CN101223337B - Variable geometry turbine - Google Patents
Variable geometry turbine Download PDFInfo
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- CN101223337B CN101223337B CN2006800263388A CN200680026338A CN101223337B CN 101223337 B CN101223337 B CN 101223337B CN 2006800263388 A CN2006800263388 A CN 2006800263388A CN 200680026338 A CN200680026338 A CN 200680026338A CN 101223337 B CN101223337 B CN 101223337B
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- turbine
- hole
- circumferential
- hole array
- variable geometry
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T10/00—Road transport of goods or passengers
- Y02T10/10—Internal combustion engine [ICE] based vehicles
- Y02T10/12—Improving ICE efficiencies
Abstract
A variable geometry turbine comprises a turbine wheel (9) supported in a housing (1) for rotation about an axis. A nozzle ring (5) is moveably mounted within a cavity (19) provided within the housing for adjustment of the width of an annular inlet passageway (4) extending radially inwards towards the turbine wheel (9). An array of inlet guide vanes (8) extends between a radial face of the nozzle ring (5) and an opposing wall of the inlet (4) defining a radial vane passage. A first circumferential array of apertures (25) is provided through the radial face, each of which lies substantially within the vane passage. A second circumferential array of apertures (24) is also provided in said radial face, each of lies substantially upstream or downstream of the first array (25) of apertures. The inlet (4) and cavity (19) are in fluid communication via both the first and second sets of apertures (25, 24).
Description
Technical field
The present invention relates to a kind of variable geometry turbine, especially but be not used for the turbosupercharger of internal-combustion engine uniquely.
Background technique
Turbosupercharger is at the known device that is higher than inside burning machine inlet supply air under the atmospheric pressure (boosting).Conventional turbosupercharger comprises the exhaust gas driven turbine wheel on the running shaft that is arranged in the turbine shroud necessarily.The rotation of turbine wheel makes the compressor impeller rotation that is arranged in a other end and the compressor housing.Compressor impeller is carried pressurized air to engine air inlet tube.Usually by shaft bearing and thrust-bearing supporting, bearing comprises the proper lubrication system to turbo-charger shaft, in the centre bearing housing that is connected between turbine and the compressor impeller housing.
In known turbochargers, turbine comprises: the annular entry passage between the radial wall relatively wherein is installed around the turbine chamber, turbine chamber of turbine wheel, is arranged on the inlet around the inlet channel, and the outlet passage that extends from turbine chamber.Passage and chamber are communicated with as follows: the pressurised exhaust gas that enters entrance cavity flows through inlet channel and arrives outlet passage and rotary turbine impeller through turbine.Also known to the blade that is called nozzle vane is provided in inlet channel, with the gas that will flow through inlet channel towards the deflection of turbine wheel sense of rotation, thereby adjust turbine performance.
Turbine can be fixed geometry or variable type.The turbine of variable geometry and the turbine of fixed geometry difference part is: can change inlet channel size so that airspeed in the certain quality range of flow, optimize, thereby can change the engine demand of power output to be fit to change of turbine.For example, when the exhausted air quantity that is delivered to turbine more after a little while, the gas velocity that will arrive turbine wheel by the size that reduces the annular entry passage maintains the degree that guarantees effective turbine operation.
In a kind of variable geometry turbine of known type, the axially movable wall elements that is commonly referred to " nozzle ring " limits an inlet channel wall.Can adjust nozzle ring with respect to the position of inlet channel facing (facing) wall axial width with the control inlet channel.Therefore for example along with the gas minimizing of the turbine of flowing through, the inlet channel width also can reduce to keep gas velocity and to make turbine output best.Such nozzle ring comprises wall and the axially extended inside and outside annular flange that radially extends necessarily.Annular flange flange extends in the annular chamber that forms in turbine shroud, the part of the housing that described turbine shroud is provided by bearing housing as reality, and bearing housing allows the axial motion of nozzle ring.
Nozzle ring can have the blade that extends in the inlet channel and pass through the groove on the inlet channel facing wall, and described groove allows the motion of nozzle ring.Selectively, blade can extend from fixed wall by the groove that is provided with in the nozzle ring.Usually, nozzle ring is bearing on the rod that extends abreast with the turbine wheel running shaft, and the actuator that is moved axially described rod moves.Become known for the various actuators of the turbine that geometrical construction changes, comprise that to be arranged on turbosupercharger outside and be connected to pneumatic, the hydraulic pressure and the electric actuator of variable geometry system by suitable coupling mechanism.
When using conventional turbine, along with gas stream is crossed inlet channel, pressure is applied on the surface of nozzle ring, trends towards forcing nozzle ring to enter annular chamber.There is pressure in the annular chamber that is arranged in wherein at nozzle ring, and accurately controls the position of nozzle ring if desired, and then actuating mechanism must overcome this pressure influence.Make nozzle ring shift near passage facing wall and can increase the load that is applied to the nozzle ring surface further to reduce channel width and to improve air stream speed.Some turbine actuators for example electric actuator compare with pneumatic actuator can only provide relatively limited power with the moving nozzle ring.Under some operating conditionss, need may exceed the ability of actuator by the power that actuator applies.In addition, also expectation guarantees that be unidirectional making a concerted effort on the nozzle ring.
EP 0654587 discloses a kind of turbine of variable geometry, has the pressure compensation opening in the nozzle ring between the nozzle vane.By the power on pressure in the chamber behind the lip-deep pressure of nozzle ring, the nozzle ring and the actuator generation nozzle ring.The function of pressure compensation opening is to guarantee that the pressure in the chamber of nozzle ring back is substantially equal to but always is slightly smaller than the pressure that acts on the nozzle ring front surface to guarantee having little but unidirectional power on nozzle ring.
Turbine nozzle ring has the blade annular array of striding the turbine entrance extension usually.Therefore air Radial Flow between adjacent blades of flowing through and entering the mouth, described blade can be considered to limit blade path.The turbine inlet has the radial flow area that reduces on the blade path zone, produce following effect: inlet gas speed increases by blade path, and the corresponding pressure that is created on this nozzle ring zone descends.Therefore, between blade, this means that the inner of each equalizing orifice and/or outer end are arranged in the nozzle guide vanes passage or the outer radial scope as EP 0 654 587 described pressure compensation openings.
Even having been found that as described in EP 0 654 587 provides pressure compensation opening, because the on-off action by outlet valve is released into the exhaust pulses in the vehicle motor outlet pipe, the fluctuation unfriendly of the power on the nozzle ring along with the fluctuation of turbine inlet internal pressure.When the fluctuation of this power all can appear during with motor " startup " mode operation and with motor " braking " mode operation in turbosupercharger.For example, the fluctuation of power can cause the undesirable fluctuation of blocking-up moment of torsion that produced in braking mode.
Term " startup " pattern and " braking " pattern are well known to those skilled in the art.
Summary of the invention
Target of the present invention is to eliminate or alleviate above-mentioned defective.
Turbine according to the invention provides a kind of variable geometry comprises: be bearing in the turbine wheel that pivots in the housing; Be installed in the axially movable annular wall element in the chamber that is arranged in the described housing; Radially inwardly extend and be limited to annular entry passage between the relative wall of the radial surface of removable wall elements and housing towards turbine wheel; Described removable wall elements housing relatively moves axially to change the axial width of inlet channel; The inlet guide vane array that between described radial surface that limits the radial blade passage and relative wall, extends; By the first circumferential hole array of described radial surface, each described first hole array be located substantially on described radially pass through in; And the second circumferential hole array in described radial surface, each hole in the described second hole array is located substantially on the upstream or the downstream of the described first hole array with respect to the flow direction through inlet, thereby enters the mouth and the first and second groups of orifice flow bodies connections in described chamber.
Have been found that, when when providing the principal pressure equalizing orifice to compare separately, by principal pressure equalizing orifice and time pressure compensation opening are provided in nozzle ring, amplitude through power on the caused actuator of the exhaust pulses interface of turbine stage under braking condition can reduce to surpass 75%, can reduce to surpass 80% under starting condition.Therefore, the present invention can obtain low mean force on nozzle ring on certain engine speed range.
Description of drawings
To specific embodiment of the present invention be described with reference to the drawings by example now.
Fig. 1 is the axial cross-sectional view according to variable geometry turbine of the present invention;
Fig. 1 b is the cross-sectional view of the part of turbine among Fig. 1 a;
Fig. 1 c is the perspective view of Fig. 1 a and the shown nozzle ring of 1b;
Fig. 2 is second embodiment's the axial cross-sectional view of a part of the turbine of Fig. 1 a to 1c;
Fig. 3 is the axial cross-sectional view of the part of third embodiment of the invention;
Fig. 4 is the axial cross-sectional view of the part of fourth embodiment of the invention.
Embodiment
With reference to figure 1a, described variable geometry turbine comprises the turbine shroud 1 that limits entrance cavity 2, is admitted to entrance cavity 2 from the gas of internal-combustion engine (not shown).Waste gas flow to outlet passage 3 through ring-type inlet channel 4 from entrance cavity 2.One side of inlet channel 4 is limited by the face of the removable annular wall element 5 that is commonly referred to " nozzle ring ", and opposite side is limited by the circular cowling 6 of the opening that covers the annular recess 7 in the facing wall.
The gas that flow to outlet passage 3 from entrance cavity 2 is through turbine wheel 9, and therefore the turbo-charger shaft 10 to Driven Compressor impeller 11 applies moment of torsion.The rotation of compressor impeller 11 is pressurizeed to the ambient air that exists in the air inlet 12, and forced air is delivered to the internal-combustion engine (not shown) to the air outlet slit 13 that send forced air.The speed of turbine wheel 9 depends on the gas velocity through annular entry passage 4.For the fixed mass flow rate of the gas that flows into inlet channel, gas velocity is the function of inlet channel 4 width, and this width can be adjusted by the axial position of control nozzle ring 5.Along with the width of inlet channel 4 reduces, the gas velocity of the passage of flowing through increases.Fig. 1 a shows the ring-type inlet channel 4 that is closed to minimum width, and inlet channel 4 is depicted as fully and opens in accompanying drawing 1b.
Circumferential equidistant blade 8 arrays of nozzle ring 5 supportings, each blade extend past inlet channel 4.Blade 8 is oriented and will flows through the sense of rotation of the gas deflection of inlet channel 4 to turbine wheel 9.When nozzle ring 5 during near circular cowling and facing wall, blade 8 is outstanding and enter in recessed 7 by the groove that covers appropriate structuring in 6.
Shown in Fig. 1 c, nozzle ring 5 has first and second circumferential array of pressure compensation opening 24,25, and first group of pressure compensation opening 25 is arranged in the blade path between the adjacent blades 8.Second group of pressure compensation opening 24 is arranged on the outside of nozzle vane channel radius.
First and second pressure compensation openings 24,25 allow the ring-type inlet channel to be communicated with ring chamber 19 fluids, and ring chamber 19 is sealed from inlet channel 4 by seal ring 20 and 21 on the other hand.
Have been found that when with provide first group of pressure compensation opening 24 (being arranged in blade path) when comparing separately, by adding second group of pressure compensation opening 24, can reduce to surpass 80% through the amplitude of power on the caused actuator of the exhaust pulses interface of turbine stage.
Fig. 2 and 3 has described the of the present invention second and the 3rd embodiment.Similar with Fig. 1 a to 1c, the details in turbine nozzle ring/inlet channel zone has only been described.In suitable place, adopt the reference mark identical with 1b in 3 with Fig. 1 a at Fig. 2.Fig. 2 and 3 has described the of the present invention application only different on the one hand with 1b embodiment with Fig. 1 a.In the embodiment of Fig. 2, second pressure compensation opening 24 is provided on the outward flange 18 of nozzle ring 5, and in the embodiments of figure 3, radially inwardly provides second pressure compensation opening 24 on the position in nozzle ring 5 top nozzle vane passage vanes 8.
To understand to provide the second pressure compensation opening array 24 in other radial position.For example, second pressure compensation opening of first group of pressure balance apertures upstream can be positioned at blade path to small part, and for example the part of each second pressure compensation opening can be positioned at blade path.Similarly, as shown in Figure 2, provide under the situation of second group of pressure compensation opening in the first pressure compensation opening array downstream, second pressure compensation opening can all or part ofly be positioned at the blade path outside relative with blade path.For example, each second pressure compensation opening can all be positioned at blade path.
In some embodiments of the invention, between the radial extension of the first pressure compensation opening radial extension and second pressure compensation opening, may exist overlapping.For example each in the second pressure compensation opening array of first pressure balance apertures upstream radially the radius on interior edge less than the radially outer of each first pressure compensation opening.Similarly, provide under the situation of the second pressure compensation opening array in the first pressure compensation opening downstream, the radially outer radius of each pressure compensation opening is all greater than inside edge, the footpath of each first pressure compensation opening.
Should be appreciated that second pressure compensation opening 24 can be arranged in blade path inside or outside or be positioned at collar flange or outer annular flange.
Fig. 4 shows the fourth embodiment of the present invention.With Fig. 1,2 similar, the details in turbine nozzle ring/inlet channel zone has only been described with 3.In suitable place, in Fig. 4, adopt the reference mark identical with earlier drawings.Fig. 4 has described and Fig. 1 a and only application of the present invention that importance is different of 1b embodiment: provide bypass as EP 1435434 (it incorporates this paper especially by reference into) is disclosed.
EP 1435434 disclosed turbines have by the circumferential hole of the bypass nozzle ring that array is out of shape is provided.Bypass opening is positioned so that except when nozzle ring during near the closing position that adopted in the engine braking pattern (this moment, the hole was by sealing), and bypass opening is positioned at nozzle ring sealing configuration one side away from the turbine inlet channel.Opened bypass path like this, allowed some waste gas through the chamber of nozzle ring back but not flow to turbine wheel from entrance cavity by inlet channel.Special because not deflection of blade gas is so the exhaust flow of walking around inlet channel and nozzle vane is with to compare role by the waste gas of inlet channel little.In other words, in case bypass opening is communicated with inlet channel, the efficient of turbosupercharger descends immediately, and compressor effluent pressure (boosting) correspondingly descends, and follows engine cylinder pressure to descend.
Therefore, the efficient of the 26 pairs of turbosupercharger of bypass opening that provide access under the conventional operation situation is influence not, but when turbine moves under the engine braking pattern and inlet channel is reduced to hour, bypass opening will promote inlet channel 4 axial widths to reduce, and cylinder excessively not pressurizeed.Should be appreciated that and to pre-determine the influence that turbocharger efficiency is descended by quantity, the size and dimension of suitable selection bypass opening 26.
Refer again to Fig. 4,, except principal pressure equalizing orifice and time pressure compensation opening 24, on nozzle ring 5 inward flanges 17, provide bypass opening 26 according to the present invention according to the instruction of EP 1435434.
In this embodiment, form bypass channel by bypass opening 26 in conjunction with pressure compensation opening 24 and 25.This is an ad hoc proposal that proposes among the EP 1435434, although in this case, only provides single group bypass opening in blade path, and the present invention can make up with other embodiment of disclosed invention among the EP 1435434.In other words, if pressure compensation opening list array can be provided all can use " two " array Anywhere according to pressure compensation opening of the present invention.
First and second groups of holes can have substantially the same size and dimension, and perhaps it can have different basically sizes and/or shape.Usually, in second group, preferably have the hole of lacking than in first group, and the hole in second group is less than the hole in first group.
In certain embodiments, first group of hole can all be arranged in blade path, but the part in each first group of hole can radially inwardly or outwards be positioned at outside the blade path in other embodiments.Similarly, second group of hole all is positioned at the blade path outside in certain embodiments, but in other embodiments, it can be positioned at the blade path in upstream, first group of hole or downstream to small part.For example, possible is, for direction radially, first group of hole can radially overlapping second group of hole among some embodiments.The hole can have different shape and as described embodiment like that for circular.
Claims (16)
1. the turbine of a variable geometry comprises: be bearing in the turbine wheel that pivots in the housing; Be installed in the axially movable annular wall element in the chamber that is arranged in the described housing; The annular entry passage, it extends radially inwardly towards turbine wheel, and be limited between the relative wall of the radial surface of removable wall elements and housing, described removable wall elements can move axially with respect to described housing, to change the axial width of described inlet channel; The inlet guide vane array that between described radial surface that limits the radial blade passage and relative wall, extends; Pass the first circumferential hole array that described radial surface is provided with, each hole in the described first circumferential hole array is located substantially in the described blade path; And the second circumferential hole array that passes described radial surface setting, each hole in the described second circumferential hole array is located substantially on the upstream or the downstream in the hole in the described first circumferential hole array with respect to the flow direction through inlet, makes orifice flow body connection in described inlet and the described chamber first circumferential hole array and the second circumferential hole array.
2. the turbine of variable geometry as claimed in claim 1, wherein removable wall elements can opened fully and move between the operating position fully, wherein for opening fully and complete all axial positions of the removable wall elements between the operating position, the hole in the first circumferential hole array and the second circumferential hole array is communicated with described inlet and described chamber fluid.
3. as the turbine of claim 1 or the described variable geometry of claim 2, wherein each hole in the first circumferential hole array is around first radius, and each hole in the described second circumferential hole array is around second radius, and wherein second radius is greater than first radius.
4. the turbine of variable geometry as claimed in claim 3, wherein said second radius is greater than the radius at the radially outer edge of described blade.
5. as the turbine of claim 1 or the described variable geometry of claim 2, wherein each hole in the first circumferential hole array is around first radius, and each hole in the described second circumferential hole array is around second radius, and wherein second radius is less than first radius.
6. the turbine of variable geometry as claimed in claim 5, wherein said second radius is less than the radius of described blade radial internal edge.
7. the turbine of each the described variable geometry in the claim 1,2,4 and 6 as described above, the Zone Full in each hole of the wherein said first circumferential hole array is positioned at blade path.
8. the turbine of each the described variable geometry in the claim 1,2,4 and 6 as described above, wherein each hole of the second circumferential hole array is located substantially on outside the described blade path at least.
9. the turbine of each the described variable geometry in the claim 1,2,4 and 6 as described above, wherein the Zone Full in each hole in the second circumferential hole array is positioned at the blade path outside.
10. the turbine of variable geometry as claimed in claim 5, wherein each hole in the second circumferential hole array is located substantially in the described blade path at least.
11. the turbine of variable geometry as claimed in claim 10, wherein each hole in the second circumferential hole array all is positioned at described blade path inside.
12. the turbine of each the described variable geometry in the claim 1,2,4 and 6 as described above, the area in each hole of the wherein said second circumferential hole array is less than the area in each hole in the described first circumferential hole array.
13. the turbine of variable geometry as claimed in claim 12, wherein said hole are circular, and in the second circumferential hole array diameter in each hole less than about 70% of the diameter in the hole in the first circumferential hole array.
14. the turbine of each the described variable geometry in the claim 1,2,4,6,10,11 and 13 as described above, wherein the radial extension in the hole of the radial extension in the hole of the second circumferential hole array and the first circumferential hole array is overlapping.
15. the turbine of each the described variable geometry in the claim 1,2,4,6,10,11 and 13 as described above wherein has in the described second circumferential hole array than still less hole in the described first circumferential hole array.
16. the turbine of variable geometry as claimed in claim 15, the wherein hole about less 50% in the second circumferential hole array of the boring ratio in the first circumferential hole array.
Applications Claiming Priority (5)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| GB0511613.2 | 2005-06-07 | ||
| GBGB0511613.2A GB0511613D0 (en) | 2005-06-07 | 2005-06-07 | Variable geometry turbine |
| GB0514465.4 | 2005-07-14 | ||
| GBGB0514465.4A GB0514465D0 (en) | 2005-06-07 | 2005-07-14 | Variable geometry turbine |
| PCT/GB2006/002069 WO2006131724A1 (en) | 2005-06-07 | 2006-06-06 | Variable geometry turbine |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN101223337A CN101223337A (en) | 2008-07-16 |
| CN101223337B true CN101223337B (en) | 2011-10-19 |
Family
ID=34835280
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN2006800263388A Active CN101223337B (en) | 2005-06-07 | 2006-06-06 | Variable geometry turbine |
Country Status (3)
| Country | Link |
|---|---|
| JP (1) | JP4885949B2 (en) |
| CN (1) | CN101223337B (en) |
| GB (2) | GB0511613D0 (en) |
Families Citing this family (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB2462115A (en) * | 2008-07-25 | 2010-01-27 | Cummins Turbo Tech Ltd | Variable geometry turbine |
| GB0822474D0 (en) * | 2008-12-10 | 2009-01-14 | Cummins Turbo Tech Ltd | Variable geometry turbine nozzle ring |
| CN102269018A (en) * | 2011-08-23 | 2011-12-07 | 常州环能涡轮动力有限公司 | Nozzle component of variable-section supercharger |
| DE102013006928A1 (en) * | 2013-04-22 | 2014-10-23 | Volkswagen Aktiengesellschaft | turbocharger |
| GB2571356A (en) * | 2018-02-27 | 2019-08-28 | Cummins Ltd | Variable geometry turbine |
Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP0654587A1 (en) * | 1993-11-19 | 1995-05-24 | Holset Engineering Company Limited | Turbine with variable inlet geometry |
| US6203272B1 (en) * | 1996-10-03 | 2001-03-20 | Holset Engineering Company, Ltd. | Variable geometry turbine |
| EP1435434A2 (en) * | 2002-11-19 | 2004-07-07 | Holset Engineering Company Limited | Variable geometry turbine |
Family Cites Families (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPH0610403B2 (en) * | 1984-02-22 | 1994-02-09 | 日産自動車株式会社 | Variable nozzle of Radiator bottle |
-
2005
- 2005-06-07 GB GBGB0511613.2A patent/GB0511613D0/en not_active Ceased
- 2005-07-14 GB GBGB0514465.4A patent/GB0514465D0/en not_active Ceased
-
2006
- 2006-06-06 JP JP2008515281A patent/JP4885949B2/en active Active
- 2006-06-06 CN CN2006800263388A patent/CN101223337B/en active Active
Patent Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP0654587A1 (en) * | 1993-11-19 | 1995-05-24 | Holset Engineering Company Limited | Turbine with variable inlet geometry |
| US6203272B1 (en) * | 1996-10-03 | 2001-03-20 | Holset Engineering Company, Ltd. | Variable geometry turbine |
| EP1435434A2 (en) * | 2002-11-19 | 2004-07-07 | Holset Engineering Company Limited | Variable geometry turbine |
Non-Patent Citations (1)
| Title |
|---|
| JP昭60-175707A 1985.09.09 |
Also Published As
| Publication number | Publication date |
|---|---|
| GB0511613D0 (en) | 2005-07-13 |
| GB0514465D0 (en) | 2005-08-17 |
| JP2008546939A (en) | 2008-12-25 |
| JP4885949B2 (en) | 2012-02-29 |
| CN101223337A (en) | 2008-07-16 |
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Effective date of registration: 20180321 Address after: Huddersfield Patentee after: Cummins Ltd Address before: Huddersfield, England Patentee before: Cummins Turbo Technologies Ltd. |
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