EP2261466A1 - Dispositif de réglage et aubes directrices d'une turbine - Google Patents

Dispositif de réglage et aubes directrices d'une turbine Download PDF

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Publication number
EP2261466A1
EP2261466A1 EP09007624A EP09007624A EP2261466A1 EP 2261466 A1 EP2261466 A1 EP 2261466A1 EP 09007624 A EP09007624 A EP 09007624A EP 09007624 A EP09007624 A EP 09007624A EP 2261466 A1 EP2261466 A1 EP 2261466A1
Authority
EP
European Patent Office
Prior art keywords
adjusting
turbine
guide vanes
vanes
adjusting device
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.)
Withdrawn
Application number
EP09007624A
Other languages
German (de)
English (en)
Inventor
Roderich Bryk
Björn Buchholz
Jens Sander
Vadim Shevchenko
Stephan Sonnen
Oliver Dr. Strohmeier
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.)
Siemens AG
Original Assignee
Siemens 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 AG filed Critical Siemens AG
Priority to EP09007624A priority Critical patent/EP2261466A1/fr
Publication of EP2261466A1 publication Critical patent/EP2261466A1/fr
Withdrawn legal-status Critical Current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
    • 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
    • F04D29/52—Casings; Connections of working fluid for axial pumps
    • F04D29/54—Fluid-guiding means, e.g. diffusers
    • F04D29/56—Fluid-guiding means, e.g. diffusers adjustable
    • F04D29/563—Fluid-guiding means, e.g. diffusers adjustable specially adapted for elastic fluid pumps
    • 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
    • F05D2260/00—Function
    • F05D2260/30—Retaining components in desired mutual position
    • 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
    • F05D2260/00—Function
    • F05D2260/50—Kinematic linkage, i.e. transmission of position
    • F05D2260/52—Kinematic linkage, i.e. transmission of position involving springs

Definitions

  • the invention relates to an adjusting device for guide vanes of a turbine, in particular an adjusting device for guide vanes of the compressor part of a gas turbine.
  • a turbine in particular a gas turbine, is divided in the axial direction usually into a compressor part (in which the fluid flowing through the turbine is compressed) and a turbine part (in which the fluid is expanded with the development of mechanical energy).
  • turbine is used below generally for both the compressor part of a turbine (or gas turbine), as well as for the "actual” turbine part of the gas or steam turbine.
  • the turbine normally comprises a housing.
  • a rotatable rotor is accommodated, on whose circumference in each case a plurality of turbine blades (blades) are arranged in several rows.
  • a row of guide vanes is usually arranged in each case between two rows of blades. The vanes are - fixed in place on the housing - in contrast to the blades.
  • the vanes serve to direct the flowing gas directed at the blades.
  • the vanes are usually pivotable about their longitudinal axis.
  • an adjusting device is provided which comprises a housing enclosing, rotatable adjusting ring, which has a Lever all vanes of a row of vanes uniformly pivoted according to its own rotation.
  • the adjusting ring is usually rotated by means of an adjusting drive.
  • the vanes remain either rigidly in the last occupied position or pivot due to external forces in an undefined position. As a result, the turbine operation can be significantly disturbed.
  • the invention has for its object to provide an adjustment for vanes of a turbine, which allows a particularly safe operation of the same.
  • the adjusting device comprises an adjusting mechanism coupled to the guide vanes for the reversible pivoting of the guide vanes about their respective axis.
  • the adjusting device further comprises an adjusting drive, which acts on the adjustment mechanism for actuating the latter.
  • the adjusting device comprises at least one - indirectly or directly - acting on the or each vane spring element that transfers the or each vane in case of deactivation or failure of the respective associated adjustment drive in a defined default position.
  • the adjusting mechanism coupled to the guide vanes is transferred into a defined rest position.
  • the adjusting device according to the invention advantageously allows the use of a merely unidirectionally operating adjusting drive or only unidirectionally force-transmitting components of the adjusting mechanism (for example Bowden cables), since the return of the guide vanes to the failure position is effected by the or each spring element.
  • the adjusting drive is formed by a hydraulic drive, alternatively by a pneumatic drive.
  • a substantially rigid adjustment mechanism which acts on all vanes of a row of vanes, so that they are always pivoted simultaneously and together.
  • This adjusting mechanism is preferably formed essentially by an adjusting ring, the -. B. via a lever device - is coupled to the vanes of the vane row, and by the - in particular a single - adjustment is rotatable.
  • several adjusting drives are each coupled via the associated adjusting mechanism with a single vane or with a group of vanes.
  • the adjusting mechanism has at least one damping element for non-abrupt, but only gradual pivoting of the guide vanes in their default position.
  • the damping element prevents a sudden twisting of the adjusting ring. This is to avoid that the adjustable vanes are abruptly - within a very short time - swung into your default position.
  • the fuel supply can be tracked and adapted to the changing gas mass flow without the gas turbine during which reaches harmful operating conditions.
  • a rigid, in particular annular adjustment mechanism which is - in particular a single - spring element preferably between the adjustment - in particular the adjusting - and a stationary turbine part - in particular a turbine housing - spanned.
  • the spring element thus acts only indirectly, namely on the adjusting mechanism, on the vanes.
  • a single spring element in particular directly, acts on each of the guide vanes.
  • the or each spring element can also be effectively attached to a drive part of the adjustment drive that actuates the adjustment mechanism.
  • the spring element is formed by a screw, a leaf or a leg spring.
  • a damping element for example, a shock absorber is provided.
  • a "closed” or “open” vane position may preferably be selected depending on the nature of the turbine and its location as a default position in which the vanes are reset under the action of the or each spring element defined.
  • the closed position is that position in which the vane, or its vane blade, is substantially transverse to the axial direction of the turbine. If all the guide vanes are in this position, in particular an operating point is set here, which corresponds to a minimum gas mass flow flowing through the row of guide vanes.
  • the closed position for example, in a so-called "Peaker machine", which is briefly used only for peak load cover, preferably be selected as a default position, but this is not mandatory.
  • the opened position is correspondingly the position in which the vane, or its vane blade, is substantially longitudinal to the axial direction of the turbine. If all the guide vanes are in this failure position, an operating point corresponding to a maximum gas mass flow is correspondingly set here.
  • the open position for example, in a so-called base load machine preferably be selected as a default position, but this is not mandatory here.
  • the failure position may be dependent on further different boundary conditions, such as, for example, the location of the gas turbine and / or existing climatic conditions on the site.
  • boundary conditions such as, for example, the location of the gas turbine and / or existing climatic conditions on the site.
  • Other boundary conditions are still conceivable.
  • a vane position lying between the closed and the open position can also be selected as the default position.
  • FIG. 1 shows a partial longitudinal section through a compressor 1 of a gas turbine 2.
  • Gas turbine 2 and the compressor 1 is oriented substantially horizontally in the illustration.
  • the compressor 1 comprises a roughly cylindrical housing 4, which accommodates a (not shown here) rotor with a plurality of axially in the axial direction 3 series of blades.
  • Each blade row comprises a plurality of rotor blades uniformly distributed over the circumference of the rotor (also not shown here).
  • the rotor blades essentially serve to compress the gas 6 intended to flow in the direction of flow 5 through the compressor 1.
  • a stationary guide blade row 7 is arranged in each case between two (rotatable) blade rows.
  • the present presentation is restricted to the area of a single row of guide vanes 7.
  • Each guide vane row 7 in turn comprises a plurality of vanes 8 uniformly distributed over the inner circumference of the housing 4.
  • Each vane 8 is aligned with its axis 9 essentially in the radial direction of the compressor 1.
  • Each guide blade 8 comprises an airfoil 10, on which radially on the inside a shaft 11, and radially outside a spindle 12 is mounted.
  • each vane 8 Radially inside each vane 8 is supported with its shaft 11 in each case in a corresponding bushing 13 of an inner ring 14 mounted on the rotor.
  • each lever 18 belonging to a lever 18 is mounted substantially rigidly at the same at this rigid.
  • Each lever 18 in turn is connected in each case via a bearing 19 hingedly connected to an adjusting ring 20.
  • the adjusting ring 20, as well as the lever device 17 are parts of a assembly referred to here as adjustment 21.
  • the adjusting mechanism 21 is in turn part of an adjusting device 22.
  • the adjusting ring 20 is rotatably mounted radially on the outside with bearing elements 23 on the housing 4, wherein its axis of rotation is substantially concentric with the axis of the gas turbine 2 and the compressor 1 is aligned.
  • a rotation of the adjusting ring 20 via the lever device 17 causes a uniform simultaneous pivoting of all vanes 8 about their respective axis.
  • the guide vanes 8 can in principle be adjusted to any desired position.
  • the first, referred to as "closed" end position is reached when the blades 10 of all vanes 8 are placed with their respective blade surface substantially transverse to the flow direction 5, that is, if the free flow area in the region of the guide blade row 7 is reduced to a minimum.
  • the second, referred to as "open" end position is accordingly reached when the blades 10 of all vanes 8 are placed with their respective blade surface substantially parallel to the flow direction 5, so if the free flow area in the region of the guide blade row 7 is maximum.
  • FIG. 2 the adjusting device 22 is shown in a schematic schematic diagram.
  • the adjusting device 22 comprises the adjusting mechanism 21, with the adjusting ring 20, which acts on the guide vanes 8 via the lever device 17 (not shown here).
  • the adjusting device 22 further comprises an adjusting drive 30.
  • the adjusting drive 30 is formed by a hydraulic unit, which comprises a piston 32 movably received in a cylinder 31.
  • the punch 32 is connected to the rotation of the adjusting ring 20 via a boom 33 with this.
  • the adjustment may be deviating also formed by a pneumatic unit.
  • a spring element 35 (here in the form of a helical compression spring) with its first end 36 is attached.
  • a transversal movement of the punch 32 causes a rotational movement of the adjusting ring 20, also indicated by an arrow 41, whereby a restoring force F (directed essentially tangentially to the adjusting ring 20) of the spring element 35 is overcome.
  • the adjusting ring 20 is rotated from a rest position into a - shown by dashed lines - working position.
  • the spring element 35 is transferred from a relaxed rest position into a tensioned working position (not shown for clarity).
  • the spring element 35 relaxes back to its rest position, wherein the adjusting ring 20 by the arm 34 acting on the restoring force F also back is gradually and not abruptly transferred to its rest position. The gradual return is accomplished by a corresponding, not shown damper element.
  • the gas turbine 2 is used for base load coverage.
  • the rest position of the adjusting ring 20 is in this case selected such that it corresponds to the previously described open failure position of the guide vanes 8.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Control Of Turbines (AREA)
EP09007624A 2009-06-09 2009-06-09 Dispositif de réglage et aubes directrices d'une turbine Withdrawn EP2261466A1 (fr)

Priority Applications (1)

Application Number Priority Date Filing Date Title
EP09007624A EP2261466A1 (fr) 2009-06-09 2009-06-09 Dispositif de réglage et aubes directrices d'une turbine

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP09007624A EP2261466A1 (fr) 2009-06-09 2009-06-09 Dispositif de réglage et aubes directrices d'une turbine

Publications (1)

Publication Number Publication Date
EP2261466A1 true EP2261466A1 (fr) 2010-12-15

Family

ID=41382412

Family Applications (1)

Application Number Title Priority Date Filing Date
EP09007624A Withdrawn EP2261466A1 (fr) 2009-06-09 2009-06-09 Dispositif de réglage et aubes directrices d'une turbine

Country Status (1)

Country Link
EP (1) EP2261466A1 (fr)

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2014205816A1 (fr) * 2013-06-28 2014-12-31 Siemens Aktiengesellschaft Actionneur d'aube directrice d'un compresseur et compresseur l'utilisant
BE1026063B1 (fr) * 2018-03-02 2019-10-03 Safran Aero Boosters S.A. Aube motrice de systeme a calage variable de compresseur pour turbomachine
CN117662524A (zh) * 2024-01-29 2024-03-08 诺顿风机(潍坊)有限公司 一种动导叶的动叶可调轴流风机

Citations (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2854211A (en) * 1955-11-25 1958-09-30 Gen Electric Adjustable vane arrangement for fluid flow machinery
GB813343A (en) * 1955-10-21 1959-05-13 Power Jets Res & Dev Ltd Improvements in or relating to apparatus for the control of ducted fluids
US3025036A (en) * 1960-01-06 1962-03-13 Curtiss Wright Corp Gas turbine speed control
US3360240A (en) * 1966-01-10 1967-12-26 Rolls Royce Vane operating mechanism
US3893784A (en) * 1972-11-08 1975-07-08 Bbc Sulzer Turbomaschinen Apparatus for adjusting stator blades
US4695220A (en) * 1985-09-13 1987-09-22 General Electric Company Actuator for variable vanes
JPH0626352A (ja) * 1992-05-14 1994-02-01 Mitsubishi Heavy Ind Ltd 可変ノズル付過給機
DE10243103A1 (de) 2002-09-17 2004-03-25 Rolls-Royce Deutschland Ltd & Co Kg Vorrichtung zur Verstellung von Kompressorschaufeln einer Gasturbine
DE10351202A1 (de) 2003-11-03 2005-06-02 Mtu Aero Engines Gmbh Vorrichtung zum Verstellen von Leitschaufeln
EP2053204A2 (fr) * 2007-10-22 2009-04-29 United Technologies Corporation Moteur à turbine à gaz avec aubes variables

Patent Citations (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB813343A (en) * 1955-10-21 1959-05-13 Power Jets Res & Dev Ltd Improvements in or relating to apparatus for the control of ducted fluids
US2854211A (en) * 1955-11-25 1958-09-30 Gen Electric Adjustable vane arrangement for fluid flow machinery
US3025036A (en) * 1960-01-06 1962-03-13 Curtiss Wright Corp Gas turbine speed control
US3360240A (en) * 1966-01-10 1967-12-26 Rolls Royce Vane operating mechanism
US3893784A (en) * 1972-11-08 1975-07-08 Bbc Sulzer Turbomaschinen Apparatus for adjusting stator blades
US4695220A (en) * 1985-09-13 1987-09-22 General Electric Company Actuator for variable vanes
JPH0626352A (ja) * 1992-05-14 1994-02-01 Mitsubishi Heavy Ind Ltd 可変ノズル付過給機
DE10243103A1 (de) 2002-09-17 2004-03-25 Rolls-Royce Deutschland Ltd & Co Kg Vorrichtung zur Verstellung von Kompressorschaufeln einer Gasturbine
DE10351202A1 (de) 2003-11-03 2005-06-02 Mtu Aero Engines Gmbh Vorrichtung zum Verstellen von Leitschaufeln
EP2053204A2 (fr) * 2007-10-22 2009-04-29 United Technologies Corporation Moteur à turbine à gaz avec aubes variables

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2014205816A1 (fr) * 2013-06-28 2014-12-31 Siemens Aktiengesellschaft Actionneur d'aube directrice d'un compresseur et compresseur l'utilisant
BE1026063B1 (fr) * 2018-03-02 2019-10-03 Safran Aero Boosters S.A. Aube motrice de systeme a calage variable de compresseur pour turbomachine
CN117662524A (zh) * 2024-01-29 2024-03-08 诺顿风机(潍坊)有限公司 一种动导叶的动叶可调轴流风机
CN117662524B (zh) * 2024-01-29 2024-04-23 诺顿风机(潍坊)有限公司 一种动导叶的动叶可调轴流风机

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