EP2614222B1 - Dispositif de rupture de tourbillon dans un courant de fuite d'une turbomachine - Google Patents

Dispositif de rupture de tourbillon dans un courant de fuite d'une turbomachine Download PDF

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Publication number
EP2614222B1
EP2614222B1 EP11757253.7A EP11757253A EP2614222B1 EP 2614222 B1 EP2614222 B1 EP 2614222B1 EP 11757253 A EP11757253 A EP 11757253A EP 2614222 B1 EP2614222 B1 EP 2614222B1
Authority
EP
European Patent Office
Prior art keywords
turbomachine
housing
swirl
swirl device
rotor
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.)
Not-in-force
Application number
EP11757253.7A
Other languages
German (de)
English (en)
Other versions
EP2614222A1 (fr
Inventor
Andreas Biesen
Johan Flegler
Michael Kleinhaus
Joachim Schettel
Armin De Lazzer
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 EP11757253.7A priority Critical patent/EP2614222B1/fr
Publication of EP2614222A1 publication Critical patent/EP2614222A1/fr
Application granted granted Critical
Publication of EP2614222B1 publication Critical patent/EP2614222B1/fr
Not-in-force legal-status Critical Current
Anticipated expiration legal-status Critical

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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
    • F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
    • F01D11/02—Preventing or minimising internal leakage of working-fluid, e.g. between stages by non-contact sealings, e.g. of labyrinth type
    • 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
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/12—Blades
    • F01D5/22—Blade-to-blade connections, e.g. for damping vibrations
    • 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
    • F05D2240/00—Components
    • F05D2240/10—Stators
    • F05D2240/12—Fluid guiding means, e.g. vanes
    • F05D2240/126—Baffles or ribs
    • 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
    • F05D2260/20—Heat transfer, e.g. cooling
    • F05D2260/231—Preventing heat transfer
    • 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
    • F05D2260/96—Preventing, counteracting or reducing vibration or noise

Definitions

  • the invention relates to a turbomachine having a rotor rotatably mounted about a rotation axis and a housing arranged around the rotor, wherein the housing has a housing inner surface formed with respect to the rotor in a circumferential direction, wherein at least one gap is formed between the rotor and the housing inner surface, wherein a Number of radially extending vanes, each having a Leitschaufelfuß are attached to the housing and in the region of the housing inner surface a swirl crusher for reducing a twist of a leakage flow is arranged. It further relates to a power plant with such a turbomachine.
  • Turbomachines in the context of this invention are, for example, steam turbines, gas turbines or compressors, the invention preferably referring to steam turbines.
  • Turbomachines are characterized by a flow medium. Hydraulic turbines, steam and gas turbines, wind turbines, centrifugal pumps and centrifugal compressors as well as propellers are summarized under the collective term "turbomachinery". All of these machines have in common that they serve the purpose of extracting energy from one fluid in order to drive another machine, or vice versa, to supply energy to a fluid in order to increase its pressure.
  • the energy conversion is indirect and preferably takes the path over the kinetic energy of the fluid.
  • Such turbomachines are used, for example, in power generation in power plants.
  • turbomachines such. B. in steam turbines
  • a flow medium in a main flow direction, which corresponds substantially to the direction of the axis of rotation.
  • the flow medium should ideally only through a so-called flow channel, which has so-called guide vanes and blades.
  • the flow channel is formed of different successively arranged guide and moving blades, wherein the guide vanes are fixed to a Leitschaufelfuß to a housing of the turbomachine, while the blades are fixed to the rotor.
  • the flow medium flows past the guide and moving blades through the flow channel, whereby the kinetic energy of the fluid is converted into rotational energy, which leads to a rotation of the rotor.
  • a first approach is to arrange so-called sealing lips between the rotating and fixed components.
  • the sealing lips are arranged rotationally symmetrically on the rotor and stator and act as a barrier to the leakage flow.
  • the leakage flow leads in turbomachinery to a further effect, which is undesirable.
  • the leakage flow through the gaps can amplify or dampen existing rotor vibrations during operation, which occurs depending on the prevailing boundary conditions.
  • This effect is referred to in fluid mechanics as Spalterregulation.
  • this effect is referred to as Dampfanfachung.
  • the branching off in the direction of the gap Flow medium portion having different directional components, in addition to the main direction component, which leads along the main flow channel also direction components are present, which are directed in the circumferential direction.
  • This circumferentially directed leakage flow component is also referred to as a spin.
  • the gap excitation or vaporization depends on the direction and magnitude of this twist of the leakage flow entering the gap.
  • the leakage flow in turbines has the effect that rather a fanning effect takes place instead of a damping.
  • swirl breakers are understood as meaning components which form a barrier to the leakage flow flowing in the circumferential direction, which is referred to as a swirl.
  • a brake fluid can be injected into the leakage flow in such a way that the twist is thereby minimized or prevented.
  • the swirl breakers are usually formed of individual components and incorporated in a suitable manner in the circumferential direction individually in the housing. This can require a high production cost, which leads to an increased production time.
  • the object of the invention is therefore to provide a turbomachine of the type mentioned above, which can be made quickly and at the same time technically particularly simple design.
  • the invention is based on the consideration that a particularly simple and rapid production of a turbomachine would be possible if the individual swirl crushers could be used in a simple manner without special effort in the construction of the turbomachine.
  • welding operations or similar complicated procedures should be omitted when introducing the individual swirl breaker.
  • This can be achieved by fixing the swirl crushers in a form-fitting manner.
  • the simplest possible structures should be used to fix the swirl crushers. This is accomplished by appropriately modifying the blade roots of adjacent vanes on the housing inner wall, i. H. by inserting corresponding recesses, and the swirl breakers clamped between two adjacent vanes feet, d. H. be fixed positively.
  • a swirl breaker is positively fixed in a plurality of intermediate spaces formed from two adjoining vanes feet. This can be achieved in a simple manner in the entire circumferential direction sufficient suppression of the peripheral components of the leakage flow.
  • the respective intermediate space is formed by recesses which are introduced into the respective adjacent guide blade feet.
  • the guide blade feet thus have recesses which serve as a fit for the swirl breaker to be introduced.
  • the respective swirl breaker is designed as a sheet metal. This allows a particularly simple and inexpensive design. Additionally or alternatively, the respective swirl breaker can advantageously be made of one piece of material, ie. H. made of one piece or piece of sheet metal. If necessary, such a swirl breaker can be used as a standard component in all gaps between the rotor and the housing inner wall. This also simplifies the manufacture and assembly.
  • the swirl breaker advantageously has a section extending in the radial direction, which is fixed in a form-fitting manner in a groove of the housing.
  • the nominal size of the swirl breaker is slightly less than that of the space between the vanes feet. This will ensure that the flow of force passes over the sides of the vanes feet.
  • the respective swirl crusher has a bead, so that it elastically deforms during installation of the guide vanes. He is then secured in the circumferential direction against tilting.
  • a profiling of the sheet by means of a bead can also serve to achieve a stiffening against the attacking flow forces.
  • the leakage flow sometimes has a wide variety of directional components, it depends greatly on the boundary conditions, which form of the swirl breaker is suitable.
  • a swirl breaker wall is conceivable, which has rounded corners, has a triangular shape or has further geometric shapes.
  • the flow of the freely flowing in the part of the swirl breaker can be arranged at an angle relative to the area clamped between two blade roots, that is, the swirl breaker is advantageously bent at a shallow angle in the circumferential direction.
  • the orientation of the swirl breaker is then independent of the orientation of the blade roots.
  • such a turbomachine is used in a power plant.
  • the advantages achieved by the invention are in particular that a particularly simple and cost-effective installation of the swirl crusher in a turbomachine is made possible by a swirl crusher, which is positively fixed between two vanes feet.
  • the swirl breaker is a standard component that can be used in the same way on all gaps between the rotor and the housing of a turbine.
  • the standard component can simply be formed from a sheet which is placed in a suitable recess on the side of a blade root.
  • a subsequent replacement is particularly simple and inexpensive possible.
  • a particularly high efficiency of the turbomachine is achieved by effective spin suppression.
  • radial, axial and circumferential direction also refer in the following to the system of the turbomachine, wherein the direction designation "axially” refers to the axis of rotation.
  • the FIG. 1 shows a turbomachine 1, here as an embodiment of a steam turbine.
  • a turbomachine is a gas turbine or a compressor.
  • the steam turbine comprises an outer housing 2, which is designed as a pot housing.
  • the pot construction is merely exemplary, the invention can also be used in turbines of other designs.
  • a lid 3 is arranged with fastening means.
  • an inner housing 4 is arranged within the outer housing 2.
  • the inner housing 4 has guide vanes 5.
  • the steam turbine 1 has an inflow opening 6 through which steam flows as a flow medium during operation. The flow medium flows through a flow channel 7 past the guide vanes 5.
  • a rotor 8 is rotatably mounted about a rotation axis 9.
  • the rotor 8 comprises rotor blades arranged on the rotor surface 10. For the sake of clarity is in the FIG. 1 only one blade provided with the reference numeral 10.
  • the rotor 8 further comprises a thrust balance piston 11, which is commonly used in high pressure turbine parts with a usual for this type blading.
  • the steam flowing through the steam turbine 1 releases its energy to the rotor 8, which leads to a rotation of the rotor 8.
  • the rotation of the rotor 8 is used, for example, to drive generators or pumps.
  • FIG. 2 is a section of a turbomachine shown.
  • the FIG. 2 shows a portion of a blade 10.
  • the blade 10 has a shroud 12 on. Opposite the shroud 12, the housing inner surface 14 of a portion of the inner housing 4 is shown.
  • the inner housing 4 has sealing lips 16, which are arranged rotationally symmetrically in the circumferential direction. Between the housing inner surface 14 and a surface of the shroud 12 of the blade 10, a gap 18 is formed. A flow of the flow medium through this gap 18 represents a loss that should be prevented or minimized.
  • the leakage flow also has a flow component which takes place in the circumferential direction, ie in FIG. 2 out of the picture plane or into it.
  • a swirl breaker 20 is mounted in the region of the housing inner surface 14.
  • the swirl breaker 20 is designed as a one-piece standard component made of sheet metal, which is fixed in a form-fitting manner between two guide blade feet 22 of two guide vanes 5. For this purpose, corresponding recesses or depressions are introduced into the guide blade feet 22, which serve as a fit for the swirl breakers 20.
  • FIG. 2 only one swirl breaker 20 is shown, but these are distributed rotationally symmetrically over the entire circumference of the turbomachine 1. In this case, the swirl breaker 20 extends in its surface substantially in the radial-axial plane.
  • the swirl breaker 20 has a radially extending Section 26, which engages in the Leitschaufelnut 28.
  • the dimensions of the swirl breaker 20 are chosen for a clearance fit.
  • the swirl crusher further has a ground edge 29 facing the shroud 12 in the installed state. This is to prevent that in the case of a touch, not the entire side surface of the swirl breaker 20 touches the shroud 12 and excessively damaged.
  • FIG. 3 is a view of the swirl breaker 20 in the circumferential direction.
  • the swirl breaker 20 has a bead 30 which extends initially in the radial direction over the radial section 26, and then over the remaining axial section. This serves on the one hand to stiffen the component, on the other hand, the swirl crusher 20 can be elastically deformed during installation so that it is secured against tilting.
  • FIG. 4 shows a corresponding view of the swirl breaker 20 in the axial direction.
  • FIG. 5 shows the swirl breaker 20 from the radial direction, wherein a bend of the swirl breaker 20 at the base of the radial portion 26 can be seen.
  • the swirl breaker 20 is bent at a flat angle about a bending axis 32 running in the radial direction.
  • the proposed here swirl breaker is a standard component, which allows a particularly simple and inexpensive construction of a turbomachine 1.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)

Claims (10)

  1. Turbomachine ayant un rotor ( 8 ) monté tournant autour d'un axe ( 9 ) de rotation et une carcasse ( 4, 2 ) disposée autour du rotor ( 8 ),
    dans laquelle la carcasse ( 4, 2 ) a une surface ( 14 ) intérieure de carcasse constituée par rapport au rotor ( 8 ) dans une direction périphérique,
    dans laquelle au moins un intervalle ( 18 ) est formé entre le rotor ( 8 ) et la surface ( 14 ) intérieure de la carcasse, dans laquelle un certain nombre d'aubes ( 24 ) directrices, s'étendant radialement et ayant respectivement une emplanture ( 22 ), sont fixées à la carcasse et, dans la région de la surface ( 14 ) intérieure de la carcasse, est monté un casseur ( 20 ) de giration pour diminuer une giration dirigée dans la direction périphérique d'un courant de fuite s'écoulant dans l'intervalle ( 18 ),
    caractérisée en ce que
    le casseur ( 20 ) de giration est constitué sous la forme d'une pièce, qui est immobilisée par complémentarité de forme, qui s'étend sensiblement dans un plan radial-axial et qui est immobilisée dans un espace intermédiaire formé par deux emplantures ( 22 ) d'aubes directrices voisines dans la direction périphérique, dans laquelle des évidements sont ménagés dans les deux emplantures ( 22 ) d'aubes directrices voisines et l'espace intermédiaire est formé essentiellement par les évidements et le casseur ( 20 ) de giration a une partie ( 26 ) qui s'étend dans la direction radiale et qui est immobilisée à complémentarité de forme dans une rainure ( 28 ) de la carcasse ( 4, 2 ).
  2. Turbomachine ( 1 ) suivant la revendication 1,
    dans laquelle respectivement un casseur ( 20 ) de giration est immobilisé par complémentarité de forme dans une multiplicité d'espaces intermédiaires formés de respectivement deux emplantures ( 22 ) d'aubes directrices voisines.
  3. Turbomachine ( 1 ) suivant la revendication 1 ou 2,
    dans laquelle des évidements sont ménagés dans respectivement les deux emplantures ( 22 ) d'aubes directrices voisines et l'espace intermédiaire respectif est formé essentiellement par les évidements.
  4. Turbomachine ( 1 ) suivant la revendication 2 ou 3,
    dans laquelle le casseur ( 20 ) de giration respectif est sous la forme d'une pièce s'étendant sensiblement dans un plan radial-axial.
  5. Turbomachine ( 1 ) suivant l'une des revendications 2 à 4,
    dans laquelle le casseur ( 20 ) de giration respectif est sous la forme d'une tôle.
  6. Turbomachine ( 1 ) suivant l'une des revendications 2 à 5,
    dans laquelle le casseur ( 20 ) de giration respectif est d'une pièce en matériau.
  7. Turbomachine ( 1 ) suivant l'une des revendications 2 à 6,
    dans laquelle le casseur ( 20 ) de giration respectif a une partie qui s'étend dans la direction radiale et qui est immobilisée par complémentarité de forme dans une rainure ( 28 ) de la carcasse ( 4, 2 ).
  8. Turbomachine ( 1 ) suivant l'une des revendications 2 à 7,
    dans laquelle le casseur ( 20 ) de giration respectif est immobilisé avec adaptation de jeu.
  9. Turbomachine ( 1 ) suivant l'une des revendications 2 à 8,
    dans laquelle le casseur ( 20 ) de giration respectif est coudé suivant un angle plat dans la direction périphérique.
  10. Centrale électrique ayant une turbomachine ( 1 ) suivant l'une des revendications précédentes.
EP11757253.7A 2010-09-10 2011-09-08 Dispositif de rupture de tourbillon dans un courant de fuite d'une turbomachine Not-in-force EP2614222B1 (fr)

Priority Applications (1)

Application Number Priority Date Filing Date Title
EP11757253.7A EP2614222B1 (fr) 2010-09-10 2011-09-08 Dispositif de rupture de tourbillon dans un courant de fuite d'une turbomachine

Applications Claiming Priority (3)

Application Number Priority Date Filing Date Title
EP10176188A EP2428649A1 (fr) 2010-09-10 2010-09-10 Dispositif de rupture de tourbillon dans un courant de fuite d'une turbomachine
EP11757253.7A EP2614222B1 (fr) 2010-09-10 2011-09-08 Dispositif de rupture de tourbillon dans un courant de fuite d'une turbomachine
PCT/EP2011/065516 WO2012032105A1 (fr) 2010-09-10 2011-09-08 Élément suppresseur de tourbillonnement disposé dans l'écoulement de fuite d'une turbomachine

Publications (2)

Publication Number Publication Date
EP2614222A1 EP2614222A1 (fr) 2013-07-17
EP2614222B1 true EP2614222B1 (fr) 2014-10-29

Family

ID=43558482

Family Applications (2)

Application Number Title Priority Date Filing Date
EP10176188A Withdrawn EP2428649A1 (fr) 2010-09-10 2010-09-10 Dispositif de rupture de tourbillon dans un courant de fuite d'une turbomachine
EP11757253.7A Not-in-force EP2614222B1 (fr) 2010-09-10 2011-09-08 Dispositif de rupture de tourbillon dans un courant de fuite d'une turbomachine

Family Applications Before (1)

Application Number Title Priority Date Filing Date
EP10176188A Withdrawn EP2428649A1 (fr) 2010-09-10 2010-09-10 Dispositif de rupture de tourbillon dans un courant de fuite d'une turbomachine

Country Status (3)

Country Link
EP (2) EP2428649A1 (fr)
CN (1) CN103109041B (fr)
WO (1) WO2012032105A1 (fr)

Families Citing this family (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JP2016089768A (ja) * 2014-11-07 2016-05-23 三菱日立パワーシステムズ株式会社 シール装置及びターボ機械

Family Cites Families (13)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US1861960A (en) * 1930-11-28 1932-06-07 Westinghouse Electric & Mfg Co Turbine blading
US4370094A (en) * 1974-03-21 1983-01-25 Maschinenfabrik Augsburg-Nurnberg Aktiengesellschaft Method of and device for avoiding rotor instability to enhance dynamic power limit of turbines and compressors
JPS6123804A (ja) * 1984-07-10 1986-02-01 Hitachi Ltd タ−ビン段落構造
DE4215440A1 (de) * 1992-05-11 1993-11-18 Mtu Muenchen Gmbh Einrichtung zur Bauteilabdichtung, insbesondere bei Turbomaschinen
DE59810557D1 (de) * 1998-11-10 2004-02-12 Alstom Switzerland Ltd Spitzendichtung für Turbinenlaufschaufeln
JP4502517B2 (ja) * 1999-03-24 2010-07-14 シーメンス アクチエンゲゼルシヤフト 流体機械の案内羽根及び案内羽根リング
US6722846B2 (en) * 2002-07-30 2004-04-20 General Electric Company Endface gap sealing of steam turbine bucket tip static seal segments and retrofitting thereof
JP2006104952A (ja) * 2004-09-30 2006-04-20 Toshiba Corp 流体機械の旋回流防止装置
EP1744015A1 (fr) * 2005-07-14 2007-01-17 Siemens Aktiengesellschaft Montage d'un segment d'étanchéité dans le pied d'une aube statorique
DE102007030764B4 (de) * 2006-07-17 2020-07-02 General Electric Technology Gmbh Dampfturbine mit Heizdampfentnahme
US20080118350A1 (en) * 2006-11-16 2008-05-22 General Electric Turbine seal guards
EP2031184A1 (fr) * 2007-08-31 2009-03-04 Siemens Aktiengesellschaft Dispositif de rupture de tourbillon pour turbomachine
US8052380B2 (en) * 2008-10-29 2011-11-08 General Electric Company Thermally-activated clearance reduction for a steam turbine

Also Published As

Publication number Publication date
CN103109041A (zh) 2013-05-15
CN103109041B (zh) 2015-11-25
EP2428649A1 (fr) 2012-03-14
WO2012032105A1 (fr) 2012-03-15
EP2614222A1 (fr) 2013-07-17

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