EP1413712A1 - Virole pour une turbine avec joint d'extrémité - Google Patents

Virole pour une turbine avec joint d'extrémité Download PDF

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Publication number
EP1413712A1
EP1413712A1 EP02023473A EP02023473A EP1413712A1 EP 1413712 A1 EP1413712 A1 EP 1413712A1 EP 02023473 A EP02023473 A EP 02023473A EP 02023473 A EP02023473 A EP 02023473A EP 1413712 A1 EP1413712 A1 EP 1413712A1
Authority
EP
European Patent Office
Prior art keywords
blade
shroud
sealing rib
recess
circumferential direction
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Withdrawn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
EP02023473A
Other languages
German (de)
English (en)
Inventor
Peter Tiemann
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 EP02023473A priority Critical patent/EP1413712A1/fr
Publication of EP1413712A1 publication Critical patent/EP1413712A1/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Withdrawn legal-status Critical Current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
    • 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
    • F01D5/225—Blade-to-blade connections, e.g. for damping vibrations by shrouding

Definitions

  • the present invention relates to a rotor blade of a turbomachine which has a rotor blade root, a platform, a wing blade and a shroud in succession along a longitudinal direction, a sealing rib running along a circumferential direction being arranged on the outer circumference of the shroud.
  • Blades for a turbine are known from DE 19,904,229 A1.
  • the blade shows a wing blade, at the tip of which a cover band is arranged.
  • the shroud is fastened in the center of the tip and cantilevered towards the two side edges of the shroud.
  • a sealing rib is arranged on the outer circumference of the cover band and runs from one freely projecting side edge to the other. It is traversed by coolant channels.
  • the centrifugal forces of the rotating rotor cause the freely projecting side edges of the shroud to move outwards. This can lead to contact between the sealing rib and the opposite guide ring, the sealing rib being deformed at its ends.
  • the outwardly striving side edges of the cover tape in the middle of the sealing rib lead to compressive stresses, which deform the sealing rib if necessary.
  • the object of the present invention is to provide a moving blade in which the above disadvantages are avoided.
  • a steam turbine and a gas turbine are to be specified in which the aforementioned disadvantages do not occur.
  • the object related to the rotor blade is achieved according to the invention by the sealing rib in Longitudinal direction of the blade has a local cross-sectional enlargement.
  • the local cross-sectional enlargement increases the load-bearing area, the cross-sectional area, in the sealing rib.
  • the sealing rib thus resists its internal compressive stresses during the operation of the turbomachine.
  • the compressive stress resulting from the centrifugal forces is almost identical in relation to a sealing rib without local cross-sectional enlargement, but this advantageously has an effect on a larger area of the sealing rib, so that deformation of the sealing rib is avoided.
  • the local cross-sectional enlargement extending over the entire extent of the sealing rib and the cover band running parallel to it represent the upper and lower crossbeams of an "I" in abstract form, and the sealing rib itself represents the vertical web of the "I".
  • Each cantilevered side of the shroud is therefore to be regarded as an I-shaped bending beam clamped on one side in relation to its fastening point on the blade.
  • the previously known shroud with the sealing rib forms a bending beam with an inverted T-shaped cross section. Because of the greater area moment of inertia of the I-shape compared to the T-shape, the design according to the invention is more rigid than the already known one. As a result, the shroud bends less during operation. This results in a reduction in the compressive stresses occurring in the sealing rib and also prevents the sealing rib from rubbing against the opposite guide ring.
  • the sealing rib is at least partially interrupted by a separating slot running transversely to the longitudinal direction.
  • the centrifugal forces occurring during the operation of the turbomachine cause a compressive stress in the sealing rib, which is in the middle of its longest dimension greatest is.
  • a separating slot arranged there reduces the build-up of the compressive stress. An inadmissible deformation of the sealing rib is prevented.
  • two or more parallel sealing ribs are arranged on the shroud, each of which has a local cross-sectional enlargement. A further increase in the bending stiffness of the freely projecting shroud is thus achieved.
  • the object related to the rotor blade is achieved according to the invention in that, in order to reduce the mass, a recess is arranged on the outer circumference of the shroud, which is delimited in the circumferential direction of the shroud by a first freely projecting side edge and by a second freely projecting side edge opposite the first side edge.
  • the shrouds of immediately adjacent rotor blades abut one another on a contact surface which adjoins these side edges.
  • This contact surface can thus continue to be generously dimensioned, which contributes to the strength and rigidity of the shroud ring formed by all shrouds of a moving blade ring. This prevents the blade ring from vibrating.
  • the mass taken out of the shroud from the center in the circumferential direction does not impair the strength of the shroud itself, since it has no load-bearing function.
  • the recess of the shroud can be easily manufactured if it has an identical depth over its extent in the circumferential direction.
  • a further advantageous development is provided if the maximum depth of the recess is arranged centrally between the first and second side edges delimiting the recess in the circumferential direction and that the depth of the recess decreases towards both sides.
  • the changing depth of the recess is a form that stiffens the shroud.
  • the characterizing features of claims 1 and 6 are applied together.
  • the combination of the features combines advantages and effects.
  • the compressive stress prevailing in the sealing ribs can be significantly reduced during operation of the gas turbine and the rubbing of the sealing rib on the guide ring can also be prevented.
  • the recess is expediently arranged in between.
  • the rotor blade can expediently be designed as a compressor rotor blade, as well as a turbine rotor blade, in which the heat resistance of the cover band and the sealing rib produced in this way is particularly useful.
  • the object related to the gas turbine is achieved in that the gas turbine is operated with a moving blade according to claims 1 to 11.
  • the object related to the steam turbine is achieved in that the steam turbine is operated with a moving blade according to claims 1 to 11.
  • the blade 1 shown in FIG. 1 has a blade root 2, a platform 3, a wing 4 and a shroud 5 in succession along a longitudinal direction L.
  • Arranged on the outer circumference of the shroud 5 are two sealing ribs 6.
  • the sealing ribs In the longitudinal direction L, the sealing ribs have a local cross-sectional enlargement 7 which extends in the circumferential direction U over their entire length.
  • the longest dimension of the sealing rib 6 extending in the circumferential direction U has a separating slot 8 in the center.
  • the recess 9 arranged between the two sealing ribs 6 is delimited in the circumferential direction U by the side edges 12a and 12b.
  • the centrifugal forces 13 occurring during the operation of the turbomachine cause compressive stresses 14 in the sealing ribs 6, which have their maximum in the middle of the longest dimension of the sealing ribs 6.
  • the separation slot 8 prevents the deforming occurrence of the compressive stress 14 and thus offers a gap which can be reduced under the influence of flying forces.
  • FIG. 2 shows a cross section through the tip of an already known rotor blade 1 with shroud 5 and sealing rib 6.
  • the compressive stresses 14 act in the sealing rib 6 due to the centrifugal forces 13.
  • the mechanical analysis of the sealing rib 6 is symbolized by the T-shaped profile 15 turned upside down.
  • the sealing rib 6 and the shroud 5 are attached to the wing blade 4 and collar in the direction of the two side edges 12a, 12b.
  • the two freely projecting areas in connection with the acting centrifugal forces 13 each behave like a cantilever clamped on one side under a linear load.
  • One-sided refers to the fastening point of the cover band 5 on the wing blade 4.
  • the compressive stresses 14 occurring from the two free ends of the clamped bending beams meet in the middle of the longest dimension of the sealing rib 6 and can act there deforming it.
  • the sealing rib 6 has a cross-sectional enlargement 7 local in the longitudinal direction L. Due to the local cross-sectional enlargement 7 of the sealing rib 6 in connection with the shroud 5, the mechanically effective profile can be symbolically represented by an I 16.
  • the compressive stresses 14, caused by the centrifugal forces 13, are lower due to the more rigid I-shaped profile 16, which has a larger moment of inertia than the T-shaped profile.
  • the arrangement of the local cross-sectional enlargement 7 of the sealing rib 6 gives the shroud 5 and the sealing rib 6 increased rigidity.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
EP02023473A 2002-10-21 2002-10-21 Virole pour une turbine avec joint d'extrémité Withdrawn EP1413712A1 (fr)

Priority Applications (1)

Application Number Priority Date Filing Date Title
EP02023473A EP1413712A1 (fr) 2002-10-21 2002-10-21 Virole pour une turbine avec joint d'extrémité

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP02023473A EP1413712A1 (fr) 2002-10-21 2002-10-21 Virole pour une turbine avec joint d'extrémité

Publications (1)

Publication Number Publication Date
EP1413712A1 true EP1413712A1 (fr) 2004-04-28

Family

ID=32049987

Family Applications (1)

Application Number Title Priority Date Filing Date
EP02023473A Withdrawn EP1413712A1 (fr) 2002-10-21 2002-10-21 Virole pour une turbine avec joint d'extrémité

Country Status (1)

Country Link
EP (1) EP1413712A1 (fr)

Cited By (21)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2005061854A1 (fr) * 2003-12-17 2005-07-07 Watson Cogeneration Company Lisses de coiffe d'extremite de turbine a gaz
EP1591625A1 (fr) * 2004-04-30 2005-11-02 ALSTOM Technology Ltd Virole pour aube de turbine à gaz
EP1873355A1 (fr) * 2006-06-27 2008-01-02 Siemens Aktiengesellschaft Aube de turbine
US7762779B2 (en) 2006-08-03 2010-07-27 General Electric Company Turbine blade tip shroud
DE102009030566A1 (de) * 2009-06-26 2010-12-30 Mtu Aero Engines Gmbh Deckbandsegment zur Anordnung an einer Schaufel
EP2369134A1 (fr) * 2010-03-12 2011-09-28 Industria de Turbo Propulsores S.A. Aude de turbine avec des cavités pour la réduction du poid et des vibrations
FR2974842A1 (fr) * 2011-05-05 2012-11-09 Snecma Joint d'etancheite dans une turbomachine, comprenant des lechettes mobiles devant de l'abradable
EP3006672A1 (fr) * 2014-10-10 2016-04-13 Universität Stuttgart Dispositif destiné à influencer l'écoulement dans une turbomachine
WO2019243708A2 (fr) 2018-06-20 2019-12-26 Safran Aircraft Engines Joint d'etancheite a labyrinthe pour une turbomachine d'aeronef
US11098609B2 (en) 2018-01-23 2021-08-24 MTU Aero Engines AG Rotor blade shroud for a turbomachine, rotor blade, method of making a rotor blade shroud and a rotor blade
CN114922695A (zh) * 2022-04-22 2022-08-19 沈阳德瓦特汽轮动力有限责任公司 一种工业汽轮机调节级动叶片围带及其优化方法
US11585225B2 (en) 2020-02-11 2023-02-21 MTU Aero Engines AG Blade for a turbomachine
US11802257B2 (en) 2022-01-31 2023-10-31 Marathon Petroleum Company Lp Systems and methods for reducing rendered fats pour point
US11860069B2 (en) 2021-02-25 2024-01-02 Marathon Petroleum Company Lp Methods and assemblies for determining and using standardized spectral responses for calibration of spectroscopic analyzers
US11891581B2 (en) 2017-09-29 2024-02-06 Marathon Petroleum Company Lp Tower bottoms coke catching device
US11898109B2 (en) 2021-02-25 2024-02-13 Marathon Petroleum Company Lp Assemblies and methods for enhancing control of hydrotreating and fluid catalytic cracking (FCC) processes using spectroscopic analyzers
US11905468B2 (en) 2021-02-25 2024-02-20 Marathon Petroleum Company Lp Assemblies and methods for enhancing control of fluid catalytic cracking (FCC) processes using spectroscopic analyzers
US11905479B2 (en) 2020-02-19 2024-02-20 Marathon Petroleum Company Lp Low sulfur fuel oil blends for stability enhancement and associated methods
US11970664B2 (en) 2021-10-10 2024-04-30 Marathon Petroleum Company Lp Methods and systems for enhancing processing of hydrocarbons in a fluid catalytic cracking unit using a renewable additive
US11975316B2 (en) 2019-05-09 2024-05-07 Marathon Petroleum Company Lp Methods and reforming systems for re-dispersing platinum on reforming catalyst
US12000720B2 (en) 2019-09-06 2024-06-04 Marathon Petroleum Company Lp Product inventory monitoring

Citations (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5201850A (en) * 1991-02-15 1993-04-13 General Electric Company Rotor tip shroud damper including damper wires
DE19904229A1 (de) 1999-02-03 2000-08-10 Asea Brown Boveri Gekühlte Turbinenschaufel

Patent Citations (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5201850A (en) * 1991-02-15 1993-04-13 General Electric Company Rotor tip shroud damper including damper wires
DE19904229A1 (de) 1999-02-03 2000-08-10 Asea Brown Boveri Gekühlte Turbinenschaufel

Cited By (34)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US7255531B2 (en) 2003-12-17 2007-08-14 Watson Cogeneration Company Gas turbine tip shroud rails
WO2005061854A1 (fr) * 2003-12-17 2005-07-07 Watson Cogeneration Company Lisses de coiffe d'extremite de turbine a gaz
US7628587B2 (en) 2004-04-30 2009-12-08 Alstom Technology Ltd Gas turbine blade shroud
WO2005106206A1 (fr) * 2004-04-30 2005-11-10 Alstom Technology Ltd Enveloppe pour aube d'une turbine a gaz
CN100404792C (zh) * 2004-04-30 2008-07-23 阿尔斯通技术有限公司 燃气轮机叶片叶冠
EP1591625A1 (fr) * 2004-04-30 2005-11-02 ALSTOM Technology Ltd Virole pour aube de turbine à gaz
EP1873355A1 (fr) * 2006-06-27 2008-01-02 Siemens Aktiengesellschaft Aube de turbine
US7762779B2 (en) 2006-08-03 2010-07-27 General Electric Company Turbine blade tip shroud
DE102009030566A1 (de) * 2009-06-26 2010-12-30 Mtu Aero Engines Gmbh Deckbandsegment zur Anordnung an einer Schaufel
US9322281B2 (en) 2009-06-26 2016-04-26 Mtu Aero Engines Gmbh Shroud segment to be arranged on a blade
EP2369134A1 (fr) * 2010-03-12 2011-09-28 Industria de Turbo Propulsores S.A. Aude de turbine avec des cavités pour la réduction du poid et des vibrations
FR2974842A1 (fr) * 2011-05-05 2012-11-09 Snecma Joint d'etancheite dans une turbomachine, comprenant des lechettes mobiles devant de l'abradable
EP3006672A1 (fr) * 2014-10-10 2016-04-13 Universität Stuttgart Dispositif destiné à influencer l'écoulement dans une turbomachine
WO2016055606A1 (fr) * 2014-10-10 2016-04-14 Universität Stuttgart Dispositif influençant l'écoulement dans un turbomoteur
US11891581B2 (en) 2017-09-29 2024-02-06 Marathon Petroleum Company Lp Tower bottoms coke catching device
US11098609B2 (en) 2018-01-23 2021-08-24 MTU Aero Engines AG Rotor blade shroud for a turbomachine, rotor blade, method of making a rotor blade shroud and a rotor blade
WO2019243708A3 (fr) * 2018-06-20 2020-02-20 Safran Aircraft Engines Joint d'etancheite a labyrinthe pour une turbomachine d'aeronef
US11692450B2 (en) 2018-06-20 2023-07-04 Safran Aircraft Engines Labyrinth sealing joint for an aircraft turbomachine
FR3082879A1 (fr) * 2018-06-20 2019-12-27 Safran Aircraft Engines Joint d'etancheite a labyrinthe pour une turbomachine d'aeronef
WO2019243708A2 (fr) 2018-06-20 2019-12-26 Safran Aircraft Engines Joint d'etancheite a labyrinthe pour une turbomachine d'aeronef
US11975316B2 (en) 2019-05-09 2024-05-07 Marathon Petroleum Company Lp Methods and reforming systems for re-dispersing platinum on reforming catalyst
US12000720B2 (en) 2019-09-06 2024-06-04 Marathon Petroleum Company Lp Product inventory monitoring
US11585225B2 (en) 2020-02-11 2023-02-21 MTU Aero Engines AG Blade for a turbomachine
US11905479B2 (en) 2020-02-19 2024-02-20 Marathon Petroleum Company Lp Low sulfur fuel oil blends for stability enhancement and associated methods
US11920096B2 (en) 2020-02-19 2024-03-05 Marathon Petroleum Company Lp Low sulfur fuel oil blends for paraffinic resid stability and associated methods
US11885739B2 (en) 2021-02-25 2024-01-30 Marathon Petroleum Company Lp Methods and assemblies for determining and using standardized spectral responses for calibration of spectroscopic analyzers
US11905468B2 (en) 2021-02-25 2024-02-20 Marathon Petroleum Company Lp Assemblies and methods for enhancing control of fluid catalytic cracking (FCC) processes using spectroscopic analyzers
US11906423B2 (en) 2021-02-25 2024-02-20 Marathon Petroleum Company Lp Methods, assemblies, and controllers for determining and using standardized spectral responses for calibration of spectroscopic analyzers
US11898109B2 (en) 2021-02-25 2024-02-13 Marathon Petroleum Company Lp Assemblies and methods for enhancing control of hydrotreating and fluid catalytic cracking (FCC) processes using spectroscopic analyzers
US11860069B2 (en) 2021-02-25 2024-01-02 Marathon Petroleum Company Lp Methods and assemblies for determining and using standardized spectral responses for calibration of spectroscopic analyzers
US11921035B2 (en) 2021-02-25 2024-03-05 Marathon Petroleum Company Lp Methods and assemblies for determining and using standardized spectral responses for calibration of spectroscopic analyzers
US11970664B2 (en) 2021-10-10 2024-04-30 Marathon Petroleum Company Lp Methods and systems for enhancing processing of hydrocarbons in a fluid catalytic cracking unit using a renewable additive
US11802257B2 (en) 2022-01-31 2023-10-31 Marathon Petroleum Company Lp Systems and methods for reducing rendered fats pour point
CN114922695A (zh) * 2022-04-22 2022-08-19 沈阳德瓦特汽轮动力有限责任公司 一种工业汽轮机调节级动叶片围带及其优化方法

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