EP0289697B1 - Dispositif de commande d'aubes de guidage à calage variable pour turbomachine axiale - Google Patents

Dispositif de commande d'aubes de guidage à calage variable pour turbomachine axiale Download PDF

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Publication number
EP0289697B1
EP0289697B1 EP88100363A EP88100363A EP0289697B1 EP 0289697 B1 EP0289697 B1 EP 0289697B1 EP 88100363 A EP88100363 A EP 88100363A EP 88100363 A EP88100363 A EP 88100363A EP 0289697 B1 EP0289697 B1 EP 0289697B1
Authority
EP
European Patent Office
Prior art keywords
adjusting ring
adjusting
ring
guide vane
guide vanes
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 - Lifetime
Application number
EP88100363A
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German (de)
English (en)
Other versions
EP0289697A1 (fr
Inventor
Edmund Owsianny
Wilfried Wengorz
Emil Aschenbruck
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.)
MAN Gutehoffnungshutte GmbH
Original Assignee
MAN Gutehoffnungshutte GmbH
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Filing date
Publication date
Application filed by MAN Gutehoffnungshutte GmbH filed Critical MAN Gutehoffnungshutte GmbH
Publication of EP0289697A1 publication Critical patent/EP0289697A1/fr
Application granted granted Critical
Publication of EP0289697B1 publication Critical patent/EP0289697B1/fr
Anticipated expiration legal-status Critical
Expired - Lifetime 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
    • F01D17/162—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

Definitions

  • the invention relates to an adjusting device for the guide vanes of an axial flow machine of the type specified in the preamble of the claim.
  • An adjustment device of this type is known from DE-A 3 519 747. It enables the angle of attack of the guide vanes to be changed during operation of the turbomachine, in particular a turbocompressor, and thereby the behavior of the machine to different operating conditions, e.g. Part load and full load, adapt and reduce efficiency losses.
  • the adjusting ring is connected to the levers of the guide vanes by simple hinge pins and is supported by them, and is therefore not guided separately on the housing.
  • the articulated connections by means of the hinge pins must have sufficient play so that the adjustment movement, in which the adjustment ring and the levers rotate in different planes, is possible.
  • the inevitable thermal expansions also require sufficient play in the joint connections.
  • Adjustment devices for guide vanes are also known, in which the guide vanes are connected in an articulated manner via levers to an adjusting sleeve which is displaceable in the axial direction, such as e.g. according to DE-C 3 125 639.
  • Axially displaceable adjusting sleeves have the disadvantage that adjacent guide vane rings can only be adjusted together, but not individually.
  • the known adjusting devices are intended for use in the low temperature range, in particular in the case of compressors or the compression stage of open gas turbines.
  • the support means have an outer axis and an inner cover ring, each blade having a radial pivot at its outer end. A number of the pivots have a greater radial length than the other pivots.
  • Ball bearings are located in the outer housing for rotatable mounting of the longer trunnions.
  • the other pivots have trunnion bearings.
  • Each vane has at its inner end a radially inwardly projecting pivot which is rotatably mounted in the inner cover ring.
  • the longer outer pivot guide vanes are such. B. made of steel, the remaining guide vanes made of aluminum alloy.
  • GB-A 621 175 describes one with successive rows of. to adjust their staggering angle of rotatably mounted guide vanes (multi-stage) axial compressor, axial turbine or similar turbomachine with blades rotatably mounted in seats formed by axially successive rings, the rings of two successive rows of guide vanes interacting so that they interact between them Form the cover band for the intermediate row of blades and with the guide blades a continuous inner surface between the inlet and outlet of the machine. Ball or roller bearings are provided for the rings.
  • DE-A 2 448 572 is concerned with a blade rotation mechanism for a blade grille, which is arranged in the housing at the front and / or behind an impeller, in particular a centrifugal pump.
  • the mechanism consists of a drive unit, a transmission and a regulation.
  • the blade housing is composed of an inner part and an outer part, a groove for guiding a regulating ring being arranged in the wall of the inner part.
  • the blades are rotatably mounted in the housing and the pins of the blades are provided with a crank which has a first cylindrical pin at the lower end and is connected to a second pin of the regulating ring by a pull rod.
  • the regulating ring is connected to a transmission, which consists of an oscillating tie rod, a spindle, a worm wheel and a worm shaft. To regulate the delivery head of the pump, the blade rotating mechanism is actuated via a drive shaft.
  • the invention has for its object to improve an adjusting device of the type mentioned so that a smooth, compact and largely protected against external influences construction is created, which can also be designed for use in the high temperature range and in which those acting on the guide vanes Forces are absorbed largely without play, so that vibrations do not occur, but on the other hand the adjustment movements can play smoothly and with little wear.
  • the guide vanes 1 of a guide vane ring of the machine have shafts 1a which are rotatably mounted in radial bearing bores of an annular guide vane carrier 12, specifically in bearing bushes 2 which have an outer flange 2a and are fixed in the bearing bore by means of a screwed-in ring nut 3.
  • a lever 4 is fitted on the elongated shaft 1 a of the guide vane in a rotationally fixed manner by means of a feather key 17. The lever 4 is supported against the end of the bearing bush 2 projecting beyond the guide vane carrier 12.
  • a plate spring 16 presses on the upper side of the lever 4 and is supported by a washer 15 against a crown nut 14 screwed onto a threaded end 1 of the shaft 1a.
  • the plate spring 16 exerts on the shaft 1a an upward biasing force in FIG. 2, by means of which a flange 1 of the shaft 1a is pressed against the lower end face of the bearing bush 2.
  • the shaft 1a is axially free of play in the bearing bush 2, and is clamped elastically and to dampen vibrations against thermal expansion.
  • the guide vane carrier 12 is inserted in a dust-tight manner into an annular recess in a carrier ring 13.
  • An adjusting ring 7 is rotatably guided in a groove 13a of the carrier ring 13.
  • the radial direction is guided by radial rollers 10 which are arranged in the groove 13a and are mounted on the carrier ring 13 by means of bearing pins 11.
  • the guidance in the axial direction is carried out by axial rollers 8, which are mounted on the adjusting ring 7 by means of bearing pins 9, with their preferably spherical peripheral surfaces project a little beyond the end face of the adjusting ring 7 and bear against the axial boundary surfaces of the groove 13a.
  • the carrier ring 13 is divided into two halves in a suitable axial plane and these are connected to one another by means of fastening means (not shown).
  • the adjusting ring 7 has a number of cylindrical axial bores 7a, which are open to the inner peripheral surface of the adjusting ring 7, in accordance with the number of guide vanes.
  • Cylinder bolts 6 are rotatably and axially displaceable therein.
  • Each cylinder pin 6 has an axially perpendicular bore in which a pin 5, which is axially parallel to the shaft 1a of the guide vane and is connected to the lever 4, is rotatably mounted.
  • an extension 19 is provided on the adjusting ring 7, which projects outwards through a recess in the carrier ring 13 and on which an adjusting spindle 21 engages by means of a cylinder bearing 20.
  • This is guided through a passage 18a of the outer housing 18 of the turbomachine, a gas and dust-tight seal being achieved by means of an elastic bellows 22 which is fastened to the bushing 18a by means of a flange 23.
  • any manual or motor-operated adjusting drive can engage in order to move the spindle 21 in its axial direction and thereby to rotate the adjusting ring 7 in its circumferential direction according to the arrow 24.
  • the entire adjustment mechanism is encapsulated in a dust-tight manner in the space enclosed by the carrier ring 13 and the guide vane carrier 12 inserted therein.
  • the entire adjustment device is of compact construction, which does not take up much more space in the axial direction than the guide vane ring itself. It is therefore easily possible to equip axially closely adjacent guide vane rings with such an adjustment device.
  • the adjustment movement generated by the externally arranged (not shown) actuator via the adjustment spindle 21 is introduced into the interior of the machine in a gas-tight manner, without sealing gas and maintenance-free, via the metal bellows 22.
  • the entire adjustment device is designed due to its compact design so that it is also suitable for retrofitting to existing machines.

Claims (3)

1. Dispositif de réglage pour les aubes directrices d'une turbo-machine axiale, avec un support d'aubes directrices annulaire comportant des alésages de paliers radiaux dans lesquels sont montés, de façon a pouvoir tourner autour de leurs axes, les fûts des aubes directrices, avec des leviers disposes sur les faces externes du support d'aubes directrices et solidaires en rotation des fûts des aubes directrices, avec un anneau de réglage dispose coaxialement par rapport au support d'aubes directrices et auquel sont articulées les extrémités des leviers, et avec un entraînement de réglage grâce auquel l'anneau de réglage est susceptible d'être déplace dans sa direction périphérique, l'anneau de réglage tournant dans une gorge fermée sur trois cotes et étant monté en direction radiale sur des galets, dispositif de réglage caractérisé en ce qu'il est prévu un anneau porteur (13) dans lequel est ménagée la gorge (13a) dont l'ouverture est dirigée radialement vers l'intérieur, tandis que le support annulaire (12) des aubes directrices est mis en place dans la gorge (13a) de façon qu'il ferme, de façon étanche, l'ouverture de cette gorge, cependant que les leviers (4) et leurs liaisons par articulation avec l'anneau de réglage (7) sont placés à l'intérieur de la gorge et sont ainsi protégés.
2. Dispositif de réglage selon la revendication 1, caractérisé en ce que l'anneau de réglage (7) est également monte axialement au moyen de galets (9) dans la gorge (13a), tandis que les galets (10) servant au montage radial de l'anneau de réglage sont montes contre la face externe de l'anneau de réglage (7) dans la gorge (13a).
3. Dispositif de réglage selon la revendication 1, caractérisé en ce que la liaison par articulation entre chaque levier (4) et l'anneau de réglage (7) est constituée par un axe cylindrique (6) qui est monté, en étant susceptible de tourner et de se déplacer axialement parallèlement à l'axe de l'anneau de réglage, dans un évidement cylindrique de l'anneau de réglage, ouvert vers la face périphérique interne de cet anneau, et par une broche (5), disposée perpendiculairement à l'axe cylindrique (6) et insérée respectivement dans un perçage de l'axe cylindrique (6) et du levier (4), cette broche étant susceptible de tourner dans un de ces perçages.
EP88100363A 1987-04-03 1988-01-13 Dispositif de commande d'aubes de guidage à calage variable pour turbomachine axiale Expired - Lifetime EP0289697B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE19873711224 DE3711224A1 (de) 1987-04-03 1987-04-03 Verstelleinrichtung fuer die leitschaufeln einer axialstroemungsmaschine
DE3711224 1987-04-03

Publications (2)

Publication Number Publication Date
EP0289697A1 EP0289697A1 (fr) 1988-11-09
EP0289697B1 true EP0289697B1 (fr) 1990-09-19

Family

ID=6324773

Family Applications (1)

Application Number Title Priority Date Filing Date
EP88100363A Expired - Lifetime EP0289697B1 (fr) 1987-04-03 1988-01-13 Dispositif de commande d'aubes de guidage à calage variable pour turbomachine axiale

Country Status (4)

Country Link
US (1) US4836746A (fr)
EP (1) EP0289697B1 (fr)
JP (1) JP2844067B2 (fr)
DE (2) DE3711224A1 (fr)

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DE4102188C2 (de) * 1991-01-25 1994-09-22 Mtu Muenchen Gmbh Leitschaufel-Verstelleinrichtung einer Turbine eines Gasturbinentriebwerks
US6092984A (en) * 1998-12-18 2000-07-25 General Electric Company System life for continuously operating engines
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ITTO20010444A1 (it) * 2001-05-11 2002-11-11 Fiatavio Spa Turbina assiale per applicazioni aeronautiche.
DE10311205B3 (de) * 2003-03-14 2004-09-16 Man B & W Diesel Ag Leitapparat für eine Radialturbine
DE10316389B3 (de) * 2003-04-10 2004-01-22 Mtu Friedrichshafen Gmbh Leiteinrichtung für einen Abgasturbolader
US20060029494A1 (en) * 2003-05-27 2006-02-09 General Electric Company High temperature ceramic lubricant
EP1669548A1 (fr) * 2004-12-08 2006-06-14 ABB Turbo Systems AG Système d'aubes de guidage réglable pour une turbine à gaz
US7543992B2 (en) * 2005-04-28 2009-06-09 General Electric Company High temperature rod end bearings
US7753647B2 (en) * 2005-07-20 2010-07-13 United Technologies Corporation Lightweight cast inner diameter vane shroud for variable stator vanes
US7665959B2 (en) * 2005-07-20 2010-02-23 United Technologies Corporation Rack and pinion variable vane synchronizing mechanism for inner diameter vane shroud
US7588415B2 (en) * 2005-07-20 2009-09-15 United Technologies Corporation Synch ring variable vane synchronizing mechanism for inner diameter vane shroud
EP1820941A1 (fr) * 2006-02-09 2007-08-22 Siemens Aktiengesellschaft Agencement d'aubes de guidage
EP1840386A1 (fr) * 2006-03-31 2007-10-03 ABB Turbo Systems AG Dispositif de prérotation
WO2008124758A1 (fr) * 2007-04-10 2008-10-16 Elliott Company Compresseur centrifuge comportant des aubes de guidage d'admission ajustables
EP2006494A1 (fr) * 2007-06-20 2008-12-24 ABB Turbo Systems AG Engrenage pour dispositif de conduite à prérotation
CN102444426B (zh) 2010-09-30 2015-05-27 阿尔斯通技术有限公司 改装汽轮机的方法
JP5747703B2 (ja) * 2011-07-13 2015-07-15 株式会社Ihi ターボ圧縮機
JP2014198999A (ja) 2012-02-23 2014-10-23 三菱重工業株式会社 圧縮機
US9422825B2 (en) 2012-11-05 2016-08-23 United Technologies Corporation Gas turbine engine synchronization ring
TWI518250B (zh) 2013-11-01 2016-01-21 財團法人工業技術研究院 進口導向葉片裝置
JP6298529B2 (ja) * 2014-07-10 2018-03-20 三菱日立パワーシステムズ株式会社 可変静翼装置のメンテナンス方法及び可変静翼装置
DE102015006080A1 (de) 2015-05-09 2016-11-10 Man Diesel & Turbo Se Kompressor
TWI544151B (zh) 2015-11-12 2016-08-01 財團法人工業技術研究院 結合進氣導葉的內流道氣體旁通裝置
US10563670B2 (en) * 2016-07-29 2020-02-18 Rolls-Royce Corporation Vane actuation system for a gas turbine engine
GB201616108D0 (en) * 2016-09-22 2016-11-09 Rolls Royce Plc Gas turbine engine
RU192552U1 (ru) * 2017-08-29 2019-09-23 Акционерное общество "Объединенная двигателестроительная корпорация" (АО "ОДК") Конструкция синхронизирующего кольца поворотной лопатки направляющего аппарата компрессора турбомашины
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Also Published As

Publication number Publication date
JPS63255501A (ja) 1988-10-21
US4836746A (en) 1989-06-06
DE3711224A1 (de) 1988-10-13
EP0289697A1 (fr) 1988-11-09
DE3860636D1 (de) 1990-10-25
JP2844067B2 (ja) 1999-01-06
DE3711224C2 (fr) 1990-08-09

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