EP0131719A2 - Dispositif variable de guidage - Google Patents
Dispositif variable de guidage Download PDFInfo
- Publication number
- EP0131719A2 EP0131719A2 EP84106015A EP84106015A EP0131719A2 EP 0131719 A2 EP0131719 A2 EP 0131719A2 EP 84106015 A EP84106015 A EP 84106015A EP 84106015 A EP84106015 A EP 84106015A EP 0131719 A2 EP0131719 A2 EP 0131719A2
- Authority
- EP
- European Patent Office
- Prior art keywords
- guide vanes
- guide
- adjustable
- ring
- adjusting ring
- 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
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D29/00—Details, component parts, or accessories
- F04D29/40—Casings; Connections of working fluid
- F04D29/42—Casings; Connections of working fluid for radial or helico-centrifugal pumps
- F04D29/44—Fluid-guiding means, e.g. diffusers
- F04D29/46—Fluid-guiding means, e.g. diffusers adjustable
- F04D29/462—Fluid-guiding means, e.g. diffusers adjustable especially adapted for elastic fluid pumps
-
- 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
Definitions
- the invention relates to an adjustable guide apparatus of a turbomachine, in particular an exhaust gas turbine of a turbocharger, with a ring of guide vanes arranged concentrically around a rotor axis, each of which is arranged between end boundaries around pivot axes, which are arranged in the front area of the guide vanes which is assigned to the AU 3 and is flowing are pivotable, one of the end limits being adjustable by means of an adjusting ring or the like.
- DE-OS 23 29 022 describes an adjustable guide device for the guide vanes of a gas turbine, the guide vanes of which are arranged so as to be pivotable about pivot axes. To pivot the guide vanes, they have lateral pins in the area of their leading edges, which engage in axial guide grooves of an adjusting ring. The guide vanes can be pivoted between end limits by means of the adjusting ring, but the guide vanes cannot be pivoted freely. The guide vanes are positively guided in each operating area of the gas turbine in accordance with the setting of the adjusting ring.
- DE-OS 24 55 361 describes an adjustable diffuser of a turbine or a compressor, in which the blades are articulated on the one hand in a housing and on the other hand on an adjusting ring.
- This adjustment ring is adjustable between two fixed stops.
- the guide vanes are therefore mechanically forcibly guided, a comparatively great mechanical outlay being necessary in order to mount each guide vane about two pivot axes each, an eccentric, elongated hole or the like being provided. Furthermore, external adjustment forces have to be applied in two directions for the adjustment of the guide vanes.
- the invention is therefore based on the object of proposing a guide apparatus of the type mentioned at the outset which has a comparatively simple construction and in which the adjusting forces can also be applied in one direction only.
- gap and / or impact losses are to be reduced with a view to low consumption.
- a compact and weight-saving structure and also a high level of operational reliability are to be achieved.
- a functional adjustment to the operational requirements and the installation conditions should be given with a low weight.
- the guide vanes be arranged in such a way that they can be freely pivoted under flow forces in a setting angle range predetermined by means of the end limits.
- the proposed diffuser has a comparatively simple construction, and adjusting forces can only be applied in one direction.
- the guide vanes are automatically adjusted within the limits specified by the end limits in accordance with the direction of the streamline. This results in a not inconsiderable reduction in gap and impact losses in the partial load range if no or even a low boost pressure is required for the engine.
- the freely pivotable guide vanes are thus set to "minimum loss" without the need for a high level of control and regulation, as would be necessary with positively driven guide vanes.
- the guide device has a high level of operational reliability with a simple construction, the adjusting force being able to be introduced practically at any desired point; an adaptation to the respective installation conditions can be done without difficulty.
- the pivotable guide vanes are not adjusted by an external torque acting on their pivot axes, but that they can be freely pivoted between the variable end limits in the partial load range.
- the guide vanes are further turned up to the greatest possible angle given by the end limitation due to the blade forces resulting from the flow which act between the pivot axis and the adjustable end limitation.
- the end limit can be set, for example, according to the charge pressure characteristic.
- the adjustability can be made according to the appropriate parameters in other turbomachines. It can be seen that due to the Adjustability depending on preselectable parameters an optimal adaptation to the respective requirements and operating conditions can be carried out.
- the guide vanes have a lateral guide pin which slides in an adjustable guide groove. It should be noted that the proposed guide groove is adjustable in the desired manner by means of the above-mentioned adjusting ring. Due to the lateral arrangement of the pin, the passage area between the guide vanes remains free.
- an adjustable guide pin is provided in the wall of the flow channel, which slides in a guide groove provided on the end face of the guide vanes or on the downstream profile side.
- the guide pin which is expediently connected directly to the adjusting ring, forms a reliable support or limitation for the guide vanes, with a comparatively low production outlay also being required here.
- the adjusting ring is provided with sawtooth-shaped contact surfaces for the free ends of the guide vanes for an impeller through which centripetal flows.
- the sawtooth-shaped contact surfaces according to the invention are at a smaller distance from the rotor axis than the pivot axes.
- the curve shape can be specified according to the respective requirements.
- the curves are expediently predefined in such a way that a displacement angle of the displacement ring is also assigned a defined displacement angle of the blades, and above all a linear dependency can be predefined without difficulty.
- the free ends of the guide vanes partially rest on the adjusting ring arranged in the flow channel, which is adjustable in the axial direction.
- the adjusting ring is in flow direction behind the pivot axes, so that the unscrewing caused by the blade forces is limited by the contact of the free ends on the adjusting ring.
- At least two guide vanes are coupled to one another and are freely pivotable together.
- the individual guide vanes can therefore no longer be freely pivoted independently of one another, but rather the guide vanes which are coupled to one another can be freely pivoted together.
- the individual blades are thus combined into groups distributed over the circumference.
- the guide vanes which are coupled to one another consequently have the same angle of attack, which ensures a particularly uniform flow against the turbine wheel.
- disadvantageous oscillation or fluttering which may occur in the case of individual blades, can be prevented.
- two are connected to each other, with more than two blades being connected to one another in accordance with the respective requirements, in particular by means of a lever or the like.
- FIG. 1 shows, purely schematically, an exhaust gas turbine with an impeller 2 through which there is a centripetal flow.
- a spiral inflow channel 4 is provided, through which the exhaust gas flowing radially inward passes in the usual way to the guide vanes 6 distributed over the circumference.
- the guide vanes 6 are arranged in a housing 8 so as to be pivotable about a pivot axis 10, the pivot axis being located in the region of the leading edge 11.
- an adjusting ring 14 which is rotatable in a suitable manner about the rotor axis 12 is also arranged.
- the guide vanes rest with their free, radially inwardly facing ends 16 on a projection 18 of the adjusting ring 14.
- the adjusting ring 14 or the projection 18, corresponding projections also being provided for the other guide vanes distributed over the circumference, has a sawtooth-shaped contour to be explained below.
- These projections 18 create 6 inner end boundaries for the respective guide vanes, against which the guide vanes bear with increasing load; otherwise the guide vanes are freely pivotable about their pivot axis 10.
- the adjusting ring 14 can be adjusted to the desired angular position with respect to the rotor axis 12 by means of suitable adjusting means, which are preferably pneumatic or also mechanical.
- Fig. 2 shows in the left part a view in viewing direction A and also in the right part a section along section line II acc. Fig. 1.
- the adjusting ring 14 has on its radial outer surface the sawtooth-shaped projections 18, with each guide vane 6 being associated with such a projection 18.
- the drawing shows the position in which the flow cross-section between the guide vanes is greatest.
- the flow cross section is reduced by rotating the adjusting ring 14 about the rotor axis 12 in the direction of the arrow 20.
- the free ends 16 of the guide vanes 6 are moved outwards on the sawtooth-shaped contour in the radial direction.
- the adjustment ring 14 designed in this way creates the inner variable end limit for the guide vanes 6.
- the outer end limitation is formed by the next following guide vane in each case in the circumferential direction.
- the guide vanes 6 adjust themselves according to the pressure and flow conditions between these two end limits, as a result of which gap and impact losses are reduced to a minimum and consequently, in this part-load range, compared to fully guided guide vanes, there are not inconsiderably lower losses.
- the sawtooth-shaped curves or surfaces of the projections 18 are designed such that there is a proportional dependence between the change in the angle of rotation of the adjusting ring 14 and the change in the setting angle of the guide vanes 6. It is also essential that there is a narrowing of the flow width in the region of the projections 18 of the adjusting ring 14 and thus in the region of the trailing edges or the free ends of the guide vanes 6.
- Fig. 3 shows purely schematically the diffuser for an exhaust gas turbine with an axially flow through stator, not shown here.
- the adjusting ring 14 Concentric to the rotor axis 12, the adjusting ring 14 can be seen, which is designed here as a hollow ring and which, according to the invention, is arranged radially on the outside in the flow channel.
- the guide vanes 6 can be pivoted about essentially radially oriented pivot axes 10, which are located at the front end or in the region of the leading edges.
- the free end or the trailing edge of the guide vane 6 lies against the end face of the adjusting ring 14 with a small, radially outer part.
- the adjusting ring 14 is guided in a suitable manner in the housing 22, and it can be adjusted parallel to the rotor axis 12, for example via a bolt 24.
- FIG. 4 shows a part of the guide apparatus projected into the drawing plane in the viewing direction B according to FIG. 3.
- the housing 22 has a slanted slot 26 for the bolt 24, so that there is not only an axial adjustability in the direction of the rotor axis but also a rotation about the rotor axis for the adjusting ring 14. According to the invention, this makes it easy to adjust the adjustment ring.
- the guide vanes 6, as can be readily recognized in connection with FIG. 3, rest with the outer part of their trailing edge on the adjusting ring 14, which thus forms the one end limit.
- the end limitation is also changed in this embodiment. It is not necessary to emphasize that the other end limitation is given by the adjacent guide vane.
- FIG. 5 shows a view similar to FIG. 4, but with the three guide vanes 6 shown being coupled to one another by means of a lever 30. Otherwise, the description of FIG. 4 applies accordingly.
- the three guide vanes 6 are coupled to one another by means of the lever 30 in such a way that they can be pivoted together about their pivot axes 10 and thus each assume the same angular position in the partial load range.
- the other guide vanes, not shown here are of course also coupled to one another in groups.
- the guide blades coupled in this way each take the same angular position. The uniformity of the inflow to the turbine wheel is significantly improved and vibrations of individual blades can be prevented.
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Supercharger (AREA)
- Control Of Turbines (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
- Harvester Elements (AREA)
- Transplanting Machines (AREA)
- Steering Controls (AREA)
Priority Applications (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
AT84106015T ATE27335T1 (de) | 1983-07-16 | 1984-05-26 | Verstellbarer leitapparat. |
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
DE3325756A DE3325756C1 (de) | 1983-07-16 | 1983-07-16 | Verstellbarer Leitapparat |
DE3325756 | 1983-07-16 |
Publications (3)
Publication Number | Publication Date |
---|---|
EP0131719A2 true EP0131719A2 (fr) | 1985-01-23 |
EP0131719A3 EP0131719A3 (en) | 1985-03-13 |
EP0131719B1 EP0131719B1 (fr) | 1987-05-20 |
Family
ID=6204187
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP84106015A Expired EP0131719B1 (fr) | 1983-07-16 | 1984-05-26 | Dispositif variable de guidage |
Country Status (5)
Country | Link |
---|---|
US (1) | US4657480A (fr) |
EP (1) | EP0131719B1 (fr) |
JP (1) | JPS6053602A (fr) |
AT (1) | ATE27335T1 (fr) |
DE (2) | DE3325756C1 (fr) |
Cited By (1)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US6824355B2 (en) | 2000-03-17 | 2004-11-30 | Abb Turbo Systems Ag | Distributor for an exhaust gas turbine with an axial flow |
Families Citing this family (15)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US4629396A (en) * | 1984-10-17 | 1986-12-16 | Borg-Warner Corporation | Adjustable stator mechanism for high pressure radial turbines and the like |
DE3516738A1 (de) * | 1985-05-09 | 1986-11-13 | Mtu Motoren- Und Turbinen-Union Friedrichshafen Gmbh, 7990 Friedrichshafen | Stroemungsmaschine |
DE3541508C1 (de) * | 1985-11-23 | 1987-02-05 | Kuehnle Kopp Kausch Ag | Abgasturbolader |
US4741666A (en) * | 1985-12-23 | 1988-05-03 | Ishikawajima-Harima Jukogyo Kabushiki Kaisha | Variable displacement turbocharger |
JPS63183207A (ja) * | 1987-01-23 | 1988-07-28 | Honda Motor Co Ltd | 可変容量式タ−ビン |
US5266003A (en) * | 1992-05-20 | 1993-11-30 | Praxair Technology, Inc. | Compressor collector with nonuniform cross section |
US5437539A (en) * | 1992-07-22 | 1995-08-01 | Massachusetts Institute Of Technology | Apparatus for the dynamic control of rotating stall and surge in turbo machines and the like |
US5730580A (en) * | 1995-03-24 | 1998-03-24 | Concepts Eti, Inc. | Turbomachines having rogue vanes |
DE19644892A1 (de) * | 1996-10-29 | 1998-04-30 | Johannes Werner | Vorleiteinrichtung für Strömungsmaschinen und Verbrennungskraftmaschinen |
US6174129B1 (en) | 1999-01-07 | 2001-01-16 | Siemens Westinghouse Power Corporation | Turbine vane clocking mechanism and method of assembling a turbine having such a mechanism |
DE50205152D1 (de) | 2001-03-30 | 2006-01-12 | Abb Turbo Systems Ag Baden | Abgasturbolader |
DE102004040536A1 (de) * | 2004-08-20 | 2006-02-23 | Volkswagen Ag | Abgasturbolader mit variabler Turbinengeometrie |
US20060177305A1 (en) * | 2005-02-07 | 2006-08-10 | Hoang Khanh C | Centrifugal volute pump with discontinuous vane-island diffuser |
US10240480B2 (en) * | 2014-11-21 | 2019-03-26 | Borgwarner Inc. | Variable turbine geometry vane with single-axle, self-centering pivot feature |
US10883379B2 (en) * | 2018-05-11 | 2021-01-05 | Rolls-Royce Corporation | Variable diffuser having a respective penny for each vane |
Citations (5)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
GB304638A (en) * | 1927-09-21 | 1929-01-21 | Neil Shaw Muir | Improvements in or relating to centrifugal blowers, compressors and the like |
GB731822A (en) * | 1952-03-14 | 1955-06-15 | Power Jets Res & Dev Ltd | Improvements relating to turbines or compressors for operation with gaseous fluids |
US3957392A (en) * | 1974-11-01 | 1976-05-18 | Caterpillar Tractor Co. | Self-aligning vanes for a turbomachine |
US4029433A (en) * | 1974-12-17 | 1977-06-14 | Caterpillar Tractor Co. | Stator vane assembly |
DE3030079A1 (de) * | 1980-08-08 | 1982-03-11 | Kraftwerk Union AG, 4330 Mülheim | Rueckschlagklappen-anordnung im ansaugkanal eines geblaeses |
Family Cites Families (10)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US1136877A (en) * | 1914-06-01 | 1915-04-20 | Thomas Henry Collett Homersham | Centrifugal blower and other centrifugal machine of a similar nature. |
DE518787C (de) * | 1926-11-02 | 1931-02-19 | Georges Claude | Turbine zum Betrieb mit Wasserdampf oder anderen Treibmitteln von geringem Druck |
DE889091C (de) * | 1940-03-08 | 1953-09-07 | Versuchsanstalt Fuer Luftfahrt | Stetig verstellbares Leitschaufelsystem |
FR1041161A (fr) * | 1951-08-14 | 1953-10-21 | Napier & Son Ltd | Perfectionnements aux appareils à réaction à courant axial de fluide comprenant au moins une rangée d'aubes radiales |
DE2262031A1 (de) * | 1972-12-19 | 1974-06-20 | Klein Schanzlin & Becker Ag | Eintritts-leitapparat fuer stroemungsmaschinen |
DE2329022A1 (de) * | 1973-06-07 | 1975-02-20 | Volkswagenwerk Ag | Einrichtung zur verstellung der leitschaufeln einer gasturbine |
DE2455361A1 (de) * | 1973-12-11 | 1975-06-12 | Plessey Handel Investment Ag | Turbine bzw. kompressor insbesondere fuer turbolader |
US4179247A (en) * | 1977-01-14 | 1979-12-18 | Wrr Industries, Inc. | Turbocharger having variable area turbine nozzles |
JPS5724500A (en) * | 1980-07-22 | 1982-02-09 | Mitsubishi Heavy Ind Ltd | Variable stator blade mechanism for turbomachine |
US4484857A (en) * | 1982-09-21 | 1984-11-27 | Pierre Patin | Bladed turbine pump with adjustable guide vanes |
-
1983
- 1983-07-16 DE DE3325756A patent/DE3325756C1/de not_active Expired
-
1984
- 1984-05-26 AT AT84106015T patent/ATE27335T1/de not_active IP Right Cessation
- 1984-05-26 DE DE8484106015T patent/DE3463812D1/de not_active Expired
- 1984-05-26 EP EP84106015A patent/EP0131719B1/fr not_active Expired
- 1984-07-11 US US06/629,601 patent/US4657480A/en not_active Expired - Fee Related
- 1984-07-13 JP JP59145877A patent/JPS6053602A/ja active Granted
Patent Citations (5)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
GB304638A (en) * | 1927-09-21 | 1929-01-21 | Neil Shaw Muir | Improvements in or relating to centrifugal blowers, compressors and the like |
GB731822A (en) * | 1952-03-14 | 1955-06-15 | Power Jets Res & Dev Ltd | Improvements relating to turbines or compressors for operation with gaseous fluids |
US3957392A (en) * | 1974-11-01 | 1976-05-18 | Caterpillar Tractor Co. | Self-aligning vanes for a turbomachine |
US4029433A (en) * | 1974-12-17 | 1977-06-14 | Caterpillar Tractor Co. | Stator vane assembly |
DE3030079A1 (de) * | 1980-08-08 | 1982-03-11 | Kraftwerk Union AG, 4330 Mülheim | Rueckschlagklappen-anordnung im ansaugkanal eines geblaeses |
Cited By (1)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US6824355B2 (en) | 2000-03-17 | 2004-11-30 | Abb Turbo Systems Ag | Distributor for an exhaust gas turbine with an axial flow |
Also Published As
Publication number | Publication date |
---|---|
JPS6053602A (ja) | 1985-03-27 |
US4657480A (en) | 1987-04-14 |
EP0131719B1 (fr) | 1987-05-20 |
DE3463812D1 (en) | 1987-06-25 |
ATE27335T1 (de) | 1987-06-15 |
DE3325756C1 (de) | 1984-09-13 |
JPH0347401B2 (fr) | 1991-07-19 |
EP0131719A3 (en) | 1985-03-13 |
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