CN104018886B - Turbo-charger impeller with Noise measarement - Google Patents
Turbo-charger impeller with Noise measarement Download PDFInfo
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- CN104018886B CN104018886B CN201410061139.7A CN201410061139A CN104018886B CN 104018886 B CN104018886 B CN 104018886B CN 201410061139 A CN201410061139 A CN 201410061139A CN 104018886 B CN104018886 B CN 104018886B
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- 230000008859 change Effects 0.000 claims description 17
- 238000000034 method Methods 0.000 claims description 10
- 238000005457 optimization Methods 0.000 claims description 8
- 238000004590 computer program Methods 0.000 claims description 6
- 238000013461 design Methods 0.000 claims description 6
- 238000012545 processing Methods 0.000 claims description 5
- 238000003754 machining Methods 0.000 claims 1
- 239000002912 waste gas Substances 0.000 description 11
- 238000002485 combustion reaction Methods 0.000 description 5
- 238000010276 construction Methods 0.000 description 4
- 238000004364 calculation method Methods 0.000 description 3
- 238000007906 compression Methods 0.000 description 3
- 238000001816 cooling Methods 0.000 description 3
- 238000009826 distribution Methods 0.000 description 3
- 238000005259 measurement Methods 0.000 description 3
- 230000008901 benefit Effects 0.000 description 2
- 230000006835 compression Effects 0.000 description 2
- 238000005516 engineering process Methods 0.000 description 2
- 238000004519 manufacturing process Methods 0.000 description 2
- 238000012986 modification Methods 0.000 description 2
- 230000004048 modification Effects 0.000 description 2
- 230000008569 process Effects 0.000 description 2
- 238000004891 communication Methods 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 230000006870 function Effects 0.000 description 1
- 239000000463 material Substances 0.000 description 1
- 230000007246 mechanism Effects 0.000 description 1
- LCCNCVORNKJIRZ-UHFFFAOYSA-N parathion Chemical compound CCOP(=S)(OCC)OC1=CC=C([N+]([O-])=O)C=C1 LCCNCVORNKJIRZ-UHFFFAOYSA-N 0.000 description 1
- 238000003672 processing method Methods 0.000 description 1
- 230000001052 transient effect Effects 0.000 description 1
- 238000011144 upstream manufacturing Methods 0.000 description 1
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
- F01D5/04—Blade-carrying members, e.g. rotors for radial-flow machines or engines
- F01D5/043—Blade-carrying members, e.g. rotors for radial-flow machines or engines of the axial inlet- radial outlet, or vice versa, type
- F01D5/048—Form or construction
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D25/00—Pumping installations or systems
- F04D25/02—Units comprising pumps and their driving means
- F04D25/024—Units comprising pumps and their driving means the driving means being assisted by a power recovery turbine
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D29/00—Details, component parts, or accessories
- F04D29/26—Rotors specially for elastic fluids
- F04D29/28—Rotors specially for elastic fluids for centrifugal or helico-centrifugal pumps for radial-flow or helico-centrifugal pumps
- F04D29/284—Rotors specially for elastic fluids for centrifugal or helico-centrifugal pumps for radial-flow or helico-centrifugal pumps for compressors
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D29/00—Details, component parts, or accessories
- F04D29/66—Combating cavitation, whirls, noise, vibration or the like; Balancing
- F04D29/661—Combating cavitation, whirls, noise, vibration or the like; Balancing especially adapted for elastic fluid pumps
- F04D29/666—Combating cavitation, whirls, noise, vibration or the like; Balancing especially adapted for elastic fluid pumps by means of rotor construction or layout, e.g. unequal distribution of blades or vanes
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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
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2260/00—Function
- F05D2260/96—Preventing, counteracting or reducing vibration or noise
- F05D2260/961—Preventing, counteracting or reducing vibration or noise by mistuning rotor blades or stator vanes with irregular interblade spacing, airfoil shape
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
- Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
- Y10T29/00—Metal working
- Y10T29/49—Method of mechanical manufacture
- Y10T29/49229—Prime mover or fluid pump making
- Y10T29/49236—Fluid pump or compressor making
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Supercharger (AREA)
Abstract
The present invention relates to the turbo-charger impeller with Noise measarement.Turbocharger turbine wheel includes a wheel hub and multiple blades.The barycenter of the barycenter of wheel hub and multiple blades is all on rotation axis.Blade is circumferentially spaced so that they are rotatably asymmetric.The continuous blade of each pair is characterized with interval angles.With the jante et perpendiculaire and line that is orthogonal to rotation axis limits the plane of symmetry, and interval angles are symmetrical across the plane of symmetry.
Description
Technical field
The present invention relates to a kind of impeller for turbocharger, relate more specifically to a kind of automobile turbocharger leaf
Wheel, it has the blade spaced apart to limit the angle of the generation of the noise in the range of audibility.
Background technology
Radial-flow type vehicle turbine machine is commonly configured with inlet volute, and waste gas stream is spiraled in the inlet volute, to drive whirlpool
The blade of engine blade wheel.In the position of the spiral case decontroled to turbine wheel first around wherein exhaust stream, there is its Leaf
The architectural feature away from spiral case wall is gone to from the spiral case wall against surrounding.Due to this feature outward appearance in cross section, so sometimes
It is referred to as tongue.
Automobile turbocharger usually has about seven to ten eight turbine blades.In relatively low blade quantity scope
It is interior, and in the typical turbine speed of rotation, the frequency that blade can be in human audible range is by tongue.This is produced
Undesirable drone noise.
One solution of the problem is the quantity for increasing blade, such as less automobile turbocharger from ten
One to ten three blades.This make blade in typical service speed with the frequency higher than human audible range by tongue.No
Good fortune, the increase of blade quantity can cause several undesirable consequences.For example, the increase of blade can cause manufacture more expensive
Impeller (increase due to material and the increase due to processing cost).Further, since the base portion presence in each blade is smaller
Space is used for fillet, so blade support is weakened, causes less durable turbine wheel.Further, since impeller may have
There is larger rotary inertia, so the change such as to pressure at expulsion during engine transient operating conditions is less responded.
In the presence of the demand to durable cost-efficient turbine wheel, it makes undesirable noise minimum.This hair
Bright preferred embodiment meets these and other demands, and provides other related advantage.
The content of the invention
In various embodiments, some in present invention solution the demand or whole demands, are made undesirable with offer
The minimum durable cost-efficient turbine wheel of noise.
The turbo-charger impeller of a part as rotor set, such as turbine wheel, including a wheel hub and multiple
Blade.Turbine wheel is characterized by limiting the line of rotation axis.The CM of the barycenter (" CM ") of wheel hub and multiple blades
On rotation axis.Multiple blades are spaced apart around circumference of hub so that blade is rotatably asymmetric around rotation axis.Have
Sharp ground, this is asymmetric to be dispersed on a different frequency for scope blade by the acoustic energy that volute tongue is generated, so as to subtract
Few acoustic energy at any one frequency.This in turn provides vehicle turbine machine impeller with than may additionally for rotate it is right
The desired less blade of the blade of title is made, and acoustic energy is concentrated on the audible frequency of the mankind by the rotationally symmetrical blade.
The continuous blade of each pair is characterized with the interval angles between this pair of continuous blade.Can iteratively calculate and meet institute
The one group of interval angles for requiring.In other feature, turbo-charger impeller, such as turbine wheel, with Article 2 line
It is characterized, the Article 2 line intersects and be orthogonal to the line with the line for limiting rotation axis.Limit the line and Article 2 of rotation axis
Line is by extending along plane and is comprised in plane and limits the plane of symmetry, and multiple blades interval angles across symmetrical
Face is symmetrical.Advantageously, the plane symmetry provide using the variable number for substantially reducing and the calculation times for therefore reducing come
Iterative calculation angle.
It is combined as the accompanying drawing of example illustration principle of the invention, other features and advantages of the present invention will be from being preferable to carry out
The described further below of example becomes apparent.It is as set forth below allowing one to set up and use embodiments of the invention
, the detailed description of specific preferred embodiment is not used in the claim that limitation is enumerated, but they are defined as with being required
The particular example of the invention of protection.
Brief description of the drawings
Fig. 1 is the system view of the embodiment of turbocharging internal-combustion engines of the invention.
Fig. 2 is the viewgraph of cross-section of the turbine of the turbocharging internal-combustion engines described for Fig. 1.
Fig. 3 is one group of description of spacing with blades angle with symmetrical plane.
Fig. 4 is to design and produce the implementation for the method for producing the turbo-charger impeller of turbo-charger impeller to process
Example.
Fig. 5 is the description of the skew between a group of pivot and CM of blade.
Fig. 6 is one group of description of spacing with blades angle with symmetrical plane and with odd number of blades.
Fig. 7 is one group of description of spacing with blades angle with symmetrical plane and with even number blade.
Specific embodiment
It is better understood by reference to the following detailed description that should be read together with accompanying drawing outlined above and by enumerating
Claim limit the present invention.The detailed description of particularly advantageous embodiment of the invention, is stated to make one below
Can set up and use specific implementation of the invention, be not used in the claim enumerated of limitation, but it is used to provide them
Particular example.
Exemplary embodiments of the invention are the motor vehicles equipped with internal combustion engine (" ICE ") and turbocharger.Turbine
Pressure booster distribution is had with unique blade turbine wheel for being characterized of construction, and unique blade construction provides durability, low turns
Dynamic the moment of inertia and the quiet operation in human hearing range.
With reference to Fig. 1, the exemplary embodiments of the turbocharger 101 with radial-flow turbine and centrifugal compressor include
Turbocharger housing and rotor set, the rotor set are configured in thrust bearing and two groups of bearings of journals that (one group is used for a phase
The impeller of rotor answered) on or alternatively on other similar spring bearings during turbocharger operation around rotation
Shaft axis 103 rotate in turbocharger housing.Turbocharger housing includes turbine cylinder 105, compressor housing 107
With bear box 109 (that is, the center housing comprising bearing), turbine cylinder is connected to compression case by the bear box 109
Body.Rotor set includes：Radial-flow turbine wheel 111, it is located substantially in turbine casing body；Centrifugal compressor impeller 113,
It is located substantially in compression case body；With axle 115, it extends through bear box along rotation axis, by turbine wheel
It is connected to compressor impeller.
Turbine cylinder 105 and turbine wheel 111 form turbine, the turbine mechanism causes from engine, for example from
The exhaust manifold 123 of internal combustion engine 125 circumferentially receives HTHP waste gas stream 121.Turbine wheel (and so as to rotor set)
Rotation axis 103 is driven around by HTHP waste gas stream to rotate, the HTHP waste gas stream becomes low-temp low-pressure waste gas stream 127
And be axially released into an exhaust system in (not shown).
Compressor housing 107 and compressor impeller 113 form compressor stage.Driven by exhaust-driven turbine wheel 111
Input air that the compressor impeller of dynamic rotation is configured to axially receive (for example, surrounding air 131, or pressed from multistage
The forced air of the previous stage in contracting machine) forced air stream 133 is compressed into, the forced air stream 133 is from compressor by circumference
Ground discharge.Due to compression process, so forced air stream is characterized with the temperature of the raising of the temperature higher than input air.
Selectively, forced air stream is directed through convection current cooling charger-air cooler 135, and convection current cooling increases
Pressure aerial cooler 135 is configured to from forced air stream dissipation heat, to improve its density.The output of resulting cooling pressurization is empty
Air-flow 137 is directed into the inlet manifold 139 on internal combustion engine, or the compressors in series for being alternatively directed into rear stage
In.The operation of system is controlled by the ECU151 (control unit of engine) that the remainder of system is connected to via communication connection
System.
Turbine
With reference to Fig. 1 and 2, turbine cylinder 105 forms the waste gas entering path 217 for leading to main volute path 219, the waste gas
Entering path 217 is configured to orthogonal with rotor set rotation axis 103 and from the direction of the radial deflection of rotor set rotation axis 103
On from engine receive waste gas stream.Main volute path substantially forms convergence path, and the convergence path is to inside spin and is converged to foot
So that waste gas 223 accelerates, the waste gas 223 is guided into by the axial direction for clashing into turbocharger turbine blade 231 with funnel-form
Upstream end 275, then passes through the gap between blade.
Lead to the position of main volute path 219 in waste gas entering path 217, exist with ought in the cross-section of fig. 2 (i.e.,
It is orthogonal with rotor set rotation axis 103) observation when the structure that is characterized of tongue-like shape.More specifically, the structure of tongue 235 is in
It is now the cuspidated protrusion of tool.
For typical automobile turbocharger it is desirable that having about 11 turbine blades 231, and
Usually there is the radius between 12mm and 75mm.In the vehicle turbine machine of typical 11 blades, and typical
During the vehicle turbine machine speed of rotation, frequency of the blade in human audible range is by tongue 235.This produce it is undesirable drone
Drone noise.
First embodiment of the invention, as the turbine blade 111 of a part for rotor set limiting rotary shaft
The line (that is, axis is conllinear with the line) of line 103 is characterized.Turbine wheel may include that rotationally symmetrical wheel hub 241 (may be to enclose
Rotate about the rotor that the spherical symmetric of axis is characterized).The multiple blades of turbine hub support.The barycenter (" CM ") of wheel hub is in rotation
On axis, and the CM of multiple blades is same on rotation axis.
Different from the turbine wheel of prior art, multiple blades 231 are separated with the angle for changing around circumference of hub,
So that blade is rotatably asymmetric around rotation axis 103.For this application, it should be understood that term is not " rotatably right
Claim " it is defined as meaning that impeller can not be around rotation axis (with any amount in addition to 360 degree of integral multiple) rotation extremely
The position of structure roughly the same (that is, reasonably measuring identical in tolerance levels in function).
In this particular embodiment, turbine wheel 111 is only made up of wheel hub 241 and multiple blades 231, and wheel hub
It is rotatably symmetrical around rotor set rotation axis.It should be understood that blade is included the fillet of blade root stress distribution to wheel hub.
Referring to figs. 1 to 3, in order that blade 231 is rotatably asymmetric, the continuous blade of each pair is characterized by this
To the S of interval angles 301 between continuous bladen.Interval angles can be from continuous blade any reference point (that is, any axle
To, radial direction and circumferential position) start measurement, as long as the same reference from each blade is lighted as one man carrying out.For example,
Can be from the preceding genesis measurement interval angle of blade, wherein leading edge is connected to wheel hub on each blade.Alternatively, can be from each
The CM of blade plays measurement interval angle, and this can simplify the calculating of the CM of whole group blade.Interval angles SnWill not be right with generation rotation
The pattern periodicity ground of title changes.
Avoid the rotationally symmetrical of impeller 111 (and, more specifically, blade 231) and also with rotor set rotary shaft
The calculating of this group of interval angles 301 of the CM on line 103 is complicated mathematical problem.Can be right by allowing the interval of blade to have
Title face and substantially simplify the problem.(and, more specifically, multiple turbine blades) is with the more specifically, turbine wheel
Two-lines 303 are characterized, and the Article 2 line 303 is orthogonal with the line for limiting rotor rotation axis 103 and intersects.Rotation axis and
Two-lines are by extending along plane and be comprised in plane and limit the plane of symmetry, and multiple blades interval angles across
The plane of symmetry is symmetrical (i.e., as indicated in figure 3, they are mirror image).Extend across the plane of symmetry in an interval angles
In the case of, it is halved by plane so that the half of the interval angles is on every side of plane.
As indicated previously, the solution in the prior art of the problem is that the quantity of blade is increased into boom frequency
Point (for example, being higher than 20,000Hz) outside human hearing range.One of shortcoming of the solution is that blade is crowded to be limited
The size of fillet, and therefore limit the distribution of blade root stress.Therefore, for making buzz needed for human hearing range is outer
Minimum blade quantity (for example, 13) and quantity (for example, 18) that may be larger, preferably at least by the S of spacing with blades angle 301n
The minimum dimension of the spacing with blades being restricted between evenly spaced blade, as long as blade root stress is in acceptable level
Can.As alluded to above, a series of problem for finding good spacing with blades angles 301 is difficult optimization problem.This is asked
Topic can be solved by using the computerization software systems of iteration.The system is programmed to implement a kind of design and produces for producing
The method of the turbine wheel processing of the raw turbine wheel with the n asymmetric blade for separating and rotation axis.
With reference to Fig. 3 to 5, multiple steps are considered as providing design and producing for producing, there is n asymmetric to separate
Blade and rotation axis turbo-charger impeller turbo-charger impeller processing method.Blade must first be established
Quantity and the initial gap angle S for the continuous blade of each pairIN.The quantity of blade will be typically based on the expection of such as turbine
The desired turbine parameters and aerodynamic Consideration of service speed are selected by design team.Can be with various differences
Mode set initial gap angle.For example, equispaced angle can change at random, or design team can arbitrarily select number
Amount.Typically, it is desirable to, it is initial using what is significantly changed from a spacing with blades angle to next spacing with blades angle
The value of interval angles 301.An exception to this is for the impeller with odd number of blades and in two continuous angular intervals
The plane of symmetry on line between degree, wherein, in the plane will be inherently identical close to the interval angles on opposite side.
Next, running iteration optimization computer program 403 on computers.Program structure is solved into using following steps
Affined optimization problem：(1) barycenter 501 for calculating whole group impeller 231 or whole impeller 111 (that is, represents blade on rotor
The CM of the CM of rotation axis) 405；(2) interval angles 407 are iteratively adjusted so that the barycenter of calculating and impeller rotating shaft line it
Between distance reduce, and interval angles change according to one group of one or more constraints and target variable, to limit
The acoustic energy produced at audible any one frequency of the mankind；(3) iteration 409 is continued, until the CM for calculating effectively exists
On rotation axis, and optimize the change of continuous interval angles, to establish one group of final interval with continuous order
Angle SFUntill.Due to the field of iteratively optimized variable being known for computer process, so need not optimize
The more details of computer program.
The distance between barycenter and impeller rotating shaft line of calculating are relatively straightforward calculating.However, it is a variety of about
Beam condition and/or target variable can be used to be limited in the acoustic energy generated at any one frequency.Every group of one or more constraint bar
Part and target variable have intensity and weakness, the calculating time for such as being needed in optimal acoustics solution is represented and/or essence
Degree.Such constraints and target variable may include the comparing of continuous blade angle and the ratio that all blade angles are mutual
Compared with, and other options.
Constraint and the example of target variable as the above-mentioned first kind, minimum and maximum angle is constrained in blade angle
While in degree, usable target variable makes the change of each continuous blade angle maximum.As above-mentioned Second Type
The example of constraints and target variable, while blade angle is constrained between minimum and maximum angle, can make the group
The standard deviation of all blade angles is maximum.
For this application, when optimizing computer program iteratively reaches the optimal level of target variable, it is continuous between
It is considered as (for example, the change of the continuous blade angle of each pair is maximized) for optimizing every the change of angle.It should be noted that
It is that when using different constraints and/or angle on target, the interval angles of optimization are probably different.Other usable mesh
Mark variable includes：Target standard deviation level (rather than maximum), angle on target change are (rather than maximum), in a certain model
Angle change in enclosing etc..
The step of iteration adjustment interval angles 407, is preferably carried out by increasing the change of continuous interval angles.Should
, it is noted that various technologies can be used, to establish the change level of continuous interval angles.For example, it is continuous to calculate each pair
The sum of the absolute value of the difference between interval angles.The number is bigger, then be considered as between all such consecutive intervals angles
Change is bigger.
It should be noted that during the iteration of solution, unless interval angles are considered as between the CM of each blade
Interval, otherwise CM is not limited to the plane of symmetry.
Once optimization program establishes one group of final interval angles S with sequential orderF, just form processing 411.Processing is configured to
Generation can be used to produce with the final interval angles S of the group with sequential orderFThe space of the turbine wheel being characterized.
As discussed above, when spacing with blades angle across the plane of symmetry be symmetrical when, optimization problem is simplified.In order to
Implement it, 401 the step of initial gap angle is established in, initial gap angle SINIt is symmetrical to be selected as across the plane of symmetry
421, the plane of symmetry comprising limit rotation axis line and partly by limit rotation axis line restriction.In addition, being changed in operation
In the step of for optimizing computer program 403, the iteration adjustment of interval angles maintains interval angles across the symmetrical of the plane of symmetry
423.Advantageously, the quantity of variable is which reduced.
As previously discussed, preferably setting is in view of good machinery and the minimum interval of air dynamic behaviour
Angle.Therefore, in the step of iteratively adjusting interval angles, each interval angles is constrained to more than minimum interval angle
SMIN, such as 20.0 or 27.7 degree (interval with 18 or 13 blades of evenly-spaced blade is corresponding).
With reference to Fig. 6 and 7, it is noted that can be realized using the meter of the plane of symmetry for odd number of blades or even number blade
Calculate simplified program.As shown in fig. 6, in order to provide odd number of blades, it is considered to which the reference point of the first blade 601 is in the plane of symmetry 303
On, and relative interval angles 603 on the opposite side of impeller are halved by the plane of symmetry.One side effect of do so is
(on the either side of the first blade) has the adjacent spacing with blades angle of identical two.As shown in fig. 7, in order to provide even number
Individual blade, it is considered to without blade reference point on the plane of symmetry, and two relative interval angles on the opposite side of impeller
Each of 701 are halved by the plane of symmetry.In any case, it is not necessary in order to the purpose that CM is calculated is used in the angle being bisected into
One, but it is preferred that using it for interval angles change calculations.
It should be understood that the present invention includes the apparatus and method for designing and for producing turbine blade, and whirlpool
The equipment of turbine blade is in itself.The alternate variation of these embodiments may include other kinds of blade construction.Although additionally, this hair
It is bright to be described as turbine wheel, but compressor impeller within the scope of the invention, but can equally there may be larger
Flowing instability problem risk.In a word, in desired extent of the invention, features disclosed above can be various
It is combined in construction.
Although having illustrated and having described particular form of the invention, but it will be apparent that without departing from essence of the invention
Various modifications can be made in the case of god and scope.Therefore, although describing the present invention in detail only with reference to preferred embodiment, this
The technical staff in field will be appreciated that can make various modifications in the case of without departing from the scope of the present invention.Therefore, originally
Invention is defined as not by limitation described above, and is defined with reference to appended claim.
Claims (11)
1. a kind of turbo-charger impeller used for rotor set, including：
Wheel hub；And
Multiple blades；
Wherein, the turbo-charger impeller is characterized by rotation axis；
Wherein, the barycenter of the wheel hub is on the rotation axis；
Wherein, the barycenter of the multiple blade is on the rotation axis；And
Wherein, the multiple blade is spaced apart around the circumference of hub so that the multiple blade is around the rotation
Axis is rotatably asymmetric；
Wherein, the consecutive intervals angle between the blade of continuous pairs circumferentially changes；
The plane of symmetry is partly limited by the rotation axis, and the rotation axis extends along the plane of symmetry；And
The interval angles of the multiple blade are symmetrical across the plane of symmetry.
2. turbo-charger impeller according to claim 1, wherein, the impeller is only by the wheel hub and the multiple leaf
Piece is constituted, and wherein, the wheel hub is rotatably symmetrical.
The interval angles of the multiple blade are symmetrical across the plane of symmetry.
3. turbo-charger impeller according to claim 1, wherein, the impeller has half between 12mm and 75mm
Footpath.
4. turbo-charger impeller according to claim 3, wherein：Described each interval angles are more than 20.0 degree.
5. turbo-charger impeller according to claim 1, wherein：Described each interval angles are more than 20.0 degree.
6. it is a kind of to design and produce the turbocharger for producing the turbo-charger impeller with n blade and rotation axis
The method of Impeller Machining, including：
It is the continuous blade establishment initial gap angle S of each pairIN；
Iteration optimization computer program is run on computers, and described program is configured to solve optimization problem using following steps：
The barycenter for representing the multiple barycenter of the blade on the rotation axis is calculated,
Iteratively adjust the interval angles so that the distance between the barycenter of the calculating and described vane rotor rotation axis
Reduce, and the interval angles change over the acoustic energy for being enough to be limited in and being produced at audible any one frequency of the mankind；With
Continue the iteration, until the barycenter of the calculating is actually on the rotation axis, and make the interval angles
Change optimize so as to continuous order establish one group of final interval angles SF；And
Once the optimization program has established one group of final interval angles SF, just being formed and processed, the processing is configured to generation can
For producing with the final interval angles S of the group with sequential orderFThe space of the turbo-charger impeller being characterized.
7. method according to claim 6, wherein, in the step of continuing the iteration, iteratively adjust the interval
Angle so that the change of the continuous interval angles is optimized.
8. method according to claim 6, wherein：
In the step of establishing, the initial gap angle SINBe selected as across partly by the rotation axis limit it is right
Title face is symmetrical, and the rotation axis extends along the plane of symmetry；And
In the step of running iteration optimization computer program, the iteration adjustment of the interval angles maintains the interval angles horizontal
Across the symmetrical of the plane of symmetry.
9. method according to claim 8, wherein, in the step of continuing the iteration, iteratively adjust the interval
Angle so that the change of the continuous interval angles is optimized.
10. method according to claim 6, wherein, described each interval angles are confined to more than minimum interval angle
SMIN。
11. methods according to claim 10, wherein, the minimum interval angle SMINIt is 20.0 degree.
Applications Claiming Priority (3)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| US13/815,373 US20140241866A1 (en) | 2013-02-25 | 2013-02-25 | Turbocharger wheel with sound control |
| US13/815373 | 2013-02-25 | ||
| US13/815,373 | 2013-02-25 |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN104018886A CN104018886A (en) | 2014-09-03 |
| CN104018886B true CN104018886B (en) | 2017-07-11 |
Family
ID=50068834
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201410061139.7A Expired - Fee Related CN104018886B (en) | 2013-02-25 | 2014-02-24 | Turbo-charger impeller with Noise measarement |
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| Country | Link |
|---|---|
| US (1) | US20140241866A1 (en) |
| EP (1) | EP2770163B1 (en) |
| KR (1) | KR20140106406A (en) |
| CN (1) | CN104018886B (en) |
Families Citing this family (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE102013224081B4 (en) * | 2013-11-26 | 2015-11-05 | Man Diesel & Turbo Se | compressor |
| CN105156365B (en) * | 2015-10-14 | 2018-08-31 | 联想(北京)有限公司 | Fan and electronic equipment |
| US10513936B2 (en) * | 2018-04-02 | 2019-12-24 | Garrett Transportation I Inc. | Turbine housing for turbocharger with linear A/R distribution and nonlinear area distribution |
| DE112020007249T5 (en) * | 2020-11-25 | 2023-03-16 | Mitsubishi Heavy Industries Engine & Turbocharger, Ltd. | TURBOCHARGER |
| CN114636197B (en) * | 2022-03-31 | 2023-09-08 | 广东美的白色家电技术创新中心有限公司 | Cross-flow fan and air conditioner |
| CN115306487B (en) * | 2022-08-05 | 2025-08-29 | 中国航发贵阳发动机设计研究所 | A design method for asymmetric guide vanes suitable for high-pressure turbine rotor blade vibration reduction |
Citations (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4253800A (en) * | 1978-08-12 | 1981-03-03 | Hitachi, Ltd. | Wheel or rotor with a plurality of blades |
| US6457941B1 (en) * | 2001-03-13 | 2002-10-01 | The United States Of America As Represented By The Secretary Of The Navy | Fan rotor with construction and safety performance optimization |
Family Cites Families (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5681145A (en) * | 1996-10-30 | 1997-10-28 | Itt Automotive Electrical Systems, Inc. | Low-noise, high-efficiency fan assembly combining unequal blade spacing angles and unequal blade setting angles |
| US6379112B1 (en) * | 2000-11-04 | 2002-04-30 | United Technologies Corporation | Quadrant rotor mistuning for decreasing vibration |
| US8398380B2 (en) * | 2009-09-02 | 2013-03-19 | Apple Inc. | Centrifugal blower with non-uniform blade spacing |
| EP2535526B1 (en) * | 2011-06-17 | 2013-10-30 | Aktiebolaget SKF | Turbocharger, notably for a combustion engine. |
-
2013
- 2013-02-25 US US13/815,373 patent/US20140241866A1/en not_active Abandoned
-
2014
- 2014-02-04 EP EP14153874.4A patent/EP2770163B1/en not_active Not-in-force
- 2014-02-19 KR KR1020140018867A patent/KR20140106406A/en not_active Withdrawn
- 2014-02-24 CN CN201410061139.7A patent/CN104018886B/en not_active Expired - Fee Related
Patent Citations (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4253800A (en) * | 1978-08-12 | 1981-03-03 | Hitachi, Ltd. | Wheel or rotor with a plurality of blades |
| US6457941B1 (en) * | 2001-03-13 | 2002-10-01 | The United States Of America As Represented By The Secretary Of The Navy | Fan rotor with construction and safety performance optimization |
Also Published As
| Publication number | Publication date |
|---|---|
| KR20140106406A (en) | 2014-09-03 |
| US20140241866A1 (en) | 2014-08-28 |
| CN104018886A (en) | 2014-09-03 |
| EP2770163B1 (en) | 2016-06-22 |
| EP2770163A1 (en) | 2014-08-27 |
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