WO2018174739A1 - Système fournissant la mobilité d'un carénage de stator dans un étage de turbine - Google Patents

Système fournissant la mobilité d'un carénage de stator dans un étage de turbine Download PDF

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Publication number
WO2018174739A1
WO2018174739A1 PCT/RU2017/000160 RU2017000160W WO2018174739A1 WO 2018174739 A1 WO2018174739 A1 WO 2018174739A1 RU 2017000160 W RU2017000160 W RU 2017000160W WO 2018174739 A1 WO2018174739 A1 WO 2018174739A1
Authority
WO
WIPO (PCT)
Prior art keywords
stator
stator shroud
segment
shroud
circumference segment
Prior art date
Application number
PCT/RU2017/000160
Other languages
English (en)
Inventor
Gennadiy Valentinovich ZAGATIN
Vitaly Motelevich BREGMAN
Alexey Dmitrievich MAKAROV
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
Priority to PCT/RU2017/000160 priority Critical patent/WO2018174739A1/fr
Publication of WO2018174739A1 publication Critical patent/WO2018174739A1/fr

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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
    • F01D11/14—Adjusting or regulating tip-clearance, i.e. distance between rotor-blade tips and stator casing
    • F01D11/16—Adjusting or regulating tip-clearance, i.e. distance between rotor-blade tips and stator casing by self-adjusting means

Definitions

  • the present invention relates generally to turbo machinery, including both turbines and compressors, and more particularly, to stator shrouds and blades therein.
  • the invention can be applicable to any type of turbines with different working medium such as gas, steam, water, etc., the turbines where there is a stator and a rotor with blades .
  • blades in turbo machinery are rotating airfoil-shaped components designed to convert energy from a working medium such as gas, steam, or water, etc. into mechanical work via the rotation of a rotor.
  • a working medium such as gas, steam, or water, etc.
  • This radial clearance also allows the escape of the some of the working medium without performing useful work. Performance of a turbine and a compressor thus can be enhanced by decreasing the radial clearance and sealing the outer edge of the blade to prevent the working medium from escaping into the gap.
  • the stator shroud is a stationary element and preferably has a high thermal response (low thermal inertia) to allow the thermal deformation of the stator shroud during periods of acceleration to accommodate the deformation of the rotor during those periods.
  • FIG 1 shows portion of a conventional turbine stage (prior art) that may be used in the turbine or otherwise.
  • the turbine stage 1 having the axis 2, comprises a rotor disc 3, a blade 4 with a blade tip 5, a stator 6 and a stator shroud 7 with a stator shroud outer surface 8.
  • the blade 4 including the blade tip 5 and the stator shroud outer surface 8 are affected by the working medium 9.
  • stator shroud 7 is formed by a plurality of arcuate stator shroud segments combined into an annular assembly, and attached to an inner peripheral wall of the stator 6 by intermediate components 10.
  • the stator shroud 7 is rigidly fixed to the stator 6.
  • stator shroud 7 Surrounding the blades 4 is an annular stator shroud 7 fixedly joined to a surrounding stator 6 casing.
  • the stator shroud 7 is suspended closely atop the blade tips 5 for providing a small gap or radial clearance 11 there between.
  • the radial clearance 11 should be as small as possible to provide an effective medium seal thereat during operation for minimizing the amount of working medium 9 leakage there through for maximizing efficiency of operation of the engine.
  • Efforts have been made to actively control the spacing between rotating engine blade tips and static stator shroud segments so as to try to maintain the target minimal spacing while avoiding blade -stator shroud contact.
  • One such active control is to utilize heat to move the stator shroud (US. No. 4, 928, 240) .
  • the object is solved by a system of providing mobility of a stator shroud in a turbine stage as defined in claim 1.
  • the present invention provides a system of providing mobility of a stator shroud in a turbine stage, wherein the turbine stage comprises a plurality of blades that are connected to a rotor disc, a stator, and at least one stator shroud.
  • the at least one stator shroud comprises a plurality of stator shroud circumference segments in the circumference direction. Each stator shroud circumference segment is connected to the stator in such way that there is at least one internal cavity between the stator and each stator shroud circumference segment. Each stator shroud circumference segment is adapted to move in radial direction.
  • the system comprises at least one group of elastic components wherein each elastic component is arranged in the at least one internal cavity between the stator and the respective stator shroud circumference segment. Each elastic component is adapted
  • the present invention is based on the insight that the fixation of the stator shroud to the stator is not rigid, and the stator shroud has elastic components implemented in the cavity between the stator and the stator shroud. Therefore the stator shroud is mobile.
  • the present invention is proposed to provide a new system of providing mobility of a stator shroud in a turbine stage .
  • the elastic components of the group are arranged in the at least one internal cavity in such way that the elastic components are evenly distributed along the circumference direction of the respective stator shroud circumference segment.
  • This feature allows providing uniform radial movement of the respective stator shroud circumference segment along the circumference direction of the stator shroud.
  • stator and each stator shroud circumference segment have special arrangements that limit the movement of the respective stator shroud circumference segment inwards and outwards.
  • This feature allows controlling the movement of the stator shroud circumference segments and also such special arrangements can be required within assembling the turbine stage .
  • stator and each stator shroud circumference segment have seals arranged in such way that there is no leakage of medium into or out of the at least one internal cavity between the stator and the respective stator shroud circumference segment.
  • At least one elastic component of the group of the elastic components is a spring or bellows.
  • FIG. 1 schematically illustrates portion of a conventional turbine stage (prior art) ;
  • Fig. 2 schematically illustrates a system of providing mobility of a stator shroud in a turbine stage in accordance with the present invention
  • Fig. 3 schematically illustrates a system of providing mobility of a stator shroud in a turbine stage in accordance with the present invention (III-III view) ;
  • FIG 2 and FIG 3 illustrate a system 12 of providing mobility of a stator shroud 7 in a turbine stage 1.
  • the turbine stage 1 comprises a plurality of blades 4 that are connected to a rotor disc 3, a stator 6, and at least one stator shroud 7.
  • the at least one stator shroud 7 comprises a plurality of stator shroud circumference segments 13 in the circumference direction.
  • Each stator shroud circumference segment 13 is connected to the stator 6 in such way that there is at least one internal cavity 14 between the stator 6 and each stator shroud circumference segment 13. There can be more internal cavities 14 formed between the stator 7 and particular stator shroud circumference segment 13. Each stator shroud circumference segment 13 is adapted to move in radial direction.
  • the rotor disc 3 rotates around the axis 2 of rotation.
  • Moving in radial direction refers to the moving towards and outwards of the axis 2 along a radius that is a line from the center of the turbine stage 1 to the outer surface perpendicular to the axis 2.
  • the system 12 comprises at least one group of elastic components 15 wherein each elastic component 15 is arranged in the at least one internal cavity 14 between the stator 6 and the respective stator shroud circumference segment 13.
  • Each elastic component 15 is adapted
  • the elastic component 15 can be a spring, a bellow or sylphon, or any other component that has compliance and elasticity in the radial direction.
  • stator shroud circumference segments 13 that are used, and therefore the bigger each stator shroud circumference segment 13 is in the circumference direction, the more elastic components 15 should be inside in the internal cavity 14 between the stator 6 and the stator shroud circumference segment 13 to provide even movement of the stator shroud circumference segment 13 along circumference direction. And vise versa the more stator shroud circumference segments 13 the stator shroud 7 are formed of, the less elastic components 15 should be inside in the internal cavity 14 between the stator 6 and the stator shroud circumference segment 13. So the only one elastic component 15 can be arranged in the at least one internal cavity 14 between the stator 6 and the respective stator shroud circumference segment 13.
  • stator shroud circumference segments 13 There are generally eight or more of these stator shroud circumference segments 13. The number of the stator shroud circumference segment 13 of the stator shroud 7, the type and number of elastic components 15 per each internal cavity 14 and their characteristics should be defined by experts.
  • stator 6 and each stator shroud circumference segment 13 have special arrangements 16 that limit the movement of the respective stator shroud circumference segment 13 inwards and outwards.
  • stator 6 and each stator shroud circumference segment 13 have seals 17 arranged in such way that there is no leakage of medium into and out of the at least one internal cavity 14 between the stator 6 and the respective stator shroud circumference segment 13. In other words, there is no leakage of working medium 9 into the at least one internal cavity 14, and there is no leakage of cooling agent, if any, out of the at least one internal cavity 14.
  • Such sealing 17 should be especially arranged in the area where the stator shroud circumference segment 13 is connected to the stator 7 and in the area of the special arrangements 16 in such a way that during the movement of the stator shroud circumference segment 13 there are no leakage of medium as well.
  • the systems 12 works as following: the stator shroud 7 that is formed of a plurality of circumferentially adjoining, segments 13, is mounted atop the blades 4.
  • the size of the blades 4 and the stator shroud 7 can vary under different conditions (temperature, vibration, etc) during different operational modes of the turbine.
  • stator shroud circumference segment 13 moves radially outwards since the stator shroud circumference segment 13 is not fixed rigid and since the elastic components 15 allow such movement.
  • the respective stator shroud circumference segment 13 moves radially outwards till the state when there is no pressure / no push from the side of the blade 4 on it.
  • stator shroud 7 and the blade 4 can be still in the contact, but such contact without mutual pressure from each component does not harm the blade tip 5 of the blade 4 and the stator shroud 7 as well. Consequently the radial clearance 11 between the stator shroud 7 and the blade tips 5 is minimal .
  • the elastic components 15 move the respective stator shroud circumference segment 13 radially inwards.
  • the elastic components 15 move the respective stator shroud circumference segment 13 radially inwards till the state when the respective stator shroud circumference segment 13 and the at least one blade 4 get in contact, but without any pressure / any push from the side of the blade 4.
  • stator shroud circumference segments 13 and the stator 6 have special arrangements 16, for example hooks as it is shown on FIG 2, that limit the movement of the respective stator shroud circumference segment 13 inwards and outwards.
  • special arrangements 16 prevent the stator shroud circumference segments 13 from separation from the stator 6.
  • special arrangements 16 are required during assembling the turbine stage 1. Type of the special arrangements 16, their sizes, etc. are defined by experts.
  • stator shroud circumference segment 13 So having such elastic components 15 inside the internal cavity 14 between the stator 6 and the stator shroud circumference segment 13 together with absence of the rigid fixation the stator shroud circumference segments 13 to the stator 6 allows providing mobility of the stator shroud 7 in the turbine stage 1, and consequently, providing minimal radial clearance 11 between the blades 4 and the stator shroud 8 during different operational modes of the turbine.

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

Abstract

L'invention concerne un système fournissant la mobilité d'un carénage de stator (7) dans un étage de turbine (1). Ledit étage de turbine comprend plusieurs pales (4) qui sont reliées à un disque de rotor (3), un stator (6) et au moins un carénage de stator qui comprend plusieurs segments de circonférence de carénage de stator (13) dans la direction circonférentielle. Chaque segment est relié audit stator de sorte qu'il y ait au moins une cavité interne (14) entre ledit stator et ledit segment, ledit segment étant conçu pour se déplacer dans une direction radiale. Le système comprend au moins un groupe d'éléments élastiques (15), chaque élément élastique étant disposé dans ladite cavité interne et étant conçu pour permettre un déplacement radial vers l'extérieur dudit segment dans le cas où au moins une desdites pales est en contact avec ledit segment et pour déplacer ledit segment radialement vers l'intérieur dans le cas où ladite pale n'est pas en contact avec ledit segment.
PCT/RU2017/000160 2017-03-21 2017-03-21 Système fournissant la mobilité d'un carénage de stator dans un étage de turbine WO2018174739A1 (fr)

Priority Applications (1)

Application Number Priority Date Filing Date Title
PCT/RU2017/000160 WO2018174739A1 (fr) 2017-03-21 2017-03-21 Système fournissant la mobilité d'un carénage de stator dans un étage de turbine

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
PCT/RU2017/000160 WO2018174739A1 (fr) 2017-03-21 2017-03-21 Système fournissant la mobilité d'un carénage de stator dans un étage de turbine

Publications (1)

Publication Number Publication Date
WO2018174739A1 true WO2018174739A1 (fr) 2018-09-27

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Citations (18)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2634090A (en) * 1950-07-28 1953-04-07 Westinghouse Electric Corp Turbine apparatus
GB881880A (en) * 1959-05-22 1961-11-08 Power Jets Res & Dev Ltd Turbo-machine stator construction
US3966356A (en) * 1975-09-22 1976-06-29 General Motors Corporation Blade tip seal mount
GB2223811A (en) * 1988-09-09 1990-04-18 Mtu Muenchen Gmbh Gas turbine having ring for sealing at rotor blade tips
US4928240A (en) 1988-02-24 1990-05-22 General Electric Company Active clearance control
US5203673A (en) 1992-01-21 1993-04-20 Westinghouse Electric Corp. Tip clearance control apparatus for a turbo-machine blade
US5263816A (en) 1991-09-03 1993-11-23 General Motors Corporation Turbomachine with active tip clearance control
EP0781371A1 (fr) * 1994-08-31 1997-07-02 United Technologies Corporation Procede de commande dynamique du jeu d'extremites
JP2000097352A (ja) * 1998-09-24 2000-04-04 Mitsubishi Heavy Ind Ltd ターボ回転機械の自動調整シール
US20040115043A1 (en) * 2002-10-10 2004-06-17 Stuart Lee Turbine shroud segment attachment
EP1467066A2 (fr) * 2003-04-09 2004-10-13 Rolls-Royce Plc Joint ridé
JP2010001777A (ja) * 2008-06-19 2010-01-07 Toshiba Corp シール装置および蒸気タービン
WO2010058137A1 (fr) * 2008-11-21 2010-05-27 Turbomeca Organe de positionnement pour segment d'anneau
US20120224953A1 (en) * 2011-03-03 2012-09-06 Techspace Aero S.A. External Segmented Shell Capable of Correcting For Rotor Misalignment in Relation to the Stator
WO2015044592A1 (fr) * 2013-09-25 2015-04-02 Snecma Dispositif de limitation de jeu pour turbomachine et procédé de démontage d'une cartouche
US20150285152A1 (en) * 2014-04-03 2015-10-08 United Technologies Corporation Gas turbine engine and seal assembly therefore
JP2016084861A (ja) * 2014-10-24 2016-05-19 株式会社東芝 ラビリンスシール装置および軸流型ターボ機械
EP3093449A1 (fr) * 2015-05-11 2016-11-16 General Electric Company Système de rétention de carénage avec des ressorts de retenue

Patent Citations (18)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2634090A (en) * 1950-07-28 1953-04-07 Westinghouse Electric Corp Turbine apparatus
GB881880A (en) * 1959-05-22 1961-11-08 Power Jets Res & Dev Ltd Turbo-machine stator construction
US3966356A (en) * 1975-09-22 1976-06-29 General Motors Corporation Blade tip seal mount
US4928240A (en) 1988-02-24 1990-05-22 General Electric Company Active clearance control
GB2223811A (en) * 1988-09-09 1990-04-18 Mtu Muenchen Gmbh Gas turbine having ring for sealing at rotor blade tips
US5263816A (en) 1991-09-03 1993-11-23 General Motors Corporation Turbomachine with active tip clearance control
US5203673A (en) 1992-01-21 1993-04-20 Westinghouse Electric Corp. Tip clearance control apparatus for a turbo-machine blade
EP0781371A1 (fr) * 1994-08-31 1997-07-02 United Technologies Corporation Procede de commande dynamique du jeu d'extremites
JP2000097352A (ja) * 1998-09-24 2000-04-04 Mitsubishi Heavy Ind Ltd ターボ回転機械の自動調整シール
US20040115043A1 (en) * 2002-10-10 2004-06-17 Stuart Lee Turbine shroud segment attachment
EP1467066A2 (fr) * 2003-04-09 2004-10-13 Rolls-Royce Plc Joint ridé
JP2010001777A (ja) * 2008-06-19 2010-01-07 Toshiba Corp シール装置および蒸気タービン
WO2010058137A1 (fr) * 2008-11-21 2010-05-27 Turbomeca Organe de positionnement pour segment d'anneau
US20120224953A1 (en) * 2011-03-03 2012-09-06 Techspace Aero S.A. External Segmented Shell Capable of Correcting For Rotor Misalignment in Relation to the Stator
WO2015044592A1 (fr) * 2013-09-25 2015-04-02 Snecma Dispositif de limitation de jeu pour turbomachine et procédé de démontage d'une cartouche
US20150285152A1 (en) * 2014-04-03 2015-10-08 United Technologies Corporation Gas turbine engine and seal assembly therefore
JP2016084861A (ja) * 2014-10-24 2016-05-19 株式会社東芝 ラビリンスシール装置および軸流型ターボ機械
EP3093449A1 (fr) * 2015-05-11 2016-11-16 General Electric Company Système de rétention de carénage avec des ressorts de retenue

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