CN101910565B - Guide vane for a variable turbine geometry - Google Patents
Guide vane for a variable turbine geometry Download PDFInfo
- Publication number
- CN101910565B CN101910565B CN200880124892.9A CN200880124892A CN101910565B CN 101910565 B CN101910565 B CN 101910565B CN 200880124892 A CN200880124892 A CN 200880124892A CN 101910565 B CN101910565 B CN 101910565B
- Authority
- CN
- China
- Prior art keywords
- section
- guide vane
- line
- curvature
- region
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Active
Links
Images
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D17/00—Regulating or controlling by varying flow
- F01D17/10—Final actuators
- F01D17/12—Final actuators arranged in stator parts
- F01D17/14—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits
- F01D17/16—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits by means of nozzle vanes
- F01D17/165—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits by means of nozzle vanes for radial flow, i.e. the vanes turning around axes which are essentially parallel to the rotor centre line
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D17/00—Regulating or controlling by varying flow
- F01D17/10—Final actuators
- F01D17/12—Final actuators arranged in stator parts
- F01D17/14—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits
- F01D17/16—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits by means of nozzle vanes
- F01D17/162—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits by means of nozzle vanes for axial flow, i.e. the vanes turning around axes which are essentially perpendicular to the rotor centre line
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/12—Blades
- F01D5/14—Form or construction
- F01D5/141—Shape, i.e. outer, aerodynamic form
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D9/00—Stators
- F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
- F01D9/026—Scrolls for radial machines or engines
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2220/00—Application
- F05D2220/40—Application in turbochargers
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2250/00—Geometry
- F05D2250/70—Shape
- F05D2250/71—Shape curved
- F05D2250/713—Shape curved inflexed
Abstract
The invention relates to a guide vane (10), particularly for a turbo charger, wherein the curvature line (12) of the guide vane (10) has at least one or more regions (b1, b2, b3) having a discontinuous course.
Description
Technical field
The present invention relates to a kind of guide vane (Leitschaufel) of the variable turbine geometry for turbosupercharger.
Background technique
Turbosupercharger is made up of the exhaust gas turbine in waste gas streams conventionally, and this exhaust gas turbine is connected with the compressor in aspirating air pipe by axle.At this, turbine is placed in rotation and drive compression machine thus by the waste gas streams of motor.At this, improve the pressure in the aspirating air pipe of motor by compressor, thereby arrive in cylinder than more substantial air in naturally aspirated engine during suction stroke.Provide in this way more oxygen for the corresponding more substantial fuel of burning.
In common turbosupercharger, if need to limit in the following manner boost pressure, that is, utilize outlet valve or bypass or wastegate (Wastegate) to make the partly other power that also reduces thus turbine through turbine of hot waste gas.For this reason, turbine design is obtained so large, that is, it is worked below well far away from the rated operation point of motor.
By also known such turbosupercharger of prior art, that is, it is provided with variable turbine geometry VTG, for making power stage (Leistungsangabe) and response characteristic can better be matched with different operating conditionss, as load variations.In order to realize this point, make adjustable, non-rotary guide vane be arranged in turbine inlet or turbine case.At this, in the guide blade position of sealing, the large circumferential component of flow velocity and high enthalpy drop cause large turbine power and cause thus high boost pressure.In the completely unlimited position of guide vane, in the case of the large centripetal component of flowing velocity vector, infer again maximum turbine throughput.Advantage compared with this power adjustments and bypass regulate is, always all waste gas streams are guided through turbine and for power transfer.
For variable turbine geometry, the shape of blade profile is the major influence factors about thermodynamic efficiency, control characteristic and essential radial structure space.
In the prior art, there is difformity for the profile of adjusting blade (Verstellschaufel).General being suitable for, the optimization of joint efficiency, control characteristic and as far as possible little standard pitch circle (Teilkreis) (structure space) aspect.Generally by the line of curvature (Kr ü mmungslinie) extending between top radius (Kopfradius) mid point at adjustment blade and end radius (Endradius) mid point, shape is described.By the tangent circle of hypothesis in profile and upside and bottom side, produce this line of curvature.At this, the connecting line of circle central point is described this line of curvature.
At this, there is pure straight, scheme bending or that combined by two kinds of possibilities.All these scheme common ground are, the line of curvature has continuous trend (Verlauf), that is, each curvature line segment is transition mutually all tangently.In other words, the line of curvature does not have flex point.
Summary of the invention
Therefore, the object of the invention is, for improved guide vane geometrical shape is provided with the turbosupercharger of variable turbine geometry.
This object is by being achieved with the guide vane of claim 1 feature.
Therefore,, according to the invention provides a kind of guide vane that is particularly useful for turbosupercharger, wherein, the line of curvature of this guide vane has at least one or more region with discontinuous trend.
Guide vane is at flow profile
design proposal aspect especially favourable.At this, can in the situation that not changing control characteristic and structure space demand, improve efficiency.
By obtaining favourable design proposal of the present invention and improvement project in dependent claims and the description by means of accompanying drawing.
According to form of implementation of the present invention, the line of curvature has at least one region with two sections, and these two sections interconnect, and wherein, these two sections are transition mutually discontinuous or not tangently at its tie point place.In other words, section is in its tie point place structure flex point.This advantage having is, this design by guide vane, for example under variable turbine geometry, can improve the efficiency of turbosupercharger.
Another according to form of implementation of the present invention in, except at least one between two sections with flex point or the region with nontangential transition, the line of curvature of guide vane also has at least one such region,, two of this region sections at its tie point place continuously or the transition mutually of tangent ground.In this way, according to realizing which kind of flow profile, can make the line of curvature of guide vane arbitrarily compatibly to change with the discontinuous region stretching continuously.
According to another, according to form of implementation of the present invention, at least one of the line of curvature, multiple or all sections are being for example consistent or different aspect its shape, position and/or size.Correspondingly also be applicable to the region of the line of curvature forming by these sections.Therefore, can realize the most different structure shape of guide vane, it all has at least one and has the region of discontinuous trend.
Another according to form of implementation of the present invention in, guide vane is for example made up of four sections, wherein, the first and second sections form with the first area of continuous trend.Second area forms by the second section and the 3rd section, wherein, second and the 3rd section in the discontinuous mutual transition in its tie point place or form flex point.The 3rd region being formed by the 3rd section and the 4th section has again continuous trend.This guide vane represents such example, that is, therein, the line of curvature has flex point.At this, first or the section in the 3rd region for example two all overarch up or down
or wherein at least one overarches up or down.
Another according to form of implementation of the present invention in, composition the line of curvature section can be configured to for example arc or straight.At this, these sections can overarch up or down, or when these sections are while being straight, and it for example flatly, vertically or be tilted to or be tilted to lower sensing.At this, section can at random combine mutually, and wherein, at least one region forming by section has discrete trend.Can realize multiple flow profile according to desired function or desired application target in this way.
Brief description of the drawings
Explain in detail the present invention by means of the embodiment who illustrates below in the illustrative diagram of accompanying drawing.Wherein:
Fig. 1 has shown the first form of implementation according to the guide vane of prior art;
Fig. 2 has shown the second form of implementation according to the guide vane of prior art;
Fig. 3 has shown the 3rd form of implementation according to the guide vane of prior art;
Fig. 4 has shown the first form of implementation according to guide vane of the present invention; And
Fig. 5 has shown the second form of implementation according to guide vane of the present invention.
In the case of not having contrary explanation, identical in the drawings reference number represents member identical or that function is identical.
Embodiment
In Fig. 1, show the first form of implementation according to the guide vane of prior art 10.At this, show guide vane 10 with line chart, wherein, line chart has x axle and y axle.This diagram is applicable to all guide vanes 10, at Fig. 1 to 5 as shown in.
As described above, the shape of guide vane 10 is generally described by the line of curvature 12, and this line of curvature 12 extends between the top of guide vane 10 radius centre point 14 and end radius centre point 16.This line of curvature 12 produces in the following manner, that is, and and at the tangent circle in the inner hypothesis of the profile of blade 10 and top side and bottom side 18,20.At this, the connecting line of circle central point is described the line of curvature 12.
Under present case, as shown in Figure 1, stretch to the line of curvature 12 waveforms.At this, the line of curvature 12 is made up of four section a1 to a4.At this, form the first and second section a1 of first area b1, a2 is configured to respectively upwards overarch in the mode of arc, wherein, and two section a1 of the line of curvature 12, a2 is the transition mutually of tangent ground at its tie point 22 places.At this, region b1 forms the continuous trend that there is no flex point.In addition, the 3rd section a3 is configured to arc equally, wherein, the 3rd section a3 and the first and second section a1, a2 overarches downwards on the contrary.Second and the 3rd section a2, a3 is in its tie point same tangent ground transition mutually in 22 places, thereby by second and the 3rd section a2, the second area b2 that a3 forms has continuous trend.Correspondingly also be applicable to the 3rd region b3.The 3rd region b3 is formed by the 3rd section a3 and the 4th section a4, wherein, two section a3, a4 is configured to arc and overarches downwards.Two section a3 of the line of curvature 12, a4 is the transition mutually of tangent ground at its tie point 22 places, that is and, region b3 has continuous trend, and at two section a3, there is not flex point in transition 22 places of a4.In the line chart of all three region b1 to b3 in Fig. 1, more than x axle, stretch, in addition, first area b1 is obviously longer and more strongly overarch than the 3rd region b3.
According to the second form of implementation of the guide vane of prior art 10, as shown in Figure 2, the line of curvature 12 is made up of four section a1 to a4 equally.At this, the line of curvature 12 stretches more than x axle, and at this, first the line of curvature 12 rose upward before the slow decreasing of the other end at it in camber line.
At this, the first section a1 of the line of curvature 12 overarch downwards in the mode of arc and immediately its section a2 upwards overarch in the mode of arc.Two section a1 and a2 be the transition mutually of tangent ground at its tie point 22 places, thereby makes by the first and second section a1, and the first area b1 that a2 forms has continuous trend.The second area b2 being made up of the second section a2 and the 3rd section a3 has continuous trend equally.Therefore, the 3rd section a3 upwards overarches in the mode of arc equally, and wherein, the 3rd section a3 and the second section a2 be the transition mutually of tangent ground at its tie point 22 places, and does not have flex point at this.The 3rd region b3 of the line of curvature 12 is formed by the 3rd section a3 and the 4th section a4.At this, the 4th section a4 overarches downwards in the mode of arc, wherein, the third and fourth section a3, a4 is the transition mutually of tangent ground at its tie point 22 places.
In addition in Fig. 3, show according to the 3rd form of implementation of the guide vane of prior art.At this, this guide vane 10 is made up of four section a1 to a4 with the same in the first and second forms of implementation.At this, first the line of curvature 12 stretches with waveform in camber line more than x axle, then in camber line at x axle with downward-extension.
The first and second section a1 of the line of curvature 12, a2 is configured to arc and stretches in the mode upwards overarching.The first and second two section a1, a2 is the transition mutually of tangent ground at its tie point 22 places.The second area b2 of the line of curvature 12 forms by the second section a2 and the 3rd section a3.The 3rd section a3 is configured to equally arc and overarches downwards.At this, two section a2 and a3 be the transition mutually of tangent ground at its tie point 22 places, thereby in this region, does not have sharp keen (scharf) flex point.In addition, the 3rd region b3 forms by the 3rd section a3 and the 4th section a4.The 4th section a4 overarches downwards in the mode of arc equally.The third and fourth section a3, a4 is the transition mutually of tangent ground at its tie point 22 places.Thus, make region b1 to b3 or the line of curvature 12 there is generally continuous trend, as another two described above according to the form of implementation of the guide vane of prior art 10.
Now, in Fig. 4, shown the first form of implementation according to guide vane 10 of the present invention.At this, guide vane 10 is for example made up of four section a1 to a4.At this, by the first and second section a1, the first area of a2 composition has continuous trend.At this, the first and second section a1, a2 is configured to arc and upwards overarches.At this, the first section a1 its jointing or its tie point 22 places tangent be transitioned in the second section a2, there is no the continuous trend of flex point thereby produce.Second area b2 forms by the second section a2 and the 3rd section a3, wherein, second and the 3rd section a2, a3 is configured to respectively arc and upwards overarches.But, be not the transition mutually of tangent ground at its tie point 22 places at this section a2 and a3, but form flex point 24.For this reason, second area b2 forms continuous trend, but forms discrete trend in other words at two section a2, and tie point 22 places of a3 have sharp keen flex point 24.The 3rd region b3 is made up of the 3rd section a3 and the 4th section a4, and forms continuous trend at this.At this, the 4th section a4 is configured to arc and upwards overarches.The third and fourth section a3, a4 is the transition mutually of tangent ground at its tie point 22 places.This means, in this example, guide vane 10 has the region b2 moving towards with discrete line of curvature 12, therein, second and the 3rd section a2, a3 forms the transition mutually not tangently in other words of a kind of flex point 24 at its tie point 22 places.On the contrary, other region b1 and b3 have the trend of the continuous line of curvature 12, and neither one is constructed flex point in these these regions.
Under present case, the line of curvature 12 forms two camber lines, a camber line upwards overarching being formed by section a1 and a2, and another is the camber line overarching in contrast, be made up of section a3 and a4 very flatly.Two camber lines form flex point 24 at its tie point 22 places.
In addition, shown in Figure 5 according to the second form of implementation of guide vane 10 of the present invention.At this, the line of curvature 12 of this guide vane 10 is made up of four section a1 to a4.The first and second section a1, a2 is configured to arc and upwards overarches.The first and second section a1, a2 is the transition mutually of tangent ground at its tie point 22 places, thereby makes by two section a1, and the region b1 that a2 forms has continuous trend.Second area b2 is formed by the second section a2 and the 3rd section a3, and wherein, the 3rd section a3 equally upwards overarches.But, two section a2, a3 is not the transition mutually of tangent ground at its tie point 22 places, but forms a kind of flex point 24, shown in Fig. 5.Thus, second area b2 has discrete trend.The 3rd region b3 being formed by the 3rd section a3 and the 4th section a4 has again continuous trend.At this, the third and fourth two section a3, a4 is configured to arc and upwards overarches.They are the transition mutually of tangent ground at its tie point 22 places.Thus, at least in the b2 of region, there is discrete trend according to the line of curvature of guide vane 10 of the present invention 12, and another two region b1 and b3 has continuous trend, do not form flex point.Different from the first form of implementation of the present invention, first area b1 in the second form of implementation of the present invention (camber line of (gespannt) being opened with a2 by section a1 in other words) is configured to longer.For this reason, the 3rd region b3 opened with a4 by section a3 in other words camber line in the second form of implementation than shorter in the first form of implementation.
Although described the present invention by means of two preferred embodiments above, the present invention is not limited to this, but can mode miscellaneous retrofit.Especially also can imagine, according to the example flow profile of each guide vane as desired, replace the section of arc also will mutually to combine with the section of for example straight shape (not shown) and/or combine with the section of arc.In addition, guide vane can have at least one region being made up of two sections or multiple region or section, for example two, three, four, five, six and more region or section.At this, can make mutually to combine with the section of arbitrary shape, layout and/or size.Correspondingly also be applicable to the region being formed by these sections.Two according to form of implementation of the present invention in, in Figure 4 and 5 as shown in, more than region b1 to b3 is arranged in respectively the x axle in line chart substantially.The region of the line of curvature 12 or section can at random stretch in principle, for example, at least in part below x axle, as for example shown with reference to prior art in Fig. 3.Alternatively, the region of the line of curvature 12 or section also can stretch completely below x axle or partly on x axle.In addition, the straight section with arc can at random change in the line of curvature 12 of guide vane 10.At this, guide vane 10 can have at least one flex point 24 or multiple flex point 24 such point in other words in principle, that is, at these some places, each curved section of the line of curvature 12 is not the transition mutually of tangent ground.For example, the line of curvature 12 can have, two, three, four and multiple of these so-called flex point nontangential transition in other words, and wherein, flex point 24 can be arranged on according to function or application target any position of the line of curvature 12.
Claims (5)
1. the guide vane of the variable turbine geometry of turbosupercharger (10), wherein, described guide vane is constructed all-in-one-piece and is had a kind of profile, this profile has top side and bottom side, wherein, the line of curvature (12) of described guide vane (10) has been described in the profile of described guide vane the connecting line with the round central point of the tangent circle in top side and bottom side, wherein, the line of curvature (12) of described guide vane (10) extends between the central point of the top radius of described guide vane (10) and the central point of end radius, wherein said guide vane (10) is by four section (a1, a2, a3, a4) composition, wherein, the first section (a1) and the second section (a2) form first area (b1) and the 3rd section (a3) and the 4th section (a4) and form the 3rd region (b3), wherein, two section (a1 of described first area, a2) the line of curvature (12) and two section (a3 in described the 3rd region, a4) the line of curvature (12) is located transition mutually continuously at its tie point (22) respectively, wherein, the second area (b2) of described guide vane (10) forms by the second section (a2) and the 3rd section (a3), wherein, second and the 3rd section (a2, a3) be connected to each other and locate discontinuous mutual transition and form flex point (24) at its tie point (22).
2. guide vane according to claim 1, is characterized in that, the line of curvature (12) of described first area and the line of curvature (12) in described the 3rd region overarch in the same way up or down.
3. guide vane according to claim 2, it is characterized in that, described second and the 3rd section (a2, a3) locate to form the flex point (24) of the arch trend that is in reverse to described first area and the 3rd region at its tie point (22).
4. with a turbosupercharger for variable turbine geometry, wherein, described variable turbine geometry has multiple according to the guide vane described in any one in claims 1 to 3 (10).
5. turbosupercharger according to claim 4, is characterized in that, multiple or all guide vanes (10) of described variable turbine geometry are of similar shape.
Applications Claiming Priority (3)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| DE102008004014.2 | 2008-01-11 | ||
| DE102008004014A DE102008004014A1 (en) | 2008-01-11 | 2008-01-11 | Guide vane for a variable turbine geometry |
| PCT/EP2008/064594 WO2009086959A1 (en) | 2008-01-11 | 2008-10-28 | Guide vane for a variable turbine geometry |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN101910565A CN101910565A (en) | 2010-12-08 |
| CN101910565B true CN101910565B (en) | 2014-06-11 |
Family
ID=40193669
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN200880124892.9A Active CN101910565B (en) | 2008-01-11 | 2008-10-28 | Guide vane for a variable turbine geometry |
Country Status (7)
| Country | Link |
|---|---|
| US (1) | US20100296924A1 (en) |
| EP (1) | EP2245275B1 (en) |
| JP (2) | JP2011509371A (en) |
| KR (1) | KR20100110867A (en) |
| CN (1) | CN101910565B (en) |
| DE (1) | DE102008004014A1 (en) |
| WO (1) | WO2009086959A1 (en) |
Families Citing this family (15)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE102009057987B4 (en) * | 2009-12-11 | 2020-08-20 | BMTS Technology GmbH & Co. KG | Loading device and guide vane for such a loading device |
| US8834104B2 (en) | 2010-06-25 | 2014-09-16 | Honeywell International Inc. | Vanes for directing exhaust to a turbine wheel |
| US10072513B2 (en) | 2011-11-30 | 2018-09-11 | Mitsubishi Heavy Industries, Ltd. | Radial turbine |
| JP5964081B2 (en) * | 2012-02-29 | 2016-08-03 | 三菱重工業株式会社 | Variable capacity turbocharger |
| FR2991373B1 (en) * | 2012-05-31 | 2014-06-20 | Snecma | BLOWER DAWN FOR AIRBORNE AIRCRAFT WITH CAMBRE PROFILE IN FOOT SECTIONS |
| US9790796B2 (en) * | 2013-09-19 | 2017-10-17 | General Electric Company | Systems and methods for modifying a pressure side on an airfoil about a trailing edge |
| DE102013224572A1 (en) * | 2013-11-29 | 2015-06-03 | Bosch Mahle Turbo Systems Gmbh & Co. Kg | Exhaust gas turbocharger, in particular for a motor vehicle |
| DE102013225642B4 (en) * | 2013-12-11 | 2020-09-17 | Vitesco Technologies GmbH | Exhaust gas turbocharger with an adjustable guide grille |
| US10240469B2 (en) * | 2014-03-04 | 2019-03-26 | Borgwarner Inc. | Cast turbocharger turbine housing having guide vanes |
| DE102014221362A1 (en) | 2014-10-21 | 2016-04-21 | Siemens Aktiengesellschaft | Profiling of vanes of nozzles in turbomachinery, in particular compressors |
| DE102015205208A1 (en) * | 2015-03-23 | 2016-09-29 | Bosch Mahle Turbo Systems Gmbh & Co. Kg | Charging device with variable turbine geometry |
| US11041505B2 (en) | 2016-03-31 | 2021-06-22 | Mitsubishi Heavy Industries Engine & Turbocharger, Ltd. | Rotary machine blade, supercharger, and method for forming flow field of same |
| US10935041B2 (en) | 2016-06-29 | 2021-03-02 | Rolls-Royce Corporation | Pressure recovery axial-compressor blading |
| US10774650B2 (en) * | 2017-10-12 | 2020-09-15 | Raytheon Technologies Corporation | Gas turbine engine airfoil |
| CN112154260B (en) * | 2018-12-19 | 2022-10-14 | 三菱重工发动机和增压器株式会社 | Nozzle vane |
Family Cites Families (19)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE522531C (en) * | 1929-01-12 | 1931-04-10 | Bbc Brown Boveri & Cie | Method for adapting the free passage cross-section of adjustably inserted guide vanes of turbines, in particular exhaust gas turbines |
| DE1096536B (en) * | 1953-08-17 | 1961-01-05 | Rheinische Maschinen Und App G | Centrifugal compressor, from the impeller of which the conveying medium enters a guide device concentrically surrounding the impeller at supersonic speed |
| CH351065A (en) * | 1957-02-21 | 1960-12-31 | Ingenieurbureau W Hausammann & | Impeller for turbo machines, especially axial compressors |
| EP0056569A1 (en) * | 1981-01-21 | 1982-07-28 | ATELIERS DE CONSTRUCTIONS ELECTRIQUES DE CHARLEROI (ACEC) Société Anonyme | Turbine with variable inlet section |
| JPH01227823A (en) * | 1988-03-08 | 1989-09-12 | Honda Motor Co Ltd | Variable nozzle structure of turbine |
| DE4220960A1 (en) * | 1992-06-25 | 1994-01-05 | Turbowerke Meisen Ventilatoren | Blades for axial and radial flow machines - use series of segments and connecting elements to create variable flow contour |
| DE4238550A1 (en) * | 1992-11-14 | 1994-05-19 | Daimler Benz Ag | Exhaust gas turbocharger for an internal combustion engine |
| FR2714109B1 (en) * | 1993-12-22 | 1996-01-19 | Snecma | Variable camber turbomachine blade. |
| EP0916812B1 (en) * | 1997-11-17 | 2003-03-05 | ALSTOM (Switzerland) Ltd | Final stage for an axial turbine |
| JP2000087899A (en) * | 1998-09-14 | 2000-03-28 | Ishikawajima Harima Heavy Ind Co Ltd | Noise reducing device for inlet guide vane device |
| JP3605398B2 (en) * | 2002-02-26 | 2004-12-22 | 三菱重工業株式会社 | Variable capacity turbocharger |
| US6709232B1 (en) * | 2002-09-05 | 2004-03-23 | Honeywell International Inc. | Cambered vane for use in turbochargers |
| DE10255389A1 (en) * | 2002-11-28 | 2004-06-09 | Alstom Technology Ltd | Low pressure steam turbine has multi-channel diffuser with inner and outer diffuser rings to take blade outflow out of it |
| CN100400798C (en) * | 2003-12-31 | 2008-07-09 | 洪尼维尔国际公司 | Curved face vane for turbocharger |
| US8109715B2 (en) * | 2004-11-16 | 2012-02-07 | Honeywell International, Inc. | Variable nozzle turbocharger |
| US7510371B2 (en) * | 2005-06-06 | 2009-03-31 | General Electric Company | Forward tilted turbine nozzle |
| EP1904730B1 (en) * | 2005-07-19 | 2008-12-10 | Honeywell International Inc. | Variable nozzle turbocharger |
| EP1790830B1 (en) * | 2005-11-25 | 2019-03-27 | BorgWarner, Inc. | Turbocharger guide vane and turbocharger |
| DE102008020673B4 (en) * | 2007-05-09 | 2018-10-31 | Schaeffler Technologies AG & Co. KG | Graded stator blade |
-
2008
- 2008-01-11 DE DE102008004014A patent/DE102008004014A1/en not_active Withdrawn
- 2008-10-28 KR KR1020107017638A patent/KR20100110867A/en not_active Application Discontinuation
- 2008-10-28 EP EP08869779.2A patent/EP2245275B1/en active Active
- 2008-10-28 WO PCT/EP2008/064594 patent/WO2009086959A1/en active Application Filing
- 2008-10-28 US US12/812,499 patent/US20100296924A1/en not_active Abandoned
- 2008-10-28 JP JP2010541722A patent/JP2011509371A/en active Pending
- 2008-10-28 CN CN200880124892.9A patent/CN101910565B/en active Active
-
2013
- 2013-09-05 JP JP2013184103A patent/JP5701352B2/en not_active Expired - Fee Related
Non-Patent Citations (1)
| Title |
|---|
| JP特开2003-254074A 2003.09.10 |
Also Published As
| Publication number | Publication date |
|---|---|
| CN101910565A (en) | 2010-12-08 |
| JP5701352B2 (en) | 2015-04-15 |
| DE102008004014A1 (en) | 2009-07-23 |
| JP2011509371A (en) | 2011-03-24 |
| EP2245275A1 (en) | 2010-11-03 |
| KR20100110867A (en) | 2010-10-13 |
| US20100296924A1 (en) | 2010-11-25 |
| WO2009086959A1 (en) | 2009-07-16 |
| JP2013238249A (en) | 2013-11-28 |
| EP2245275B1 (en) | 2015-04-08 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN101910565B (en) | Guide vane for a variable turbine geometry | |
| EP1700007B1 (en) | Vane and throat shaping for a radial turbine assembly | |
| JP4625497B2 (en) | Exhaust gas turbocharger for internal combustion engine and internal combustion engine equipped with the same | |
| US8641382B2 (en) | Turbocharger | |
| JP3931507B2 (en) | Diesel engine turbocharger system | |
| CN102296995B (en) | For guiding the blade of waste gas to turbine | |
| CN104632300B (en) | The drive device of the synchronous ring of variable blade component | |
| CN104863700B (en) | The extraction flow valve and its operating method of double volute turbines | |
| CN106014492A (en) | Variable geometry nozzle for partitioned volute | |
| CN102667100B (en) | Turbocharger | |
| EP2799689B1 (en) | Twin-scroll turbocharger | |
| JP2012524854A (en) | Internal combustion engine and method of operating internal combustion engine | |
| SE514969C2 (en) | Internal combustion engine | |
| JP2018053895A (en) | System and method for energy recovery from exhaust gas | |
| CN106414946A (en) | Four-stroke reciprocating-piston internal combustion engine having an exhaust-gas turbocharger, and operating method for the same | |
| SE1050440A1 (en) | Turbine housing for superchargers | |
| CN103277185B (en) | For live gas supplier and the controlling method thereof of the internal-combustion engine with exhaust-gas turbocharger | |
| US20130318988A1 (en) | Aircraft engine with turbine heat exchanger bypass | |
| WO2017120031A1 (en) | Turbocharger compressor and method | |
| CN103352754A (en) | Multi-mode large and small turbocharger diesel engine sequential supercharging structure | |
| CN102648334B (en) | Variable-geometry turbine | |
| CN108699963A (en) | The control method of booster, two-stage turbine system and two-stage turbine system | |
| CN108713093B (en) | Two-stage turbine system and control method of two-stage turbine system | |
| CN102782259A (en) | Variable geometry turbine | |
| US20110142600A1 (en) | Charging device |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C06 | Publication | ||
| PB01 | Publication | ||
| C10 | Entry into substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| C53 | Correction of patent of invention or patent application | ||
| CB02 | Change of applicant information |
Address after: Hannover Applicant after: CONTINENTAL AUTOMOTIVE GmbH Address before: Hannover Applicant before: Continental Automotive GmbH |
|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| TR01 | Transfer of patent right |
Effective date of registration: 20230412 Address after: Regensburg, Germany Patentee after: WeiPai Technology Co.,Ltd. Address before: Hannover Patentee before: CONTINENTAL AUTOMOTIVE GmbH |
|
| TR01 | Transfer of patent right |