CN1236196C - Centrifugal or mixed-flow turbine machinery - Google Patents
Centrifugal or mixed-flow turbine machinery Download PDFInfo
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- CN1236196C CN1236196C CN 94195152 CN94195152A CN1236196C CN 1236196 C CN1236196 C CN 1236196C CN 94195152 CN94195152 CN 94195152 CN 94195152 A CN94195152 A CN 94195152A CN 1236196 C CN1236196 C CN 1236196C
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Abstract
The present invention relates to an impeller (6) of turbine machinery, which comprises blades (3), wherein the contrast static pressure difference delta Cp between an impeller hub (2) and a covering plate (4) on the negative pressure surface of the blades (3) is obviously reduced in the position near an impeller outlet (6b) when the blades (3) approach the impeller outlet from the position between an impeller inlet (6a) and the impeller outlet (6b) because of the design of the blades.
Description
The present invention relates to turbomachinery, this turbomachinery comprises centrifugal pump or the mixed flow pump of carrying liquid, be used for the blower or the compressor of pressurized gas, and be particularly related to such turbomachinery, the impeller of this turbomachinery has the improved blade shape of hydrokinetics to suppress the warp-wise component of auxilliary stream.
Usually, in centrifugal or mixed-flow turbine machinery impeller channel, because the static pressure gradient in the runner, the auxilliary stream that the motion of low-yield fluid causes in the interlayer of wall surface top exerts an influence to the main flow in the runner.This phenomenon has caused flowing of nonuniform speed in the formation of stream strand shape eddy current or the runner, and this result not only causes a large amount of fluid energy losses in impeller but also in the diffuser in impeller downstream or guide vane.
Auxilliary stream is defined in to having flowing of velocity component on the direction perpendicular to main flow.The total energy loss that is caused by auxilliary stream is called auxilliary stream loss.The low-yield fluid that certain zone is gathered in the runner can cause large-scale flow separation, thereby the characteristic curve that is definitely tilted and and then hindered the stable operation of turbomachinery.
Two kinds of known methods that are used for suppressing the auxilliary stream of turbomachinery are arranged, and a kind of is to make impeller have specific runner geometrical shape, and another kind is to provide energy from the external world.An example as the preceding a kind of method that adopts specific flow channel shape, a kind of known method is arranged, the impeller blade of axial flow turbomachinery tilts along its circumferential direction in this method, or along suction or along the direction inclination (L.H.Smith and the H.Yeh that discharge side, " skimming over and the two sides effect in the axial flow eddy current machinery ", AS ME proceedings, the basic engineering magazine, volume 85, NO.3,1963, P401～416), a kind of method has the bending blade part for warp-wise rotor in this method in spanwise, this partly has the blade malleation surface of a protrusion and/or the blade negative pressure surface (GB2224083A) of a depression, or a kind of method, and the blade of turbomachinery cascade is towards its peripheral, oblique or bending (people such as W.Zhongqi in this method, " use dihedral vane with angle to reduce the experimental research of the reason of auxilliary stream loss in the cascade of rectangle turbomachinery ", AS ME paper 88-GT-4).These methods are known to have satisfied influence for the auxilliary stream in the cascade under situation about suitably using.
But the shape of blade camber line or blade profile are not also got clear fully to the influence of auxilliary stream, so the blade lean or the span are subjected to certain restriction to vane curvature to the utilization of assisting the influence of flowing, do not change blade camber line or blade profile significantly.In addition, Japan Patent NO.63-10281 has proposed a kind of structure, has a projection to reduce auxilliary stream loss in the angle of turbomachinery impeller boss surface and blade surface in this structure.Because its specific blade shape of this flow channel shape has non-axisymmetric impeller boss surface, so impeller is difficult to make.
In all situations of document, the method that obtains effect is not all studied fully before above-mentioned.
Therefore, under different design conditions,, suppress the universal method of auxilliary stream and also do not set up for the turbomachinery of different types.In this case, have that above-mentioned effect has reduced many time, or effect is more damnable, has produced reverse effect.Therefore up to the present, also do not adopt specific flow channel shape to reduce the standard design criterion of auxilliary stream.So the 3 dimensional coil geometry of impeller is to adopt try and error method to design the optimum configuration of the impeller of assisting stream to be inhibited.
An example as a kind of method in back, flow to suppress auxilliary from extraneous energize in this method, instability for fear of turbomachinery, people have proposed a kind of method, the auxilliary stream of turbomachinery cascade is blown into fluid by the inlet to cascade and controls (T.E.Biesinger and D.G.Gregory-Smith in this method, " winding-up by the upstream edge interlayer reduces auxilliary stream and the energy loss in the turbomachinery cascade " AS ME paper 93-GT-114), or a kind of method, be blown into jet by inlet in this method and control auxilliary stream (PCT/JP92/01280) in the impeller to impeller.But the method that these proposed has shortcoming, promptly needs to be blown into the energy and the corresponding fixture of fluid or jet.In addition, also be a shortcoming in order to suppress the regular energy consumption of auxilliary stream needs.
The present invention relates to preceding a kind of method, promptly adopt the method for specific flow channel shape.Can learn obviously that from auxilliary stream theory the auxilliary stream in the impeller is caused by the effect of the Corioli power that the impeller rotation produces, and caused by the influence of stream strand curvature.Auxilliary stream in the impeller roughly is divided into two classes, a kind of be along the cladding plate surface or the blade that produces of impeller boss surface to the auxilliary stream of blade, another kind is along blade malleation surface or the warp-wise component of the auxilliary stream that produces of negative pressure surface.
People know, blade to the auxilliary stream of blade can reduce by making to plunder behind the blade.For the auxilliary stream of another kind of form, promptly the warp-wise component of auxilliary stream then is difficult to weaken or eliminate.If we wish to weaken or eliminate the radial component of auxilliary stream, then need to optimize very in earnest the 3 dimensional coil geometry of runner.
Purpose of the present invention is exactly to suppress the warp-wise component of auxilliary stream in centrifugal or the mixed-flow turbine machinery.
As an example that adopts turbomachinery typical impeller of the present invention, the 3 dimensional coil geometry of double shrouded wheel is shown in Fig. 1 (A) and 1 (B), and the major part on cladding plate surface has been removed among this figure.Fig. 1 (A) is a perspective view, and part is a section, and Fig. 1 (B) is the warp-wise sectional drawing for the sectional drawing along A-A ' line.Fig. 1 (A) and 1 (B) middle period hub surface 2 outwards stretch along warp-wise from running shaft 1, so it has the curved surface that is similar to the corn surface.Have a large amount of blade 3 on the impeller boss surface 2, blade 1 outwards stretches and is arranged in week upwards with identical distance along warp-wise from running shaft.The top 3a of blade 3 is stamped cladding plate 4, shown in Fig. 1 (B).Runner is determined by 2 blades that face one another 3, impeller boss surface 2 and cladding plate surface 4, so fluid flows to impeller outlet 6b from impeller eye 6a.When impeller 6 with angular velocity omega during around the rotation of the axis of running shaft 1,, flow into the impeller outlet 6b of the direction of flow impeller 6 of runner from impeller eye 6a.In this case, the surface of facing sense of rotation is malleation surface 3b, and the reverse side of malleation surface 3b is negative pressure surface 3c.In unshrouded impeller, do not form the individual components on cladding plate surface 4, but a shell (not shown) of surrounding impeller 6 plays the effect on cladding plate surface 4.So, aspect the generation and inhibition of the warp-wise component of auxilliary stream, there is not basic hydrokinetics difference between unshrouded impeller and the double shrouded wheel, double shrouded wheel is only described below therefore.
Impeller 5 with a large amount of blades 3 is integrated critical pieces, and running shaft 1 is connected with transmission power source, thereby constitutes turbomachinery together.Fluid is introduced impeller eye 6a by suction line, is carried and is discharged from impeller outlet 3b by impeller 6, drains into the outside of turbomachinery then by discharge pipe.
Unsolved serious problems are auxilliary flowing through to the inhibition of component in the turbomachinery impeller.The mechanism of production of the warp-wise component of auxilliary stream is explained as follows, and the inhibition of this warp-wise component is a purpose of the present invention.
Shown in Fig. 1 (B), consider mobilely relatively, be defined as P
*=P-0.5 ρ U
2The contrast static pressure distribution be by centrifugal force W
2The effect of the effect of/R and Corioli power 2 ω W forms, this centrifugal force is that the stream strand curvature owing to main flow produces, this Corioli power is that the rotation owing to impeller produces, wherein W is the relative velocity that flows, R is the radius of stream burst curvature, W is the angular velocity of impeller, We be W in a circumferential direction with respect to the component of running shaft 1, P
*Be the contrast static pressure, P is a static pressure, and ρ is a fluid density, and U is the peripheral velocity of leaving on running shaft 1 certain radial location.Contrast static pressure P
*Distribution in, the impeller boss side pressure is higher and the cladding plate side pressure is lower, thus the pressure gradient balance point to the centrifugal force W of impeller boss side
2/ R and Corioli power 2 ω W.
Along in the boundary layer of blade surface, because being subjected to the influence of wall surface, relative velocity W reduces, so act on the centrifugal force W on the fluid in the boundary layer
2/ R and Corioli power 2 ω W diminish.Their contrast static pressure gradient in can not the balance main flow, and the low contrast of the low-yield direction of flow in boundary layer static pressure P as a result
*The zone, thereby cause the auxilliary warp-wise component that flows.That is, shown in the solid line on dotted line on the malleation surface 3b among Fig. 1 (A) and the negative pressure surface 3c, fluid on the 3b of malleation surface and 3c upper edge, negative pressure surface blade surface from the impeller boss effluent to the cladding plate side, form the warp-wise component of auxilliary stream.
All produce the warp-wise component of auxilliary stream on negative pressure surface 3c and the malleation surface 3b.Usually, because the interlayer on the limit on the 3c of negative pressure surface is than the border bed thickness on the surperficial 3b of malleation, so the auxilliary stream on the 3c of negative pressure surface wants big to the performance impact of turbomachinery.Purpose of the present invention suppresses the lip-deep auxilliary flow component of blade negative pressure exactly.
When the low-yield fluid in the boundary layer during to the cladding plate side, forms the fluid flow rate that fluid flows and flowed away with compensation from the impeller boss effluent near the neutral position from the impeller boss side to the cladding plate side.Therefore, shown in Fig. 2 (B), this figure be among Fig. 2 (A) along the sectional drawing of B-B ' line, when fluid when outlet is flowed, formed a pair of eddy current in the runner between two blades with different swirl direction.These eddy current are called as auxilliary stream eddy current.Low-yield fluid in the runner is assembled in certain position of impeller outlet direction owing to eddy current, this place's contrast static pressure P
*Minimum, and the fluid of steady flow in this low-yield fluid and the runner mixes mutually, causes producing big flow losses.
In addition, when inhomogeneous the flowing when draining into the downstream canal of blade that the insufficient mixing of low relative velocity (high loss) fluid and high relative velocity (high loss) fluid causes, the mixing of two kinds of fluids just produces big flow losses.
Leave this uneven of impeller and flow, make the velocity triangle of diffusor entry undesirable and cause flow separation on the diffuser vane or the reverse flow in the on-bladed diffuser, thereby reduce the overall performance of turbomachinery greatly.
Also have, the height loss fluid mass of gathering in a certain position of runner is easy to generate large-scale reverse flow, thereby the characteristic curve that is definitely tilted.So can produce pulsation, vibration, noise etc., and turbomachinery can not move stably.
So,, when the 3 dimensional coil geometry of design runner, should suppress auxilliary stream as far as possible for the performance of improving centrifugal or mixed-flow turbine machinery and the stable operation that realizes turbomachinery.The formation of auxilliary like this stream eddy current and the inhomogeneous mobile and large-scale flow separation that produces etc. thereof can be prevented from.
So one object of the present invention is exactly the shortcoming that overcomes turbomachinery loss increase and irregular operation, this shortcoming is to be caused to insufficient inhibition of component by auxilliary flowing through in the impeller, and following four kinds of designs that can reduce above loss and improve the turbomachinery operation stability are provided.
(1) according to a first aspect of the invention, centrifugal or mixed-flow turbine machinery has an impeller, be characterized in, contrast differential static pressure Δ Cp on the described impeller negative pressure surface between impeller boss and cladding plate or relative Mach number difference DELTA M, zero dimension warp-wise distance be 0 position (impeller eye) and zero dimension warp-wise distance for the position of l (impeller outlet) between, when described zero dimension presents the trend that obviously reduces during apart from increase.Also have, contrast differential static pressure Δ Cp (or Mach number difference Δ M) is approximate vanishing or from just to negative its symbol that changes during near impeller outlet between impeller eye and impeller outlet.
By the distribution of design contrast differential static pressure Δ Cp in the following manner, present the position that obviously reduces trend at contrast differential static pressure Δ Cp or relative Mach number difference Δ M, the warp-wise component of auxilliary stream obtains obvious suppression.Therefore, the auxilliary flow path on the whole impeller is suppressed effectively to component.In this case, if degree that contrast static pressure Δ Cp obviously reduces and the position that reduces are best, then assist the inhibition effect maximum of the warp-wise component of stream.
The difference that contrasts differential static pressure Δ Cp (or relative Mach number difference Δ M) on minimum contrast differential static pressure Δ Cp (or relative Mach number difference Δ M) and certain position is not less than 0.20, and (or relative Mach number differs from 0.15) time, the degree that obviously reduces is for best, and the zero dimension warp-wise distance of this position correspondence deducts zero dimension warp-wise distance 0.4 resulting value for the zero dimension warp-wise distance of the described minimum value of representative.When the position that trend takes place obviously to reduce was positioned at zero dimension warp-wise distance and is not less than m=0.4, this position was best.Here zero dimension warp-wise distance defines on the warp-wise surface plane of impeller shown in Fig. 1 (B).In the cladding plate side, the zero dimension warp-wise is defined as m=l apart from m
s/ l
R, s, this value is that warp-wise is apart from l
sWith warp-wise apart from l
R, sRatio, l
sBe the value of measuring from impeller eye 6a along cladding plate, and l
R, sBetween impeller eye 6a and impeller outlet 6b, measure along cladding plate.Similarly, on impeller boss, the zero dimension warp-wise is defined as m=l apart from m
H/ l
T, H, this value is l
HAnd l
T, HRatio, l
HBe the warp-wise distance of measuring from impeller eye 6a along impeller boss, and l
T, HThe warp-wise distance of between impeller eye 6a and impeller outlet 6b, measuring along impeller boss.So m=0 is corresponding to impeller eye 6a, and m=1.0 is corresponding to impeller outlet 6b.
When Δ Cp (or Δ M) certain the locational value that is not less than m=0.6 approach zero or its value when just becoming negative, the auxilliary warp-wise component that flows is suppressed.When this position be in the zero dimension warp-wise apart from the scope of m=0.65～0.9 in the time, auxilliary flow through best to the inhibition effect of component.
By the way, contrast differential static pressure Δ Cp is used for the incompressible fluid of liquid pump, and relative Mach number difference Δ M is used for the compressible fluid of compressor.They are being equivalent aspect the hydrokinetics to the influence that produces auxilliary stream.So contrast differential static pressure Δ Cp is only used in following description.
(2) according to a second aspect of the invention, centrifugal or mixed-flow turbine machinery has an impeller, and its characteristics are, along the warp-wise derivative distribution of r ve on the warp-wise range direction, i.e. (r Ve)/ m.
Here, r is the warp-wise coordinate of cylindrical coordinates system shown in Fig. 1 (B), the tangential mean value of the circumferential speed component Ve of vV.Designed impeller makes the maximum value of on its cladding plate (r Ve)/ m appear at the front portion of blade, and the maximum value of (r Ve)/ m appears at the rear portion of blade on the impeller boss.
In addition, it is that (r the Ve)/ m on the cladding plate of position (impeller eye side) is greater than the value on the impeller boss near 0 in zero dimension warp-wise distance that the design of impeller makes it, and the warp-wise derivative of described r Ve is (r Ve)/ m near the zero dimension distance is 1.0 position (impeller outlet side), value on its cladding plate is less than the value on the impeller boss, and the warp-wise derivative of the described r Ve on the impeller boss distributes, in zero dimension warp-wise distance is that the described position and the zero dimension warp-wise distance of 0 (impeller eye) is between the described position of 1.0 (impeller outlets), and distributing with the warp-wise derivative of r Ve on the cladding plate intersects.
Achieve above (r Ve)/ m by the design impeller and distribute, the blade load at impeller eye place is big and less in the impeller boss side in the cladding plate side, and the blade load at impeller outlet place is less and bigger in the impeller boss side in the cladding plate side.Therefore, the above is reflected in first aspect of the present invention, because obtain relatively large contrast differential static pressure Δ Cp at the impeller eye place and obtain less relatively contrast differential static pressure Δ Cp at the impeller outlet place.So the trend that contrast differential static pressure Δ Cp can obviously be reduced, thereby suppress the auxilliary warp-wise component that flows effectively.
In this case, if the position, described point of intersection of the r Ve warp-wise derivative between cladding plate and impeller boss is best, then auxilliary flowing through to the inhibition effect maximum of component.Suitable position is that the zero dimension warp-wise is not less than 0.5 apart from m, and the optimum position is positioned at the scope of zero dimension warp-wise apart from m=0.55～0.85. on the cladding plate (r Ve) if/ m has peaked position and is positioned at the scope of zero dimension warp-wise apart from m=0～0.3 in the impeller front portion, then this position is suitable, and the on the impeller boss (r Ve) if/ m has peaked position and is positioned at the zero dimension warp-wise apart from the scope of m=0.6～1.0 then this position is suitable at the impeller rear portion.
(3) according to a third aspect of the present invention, entire portion or a part of upper edge circumferential direction of blade between impeller eye and impeller outlet tilts, so the blade of impeller boss side will be prior to the blade of cladding plate side on the impeller sense of rotation, and blade angle γ does not keep constant and make it have the trend that reduces on the impeller outlet direction.Here, blade tilt γ is defined as the angle of surface of cladding plate on the flow area and blade centreline, and Figure 11 (c) showed the blade tilt γ on the impeller outlet cross section, and this figure is E-E ' view of Figure 10.In addition, on the paddle wheel plane view of looking from the impeller eye side, blade outlet angle
TE(Figure 11 (c)) is from the value α of impeller boss side
TE, HBe decreased to the value α of cladding plate side
TE, S, this angle T
EBe defined as the angle of outlet port blade camber line and tangential direction, and the blade angle α of impeller boss side on the paddle wheel plane figure
H(Figure 11 (c)) is designed to have maximum value or local maximum in impeller outlet one side, this angle α
HBe defined as the angle of blade camber line and tangential direction.
That is to say that the improvement of impeller boss upper blade shape reduces the sweepback angle of impeller posterior leaflet, and along the blade angle α of impeller outlet direction with respect to the cladding plate side
SIncreased the blade angle α of impeller boss side
H, thereby designed runner on the impeller sense of rotation its impeller boss side prior to the cladding plate side.
By designing blade by this way it is tilted at circumferencial direction, the contrast static pressure P of cladding plate side
*Increase, thereby its pressure coefficient C
PReduce.On the other hand, the contrast static pressure P of impeller boss side
*Reduce, thereby its pressure coefficient increases.More than be reflected in first aspect of the present invention, and between impeller eye and the impeller outlet particularly when the time near impeller outlet,, contrast differential static pressure Δ Cp presents the trend that reduces.
In this case, when the shape of blade when peripheral, oblique is suitable, the inhibition effect maximum of auxilliary stream.That is to say that on the paddle wheel plane view of looking from impeller eye, the position of turning back a little is not less than radius ratio r
*=(t-r
1H)/(r
2H-r
1H)=0.6 or be not less than the zero dimension warp-wise apart from m=0.7, this blade shape of place's impeller boss side of turning back has maximum blade angle α
HBlade sweepback degree along impeller outlet direction cladding plate side is greater than impeller boss side (Figure 11 (c)), and satisfies following relation { d (r θ)/dr}s＞{ d (r θ)/dr}
HHere, r and θ are respectively the warp-wise and the angular coordinatess of cylindrical coordinate.When the counter clockwise direction with impeller is benchmark metric, angular coordinates θ be defined as on the occasion of.Blade lean ratio S is defined as S=(θ
TE, S-θ
TE, H)/(θ
TE, M-θ LE, M), as a parameter of expression blade lean general status, and best blade lean ratio is not less than S=0.14.Here, θ
TE, SBe the angular coordinates of cladding plate lateral lobe wheel outlet, θ
TE, HBe the angular coordinates of impeller boss lateral lobe wheel outlet, θ
TE, MBe the angular coordinates of middle span position impeller outlet, i.e. the neutral position of cladding plate and impeller boss, θ
LE, MFor span position (Figure 11 (c)) in the middle of described goes up the angular coordinates of impeller eye.
When the auxilliary stream that will suppress stronger, and when only adopting the 3rd aspect of the present invention, suppress the auxilliary trend of flowing through and fully being reduced in order to make to the cladding plate of component and the contrast differential static pressure Δ Cp between the impeller boss, blade is increased to the degree that is difficult to make along the inclination angle of peripheral, oblique, in this case, the 3rd aspect of the present invention combines with second aspect and can suppress the warp-wise component of auxilliary stream effectively and do not cause difficulty in the manufacturing.
(4) according to a fourth aspect of the present invention, centrifugal or mixed-flow turbine machinery has an impeller, and its characteristics are, during the blade angle that described impeller is along the circumferential direction measured distributes, and the blade angles of impeller boss side
HBlade angles with the cladding plate side
SBetween blade angular difference β
H-β
SPresent the trend of obvious increase with the increase of zero dimension warp-wise distance, this zero dimension warp-wise distance increases to 1 (impeller outlet) from zero (impeller eye).
Here, blade angle is defined in from blade to the blade of looking perpendicular to crooked impeller boss surface and flows on burst surface, or is defined on the cladding plate surface, and measures from tangential direction.That is to say β
HBe the angle of impeller boss lateral lobe sheet camber line and radius r place tangential direction, and blade angles
SAngle (Figure 12 (B) and 12 (c)) for cladding plate lateral lobe sheet camber line and radius r place tangent direction.
By pressing with upper type design blade angle difference β
H-β
SDistribution, impeller boss side blade angles when near impeller outlet
HBecome big, and can become big along the blade load of impeller outlet direction impeller boss side.On the other hand, the blade angles of cladding plate side when near impeller outlet
SDiminish, and can diminish along the blade load of impeller outlet direction cladding plate side.Therefore, above situation is reflected in first aspect of the present invention, and can obtain less relatively contrast differential static pressure Δ Cp at impeller outlet.That is, between impeller eye and impeller outlet contrast differential static pressure Δ Cp obviously reduce the warp-wise component of auxilliary stream is effectively suppressed.
In this case, if blade angle difference β
H-β
SMaximum value or the position that occurs of local maximum and this maximum value or local maximum be best, then the inhibition effect of the warp-wise component of auxilliary stream is maximum.Maximum value or local maximum are not less than 20 degree for best, and difference maximum or local maximum blade angular difference and average blade angle difference preferably is not less than 10 degree, and this average blade angular difference is that warp-wise is apart from the mean value in m=0～0.2 scope.When peaked position occurring and being positioned at zero dimension warp-wise distance and being not less than the position of m=0.5 is suitably, and to be positioned at the zero dimension warp-wise be best apart from m=0.7～1.0 scopes in this position.
A kind of situation is arranged, blade angular difference β in this situation
H-β
SBe distributed in the part scope of nothing because of radial distance m=0～1.0 and present the trend that reduces, present the trend of obvious increase subsequently along with the increase of zero dimension distance.But this tangible increase that blade angle distributes is essentially identical to the inhibition effect of auxilliary stream.
In the accompanying drawing:
Fig. 1 and 2 is a view of showing background document;
Fig. 1 (A) and 1 (B) show auxilliary flowing through to the view of component with the 3 dimensional coil geometry of double shrouded wheel, and Fig. 1 (A) is a perspective view, and part is a section, and Fig. 1 (B) is along the warp-wise sectional drawing of A-A ' line among Fig. 1 (A);
Fig. 2 (A) and 2 (B) are the views of showing the auxilliary auxilliary stream eddy current that causes to component of flowing through of double shrouded wheel, and Fig. 2 (A) is a perspective view, and part is a section, and Fig. 2 (B) is along the sectional drawing of B-B ' line among Fig. 2 (A);
Fig. 3 to 14 shows the view of implementing the optimum state of the present invention;
Fig. 3 to 6 shows that the zero dimension warp-wise is apart from the plotted curve that concerns between m and the pressure coefficient Cp;
Fig. 7 (A), 7 (B) and 8 show that the zero dimension warp-wise is apart from the plotted curve that concerns between m and (r the Ve)/m, /(r Ve)/ m is the warp-wise derivative of r Ve (moment of momentum), and this moment of momentum is the product of tangential mean value of the circumferential speed component Ve of runner radius r and the absolute velocity V of radius r place;
Fig. 9 to 11 is views of showing blade circumferencial direction inclination situation;
Fig. 9 (A) be the perspective view, part of impeller for section, Fig. 9 (B) is along the sectional drawing of C-C ' line among Fig. 9 (A);
Figure 10 is that the length of impeller is to sectional drawing;
The last figure of Figure 11 (A), 11 (B), 11 (C) and figure below are respectively along the view of D-D ' line and E-E ' line among Figure 10, what Figure 11 (A) showed is the impeller that traditional design method designs, what Figure 11 (B) showed is the impeller that designs dihedral vane with traditional design method, and what Figure 11 (C) showed is the impeller that has with the dihedral vane of the present invention's design;
Figure 12 (A), 12 (B), 12 (C) have showed the blade angle that defines to the blade stream burst surface at blade, Figure 12 (A) is the perspective view of impeller, Figure 12 (B) is the view of F direction along the blade of impeller boss 2 to blade stream burst surface among Figure 12 (A), and Figure 12 (C) is the view on G direction stream burst surface along the blade that covers sheet 4 to blade among Figure 12 (A);
Figure 13 (A) and 13 (B) show the zero dimension warp-wise apart from the plotted curve that concerns between m and the blade angle, and Figure 13 (A) has showed the blade angle β on the impeller boss
HCurve, Figure 13 (B) are showed is blade angle β on the cladding plate
SCurve;
Figure 14 has showed impeller boss upper blade angle beta
HWith cladding plate upper blade angle beta
SDifference β
H-β
SCurve;
Figure 15 to 74 has showed the verification msg of implementing the optimum state of the present invention;
Figure 15 to 26 has showed the various plotted curves of low specific speed centrifugal pump impeller, Figure 15,18,21 and 24 have showed pressure coefficient Cp curve (solid line represents the curve on the impeller boss and dotted line is represented the curve on the cladding plate), Figure 16,19,22,25 have showed blade load (r Ve)/ m curve (solid line represents the curve on the impeller boss and dotted line is represented the curve on the cladding plate), Figure 17,20,23 and 26 have showed the auxilliary spirogram that flows to, what Figure 15 to 17 showed is the situation of traditional design method design, what Figure 18 to 20 showed is the situation of only using dihedral vane according to the present invention at circumferencial direction, Figure 21 to 23 shows is to consider dihedral vane and blade load (r Ve)/ m according to the present invention and situation about designing, and Figure 24 to 26 shows is only to use blade load (r Ve)/ m according to the present invention and situation about designing;
What Figure 27 to 38 showed is middle than speed, the verification msg of mixed-flow pump impeller, Figure 27,30,33 and 36 have showed pressure coefficient Cp curve (solid line represents the curve on the impeller boss and dotted line is represented the curve on the cladding plate), Figure 28,31,34 and 37 have showed blade load (r Ve)/ m curve (solid line represents the curve on the impeller boss and dotted line is represented the curve on the cladding plate), Figure 29,32,35,38 have showed auxilliary flow velocity degree vector diagram, what Figure 27 to 29 showed is the situation of traditional design method design, what Figure 30 to 32 showed is the situation of only using dihedral vane according to the present invention at circumferencial direction, what Figure 33 to 35 showed is the situation of considering dihedral vane and blade load according to the present invention simultaneously, and what Figure 36 to 38 showed is the situation of only considering blade load (r Ve)/ m according to the present invention.
Figure 39 to 50 is verification msgs of Centrufugal compressor impeller, Figure 39,42,45 and 48 what show is relative Mach number M curve (solid line represent the curve on the impeller boss and dotted line is represented the curve on the cladding plate), Figure 40,43,46 and 49 what show is blade load (r Ve)/ m curve (solid line represent the curve on the impeller boss and dotted line is represented the curve on the cladding plate), Figure 41,44,47 and 50 have showed the auxilliary spirogram that flows to, what Figure 39 to 41 showed is the situation of traditional design method design, what Figure 42 to 44 showed is the situation of only considering blade lean according to the present invention at circumferencial direction, Figure 45 to 47 shows is to consider blade lean and blade load (r Ve)/ m simultaneously according to the present invention and situation about designing, and Figure 48 to 50 shows is only to consider blade load (r Ve)/ m according to the present invention and situation about designing;
Figure 51 to 62 is verification msgs of mixed flow compressor impeller, Figure 51,54,57 and 60 has showed relative Mach number M curve (solid line represents the curve on the impeller boss and dotted line is represented the curve on the cladding plate), Figure 52,55,58 and 61 has showed blade load (r Ve)/ m curve (solid line represents the curve on the impeller boss and dotted line is represented the curve on the cladding plate), Figure 53,56,59 and 62 has showed the auxilliary spirogram that flows to, and what Figure 51 to 53 showed is situation about designing according to traditional design method.What Figure 54 to 56 showed is the situation of only considering blade lean according to the present invention at circumferencial direction, Figure 57 to 59 shows is to consider blade lean and blade load (r Ve)/ m simultaneously according to the present invention and situation about designing, and Figure 60 to 62 shows is only to consider blade load (r Ve)/ m according to the present invention and situation about designing;
Figure 63 to 74 has showed the relation curve of warp-wise distance and blade angle, this curve ratio the traditional design method design situation and only consider the situation of blade lean at circumferencial direction according to the present invention, or consider the situation of circumferencial direction blade lean and blade load (r Ve)/ m simultaneously according to the present invention, or only consider the situation of blade load (r Ve)/ m according to the present invention;
Figure 63 to 65 is situations of low specific speed centrifugal pump impeller, and Figure 63 has showed the blade angles on the impeller boss
HCurve, Fig. 64 have been showed the blade angles on the cladding plate
SCurve, Fig. 65 have been showed blade angle difference β
H-β
SCurve;
Figure 66 to 68 is situations of the fast mixed-flow pump impeller of middle ratio, and Figure 66 has showed the blade angles on the impeller boss
HCurve, Figure 67 have been showed the blade angles on the cladding plate
SCurve, Figure 68 have been showed blade angle difference β
H-β
SCurve;
Figure 69 to 71 is situations of Centrufugal compressor impeller, and Figure 69 has showed the blade angles on the impeller boss
HCurve, Figure 70 have been showed the blade angles on the cladding plate
SCurve, Figure 71 have been showed blade angle difference β
H-β
SCurve;
Figure 72 to 74 is situations of mixed flow compressor impeller, and Figure 72 has showed the blade angles on the impeller boss
HCurve, Figure 73 have been showed the blade angles on the cladding plate
SCurve, Figure 74 have been showed blade angle difference β
H-β
SCurve;
Figure 75 (A) and 75 (B) are the perspective views of showing mixed-flow pump impeller blade lean difference, Figure 75 (A) is a situation of only considering blade lean according to the present invention at circumferencial direction, and Figure 75 (B) is a situation of considering blade lean and blade load (r Ve)/ m according to the present invention simultaneously;
Figure 76 is a flow chart of showing three-dimensional reverse design method numerical calculation, and this method is used to obtain the verification msg of turbomachinery impeller of the present invention.
Embodiment as first aspect of the present invention is below described.
The main flow that flows relatively in the impeller channel can be ignored by the influence of viscosity, so following formula is applicable to the incompressible fluid in the liquid pump substantially.
P
Trel=P
*+ 0.5 ρ W
2=constant
P wherein
TrelIt is the relative stagnation pressure of impeller upstream.
In addition, as contrast static pressure P on the blade surface
*Nondimensional number, pressure coefficient Cp defines with following formula:
Cp＝(P
Trel-P
*)/(0.5ρU
2)＝(W/U)
2
Wherein U represents the peripheral velocity of impeller outlet.
Fig. 3 showed on the impeller boss and on the blade cladding plate zero dimension warp-wise apart from the relation between m and the pressure number Cp.Can be clear that from above-mentioned equation Cp is bigger at cladding plate upward pressure coefficient, this place's contrast static pressure P
*Less, and less at impeller boss upward pressure coefficient Cp, contrast static pressure P on this impeller boss
*Bigger.As mentioned above, because the warp-wise component of auxilliary stream is from having bigger contrast static pressure P on the blade negative pressure surface
*Blade hub one side point to cladding plate one side with low contrast static pressure, so the warp-wise component of auxilliary stream can suppress by reducing pressure difference Δ Cp.Incidentally, under the situation of incompressible fluid, pressure coefficient Cp equals (W/U)
2, wherein W is a relative velocity.For the compressible fluid in the compressor, the physical quantity relevant with the situation of auxilliary stream is relative Mach number.The distribution of pressure coefficient Cp is only described for simplicity.The distribution of pressure coefficient Cp equals the influence of relative Mach number in the compressible fluid in the incompressible fluid to the influence of the warp-wise component of auxilliary stream.
Because the thickness of blade surface boundary layer is thickening gradually from impeller eye to impeller outlet, this boundary layer forms along the flow path wall in the impeller.So the present invention under the situation of the distribution of considering impeller latter half part pressure coefficient Cp, has proposed to be used to suppress auxilliary flowing through to the structure of component on the blade negative pressure surface.Be that the shaped design of blade becomes to make it to have as shown in Figure 4 pressure distribution, so that the pressure difference of impeller boss side and cladding plate side presents in the impeller outlet direction and significantly reduces trend on the negative pressure surface.Pressure distribution on the blade can obtain by the following method, and in this pressure distribution, pressure difference Δ Cp obviously reduces along the impeller outlet direction:
(a) as shown in Figure 5, increase the blade load of impeller boss one side, promptly in impeller boss one side, the malleation surface of blade and the pressure difference between the negative pressure surface obviously reduce along the impeller outlet direction.
(b) as shown in Figure 6, along the impeller outlet direction, obviously reduce the blade load in cladding plate one side.
(c) combine with (a) with (b).
Under any circumstance, must make in the pressure distribution on the blade, the lip-deep pressure difference Δ of blade negative pressure Cp obviously reduces along the impeller outlet direction, as shown in Figure 4.
According to a large amount of verification msgs, under following situation, the trend that above-mentioned pressure difference obviously reduces is for best, this situation promptly: the difference of the value of reduced pressure difference Δ Cp (or relative Mach number difference Δ M) is not less than 0.2 (is 0.15 for the relative Mach number difference) on the minimum value of contrast differential static pressure Δ Cp (or relative Mach number difference Δ M) and certain position.This difference deducts the value of zero dimension warp-wise distance 0.4 corresponding to the zero dimension warp-wise distance of minimum.Verification msg shows that also the optimum position that appearance obviously reduces trend is within the scope of zero dimension warp-wise apart from m=0.4～1.0.
In low specific-speed centrifugal impeller or mixed flow impeller, the width of impeller outlet is narrower, and the pressure difference on impeller boss surface and cladding plate surface is less.So pressure difference Δ Cp is less usually at the impeller outlet place, as shown in Figure 4, promptly in the position of zero dimension warp-wise apart from m=1.0.On the other hand, at the impeller eye place, the pressure coefficient on the cladding plate is greater than the pressure coefficient on the impeller boss.Correspondingly, the pressure difference Δ P on the blade vacuum table face also has the reduce trend similar to mode shown in Figure 4 along the impeller outlet direction in the centrifugal impeller.But, in order to suppress the auxilliary stream in this impeller, must make almost vanishing of pressure difference Δ Cp, or pressure difference Δ Cp becomes negative value, promptly the trend that reduces of intensified pressure difference Δ Cp so that the pressure coefficient Cp of impeller boss side greater than the pressure coefficient of cladding plate one side.According to a large amount of verification msgs, when the zero dimension warp-wise of certain position distance is not less than m=0.6, and on this position Δ Cp near zero or its symbol when just becoming negative, this position is more suitable, when this position was positioned at zero dimension radial distance m=0.65～0.9 scope, this position was best.In traditional design, because of there not being this consideration, so can not effectively suppress the warp-wise component of auxilliary stream.
Embodiment as second aspect of the present invention will be described below again.
In order to realize above-mentioned contrast static pressure P
*Distribute, the present invention proposes a kind of structure, the blade shape in this structure is decided at the derivative of zero dimension warp-wise apart from the m direction by the circumferential average angle momentum r Ve of fluid, and this moment of momentum is provided by the impeller work.
Usually, the blade load of impeller in the turbomachinery, i.e. the pressure difference P on malleation surface and negative pressure surface
*(+) ρ-P
*(-) ρ= π (W
B1 r Ve)/B, wherein W
B1Be the relative velocity of blade surface position, B is the number of blade, is the differential divisor that provides the elementary derivative of space coordinates, the tangential mean value of Ve, as Figure 12 (C) impeller boss upper blade to shown in the blade plane.
Learn that from above-mentioned equation the pressure difference on malleation surface and negative pressure surface and the warp-wise derivative of r Ve (moment of momentum) are closely related, this moment of momentum is the product of tangential mean value of the circumferential speed component Ve of runner radius and this radius absolute velocity.
So as shown in Figure 5 and Figure 6, in order to increase or reduce pressure coefficient Cp, the warp-wise derivative of r Ve should be decided to be suitable value.Among the present invention, the warp-wise derivative of r Ve provides as follows:
The distribution of on the impeller boss (r Ve)/ m makes (r Ve)/ m have maximum value near the impeller eye place a little numerical value being arranged near the impeller outlet place, shown in Fig. 7 (A), like this, the lip-deep blade load of impeller boss P
*(+)-P
*(-) increases at the rear portion of impeller and reduces in the front portion of blade.In addition, the lip-deep of cladding plate (r Ve)/ m distributes and makes to have maximum value near the of impeller eye place (r Ve)/ m, and has a little numerical value near the impeller outlet place, shown in Fig. 7 (B), like this, the lip-deep blade load of cladding plate P
*(+)-P
*(-) increases in the front portion of impeller and reduces at the rear portion of blade.In Fig. 8, compare as can be seen by impeller boss surface and the lip-deep of cladding plate (r Ve)/ m distribution, at close impeller eye place, the warp-wise derivative of r Ve is than the warp-wise derivative height of r Ve on the impeller boss on the cladding plate, and at the impeller outlet place, the warp-wise derivative of r Ve is than the warp-wise derivative height of r Ve on the cladding plate on the impeller boss.In this case, the distribution curve of on the impeller boss (r Ve)/ m and the distribution curve on the cladding plate intersect, intersection point the zero dimension warp-wise apart from m=0～1.0 scopes in.By adopting such (r Ve)/ m to distribute, contrast differential static pressure Δ Cp is strengthened towards the trend that reduces at impeller outlet place greatly in warp direction, bigger and smaller because such distribution makes near the value of the Δ Cp of impeller eye place near the value of the Δ Cp of impeller outlet place.Thereby the warp-wise component of the auxilliary stream in blade negative pressure surface can be suppressed effectively.Many verification msgs prove that the intersection location of two curves preferably zero dimension warp-wise distance is not less than the position of m=0.5 and is best in the scope of m=0.55～0.85.When certain position the zero dimension warp-wise apart from m=0～0.3 scope in, and when the on this position cladding plate (r Ve)/ m has a maximum value in the front portion of impeller, this position is suitable, when certain position the zero dimension warp-wise apart from m=0.6～1.0 scopes in, and when the on this position impeller boss (r Ve)/ m had a maximum value at the rear portion of impeller, this position was suitable.
If determined the suitable distribution of load distribution (r Ve)/ m, can realize that so the 3 dimensional coil geometry of the impeller of this distribution can adopt the flow analysis method to determine by examination difference modification blade shape.But this 3 dimensional coil geometry also can be more effectively by adopting three-dimensional reverse design method to determine, this method is a kind of method that is widely known by the people, and this method is used for numerical calculation three dimendional blade shape and distributes with the blade load of realizing setting.People have proposed the different theory about three-dimensional reverse design method; For example, Zangeneh, " being used for radially compressible three dimendional blade design method " M.1991 year with the mixed-flow turbine machinery blade, the international journal of fluid numerical method, volume 13, page or leaf 599～624, Borges, " the three-dimensional reverse design method of turbomachinery: part I-theory " of J.E.1990, AS ME proceedings, turbomachinery magazine, volume 112, page or leaf 346～354, Yang, Y.L., Tan, C.S. and Hawthorne, " aerodynamic design of the turbine blade in the Three-dimensional Flow: be applied to the radial inward flow turbomachinery " that W.R.1992 delivers, AS ME, paper 92-GT-74, Dang, " the complete three-dimensional inverse approach of the turbomachinery blade during supersonic speed is mobile " that T.Q.1993 delivers, AS ME proceedings, turbomachinery magazine, volume 115, page or leaf 354～361.Propose and to be used for the present invention's method brief explanation as follows by M.Zangeneh (1991).Blade represents that with backset bed backset bed distributes along the blade camber line, and the intensity of eddy current determines that by the distribution of the r Ve that sets r Ve is the tangential mean value of peripheral velocity Ve and the product of radius r.Ve can determine apart from the m integration along zero dimension by (r Ve)/ m at an easy rate by blade load distribution (r Ve)/ m and warp-wise geometric condition.Realize that the blade shape that blade load that the present invention sets distributes can determine by utilizing following condition, this condition promptly: the speed that backset bed causes in the runner must be consistent with blade surface.Numerical calculation flow process in the three-dimensional inverse approach and is briefly described below shown in Figure 76.
(load distribution (r the Ve)/ m of step 1) by setting apart from the m direction integral along the zero dimension warp-wise calculates the distribution of r Ve on the warp-wise plane.
The warp-wise component of (step 2) estimated speed Vm, this speed Vm are decided by the sectional area of the warp-wise geometrical shape of designing quality flow that impeller is set and setting.
(step 3) is by removing the tangential component that r Ve comes estimated speed Ve with radius r on each position in impeller.At this sections, the velocity field that obtains is the initial approximation of actual velocity field, because the influence of blade shape is not considered exactly.
(step 4) adopts velocity field and non-sticky sliding condition to calculate blade shape on each position, and this condition means mobile relatively must the calibration with blade surface.Blade shape is calculated by finding the solution single order hyperbolic partial differential equation, so distribute as the initial value of integration by setting along the θ of blade exit direction, can provide the blade lean degree at impeller outlet place.
(step 5) is calculated the velocity distribution in whole blade zone according to the blade shape that r Ve distributes and this sections obtains from step 4 that step 1 calculates.
(blade shape that step 6) utilizes velocity distribution that step 5 obtains and step 4 to calculate is by finding the solution the control partial differential equation, the computational speed field.
(the step 7) band the velocity field of the modification that step 6 obtains and is returned step 4, and repeating step 4 is till the variation of step 7 blade shape in the twice iteration error given less than certain.
Embodiment as third aspect of the present invention will be described below.
According to the present invention, in order to optimize the contrast static pressure P in the impeller
*Distribution, blade tilts at circumferencial direction, promptly the blade of impeller boss side is more forward than blade its position on the sense of rotation of impeller of cladding plate side.Similar to Fig. 1 (A), Fig. 9 (A) has showed that the perspective view of double shrouded wheel 3 dimensional coil geometry partly is section.Fig. 9 (B) has showed among Fig. 9 (A) sectional drawing along C-C ' line.Here identical identical parts of symbology among the symbol among Fig. 9 (A) and Fig. 9 (B) and Fig. 1 (A).
Shown in Fig. 9 (B), because the pressure difference between blade malleation surface 3b and negative pressure surface 3c, the power of fluid with near perpendicular to the directive effect of blade surface in blade, and its reaction force is along opposite directive effect in fluid, and the direction of this reaction force is pointed to blade negative pressure surface 3c and approximately perpendicular to blade 3.Shown in dotted line among Fig. 9 (B), when blade when circumferentially not having the tilt angle, reaction force is along circumferentially acting on fluid, and not perpendicular to the component of impeller boss or cladding plate.
On the other hand, if the inclination mode of blade makes the blade of on impeller sense of rotation impeller boss side 3CH prior to the blade of cladding plate side, the power that acts on fluid so has the component perpendicular to the cladding plate surface, and this active force points to suction side from the malleation side of runner, shown in Fig. 9 (B).Therefore, produce a contrast static-pressure field in the runner, and compare, this contrast static pressure P with the situation that does not have blade pitch angle with the above-mentioned BLADE FORCE that acts on fluid of balance
*Bigger value is arranged and have less value on the cladding plate surface on the impeller boss surface.So reduce as impeller boss surface in the pressure coefficient Cp distribution among Fig. 3 and the pressure difference between the cladding plate surface, be fit to suppress the auxilliary pressure field that flows thereby can form, as shown in Figure 4.
By the traditional research to axial flow turbine machinery, blade has had qualitatively the influence of assisting the warp-wise component that flows along circumferential inclination to be understood.But, because blade geometric shape is not also understood fully and quantitatively to the influence of auxilliary stream, so the utilization of blade lean effect is subjected to certain restriction in traditional blade lean mode, traditional blade lean mode is cladding plate one side at the circumferential offset blade, and keep blade pitch angle r identical with the blade exit place, or pile up line along crooked spademan direction and pile up traditional blade profile curve at the blade inlet place.
Figure 10 has showed the concise and to the point warp-wise section of double shrouded wheel, and planimetric map of looking along D-D ' direction among Figure 10 from impeller eye 6a and the planimetric map of looking along E-E ' direction Figure 10 from impeller outlet are illustrated in respectively the last figure and figure below of Figure 11 (A), 11 (B) and 11 (C) together.As described in Japan Patent NO.55-134798, when traditional blade lean mode was applied to shown in Figure 11 (A) in the conventional impellers, the planimetric map of impeller was shown in Figure 11 (B).In this traditional blade lean mode, the blade of cladding plate side circumferentially simply is being offset, and does not change the blade geometric shape of cladding plate side.In this case, the position of a q that turns back of impeller boss 2 lateral lobe sheet camber lines is a little identical with turning back of the conventional impellers shown in Figure 11 (A), changes its symbol in this position vane curvature of turning back.The last figure of Figure 11 (B) also shows in addition, and blade pitch angle r is keeping constant substantially near the impeller outlet place, and this inclination angle is defined as the center line of blade 3 and the angle on cladding plate surface 4.
On the other hand, in the third mode of the present invention, by radially outwards being offset the position of a q that turns back, the shape of impeller boss lateral lobe sheet has been carried out modification more initiatively, thereby has reduced the sweepback angle at blade rear portion.That is the blade angle α of impeller boss side,
HIncrease along the impeller outlet direction, and the design of the blade geometric shape of runner makes blade, and its impeller boss side should be prior to the cladding plate side on the impeller sense of rotation.Shown in Figure 11 (C), in this case, compare with the traditional blades inclination mode shown in Figure 11 (B), a q that turns back of impeller boss lateral lobe sheet camber line has shifted to the impeller outlet direction.The sweepback angle that the design of impeller also makes the cladding plate side promptly d (r θ)/dr} increases along the impeller outlet direction, thus { d (r θ)/dr}
S＞{ d (r θ)/dr}
HWherein subscript " S " refers to the value of cladding plate side and " H " refers to the value of impeller boss side.
Also have, the suitable design of blade tilt r should make it show the trend of minimizing along the impeller outlet direction, shown in Figure 11 (C).Here need not keep blade tilt r is a steady state value.In this case, because the value of ingress blade tilt r is relatively large, the influence of blade tilt is less, so pressure difference Δ Cp is relatively large in the ingress, and along the impeller outlet direction because the value of blade tilt r is less relatively, the influence of blade tilt is bigger, so Δ Cp has the trend that obviously reduces.Except these, shown in Figure 11 (C), the design of impeller should make angle of impeller outlet alpha
TEAngle [alpha] from impeller boss 2 sides
TE, HAngle [alpha] to cladding plate 4
TE, SThe trend that reduces is arranged, and the blade angle α of impeller boss side
HHave a maximum value or local maximum in the outlet port of impeller.
Except the traditional blades inclination mode that produces with moving blade cladding plate side by the phase negative side along the impeller rotation, by the special blade shape of considering the impeller boss side, the influence of blade lean becomes more effective again.Many verification msgs confirm, a little the suitable radial location of turning back is positioned at radius ratio and is not less than r
*=(r-r
1H)/(r
2H-r
1HThe position of)=0.6 or be positioned at the zero dimension warp-wise apart from the position after the m=0.7, on turning back a little, blade angle α
HThe blade curve of maximum and impeller boss side changes the symbol of its curvature.Wherein, r
1HImpeller eye radius r for the impeller boss side
2HBe the impeller outlet radius of impeller boss side, as shown in figure 10.Many verification msgs also confirm, when blade lean than S greater than S=(θ
TE, S-θ
TE, H)/(θ
TE, M-θ
LE, M)=0.14 o'clock, the best results of blade lean.Wherein, θ is the circumferential coordinate of the cylindrical coordinates system shown in Figure 11 (C), the value that on behalf of blade exit (blade hangover limit), subscript " TE " locate, the value that on behalf of blade inlet (blade leading edge), " LE " locate, " S " representative is positioned at the value of cladding plate 4 sides, " H " representative is in the value of impeller boss 2 sides, and " M " represents the value of middle span position.
But, in order to suppress the warp-wise component of auxilliary stream in centrifugal or the mixed-flow turbine machinery fully, auxilliary stream in this centrifugal or mixed-flow turbine machinery is mechanical more serious than axial flow turbine, blade needs undue blade lean along circumferential direction, because difficulty on making and the problem on structure and the intensity, the application of this inclination mode is unpractiaca.On the other hand, according to the present invention proposes a kind of method, this method adopts manufacturing difficulty also not have the blade lean mode of structure and strength problem to suppress the warp-wise component of auxilliary stream by adopting second aspect (optimizing blade load distribution (r Ve)/ m) simultaneously.
The embodiment who below description is met the 4th aspect of the present invention.
Consider (r Ve)/ m distribution optimization, or along the blade lean of circumferential direction, or the two is considered all according to the present invention, the 3D shape of blade can be calculated by three-dimensional reverse design method according to the flow process among Figure 76.And people confirm, can effectively suppress auxilliary flowing through and have the blade angle distribution of feature to the impeller of component, and the 4th aspect promptly of the present invention is to become to make it to have following blade angle impeller design to distribute.
(a) the impeller boss side obviously increases along the impeller outlet direction with respect to the blade angle distribution of zero dimension distance, shown in Figure 13 (A).
(b) the cladding plate side obviously reduces along the impeller outlet direction with respect to the blade angle distribution of zero dimension distance, shown in Figure 13 (B).
(c) the blade angle difference of blade angle distribution middle period hub side and cladding plate side obviously increases along the impeller outlet direction with respect to the zero dimension distance, as shown in figure 14.
In this case, when the peaked position of blade angle difference is not less than the zero dimension warp-wise apart from m=0.5 or more effectively be positioned at the zero dimension warp-wise apart from m=0.7～1.0 scopes, and maximum blade angular difference value is not less than 20 when spending, many verification msgs prove that all the inhibition effect of the warp-wise component of auxilliary stream is tangible.Checking numerical value confirms that also in the scope of zero dimension warp-wise apart from m=0.0～0.2, the maximum value of blade angle difference exceeds more than average blade angle difference 10 degree.Figure 12 (A) and Figure 12 (B) are seen in the definition of above-mentioned blade angle.Figure 12 (A) has showed the perspective view of double shrouded wheel, and part is a section, and this figure is corresponding to Fig. 1 (A).Figure 12 (B) be Figure 12 (A) along F to view, this figure has showed from the curve of blade at its curved surface 2 of 2 upper edges, impeller boss surface of looking perpendicular to the direction of impeller boss 2.The blade angles of impeller boss 2 sides
HBe defined as the camber line and the tangential angle that leaves the radial distance r place of running shaft 1 of blade 3.Figure 12 (C) be among Figure 12 (A) along G to view, this figure has showed from the appearance curve of blade on cladding plate surface 4 of looking perpendicular to the direction of cladding plate 4.The blade angles of cladding plate 4 sides
SBe defined as the camber line and the tangential angle that leaves the radial distance r place of running shaft 1 of blade 3.Blade angle difference β
H-β
SBe defined as the blade angles of impeller boss 2 sides
HBlade angles with cladding plate 4 sides
SPoor.Thinking suppresses auxilliary flowing through to the basic structure of component as shown in Figure 4, is appreciated that the physical significance that the blade angle characteristic distributes.Because blade angle (from circumferential direction definition) becomes big, so the fluid of discharging from impeller has bigger swirl speed, thereby impeller convection cell work is bigger.At this moment, the pressure difference on negative pressure surface and malleation surface also becomes greatly, thereby the blade load increases this pressure difference generation impeller merit.That is, shown in Figure 13 (A), owing to increase along the blade angle on impeller outlet direction impeller boss surface, so corresponding blade load (solid line and dotted line region surrounded among Fig. 5) increases along the impeller outlet direction on the impeller boss surface, as shown in Figure 5.On the other hand, shown in Figure 13 (B), because the blade angle on cladding plate surface reduces along the impeller outlet direction.So one will understand that, make it have this blade angle by the design impeller and distribute, can realize that effectively suppressing to assist the blade pressure of flowing through to component distributes.From the explanation of Fig. 4, can obviously find out, be decided by the poor of the contrast static pressure distribution between impeller boss and cladding plate on the blade negative pressure surface, so in fact the blade angle difference between impeller boss and cladding plate is important because auxilliary stream tangential component suppresses effect.So the characteristics of the blade shape of impeller are reflected in the blade angle difference distribution shown in Figure 14, these characteristics can suppress the warp-wise component of auxilliary stream effectively.
A kind of situation is arranged, blade angular difference value β in this situation
H-β
SThe zero dimension that is distributed in present the trend that reduces apart from a part of between m=0～1.0, then present the trend of obvious increase when increasing when zero dimension.But this tangible increase of blade angle difference is basic identical to the inhibition effect of auxilliary stream.
The above-mentioned characteristic reaction that blade angle distributes aspect the 3rd of the present invention in, i.e. the feature of blade lean in a circumferential direction.Turn back a little position has provided the feature of the 3rd aspect of the present invention, and be defined as changing minimum position in radial direction (r θ), i.e. the position of d (r θ)/dr minimum is in a position of turning back, shown in Figure 11 (C), impeller boss lateral lobe sheet curve changes the symbol of its curvature.On the other hand, the blade angles of Figure 12 (B) definition
HBy tan β
H={ dm/d (r θ) }
HProvide.Here, tan α
H={ dr/d (r θ) }
H={ dm/d (r θ) }
H=tan β
H(dr/dm)
H, in a single day and determined the warp-wise geometrical shape, (dr/dm)
HValue just calculate.Thereby, { d (r θ)/dr}
HMinimum position and β
HMaximum position is closely related.Because this point people are easy to learn that this most effective position of turning back a little is that the zero dimension radius ratio is not less than r on the impeller boss
*=0.6 or zero dimension distance be not less than the position of m=0.7, it is the feature of third aspect of the present invention that this Must Significant Bit is put.
The verification msg of determining the foregoing description below will be described.
Figure 15 to 26 and Figure 27 to 38 have showed the verification msg of pump impeller, and what Figure 15 to 26 showed is the situation of low specific-speed centrifugal impeller, and Figure 27 to 38 displaying is the situation of the fast mixed flow impeller of middle ratio.Figure 39 to 50 and Figure 51 to 62 have showed the verification msg of compressor impeller, and Figure 39 to 50 shows is the situation of centrifugal impeller and Figure 51 to 62 shows is the situation of mixed flow impeller.In order to learn auxilliary flowing through to the inhibition effect of component, used the result of numerical analysis, this numerical analysis is the (Dawes that finishes by the three-dimensional viscosity computational methods of determining very much, W.N.1988, " three-dimensional Navier-Stores solution is used for the exploitation of various turbomachineries " AS ME opinion code NO.88-GT-70).Figure 17,20,23,26,29,32,35,38,41,44,47,50,53,56,59,62 showed the numerical analysis prediction in the flow-rate vectors of blade negative pressure near surface and along the mobility status of the auxilliary stream in the negative pressure surface boundary layer.
The present invention now will be described according to the verification msg that is used for centrifugal pump impeller among Figure 15 to 26 more.In the design of conventional impellers, do not consider the inhibition of auxilliary stream in the impeller, and the pressure coefficient difference Δ Cp between impeller boss and cladding plate increases along this impeller outlet direction on the blade negative pressure surface, during the warp-wise of this pressure coefficient Cp distributes, the Δ Cp decrease that suppresses auxilliary stream is insufficient, as shown in figure 15.As shown in figure 16 (rV θ)/ m be distributed in the cladding plate side and the impeller boss side is all more smooth, and be different from second described distribution in aspect of the present invention, this distributes and is fit to suppress auxilliary stream.Therefore can confirm in the load of traditional design distributes, not consider to suppress auxilliary stream.So on the blade negative pressure surface from impeller boss to cladding plate, numerical analysis dopes strong auxilliary stream, shows the unsuitable type of flow as shown in figure 17.
On the other hand, under the verification msg situation of Figure 18 to 20, this situation has adopted the 3rd aspect of the present invention, because the effect that the circumferencial direction upper blade tilts has realized first aspect of the present invention.Among Figure 18 on the negative pressure surface pressure coefficient difference Δ Cp between impeller boss and cladding plate present along the impeller outlet direction and significantly reduce trend, and Δ Cp is approximately 0.7 position change symbol in zero dimension warp-wise distance, thereby has the trend of the auxilliary stream of enough inhibition.In this case, though the maximum load on the cladding plate appears at the front portion of blade, the maximum load on the impeller boss does not fully satisfy aspect the rear portion of blade and second of the present invention.But by adopting blade lean than S=0.142, the 3rd aspect of the present invention is fully exploited, thereby obtains suitable pressure distribution as shown in figure 18.Therefore, the auxilliary stream from impeller boss to cladding plate on the negative pressure surface obtains complete inhibition, and obtains the suitable type of flow shown in the numerical analysis result of Figure 20.
Figure 21 to 23 has showed the 3rd aspect of the present invention and second situation that the aspect combines.Synergy by second aspect of the 3rd aspect of blade peripheral, oblique and blade load, pressure coefficient difference Δ Cp on the negative pressure surface between impeller boss and cladding plate obtains significantly to reduce trend along the impeller outlet direction, and Δ Cp apart from the position change symbol that is approximately 0.75, assists the trend that flows thereby have enough inhibition at the zero dimension warp-wise.Therefore, the auxilliary stream from impeller boss to cladding plate is suppressed and obtains the suitable type of flow shown in numerical analysis result Figure 23 on the negative pressure surface.In this case, the blade lean ratio is S=0.078, and this value is approximately Figure 18 to 20 and only adopts the 3rd aspect to design half of resulting value.Just because of this, just successfully obtained three-dimensional runner geometrical shape, this runner geometrical shape is more suitable in manufacturing.
Figure 24 to 26 has showed the result who only adopts second aspect of the present invention.Because the suitable distribution of blade load (rVe)/ m of Figure 25, pressure coefficient difference Δ Cp on the negative pressure surface between impeller boss and cladding plate, compare with the situation of traditional design, present the trend that obviously reduces, thereby have the visible trend that suppresses auxilliary stream along the impeller outlet direction.Just because of this, the auxilliary stream from impeller boss to cladding plate on the negative pressure surface is compared with the traditional design situation of Figure 17 and to be subjected to suppressing fully shown in the result of Figure 26 numerical analysis.But, from the comparison of Figure 18 and 24, can be clear that, among Figure 24 on the negative pressure surface pressure coefficient between impeller boss and cladding plate reduce trend not as among Figure 18 obviously.Just because of this, can be clear that from the comparison of Figure 20 and 26 that the inhibition of auxilliary stream adopts the design of third aspect of the present invention effective not as the front.
Figure 27 to 38 has showed the verification msg of mixed-flow pump impeller, and auxilliary stream suppresses the situation (Figure 15 to 26) that effect is similar to above-mentioned centrifugal pump impeller, and confirmable is that the present invention also is applicable to mixed-flow pump impeller.
Below will describe the verification msg of the Centrufugal compressor impeller of Figure 39 to 50 in detail.As previously described, in compressible fluid, physical descriptor is that relative Mach number distributes, and this variable is closely related and be used for first aspect of the present invention with the behavior of auxilliary stream.In the impeller of traditional design, do not have to consider the inhibition of auxilliary stream, and distribute along the warp-wise of impeller outlet direction relative Mach number M, reduce trend fully not showing between impeller boss and the cladding plate on the negative pressure surface, as shown in figure 39.In addition, the distribution that the blade load among Figure 40 all shows relatively flat in impeller boss side and cladding plate side, and different with the distribution that is fit to the auxilliary stream of inhibition.Thereby can confirm, do not consider in the traditional design that the load that suppresses auxilliary stream distributes.So the result of numerical analysis 1 shown in Figure 41 dopes more serious auxilliary stream, this auxilliary stream is positioned at from impeller boss to the blade negative pressure surface between cladding plate along the impeller outlet direction.
On the other hand, under the verification msg situation of Figure 42 to 44,, in these verification msgs, adopted aspect the 3rd of the present invention because the gap tilt effect of circumferential blade has been realized first aspect of the present invention.Relative Mach number difference Δ M on the negative pressure surface between impeller boss and cladding plate presents the trend that obviously reduces along the impeller outlet direction, as shown in figure 42, and Δ M is approximately its symbol of position change of 0.8 in zero dimension warp-wise distance, thereby has the trend of the auxilliary stream of sufficient inhibition.In this case, the maximum load on the cladding plate appears at the rear portion of blade, and second aspect of the present invention fully do not satisfy.But made full use of the 3rd aspect of the present invention, and the suitable relative Mach number that therefore obtains as shown in figure 42 distributes.Just because of this, the auxilliary stream from impeller boss to cladding plate on the negative pressure surface is subjected to suppressing fully, and obtains the suitable type of flow shown in Figure 44 numerical analysis result.
Figure 45 to 47 has showed that the 3rd and second aspect of the present invention combines and the result that obtains.Because the synergy of the 3rd aspect of blade peripheral, oblique and second aspect of blade load, relative Mach number difference on the negative pressure surface between impeller boss and cladding plate presents a trend that obviously reduces along the impeller outlet direction, as shown in figure 45, show among the figure that Δ M is approximately its symbol of position change of 0.75 in zero dimension warp-wise distance, thereby have the trend of the auxilliary stream of enough inhibition.Just because of this, the auxilliary stream from impeller boss to cladding plate is suppressed and obtains the suitable type of flow shown in the numerical analysis result of Figure 47 on the negative pressure surface.In this case, the blade lean rate is similar to the situation of Figure 42 to 44, and third aspect of the present invention has only been adopted in the design of this situation.But, from the contrast of Figure 42 and 45, obviously find out, adopt second aspect of the present invention, the trend that relative Mach number is obviously reduced by combination.
Figure 48 to 50 has showed the result who only adopts second aspect of the present invention.Because the suitable distribution of blade load (rV θ)/ m among Figure 49, relative Mach number difference Δ M on the negative pressure surface between impeller boss and cladding plate presents the trend that reduces along the impeller outlet direction, and Δ M is very approaching zero apart from the position that is approximately 0.9 in zero dimension, thereby has provided the auxilliary suitable distribution of flowing of inhibition.Just because of this, the auxilliary stream from impeller boss to cladding plate on the negative pressure surface is suppressed fully, shown in the numerical analysis result of Figure 50, and has obtained the suitable type of flow.
Figure 51 to 62 showed the verification msg of mixed flow compressor impeller and suppressed the effect of auxilliary stream, and this effect is similar to the situation of above-mentioned Centrufugal compressor impeller, and applicability of the present invention is identified and also can be used for the mixed flow compressor impeller.
Figure 63 to 74 has showed that feature blade angle according to a fourth aspect of the present invention distributes.Predicting the outcome of warp-wise component by the auxilliary stream that obtains with the numerical analysis shown in Figure 15 to 38 compared, and can confirm, when the characteristic feature that distributes when blade angle became obvious, auxilliary inhibition effect of flowing through to component strengthened.
Promptly, the result of centrifugal pump impeller numerical analysis order in Figure 20,23 and 26 has showed that auxilliary stream suppresses the enhancing of effect, and in the corresponding blade angle difference of Figure 65 distributed, the blade angle difference presented more obvious increase tendency along the impeller outlet direction with identical order.So the validity of the 4th aspect of the present invention is significantly confirmed.Also have, the blade angle distribution table on impeller boss and the cladding plate reveals as the Figure 13 (A) and (B) feature of described the 4th aspect of the present invention.
In the verification msg of mixed-flow pump impeller, blade angles
HAnd β
SFeature can see from Figure 66 to 68.Similar with the situation of centrifugal pump impeller, can confirm that the 4th aspect of the present invention and Figure 32 among Figure 68,35 and 38 shown auxilliary stream inhibition degree are closely related.
In above-mentioned figure, distributing with the blade angle of the impeller of traditional design method design dots.Conventional method and difference of the present invention can be learnt significantly.According to the traditional design method of centrifugal or mixed-flow pump impeller, " the centrifugal or axial-flow pump " of this method such as A.J.Stepanoff, second edition, John Willy ﹠amp; Sons, New York, 1957, P95～104, or J.L.Dicmas " vertical turbine engine, mixed flow and volute pump ", Mac Graw-Hill, New York, 1989, P305～311, in case the blade angle of impeller eye and impeller outlet determines by designing requirement, then impeller eye and blade angle between impeller outlet distribute and can come roughly definitely by be connected them with a curve, and this curvilinear motion is mild, smooth.So in traditional design method, do not consider the inhibition of auxilliary stream.Dash lines show among Figure 63 to 68 blade angle of the impeller by the design of this traditional design method distribute.Therefore, auxilliary stream can not get suppressing in conventional impellers, and the numerical analysis result of this point by Figure 17 and 29 obtains confirming that this figure is corresponding to the represented conventional impellers of dotted line in Figure 65 and 68.Figure 69 to 74 has showed the verification msg of compressor impeller.This impeller has the feature of the blade angle distribution of the 4th aspect of the present invention.By comparing, can confirm obviously that when the blade angle distribution characteristics of the 4th aspect became obvious gradually, the effect that auxilliary stream suppresses strengthened with the auxilliary stream of warp-wise of numerical analysis prediction among Figure 44,47,50,56,59,69.Here, the dash lines show among Figure 69 to 74 blade angle of conventional impellers of typical compressor distribute.In this compressor, owing to finished in the front portion of blade along the deceleration of flowing on cladding plate surface for reducing frictional loss, the blade angle that is different from pump impeller distributes so blade angle distributes.But, because the basic inhibition that does not have the auxilliary stream of consideration, so the distribution of the warp-wise of auxilliary stream is not inhibited.This point can obtain by the accordingly result of the numerical analysis shown in Figure 41 and 53 confirming.
The 3rd aspect that Figure 75 has showed blade lean in the mixed-flow pump impeller and second aspect of blade load be result's effect mutually.Its blade lean ratio of geometrical shape of only adopting the impeller of the 3rd aspect of the present invention design is S=0.217, shown in Figure 75 (A), this impeller shows very big blade lean and has very little blade pitch angle γ at circumferencial direction, and the shape of impeller is difficult to make.On the other hand, the impeller that adopts the 3rd aspect of the present invention and second aspect to combine and design has the blade lean that reduces by half and compares S=0.1, with the relatively large tilt angle r shown in Figure 75 (B), thereby solved the difficulty of making, and effect of the present invention obtains also confirming.
Industrial usability
The present invention has the feature of the following aspects in design turbine machinery impeller.
(1) the quiet pressure differential deltap Cp of contrast or relatively Mach number difference Δ M with respect to zero dimension through showing to distance The trend that obviously reduces.
(2) r Ve through being (r to derivative Ve)/ m is along through having such to the distance direction Distribute, i.e. (r on the cladding plate Ve)/maximum of m appears at the front portion of blade, and/or on the impeller hub (r Ve)/maximum of m appears at the rear portion of blade.
(3) blade is not a constant value at circumferential inclination angle r, thus on the direction of rotation of impeller impeller The blade main points of hub side are prior to the blade of cladding plate side.
(4) blade angles on the impeller hubHWith the blade angles on the cladding plateSBetween blade angle difference βH
-β
SWith respect to zero dimension through present the trend of obvious increase to distance.
According to the feature of above several aspects, secondary flow through can effectively being suppressed to component, so turbine machinery Or the loss in the downstream canal can reduce, and can avoid occurring the absolute feature curve that tilts, and can improve The stability of operation. Therefore, the present invention has great practical value in industry.
Consider above 4 aspects, by the checking number consistent with reverse design method and Flow Analysis Technique According to, these applicabilities have obtained enhancing, so the present invention can be used for industry effectively.
Claims (19)
1. the centrifugal or mixed-flow turbine machinery that has an impeller, this impeller has a large amount of blade (3) and is supported on the impeller boss (2), this impeller boss upper blade (3) is along circumferentially arranging and covering a cladding plate (4), this cladding plate has formed the external boundary that fluid flows in the runner, between two adjacent vanes (3), determined the direction that flows, its characteristics are, the design of described impeller (6) makes contrast differential static pressure Δ Cp or the relative Mach number difference Δ M between impeller boss (2) and cladding plate (4) on blade (3c) the negative pressure surface, between the position (impeller eye (6a)) and zero dimension warp-wise position (impeller outlet (6b)) apart from m=1.0 of zero dimension, present reducing of enough degree to suppress the warp-wise component of auxilliary stream effectively with the increase of described zero dimension warp-wise distance apart from m=0.
2. centrifugal or mixed-flow turbine machinery as claimed in claim 1, it is characterized in that, wherein pressure coefficient Cp on impeller boss side (2) blade (3) the malleation surface (3a) and the pressure difference between the pressure coefficient Cp on negative pressure surface (3b), and the pressure difference between the pressure coefficient Cp on the pressure coefficient Cp on cladding plate side (4) blade (3) the malleation surface (3a) and negative pressure surface (3b), only in of the position vanishing of impeller (6) rear portion zero dimension warp-wise apart from m=1.0.
3. centrifugal or mixed-flow turbine machinery as claimed in claim 1, it is characterized in that, the design of wherein said impeller (6) makes that the warp-wise derivative of r Ve is (r Ve)/ m, in the anterior cladding plate side (4) of impeller with in the position of zero dimension warp-wise apart from necessity, have the warp-wise component of a maximum value with the auxilliary stream of effective inhibition, this r Ve is the product of the tangential mean value of the circumferential speed component Ve of fluid absolute velocity V in impeller (6) radius r and described impeller radius r place impeller (6) runner, and the derivative of this r Ve only has minimum value of zero at impeller (6) rear portion zero dimension warp-wise apart from the cladding plate side (4) that is the position of m=1.0, and/or the warp-wise derivative of r Ve is (r Ve)/ m, in impeller rear portion impeller boss side (2) with in the position of zero dimension warp-wise apart from necessity, have the warp-wise component of a maximum value, and the warp-wise derivative of this r Ve only has minimum value of zero at impeller rear portion zero dimension warp-wise apart from the impeller boss side (2) that is the position of m=1.0 with the auxilliary stream of effective inhibition.
4. centrifugal or mixed-flow turbine machinery as claimed in claim 1, it is characterized in that, the design of wherein said impeller (6) makes that the warp-wise derivative of r Ve is (r Ve)/ m, the zero dimension warp-wise apart from m=0 near the value of (impeller eye side) its cladding plate side (4) be greater than its impeller boss side value to a certain degree, to suppress the warp-wise component of auxilliary stream effectively, r Ve is the product of the tangential mean value of circumferential speed component Ve of fluid absolute velocity V in impeller (6) radius r and described impeller radius r place impeller (6) runner, and the warp-wise derivative of described r Ve is (r Ve)/ m, the zero dimension warp-wise apart from m=1 (impeller outlet side) near the value of its cladding plate side (4) be less than its impeller boss (2) side value to a certain degree, warp-wise component with the auxilliary stream of effective inhibition, and the distribution of the described r Ve of impeller boss side (2) warp-wise derivative only intersects with the distribution of cladding plate side (4) on a position at impeller rear portion, only on the position of zero dimension warp-wise apart from m=1.0 (impeller outlet (6b)), impeller (6) rear portion, its cladding plate side (4) and impeller boss side (2) all have minimum value of zero to the warp-wise derivative that also has described r Ve.
5. centrifugal or mixed-flow turbine machinery as claimed in claim 4 is characterized in that, wherein said intersection occurs in zero dimension warp-wise distance and is not less than on the interior position of 0.5 (impeller outlet side) scope.
6. centrifugal or mixed-flow turbine machinery as claimed in claim 4 is characterized in that, it is on the interior position of 0.55～0.85 (impeller outlet side) scope that wherein said intersection occurs in zero dimension warp-wise distance.
7. centrifugal or mixed-flow turbine machinery as claimed in claim 1, it is characterized in that, wherein said blade (3), along the circumferential direction tilt between apart from the position (impeller outlet (6b)) of m=1.0 apart from the position (impeller eye (6a)) of m=0 and zero dimension warp-wise at the zero dimension warp-wise, so the blade of impeller boss side (3) will be prior to the blade (3) of cladding plate side on the sense of rotation of described impeller, and blade tilt r along the Way out of described impeller (6) present to a certain degree reduce the warp-wise component of trend with the auxilliary stream of effective inhibition, this angle r is defined as the angle of cladding plate surface (4) and blade centreline on the runner sectional drawing.
8. centrifugal or mixed-flow turbine machinery as claimed in claim 7, wherein blade angle α
TEThe value α of (2) from impeller boss
TE, HBe decreased to the value α on the cladding plate (4)
TE, S, this angle α
TEThe angle of tangent direction on described impeller (6) planimetric map that is defined as the impeller camber line in outlet port (6b) and looks from impeller eye.
9. centrifugal or mixed-flow turbine machinery as claimed in claim 8 is characterized in that, wherein blade angle α
HHave a maximum value or local maximum at impeller (6) outlet side, this angle α
HBe defined as the blade camber line of impeller boss (2) side on the described paddle wheel plane figure that looks from the impeller eye side and the angle of tangent direction.
10. centrifugal or mixed-flow turbine machinery as claimed in claim 9, wherein blade angle α
HDescribed maximum value or local maximum appear at position or the zero dimension radius ratio that zero dimension warp-wise distance is not less than m=0.7 and be not less than r
*=0.6 position (impeller outlet side).
11. centrifugal or mixed-flow turbine machinery as claimed in claim 1, wherein said blade (3) along the circumferential direction tilts between for the position of m=1.0 (impeller outlet (6b)) apart from the position (impeller eye (6a)) and the zero dimension warp-wise that are m=0 at the zero dimension warp-wise, so that the blade of impeller boss side (3) will be prior to the blade (3) of cladding plate side on the sense of rotation of described impeller (6), and blade (3) changes to the warp-wise component of certain big degree with the auxilliary stream of effective inhibition at the sweepback angle of cladding plate (4) side along impeller outlet direction (6b), makes
{d(rθ)/dr}
S＞{d(rθ)/dr}
H。
12. the centrifugal or mixed-flow turbine machinery as one of claim 7 to 11 is characterized in that wherein along the circumferential direction the design of described blade lean makes blade lean be not less than S=0.14 than S, this S value is represented the overall degree of impeller inclination and is defined as S=(θ
TE, S-θ
TE, H)/(θ
TE, M-θ
LE, M), θ wherein
TE, SBe the angular coordinates of cladding plate side (4) impeller outlet (6b), θ
TE, HBe the angular coordinates of impeller boss (2) lateral lobe wheel outlet (6b), θ
TE, MBe the angular coordinates of impeller outlet (6b) on the intermediate point between cladding plate (4) and the impeller boss (2), θ
LE, MAngular coordinates for impeller eye (6a) on the intermediate point between cladding plate (4) and the impeller boss (2).
13. as claim 1,2,3,4, one of 5 and 6 centrifugal or mixed-flow turbine machinery, it is characterized in that, wherein blade (3) along the circumferential direction tilts so that on the sense of rotation of impeller (6) blade (3) of impeller boss (2) side prior to the blade (3) of cladding plate (4) side.
14. centrifugal or mixed-flow turbine machinery as claimed in claim 1 is characterized in that, the design of wherein said impeller (6) makes from the distribution of the blade angle of circumferencial direction tolerance, the blade angles of impeller boss (2) side
HBlade angles with cladding plate side (4)
SBetween difference β
H-β x presents to a certain degree increase trend effectively to suppress the warp-wise component of auxilliary stream apart from the position (impeller eye (6a)) of m=0 to zero dimension apart from the position (impeller outlet (6b)) of m=1. from zero dimension.
15. centrifugal or mixed-flow turbine machinery as claimed in claim 1 is characterized in that, the design of wherein said impeller (6) makes from the blade angle of circumferencial direction tolerance distributes, the blade angles of impeller boss (2) side
HBlade angles with cladding plate side (4)
SBetween poor β
H-β
SZero dimension apart from the position (impeller eye (6a)) of m=0 and zero dimension warp-wise apart from the part between the position (impeller outlet (6b)) of m=1.0 in, present the trend that reduces, subsequently along with the increase of described zero dimension warp-wise distance presents to a certain degree increase tendency with the warp-wise component of the auxilliary stream of effective inhibition.
16. the centrifugal or mixed-flow turbine machinery as claim 14 or 15 is characterized in that, wherein said blade angular difference β
H-β
SHas a maximum value or a local maximum that is not less than 20 degree.
17. the centrifugal or mixed-flow turbine machinery as claim 14 or 15 is characterized in that, wherein said blade angular difference β
H-β
SHave a maximum value or local maximum, this value will be greatly apart from interior the average blade angular difference of m=0～0.2 (impeller eye side) scope than zero dimension warp-wise 10 be spent at least.
18. the centrifugal or mixed-flow turbine machinery as claim 16 or 17 is characterized in that, wherein said blade angular difference β
H-β
SDescribed maximum value appear at zero dimension distance and be not less than on the position in m=0.5 (impeller outlet side) scope.
19. the turbomachinery as claim 16 or 17 is characterized in that, wherein said blade angular difference β
H-β
SDescribed maximum value appear at the zero dimension warp-wise apart from the position in the scope of m=0.7～1.0 (near impeller outlet).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 94195152 CN1236196C (en) | 1994-06-10 | 1994-06-10 | Centrifugal or mixed-flow turbine machinery |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 94195152 CN1236196C (en) | 1994-06-10 | 1994-06-10 | Centrifugal or mixed-flow turbine machinery |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN1156493A CN1156493A (en) | 1997-08-06 |
| CN1236196C true CN1236196C (en) | 2006-01-11 |
Family
ID=5039655
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN 94195152 Expired - Lifetime CN1236196C (en) | 1994-06-10 | 1994-06-10 | Centrifugal or mixed-flow turbine machinery |
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| Country | Link |
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| CN (1) | CN1236196C (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101915126A (en) * | 2010-06-04 | 2010-12-15 | 清华大学 | Tandem blade type mixed-flow or radial-flow turbine |
Families Citing this family (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US7281901B2 (en) * | 2004-12-29 | 2007-10-16 | Caterpillar Inc. | Free-form welded power system component |
| WO2015023850A1 (en) * | 2013-08-14 | 2015-02-19 | Heartware, Inc. | Impeller for axial flow pump |
| ITFI20130261A1 (en) * | 2013-10-28 | 2015-04-29 | Nuovo Pignone Srl | "CENTRIFUGAL COMPRESSOR IMPELLER WITH BLADES HAVING AN S-SHAPED TRAILING EDGE" |
| JP6184017B2 (en) * | 2014-01-14 | 2017-08-23 | 三菱重工業株式会社 | Impeller and rotating machine having the same |
| CN104863892A (en) * | 2014-02-20 | 2015-08-26 | 顾发华 | Impeller with high outlet flow field uniformity and centrifugal compressor |
| CN105422503B (en) * | 2015-12-30 | 2019-03-22 | 合肥华升泵阀股份有限公司 | A kind of combination type blade wheel |
| CN112128120B (en) * | 2020-09-17 | 2022-08-23 | 青岛海信日立空调系统有限公司 | Ultra-thin indoor unit |
-
1994
- 1994-06-10 CN CN 94195152 patent/CN1236196C/en not_active Expired - Lifetime
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101915126A (en) * | 2010-06-04 | 2010-12-15 | 清华大学 | Tandem blade type mixed-flow or radial-flow turbine |
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| Publication number | Publication date |
|---|---|
| CN1156493A (en) | 1997-08-06 |
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