EP0536575B1 - Bande de recouvrement pour roue de turbine axiale - Google Patents

Bande de recouvrement pour roue de turbine axiale Download PDF

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Publication number
EP0536575B1
EP0536575B1 EP92116009A EP92116009A EP0536575B1 EP 0536575 B1 EP0536575 B1 EP 0536575B1 EP 92116009 A EP92116009 A EP 92116009A EP 92116009 A EP92116009 A EP 92116009A EP 0536575 B1 EP0536575 B1 EP 0536575B1
Authority
EP
European Patent Office
Prior art keywords
gap
casing
blade
shroud
throttle
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
EP92116009A
Other languages
German (de)
English (en)
Other versions
EP0536575A1 (fr
Inventor
Franz Kreitmeier
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.)
ABB Asea Brown Boveri Ltd
ABB AB
Original Assignee
ABB Asea Brown Boveri Ltd
Asea Brown Boveri AB
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 ABB Asea Brown Boveri Ltd, Asea Brown Boveri AB filed Critical ABB Asea Brown Boveri Ltd
Publication of EP0536575A1 publication Critical patent/EP0536575A1/fr
Application granted granted Critical
Publication of EP0536575B1 publication Critical patent/EP0536575B1/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
    • F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
    • F01D11/08—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator
    • F01D11/12—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator using a rubstrip, e.g. erodible. deformable or resiliently-biased part
    • 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
    • F01D11/08—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator
    • 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 invention relates to a device for sealing the gap between the rotor blades and the housing of a turbomachine which is designed with a conical contour, the rotor blades being provided with circumferential cover plates which seal against the housing with prongs to form radial gaps.
  • Such devices are known, see e.g. the previously published document FR-A-2 406 074. They consist essentially of cover plates with circumferential tines which seal against the housing or against a honeycomb arrangement (honeycomb). They form a smooth or a stepped labyrinth with pure radial gaps. As a rule, these cover plates extend over the entire blade width.
  • a known seal which has two sealing prongs, is shown in FIG. 1 to be described later with reference to the rotor blade of the first stage.
  • the invention has for its object to ensure clean guidance of the main flow in blades of the type mentioned and to create a shroud which is accessible to good cooling and good cooling.
  • the cover plate arranged at the blade end has four throttle points against the housing, the throttle point on the inlet side forming a diagonal gap in the stationary operating state.
  • the outlet-side throttle point preferably forms a radial gap.
  • the advantage of the invention can be seen, inter alia, in the fact that only small amounts of gap occur in the new seal. As a result, high efficiencies can be achieved. In addition, a good introduction of the gap flow into the main flow is achieved.
  • cover plates are rotationally symmetrical and if the parting lines between adjacent cover plates run in the direction of the chord. With this design, the inevitable leakage flow between the cover plates is deflected in the direction of the main flow.
  • the parting line is provided with four steps, the steps running in the axial plane of the three throttling points.
  • the blades come into contact between adjacent cover plates when the blades are unwinding. This creates the necessary damping effect.
  • the inlet-side blade end advantageously has a lower inclination than the housing contour.
  • This inclination should be such that there is a positive offset at the blade end, which has its greatest value in the area of the blade leading edge and which, together with the associated cover plate part, projects into a gap relief chamber arranged in the housing. With this gap relief, a reduction in the leakage flow over the shroud is achieved by pushing the main flow near the gap.
  • the housing is provided with honeycomb arrangements at the four throttling points, no damage to the highly sensitive cover tape is to be expected if it is touched; These honeycomb seals also ensure that the heat generated when touching remains as low as possible. This means that the strength properties of the highly stressed elements involved remain intact.
  • the tines of the cover plates forming the throttling points are preferably tapered in the circumferential direction on the cover plate overhangs.
  • the three-stage gas turbine in FIG. 1 essentially consists of the bladed rotor 1 and the blade carrier 2 equipped with guide blades.
  • the blade carrier which has a strongly conical channel contour of 40 °, is suspended in a turbine housing (not shown).
  • the term blade carrier is synonymous with the term housing.
  • the working medium enters the turbine from the outlet of the combustion chamber 3.
  • the channel through which it flows opens into the exhaust gas housing, of which only the inner walls 4 of the diffuser are shown.
  • the blading consists of three guide rows 5a, 5b and 5c and three run rows 6a, 6b and 6c.
  • the blades of the guide rows seal against the rotor 1 by means of cover strips 7.
  • the blades of the first rotor row 6a are provided with the cover plate seal 8 known per se, mentioned at the beginning.
  • the actual seal consists of tines running in the circumferential direction, which run against a honeycomb arrangement (honeycomb) 9.
  • honeycomb honeycomb arrangement
  • the cover plates which extend across the entire blade width, form a classified labyrinth with pure radial gaps.
  • the highly loaded blades 6 of the outlet barrel row 6c are each provided with a cover plate 30 arranged centrally at the blade end, which forms three throttle points against the blade carrier 2.
  • the blades of the middle row of races are provided with cover plates 11 which, according to FIG. 2, counter four throttling points form the blade carrier 2.
  • the plates are provided with circumferential teeth 12, 13, 14 and 15 in four different radial planes.
  • the outlet-side prongs 15, together with a honeycomb arrangement 25 inserted in the blade carrier 2, form a radial gap 16.
  • the middle prongs 13 and 14 likewise form radial gaps 17 and 28 with the opposite honeycomb arrangements 27 and 28. 18.
  • the entry-side prong 12 runs diagonally and forms a diagonal gap 19 together with a correspondingly configured honeycomb arrangement 26.
  • 2 shows the operating position, that is to say the position in which the diagonal gap 19 represents the operating play. The axial expansion is therefore used to create a throttle gap.
  • the four prongs enclose three vortex chambers 20, 21, 22, the radial displacement of the throttle points not influencing one another.
  • the new type of seal at the outlet by means of a radial gap results in a cleanly guided outflow into the channel through which the previous free swirl spaces exist, as is contained in the cover plate seal 8 in the first row 5b.
  • the wall 29 of the channel through which the honeycomb arrangement 25 adjoins is initially rounded off slightly before it changes into the slope of the channel contour. With this measure, a deflecting Coanda effect is exerted on the gap stream emerging from the radial gap 16, so that the main flow is impaired as little as possible.
  • the blade end is provided with a positive offset 10 on the inlet side.
  • This offset is formed in that the blade tip has a smaller value than the taper 32 of the channel contour.
  • the offset 10 projects together with the cover plate part belonging to it a gap relief chamber 31 arranged in the blade carrier 2.
  • the inner contour of the gap relief chamber is adapted to the taper of the blade tip. This results in an aerodynamic relief of the blade gap. The pressure difference across the blade gap drops and the deflection is improved. This reduces the overall gap losses.
  • Fig. 3 it can be seen that the cover plates 11 are rotationally symmetrical.
  • the parting lines 23 between adjacent cover plates run in the direction of the chord.
  • the circumferential sides of the cover plates are provided with four steps 24. These steps run in the axial plane of the four sealing teeth to ensure a continuous seal on the sealing surfaces. In addition, these stages take over the mechanical coupling of the cover plates to one another in order to achieve the damping effect.
  • the prongs 12, 13, 14 and 15 are tapered in the circumferential direction on the two overhangs of each cover plate. These tapers 12a, 13a, 14a and 15a contribute significantly to the weight saving of the cover plates.

Landscapes

  • 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 (9)

  1. Dispositif pour réaliser l'étanchéité de la fente entre les aubes mobiles et le corps (2) à configuration de contour conique (28) d'une turbomachine, les aubes mobiles (6) étant pourvues de plaques de recouvrement (11) périphériques, qui assurent l'étanchéité par rapport au corps avec des dents (12, 13, 14, 15) formant des fentes radiales (16, 17, 18), caractérisé en ce que la plaque de recouvrement (11) disposée à l'extrémité de l'aube présente quatre zones d'étranglement contre le corps, la zone d'étranglement du côté de l'entrée formant une fente diagonale (19) à l'état de fonctionnement stationnaire.
  2. Dispositif selon la revendication 1, caractérisé en ce que la zone d'étranglement du côté de la sortie forme une fente radiale (16).
  3. Dispositif selon la revendication 1, caractérisé en ce que les plaques de recouvrement (11) sont conçues suivant une symétrie de révolution.
  4. Dispositif selon la revendication 1, caractérisé en ce que les lignes de joint (23) entre les plaques de recouvrement (11) adjacentes s'étendent dans la direction de la profondeur du profilé.
  5. Dispositif selon la revendication 4, caractérisé en ce que la ligne de joint (11) est pourvue de quatre étages (24), les étages s'étendant dans le plan axial des dents (12, 13, 14).
  6. Dispositif selon la revendication 1, caractérisé en ce que le corps est pourvu de dispositions alvéolaires (25, 26, 27, 28) aux quatres zones d'étranglement.
  7. Dispositif selon la revendication 1, caractérisé en ce que l'extrémité de l'aube du côté de l'entrée présente une inclinaison relativement faible par rapport au contour du corps (32), de sorte que le déport positif (10) qui en résulte à l'extrémité de l'aube fasse saillie, avec la partie correspondante de la plaque de recouvrement, dans une chambre de décharge de fente (31) formée dans le corps (2).
  8. Dispositif selon la revendication 1, caractérisé en ce que les dents (12, 13, 14, 15) des plaques de recouvrement (11), formant les zones d'étranglement, sont rétrécies (12a, 13a, 14a, 15a) dans la direction tangentielle aux parties en surplomb des plaques de recouvrement.
  9. Dispositif selon la revendication 1, caractérisé en ce que la paroi (29) du canal parcouru par le fluide, adjacente à la disposition alvéolaire (25) du côté de la sortie, est d'abord légèrement arrondie, avant de se biseauter au niveau du contour du canal.
EP92116009A 1991-10-08 1992-09-18 Bande de recouvrement pour roue de turbine axiale Expired - Lifetime EP0536575B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
CH296591 1991-10-08
CH2965/91 1991-10-08

Publications (2)

Publication Number Publication Date
EP0536575A1 EP0536575A1 (fr) 1993-04-14
EP0536575B1 true EP0536575B1 (fr) 1995-04-05

Family

ID=4245626

Family Applications (1)

Application Number Title Priority Date Filing Date
EP92116009A Expired - Lifetime EP0536575B1 (fr) 1991-10-08 1992-09-18 Bande de recouvrement pour roue de turbine axiale

Country Status (5)

Country Link
US (1) US5290144A (fr)
EP (1) EP0536575B1 (fr)
JP (1) JP3307692B2 (fr)
DE (1) DE59201833D1 (fr)
PL (1) PL296074A1 (fr)

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US6893216B2 (en) * 2003-07-17 2005-05-17 General Electric Company Turbine bucket tip shroud edge profile
DE102004025321A1 (de) * 2004-05-19 2005-12-08 Alstom Technology Ltd Strömungsmaschinenschaufel
US7234918B2 (en) * 2004-12-16 2007-06-26 Siemens Power Generation, Inc. Gap control system for turbine engines
US7861823B2 (en) * 2005-11-04 2011-01-04 United Technologies Corporation Duct for reducing shock related noise
US20070273104A1 (en) * 2006-05-26 2007-11-29 Siemens Power Generation, Inc. Abradable labyrinth tooth seal
EP1995413B1 (fr) * 2007-04-05 2010-04-28 ALSTOM Technology Ltd Joint d'étanchéité pour le jeu d'aubes d'une turbomachine
DE102008023326A1 (de) * 2008-05-13 2009-11-19 Mtu Aero Engines Gmbh Deckband für Laufschaufeln einer Strömungsmaschine und Strömungsmaschine
DE102008061800A1 (de) * 2008-12-11 2010-06-17 Rolls-Royce Deutschland Ltd & Co Kg Segmentierte Dichtlippen für Labyrinthdichtungsringe
EP2218918A1 (fr) * 2009-02-13 2010-08-18 Siemens Aktiengesellschaft Compresseur turbo axial pour une turbine à gaz ayant des pertes de gaz et des pertes de diffuseur réduites
US8317465B2 (en) * 2009-07-02 2012-11-27 General Electric Company Systems and apparatus relating to turbine engines and seals for turbine engines
US20110070072A1 (en) * 2009-09-23 2011-03-24 General Electric Company Rotary machine tip clearance control mechanism
US8608424B2 (en) * 2009-10-09 2013-12-17 General Electric Company Contoured honeycomb seal for a turbomachine
US8333557B2 (en) * 2009-10-14 2012-12-18 General Electric Company Vortex chambers for clearance flow control
US8708639B2 (en) * 2010-10-11 2014-04-29 The Coca-Cola Company Turbine bucket shroud tail
US20120195742A1 (en) * 2011-01-28 2012-08-02 Jain Sanjeev Kumar Turbine bucket for use in gas turbine engines and methods for fabricating the same
EP2551460A1 (fr) * 2011-07-29 2013-01-30 Siemens Aktiengesellschaft Groupe d'aubes
US9080459B2 (en) * 2012-01-03 2015-07-14 General Electric Company Forward step honeycomb seal for turbine shroud
US9291061B2 (en) * 2012-04-13 2016-03-22 General Electric Company Turbomachine blade tip shroud with parallel casing configuration
EP2998517B1 (fr) * 2014-09-16 2019-03-27 Ansaldo Energia Switzerland AG Agencement d'étanchéité au niveau de l'interface entre une chambre de combustion et une turbine d'une turbine à gaz et turbine à gaz avec un tel agencement d'étanchéité
CN107438717B (zh) 2015-04-15 2021-10-08 罗伯特·博世有限公司 自由梢端型轴流式风扇组件
US20180340438A1 (en) * 2017-05-01 2018-11-29 General Electric Company Turbine Nozzle-To-Shroud Interface
JP7086595B2 (ja) * 2017-12-28 2022-06-20 三菱重工航空エンジン株式会社 航空機用ガスタービン
KR102238435B1 (ko) * 2019-04-30 2021-04-09 두산중공업 주식회사 터빈의 실링 모듈 및 이를 포함하는 발전용 터빈 장치
JP2021110291A (ja) * 2020-01-10 2021-08-02 三菱重工業株式会社 動翼、及び軸流回転機械
CN113266431B (zh) * 2021-06-03 2022-08-09 西安交通大学 向心透平叶尖间隙超声波密封结构

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Also Published As

Publication number Publication date
JPH05195988A (ja) 1993-08-06
DE59201833D1 (de) 1995-05-11
PL296074A1 (en) 1993-05-17
EP0536575A1 (fr) 1993-04-14
US5290144A (en) 1994-03-01
JP3307692B2 (ja) 2002-07-24

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