WO2018157958A1 - Étage de turbine muni d'un élément d'accouplement - Google Patents

Étage de turbine muni d'un élément d'accouplement Download PDF

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Publication number
WO2018157958A1
WO2018157958A1 PCT/EP2017/081325 EP2017081325W WO2018157958A1 WO 2018157958 A1 WO2018157958 A1 WO 2018157958A1 EP 2017081325 W EP2017081325 W EP 2017081325W WO 2018157958 A1 WO2018157958 A1 WO 2018157958A1
Authority
WO
WIPO (PCT)
Prior art keywords
turbine
coupling element
turbine stage
coupling
stage according
Prior art date
Application number
PCT/EP2017/081325
Other languages
German (de)
English (en)
Inventor
Frederik Popig
Christoph Sporbert
Original Assignee
Siemens Aktiengesellschaft
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 Aktiengesellschaft filed Critical Siemens Aktiengesellschaft
Publication of WO2018157958A1 publication Critical patent/WO2018157958A1/fr

Links

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
    • 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
    • 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
    • F01D5/24—Blade-to-blade connections, e.g. for damping vibrations using wire or the like
    • 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
    • F05D2230/00—Manufacture
    • F05D2230/60—Assembly methods
    • F05D2230/64—Assembly methods using positioning or alignment devices for aligning or centring, e.g. pins
    • 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

Definitions

  • the invention relates to a turbine stage according to the Oberbe ⁇ handle of the independent claim 1.
  • the blades can be connected to one another, for example via a shroud, or coupled to one another at very high mechanical loads, by means of a coupling wire or by loose insertion of coupling pins.
  • Such coupling elements are known for example from DE 10 2010 041 702 AI.
  • the vibration amplitude of the individual blades is significantly reduced, thereby reducing the Schwingungsbe ⁇ utilization in the individual blades, can be effectively prevented so that fatigue fractures of the turbine blades.
  • a disadvantage of the coupling elements is that in the event of damage or breakage of the coupling element, the entire turbine stage must be dismantled to replace the coupling element. This results in considerable
  • the turbine stage according to the invention comprising at least egg NEN turbine rotor and a plurality of spaced about the circumference of the turbine rotor turbine blades, as at least one coupling element being formed in at least two adjacent Turbi ⁇ nenschaufeln bores in which the coupling element extends into or through which and the Turbine blades mechanically coupled with each other, characterized in that the coupling element is arranged spatially such that it can be removed without disassembly of a turbine blade from the turbine stage.
  • Cutting plane orthogonal to the drilling axis of the respective Bohrun ⁇ gene at an angle not equal to 90 ° to a sectional plane orthogonal to the axis of rotation of the turbine rotor extends.
  • ⁇ through the coupling elements are arranged such that they can be pulled out laterally from the turbine stage. A disassembly of the turbine blades of the turbine stage can thus eliminated. This makes it possible to easily and within a short time replac defective coupling elements ⁇ zen.
  • a further embodiment of the invention provides that the angle is chosen so that the coupling element when pulling ⁇ out of the bore does not abut against a subsequent Turbi ⁇ nenschaufel. By such an arrangement, the Demon ⁇ days of the coupling elements is simplified once again.
  • a further embodiment of the invention provides that the angle is between 30 ° and 60 °.
  • a further embodiment of the invention provides that boreholes belonging to the reception of a coupling element have a common drilling axis.
  • the coupling elements may consist of substantially cylindrical bodies and can be easily inserted through the hole. This further reduces the assembly effort.
  • a further embodiment of the invention provides that the common bore axis is substantially tangential to a Zy ⁇ relieving surface which is aligned coaxially to the outer surface of the turbine rotor. This results in a substantially uniform arrangement of the coupling elements over the circumference. In addition, this ensures that the imbalance in the turbine stage is reduced.
  • a further embodiment of the invention provides that a first end of the coupling element in a blind hole of a first turbine blade and the second end of Koppelelemen ⁇ tes in a through hole of a second turbine blade protrudes, wherein the through hole is provided with a closure ⁇ element, which prevents slipping out of Koppelele ⁇ Mentes from the first and second bore. The closure element ensures an easy and secure attachment of the coupling element between the turbine shop ⁇ feln.
  • FIG. 1 shows a detail view of a turbine stage according to the prior art in a sectional representation
  • FIG. 2 is a detail view of the turbine stage according to the invention in a sectional view without coupling element.
  • FIG. 3 a shows the turbine stage according to the invention from FIG. 2 with a coupling element and a first exemplary embodiment of a closure element
  • FIG. 3b shows the turbine stage according to the invention from FIG. 2 with coupling element and a second exemplary embodiment of a closure element
  • Figure 1 shows a turbine stage according to the prior art.
  • the figure does not show the entire turbine stage, but only two circumferentially adjacent Turbinenschau ⁇ blades 2.
  • the turbine stages 2 are mechanically coupled to each other via a coupling element 3.
  • the coupling element 3 has a straight course in the exemplary embodiment.
  • Grunds obviously ⁇ Lich, the coupling element 3 also have a curved course.
  • the arcuate course of the coupling element 3rd then corresponds, for example, a circular arc around the rotation ⁇ axis 8 of the turbine rotor 1.
  • the fixation of Koppelele ⁇ ment 3 takes place such that in the turbine blades 2 ⁇ each case a blind hole 4 is formed, projecting into the respective ends of the coupling element.
  • the coupling element 3 between the two adjacent turbine acting ⁇ feln 2 is fixed.
  • the coupling elements 3 are thus all in one plane. In addition, they are spatially arranged such that they can not be pulled laterally out of the blade assembly. Assembly / disassembly of the coupling elements 3 can thus only take place when the entire blade assembly of the turbine stage is released.
  • FIG. 2 shows a detailed view of a firsttrusbei ⁇ game of a turbine stage according to the invention.
  • the turbine stage comprises a turbine rotor 1 which rotates about an axis of rotation 8. Further comprising the turbine stage sev- eral over the circumference of the turbine rotor 1 arranged Turbi ⁇ nenschaufeln 2 and at least one coupling element 3.
  • Turbi ⁇ nenschaufeln 2 In order to ⁇ exception of the coupling element 3 2 holes 4 are formed in two adjacent Turbi ⁇ nenschaufeln in which the coupling element 3 in or through which it projects through and mechanically couples the turbine blade 2 with one another.
  • the holes 4 can be formed as a blind hole or as a through hole, wherein at least one of the holes for inserting the coupling element is always formed as a through hole.
  • the coupling element 3 is such spatially arranged in the turbine stage that it can be removed without dismantling a ⁇ of individual turbine blades 2 of the turbine stage.
  • the bores 4 are arranged such that the coupling element 3 extends laterally out of the blade assembly. can be pulled without an adjacent Turbinenschau ⁇ fel 2 prevents the pulling out of the coupling element 3. Since ⁇ with the coupling element 3 when pulling out of the holes 4 does not abut against an adjacent turbine stage 2, the drilling axis 6 of the respective bore 4 is formed at a certain angle.
  • a cutting plane 5 is orthogonal to the drilling axis 6 of the respective bore 4 at an angle of not equal to 90 ° to a sectional plane 7 orthogonal to the rotation ⁇ axis 8 to arrange the turbine rotor.
  • the angle is to be chosen so that the coupling element 3 when pulling out of the holes 4 does not abut against a subsequent Turbinenschau ⁇ fel 2.
  • the angle between 30 ° and 60 ° to choose.
  • the sheets 4 belonging to a coupling element 3 have a common drilling axis 9.
  • the coupling element 3 can also be formed arcuate, however, so that the members of the receptacle of the coupling element 3 prepared holes ⁇ gen 4 has no common drilling axis.
  • the common bore axis 9 is substantially tangential to a ZY-relieving surface which is disposed coaxially to the envelope surface 10 of the Turbi ⁇ nenrotors. 1
  • the tangential orientation ensures a uniform pressing of the coupling element in the holes 4 and thus for a secure stiffening of the show ⁇ felverbundes.
  • FIG. 3a and b A particularly simple and secure fixing of the Koppelele ⁇ mentes 3 is shown in Figures 3a and b.
  • a first end of the coupling element 3 protrudes into a blind hole
  • FIG. 3a A first embodiment of such a VerNMele ⁇ element 13 is shown in Figure 3a.
  • the closure element 13 is formed as a simple plug. The fastening ⁇ movement of the closure element 13 via the screwing of the closure element 13 into the through hole 12 of the
  • the through hole 12 has an internal thread and the closure element 13 has a corresponding external thread.
  • a hexagon socket can be provided in the end face of the closure element 13.
  • Closing element 13 are secured, for example by gluing. Basically, the closure member 13 may attached in other ways, for example by pressing the ⁇ .
  • FIG. 3b shows a second embodiment of a Ver ⁇ locking element 13.
  • the closing element 13 is in the form of a pot element is formed.
  • the coupling element 3 protrudes into the pot of the closure element 13 and is thereby secured.
  • the attachment of the coupling element 3 can in turn be carried out in an advantageous manner via a screw by means of internal and external thread.
  • the closure elements 13 in FIGS. 3 a and 3 b enable the attachment of the coupling element 3 between adjacent turbine blades 2 in a simple manner.
  • the assembly of the coupling element 3 takes place in which the coupling element is first pushed through the through-bore 12 of the second turbine blade 2 until it protrudes in the blind hole 11 of the first turbine blade 2. Subsequently, the through hole 12 is closed by means of the closure element 13 and thus secured the coupling element 3 against slipping out.
  • the closure element 13 In the event of a defect or replacement of the coupling element 3 for another reason, only the closure element 13 must be solved, the coupling element 3 are pulled out ⁇ back and a new coupling element 3 are inserted, which in turn is secured by means of the closure element 13.
  • the turbine blade arrangement according to the invention thus makes it possible, for the first time, to replace individual coupling elements without the entire blade composite of the turbine blade arrangement having to be loosened.
  • the replacement of individual coupling elements can thus be done very quickly and with little effort.
  • a mounting flap is provided in the turbine housing, through which access is permitted to the turbine stage.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)

Abstract

L'invention concerne un étage de turbine comprenant au moins un rotor de turbine (1) et plusieurs aubes de turbine (2) agencées sur la circonférence du rotor de turbine (1), ainsi qu'au moins un élément d'accouplement (3). Au moins dans deux aubes de turbine (2) voisines sont pratiqués des alésages (4) dans lesquels l'élément d'accouplement (3) pénètre, ou qu'il traverse, accouplant mécaniquement les aubes de turbine (2) l'une à l'autre. L'élément d'accouplement (3) est agencé dans l'espace de telle manière qu'il peut être retiré de l'étage de turbine sans montage d'une aube de turbine (2).
PCT/EP2017/081325 2017-03-01 2017-12-04 Étage de turbine muni d'un élément d'accouplement WO2018157958A1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE102017203308.8 2017-03-01
DE102017203308.8A DE102017203308A1 (de) 2017-03-01 2017-03-01 Turbinenstufe mit Koppelelement

Publications (1)

Publication Number Publication Date
WO2018157958A1 true WO2018157958A1 (fr) 2018-09-07

Family

ID=60702670

Family Applications (1)

Application Number Title Priority Date Filing Date
PCT/EP2017/081325 WO2018157958A1 (fr) 2017-03-01 2017-12-04 Étage de turbine muni d'un élément d'accouplement

Country Status (2)

Country Link
DE (1) DE102017203308A1 (fr)
WO (1) WO2018157958A1 (fr)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN112483190A (zh) * 2020-11-27 2021-03-12 日照黎阳工业装备有限公司 一种基于航空发动机具备扰流结构的涡轮叶片

Families Citing this family (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE102020215479A1 (de) 2020-12-08 2022-06-09 Siemens Energy Global GmbH & Co. KG Neuartiges Dämpfungselement für Dampfturbinenschaufeln

Citations (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3131461A (en) * 1961-04-20 1964-05-05 Carrier Corp Method of making vibration damped turbo machinery
GB1499586A (en) * 1976-07-16 1978-02-01 English Electric Co Ltd Axial-flow turbo-machines
EP0203287A1 (fr) * 1985-05-31 1986-12-03 BBC Brown Boveri AG Elément supprimant les vibrations des aubes de turbomachines
US20030049131A1 (en) * 2001-08-30 2003-03-13 Kabushiki Kaisha Toshiba Moving blades for steam turbine
DE102008059836A1 (de) * 2008-12-01 2010-06-02 Alstom Technology Ltd. Strömungsmaschine, insbesondere Dampfturbine
US20110142650A1 (en) * 2009-12-14 2011-06-16 Beeck Alexander R Turbine Blade Damping Device with Controlled Loading
DE102010041702A1 (de) 2010-09-30 2012-04-05 Siemens Aktiengesellschaft Koppelbolzen für Turbinenschaufeln

Family Cites Families (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CH272378A (de) 1949-02-17 1950-12-15 Escher Wyss Ag Beschaufelung an Rotoren von axial durchströmten, verwundene Schaufeln aufweisenden Kreiselmaschinen, insbesondere von Dampf-, Gasturbinen und Verdichtern.
GB1309646A (en) 1970-04-10 1973-03-14 Secr Defence Bladed rotor for a gas turbine engine

Patent Citations (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3131461A (en) * 1961-04-20 1964-05-05 Carrier Corp Method of making vibration damped turbo machinery
GB1499586A (en) * 1976-07-16 1978-02-01 English Electric Co Ltd Axial-flow turbo-machines
EP0203287A1 (fr) * 1985-05-31 1986-12-03 BBC Brown Boveri AG Elément supprimant les vibrations des aubes de turbomachines
US20030049131A1 (en) * 2001-08-30 2003-03-13 Kabushiki Kaisha Toshiba Moving blades for steam turbine
DE102008059836A1 (de) * 2008-12-01 2010-06-02 Alstom Technology Ltd. Strömungsmaschine, insbesondere Dampfturbine
US20110142650A1 (en) * 2009-12-14 2011-06-16 Beeck Alexander R Turbine Blade Damping Device with Controlled Loading
DE102010041702A1 (de) 2010-09-30 2012-04-05 Siemens Aktiengesellschaft Koppelbolzen für Turbinenschaufeln

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN112483190A (zh) * 2020-11-27 2021-03-12 日照黎阳工业装备有限公司 一种基于航空发动机具备扰流结构的涡轮叶片
CN112483190B (zh) * 2020-11-27 2022-05-13 日照黎阳工业装备有限公司 一种基于航空发动机具备扰流结构的涡轮叶片

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