CN106103998A - For the method manufacturing low inertia laminated rotor - Google Patents

For the method manufacturing low inertia laminated rotor Download PDF

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Publication number
CN106103998A
CN106103998A CN201580012975.9A CN201580012975A CN106103998A CN 106103998 A CN106103998 A CN 106103998A CN 201580012975 A CN201580012975 A CN 201580012975A CN 106103998 A CN106103998 A CN 106103998A
Authority
CN
China
Prior art keywords
rotor
pack
rotor pack
salient angle
mandrel
Prior art date
Application number
CN201580012975.9A
Other languages
Chinese (zh)
Inventor
W·N·埃博根
M·L·基利安
M·J·福尔蒂尼
J·K·斯普林
Original Assignee
伊顿公司
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
Priority to US201461951788P priority Critical
Priority to US61/951,788 priority
Application filed by 伊顿公司 filed Critical 伊顿公司
Priority to PCT/US2015/019876 priority patent/WO2015138557A1/en
Publication of CN106103998A publication Critical patent/CN106103998A/en

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Classifications

    • FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04CROTARY-PISTON, OR OSCILLATING-PISTON, POSITIVE-DISPLACEMENT MACHINES FOR LIQUIDS; ROTARY-PISTON, OR OSCILLATING-PISTON, POSITIVE-DISPLACEMENT PUMPS
    • F04C18/00Rotary-piston pumps specially adapted for elastic fluids
    • F04C18/08Rotary-piston pumps specially adapted for elastic fluids of intermeshing-engagement type, i.e. with engagement of co-operating members similar to that of toothed gearing
    • F04C18/12Rotary-piston pumps specially adapted for elastic fluids of intermeshing-engagement type, i.e. with engagement of co-operating members similar to that of toothed gearing of other than internal-axis type
    • F04C18/126Rotary-piston pumps specially adapted for elastic fluids of intermeshing-engagement type, i.e. with engagement of co-operating members similar to that of toothed gearing of other than internal-axis type with radially from the rotor body extending elements, not necessarily co-operating with corresponding recesses in the other rotor, e.g. lobes, Roots type
    • FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01CROTARY-PISTON OR OSCILLATING-PISTON MACHINES OR ENGINES
    • F01C21/00Component parts, details or accessories not provided for in groups F01C1/00 - F01C20/00
    • F01C21/08Rotary pistons
    • FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04CROTARY-PISTON, OR OSCILLATING-PISTON, POSITIVE-DISPLACEMENT MACHINES FOR LIQUIDS; ROTARY-PISTON, OR OSCILLATING-PISTON, POSITIVE-DISPLACEMENT PUMPS
    • F04C18/00Rotary-piston pumps specially adapted for elastic fluids
    • F04C18/08Rotary-piston pumps specially adapted for elastic fluids of intermeshing-engagement type, i.e. with engagement of co-operating members similar to that of toothed gearing
    • F04C18/082Details specially related to intermeshing engagement type pumps
    • F04C18/084Toothed wheels
    • FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04CROTARY-PISTON, OR OSCILLATING-PISTON, POSITIVE-DISPLACEMENT MACHINES FOR LIQUIDS; ROTARY-PISTON, OR OSCILLATING-PISTON, POSITIVE-DISPLACEMENT PUMPS
    • F04C18/00Rotary-piston pumps specially adapted for elastic fluids
    • F04C18/08Rotary-piston pumps specially adapted for elastic fluids of intermeshing-engagement type, i.e. with engagement of co-operating members similar to that of toothed gearing
    • F04C18/12Rotary-piston pumps specially adapted for elastic fluids of intermeshing-engagement type, i.e. with engagement of co-operating members similar to that of toothed gearing of other than internal-axis type
    • F04C18/14Rotary-piston pumps specially adapted for elastic fluids of intermeshing-engagement type, i.e. with engagement of co-operating members similar to that of toothed gearing of other than internal-axis type with toothed rotary pistons
    • F04C18/16Rotary-piston pumps specially adapted for elastic fluids of intermeshing-engagement type, i.e. with engagement of co-operating members similar to that of toothed gearing of other than internal-axis type with toothed rotary pistons with helical teeth, e.g. chevron-shaped, screw type
    • FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04CROTARY-PISTON, OR OSCILLATING-PISTON, POSITIVE-DISPLACEMENT MACHINES FOR LIQUIDS; ROTARY-PISTON, OR OSCILLATING-PISTON, POSITIVE-DISPLACEMENT PUMPS
    • F04C2230/00Manufacture
    • F04C2230/20Manufacture essentially without removing material
    • F04C2230/23Manufacture essentially without removing material by permanently joining parts together
    • F04C2230/231Manufacture essentially without removing material by permanently joining parts together by welding
    • FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04CROTARY-PISTON, OR OSCILLATING-PISTON, POSITIVE-DISPLACEMENT MACHINES FOR LIQUIDS; ROTARY-PISTON, OR OSCILLATING-PISTON, POSITIVE-DISPLACEMENT PUMPS
    • F04C2230/00Manufacture
    • F04C2230/60Assembly methods
    • FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04CROTARY-PISTON, OR OSCILLATING-PISTON, POSITIVE-DISPLACEMENT MACHINES FOR LIQUIDS; ROTARY-PISTON, OR OSCILLATING-PISTON, POSITIVE-DISPLACEMENT PUMPS
    • F04C2240/00Components
    • F04C2240/20Rotors
    • FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04CROTARY-PISTON, OR OSCILLATING-PISTON, POSITIVE-DISPLACEMENT MACHINES FOR LIQUIDS; ROTARY-PISTON, OR OSCILLATING-PISTON, POSITIVE-DISPLACEMENT PUMPS
    • F04C2240/00Components
    • F04C2240/60Shafts
    • FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04CROTARY-PISTON, OR OSCILLATING-PISTON, POSITIVE-DISPLACEMENT MACHINES FOR LIQUIDS; ROTARY-PISTON, OR OSCILLATING-PISTON, POSITIVE-DISPLACEMENT PUMPS
    • F04C2240/00Components
    • F04C2240/70Use of multiplicity of similar components; Modular construction

Abstract

Disclose the rotor assembly of a kind of multiple rotor packs having mounted to axle and for the constructive method of rotor assembly.Each rotor pack in described assembly can be provided with between the first side and the second side the central opening extended, and axle extends through this central opening.In one aspect, rotor pack is provided with the multiple salient angles extended away from central opening, and the most each salient angle has the salient angle opening of the thickness extension through each lamination.In one embodiment, rotor pack is stacked formation rotatably with helical rotor.

Description

For the method manufacturing low inertia laminated rotor

Related application

The application and required to carry on March 12nd, 2014 as PCT International Patent Application submission on March 11st, 2015 The priority of the US application serial No. 61/951,788 handed over, the full content of this U. S. application is hereby incorporated.

Technical field

The present invention relates to rotor assembly, it may be used for rotary apparatus such as positive displacement and expands and in compressor.

Background technology

Rotor is generally used for needing compression or driving fluid and needs to remove from fluid in the application of energy.At one In example, compressor or supercharger utilize a pair rotor to carry out the air stream that increasing combustion engine sucks.In another example, volume Formula fluid expanders includes making working fluid expand with a pair rotor producing useful work on output shaft.In this type of application, It is known that provide machining or the cast rotor of a kind of integral structure with solid cross sectional area.It is desired with improving.

Summary of the invention

The present invention relates to the rotor assembly of a kind of multiple rotor packs including and being mounted on an axle.In one aspect, each Rotor pack has the first side and the second relative side separated by the first thickness.Each rotor pack is also provided with The central opening extended between first side and the second side, axle extends through this central opening.On the other hand, rotor pack is arranged Having the multiple salient angles extended away from central opening, the most each salient angle has the salient angle extended between the first and second sides and opens Mouthful.Multiple rotor packs stack and tighten together to form rotor assembly so that the first side of a rotor pack and second At least one in side is adjacent with at least one in the first side of another rotor pack and the second side and contacts.A reality Executing in example, rotor pack is directly stacked upon to be gone up each other, so that the whole side of a rotor pack is by adjacent rotor lamination It is completely covered.In one embodiment, rotor pack stacks to form helical rotor rotatably, so that a rotor pack is not Adjacent rotor lamination is completely covered.Present invention additionally comprises a kind of displacement fluid decompressor with a pair above-mentioned rotor and compression Machine or supercharger.

The invention still further relates to a kind of method for manufacturing laminated rotor assembly.In a step of described method, According to foregoing, it is provided that multiple rotor packs.In one step, rotor pack is stacked to form straight rotor or spiral shell Gyrator.In one step, rotor pack is such as by being weldingly secured at together.In one step, rotor is installed to axle On to form laminated rotor assembly.Described axle can form burr/burr (be burred) so that described axle and laminated rotor Lamination preferably engages.Described method can also include also rotor being applied wear-resistant coating.

In one embodiment, each rotor pack is also provided with the first labelling (index) structure, this first mark structure It is configured to align with the second mark structure in mandrel.In such configuration, for constructing the second of laminated rotor assembly Method can include providing multiple rotor packs with the first mark structure and the step providing the mandrel with the second mark structure Suddenly.In a step of second method, rotor pack is stacked in mandrel so that mandrel extends through the center of each lamination Opening and the first mark structure of each rotor pack is alignd with the second mark structure of mandrel.In one embodiment, Second mark structure extends along the length of mandrel and is parallel to the longitudinal axis of mandrel so that will form straight rotor.At one In embodiment, the second translocation domain extends along the length of mandrel and has spiral-shaped so that will form helical rotor.

In a step of second method, rotor pack is such as secured together by welding.In second method In one step, remove mandrel from rotor pack.In one embodiment, it is provided with from the rotor pack extrusion mandrel assembled Extraction tool.In a step of second method, it is inserted into deckle-edged axle can be arranged in the central opening of rotor sheet To form rotor assembly.As first method, apply wear-resistant coating can in the second approach the rotor assembled.In second party In one step of method, such as balance pipe can be set by boring in the rotor pack of stacking, so that rotor assembly rotates Balance.

In conjunction with accompanying drawing by the following detailed description for preferred embodiment of the present invention, the features above of the present invention and Advantage and further feature and advantage will be more readily understood.

Accompanying drawing explanation

Fig. 1 is the perspective view of low inertia laminated rotor assembly in accordance with the principles of the present invention.

Fig. 2 is the top view that can be used for the rotor pack in the rotor assembly shown in Fig. 1.

Fig. 3 is the side view of the rotor pack shown in Fig. 2.

Fig. 4 is the top view that can be used for the rotor pack in the rotor assembly shown in Fig. 1.

Fig. 5 is the top view that can be used for the rotor pack in the rotor assembly shown in Fig. 1.

Fig. 6 is the perspective view of the integral type rotor after removing axle.

Fig. 7 is can be with the perspective view of the axle of the rotor pack in installation diagram 2-5 on it.

Fig. 8 is the end-view of axle shown in Fig. 7 in contour forging technique.

Fig. 9 is the schematic diagram of the method for manufacturing laminated rotor.

Figure 10 is the showing of vehicle with the fluid expanders of the rotor assembly that can include type shown in Fig. 1 and compressor It is intended to.

Figure 11 is the schematic diagram of the second method for manufacturing laminated rotor.

Figure 12 is the saturating of the rotor set assembling device in the second method that can be used for the laminated rotor shown in manufacture Figure 10 View.

Figure 13 is the perspective view of the rotor set assembling device shown in the Figure 12 after rotor pack aligns with mandrel.

Figure 14 is the perspective view of the rotor set assembling device shown in the Figure 12 after rotor pack aligns with mandrel.

Figure 15 is that rotor pack aligns with mandrel and rotor pack is around the rotor shown in the Figure 12 after mandrel installation The perspective view of assembling device.

Figure 16 is the perspective view of the rotor set assembling device shown in Figure 12 after two rotor packs are installed around mandrel.

Figure 17 is that multiple rotor pack installs the rotor set assembling device shown in the Figure 12 after forming full rotor around mandrel Perspective view.

Figure 18 is that additional base portion is fixed on assembly so that rotor pack can formation integral type rotor secured together After the rotor shown in Figure 17 and the perspective view of rotor set assembling device.

Figure 19 is the perspective view of the complete rotor that base portion has been removed from mandrel and lamination can be secured together.

Integral type rotor that Figure 20 is mounted in mandrel extraction tool and the perspective view of mandrel.

Detailed description of the invention

Various embodiment will be described in detail with reference to the attached drawings, the most identical/similar reference represent identical/ Similar parts and assembly.Multiple embodiments are mentioned and is not limiting as scope of the following claims.It addition, description is given Any example gone out is not used in the restriction present invention, and is only given in the most possible embodiment of claims Some.With reference to accompanying drawing, the most identical/similar reference represents identical/similar or similar component.

Rotor structure

See Fig. 1, it is shown that complete laminated rotor assembly 5.As it can be seen, laminated rotor 30 includes being installed to The rotor pack 200 of the multiple stackings on common axis 38.In an illustrated embodiment, rotor pack 200 is stacked rotatably, from And make rotor assembly 30 have the helical rotor at band constant helical angle.Term " stacking rotatably " is used to represent that described lamination is relative Offset, so that a rotor pack not exclusively covers adjacent rotor lamination mutually rotatingly.By stacking rotor pack 200 So that the mode that adjacent rotor lamination 200 is completely covered each other, laminated rotor 30 is also provided with the form of straight rotor.

Fig. 2-5 shows multiple examples of rotor pack 200.As indicated, rotor pack 200 has from central axis X Extend to corresponding top ends 203-1, three salient angles 202-1 being radially spaced of 203-2,203-3 (being referred to as top 203), 202-2,202-3 (are referred to as salient angle 202).In one aspect, salient angle 202 has or limits convex, and root 204 has Having or limit recessed profile, they limit the periphery 206 of rotor pack 200 jointly.

As indicated, salient angle 202 is separated with first by adjacent root 204-1,204-2,204-3 (being referred to as root 204) Angle a1 is equally spaced apart from.In the embodiment shown, angle a1 about 120 degree is separated.Though it is shown that three salient angles, it will be appreciated that Can separate angle accordingly and provide less or more salient angle, such as, separate two salient angles that angle is 180 degree, separating angle is 90 degree Four salient angles, separating angle is five salient angles of 72 degree, and separates six salient angles that angle is 60 degree.When be stacked with Formed rotor 30 time, the central axis X of each rotor pack 200 respectively with axis X 1, X2 is coaxial.

Each rotor pack 200 also has the first side 208 and the second side 210 separated by the first thickness t1.At one In embodiment, thickness t1 is of about 0.25 millimeter (mm).It should, however, be mentioned that other thickness can be used, such as, about Thickness between 0.1mm to about 1mm, and the thickness between about 0.1mm to about 0.5mm.Each lamination 200 is also shown Going out to be provided with in the first side and the second side 208, the central opening 212 extended between 210, wherein this central opening 212 is with central shaft Centered by line X.

Mark structure 214 may also be arranged near central opening 212 or is set to one part.In shown embodiment In, mark structure 214 includes three alignd the respectively groove 214-being radially spaced with salient angle 202-1,202-2 and 202-3 1,214-2 and 214-3.As being discussed in more detail about rotor assemble method 2000, mark structure 214 allows rotor pack 200 relative to each other align in stacking or assembling process.Although showing three grooves for mark structure 214, it should reason Solve, more or less of groove can be set or be able to carry out other structure of alignment function, such as towards the center of central opening 212 The tab extended.

Rotor pack 200 shown in Figure 2, it can be seen that salient angle 202 is completely solid material, so that extend through The opening of the thickness t1 crossing rotor only has central opening 212.Such salient angle is referred to as solid salient angle, has this salient angle Rotor pack be referred to as solid salient angle rotor pack.But, can be provided with in each salient angle one or many of rotor pack 200 Individual opening.Such salient angle can be described as hollow salient angle, and the rotor pack with this salient angle is referred to as hollow salient angle rotor Lamination.

Seeing Fig. 4, it is shown that an example of hollow salient angle rotor pack 200, the most each salient angle 202 is provided with accordingly Opening 205-1,205-2,205-3 (are referred to as opening 205).In one aspect, the area of each opening 205 occupies by salient angle 202 The major part of the surface area of salient angle 202 that limited of periphery.In one aspect, opening 205 and central opening 212 are limited (rotor pack) gross area that total aperture area is limited more than the periphery 206 of rotor pack 200.On the one hand, opening 205 is joined It is set to the width w1 making the surplus material of the salient angle 202 of adjacent with periphery 206 and close top ends 203 have constant.? Near root 204, material width is shown as more than the first width w1 to improve intensity.

In the embodiment shown in fig. 4, total aperture area of opening 205 and central opening 212 is limited by periphery 206 About the 50% of the gross area so that rotor pack 200 is few for comparing the solid salient angle rotor with same central opening size The material of about 50%.The size of the opening 205 in rotor pack 200 and configuration may be arranged so that total aperture area is total periphery 0% to the 70% of area, about the 30% of the most total outer circumferential area arrives about 60%.In other words, the opening in rotor pack 200 The size of 205 and configuration can be configured to make total material reduce total outer circumferential area 0% to about 70%, and preferably from about 30% to about 60%.

Opening 205 is set in salient angle 204, as shown in Figure 4, greatly reduces the quantity of material formed needed for rotor 30.Phase Ying Di, with solid rotor or use solid salient angle lamination laminated rotor compared with, the weight of rotor pack 200 and rotor 30 Weight reduce significantly.It is essential that rotor pack 200 and the moment of inertia of assemble rotor 30 or rotary inertia compare reality Core material rotor substantially reduces.In the embodiment shown, rotor pack 200 is made than identical material with the rotary inertia of rotor 30 And the solid rotor with identical geometric configuration is low by about 45%.The size of the opening 205 in rotor pack 200 and configuration can configure Becoming and make to compare solid rotor, rotary inertia reduces by 0% to about 45%, and preferably reduces about 25% to 55%.Although Figure 4 and 5 Shown rotor sheet is folded 200 and is illustrated in each salient angle 202 and has an opening 205, on-demand can arrange one in each salient angle Individual above opening, has two, three or four openings 205 in the most each salient angle 202.Although turning shown in Figure 4 and 5 Sub-pieces 200 is illustrated in each salient angle 202 opening 205, but can arrange many as required in each salient angle In the opening of, such as, each salient angle 202 is provided with two, three or four openings 205.

Seeing Fig. 5, opening 205-1,205-2,205-3 are as can be used for determining the several of rotor pack 200 during assembly The less circular open at what center is arranged.Hole 205-1,205-2,205-3 allow after the assembling of rotor 30 processed Journey is accurately determined and the center of labelling rotor lobes.In the case of being provided with hole 205-1,205-2 and 205-3, then The marking tool of reference opening 205-1,205-2,205-3 can be used for the course of processing.

Due to rotor 30 Quality Down in the case of being made up of at least some hollow salient angle rotor pack 200, rotor is folded Sheet 200 can be made up of such material, and it be enough under high temperature and high load condition keep structural intergrity, such as has rotor The displacement fluid decompressor 20 of assembly 5 directly receives the situation (discussed below) of the aerofluxus from internal combustion engine.At some example In, each rotor pack 200 is the most stainless by fine-edge blanking (fine blank), punching press, laser or water jet cutting sheet metal Steel, carbon steel or aluminium sheet form.Described material use silk-screen printing technique pre-coated/be coated with copper or nickel.

Rotor assemble method 1000

See Fig. 9, give the example of rotor assembly system and method 1000 according to the present invention.Note that while accompanying drawing It is shown schematically in by specific order of step, but described flow process is not necessarily limited to implement in the indicated order.Specifically, extremely Step shown in some can perform in different orders in an overlapping manner and/or perform simultaneously less.It addition, the side shown in Fig. 8 Method is substantially schematic, on the premise of without departing from central idea of the present invention can in conjunction with or change other step or step Combination.

In step 1002, it is provided that according to the multiple rotor packs 200 described before.In step 1004, stack each The rotor pack 200 provided so that at least some of and another rotor pack side 208 of one of rotor pack side 208,210, 210 is adjacent and contact.In the embodiment shown, the described side 208 of each rotor pack 200,210 is completely flat, so that Stacking time adjacent rotor pack between very close to each other.As shown, each rotor pack 200 and adjacent rotor lamination around Central axis X slightlys offset, thus forms helical rotor 30.

Notice that many configurations of stacking rotor pack 200 can use assemble method 1000.In an illustrated embodiment, This stacking may be included in the closing salient angle rotor pack with index aperture of Fig. 5 shown type at two ends, has class shown in Fig. 4 therebetween The hollow salient angle rotor pack of type.In another embodiment, this stacking can the most as shown in Figure 4 type hollow salient angle rotor fold Sheet forms.Or, this stacking may be included in the closing salient angle rotor pack of Fig. 2 shown type at two ends, has class shown in Fig. 4 therebetween The hollow salient angle rotor sheet of type.In another configuration, this stacking can include hollow convex with what solid salient angle rotor pack replaced Angle rotor pack.Or, described stacking includes it being most of lamination of hollow salient angle rotor pack, solid salient angle rotor pack edge Whole stacking is inserted by compartment of terrain, such as, has a solid salient angle rotor pack, and remaining is hollow convex in every ten laminations Angle rotor pack.

In step 1006, rotor pack 200 is secured together.The rotor pack 200 of stacking is such as solid by welding It is scheduled on together.In one example, lamination 200 is secured together by laser welding.In another example, rotor pack 200 weld together in vacuum type or continuous ribbon furnace.Or, then described lamination 200 is plated that resistance welding is together. In one embodiment, rotor pack 200 is prolonged by the every side along rotor sheet top 203 and along rotor lobes 202 Weld seam/the welding stretched is fastened, a total of nine spiral welds crossing rotor length.Other welding configuration and other attachment Means such as binding agent is also feasible.Fig. 6 shows the rotor 30 after described lamination has been stacked and has tightened together.

The most described rotor pack 200-is such as by one of said welding method-secured together, in step 1008 Rotor axle 38 is forced on rotor 30, thus produces the rotor assembly 5 shown in Fig. 1.In one embodiment, and from Fig. 7 and 8 Can find out, armature spindle 38 is formed by mould 540, thus includes around output shaft 38 with 90 degree of spaced multiple burr/hairs Thorn (burrs) 542.The height of burr 542 is set to after axle 38 is inserted into and opens with the center in the lamination 200 forming rotor 30 Mouth 212 interference engagement.This allows power to be delivered to axle 38 from rotor pack 200.

In step 1010, coating is applied to the rotor pack 200 of rotor 30.In one embodiment, described coating is Wear-resistant coating, to allow the gap more closely between a pair adjacent rotor 30, this is particularly useful for high temperature application.

Rotor assembly is applied

Above-mentioned rotor assembly 5 can be used for relating to the multiple application of rotary apparatus.Two kinds of such application are for flowing Volume expansion machine 20 and compressor 21 (such as supercharger), as shown in Figure 10.In one embodiment, fluid expanders 20 and pressure Compression apparatus 21 is positive displacement arrangements, and wherein the fluid in decompressor 20 and compressor 21 is conveyed through rotor 30, and volume/appearance Long-pending constant.Figure 10 shows to be arranged on have wheel 12 with the decompressor 20 in the vehicle 10 that moves along suitable road surface With supercharger 21.Vehicle 10 includes receiving air inlet 17 and produces in aerofluxus the power set 16 of high-temperature exhaust air form in 15.Dynamic Power apparatus 16 can be internal combustion (IC) machine or fuel cell.

As indicated, decompressor 20 receives the heat from power plant exhaust 15, and converting heat to useful work, this has It is transmitted back to power set 16 hard to improve the overall operation efficiency of power set.As configured, decompressor 20 includes shell Body 23, is provided with a pair rotor assembly 5 with intermeshing rotor 30 and axle 38 in housing.There is the swollen of rotor assembly 5 Swollen machine 20 is configured to receive the heat from power set 16 from aerofluxus directly or indirectly.

Directly receive an example of fluid expanders 20 of the aerofluxus from power set 16 at entitled " EXHAUST GAS ENERGY REVOCERY SYSTEM (exhaust energy recovery system) " PCT International Application Serial No. PCT/US2013/078037 in Open.The full content of PCT/US2013/078037 is hereby incorporated.

An example of the fluid expanders 20 of the heat from power plant exhaust is indirectly received by organic Rankine bottoming cycle Son is in the Shen, the PCT world of entitled " VOLUMETRIC ENERGY RECOVERY DEVICE (positive displacement energy recycle device) " Please be disclosed in WO2013/130774.The full content of WO 2013/130774 is hereby incorporated.

Referring also to Figure 10, compressor 21 is shown having housing 25, is disposed with and has intermeshing rotor in housing 30 and a pair rotor assembly 5 of axle 38.As configured, compressor is driven by power set 16.As configured, compression dress Put 21 amounts adding the air inlet 17 being fed to power set 16.In one embodiment, compressor 21 is entitled " OPTIMIZED HELIX ANGLE ROTORS FOR ROOTS-STYLE SUPERCHARGER is (for Roots type super charger Optimize helical angle rotor) " United States Patent (USP) US7,488,164 shown in and the root's blower of type that describes.The U.S. is special The full content of profit 7,488,164 is hereby incorporated.

Material selects

In the case of rotor 30 is disposed in housing such as housing 23 and 25, it is necessary to correctly consider for rotor and The material of housing selects, thus keeps the expectation gap between rotor and housing.Such as, incorrect material selection can cause turning Son is expanded into the inwall of housing when being heated by working fluid (such as, engine exhaust), thus damages rotor and housing, and Device is caused not work.The selection of the correct material with suitable relative thermal expansion coefficient will make turning under swelling state Son will not contact the housing also expanded, and the minimum clearance between rotor and housing can be kept within the scope of wider temperature with reality Existing maximal efficiency.Further, since rotor is more directly contacted working fluid, (use in such as aerofluxus or Rankine cycle is molten Agent), and heat can radiate to outside by housing, can expect that the degrees of expansion of described rotor is more than described housing.Therefore, for turning Son selects the material of the thermal coefficient of expansion with the thermal coefficient of expansion less than housing to be desired.

Because rotor can be provided with hollow salient angle, so the material with relatively low thermal coefficient of expansion can be used for rotor The selection of material is more extensive, because of being formed by the hollow salient angle rotor that has made by the rotor pack of relative high density Rotary inertia can equal to or less than by the casting having made by the most low-density material, machining orStackedSolid The rotary inertia of salient angle rotor.Such as, the rotary inertia that the rustless steel rotor with hollow salient angle can produce is substantially similar to The solid salient angle rotor of aluminum.Equally, disclosed rotor design is allowed for the bigger material selection of rotor, and this enters one Step has widened the suitability of the multiple material for housing.

In one specifically application, rotor assembly 5 is used for receiving in the decompressor of the aerofluxus of internal combustion engine.This In application, rotor pack 200 must by be suitable under high exhaust temperature run material be formed, such as rustless steel, tungsten, titanium, And carbon steel.Because rotor 30 can have hollow salient angle, so these materials can be used for high temperature expander application, without causing The rotary inertia of rotor 30 is the highest for Effec-tive Function.In one embodiment, rustless steel rotor combines aluminum enclosure use. Because rustless steel has the thermal coefficient of expansion lower than aluminum, so housing and rotor can expand into so that each parts expand To realizing allowing the degree in the gap of maximal efficiency.Certainly, based on desired performance standard, rotor and case material are existed Much other may.

Rotor assemble method 2000

See Figure 11-24, give an example of rotor assembly system and method 2000 according to the present invention.Notice Although accompanying drawing is shown schematically in specific order of step, but described flow process is not necessarily limited to implement with shown order.Definitely For, at least some of step in shown step can perform in different orders in an overlapping manner and/or perform simultaneously.Separately Outward, the method shown in Figure 11 is substantially schematic, can in conjunction with or change the combination of other step or step, without deviating from The central idea of the present invention.

In step 2002, it is provided that rotor set assembling device 300.As shown in figure 12, this rotor set assembling device includes end Plate 302 and the substrate 304 with central opening 304a.It is additionally provided with the mandrel 306 extended from substrate 302.See Figure 13, it is seen that base Plate 304 is arranged in mandrel 306 and is abutted against with end plate 302.As shown in figure 12, mandrel has and includes jut 308-1,308-2 Mark structure 308 with 308-3.As indicated, jut 308 along mandrel 306 length arrange and be wound around mandrel 306 Spiral, so that helical rotor 30 can be formed.However, it was noted that the length that jut 308 may be configured as being parallel to mandrel 306 is prolonged The straight jut stretched so that straight rotor 30 can be formed.

Mark structure 308 is configured to engage with the mark structure 214 of each rotor pack 200 so that when rotor pack 200 heap When being laminated in mandrel 308, jut 308-1 aligns with groove 214-1, and jut 308-2 aligns with groove 214-2, and projection Portion 308-3 aligns with groove 214-3.Be also noted that mark structure 308 can be provided with and replace the recess of jut or passage, with The respective tabs cooperation that will be arranged on rotor pack 200.

In shown specific embodiment, mark structure 308 will give the torsion of gradually spiral to assemble rotor 30, and it will There is the helical angle limited by mark structure 308.Total torsion angle of rotor 30 can be limited by the sum of the rotor pack 200 stacked And helical angle is limited by mark structure 308.In an illustrated embodiment, the mark structure 308 of mandrel the helical angle limited is Constant.But, the mark structure 308 in mandrel 306 helical angle limited can increase along the length of mandrel 306 or reduce, So that variable helical angle can be given on the rotor pack 200 of stacking.

In step 2004, it is provided that according to the multiple rotor packs 200 described before.In step 2006, will be provided Each rotor pack 200 be stacked in mandrel 306 so that mandrel 306 extends through each central opening of rotor pack 200 212 and mark structure 308,214 alignment.See Figure 14, it is seen that the first rotor lamination 200a of Figure 11 shown type and mandrel 306 alignment.Figure 15 illustrates the rotor pack 200a shown in the Fig. 5 being arranged in mandrel 306, wherein the second of Fig. 4 shown type Rotor pack 200b aligns with mandrel 306.Figure 16 illustrates that the second rotor pack 200b is arranged on adjacent to the first rotor lamination 200a In mandrel 306.Figure 17 is shown in this point wherein for the rotor pack 200 of totally 125 stackings, multiple second rotors Lamination 200b is stacked, and two other the first rotor lamination 200a rests on the method on the top of stacking. Due to the spiral mark structure 308 in mandrel 306, it is seen that each rotor pads 200 around central axis X from adjacent rotor pack Slightly offset forming helical rotor.As configured, there is not gap in the rotor pack 200 of each stacking between adjacent laminates Mode adjacent with another rotor pack 200.

Notice that many configurations of stacking rotor sheet 200 can use assemble method 2000.In an illustrated embodiment, should Stacking may be included in the closing salient angle rotor pack of the index aperture with Fig. 5 shown type at two ends, Fig. 4 shown type hollow Salient angle rotor sheet is therebetween.In another embodiment, this stacking can the hollow salient angle rotor pack of type the most as shown in Figure 4 Composition.Or, this stacking may be included in the closing salient angle rotor pack of Fig. 2 shown type at two ends, has Fig. 4 shown type therebetween Hollow salient angle rotor pack.In another configuration, it is hollow convex that this stacking can include using solid salient angle rotor pack to substitute Angle rotor pack.Or, described stacking can include that major part is the lamination of hollow salient angle rotor pack, solid salient angle rotor pack Inserted by compartment of terrain along whole stacking, such as, every ten laminations have a solid salient angle rotor pack, and remaining lamination is Hollow salient angle formula.

In step 2008, as shown in figure 18 rotor pack 200 is tightened together.In one embodiment, initially lead to Cross and top board 310 is arranged in mandrel 306 and utilizes sleeve pipe 312 and nut 314 fasten top board 310 by tight for rotor pack 200 Gu together.When nut is tightened, the rotor that compression stress is applied to stacking via top board 310, base plate 304 and mandrel 306 is folded On sheet.Then the rotor pack 200 of stacking can such as be tightened together by welding further.In one example, multiple folded Sheet 200 is tightened together by laser welding.In another example, multiple rotor packs 200 are at vacuum type or continuous band Stove welds together.Or, then described lamination 200 is plated that resistance welding is together.In one embodiment, rotor is folded The weld seam that sheet 200 is extended by the every side along rotor pack top 203 and along rotor lobes 202/be welded and fixed, always Total nine spiral welds crossing rotor length.Other welding configuration and other attachment means such as binding agent are also feasible 's.

Once rotor pack 200 is such as secured together by one of above-mentioned welding method, then can be from end plate 302, base Plate 304 and top board 306 remove rotor pack 200 and mandrel 306, as shown in figure 19.In step 2010, utilization is reconfigured for The rotor set assembling device 300 of extraction tool extracts mandrel 306 from the rotor pack 200 of fastening, and wherein the first end plate 302 is via many Individual connecting rod 322 is fastened on the second end plate 320.Then push rod 324, its rotor pack compeling to pass a mandrel through stacking can be set 200 to obtain the stacking rotor pack assembly shown in Figure 21.

In step 2012, armature spindle 38 is pressed in the rotor pack assembly of stacking and turns to be formed to assemble as shown in Figure 1 Son 30.In step 2014, apply coating to the rotor pack 200 of rotor 30.In one embodiment, described coating is wear-resisting Coating, to allow to have between two adjacent rotor 30 gap more closely, this is particularly useful in high temperature is applied.In step In rapid 1016, rotor assembly 5 is made to balance.In one embodiment, by from one or many of one or more rotor packs 200 Individual salient angle optionally removes material to make rotor assembly 5 balance.

Although describe in detail the most many optimal modes that present invention teach that for enforcement, but these teaching phases Close skilled person it will also be recognized that replacing for implementing the multiple of the teachings of the present invention within the scope of the appended claims Change face.

Claims (20)

1. the method manufacturing laminated rotor, said method comprising the steps of:
A. provide multiple rotor pack, each described lamination to have and be radially away from multiple salient angles and that central opening extends One mark structure;
B., the mandrel with the second mark structure is provided;
C. each described rotor pack is stacked in described mandrel so that described mandrel extends through the center of each described lamination Opening and the first mark structure of described rotor pack is alignd with the second mark structure of described mandrel;
D. described rotor pack is tightened together;
E. described mandrel is removed from described rotor pack;And
F. an axle is inserted in the central opening of described rotor pack.
The method of manufacture laminated rotor the most according to claim 1, wherein, the step of the multiple rotor pack of described offer Including at least some of described rotor pack, opening is set in the salient angle of described rotor pack.
The method of manufacture laminated rotor the most according to claim 1, wherein, described tightens together rotor pack Step includes welding together described rotor pack.
The method of manufacture laminated rotor the most according to claim 1, is additionally included in and described axle is inserted into described rotor Described axle is made to form the step of burr before step in the central opening of lamination.
The method of manufacture laminated rotor the most according to claim 1, wherein, described rotor is being folded by the step inserting axle Perform after the step that sheet tightens together.
The method of manufacture laminated rotor the most according to claim 1, also includes being cut by punching press, fine-edge blanking, laser Cut the one in cutting with water jet and form the step of each rotor pack in multiple rotor pack.
The method of manufacture laminated rotor the most according to claim 1, wherein, the step of described offer mandrel includes to the heart Axle arranges the second mark structure of multiple juts with the length extension along described mandrel.
The method of manufacture laminated rotor the most according to claim 7, wherein, the step of described offer mandrel includes to the heart Axle arranges second mark structure with multiple spiral protrusion portion.
The method of manufacture laminated rotor the most according to claim 8, wherein, the step of described offer mandrel includes to the heart Axle arranges second mark structure with three spiral protrusion portions.
The method of manufacture laminated rotor the most according to claim 8, wherein, it is provided that the step bag of multiple rotor packs Including and provide multiple rotor packs with multiple recess, the plurality of recess forms the first mark structure.
The method of 11. manufacture laminated rotors according to claim 10, wherein, described offer mandrel and multiple turns of offer The step of sub-lamination includes to the mandrel jut that to arrange quantity equal with the quantity of the recess being arranged on each rotor pack.
12. 1 kinds of rotor assembly, including:
The most rotor packs, each rotor pack includes:
I. the first side separated by the first thickness and the second relative side;
Ii. the central opening extended between described first side and the second side;
Iii. the multiple salient angles extended away from this central opening;
Iv. mark structure, described mark structure includes at least one recess extended from described central opening;With
B. axle, described axle extends through the central opening of each rotor pack in the plurality of rotor pack;
Wherein, the plurality of rotor pack is stacked and tightens together to form described rotor assembly so that a rotor At least one in first side of at least one in the first side of lamination and the second side and another rotor pack and the second side Adjacent and contact.
13. rotor assembly according to claim 12, wherein, described rotor pack relative to each other rotates to form spiral Rotor.
14. rotor assembly according to claim 13, wherein, each the rotor pack bag in the plurality of rotor pack Include the first salient angle, the second salient angle and the 3rd salient angle being angularly radially spaced.
15. rotor assembly according to claim 14, wherein, each rotor pack in the plurality of rotor pack is also Including the 4th salient angle, wherein said first salient angle, the second salient angle, the 3rd salient angle and the 4th salient angle are angularly radially spaced.
16. rotor assembly according to claim 13, wherein, described helical rotor have be substantially equal to stacking multiple The total length of the summation of described first thickness of rotor pack.
17. rotor assembly according to claim 12, wherein, each salient angle in the plurality of salient angle includes salient angle Opening.
18. rotor assembly according to claim 12, wherein, each rotor pack in described rotor pack is by gold Belong to material to be formed.
19. rotor assembly according to claim 18, wherein, each rotor pack in described rotor pack is not by Rust steel is formed.
20. rotor assembly according to claim 18, wherein, described rotor pack is by being weldingly secured at together.
CN201580012975.9A 2014-03-12 2015-03-11 For the method manufacturing low inertia laminated rotor CN106103998A (en)

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Families Citing this family (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2014081823A1 (en) 2012-11-20 2014-05-30 Eaton Corporation Composite supercharger rotors and methods of construction thereof
EP2971776A2 (en) 2013-03-15 2016-01-20 Eaton Corporation Low inertia laminated rotor
WO2020165689A1 (en) * 2019-02-12 2020-08-20 Atlas Copco Airpower, Naamloze Vennootschap Screw rotor and method for manufacturing such screw rotor

Citations (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2304067A (en) * 1940-07-29 1942-12-08 Fairbanks Morse & Co Production of rotors for electric machines
US2362106A (en) * 1941-04-21 1944-11-07 Equi Flow Inc Laminated gear pump
US2368295A (en) * 1942-09-14 1945-01-30 Allis Louis Co Method of making cast squirrel cage rotors
EP0477601A1 (en) * 1990-09-28 1992-04-01 Leybold Aktiengesellschaft Method of making a rotor for a vacuum pump and rotor made according to this method
US5290150A (en) * 1991-10-17 1994-03-01 Ebara Corporation Screw rotor comprising a plurality of thin plates
CN101265816A (en) * 2007-01-11 2008-09-17 通用汽车环球科技运作公司 Rotor assembly and method of forming
JP2011112019A (en) * 2009-11-30 2011-06-09 Hitachi Industrial Equipment Systems Co Ltd Method of manufacturing screw rotor, screw rotor, and water injection type screw compressor
CN104052175A (en) * 2013-03-15 2014-09-17 伊顿公司 Low inertia laminated rotor

Family Cites Families (26)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US1304102A (en) * 1919-05-20 routledge
US885109A (en) * 1905-11-02 1908-04-21 Thomas Frederick John Truss Screw-propeller.
US1399290A (en) * 1920-11-16 1921-12-06 Brulle Alexander Propeller for aircraft
US1610816A (en) * 1925-02-09 1926-12-14 Gen Electric Alternating-current motor
US2139748A (en) * 1936-11-18 1938-12-13 Reliance Electric & Eng Co Squirrel cage rotor and process for making the same
US2325617A (en) * 1938-01-13 1943-08-03 Jarvis C Marble Rotor
US2483024A (en) * 1945-03-03 1949-09-27 Casner Patents Inc Method of manufacturing dynamo-electric machines
US2763916A (en) * 1953-08-19 1956-09-25 Emerson Electric Mfg Co Method of making cast rotors
GB799337A (en) * 1956-01-12 1958-08-06 Wade Engineering Ltd Improvements in rotary motors of the roots blower type
US3175277A (en) * 1961-02-16 1965-03-30 Red Jacket Mfg Co Method of making stators
US3490143A (en) * 1964-06-26 1970-01-20 Bobbie B Hull Method of manufacturing a core for an electrical inductive device
US3706511A (en) * 1971-04-06 1972-12-19 Atomic Energy Commission Laminated plastic propeller
US3918838A (en) * 1974-01-04 1975-11-11 Dunham Bush Inc Metal reinforced plastic helical screw compressor rotor
US4015154A (en) * 1974-12-23 1977-03-29 Sony Corporation Motor and method for making same
US4272579A (en) * 1977-07-27 1981-06-09 Mitsui Mfg. Co., Ltd. Laminated stack manufacture
US5087849A (en) * 1983-03-25 1992-02-11 L H Carbide Corporation Laminated parts and a method for manufacture thereof
US4710085A (en) * 1986-02-20 1987-12-01 Statomat-Globe, Inc. Lamination stack selection method and apparatus
SE470337B (en) * 1986-09-05 1994-01-24 Svenska Rotor Maskiner Ab The rotor for a rotary screw machine and process for its manufacturing
JPH06101671A (en) * 1992-09-21 1994-04-12 Kobe Steel Ltd Screw rotor
JP2945228B2 (en) * 1993-02-18 1999-09-06 ファナック株式会社 Method of manufacturing cage rotor for high-speed induction motor
SE9903772D0 (en) * 1999-10-18 1999-10-18 Svenska Rotor Maskiner Ab Polymer Rotor and method for making polymerrotorer
JP4013537B2 (en) * 2001-12-17 2007-11-28 株式会社日立製作所 Fiber reinforced resin screw rotor
JP4504836B2 (en) * 2005-02-23 2010-07-14 株式会社日立産機システム Screw rotor manufacturing method
WO2007031092A1 (en) * 2005-05-06 2007-03-22 Inter-Ice Pump Aps A rotor, a method for producing such rotor and a pump comprising such rotor
JP4176121B2 (en) * 2006-10-13 2008-11-05 株式会社三井ハイテック Rotor laminated iron core and manufacturing method thereof
US8993084B2 (en) * 2010-08-17 2015-03-31 The Boeing Company Multi-layer metallic structure and composite-to-metal joint methods

Patent Citations (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2304067A (en) * 1940-07-29 1942-12-08 Fairbanks Morse & Co Production of rotors for electric machines
US2362106A (en) * 1941-04-21 1944-11-07 Equi Flow Inc Laminated gear pump
US2368295A (en) * 1942-09-14 1945-01-30 Allis Louis Co Method of making cast squirrel cage rotors
EP0477601A1 (en) * 1990-09-28 1992-04-01 Leybold Aktiengesellschaft Method of making a rotor for a vacuum pump and rotor made according to this method
US5290150A (en) * 1991-10-17 1994-03-01 Ebara Corporation Screw rotor comprising a plurality of thin plates
CN101265816A (en) * 2007-01-11 2008-09-17 通用汽车环球科技运作公司 Rotor assembly and method of forming
JP2011112019A (en) * 2009-11-30 2011-06-09 Hitachi Industrial Equipment Systems Co Ltd Method of manufacturing screw rotor, screw rotor, and water injection type screw compressor
CN104052175A (en) * 2013-03-15 2014-09-17 伊顿公司 Low inertia laminated rotor
CN204012971U (en) * 2013-03-15 2014-12-10 伊顿公司 Rotor assembly and whirligig

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EP3117102A1 (en) 2017-01-18
EP3117102A4 (en) 2017-12-13
WO2015138557A1 (en) 2015-09-17

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