CN1920260A - Structure of radial turbine scroll and blades - Google Patents
Structure of radial turbine scroll and blades Download PDFInfo
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- CN1920260A CN1920260A CN 200610110865 CN200610110865A CN1920260A CN 1920260 A CN1920260 A CN 1920260A CN 200610110865 CN200610110865 CN 200610110865 CN 200610110865 A CN200610110865 A CN 200610110865A CN 1920260 A CN1920260 A CN 1920260A
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Abstract
The improvements are made in the turbine scroll and the turbine blades. The scroll structure for the radial turbines is characterized by the foregoing scroll having a scroll width ratio between the width in the radial direction (DELTA R) and the width in the direction of the rotation (B) ranging from DELTA R/B = 0.3 to 0.7. It is further characterized by the configuration in which the turbine blades have cut-away areas at the blade corners by a prescribed amount, which are provided on the inlet edge at the shroud side and hub side where the operating gas flows.
Description
The application is that application number is 02147229.7, the applying date is on October 18th, 2002, denomination of invention is divided an application for the patent application of " structure of the Structure of radial turbine scroll and the moving wing ".
Technical field
The present invention relates to the structure of a kind of Structure of radial turbine scroll and the moving wing.Structure of radial turbine scroll is used in the pressurized machine (waste gas supercharger) of internal-combustion engine, small-sized gas turbine, expansion turbine etc., formation is flowed out after making it act on this moving wing on the moving wing of start gas from Vorticose volute pipeline radial inflow to turbine rotor vertically, rotation drives the gas flow path of the radial turbine of the such structure of this turbine rotor, in addition, the moving wing is fixed in the rotating shaft of compressor.
Background technique
The radial turbines that adopt such as the more small-sized pressurized machine (waste gas supercharger) that is used in automobile engine etc. more, this radial turbine radially flow into the moving wing that is positioned at this volute insides of pipes turbine rotor by making start gas from the Vorticose volute pipeline that is formed in the turbine cylinder, makes it flow out rotation vertically after acting on this moving wing and drives this turbine rotor.
Figure 11 represents to use an example of the pressurized machine of such radial turbine, in the drawings, the 1st, the turbine cylinder, 4 are formed in the Vorticose volute pipeline in this turbine cylinder 1,5 are formed in the gas outlet path on interior week of above-mentioned vortex cylinder 1, the 6th, compression case, the 9th, connect the bearing housing of above-mentioned turbine cylinder 1 and compression case 6.
The 10th, turbine rotor is circumferentially equally spaced being fixed the moving wing 3 of a plurality of turbines in its periphery upper edge.The 7th, compressor, 8 are provided in a side of the diffuser of the air outlet slit of this compressor 7, and the 12nd, connect the rotor shaft of this turbine rotor 10 and compressor 7.11 are mounted on the above-mentioned bearing housing 9 and support the pair of bearings of above-mentioned rotor shaft 12.The 20th, above-mentioned turbine rotor 10, compressor 7, and the axis of rotation of rotor shaft 12.
In pressurized machine with such radial turbine, discharge gas from internal-combustion engine (omitting among the figure) enters above-mentioned volute pipeline 4, outer circumferential side entrance face from the moving wing 3 of a plurality of turbines when changeing along the vortex of this volute pipeline 4 flows into the moving wing 3 of this turbine, expansion work has been finished in the back of radially flowing towards turbine rotor 10 central sides in this turbine rotor 10 after, flow out vertically and be sent outside the machine from gas outlet path 5.
Figure 12 is above-mentioned volute pipeline 4 and near the pie graph thereof in the such radial turbine of expression.In the drawings, the 4th, volute pipeline, the 41st, the periphery wall of this volute pipeline 4, the 43rd, inner circle wall, the 42nd, sidewall.The 3rd, turbine moves the wing, the 36th, the moving wing 3 of this turbine cover ring (shroud) side, the 34th, wheel hub (hub) side.
The width Delta R of the radial direction of above-mentioned volute pipeline 4
0Width B with the axis of rotation direction
0(the volute channel width is than Δ R to form essentially identical size
0/ B
0=1).
In addition, Figure 13 (A), (B) are formed near the pie graph the tongue on week in the gas access of such radial-flow type scroll machine.Figure 13 (A) is the front view vertical with axis of rotation, and Figure 13 (B) is that the B-B of Figure 13 (A) is to view.
In Figure 13 (A), Figure 13 (B), the 4th, the volute pipeline, the 44th, the entrance face of this volute pipeline 4,45 is formed in the tongue in week in the gas access, 45a is the tongue end as the downstream of this tongue 45, the 046th, be positioned at the tongue downstream sidewall in this positive downstream of tongue end 45a of above-mentioned volute pipeline 4.
The width that this tongue downstream sidewall is 046 is identical with above-mentioned tongue end 45a or dwindle sleekly along the shape of volute pipeline 4 from this tongue end 45a.
In such radial turbine,, the vortex of the above-mentioned volute pipeline 4 in an edge has different velocity distribution in the short transverse (Z direction) of the moving wing 3 of turbine Yi Bian changeing the gas inflow velocity that flows into the gas in the moving wing 3 of turbine.
Promptly as shown in figure 14, above-mentioned gas inflow velocity C is owing to be formed near the height B with above-mentioned entrance face 31 of entrance face 31 (with reference to Figure 12) of the moving wing 3 of above-mentioned turbine
2The three-dimensional boundary layer of 15～20% width, as the circumferential speed C of the Zhou Fangxiang composition of above-mentioned gas speed C
θThe central part of above-mentioned entrance face 31 is big, and ring side 36 is promptly covered in the bight at two ends and hub side 34 diminishes.In addition, as the radial direction speed C of radial direction composition
RAs shown in figure 11, the central part that becomes above-mentioned entrance face 31 is little, and the distribution that ring side 36 and hub side 34 becomes big such short transverse is promptly covered in the bight at two ends.
And when the Flow Distribution that inflow gas is arranged on the entrance height direction of the moving wing 3 of above-mentioned turbine was flow deformation, the flow losses at the moving wing 3 places of this turbine increased and cause the reduction of efficiency of turbine.Promptly flow into relative angle β with respect to optimal gas with the moving wing 3 of above-mentioned turbine
1The moving wing 3 inlet central parts of the turbine that coincide, the wall side of entrance face 31 are that above-mentioned hub side 34 and the gas that covers ring side 36 flow into relative angle β
2Become big, in above-mentioned hub side 34 and cover difference that ring side 36 gases flow into relative angle β and promptly collide angle (incident angle) when becoming big, gas is to collide the dorsal part that angle (incident angle) flows into the moving wing 3 of above-mentioned turbine, produce the collision loss of moving wing inlet, above-mentioned hub side 34 and the increase of covering the collision angle (incident angle) at ring side 36 places have encouraged the increase of the secondary flow loss of the moving wing 3 of turbine, and efficiency of turbine reduces.
In addition, constituting in the above-mentioned volute pipeline 4 of the gas access stream of the moving wing 3 of above-mentioned turbine, because the shape of this volute pipeline 4 former thereby produce three-dimensional boundary layer, therefore shown in Figure 15 (B), in the wing short transverse of the moving wing 3 of turbine, radial direction speed C
RThe central part that constitutes its above-mentioned entrance face 31 diminishes, ring side 36 is promptly covered in the bight at two ends and hub side 34 becomes big such velocity flow profile.
But in Figure 12 and existing turbine 4 shown in Figure 13,
(1) the stream section configuration of volute pipeline 4 is width Delta R of radial direction
0Width B with the axis of rotation direction
0(the vortex width is than Δ R to form essentially identical size
0/ B
0=1) roughly square section.
(2) two side walls 42 of promptly covering the volute pipeline 4 that ring side 36 and hub side 34 link to each other with two vertex angle parts of the moving wing 3 of turbine is even surfaces.
(3) form the width B of axis of rotation direction of the stream of volute pipeline 4
0On radial direction, necessarily or from outer circumferential side dwindle in certain proportion towards interior all sides.
Above-mentioned result produces following problem.
Owing to be formation as described above,, form above-mentioned three-dimensional boundary layer easily towards the place, gas access of the moving wing 3 of above-mentioned turbine.
In addition, at above-mentioned tongue 45 places, because the pressure difference up and down of these tongue 45 thickness produces the wake flow 50 shown in Figure 13 (A), in the prior art, as shown in figure 10, because the width of 046 of tongue downstream sidewall and tongue end 45a be with wide or dwindle sleekly along the shape of volute pipeline 4 from this tongue end 45a, so do not reduce the effect of above-mentioned wake flow 50, thus, be shown on the Zhou Fangxiang radial direction speed C as Figure 15 (A)
RForm flow deformation at random.
Therefore, in such prior art, owing to the shape of the such volute pipeline 4 in above-mentioned (1), (2), (3) generates three-dimensional boundary layer, because gas stream has the moving wing 3 of flow deformation ground inflow turbine in the short transverse of the moving wing 3 of turbine, the flow losses of the moving wing 3 of turbine increase, and cause efficiency of turbine to reduce.
In addition, in such prior art, have because the formation of the downstream sidewall 046 of above-mentioned tongue end 45a, do not reduce the effect of the wake flow 50 that the thickness T of tongue 45 produces, and since boundary layer along circumferentially forming radial direction speed C
RFlow deformation at random, volute stream loss increases, and causes the problem of the reduction etc. of efficiency of turbine.
In addition, therefore the shape of the moving wing 3 of above-mentioned turbine moves wing circular velocity U owing to the external diameter that is entrance face 31 is identical along the overall height that covers ring side 36, central part, hub side 34 like that shown in the B part of Figure 16 (A)
2=U
1Therefore gas flows into relative angle β difference on the short transverse of this moving wing 3, when the gas with the central part shown in the E part of Figure 16 (A) flows into relative angle β
1When being adjusted into the best, the wall side shown in the D of Figure 16 (A) part is that above-mentioned hub side 34 and the gas that covers ring side 36 flow into relative angle β
2Owing to the flow deformation from above-mentioned volute pipeline 4 becomes than the gas inflow relative angle β of central part
1Greatly.
And, W
1, W
2Be that gas flows into relative angle, C
1, C
2Be that gas flows into absolute velocity.
Therefore, in such prior art, above-mentioned hub side 34 and cover the ring side 36, gas is to collide the dorsal part (suction surface side) that angle (incident angle) flows into the above-mentioned moving wing 3, produce the collision loss of moving wing inlet, above-mentioned hub side 34 and the increase of covering the collision angle (incident angle) of ring side 36 simultaneously encouraged the increase of the secondary flow loss of the moving wing 3 inside, causes the reduction of efficiency of turbine.
Summary of the invention
The present invention develops in view of such prior art problems.Promptly the Structure of radial turbine scroll and the moving wing are improved.The volute pipe configuration that the purpose of this invention is to provide a kind of radial turbine, this volute pipe configuration, the generation of the three-dimensional boundary layer that inhibition is caused by the shape of the volute pipeline of the moving wing ingress of turbine, the formation of the flow deformation by the air-flow in the short transverse of avoiding the moving wing of this turbine reduces the flow losses of the moving wing of this turbine, and the formation of the discrete flow deformation that produces of Zhou Fangxiang by reducing the radial direction speed in the volute pipe passage suppresses the increase of volute pipe passage loss, has improved the efficient of turbine.
In order to realize purpose of the present invention, the structure of Structure of radial turbine scroll of the present invention is used in the structure of the Structure of radial turbine scroll of radial turbine, wherein by make start gas from be formed on Vorticose volute pipeline in the turbine cylinder flow into along radial direction the inboard be positioned at the volute pipeline turbine rotor the moving wing and act on this moving wing after flow out vertically that this turbine rotor of rotary driving constitutes, it is characterized in that the stream cross-section area in positive downstream side of tongue that is formed in the gas access week is than the stream cross-section area of tongue end uvula portion thickness size (T) partly on width direction.
Width between the sidewall in the positive downstream side of above-mentioned tongue also can form than the uvula portion thickness size (T) partly on width direction of the width between the sidewall of tongue end.
According to such invention, the stream cross-section area than tongue end that forms by the inflow cross-section area with the positive downstream side of tongue partly little (particularly the width between the sidewall in the positive downstream side of tongue being formed than the uvula portion thickness size (T) partly on width direction of the width between the sidewall of tongue end) can be reduced in the wake flow that tongue produces and can reduce the flow deformation of volute pipeline exit.
In addition, by on width direction, the flow path width in the positive downstream side of tongue being dwindled tongue thickness size (T) partly, can suppress the development of three-dimensional boundary layer, reduce the flow losses that the state that has flow deformation on the short transverse of air-flow with the moving wing flows into the moving wing that this moving wing produced same as the previously described embodimentsly, improve efficiency of turbine.
Description of drawings
Fig. 1 is the pie graph along the section of upper half part of axis of rotation of expression vortex body of the first embodiment of the present invention and turbine rotor.
Fig. 2 is above-mentioned first embodiment's an Action Specification line chart.
Fig. 3 (A) is expression second embodiment's the figure corresponding with Fig. 1, and Fig. 3 (B) is the gas flow rate distribution map.
Fig. 4 is expression the 3rd embodiment, and Fig. 4 (A) is the figure corresponding with Fig. 1, and Fig. 4 (B) is that the A-A of Fig. 4 (A) is to view.
Fig. 5 is expression the 4th embodiment, and Fig. 5 (A) is the front view of volute pipeline, and Fig. 5 (B) is that the B-B of Fig. 5 (A) is to view.
Fig. 6 (A), (B), (C) are above-mentioned the 4th embodiment's Action Specification figure.
Fig. 7 (A), (B) are the gas flow rate distribution maps in the volute pipeline.
Fig. 8 (A) is to use the sectional drawing along axis of rotation of the pressurized machine that is suitable for radial turbine of the present invention.Fig. 8 (B) is an External view.
Fig. 9 is the sectional drawing of other embodiments of the invention.
Figure 10 (A), (B) are the explanatory drawings of the secondary flow in the moving wing of such embodiment's inhibition turbine.
Figure 11 is the sectional drawing of the example radial turbine of prior art.
Figure 12 is the volute pipe section 4 of radial turbine of example of expression prior art and near pie graph.
Figure 13 (A), (B) are near the pie graphs of going up in week in the gas access of such radial turbine the tongue that forms, and Figure 13 (A) is the front view vertical with rotating center, and Figure 13 (B) is that the B-B of Figure 13 (A) is to view.
Figure 14 is the Action Specification figure of expression gas inflow velocity C.
Figure 15 is the interior gas flow distribution figure of volute pipeline of prior art.
Figure 16 (A) is the moving wing of expression prior art example, and Figure 16 (B) is the circumferential speed C of expression as the circumferential composition of the gas velocity C of the moving wing ingress of turbine
θ
Figure 17 is the plotted curve that circumferentially reaches the variation of the gas flow rate in the height of the moving wing inlet of expression.
Embodiment
Below, describe the present invention in detail with illustrated embodiment.But, short of specific especially records such as the size of the constituent part of putting down in writing among this embodiment, material, shape, its relative position, this scope of invention is not limited to this, only only is illustrative examples.
The structure of volute pipeline
The basic comprising and the existing turbosupercharger shown in Figure 11 of turbosupercharger that has radial turbine is similar.But the shape to the volute pipeline improves in the present invention.
In Figure 11, represented to use the unitary construction that is suitable for the pressurized machine of radial turbine of the present invention.The 1st, the turbine cylinder, 4 are formed in the Vorticose volute pipeline in this turbine cylinder 1, and 5 are formed in the gas outlet path on interior week of above-mentioned turbine cylinder 1, and the 6th, compressor housing, the 9th, connect the bearing housing of above-mentioned turbine cylinder 1 and compressor housing 6.
The 10th, turbine rotor, the circumferential moving wing 3 of a plurality of turbines of equally spaced fixing in its periphery upper edge.The 7th, compressor, 8 are provided in a side of the diffuser of the air outlet slit of this compressor 7, and the 12nd, connect the rotor shaft of this turbine rotor 10 and compressor 7.11 are mounted in the pair of bearings that is used to support above-mentioned rotor shaft 12 on the above-mentioned bearing housing 9.The 20th, the axis of rotation of above-mentioned transparent rotor 10, compressor 7 and rotor shaft 12.
In such pressurized machine with radial turbine, the exhaust of coming out from the internal-combustion engine (not shown) enters above-mentioned volute pipeline 4, flow into the moving wing 3 of this turbine along the vortex of this volute pipeline 4 while changeing, flow out vertically expansion work has been finished in the back in this turbine rotor 10 after and be sent outside the machine flowing along radial direction from gas outlet path 5 towards turbine rotor 10 central sides from the outer circumferential side entrance face of the moving wing 3 of a plurality of turbines.
That is, in Fig. 1 of first embodiment who represents the volute pipeline, the 10th, turbine rotor is equally spaced being fixed the moving wing 3 of a plurality of turbines vertically on its periphery.
4 are formed in the volute pipeline in the turbine cylinder 1, the 41st, its periphery wall, the 42nd, the sidewall of front side and rear side, the 43rd, inner circle wall.The distance that the sidewall of above-mentioned volute pipeline 4 front sides and rear side is 42 is that the width B of axis of rotation 20 directions is that the width Delta R of radial direction forms greatly than the distance of periphery wall 41 and inner circle wall 43.
And the volute channel width of the width of the above-mentioned radial direction of above-mentioned volute pipeline 4 (Δ R) and the width B of axis of rotation 20 directions is Δ R/B=0.3～0.7 than Δ R/B, preferably Δ R/B=0.5.
In such embodiments, the volute channel width of the width Delta R of the radial direction of volute pipeline 4 and the width B of axis of rotation 20 directions is constituted Δ R/B=0.3～0.7 than Δ R/B, and with the width B of axis of rotation 20 directions of this volute pipeline 4 along about the twice of the long width Delta R that forms radial direction longways of the direction of axis of rotation 20, thereby make the flattening of volute pipe shape.
Thus, 42 frictional losses with 41,42 ones of internal and external peripheral walls of sidewall that added up to volute pipeline 4 are the same degree that constitute roughly 1 prior art with the volute channel width than Δ R/B, but with the speed C of the radial direction at the place, two side of covering this corresponding volute pipeline of ring side and hub side as the moving wing two vertex angle parts
RReduce the radial direction speed C in axis of rotation 20 directions of volute pipeline 4 than above-mentioned volute channel width than what Δ R/B constituted prior art about 1
RDistribution average out.Therefore the secondary flow loss in the volute pipeline reduces.
Fig. 2 is the analog result (above-mentioned volute channel width is than the relation of Δ R/B with the pressure loss) of the gas flow loss of the expression volute pipeline 4 and the moving wing 3 of turbine.As shown in Figure 2, as the present invention (scope of N), if Δ R/B=0.3～0.7, preferably Δ R/B=0.5 then is in N with the volute channel width than Δ R/B
0The prior art of scope compare, the gas flow loss diminishes significantly.
Thus, suppressed the generation of three-dimensional boundary layer, the air-flow that has passed through volute pipeline 4 on the short transverse of the moving wing 3 of turbine, have flow losses that flow deformation ground flows into these the moving wing 3 caused moving wings 3 particularly losses by mixture be lowered.
Among second embodiment of the volute pipeline shown in Fig. 3 (A), (B), shown in (A), the section configuration of volute pipeline 4 is formed the width B of the B of axis of rotation 20 direction width from the radial direction outer circumferential side
1Width B towards interior all sides
2Straight line or curve-like enlarge (situation of expression straight line shape in this example) in certain proportion.
The width B of above-mentioned axis of rotation 20 directions is with the width B of all sides in the radial direction
2Form the distolateral width B of periphery
11.2～1.5 times.Other formation is identical with first embodiment shown in Figure 1, and identical therewith member is with identical symbolic representation.
In such embodiments, because the width B of the axis of rotation direction of volute pipeline 4 is enlarged along radial direction towards inner circle wall 43 sides from periphery wall 41, therefore, promptly cover the radial direction speed C of two side 42 sides of this corresponding volute pipeline of ring side 36 and hub side 34 with two vertex angle parts of the moving wing 3 of turbine
RAlong with being decelerated the speed C of the radial direction of two side 42 sides near the moving wing 3 of the above-mentioned turbine of the interior all sides that are in the volute pipeline
RConstitute certain prior art than width and reduce the radial direction speed (C in the axis of rotation direction of this volute pipeline 4 above-mentioned volute pipeline
R) distribution homogenized.
That is, shown in Fig. 3 (B), with the M of the outer circumferential side of volute pipeline 4
1The radial direction speed C of portion
RAxis of rotation direction its two side 42 sides that distribute bigger and inhomogeneous than central part, relative therewith, with the M of the approaching interior all sides of the moving wing of turbine 3
2Radial direction speed C on the axis of rotation direction of portion
RThe axis of rotation direction distribute by the radial direction speed C of these two side 42 sides of slowing down
RAnd it is homogenized.
Thus, suppressed the development of three-dimensional boundary layer, air-flow is lowered with the loss that the state that has flow deformation on the short transverse of moving the wing flows into the caused moving wing of this moving wing.
In the 3rd embodiment of the volute pipeline shown in Fig. 4 (A), (B), the two side 042 of above-mentioned volute pipeline 4 is formed male and fomale(M﹠F).No matter the male and fomale(M﹠F) of above-mentioned two side 042 is to form multilayer concentric along radial direction to justify the ditch of shape, still form spiral helicine ditch, so long as play the such radial direction speed C of needed aftermentioned shown in Fig. 4 (B)
RThe male and fomale(M﹠F) of decelerating effect get final product.Other formation is identical with first embodiment shown in Figure 1, and the member identical with it is with identical symbolic representation.
In such embodiments, form male and fomale(M﹠F), slow down by above-mentioned male and fomale(M﹠F) and promptly cover the radial direction C at 042 place, two side that encircles this corresponding volute pipeline 4 of side 36 and hub side 34 with two vertex angle parts of the moving wing 3 of above-mentioned turbine by two side 042 with volute pipeline 4
R, diminish the radial direction speed C on the rotating center direction of this volute pipeline 4 than the prior art that the volute pipe side wall is formed even surface
RDistribution homogenized.
Thus, suppressed the generation of three-dimensional boundary layer, had the loss that the indeformable state that flows flows into these the moving wing 3 caused moving wings 3 on the short transverse of air-flow with the moving wing of turbine and be lowered.
In the 4th embodiment shown in Fig. 5 (A), (B), the width that the tongue downstream sidewall in the positive downstream side of the tongue 45 of thickness T above-mentioned volute pipeline 4, that be formed in the gas access week is 46 dwindles tongue width dimensions T partly than the width of 42 of the sidewalls at tongue end 45a place on width direction, the stream cross-section area in the positive downstream side of above-mentioned tongue 45 is diminished partly than the stream cross-section area of tongue end 45a.
During gas flow in above-mentioned volute pipeline 4, as described above since above-mentioned tongue 45 thickness up and down pressure difference produce wake flow 50.Yet, in the 4th embodiment by with the width of 46 of above-mentioned tongue downstream sidewalls at width direction uvula portion thickness size (T) partly, stream cross-section area than tongue end is little partly and with the positive downstream side stream cross-section area of above-mentioned tongue 45, therefore, stream throttling action by the positive downstream side of tongue end 45a can be reduced in the wake flow 50 that above-mentioned tongue 45 produces, and can reduce the flow deformation in volute pipeline 4 outlet ports thus.
In addition, in such embodiments, shown in Fig. 6 (C), because the stream throttling action that the flow path width in the positive downstream side of above-mentioned tongue end 45a has been diminished partly, at tongue 45 position (L
1) locate, with generation, near the circumferential speed C of sidewall 42 sidewalls owing to boundary layer
θDiminish, the circumferential speed skewness of rotating center 20 directions of volute pipeline 4 is relative, at tongue downstream 46 (L
2), avoided the above-mentioned circumferential speed C of close sidewall 42
θReduction and above-mentioned circumferential distribution is become evenly.Therefore, the radial direction speed C of above-mentioned axis of rotation 20 directions
RDistribution also become evenly, thereby can suppress the generation of three-dimensional boundary layer, reduced the loss that the state that has flow deformation on the short transverse of air-flow with the moving wing flows into the caused moving wing of this moving wing.
The radial direction speed C of Fig. 7 (A), above-mentioned first～the 4th embodiment's of (B) expression volute pipeline of the present invention and original volute pipeline
RDistribution situation, Fig. 7 (A) expression is the distribution of (θ) circumferentially, the distribution of Fig. 7 (B) expression wing short transverse (Z).As can be seen from Figure 7, radial direction speed C
RThe distribution of circumferential (θ) because above-mentioned the 4th embodiment and from the ducted A of original volute
1To the ducted A of volute of the present invention
2Homogenized like that, and radial direction speed C
RThe distribution of wing short transverse (Z) because above-mentioned first～the 4th embodiment and from the ducted B of original volute
1To the ducted B of volute of the present invention
2Homogenized like that.
The structure of the moving wing
The basic comprising and the existing turbosupercharger shown in Figure 11 of turbosupercharger that has radial turbine is similar.
That is, as represent that the 5th embodiment's turbine moves shown in Fig. 8 (A) of the wing, (B), the week that a plurality of moving wings 3 are fixed on turbine rotor 10 regularly makes progress.This turbine is moving, and the wing is following is being configured like that.
The 31st, the entrance face of formation gas access, the 35th, wheel hub, the 37th, cover ring, the 32nd, exit end face, above-mentioned entrance face 31 is forming a certain amount of portion 33 of cutting is being cut in the bight in cover ring side 36 and the hub side 34 that central part are formed the plane and constitute the short transverse two end part.The above-mentioned stravismus shape of cutting 33 formation portions of portion of (B) expression of Fig. 8.
Above-mentionedly cut portion's 33 its sections and form curve-like with circularity, and joint access end face 31 and cover ring 37 and wheel hub 35 sleekly.
In other example of the moving wing of turbine shown in Figure 9, cut portion 33 to form section configuration be straight line shape above-mentioned.Other formation is identical with the example shown in Fig. 8 (A), and the member identical with it under this embodiment's situation, is straight line shapies owing to cut the section configuration of portion 33 with identical symbolic representation, therefore can easily adjust the diameter D of the such hub side of aftermentioned 34
1And cover the ring side 36 diameter D
2
Above-mentioned wing short transverse of cutting portion 33 cut amount c and radial direction cuts amount d
1And d
2Shown in Figure 16 (B) because the formation width of above-mentioned three-dimensional boundary layer is less than 20% of the height B of above-mentioned entrance face 31, therefore with the formation width of above-mentioned three-dimensional boundary layer as one man constitute above-mentioned entrance face 31 height B 10%～20%.D
0Be the mid-diameter of above-mentioned entrance face 31, D
1Be hub side 34 cut portion's diameter, D
2Be cover ring side 36 cut portion's diameter.The above-mentioned amount of cutting of cutting portion 33 is set as described below.
In Figure 16 (A), with the relative angle beta that flows into of gas with entrance face 31 central part highly
1Be adjusted into the diameter D of these entrance face 31 central parts of optimum value
0, hub side 34 and the diameter that covers ring side 36 are retreated the above-mentioned amount d that cuts with respect to above-mentioned central part
1And d
2And become D respectively
1And D
2
The diameter D of above-mentioned hub side 34
1And cover the ring side 36 diameter D
2Circumferential composition C from the absolute flow velocity C of gas of the moving wing ingress shown in Figure 16 (B)
θObtain with the relation of the peripheral speed U of moving wing ingress.That is the circumferential composition C of above-mentioned absolute flow velocity C,
θSince when moving wing inlet diameter and reduce by the rule (C of free vortex
θR=is certain) speedup, circular velocity U (U=π DN/60, N are the rotating speeds of turbine rotor) reduces on the contrary in addition, therefore by the above-mentioned diameter D that cuts portion 33 with above-mentioned hub side 34
1With the diameter D that covers ring side 36
2The diameter at two end part that is above-mentioned entrance face 31 is than central part diameter D
0Retreat the above-mentioned amount d that cuts
1And d
2, the circumferential composition C of the absolute flow velocity C of speedup
θReduce circular velocity U simultaneously, make the gas at above-mentioned two end part flow into angle beta relatively thus
2The gas that is reduced to central part flows into angle beta relatively
1And become optimum value.
At this, the circumferential composition C of the above-mentioned absolute flow velocity C that the central part of entrance face 31 and two end part (hub side 34 and cover ring side 36) located
θWith radial direction composition C
RRatio from Figure 16 (A) velocity triangle and Figure 16 (B) as can be known, therefore make the moving wing inlet diameter D at above-mentioned two end part (hub side 34 and cover ring side 36) from such relation
1And D
2Diameter D than central part
0Become 90%～99% ground and retreat, obtain above-mentioned two end part gas and flow into angle beta relatively
2Optimum value.
The comparison of the state of the secondary flow in the moving wing 3 of the embodiment's that Figure 10 (A), (B) expression is such turbine and the moving wing 3 of this turbine of the moving wing of existing turbine.Secondary flow is the stream that produces in vertical direction with respect to main flow.In the drawings, S
1Represent original secondary flow state, S
2The secondary flow state of representing embodiments of the invention, (A) influence of the stream of the moving wing inside that secondary flow produced of expression aerofoil, (B) the inner influence of flowing of the moving wing of the secondary flow generation of anchor ring is covered in expression.In Figure 10 (A) as can be known, at original S
1In, produce towards suction surface F
1The wing of side exports, encircles the secondary flow that side (wing top direction) rises to covering, but in such embodiments, by forming the above-mentioned portion 33 of cutting, has suppressed secondary flow at the mobile (S of hub side
2).In addition, from figure (B) as can be known, at original S
1In, secondary flow is created in covers the anchor ring side, but above-mentionedly cuts portion 33 and suppressed secondary flow by forming in such embodiments, in pressure side F2 side flow.
Like this, gas at the inlet side (covering ring, wheel hub) of the moving wing 3 towards suction surface F
1The collision angle (incident angle) of side diminishes, and has reduced the collision loss of moving wing inlet, has suppressed secondary flow simultaneously.
According to such embodiment, the entrance face 31 that moves the wing 3 by turbine is covering ring side 36 and hub side 34, forms on the bight and cuts portion 33, the two end part diameter D of above-mentioned entrance face 31
1And D
2Diameter D than central part
0Little, by make above-mentioned cut portion cut quantitative changeization, the two end part that make the entrance face 31 of the wing 3 are that move back the above-mentioned inside accordingly all rear flank of gas flow distribution of covering ring side 3 and hub side 34 and moving wing inlet, the relative inflow angle (β) that flows into the gas of the moving wing 3 can be adjusted into best angle on the short transverse of this moving wing.
Thus, can be certain on the short transverse of the moving wing 3 with the collision angle (incident angle) of moving the gas of wing ingress.
Put down in writing among such the present invention above, because the volute channel width of the width (Δ R) of the radial direction of volute pipeline and the width (B) of axis of rotation direction is constituted 0.3～0.7 than Δ R/B, and make the shaped flatization of volute pipeline, therefore the radial direction speed at place, the two side of this volute pipeline corresponding with two vertex angle parts of the moving wing reduces than the prior art that Δ R/B constitutes about 1 than volute channel width, suppress the development of three-dimensional boundary layer thus, reduced the flow losses that flow into the moving wing that this moving wing gives birth under gas has flow deformation in the short transverse of the moving wing the state.
The radial direction speed at the place, two side of this volute pipeline corresponding with moving wing two end part is along with being decelerated near the moving wing of the interior all sides that become the volute pipeline, ratio is that certain prior art reduces with volute channel width member, the velocity distribution of the axis of rotation radial direction of this volute pipeline is homogenized, suppress the development of three-dimensional boundary layer thus, reduced the flow losses that flow into the moving wing that this moving wing produces under air-flow has flow deformation in the short transverse of the moving wing the state.
The radial direction speed at the place, two side of this volute pipeline corresponding with moving wing two end part is slowed down by above-mentioned male and fomale(M﹠F), reduce than the prior art that the volute pipe side wall is formed even surface, and it is the velocity distribution of the axis of rotation radial direction of this volute pipeline is homogenized, suppress the development of three-dimensional boundary layer thus, reduced the flow losses that flow into the moving wing that this moving wing gives birth under air-flow has flow deformation in the short transverse of the moving wing the state.
In the present invention,, the wake flow that tongue produces can be reduced in, the flow deformation of volute pipeline exit can be reduced by the stream cross-section area in the positive downstream side of the tongue stream cross-section area than tongue end is diminished partly.
In addition, dwindle tongue thickness size (T) partly by flow path width in the present invention with the positive downstream side of tongue, can suppress three-dimensional interfacial development, reduce the flow losses that flow into the moving wing that this moving wing gives birth under air-flow has flow deformation in the short transverse of the moving wing the state.
According to above the present invention who puts down in writing, cut portion by the bight formation of covering ring side and hub side at the entrance face that moves the wing, the gas flow of the two end part of entrance face of the wing and the moving wing ingress inside accordingly all rear flank that distribute are moved back, the relative inflow angle (β) that flows into the gas of the moving wing can be adjusted into best angle on moving wing short transverse.
Thus, can on the short transverse of the moving wing, the collision angle (incident angle) of the gas of wing ingress be become necessarily, avoid gas owing to the short transverse of the moving wing flow into relatively angle the inhomogeneous moving wing inlet that produces the collision loss and move the secondary flow loss increase of wing inside, can prevent the reduction of the efficiency of turbine that causes by such loss.
In addition, in the present invention, cut 10%～20% of height that length constitutes above-mentioned entrance face by the radial direction that the amount of cutting of cutting portion at above-mentioned entrance face place is as one man cut this fall portion with the formation width of above-mentioned three-dimensional boundary layer at least, the central part of having eliminated the moving wing inlet that influence produced that should the three-dimensional boundary layer is relative with the gas of two end part (covering ring side and hub side) to flow into the inhomogeneous of angle, the gas collision angle that can make wing ingress as described above in the short transverse of moving the wing necessarily.
More than, according to the present invention, can reduce the gas flow loss of the volute pipeline and the moving wing, can improve the efficient of turbine thus.
Claims (2)
1. the volute pipe configuration of a radial turbine, it is to use in the structure of the Structure of radial turbine scroll of radial turbine, it be by make start gas from be formed on Vorticose volute pipeline in the turbine cylinder flow into along radial direction the inboard be positioned at the volute pipeline turbine rotor the moving wing and act on this moving wing after flow out this turbine rotor of rotary driving vertically, it is characterized in that the stream cross-section area in positive downstream side of tongue that is formed in the gas access week is than the stream cross-section area of tongue end uvula portion thickness size (T) partly on width direction.
2. the volute pipe configuration of radial turbine as claimed in claim 1 is characterized in that, the width between the sidewall in the positive downstream side of above-mentioned tongue forms than the uvula portion thickness size (T) partly on width direction of the width between the sidewall of tongue end.
Applications Claiming Priority (4)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP321416/2001 | 2001-10-19 | ||
| JP2001321416A JP3534728B2 (en) | 2001-10-19 | 2001-10-19 | Scroll structure of radial turbine |
| JP2001376050A JP3534730B2 (en) | 2001-12-10 | 2001-12-10 | Rotor blade of radial turbine |
| JP376050/2001 | 2001-12-10 |
Related Parent Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CNB021472297A Division CN100447373C (en) | 2001-10-19 | 2002-10-18 | Turbine volute pipeline and moving blade structure |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN1920260A true CN1920260A (en) | 2007-02-28 |
| CN1920260B CN1920260B (en) | 2010-09-29 |
Family
ID=19138634
Family Applications (2)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN2006101108659A Expired - Lifetime CN1920260B (en) | 2001-10-19 | 2002-10-18 | Structure of radial turbine scroll and blades |
| CN2006101108663A Expired - Lifetime CN1920257B (en) | 2001-10-19 | 2002-10-18 | Structure of radial turbine scroll and blades |
Family Applications After (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN2006101108663A Expired - Lifetime CN1920257B (en) | 2001-10-19 | 2002-10-18 | Structure of radial turbine scroll and blades |
Country Status (2)
| Country | Link |
|---|---|
| JP (1) | JP3534728B2 (en) |
| CN (2) | CN1920260B (en) |
Families Citing this family (12)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP4468286B2 (en) | 2005-10-21 | 2010-05-26 | 三菱重工業株式会社 | Exhaust turbocharger |
| CN101960120B (en) | 2008-10-20 | 2013-03-06 | 三菱重工业株式会社 | Radial turbine scroll structure |
| JP5012915B2 (en) | 2010-01-15 | 2012-08-29 | トヨタ自動車株式会社 | Turbocharger and wheel housing thereof |
| JP5660878B2 (en) | 2010-12-20 | 2015-01-28 | 三菱重工業株式会社 | Scroll structure of radial turbine or mixed flow turbine |
| JP5433560B2 (en) * | 2010-12-27 | 2014-03-05 | 三菱重工業株式会社 | Turbine scroll part structure |
| WO2013080795A1 (en) | 2011-11-30 | 2013-06-06 | 三菱重工業株式会社 | Radial turbine |
| JP5964056B2 (en) | 2012-01-11 | 2016-08-03 | 三菱重工業株式会社 | Scroll structure of turbine housing |
| CN105392975B (en) * | 2013-07-05 | 2017-09-26 | 株式会社Ihi | Scroll structure and booster |
| JP5870083B2 (en) | 2013-12-27 | 2016-02-24 | 三菱重工業株式会社 | Turbine |
| US10364689B2 (en) | 2014-08-28 | 2019-07-30 | Mitsubishi Heavy Industries Engine & Turbocharger, Ltd. | Expansion turbine and turbocharger |
| JP6351049B2 (en) * | 2014-11-04 | 2018-07-04 | 三菱重工エンジン＆ターボチャージャ株式会社 | Turbine housing and method for manufacturing turbine housing |
| DE102017124467A1 (en) * | 2017-10-19 | 2019-04-25 | Abb Turbo Systems Ag | Diffuser arrangement of an exhaust gas turbine |
Family Cites Families (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3032315A (en) * | 1955-08-16 | 1962-05-01 | Laval Steam Turbine Co | Turbine blading |
| ES195737Y (en) * | 1970-05-02 | 1975-07-16 | A. G. Kuhnle Kopp & Kausch | AN EXHAUST GAS DRIVEN TURBOCHARGER DEVICE WILL BE USED IN CONNECTION WITH INTERNAL COMBUSTION ENGINES. |
-
2001
- 2001-10-19 JP JP2001321416A patent/JP3534728B2/en not_active Expired - Lifetime
-
2002
- 2002-10-18 CN CN2006101108659A patent/CN1920260B/en not_active Expired - Lifetime
- 2002-10-18 CN CN2006101108663A patent/CN1920257B/en not_active Expired - Lifetime
Also Published As
| Publication number | Publication date |
|---|---|
| JP3534728B2 (en) | 2004-06-07 |
| CN1920260B (en) | 2010-09-29 |
| JP2003120303A (en) | 2003-04-23 |
| CN1920257A (en) | 2007-02-28 |
| CN1920257B (en) | 2012-04-04 |
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