud wall 32 is part of the compressor housing 16, and the hub wall 30 is typically part of a bearing housing, but also may be a back plate of the compressor housing 16.
• the diffuser 18 includes a retractable vane diffuser system 36 suitable for a radial or mixed flow compressor stage 12.
• the retractable vane diffuser system 36 includes a retractable vane 38 or preferably a set of vanes 40 that can be inserted into the flow path 34 of the diffuser 18 to change the operating characteristics of the compressor stage 12, such as improving the surge margin or improving peak stage efficiency.
• Figure 1 shows how the vanes 38 extend from the shroud wall 32 into the flow path 34 from a retracted position (as shown in dashed lines). The vanes 38 can be retracted into a cavity 42 on either or both the hub wall 30 and the shroud wall 32 of the diffuser 18 when operation as a vaneless diffuser is desired.
• the vanes 38 can be fully retractable to be completely out of the flow path 34 to avoid any blockage of airflow. On the other hand, the vanes 38 can be extended into the flow path 34 singly or as a group to further optimize performance of the compressor stage 12. With the retractable vane diffuser system 36, it is appreciated that a length of the diffuser 18 can be shorter than typical, allowing for a more compact turbocharger.
• the retractable vane diffuser system 36 allows the vanes 38 to operate when efficient such as at lower mass airflows but can avoid flow restrictions at higher mass airflows.
• the vanes 38 When the vanes 38 are extended into the flow path 34, the vanes 38 can help build pressure after air leaves the compressor impeller 14 to increase the efficiency of the compressor stage 12.
• the vanes 38 help control flow at lower mass airflow, and the vanes 38 extended into the flow path 34 can slow the onset of diffuser stall and surge with flow reversal.
• the vanes 38 can block total airflow that could cause earlier compression choke.
• the vanes 38 can be totally removed from the flow path 34 when fully retracted.
• the vanes 38 when retracted increase choke flow with less obstructed flow of air, such as preferred at higher operating speeds.
• the vanes 38 are preferably mounted on a movable vane ring 44. It is preferred that multiple vane rings 44 are used to control movement of the vanes 38.
• the diffuser 18 may have two sets of vanes 40 optimized for different operating points.
• the sets of vanes 40 may be staggered so as to not overlap in the shroud wall 32.
• a ring of vanes in the hub wall 30 and a ring of vanes in the shroud wall 32 may be extended into the flow path 34.
• two sets of vanes 40 may be on each side of the diffuser 18.
• a shroud set of vanes 40 and a hub set of vanes 140 may retract and extend from each wall, namely the shroud wall 32 and the hub wall 30.
• the vanes 38 are retracted into the hub wall 30 and the shroud wall 32, and the vanes 38 can be extended from the hub wall 30 and the shroud wall 32 into the flow path 34.
• the vanes 38 can be staggered or offset on the hub wall 30 or the shroud wall 32 or both walls.
• each vane 38 can be separate so that the solidity of the diffuser 18 could be changed. Alternating vanes 38 can be retracted or extended.
• One set of vanes 40 can be attached to the vane ring 44 in the shroud wall 32, i.e. an upper ring in the compressor housing 16.
• Another set of vanes 140 can be attached to a vane ring 144 in the hub wall 30, i.e. a lower ring in the bearing housing.
• Each vane of the set of vanes 140 can alternate and be between vanes of the other set of vanes 40 as shown in Figure 4.
• Activation of the retractable vane diffuser system 36 can vary depending on the diffuser 18 and characteristics sought.
• the retractable vane diffuser system 36 could be activated by mass airflow. As such, lower mass airflow would cause the vanes 38 to extend into the flow path 34. Higher mass airflow would cause the vanes 38 to retract.
• the retractable vane diffuser system 36 could be activated by acceleration or deceleration of the turbocharger. As such, rapid acceleration or deceleration would cause the vanes 38 to extend into the flow path 34. Thus, at steady high speed, the vanes 38 would be retracted.
• the retractable vane diffuser system 36 could be controlled by a single actuator that also controls a set of Variable Turbine Geometry (VTG) vanes. For example, when the set of VTG vanes is closed, the vanes 38 of the compressor stage 12 could be extended into the flow path 34. It is appreciated that the single actuator can be operably connected to a VTG actuation mechanism and the retractable vane diffuser system 36.
• VTG Variable Turbine Geometry
• the retractable vane diffuser system 36 in the compressor stage 12 of the turbocharger uses selectively retractable vanes 38 or sets of vanes 40, which can be extended into the flow path 34 of the diffuser 18, to help control airflow and to change the operating characteristics of the compressor stage 12, such as making the compressor stage 12 operate in a stable fashion at lower mass airflow rates or improving peak stage efficiency.
• the vanes 38 can be retracted into the cavity 42 in a wall (30 and/or 32) of the diffuser 18 to maximize flow capacity as a vaneless system.

Priority Applications (6)

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Publications (1)

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Family Applications (1)

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Citations (5)

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• 2013
  • 2013-07-11 WO PCT/US2013/050010 patent/WO2014018272A1/en active Application Filing
  • 2013-07-11 DE DE112013003162.0T patent/DE112013003162T5/de not_active Withdrawn
  • 2013-07-11 RU RU2015104708A patent/RU2015104708A/ru not_active Application Discontinuation
  • 2013-07-11 KR KR1020157003811A patent/KR102027187B1/ko active IP Right Grant
  • 2013-07-11 US US14/415,609 patent/US20150176600A1/en not_active Abandoned
  • 2013-07-11 CN CN201380038056.XA patent/CN104471204B/zh not_active Expired - Fee Related
• 2015
  • 2015-01-30 IN IN799DEN2015 patent/IN2015DN00799A/en unknown

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