EP0056669A1 - Turbine mit regelbarem Einlassquerschnitt - Google Patents

Turbine mit regelbarem Einlassquerschnitt Download PDF

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Publication number
EP0056669A1
EP0056669A1 EP82200035A EP82200035A EP0056669A1 EP 0056669 A1 EP0056669 A1 EP 0056669A1 EP 82200035 A EP82200035 A EP 82200035A EP 82200035 A EP82200035 A EP 82200035A EP 0056669 A1 EP0056669 A1 EP 0056669A1
Authority
EP
European Patent Office
Prior art keywords
turbo
fluid
opening
sector
injection
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
Application number
EP82200035A
Other languages
English (en)
French (fr)
Other versions
EP0056669B1 (de
Inventor
Albert Van Gucht
Raymond Wattez
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.)
Umicore NV SA
Original Assignee
Ateliers de Constructions Electriques de Charleroi SA
ACEC SA
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 Ateliers de Constructions Electriques de Charleroi SA, ACEC SA filed Critical Ateliers de Constructions Electriques de Charleroi SA
Priority to AT82200035T priority Critical patent/ATE23905T1/de
Publication of EP0056669A1 publication Critical patent/EP0056669A1/de
Application granted granted Critical
Publication of EP0056669B1 publication Critical patent/EP0056669B1/de
Expired legal-status Critical Current

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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

Definitions

  • centripetal wheel of the turbine is done by a constant opening injection sector whose fixed guide vanes impose on the fluid a suitable orientation.
  • the invention claimed below makes it possible to maintain the yield at its optimum value whatever the flow rate of the fluid and its application covers both the recovery of energy by expansion of gas at high pressure and that by expansion of water vapor. . In addition, it simplifies the installation upstream of the machine by replacing the flow control valve, high cost and generating energy loss, by a simple shut-off valve.
  • the invention essentially consists of a device making it possible to vary the sector of injection of the fluid without appreciably modifying the speed of the latter even if the flow rate undergoes significant fluctuations.
  • This device comprises a regulator provided with a variable injection sector, the opening of which is adjusted according to the characteristics of the fluid conveyed.
  • adjustable guide vanes controlled by a servo-motor whose action is proportional to the flow rate observed, are oriented so as to obtain an adequate passage section.
  • a high-pressure body 1 conveys the fluid to introduce it radially by an injection sector 2 extending, in this example, over an arc of approximately 140 °.
  • This injection sector 2 comprises, in the central zone, three fixed guide vanes 3, a first group of four guide vanes 4A, 5A, 6A, 7A each orientable by rotation around a pivot 4P, 5P, 6P, 7P and each controlled by an arm 4B, 5B, 6B, 7B secured at dawn and terminated by a roller 4R, 5R, 6R, 7R.
  • These rollers are guided by a groove 8 formed in a control ring 9 concentric with a discharge cylinder 10 whose axis coincides with that of the machine.
  • This injection sector 2 also includes a second group with three guide vanes IIA, 12A, 13A each orientable by rotation about a pivot IIP, 12P, 13P, each controlled by an arm 11B, 12B, 13B secured at dawn and ended with a roller 11R, 12R, 13R.
  • These rollers IIR, 12R, 13R are guided respectively by the grooves 14, 15, 16 of the control ring 9 which, by means of a linkage 17, is actuated by a servo-motor not shown.
  • FIG. 1 represents the injection sector 2 in the position corresponding to the minimum flow rate of the fluid. The latter is expanded by passing through the three channels formed by the three fixed guide vanes 3 and the orientable guide vane 11A.
  • the control crown 9 rotates, clockwise, by an angle proportional to the increase in flow and the guide vanes orientable open successively and gradually depending on the position of the rollers on the ramps of the guide grooves. From the position shown in FIG. 1, the orientable guide vane 4A gradually pivots according to the progression of the roller 4R on the ramp 8R of the groove 8 formed in the control crown 9. However, in order to establish a linear law between the angle of rotation of the control crown 9 and the passage section offered to the fluid, the orientable guide vane IIA begins its rotation before the total opening of the orientable guide vane 4A.
  • the opening control of the adjustable guide vanes 4A, 5A, 6A is carried out by the single ramp 8R of the groove 8 while the opening control of the vanes 11A, 12A, 13A is made by the ramps 14R, 15R, 16R belonging respectively to the grooves 14, 15, 16 formed in the control ring 9.
  • This control ring 9 consists of two co-axial plates 18, 19 of the same diameter, made integral with one another and carrying one 18 the guide grooves 8 and 15 and the other 19 the grooves of guidance 14 and 16.
  • the injection sector may extend over a different arc from that shown in FIG. 1. It is even possible to obtain an injection of the fluid over an opening of the order of 360 °. It is also possible that the order of opening of the orientable guide vanes takes place according to another process. For example, contrary to FIG. 1 where the progressive opening of the injection sector is done by extension of a central zone widening on either side of a minimum opening, an opening can be made. progressive spreading on one side of the minimum opening.
  • FIG. 3 represents the orientable guide vane 4A in the fully open position while the orientable guide vane 5A is still completely closed.
  • all the blades have an aerodynamic profile in the shape of a very flat triangle.
  • the base of this triangle determines with its long side an edge which is the trailing edge of the blade and with its short side another edge which constitutes the leading edge of the blade.
  • the apex of the triangle is rounded according to a curvature concentric with the pivot of the blade so as to determine a range on which the trailing edge of the neighboring blade can bear. This range, called neutral zone, allows the neighboring blade to keep the same position whatever the orientation of the blade on which it rests,
  • the orientable guide vane 5A rests by its trailing edge on the neutral zone of the guide vane orientable 4A. Therefore, the orientation of the steerable guide vane 4A can vary without changing the orientation of the steerable guide vane 5A.
  • This configuration makes it possible not to create parasitic openings, generating eddies which modify the flow of the fluid and reduce the efficiency of the fluid expansion.
  • FIG. 3 also shows an implantation of the pivots of the orientable guide vanes on the high-pressure body 1 so as to form converging channels, whatever the degree of opening of the vanes, to allow suitable relaxation of the fluids conveyed.
  • the steerable guide vanes shown in Figure 3 have two wings which, counted from the axis of the pivot of the blade, are of unequal sizes. This asymmetry allows by the play of pressures applied to the different faces of the triangle to obtain a resulting torque always acting in the same direction and to allow on the one hand to the whole linkage to work without shaking and on the other hand to the roller, located at the end of the arm, to remain applied to the same flank of the groove made in the control ring 9.
  • the result of the forces acting on the different forces of the orientable guide vane 6A results in a torque acting in the anticlockwise to apply the roller 6R on the lower side of the groove 8.
  • the regulator with variable injection sector equips the high-pressure body with a centriped turbine. It is obvious that the same device can equip both the high and low pressure bodies of this turbine.
  • control ring 9 is ' consisting of two independent co-axial plates actuated independently or simultaneously, - depending on the sequence, by a linkage to achieve a progressive opening or closing of the sector of injection (2).
  • This latter arrangement makes it possible in particular to produce an opening from 0 9 to 360 ° with reduced rotation of the control ring 9.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Control Of Turbines (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Superconductors And Manufacturing Methods Therefor (AREA)
  • Supercharger (AREA)
EP82200035A 1981-01-21 1982-01-14 Turbine mit regelbarem Einlassquerschnitt Expired EP0056669B1 (de)

Priority Applications (1)

Application Number Priority Date Filing Date Title
AT82200035T ATE23905T1 (de) 1981-01-21 1982-01-14 Turbine mit regelbarem einlassquerschnitt.

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
EP81870007A EP0056569A1 (de) 1981-01-21 1981-01-21 Turbine mit regelbarem Einlassquerschnitt
EP81870007 1981-01-21

Publications (2)

Publication Number Publication Date
EP0056669A1 true EP0056669A1 (de) 1982-07-28
EP0056669B1 EP0056669B1 (de) 1986-11-26

Family

ID=8188745

Family Applications (2)

Application Number Title Priority Date Filing Date
EP81870007A Withdrawn EP0056569A1 (de) 1981-01-21 1981-01-21 Turbine mit regelbarem Einlassquerschnitt
EP82200035A Expired EP0056669B1 (de) 1981-01-21 1982-01-14 Turbine mit regelbarem Einlassquerschnitt

Family Applications Before (1)

Application Number Title Priority Date Filing Date
EP81870007A Withdrawn EP0056569A1 (de) 1981-01-21 1981-01-21 Turbine mit regelbarem Einlassquerschnitt

Country Status (3)

Country Link
EP (2) EP0056569A1 (de)
AT (1) ATE23905T1 (de)
DE (1) DE3274480D1 (de)

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0332354A1 (de) * 1988-03-08 1989-09-13 Honda Giken Kogyo Kabushiki Kaisha Turbine mit Verstelleinrichtung
WO2009086959A1 (de) * 2008-01-11 2009-07-16 Continental Automotive Gmbh Leitschaufel für eine variable turbinengeometrie
DE102009057987A1 (de) * 2009-12-11 2011-06-16 Bosch Mahle Turbo Systems Gmbh & Co. Kg Ladeeinrichtung

Families Citing this family (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE19741992A1 (de) * 1997-09-24 1999-03-25 Voith Hydro Gmbh & Co Kg Strömungsmaschine, insbesondere Wasserturbine
DE19936507A1 (de) * 1999-08-05 2001-02-15 3K Warner Turbosystems Gmbh Turbinenleitschaufel für einen Abgas-Turbolader
AT411615B (de) * 2000-10-31 2004-03-25 Blank Otto Ing Abgasturbolader für eine brennkraftmaschine

Citations (12)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR918317A (fr) * 1945-08-10 1947-02-05 Brandt Edgar Ets Turbo-soufflante à gaz d'échappement alimentant un moteur à combustion interne à grande variation de vitesse
CH254459A (de) * 1945-03-02 1948-04-30 Berger Hans Abgasturbolader.
GB704351A (en) * 1951-03-21 1954-02-17 Alan Muntz & Co Ltd Improvements in and relating to turbines operated by gases supplied by free-piston gas-generators
GB731822A (en) * 1952-03-14 1955-06-15 Power Jets Res & Dev Ltd Improvements relating to turbines or compressors for operation with gaseous fluids
US2985427A (en) * 1955-11-25 1961-05-23 Gen Electric Adjustable blading for fluid flow machines
US3029067A (en) * 1956-05-31 1962-04-10 Garrett Corp Variable area nozzle means for turbines
US3243159A (en) * 1964-04-27 1966-03-29 Ingersoll Rand Co Guide vane mechanism for centrifugal fluid-flow machines
FR2064617A5 (de) * 1969-09-22 1971-07-23 Garrett Corp
FR2162662A1 (de) * 1971-12-11 1973-07-20 Lucas Aerospace Ltd
US3799689A (en) * 1971-05-14 1974-03-26 Hitachi Ltd Operating apparatus for guide vanes of hydraulic machine
US4179247A (en) * 1977-01-14 1979-12-18 Wrr Industries, Inc. Turbocharger having variable area turbine nozzles
EP0009843A1 (de) * 1978-10-05 1980-04-16 ATELIERS DE CONSTRUCTIONS ELECTRIQUES DE CHARLEROI (ACEC) Société Anonyme Entspannungsturbinen-Generator-Einheit

Patent Citations (12)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CH254459A (de) * 1945-03-02 1948-04-30 Berger Hans Abgasturbolader.
FR918317A (fr) * 1945-08-10 1947-02-05 Brandt Edgar Ets Turbo-soufflante à gaz d'échappement alimentant un moteur à combustion interne à grande variation de vitesse
GB704351A (en) * 1951-03-21 1954-02-17 Alan Muntz & Co Ltd Improvements in and relating to turbines operated by gases supplied by free-piston gas-generators
GB731822A (en) * 1952-03-14 1955-06-15 Power Jets Res & Dev Ltd Improvements relating to turbines or compressors for operation with gaseous fluids
US2985427A (en) * 1955-11-25 1961-05-23 Gen Electric Adjustable blading for fluid flow machines
US3029067A (en) * 1956-05-31 1962-04-10 Garrett Corp Variable area nozzle means for turbines
US3243159A (en) * 1964-04-27 1966-03-29 Ingersoll Rand Co Guide vane mechanism for centrifugal fluid-flow machines
FR2064617A5 (de) * 1969-09-22 1971-07-23 Garrett Corp
US3799689A (en) * 1971-05-14 1974-03-26 Hitachi Ltd Operating apparatus for guide vanes of hydraulic machine
FR2162662A1 (de) * 1971-12-11 1973-07-20 Lucas Aerospace Ltd
US4179247A (en) * 1977-01-14 1979-12-18 Wrr Industries, Inc. Turbocharger having variable area turbine nozzles
EP0009843A1 (de) * 1978-10-05 1980-04-16 ATELIERS DE CONSTRUCTIONS ELECTRIQUES DE CHARLEROI (ACEC) Société Anonyme Entspannungsturbinen-Generator-Einheit

Cited By (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0332354A1 (de) * 1988-03-08 1989-09-13 Honda Giken Kogyo Kabushiki Kaisha Turbine mit Verstelleinrichtung
WO2009086959A1 (de) * 2008-01-11 2009-07-16 Continental Automotive Gmbh Leitschaufel für eine variable turbinengeometrie
JP2011509371A (ja) * 2008-01-11 2011-03-24 コンチネンタル オートモーティヴ ゲゼルシャフト ミット ベシュレンクテル ハフツング 可変のタービンジオメトリのためのガイドベーン
DE102009057987A1 (de) * 2009-12-11 2011-06-16 Bosch Mahle Turbo Systems Gmbh & Co. Kg Ladeeinrichtung
US8662836B2 (en) 2009-12-11 2014-03-04 Bosch Mahle Turbo Systems Gmbh & Co. Kg Charging device
DE102009057987B4 (de) * 2009-12-11 2020-08-20 BMTS Technology GmbH & Co. KG Ladeeinrichtung und Leitschaufel für eine derartige Ladeeinrichtung

Also Published As

Publication number Publication date
ATE23905T1 (de) 1986-12-15
DE3274480D1 (en) 1987-01-15
EP0056669B1 (de) 1986-11-26
EP0056569A1 (de) 1982-07-28

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