CN1530519A - Guider - Google Patents
Guider Download PDFInfo
- Publication number
- CN1530519A CN1530519A CNA200410028665XA CN200410028665A CN1530519A CN 1530519 A CN1530519 A CN 1530519A CN A200410028665X A CNA200410028665X A CN A200410028665XA CN 200410028665 A CN200410028665 A CN 200410028665A CN 1530519 A CN1530519 A CN 1530519A
- Authority
- CN
- China
- Prior art keywords
- adjustable lever
- face
- guiding device
- blade
- described guiding
- 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.)
- Granted
Links
Images
Classifications
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- 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
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D9/00—Stators
- F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
- F01D9/04—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02B—INTERNAL-COMBUSTION PISTON ENGINES; COMBUSTION ENGINES IN GENERAL
- F02B37/00—Engines characterised by provision of pumps driven at least for part of the time by exhaust
- F02B37/12—Control of the pumps
- F02B37/24—Control of the pumps by using pumps or turbines with adjustable guide vanes
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2220/00—Application
- F05D2220/40—Application in turbochargers
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2250/00—Geometry
- F05D2250/10—Two-dimensional
- F05D2250/14—Two-dimensional elliptical
- F05D2250/141—Two-dimensional elliptical circular
Abstract
A duct apparatus for a radial-flow turbine has a blade adjusting a pass flow by an adjusting device. The duct apparatus has an adjusting ring having recesses opened outward and adjusting levers each engaged with the recesses by one circular end portion. The recesses are defined by two bearing surfaces radially extended. The adjusting levers are each coupled to blade shafts at the other end in a state incapable of rotating.
Description
Technical field
The present invention relates to a kind of guiding device of radial turbine, have and be arranged in the blade that can carry out Flow-rate adjustment in the housing by a controlling mechanism.
Summary of the invention
Task of the present invention is the guiding device that proposes a kind of the above-mentioned type, and its construction expenditure is very low, and can guarantee reliable functioning under higher heat load.
According to the present invention, above-mentioned technical problem solves by a regulating ring and adjustable lever, this regulating ring has outwardly open breach, breach is limited by two parallel sidewalls that radially extend respectively, and adjustable lever is embedded in the breach and at the other end and each blade neck with round nose parts respectively and links antitorquely.
By moving in the breach of adjustable lever in regulating ring, produce a kind of regulating ring structure of torsional rigid.Because adjustable lever is because its structure has only very little surface of contact in breach, so reduced adjusting power.In addition, this structure reduces to minimum with possible retardation phenomenon.And each parts manufacturing is simple.
According to a kind of design proposal of the present invention, the other end of each adjustable lever have respectively two perpendicular to that adjustment movement extends in parallel by transmitting, with the blade neck on the coefficient subtend face of respective synchronization face.This connection makes structure simple especially.
Preferably, each blade neck has a cylindrical part, and this cylindrical part is embedded in the hole that the contiguous abutment facing of of adjustable lever is provided with.Preferably each adjustable lever stops the motion of blade neck axis direction by a nut of twisting thereon.It is simple especially that this makes parts install.
Preferably, each blade is different big at the face of the rotating shaft both sides that the blade neck is determined, wherein the face of swinging to turbine running wheel direction when opening movement is greater than another face.This measure has guaranteed that when the control fails of regulating ring mobilization force takes blade to a wide-open position of blade.Avoided the hypervelocity of turbine thus.
Further feature and advantage are by dependent claims and do with reference to the accompanying drawings to describe and provide.
Description of drawings
Fig. 1 shows the sectional view according to guiding device major part of the present invention.
Fig. 2 shows along the sectional view of Fig. 1 center line II-II.
Fig. 3 shows the view of adjustable lever.
Fig. 4 shows along the sectional view of Fig. 3 center line IV-IV.
Fig. 5 shows the details of regulating ring.
Embodiment
Guiding device shown in the figure is used for the radial turbine of the exhaust gas turbocharger of internal-combustion piston engine, has two housing parts 1 and 2, and these two housing parts define a flow channel, and waste gas flows through this flow channel along the direction shown in the arrow 3.Between two housing parts 1 and 2, be blade 4.Each blade 4 has an integral body with 5 necks of representing.Blade neck 5 has a supporting portion 6 in the face of blade 4, and this supporting portion 6 is bearing in the cushion block 7 that is embedded in the housing parts 1.
Housing parts 1 is arranged the side in the face of compressor of exhaust gas flow direction shown in the arrow 3, thereby is arranged in a position that heat load is as far as possible little.
The end that deviates from blade 4 at supporting portion 6 is a sync section 8.This sync section 8 has two synchronous faces 9 parallel with the diagram face up and down.In synchronous face 9 outsides against the parallel subtend face 10 that an adjustable lever 11 is arranged.Adjustable lever 11 also has a hole 12 except subtend face 10, can support to by this hole adjustable lever 11 on another circular portion 13 of blade neck 5.On this part, be connected with a helical thread portion 14, the nut 15 of screwing on above, lock washer of middle pad.Adjustable lever 11 also has the end piece 16 of a circle.
This end piece 16 is embedded in the outwardly open breach 17 in the regulating ring 18.Each breach 17 have two parallel up and down, be roughly parallel to the abutment facing 19 that is transmitted adjustment movement.Select the relative distance of abutment facing 19, the round nose parts 16 of adjustable lever 11 are embedded in the breach 17 movably.Leave gap 20 between the end piece 16 of breach bottom and adjustable lever 11 when the size of breach 17 makes regulating ring 18 colder in addition.As shown in Figure 1, breach 17 is wideer than the thickness of the end piece 16 of adjustable lever 11, thereby the small thermal expansion of blade neck 5 can not have influence on the validity of adjusting.
As shown in Figure 5, regulating ring 18 has slip joint 21.This slip joint can for example constitute with a kind of ferronickel sintering body that has sulphurous acid molybdenum (Molybd nsulfitd) interlayer.This slip joint 21 can be arranged on the acting in conjunction face of regulating ring 18 and adjustable lever 11 and supporting portion 6 and cushion block 7.
As shown in Figure 2, each blade has the blade face 22,23 of different sizes in blade neck 5 both sides.Wherein the face of swinging to arrow a direction when the blade opening movement 22 is greater than face 23.Avoid the hypervelocity of exhaust gas turbocharger thus, improved functional reliability.
If thereby regulating ring 18 heating radial expansion at work, then the end piece 16 of adjustable lever 11 can enter in the gap 20, thus the thermal expansion of regulating ring 19 to the position of adjustable lever 11 without any influence.
Claims (8)
1, a kind of guiding device of radial turbine, have and be arranged in the blade that can carry out Flow-rate adjustment in the housing by a controlling mechanism, it is characterized in that, a regulating ring (18) and an adjustable lever (11) are arranged, described regulating ring has outwardly open breach (17), this breach is limited by two parallel abutment facings (19) that radially extend respectively, and described adjustable lever is embedded in each breach (17) and at the other end with the end piece (16) of a circle respectively and links with each blade neck (5) antitorquely.
2, according to the described guiding device of claim 1, it is characterized in that, be provided with on the other end of each adjustable lever (11) two perpendicular to transmitted adjustment movement extend in parallel, with blade neck (5) on the coefficient subtend face of respective synchronization face (9) (10).
According to claim 1 or 2 described guiding devices, it is characterized in that 3, each blade neck (5) all has a cylindrical part (13), this cylindrical part is embedded in the hole that the contiguous subtend face (10) of adjustable lever (11) is provided with.
According to the described guiding device of one of aforementioned claim, it is characterized in that 4, adjustable lever (11) stops the motion of blade neck (5) axial direction by dress nut (15) thereon.
5, according to the described guiding device of one of aforementioned claim, it is characterized in that, each blade (4) is different big at the face of the rotating shaft both sides that blade neck (5) is determined, wherein the face of swinging to turbine running wheel direction when opening movement (a) (22) is greater than another face (23).
6, according to the described guiding device of one of aforementioned claim, it is characterized in that, for regulating ring (18) and/or adjustable lever (11) are provided with a kind of dry lubrication.
7, according to the described guiding device of claim 6, it is characterized in that,, slip joint (21) is set in lubricated parts in order to realize dry lubrication.
According to the described guiding device of one of aforementioned claim, it is characterized in that 8, regulating ring (18) and adjustable lever (11) are contained in one in the face of in the housing parts (1) of exhaust gas turbocharger compressor.
Applications Claiming Priority (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| DE10311227A DE10311227B4 (en) | 2003-03-14 | 2003-03-14 | diffuser |
| DE10311227.8 | 2003-03-14 |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN1530519A true CN1530519A (en) | 2004-09-22 |
| CN100404796C CN100404796C (en) | 2008-07-23 |
Family
ID=32920793
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CNB200410028665XA Expired - Fee Related CN100404796C (en) | 2003-03-14 | 2004-03-08 | Guiding device |
Country Status (5)
| Country | Link |
|---|---|
| JP (1) | JP4444699B2 (en) |
| KR (1) | KR100997507B1 (en) |
| CN (1) | CN100404796C (en) |
| CH (1) | CH697363B1 (en) |
| DE (1) | DE10311227B4 (en) |
Families Citing this family (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP1818509A1 (en) | 2006-02-09 | 2007-08-15 | Siemens Aktiengesellschaft | Guide vane assembly |
| KR101026989B1 (en) * | 2010-12-20 | 2011-04-11 | 한국기계연구원 | Flow controllable type turbine |
| GB201409449D0 (en) | 2014-05-28 | 2014-07-09 | Rolls Royce Deutschland | A variable stator vane arrangment |
| GB2527297B (en) * | 2014-06-16 | 2016-08-17 | Rolls Royce Plc | An assembly |
| DE102014215885B3 (en) | 2014-08-11 | 2015-12-31 | Ford Global Technologies, Llc | Supercharged internal combustion engine with mixed-flow turbine |
| DE102014215888B4 (en) * | 2014-08-11 | 2016-06-09 | Ford Global Technologies, Llc | Internal combustion engine with variable mixed-flow turbine |
Family Cites Families (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4179247A (en) * | 1977-01-14 | 1979-12-18 | Wrr Industries, Inc. | Turbocharger having variable area turbine nozzles |
| US4490622A (en) * | 1979-05-11 | 1984-12-25 | Osborn Norbert L | Turbocharger and adaptations thereof |
| JPS58130030U (en) | 1982-02-26 | 1983-09-02 | 三菱自動車工業株式会社 | Control device for supercharger with variable nozzle |
| GB2183302B (en) | 1985-10-24 | 1990-07-04 | Household Mfg Inc | Turbocharger with variable vanes |
| CA1270120A (en) * | 1985-12-11 | 1990-06-12 | Alliedsignal Inc. | Suspension for the pivoting vane actuation mechanism of a variable nozzle turbocharger |
| JP3341806B2 (en) * | 1996-08-27 | 2002-11-05 | 株式会社日立製作所 | Variable displacement turbocharger |
| DE10013335A1 (en) * | 2000-03-17 | 2001-09-20 | Abb Turbo Systems Ag Baden | Conducting apparatus is for position alteration of conducting blades in turbocharger exhaust gas turbine has blades arranged axially symmetrically to the turbine axis in an exhaust gas flow channel and can be pivoted by a pivot device |
-
2003
- 2003-03-14 DE DE10311227A patent/DE10311227B4/en not_active Expired - Fee Related
-
2004
- 2004-02-02 CH CH00147/04A patent/CH697363B1/en unknown
- 2004-03-08 CN CNB200410028665XA patent/CN100404796C/en not_active Expired - Fee Related
- 2004-03-10 JP JP2004067287A patent/JP4444699B2/en not_active Expired - Fee Related
- 2004-03-15 KR KR1020040017392A patent/KR100997507B1/en active IP Right Grant
Also Published As
| Publication number | Publication date |
|---|---|
| JP4444699B2 (en) | 2010-03-31 |
| JP2004278533A (en) | 2004-10-07 |
| CH697363B1 (en) | 2008-08-29 |
| KR20040081076A (en) | 2004-09-20 |
| DE10311227B4 (en) | 2005-03-31 |
| CN100404796C (en) | 2008-07-23 |
| DE10311227A1 (en) | 2004-09-30 |
| KR100997507B1 (en) | 2010-12-01 |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C06 | Publication | ||
| PB01 | Publication | ||
| C10 | Entry into substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| CP01 | Change in the name or title of a patent holder | ||
| CP01 | Change in the name or title of a patent holder |
Address after: Augsburg Patentee after: MAN ENERGY SOLUTIONS SE Address before: Augsburg Patentee before: Man Diesel & Turbo SE |
|
| TR01 | Transfer of patent right | ||
| TR01 | Transfer of patent right |
Effective date of registration: 20190423 Address after: Augsburg Patentee after: Man Diesel & Turbo SE Address before: Augsburg Patentee before: Man Diesel Se |
|
| CF01 | Termination of patent right due to non-payment of annual fee | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20080723 Termination date: 20210308 |