EP0528138B1 - Anneau d'aube de turbine axiale - Google Patents

Anneau d'aube de turbine axiale Download PDF

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Publication number
EP0528138B1
EP0528138B1 EP92110494A EP92110494A EP0528138B1 EP 0528138 B1 EP0528138 B1 EP 0528138B1 EP 92110494 A EP92110494 A EP 92110494A EP 92110494 A EP92110494 A EP 92110494A EP 0528138 B1 EP0528138 B1 EP 0528138B1
Authority
EP
European Patent Office
Prior art keywords
blade
casing
gap
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
EP92110494A
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German (de)
English (en)
Other versions
EP0528138A1 (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 EP0528138A1 publication Critical patent/EP0528138A1/fr
Application granted granted Critical
Publication of EP0528138B1 publication Critical patent/EP0528138B1/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
    • F01D11/127—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 with a deformable or crushable structure, e.g. honeycomb
    • 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
    • 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. They essentially consist of cover plates with tines running in the circumferential direction, which seal against the housing or against a honeycomb arrangement (honeycomb). Such an arrangement is known, for example, from FR-A-2 406 074, but the housing therein is cylindrical. 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 is shown in FIG. 1 to be described later on the basis of the rotor blade of the second stage. With the mechanically and / or thermally highly loaded blades of the last stage, for example a gas turbine, such a solution with conventional materials is no longer possible.
  • a damper device which can be a damper wire, for example, is absolutely necessary for free-standing, long blades with a low natural frequency.
  • blades with tip seals and means for preventing vibrations have the disadvantage of large dissipation on the damper wire and in the tip seal.
  • GB-A-10179 A.D. 1912 discloses cover bands arranged centrally on the blade tips.
  • the invention tries to avoid all these disadvantages. Furthermore, it is based on the additional task of ensuring the guidance of the main flow in the case of blades of the type mentioned at the beginning.
  • this is achieved in that the conical end of the blades seals on the inlet and outlet sides with the tip against the housing and in that the cover plate arranged in the middle at the blade end has three throttle points against the housing, the throttle point on the inlet side forming a diagonal 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, which is particularly important in the case of output stages. In this way, high efficiencies of the combination power amplifier / diffuser can be achieved. In addition, low friction losses are to be expected due to the narrow shroud at the high peripheral speeds.
  • cover plates are rotationally symmetrical and if the parting lines between adjacent cover plates run in the direction of the chord. With this training, the inevitable Leakage flow deflected between the cover plates in the direction of the main flow.
  • the parting line is provided with three 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 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 protrudes 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.
  • cover plate spike which forms the middle throttle point, is in the axial plane of the blade's heavy line, additional bending moments on the blade are avoided.
  • 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 teeth of the cover plates which form 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 free-standing; ie they seal with the blade tip against the blade carrier 2.
  • the blades of the middle row 6b 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
  • the cover plates which extend across the entire blade width, form a stepped labyrinth with pure radial gaps. In the present case it is assumed that the rotor and the housing converge during operation due to the large relative axial expansions. For this reason, a further honeycomb arrangement 10 is provided on the blade carrier opposite the entry-side part of the cover plates against axial rubbing.
  • the highly loaded blades 6 of the outlet row 6c have a pitch / chord ratio of approximately 1 in the radially outer region. They work at high peripheral speeds of up to 650 m / sec in a temperature range of up to 650 ° C.
  • they are each provided with a cover plate 11 arranged centrally at the end of the blade, which plate forms three throttle points against the blade carrier 2.
  • the plates are provided with circumferential serrations 12, 13, 14 in three different radial planes.
  • the exit-side prong 14 forms, together with a honeycomb arrangement 15 inserted in the blade carrier 2, a radial gap 16.
  • the entry-side prong 12 runs diagonally and, together with a correspondingly configured honeycomb arrangement 18, forms a diagonal gap 19.
  • the operating position is shown in FIG. 2, 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 three prongs enclose two vortex chambers 20, 21, the radial displacement of the throttle points not influencing one another.
  • the conical end of the blades seals on the inlet and outlet sides with the tip 24, respectively. 29 against the housing.
  • An additional throttle point 22 is thus formed at the blade inlet via this tip seal.
  • the tip seal at the outlet also forms an additional throttling point 23 instead of the previous free swirl spaces at this point, as is contained in the cover plate seal 8 in the middle row 6b. This new type of tip seal at the outlet ensures a clean flow into the diffuser.
  • the blade end is provided with a positive offset 31 on the inlet side.
  • This offset is formed in that the blade tip has a smaller value than the taper 28 of the channel contour.
  • the offset 31 projects into a gap relief chamber 25 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 26 between adjacent cover plates run in the direction of the chord.
  • the circumferential sides of the cover plates are provided with three steps 27. These steps run in the axial plane of the three 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 teeth 12, 13 and 14 are tapered in the circumferential direction on the two overhangs of each cover plate. This Tapering 12a, 13a and 14a contribute significantly to the weight saving of the cover plates.
  • the invention is not limited to the exemplary embodiment shown and described.

Landscapes

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

Claims (8)

  1. Dispositif de garniture étanche de la fente entre les aubes mobiles et le corps (2) à contour conique (28) d'une turbomachine, dans lequel les aubes mobiles (6) sont pourvues de plaques de recouvrement périphériques (11), qui assurent l'étanchéité par rapport au corps avec des dents (12, 13, 14) en formant des fentes radiales (16, 17), caractérisé en ce que l'extrémité conique des aubes (6) du côté de l'entrée et du côté de la sortie assure l'étanchéité par rapport au corps (2) avec la pointe (24, 29) et que la plaque de recouvrement (11) disposée au milieu sur l'extrémité des aubes présente trois zones d'étranglement contre le corps, la zone d'étranglement du côté de l'entrée formant une fente diagonale (19).
  2. Dispositif suivant la revendication 1, caractérisé en ce que les plaques de recouvrement (11) présentent une symétrie de rotation.
  3. Dispositif suivant la revendication 1, caractérisé en ce que les joints (26) entre des plaques de recouvrement (11) voisines sont orientés dans la direction de la corde du profil.
  4. Dispositif suivant la revendication 3, caractérisé en ce que la plaque de recouvrement (11) est pourvue de trois degrés (27), les degrés étant situés dans le plan axial des dents (12, 13, 14).
  5. Dispositif suivant la revendication 1, caractérisé en ce que l'extrémité des aubes présente par rapport au contour (28) du profil une inclinaison moindre, de telle sorte que le décalage positif (31) ainsi créé à l'extrémité des aubes s'engage dans une chambre (25) de délestage des fentes disposée dans le corps (2).
  6. Dispositif suivant la revendication 1, caractérisé en ce que la dent (13) de la plaque de recouvrement qui forme la zone d'étranglement moyenne, se trouve au moins approximativement dans le plan axial de la ligne de gravité (30) des aubes.
  7. Dispositif suivant la revendication 1, caractérisé en ce qu'aux trois zones d' étranglement, le corps est pourvu de structures en nid d'abeilles (15, 18).
  8. Dispositif suivant la revendication 1, caractérisé en ce que les dents (12, 13, 14) des plaques de recouvrement (11) formant les zones d'étranglement se rétrécissent (12a, 13a, 14a) dans le sens périphérique aux endroits de chevauchement des plaques de recouvrement.
EP92110494A 1991-08-08 1992-06-22 Anneau d'aube de turbine axiale Expired - Lifetime EP0528138B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
CH2349/91 1991-08-08
CH234991 1991-08-08

Publications (2)

Publication Number Publication Date
EP0528138A1 EP0528138A1 (fr) 1993-02-24
EP0528138B1 true EP0528138B1 (fr) 1995-05-17

Family

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Family Applications (1)

Application Number Title Priority Date Filing Date
EP92110494A Expired - Lifetime EP0528138B1 (fr) 1991-08-08 1992-06-22 Anneau d'aube de turbine axiale

Country Status (5)

Country Link
US (1) US5238364A (fr)
EP (1) EP0528138B1 (fr)
JP (1) JPH05195815A (fr)
CA (1) CA2074326A1 (fr)
DE (1) DE59202211D1 (fr)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN106988797A (zh) * 2015-11-11 2017-07-28 通用电气公司 用于涡轮的整合的区段的***

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US6231301B1 (en) 1998-12-10 2001-05-15 United Technologies Corporation Casing treatment for a fluid compressor
EP1026367A1 (fr) * 1999-02-05 2000-08-09 Siemens Aktiengesellschaft Système d'étanchéité pour les extrémités d'aubes mobiles de turbomachine
US6241471B1 (en) * 1999-08-26 2001-06-05 General Electric Co. Turbine bucket tip shroud reinforcement
US6896483B2 (en) 2001-07-02 2005-05-24 Allison Advanced Development Company Blade track assembly
RU2302534C2 (ru) * 2001-12-11 2007-07-10 Альстом (Свитзерлэнд) Лтд. Газотурбинное устройство
US6805530B1 (en) * 2003-04-18 2004-10-19 General Electric Company Center-located cutter teeth on shrouded turbine blades
US6890150B2 (en) * 2003-08-12 2005-05-10 General Electric Company Center-located cutter teeth on shrouded turbine blades
US6913445B1 (en) * 2003-12-12 2005-07-05 General Electric Company Center located cutter teeth on shrouded turbine blades
DE102004025321A1 (de) * 2004-05-19 2005-12-08 Alstom Technology Ltd Strömungsmaschinenschaufel
US20070273104A1 (en) * 2006-05-26 2007-11-29 Siemens Power Generation, Inc. Abradable labyrinth tooth seal
EP1862641A1 (fr) 2006-06-02 2007-12-05 Siemens Aktiengesellschaft Canal d'écoulement axial pour turbomachine
US8568095B2 (en) * 2006-12-29 2013-10-29 Carrier Corporation Reduced tip clearance losses in axial flow fans
GB2445952B (en) * 2007-01-25 2011-07-20 Siemens Ag A gas turbine engine
US7901180B2 (en) * 2007-05-07 2011-03-08 United Technologies Corporation Enhanced turbine airfoil cooling
US8534993B2 (en) * 2008-02-13 2013-09-17 United Technologies Corp. Gas turbine engines and related systems involving blade outer air seals
DE102008023326A1 (de) * 2008-05-13 2009-11-19 Mtu Aero Engines Gmbh Deckband für Laufschaufeln einer Strömungsmaschine und Strömungsmaschine
DE102008038038A1 (de) * 2008-08-16 2010-02-18 Mtu Aero Engines Gmbh Laufschaufelsystem für eine Laufschaufelreihe einer Strömungsmaschine
US8608424B2 (en) * 2009-10-09 2013-12-17 General Electric Company Contoured honeycomb seal for a turbomachine
WO2011070636A1 (fr) * 2009-12-07 2011-06-16 三菱重工業株式会社 Turbine et pale de rotor de turbine
US8821114B2 (en) 2010-06-04 2014-09-02 Siemens Energy, Inc. Gas turbine engine sealing structure
DE102011086775A1 (de) 2011-07-20 2013-01-24 Mtu Aero Engines Gmbh Verfahren zur Herstellung eines Einlaufbelags, Einlaufsystem, Strömungsmaschine sowie Leitschaufel
JP5464233B2 (ja) * 2012-05-25 2014-04-09 株式会社Ｉｈｉ 圧縮機動翼
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
JP6571322B2 (ja) * 2014-10-06 2019-09-04 時夫 大川 空水熱発電システム
US10808539B2 (en) * 2016-07-25 2020-10-20 Raytheon Technologies Corporation Rotor blade for a gas turbine engine
DE102019216646A1 (de) * 2019-10-29 2021-04-29 MTU Aero Engines AG Laufschaufelanordnung für eine strömungsmaschine
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

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Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN106988797A (zh) * 2015-11-11 2017-07-28 通用电气公司 用于涡轮的整合的区段的***
CN106988797B (zh) * 2015-11-11 2020-10-23 通用电气公司 用于涡轮的整合的区段的***

Also Published As

Publication number Publication date
CA2074326A1 (fr) 1993-02-09
EP0528138A1 (fr) 1993-02-24
DE59202211D1 (de) 1995-06-22
JPH05195815A (ja) 1993-08-03
US5238364A (en) 1993-08-24

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