CN101709667A - Turbomachine - Google Patents
Turbomachine Download PDFInfo
- Publication number
- CN101709667A CN101709667A CN 200910221464 CN200910221464A CN101709667A CN 101709667 A CN101709667 A CN 101709667A CN 200910221464 CN200910221464 CN 200910221464 CN 200910221464 A CN200910221464 A CN 200910221464A CN 101709667 A CN101709667 A CN 101709667A
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- shaft
- compressor
- rotor assembly
- turbine
- compressor impeller
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Classifications
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- 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
- F01D5/02—Blade-carrying members, e.g. rotors
- F01D5/027—Arrangements for balancing
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- 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
- F02C6/00—Plural gas-turbine plants; Combinations of gas-turbine plants with other apparatus; Adaptations of gas-turbine plants for special use
- F02C6/04—Gas-turbine plants providing heated or pressurised working fluid for other apparatus, e.g. without mechanical power output
- F02C6/10—Gas-turbine plants providing heated or pressurised working fluid for other apparatus, e.g. without mechanical power output supplying working fluid to a user, e.g. a chemical process, which returns working fluid to a turbine of the plant
- F02C6/12—Turbochargers, i.e. plants for augmenting mechanical power output of internal-combustion piston engines by increase of charge pressure
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- 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
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- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Combustion & Propulsion (AREA)
- Chemical Kinetics & Catalysis (AREA)
- General Chemical & Material Sciences (AREA)
- Supercharger (AREA)
Abstract
A turbocharger rotor assembly comprises a turbine wheel 5 and a compressor wheel 7 mounted to a rotor shaft 8 for rotation about a turbocharger axis. The turbine wheel 5 is mounted to a turbine shaft portion 8a and the compressor wheel 7 is mounted to a compressor shaft portion 8b. The turbine shaft 8a and compressor shaft 8b are connected to each other to define said rotor shaft 8.
Description
Technical field
The present invention relates to a kind of turbo machine, relate in particular to a kind of turbine rotor.
Background technique
Turbosupercharger is known being used for to be higher than the device that atmospheric pressure (supercharging) supplies air to the air-intake of combustion engine mouth.Traditional turbosupercharger mainly comprises the exhaust-driven turbine wheel that is installed in running shaft one end that is positioned at turbine cylinder.The rotation of this turbine wheel drives the compressor wheel spins that is installed in the axle the other end that is positioned at compressor housing.Compressor impeller is sent to engine intake manifold with the air of compression, increases engine power with this.
Turbo-charger shaft supports by shaft bearing (sliding bearing) (journal bearing) and thrust bearing (thrust bearing) usually, and it comprises the suitable lubrication system that is connected between turbo machine and the compressor impeller housing in the intermediate bearing housing.Described axle, the compressor impeller that is connected and turbine wheel (being connected in the opposite ends of axle) jointly form rotor assembly.Known, the balance of rotor assembly is important, to guarantee that axle really is positioned at bearing and rotates.Any imbalance all can be brought harm to the operation and the life-span of turbosupercharger.For example, the imbalance of rotor assembly can cause the noise of turbosupercharger and the increase of vibration and wearing and tearing, the wearing and tearing that especially increase bearing surface.Under opposite extreme situations, the imbalance of rotor assembly can (for example) make compressor impeller move with respect to the spin axis radially outward of axle, may cause turbosupercharger to produce catastrophe failure potentially.
Usually the technology that realizes acceptable rotor assembly balance is the rapid technology of multistep.At first, before assembling, each part of forming this rotor assembly is balance individually all.Next, with the turbine wheel friction welding to this axle, this axle of balance and the turbine wheel that is connected then.Then, this and the turbine wheel that connected are inserted in the turbosupercharger, and, comprise compressor impeller the miscellaneous part of rotor assembly, be connected to be contained in this opposite end to finish the assembling of rotor assembly.At last, in turbosupercharger in position/this rotor assembly of field balancing.The balance of rotor assembly comprises balance and/or the position of regulating each parts of rotor assembly, to compensate any imbalance.Can increase or remove the balance that material is adjusted assembly by specific part from parts.Alternatively, the single parts of rotor assembly are removable, so that the combination of the parts of the rotor assembly of effort acquisition formation balance.Because the balance of rotor assembly, particularly increase or remove material and when rotor assembly is in original position/scene, carry out because thereby this process can be complicated because the passage of rotor assembly is limited.In addition, compressor impeller adopts the material softer than axle to make usually, and is well-known, carries out in the process in balance, compressor impeller is connected to this goes up, replace compressor impeller, will produce the damage that to repair compressor impeller from this removal compressor impeller or from this axle.Any this damaged compressor impeller has to scrap.
Summary of the invention
Target of the present invention be to eliminate or alleviate the problems referred to above to small part.
According to the present invention, a kind of turbocharger rotor assembly is provided, comprise being installed on the rotor shaft with its turbine wheel and compressor impeller, wherein around rotational:
This turbine wheel is installed on the turbine shaft;
This compressor impeller is installed on the compressor shaft; And
This turbine shaft and compressor shaft are connected with each other to limit described rotor shaft.
Therefore, can constitute by two sub-components, promptly comprise the turbine end sub-component of the turbine wheel that is installed in the turbine shaft part and comprise the compressor end sub-component that is installed in compressor shaft compressor impeller partly according to turbocharger rotor assembly of the present invention.These two rotor shaft parts can coaxially be joined together to form complete rotor shaft.An advantage of this structure is can be before being assembled into rotor shaft on the turbosupercharger, each sub-component of balance individually outside turbosupercharger.
This turbine shaft can be connected dividually each other with compressor shaft.The assembling of this permission (for example) rotor assembly allows one or more parts of this assembly to be replaced.
This turbine shaft and compressor shaft can link together by intermeshing flank of thread separately.For example, the part at its outer surface in turbine shaft and the compressor shaft is provided with screw thread, and another is provided with axially extended tapped hole in order to receive described thread spindle.For example, in one embodiment of the invention, the compressor shaft outer surface forms screw thread and screws in along in the hole that the axis of turbine shaft forms.Should be realized that in this case, have externally threaded axle or along the diameter of at least a portion axle of its axial length, littler than another the external diameter that is formed with the endoporus (or base) that is used to receive above-mentioned axle.Being provided with externally threaded axle and tapped hole extends along the part basically of the length of rotor shaft.Alternatively, this hole can be shorter relatively when the outside thread axle is minor axis.
Should be realized that this screw thread can be arranged such that being threaded between turbine shaft and the compressor shaft will be tightened rather than unclamp to the rotational torque that is passed to compressor impeller by turbine wheel when rotor shaft assembly is installed in the turbosupercharger of work.
Other devices can be used for connecting compressor shaft and turbine shaft.For example, described connection can be the spline connection rather than be threaded.
According to the present invention, compressor shaft is installed on the compressor impeller.In certain embodiments, the extensible hole that is provided with along the compressor wheel spins axis of passing of first end of compressor shaft, and this compressor impeller can keep on the tape spool by nut, this nut spiral is connected on described first end of compressor shaft and directly or indirectly near compressor impeller, on the radially adjacent portion that limits with the part that impeller is clamped in by compressor shaft.This nut can be on (for example) direct preceding protuberance near compressor impeller, perhaps between locking nut and compressor impeller pad or like can be set.Similarly, this compressor impeller can clampedly prop up the radially adjacent portion on the axle, perhaps pad or like can be set between the two.In another optional embodiment, first end that the hole can only extend through the part of compressor impeller and compressor shaft can be contained in this hole and by being threaded of cooperating or connect by other connection sets that are fit to.As another alternate embodiment, compressor impeller can be included in the minor axis that extends in the respective aperture, extends in the compressor shaft this bore portion.Equally, can adopt the screw thread that matches that compressor impeller minor axis and one of compressor shaft are connected on another, but the connection set that also can adopt any other to be fit to.According to the present invention, the method that compressor impeller is mounted to turbo-charger shaft all is known method, and any traditional method all can be used for compressor impeller is installed on the compressor shaft.
The adjacent portion annular shoulder that can be (for example) be limited by the enlarged diameter portion of compressor shaft radially.The described enlarged diameter portion of this compressor shaft can for example limit the seal boss that is suitable for being contained in the hole that is limited by the turbocharger housing wall, so just with compressor impeller and separate in the turbo-charger bearing chamber and circular groove wherein is set in order to hold seal ring on the radially-outer surface of described seal boss.The backboard (it is commonly referred to compressor backplate) that this turbocharger housing wall can be for example cartridge housing body wall, compressor housing or both combinations.The sealing circle can be (for example) conventional piston ring or other seal elements that is fit to, typically as flinger ring adopted in traditional compressor end seal/bearing structure like.
The approximal surface of the enlarged diameter portion of this compressor impeller and compressor shaft can be approximately perpendicular to that axis extends or for example around this taper shape of frustum basically of axis, make its each be positioned on the identical general conical surface of revolution of described axis.In latter instance, this approximal surface can interact and make compressor impeller tend to aim at described axis centre when being applied on this compressor impeller of clamping force with box lunch.This surface can be positioned at (for example) straight line on the conical surface that described axis rotation limits, and is perhaps roughly rotated on the conical surface roughly that limits around described axis by curve.The approximal surface that compressor impeller limits can be recessed/concave surface, and the approximal surface that the enlarged diameter portion of compressor shaft limits can be protruding/convex surface, and vice versa.
Approximal surface between compressor impeller and the locking nut can be an analogous shape, is registered in the compressor shaft in the heart to help compressor impeller.For example, the front end of compressor impeller can have the conical surface of female or male, its with match with any parts (for example pad or the analog) protrusion that provides or the recessed conical surface between the compressor impeller by locking nut or at locking nut.
Flinger ring and/or thrust ring are supported on this rotor shaft and are clamped at radially extended surface that turbine shaft limits and that the part of compressor shaft limits is described radially between the approximal surface, and perhaps other that are limited by turbine shaft or compressor shaft are radially between the extended surface.
For example, be contained in the embodiment of the invention of the axial bore inside that is limited in the turbine shaft at compressor shaft, thrust ring/flinger ring can be clamped at the sagittal plane that is limited to the turbine shaft end and the ring surface that limits by the seal boss that is provided with on the compressor shaft between.Thrust ring/flinger ring can be that one-piece element or thrust ring are to separate with flinger ring.When the two constituted whole single parts, thrust bearing can have radially that extending groove is assembled on the thrust ring to allow thrust bearing.
Turbine wheel can be connected on the turbine shaft in any conventional mode.Similarly, turbine shaft can be provided with the piston boss with the turbine wheel adjacency, and it limits the outer annular groove that is used to hold seal ring in a usual manner.
The invention provides a kind of turbosupercharger, it comprises according to the described rotor assembly of aforementioned claim.
The present invention also provide a kind of in turbosupercharger the method for assembling turbine supercharger rotor assembly, this turbosupercharger comprises the turbine and the compressor of two opposite ends that are positioned at bearing bore, first shell body wall is separated turbine and this bearing bore, and second shell body wall is separated compressor and this bearing bore; Each shell body wall is provided with the hole that is used to receive the turbocharger rotor axle, and described turbocharger rotor axle passes described bearing bore and extends to compressor from turbine, and this method comprises:
The first rotor sub-component is provided, comprises the turbine wheel that is installed on the turbine shaft;
The second rotor sub-component is provided, comprises the compressor impeller that is installed on the compressor shaft;
This first and second rotors sub-component of balance independently;
Turbine shaft is passed the hole that is arranged on first shell body wall be inserted into this bearing bore, compressor shaft is passed the hole that is arranged on this second shell body wall insert this bearing bore;
With this turbine shaft and compressor shaft are linked together coaxially to finish this turbocharger rotor assembly.
According to a further aspect in the invention, a kind of method of safeguarding turbosupercharger also is provided, this turbosupercharger comprises foregoing turbocharger rotor assembly, and this method comprises one or more parts of taking turbine shaft and replacing or repairing rotor assembly from compressor shaft apart.
Description of drawings
Now will introduce specific embodiments of the invention with reference to the accompanying drawings by way of example, in the accompanying drawing:
Fig. 1 is the existing axial section that has the turbosupercharger of fixed geometry turbine, shows the basic element of character of turbosupercharger and turbocharger rotor assembly;
Fig. 2 is the axial section of existing rotor assembly, and it has constituted the part of turbosupercharger as shown in Figure 1;
Fig. 3 is the axial section according to the rotor assembly of first embodiment of the invention;
Fig. 4 is the axial section according to the rotor assembly of second embodiment of the invention;
Fig. 5 is the thrust bearing side view of rotor assembly shown in Figure 4;
Fig. 6 is the axial section according to the rotor assembly of third embodiment of the invention.
Embodiment
Fig. 1 is the axial section by the turbosupercharger that typically has fixed geometry turbine, shows the basic element of character of turbosupercharger.This turbosupercharger comprises turbine 1, and turbine 1 joins on the compressor 2 by central bearing housing 3.Turbine 1 comprises the turbine shroud 4 that holds turbine wheel 5.Similarly, compressor 2 comprises the compressor housing 6 that holds compressor impeller 7.Turbine wheel 5 and compressor impeller 7 are installed on two opposite ends of shared turbine shaft 8, and this turbine shaft 8 is supported on the bearing unit 9 that is positioned at bearing housing 3.
Turbine shroud 4 is provided with exhaust gas inlet 10 and waste gas outlet 11.The waste gas that import 10 guiding enter is to annular chamber, and promptly volute 12, and it is around turbine wheel 5 and annular entry passage 13 and its UNICOM by radially extending.The moving compressor impeller 7 of the rotating band of turbine wheel 5 rotates, and the rotation of compressor impeller 7 sucks air and carries pressurized air by annular exit volute 15 to the engine intake (not shown) by axial inlet 14.Comprise be installed to axle on 8 turbine wheel 5 and the assembly of compressor impeller 6 be known as rotor assembly 16.
Simultaneously with reference to figure 1 and Fig. 2 (showing the axis profile figure by rotor assembly), turbocharger rotor assembly 16 comprises turbine wheel 5, compressor impeller 7, thrust ring 21a and flinger ring 21, and they all are installed on the turbine shaft 8 with its rotation.Turbine wheel 5 is friction welded on the seal boss 17 that is arranged on axle 8 turbine end (being known as the piston boss sometimes).Sealing boss 17 is enlarged diameter portion of axle 8, has circular groove 18 on its outer surface.Seal ring 19 (for example, piston ring) is arranged in groove 18 and seals up axle 8 with respect to the hole 19a of cartridge housing body wall 19b, and cartridge housing body wall 19b separates turbine 1 and bearing housing 3.
The compressor end of axle 8 is radius-zoom-out parts (integrally referring to 20).The axial bore (axial bores) (being respectively 22,23) that this minor radius is dwindled on the part 20 by the appropriate size in thrust ring 21a, flinger ring 21 and the compressor impeller 7 supports thrust ring 21a, flinger ring 21 and compressor impeller 7.Flinger ring 21 and compressor impeller 7 are roughly coaxial and disposed adjacent one another, flinger ring 21 more close turbine wheels 5 among both.Thrust bearing 21b is arranged between flinger ring 21 and the thrust ring 21a.Flinger ring 21, thrust ring 21a and compressor impeller 7 are clamped in the middle of the annular shoulder 24 and locking nut 25 of axle 8, and this locking nut 25 is placed on the end of axle 8 by screw thread 26.Flinger ring 21 has the part of the hole 28a that extends through in the bearing housing 3, and is provided with peripheral groove 27, and seal ring 28 (for example, piston ring) is positioned at peripheral groove 27.Seal ring 28 is with respect to bearing housing 3 canned rotor assemblies.
For the operation of optimization turbosupercharger, importantly, balancing rotor assembly 16 makes the center of gravity of rotor assembly roughly drop on the rotation axis of rotor assembly, thereby makes the resultant couple minimum of any on its spin axis of rotor assembly 16.Reduce on the rotor assembly 16 relative rotation axi lines resultant couple of a bit, the centrifugal force that rotor assembly 16 is subjected in the time of will making rotor assembly 16 rotations reduces, and then has increased the stability of rotor assembly.Act on the rotor assembly 16 centrifugal force too conference cause the vibration of rotor assembly 16, and therefore increased the turbosupercharger noise and reduced its serviceability.In addition, since rotor assembly 16 constituted its part turbosupercharger can (＜140,000rpm) and down operation of high temperature (＜200 ℃), the balance of rotor assembly 16 be even more important at very high rotating speed.Since high rotating speed down any imbalance produced acts on power on the rotor assembly 16, and, all can cause compressor impeller 7 radially to trackslip with respect to axle 8, flinger ring 21 and locking nut 26 owing to the infringement of the material property that brings under the high running temperature.Trackslip if compressor impeller 7 takes place, the whole machine balancing of rotor assembly 16 will worsen, thereby cause the increase of compressor boost device vibration and therefore noise increase.Under extreme case, can cause the turbosupercharger catastrophe failure.
The imbalance of rotor assembly 16 may be caused by multiple reason, comprise (for example): the parts squareness inaccuracy at fitting surface place; The inaccuracy of parts manufacturing causes the radial clearance between compressor impeller 7 and/or flinger ring 21 and the axle 8; Be applied to power on compressor impeller 7 and/or the flinger ring 21 because the tightening of locking nut 26 brought with radial component.In addition, may be out of shape under any torque that rotor assembly 16 produces when locking nut 26 is tightened.If the parts of rotor assembly are not the right angles with respect to the clamping axis of miscellaneous part and locking nut 26 (in this case just the axis of rotor assembly 16), be applied to any clamping force on this non-right angle parts and all will have component perpendicular to rotor assembly 16 axis, the imbalance that this can cause moving radially of described parts and therefore produce rotor assembly 16 by tightening locking nut 26 so.
The method that a kind of known being used for obtains acceptable rotor assembly 16 balances is as follows: in case axle 8 has connected turbine wheel 5, just check the balance of turbine wheel 5 and the axle 8 that is connected.This automatic by special setting is finished.In a kind of like this machinery, when axle 8 and impeller 5 during with about 300rpm rotational speed, axle 8 is by air bearings support.Can come its imbalance is proofreaied and correct by the material that grinds off on the impeller 5 then.Compressor impeller 7 is connected on the axle temporarily and carries out balance in the mode identical with axle 8 and impeller 5.In case after being balanced, turbine wheel 5 and coupling shaft 8 are placed in respectively in bearing housing 3 and the turbine 1, the hole 28a that the compressor end of feasible axle 8 extends through shell body wall enters compressor housing 6.Axle 8 is by making its mode of sliding on axle 8 compressor ends receive thrust ring 21a, thrust bearing 21b and flinger ring 21.Compressor impeller 7 is assembled on the axle 8 then, makes compressor impeller 7 be positioned at compressor.Tighten locking nut 26 then to clamp impeller 7, flinger ring 21 and thrust ring 21 near annular shoulder 24.After assembling, whole rotor assembly is a balance, is located in the original position in the turbosupercharger simultaneously.Any imbalance of rotor assembly all can be proofreaied and correct by removing material from least one assembly.Since rotor assembly 16 be balance and be positioned at the turbosupercharger original position, then any remove material from its part (for example back side of compressor impeller) all can be in the serious restriction of the narrow passage that is subjected to turbocharger housing.
In addition, known compressor impeller 7 can be with making with axle 8 different materials.For example, compressor impeller 7 can be made by axle 8 usefulness steels with the aluminium manufacturing.The axle 8 and the material of impeller 7 different and be used for that axle 8 and impeller 7 are secured together used big power and can cause fret wear or distortion.This problem is serious in above-mentioned parts replacement process.In case this wearing and tearing or distortion take place, can not proofread and correct any imbalance and the rotor assembly 16 of rotor assembly 16 usually again and must scrap, this causes unnecessary waste and cost.
Fig. 3 shows the turbocharger rotor assembly according to the embodiment of the invention.Although the concrete structure of axle is different with the structure of the rotor assembly of Fig. 2, be used to represent corresponding parts in suitable local same reference numerals.Turbine shaft (whole represent with 8) has two-part: the turbine shaft 8a of turbine wheel 5 is installed and the compressor shaft 8b of compressor impeller 7 is installed.Turbine shaft 8a and turbine wheel 5 have constituted turbine sub-component 38a.As previously mentioned, turbine shaft 8a comprises seal boss part 17, and seal boss part 17 is soldered on the turbine wheel 5 by friction.On the whole, compressor shaft 8b, compressor impeller 7 and their connection set (being locking nut 25 and screw thread 26 in this case) have constituted compressor impeller sub-component 38b.Compressor impeller 7 is sandwiched between the annular shoulder and locking nut 25 that the radius part 35 by the expansion of axle 8b limits, and the helical thread portion 26 of this nut 25 and compressor shaft 8b is to match with the same way as of mode mentioned above.
In order to prevent that the 8b from rotating when tightening locking nut 25, axle 8b (for example) can fix with chuck (chuck), flat face (not shown) perhaps is set comes and suitable tool engagement.
According to the present invention, turbine and compressor sub-component are joined together to constitute complete rotor assembly.In illustrated embodiment, turbine shaft 8a comprises base or the axis hole 29 that is threaded part 30.Compressor shaft 8b has less diameter (integral body is represented with 31), and its shape and size are formed so that can be contained in the hole 29 in friction tight mode.Additionally, the end of compressor shaft 8b comprises screw portion 32, and screw portion 32 matches with helical thread portion 30, so that turbine shaft 8a and compressor shaft 8b can be threaded onto together.Screw portion 32 and helical thread portion 30 be screw-thread fit also, makes when work turbine wheel 5 be applied to any torque on the 8b and all can tighten rather than unclamp joint between turbine shaft 8a and the compressor shaft 8b.
Have on the flinger ring 33 of axial bore 22 and 22a and the smaller diameter portion 31 that thrust ring 33a is supported on compressor shaft 8b, make to be threaded onto a time-out as diaxon 8a and 8b that flinger ring 33 and thrust ring 33a are sandwiched between the expansion radius part 35 of the shoulder 34 of turbine shaft 8a and compressor shaft 8b.When assembling part, can provide thrust bearing 42 between flinger ring 33 on the axle 8b and thrust ring 33a.Enlarge radius part 35 and comprise peripheral groove 36, seal ring 37 (for example, traditional piston type seal ring) is installed in the peripheral groove 36.
According to the present invention, when assembling and balance rotor assembly 16 shown in Figure 3, adopt and prior art diverse ways mentioned above.Turbine shaft 8a is connected on the turbine wheel 5 to constitute turbine sub-component 38a, and the balance of turbine sub-component 38a is to test with the mode that described mode is identical before and to proofread and correct.Assemble compressible machine impeller sub-component 38b between enlarged 35 by compressor impeller 7 being fixed to a 8b and the locking nut 26 then.With this compressor impeller sub-component of back balance 38b.Such balancing machine that uses as indicated above is realized balance, and wherein compressor impeller sub-component 38b is supported by the diameter of pneumatic bearing by axle 8b.Alternatively, the screw rod 32 of axle 8b end can be used to compressor impeller sub-component 38b is connected to balancing machine.Alternatively, this balancing machine can support (also being known as locating face) shoulder 39.Other methods that are used for the installation compressor impeller sub-component of balance also are conspicuous to those skilled in the art.Again,, perhaps preferably, remove material, obtain the balance of acceptable compressor impeller sub-component 38b from compressor impeller 7 by increasing material to compressor impeller 7.With described conventional rotor 16 assembling methods are opposite before, the major component of balance, promptly the balance of turbine wheel sub-component 38a and compressor impeller sub-component 38b can not realize under the situation of turbosupercharger original position at rotor assembly 16.This makes equilibrium process more direct, because no longer include the restriction of rotor assembly 16 member passage.For example, no longer need usually to dismantle or change single parts to obtain balance.
After compressor impeller sub-component 38b balance, flinger ring 33 and thrust ring 33a are installed on the compressor shaft 8b.Turbine wheel sub-component 38a is inserted into the turbine end of bearing housing 3.Before smaller diameter portion 31 is inserted in the base 29, compressor impeller sub-component 38b is inserted into the compressor end of bearing housing and rotates, so that axle 8a and 8b are fixed to one another to together by screw portion 32 and screw device 30.As previously mentioned, the direction that relatively rotates that they need be secured together between turbine wheel sub-component 38a and the compressor impeller sub-component 38b makes that being applied to any torque on the turbine wheel 5 when turbocharger operation all can tighten binding between turbine wheel sub-component 38a and the compressor impeller sub-component 38b.In this mode, receive rotor assembly 16 by turbosupercharger by bearing unit 9.In order to rotate compressor shaft 8b relative to turbine shaft 8a utilizing screw rod and screw device 30,32, can tool using engage the locking nut 25 of hexagonal cross-section form.Compare with the moment that the locking nut 25 of tightening compressor impeller 7 next doors is required, screw the required moment of a 8a, 8b and be much smaller.This guarantees can not produce the balance of destroying compressor sub-component 38b and then the slip that destroys the balance of whole rotor assembly rotor assembly 16 with diaxon 8a, when 8b links together between compressor 7 and locking nut 25.
Axle 8a, 8b make that they have close tolerance fit when they are threaded onto a time-out, so that obtain good concentricity.In addition, the longitudinal axis of hole 29 and smaller diameter portion 31 makes that working as axle 8a, a 8b is threadingly attached to a time-out, and axle 8a, a 8b are coaxial.This helps to guarantee when the turbine sub-component 38a of pre-equilibration is connected to compressor impeller sub-component 38b and goes up, and resulting rotor assembly 16 is balances roughly.In addition, preferably between the longitudinal axis of matched edges (or shoulder) 34 and axle 8a, and has good squareness between the longitudinal axis of matched edges 39 and spool 8b.This helps also to guarantee that be coaxial when axle 8a and 8b are secured together.In addition, flinger ring 33 and thrust ring 33a make them have the face of two almost parallels, are connected one to the other to these two faces of a time-out at axle (8a and 8b) and engage with matched edges (34 and 39), and be mated to guarantee that a 8a and 8b are coaxial.
The advantage of the assembling method that is proposed is: compare with existing assembling method, when being assembled into rotor assembly 16 on the turbosupercharger, reduced the quantity of parts surface of contact.Therefore any this parts surface of contact all can cause the imbalance of rotor assembly 16, reduces the imbalance that the parts surface of contact minimizes any possible rotor assembly 16.Can before structure rotor assembly 16, assemble and balance compressor impeller sub-component 38b.It is uneven and then cause final rotor assembly 16 unbalanced factors that the balance of compressor impeller sub-component 38b can compensate the various compressor impeller sub-component 38b that cause, and comprising: the parts squareness inaccuracy of any matching surface between the parts of compressor assembly; The imbalance that cooperates inaccuracy to produce between compressor impeller 7 and the axle 8b; Any one single parts imbalance in axle 8b, compressor impeller 7 or locking nut 25; And because any imbalance that the compressor impeller sub-component 38b distortion that fastening nut 25 causes is produced.Therefore, before structure compressor impeller sub-component 38b, no longer need balance to constitute the single parts of compressor impeller sub-component 38b.In case compressor impeller sub-component 38b balance is owing to the caused imbalance of inaccuracy of any one in its constituent elements can not cause the imbalance of rotor assembly 16 again.Thereby, have only the smaller diameter portion 31 of a 8b and the concentricity between the base 29, and flinger ring 33 and thrust ring 33a matching surface, can cause the imbalance of rotor assembly 16.Can predict, but the number of the minimizing rotor assembly 16 unbalanced energy will mean that the processing inaccuracy of flinger ring and thrust ring 33a will be not enough to cause the unacceptable imbalance of rotor assembly 16.
In addition, owing to turbine wheel sub-component 38a and the fixing required together torque of compressor impeller sub-component 38b are significantly adopted the fixedly required torque of all parts of prior art rotor assembly 16 of locking nut 25 less than passing through, so make power that fastening sub-component 38a, 38b produce, that act on the rotor assembly 16 cause distortion and then make rotor assembly 16 unbalanced probabilities littler.
As previously mentioned, during use, rotor assembly 16 is supported on the interior bearing unit 9 of turbosupercharger.The arbitrary portion 40 that rotor assembly can be arranged such that the axle 8a that can be out of shape potentially in response to tightening of helical thread portion 30 no longer by 9 of bearing uniies around.This makes any distortion of axle 8a can not influence the gap between bearing unit 9 and the axle 8a.Any friction that reduces all can increase between a 8a and the bearing unit 9 in gap perhaps makes a 8a be stuck in the bearing unit 9.
Opposite with existing rotor assembly, promptly compressor end piston packing 28 is positioned at the groove 27 of flinger ring 21 in rotor assembly 16 as shown in Figure 2, and the application's seal ring 37 is arranged in the groove 36 that enlarges radius part 35.This allows the axial length of flinger ring to be shortened, and increases thereby compare the length of having avoided the application's rotor assembly 16 with traditional turbocharger rotor assembly (what promptly be used in combination with major diameter part 35 is the standard flinger ring).This allows the application's rotor assembly 16 and traditional rotor assembly to exchange.
Fig. 4 shows according to another optional embodiment of the present invention.Its form and previous embodiment substantially is very similar, and therefore similarly feature adopts identical reference character.Difference between this embodiment and the last embodiment is that smaller diameter portion 31 is formed the part of turbine wheel sub-component 38a, and 38b is relative with the compressor impeller sub-component.Therefore, the base 29 of this embodiment of the invention shown in Figure 4 is formed the part of compressor impeller sub-component 38b, and 38a is relative with the turbine wheel sub-component.
Embodiment shown in Figure 4 also comprises the flinger ring 41a that forms one with thrust ring.The overall permanence of thrust ring and flinger ring makes has eliminated flinger ring independent among the embodiment of front and the surface of contact between the thrust ring.Again, because each parts surface of contact can cause rotor assembly 16 imbalances, the quantity that therefore reduces parts surface of contact in the rotor assembly 16 can minimize the imbalance of any possible rotor assembly 16.However, it is to be understood that the flinger ring 41a that embodiment's noted earlier two-part flinger ring and thrust ring can alternative combinations.Similarly, can recognize that two-part flinger ring and thrust ring can be substituted by the combination flinger ring of embodiments of the invention shown in Figure 4 among the embodiment of front.
Fig. 4 embodiment's thrust bearing 42 is shown in Figure 5, and it comprises radial groove 44, and the size of radial groove 44 forms and makes it partly to match with the thrust ring of the flinger ring/thrust ring that makes up.As known in the art, thrust bearing 42 also has oil duct 43.
Fig. 6 shows according to another embodiment of the present invention.Under suitable situation, used the reference character identical among Fig. 6 with Fig. 3 to 5.Complementary fit surface 48 between the enlarged 35 of axle 8b and the surface 47 of the complementary fit between the compressor impeller 7 and locking nut 25 and the compressor impeller 7 all is that frustum is conical.When compressor 7 was fixed on the 8b by tightening of nut 25, the conical fitting surface 47,48 of frustum cooperatively interacted, so that help compressor impeller 7 to concentrate on axle 8b.In addition, when rotor assembly 16 work, matching surface 47,48 cooperatively interacts to help prevent compressor 7 with respect to moving radially along axle 8b.Thereby the balance of rotor assembly 16 is not easy to prolong in time and worsens when rotor assembly 16 uses.In addition, the characteristic of matching surface can reduce soft compressor impeller 7 owing to be fixed to the wearing and tearing that the hard axle 8b of different geometries goes up generation.
In the embodiment shown, the matching surface of compressor impeller 7 is recessed, and has slight curving profile with respect to the rotor assembly axis.Should be realized that, also can protrude, and the matching surface on the axle is recessed as the replacement of compressor impeller matching surface.Should the surface need be crooked equally, but can be positioned on the conical surface.In addition, can use the feature of other replacements to stop compressor impeller 7 moving radially with respect to axle 8b.
Except simplifying assembly and balance turbocharger rotor axle, the embodiment of the invention can also allow turbine and compressor impeller sub-component separately, to help the maintenance and repair of turbosupercharger.
Other improvement for the invention described above embodiment and the present invention's application it will be apparent to those skilled in the art that.
Claims (14)
1. turbocharger rotor assembly, it comprises and being installed on the rotor shaft with its turbine wheel and compressor impeller around rotational, wherein:
Described turbine wheel is installed on the turbine shaft;
Described compressor impeller is installed on the compressor shaft; With
Described turbine shaft and compressor shaft are connected to each other to limit described rotor shaft.
2. turbocharger rotor assembly according to claim 1, wherein said turbine shaft is connected with removable each other the turning up the soil of compressor shaft.
3. turbocharger rotor assembly according to claim 1 and 2, wherein said turbine shaft connects together by the flank of thread separately that is engaged with each other with compressor shaft.
4. turbocharger rotor assembly according to claim 3, one in wherein said turbine shaft and the compressor shaft is provided with screw thread on the part of its outer surface, and another is provided with along the tapped hole of axis extension, in order to receive described thread spindle.
5. according to each described turbocharger rotor assembly of front claim, first end of wherein said compressor shaft extends through the hole that is provided with along the described spin axis of described compressor impeller, be maintained on the described axle by nut with wherein said compressor impeller, described nut thread is connected on described first end of described compressor shaft and directly or indirectly near described compressor impeller, clamp described impeller with the radially adjacent portion that limits near the part by described compressor shaft.
6. turbocharger rotor assembly according to claim 5, wherein said radially adjacent portion are the annular shoulders that the enlarged diameter portion by described compressor shaft limits.
7. turbocharger rotor assembly according to claim 6, the described enlarged diameter portion of wherein said compressor shaft limits the seal boss that is suitable for being contained in the hole that the turbocharger housing wall limited, described turbocharger housing wall with described compressor impeller and separate in the turbo-charger bearing chamber and wherein circular groove be limited on the radially-outer surface of described seal boss in order to hold seal ring.
8. according to claim 6 or 7 described turbocharger rotor assemblies, the approximal surface of the described enlarged diameter portion of wherein said compressor impeller and described compressor shaft is the roughly frustum taper shape around the axis of described axle, make its each be positioned on the identical general conical surface of revolution of described axis.
9. according to each described turbocharger rotor assembly in the claim 5 to 8, wherein flinger ring and/or thrust ring be supported on the described rotor shaft and be clamped at the radially extended surface that limits by described turbine shaft and by the part of described compressor shaft limit described radially between the adjacent portion.
10. according to each described turbocharger rotor assembly of front claim, wherein flinger ring and/or thrust ring be supported on the described rotor shaft and be clamped at by described turbine shaft and described compressor shaft limit respectively radially between the extended surface.
11. a turbosupercharger, it comprises according to each described rotor assembly of front claim.
12. the method for an assembling turbine supercharger rotor assembly in turbosupercharger, described turbosupercharger comprise the turbine of two opposite ends that are positioned at bearing bore and compressor, with described turbine and separated first shell body wall of described bearing bore with described compressor and separated second shell body wall of described bearing bore; Each shell body wall is provided with the hole that is used to receive the turbocharger rotor axle, and described turbocharger rotor axle passes described bearing bore and extends to described compressor from described turbine, and described method comprises:
The first rotor sub-component is provided, and described the first rotor sub-component comprises the turbine wheel that is installed on the turbine shaft;
The second rotor sub-component is provided, and the described second rotor sub-component comprises the compressor impeller that is installed on the compressor shaft;
Described first and second rotor sub-components of balance independently;
Described turbine shaft is passed the described hole that is arranged on described first shell body wall to be inserted described bearing bore and described compressor shaft is passed the described hole that is arranged on described second shell body wall insert described bearing bore;
With described turbine shaft and compressor shaft are linked together coaxially to limit described turbocharger rotor assembly.
13. method according to claim 12, wherein said turbocharger rotor assembly are according to each described rotor assembly in the claim 1 to 10.
14. method of safeguarding turbosupercharger, described turbosupercharger comprises according to each described turbocharger rotor assembly of claim 1 to 10, and described method comprises from described compressor shaft and separates described turbine shaft and replacing or repair one or more parts of described rotor assembly.
Applications Claiming Priority (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| GB0816393.3 | 2008-09-06 | ||
| GB0816393A GB2463453B (en) | 2008-09-06 | 2008-09-06 | Turbomachine |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN101709667A true CN101709667A (en) | 2010-05-19 |
Family
ID=39888990
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN 200910221464 Pending CN101709667A (en) | 2008-09-06 | 2009-09-07 | Turbomachine |
Country Status (2)
| Country | Link |
|---|---|
| CN (1) | CN101709667A (en) |
| GB (1) | GB2463453B (en) |
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| CN102400943A (en) * | 2010-09-15 | 2012-04-04 | 哈米尔顿森德斯特兰德公司 | Thrust bearing shaft for thrust and journal air bearing cooling in compressor |
| CN102400942A (en) * | 2010-09-15 | 2012-04-04 | 哈米尔顿森德斯特兰德公司 | Shaft for air bearing and motor cooling in compressor |
| CN102562263A (en) * | 2012-01-18 | 2012-07-11 | 潍坊富源增压器有限公司 | Turbocharger |
| CN103362860A (en) * | 2012-04-02 | 2013-10-23 | 珠海格力电器股份有限公司 | High-speed hydrodynamic machine and composition method and assembly method of rotor of high-speed hydrodynamic machine |
| CN103842631A (en) * | 2011-12-27 | 2014-06-04 | 三菱重工业株式会社 | Turbine for supercharger and method for assembling supercharger |
| CN105003302A (en) * | 2014-04-18 | 2015-10-28 | 松下知识产权经营株式会社 | Turbomachine |
| CN105252201A (en) * | 2015-10-19 | 2016-01-20 | 中航湖南通用航空发动机有限公司 | Dynamic balance disqualification remedying method for precisely-cast integral power turbine impeller |
| CN109996932A (en) * | 2016-10-05 | 2019-07-09 | 博格华纳公司 | The method for assembling turbocharger |
| CN110878765A (en) * | 2018-09-06 | 2020-03-13 | 意博能源意大利股份公司 | Method for repairing a rotor of a multistage axial compressor of a gas turbine |
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| JP5524427B2 (en) * | 2011-12-27 | 2014-06-18 | 三菱重工業株式会社 | Thrust bearing device for turbocharger |
| US9771946B2 (en) * | 2014-08-01 | 2017-09-26 | Caterpillar Inc. | Turbocharger compressor oil deflector and method |
| CN104696062B (en) * | 2015-03-13 | 2017-05-24 | 费传华 | One-shaft two-unit horizontal turbocharger for vehicle |
| FR3089585B1 (en) * | 2018-12-07 | 2021-09-17 | Safran Helicopter Engines | TURBOMACHINE ROTOR |
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| GB595669A (en) * | 1942-04-27 | 1947-12-12 | Power Jets Ltd | Rotor assembly |
| DE3039961A1 (en) * | 1980-10-23 | 1982-06-03 | Volkswagenwerk Ag, 3180 Wolfsburg | Exhaust turbocharger with ceramic turbine shaft - has ceramic shaft connected to metal compressor shaft with radial bearings |
| JPS6140879A (en) * | 1984-08-03 | 1986-02-27 | 日本碍子株式会社 | Metal ceramic bonded body and manufacture |
| DE3625996A1 (en) * | 1986-07-31 | 1988-02-04 | Kuehnle Kopp Kausch Ag | Rotor for an exhaust turbocharger |
| JP3386559B2 (en) * | 1993-05-11 | 2003-03-17 | マツダ株式会社 | Engine supercharger |
| KR100291057B1 (en) * | 1997-08-29 | 2001-09-17 | 이계안 | Exhaust turbine supercharger |
| US6499969B1 (en) * | 2000-05-10 | 2002-12-31 | General Motors Corporation | Conically jointed turbocharger rotor |
| KR100373021B1 (en) * | 2000-09-05 | 2003-02-25 | 현대자동차주식회사 | Turbo-charger wherein a transmission is equiped |
| EP1353041A1 (en) * | 2002-04-12 | 2003-10-15 | ABB Turbo Systems AG | Turbocharger with means on the shaft to axially restrain said shaft in the event of the compressor bursting |
| US6896479B2 (en) * | 2003-04-08 | 2005-05-24 | General Motors Corporation | Turbocharger rotor |
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| CN102400942A (en) * | 2010-09-15 | 2012-04-04 | 哈米尔顿森德斯特兰德公司 | Shaft for air bearing and motor cooling in compressor |
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| CN103842631A (en) * | 2011-12-27 | 2014-06-04 | 三菱重工业株式会社 | Turbine for supercharger and method for assembling supercharger |
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| US9810225B2 (en) | 2011-12-27 | 2017-11-07 | Mitsubishi Heavy Industries, Ltd. | Turbine for turbocharger and method for assembling turbocharger |
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| CN103362860A (en) * | 2012-04-02 | 2013-10-23 | 珠海格力电器股份有限公司 | High-speed hydrodynamic machine and composition method and assembly method of rotor of high-speed hydrodynamic machine |
| US9863272B2 (en) | 2014-04-18 | 2018-01-09 | Panasonic Intellectual Property Management Co., Ltd. | Turbomachine |
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| CN109996932B (en) * | 2016-10-05 | 2022-08-26 | 博格华纳公司 | Method of assembling a turbocharger |
| CN110878765A (en) * | 2018-09-06 | 2020-03-13 | 意博能源意大利股份公司 | Method for repairing a rotor of a multistage axial compressor of a gas turbine |
| CN110878765B (en) * | 2018-09-06 | 2023-01-31 | 意博能源意大利股份公司 | Method for repairing a rotor of a multistage axial compressor of a gas turbine |
Also Published As
| Publication number | Publication date |
|---|---|
| GB2463453B (en) | 2012-08-08 |
| GB2463453A (en) | 2010-03-17 |
| GB0816393D0 (en) | 2008-10-15 |
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Application publication date: 20100519 |