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EP0131719B1 - Verstellbarer Leitapparat - Google Patents

Verstellbarer Leitapparat Download PDF

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Publication number
EP0131719B1
EP0131719B1 EP84106015A EP84106015A EP0131719B1 EP 0131719 B1 EP0131719 B1 EP 0131719B1 EP 84106015 A EP84106015 A EP 84106015A EP 84106015 A EP84106015 A EP 84106015A EP 0131719 B1 EP0131719 B1 EP 0131719B1
Authority
EP
European Patent Office
Prior art keywords
guide
guide vanes
adjusting ring
adjustable
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.)
Expired
Application number
EP84106015A
Other languages
German (de)
English (en)
French (fr)
Other versions
EP0131719A3 (en
EP0131719A2 (de
Inventor
Horst Prof. Dr.-Ing. Pfeil
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Howden Turbo GmbH
Original Assignee
Siemens Turbomachinery Equipment GmbH
Kuehnle Kopp and Kausch AG
Priority date (The priority date 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 date listed.)
Filing date
Publication date
Application filed by Siemens Turbomachinery Equipment GmbH, Kuehnle Kopp and Kausch AG filed Critical Siemens Turbomachinery Equipment GmbH
Priority to AT84106015T priority Critical patent/ATE27335T1/de
Publication of EP0131719A2 publication Critical patent/EP0131719A2/de
Publication of EP0131719A3 publication Critical patent/EP0131719A3/de
Application granted granted Critical
Publication of EP0131719B1 publication Critical patent/EP0131719B1/de
Expired legal-status Critical Current

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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 device of an exhaust gas turbine, in particular a turbocharger, with a ring of guide vanes arranged concentrically around a rotor axis, which are each pivotable between two end boundaries about pivot axes, which are arranged in the front area of the guide vanes assigned to the outflow edges, whereby means of an adjustment ring the end limits are adjustable.
  • DE-A-23 29 022 describes an adjustable guide apparatus 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.
  • a radial compressor is known from US-A-39 57 392, the diffuser ring of which has movable blades in order to ensure that it operates in a stable region.
  • the unstable area should be avoided in particular with regard to so-called pumping and stalling.
  • a spring engages on the axes of the blades in order to prevent the blades from fluttering, particularly in the vicinity of the surge line. These springs are a necessary prerequisite and there is no free movement of the blades.
  • the invention has for its object to propose a guide device of the type mentioned, 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 adjusting ring for the guide vanes have contact surfaces which form an end limitation for the respective guide vane, that the guide vanes are freely pivotable under the flow forces in the angular range adjustable by means of the adjusting ring, and that the adjusting ring is inside the flow channel is arranged and / or forms part of the wall of the flow channel.
  • 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 adjustment ring can be formed in one piece or consist of several individual parts or segments.
  • the swiveling guide vanes are not adjusted by an external torque acting on their swivel axes, but can be swiveled freely in the partial load range between the variable end limits. On the other hand, the guide vanes are subjected to further loads due to the vane forces resulting from the flow, which act between the pivot axis and the adjustable end limit, by the end limit in each case predetermined maximum possible angle turned up.
  • the end limit can be set, for example, according to the charge pressure characteristic. It is not necessary to emphasize that in other exhaust gas turbines the adjustability can be made in accordance with the appropriate parameters. It can be seen that, due to the adjustability as a function of preselectable parameters, an optimal adaptation to the respective requirements and operating conditions can be carried out.
  • the guide device for a centripetal flow-through impeller is characterized in that the adjusting ring has the sawtooth-shaped contact surfaces for the free ends of the guide vanes on projections directed towards the flow channel.
  • the sawtooth-shaped bearing surfaces 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 associated with a defined displacement angle of the blades, and above all a linear dependency can be predefined without difficulty.
  • the contact surfaces of the adjusting ring are arranged in guide grooves, in which the guide vanes each engage with a lateral pin. Due to the lateral arrangement of the pin, the passage area between the guide vanes remains free.
  • the contact surfaces of the adjusting ring are each arranged on a guide pin which engages in a guide groove provided on the end face of the guide vane or on which the guide vane rests with the profile side located downstream.
  • the guide pin which is expediently connected directly to the adjusting ring, forms a reliable support or delimitation for the guide vane, with a low manufacturing effort also being required here.
  • the contact surface for an axially flowed through impeller is arranged on an axial end face of the adjusting ring designed as a hollow ring, on which end face the free ends of the guide vanes partially rest.
  • the adjusting ring is located behind the swivel axes in the flow direction, so that the unscrewing caused by the blade forces is limited by the free ends abutting 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 present, through which the exhaust gas flowing radially inward reaches the guide vanes 6 distributed over the circumference in the usual way.
  • 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 free, radially inward-pointing ends 16 of the guide vanes rest 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.
  • suitable adjusting means which are preferably pneumatic or are also mechanically designed, the adjusting ring 14 can be set in the desired angular position with respect to the rotor axis 12.
  • 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 blades 6 are moved outward 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 formed 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 the flow width is narrowed in the area of the projections 18 of the adjusting ring 14 and thus in the area 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. Fig. 3.
  • the housing 22 has an inclined slot 26 for the bolt 24, so that 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 is given. 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.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Supercharger (AREA)
  • Control Of Turbines (AREA)
  • Transplanting Machines (AREA)
  • Steering Controls (AREA)
  • Harvester Elements (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
EP84106015A 1983-07-16 1984-05-26 Verstellbarer Leitapparat Expired EP0131719B1 (de)

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 EP0131719A2 (de) 1985-01-23
EP0131719A3 EP0131719A3 (en) 1985-03-13
EP0131719B1 true EP0131719B1 (de) 1987-05-20

Family

ID=6204187

Family Applications (1)

Application Number Title Priority Date Filing Date
EP84106015A Expired EP0131719B1 (de) 1983-07-16 1984-05-26 Verstellbarer Leitapparat

Country Status (5)

Country Link
US (1) US4657480A (da)
EP (1) EP0131719B1 (da)
JP (1) JPS6053602A (da)
AT (1) ATE27335T1 (da)
DE (2) DE3325756C1 (da)

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0276023A2 (en) * 1987-01-23 1988-07-27 Honda Giken Kogyo Kabushiki Kaisha Variable-displacement turbine
US6739832B2 (en) 2001-03-30 2004-05-25 Abb Turbo Systems Ag Exhaust turbocharger

Families Citing this family (14)

* Cited by examiner, † Cited by third party
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
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
DE10013335A1 (de) 2000-03-17 2001-09-20 Abb Turbo Systems Ag Baden Leitapparat für eine axial durchströmte Abgasturbine
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
JP6768287B2 (ja) * 2014-11-21 2020-10-14 ボーグワーナー インコーポレーテッド 一軸のセルフセンタリングピボット部を有する可変タービンジオメトリベーン
US10883379B2 (en) * 2018-05-11 2021-01-05 Rolls-Royce Corporation Variable diffuser having a respective penny for each vane

Family Cites Families (15)

* Cited by examiner, † Cited by third party
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
GB304638A (en) * 1927-09-21 1929-01-21 Neil Shaw Muir Improvements in or relating to centrifugal blowers, compressors and the like
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
GB731822A (en) * 1952-03-14 1955-06-15 Power Jets Res & Dev Ltd Improvements relating to turbines or compressors for operation with gaseous fluids
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
US3957392A (en) * 1974-11-01 1976-05-18 Caterpillar Tractor Co. Self-aligning vanes for a turbomachine
GB1524969A (en) * 1974-12-17 1978-09-13 Penny Turbines Ltd Noel Stator vane assembly
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
DE3030079A1 (de) * 1980-08-08 1982-03-11 Kraftwerk Union AG, 4330 Mülheim Rueckschlagklappen-anordnung im ansaugkanal eines geblaeses
US4484857A (en) * 1982-09-21 1984-11-27 Pierre Patin Bladed turbine pump with adjustable guide vanes

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0276023A2 (en) * 1987-01-23 1988-07-27 Honda Giken Kogyo Kabushiki Kaisha Variable-displacement turbine
EP0276023A3 (en) * 1987-01-23 1989-04-26 Honda Giken Kogyo Kabushiki Kaisha Variable-displacement turbine
US6739832B2 (en) 2001-03-30 2004-05-25 Abb Turbo Systems Ag Exhaust turbocharger

Also Published As

Publication number Publication date
JPS6053602A (ja) 1985-03-27
EP0131719A3 (en) 1985-03-13
JPH0347401B2 (da) 1991-07-19
DE3463812D1 (en) 1987-06-25
US4657480A (en) 1987-04-14
DE3325756C1 (de) 1984-09-13
ATE27335T1 (de) 1987-06-15
EP0131719A2 (de) 1985-01-23

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