WO2011018413A1 - Diaphragmes de turbine - Google Patents

Diaphragmes de turbine Download PDF

Info

Publication number
WO2011018413A1
WO2011018413A1 PCT/EP2010/061451 EP2010061451W WO2011018413A1 WO 2011018413 A1 WO2011018413 A1 WO 2011018413A1 EP 2010061451 W EP2010061451 W EP 2010061451W WO 2011018413 A1 WO2011018413 A1 WO 2011018413A1
Authority
WO
WIPO (PCT)
Prior art keywords
ring
inner ring
blade units
blade
diaphragm
Prior art date
Application number
PCT/EP2010/061451
Other languages
English (en)
Inventor
David Nelmes
Philip David Hemsley
Terence James
Original Assignee
Alstom Technology Ltd
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 Alstom Technology Ltd filed Critical Alstom Technology Ltd
Publication of WO2011018413A1 publication Critical patent/WO2011018413A1/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
    • F01D9/00—Stators
    • F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
    • F01D9/04—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector
    • F01D9/042—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector fixing blades to stators
    • 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
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/24—Casings; Casing parts, e.g. diaphragms, casing fastenings
    • F01D25/246—Fastening of diaphragms or stator-rings
    • 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
    • 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
    • F05D2240/00—Components
    • F05D2240/80—Platforms for stationary or moving blades

Definitions

  • the present disclosure relates to diaphragms for use in axial fluid flow turbo- machines such as steam turbines, in which power is extracted from a compressed gas by expanding it through an alternating sequence of rotating blades mounted on a rotor and static blades mounted in a diaphragm.
  • a traditional way of constructing a turbine diaphragm is to mount an annulus of aerofoil blades between an inner ring and an outer ring.
  • Each blade is formed as part of a blade unit in which the blade extends between an inner platform and an outer platform, the blade unit being machined as a single component.
  • Each platform is in the form of a segment of a cylinder so that when the annulus of blade units is assembled the inner platforms combine to create an inner cylinder and the outer platforms combine to create an outer cylinder.
  • the outer platforms are welded to an outer ring that provides support and rigidity to the diaphragm.
  • the inner platforms are welded to an inner ring that prevents axial deflection of the turbine blades.
  • the inner and outer rings are each divided into two semicircular halves along a plane that contains the axis of the diaphragm and passes between blade units so that the entire diaphragm can be separated into two parts for assembly around the rotor of the turbo- machine.
  • the two halves of the outer ring are bolted together when the diaphragm is assembled.
  • the two halves of the inner ring are not bolted together but are held in place by being welded to the blade units, which in turn are welded to the outer ring.
  • the inner ring presents a large axially facing surface, which is subjected to the high pressure of the working fluid passing through the turbine. The resulting high force tends to cause large axial deflections of the inner ring out of the plane of the diaphragm. Moreover, because the two halves of the inner ring are not bolted together, each half can be deflected independently and break the symmetry of the diaphragm about the axis.
  • Published patent application US 2008/0170939 discloses a compact turbine diaphragm that does away with the inner ring, thereby saving the cost of manufacturing that component and the cost of welding it to the blade units.
  • the inner platforms are made to interlock in such a manner that the inner cylinder created by them serves the purpose of the inner ring.
  • the blade units become subject to a torque that pre-stresses them and helps to increase the rigidity of the diaphragm. Nevertheless, the absence of an inner ring leaves the blades more vulnerable to local axial deflection, with the consequence that the compact diaphragm ring is not suitable for use under the higher forces experienced in the environment of an impulse turbine.
  • a first form of mechanical engagement between the inner platform of each blade unit and the inner ring preferably comprises a circumferential rib formed on one of the inner ring and the inner platforms, the rib locating in a circumferential groove formed in the other one of the inner ring and the inner platforms.
  • a second form of mechanical engagement between the inner platform of each blade unit and the inner ring preferably comprises radially extending dowels or keys that form a radial connection between the inner platform portions of the blade units and the ring and are operative to prevent relative circumferential movement between the blade units and the ring and to maintain concentricity of the inner ring with the outer ring during differential thermal growth of the two components.
  • the inner ring preferably comprises two semicircular halves, which are bolted to one another during assembly of the diaphragm. Because the halves are bolted together, the inner ring behaves as a single unit, thereby overcoming the problem in the prior art that the two halves could be axially deflected independently of one another.
  • Figure 1 is a perspective view of an assembled steam turbine diaphragm according to the present disclosure.
  • Figure 2A is a cross section through one half of a diaphragm ring according to a first embodiment, taken on a plane that contains the axis.
  • Figure 2B is a cross section similar to Figure 2A through one half of a diaphragm ring according to a second embodiment.
  • Figures 3A-3D are a series of perspective views showing steps in the assembly of a diaphragm ring according to the first embodiment.
  • Figures 4A and 4B are perspective views showing steps in the assembly of a diaphragm ring according to a third embodiment.
  • FIGs 1 and 2A illustrate a steam turbine diaphragm comprising an inner ring 2 formed from two semicircular halves 3,4; an outer ring 6 formed from two semicircular halves 7,8; and an annulus of static blades formed from a large number of static blade units 12 arranged between the inner and outer rings 2,6.
  • the inner ring 2 is fitted with seals (not shown), which seal against an inner rotating shaft or like rotating parts of the turbine.
  • the outer ring 6 is seated in and fixed to an outer turbine casing (not shown).
  • Each blade unit 12 is machined from a single block and comprises an aerofoil blade 14 extending between an inner platform 16 and an outer platform 18.
  • a blade unit may comprise two or more blades joined to unitary inner and outer platform portions.
  • Such blade units may be manufactured either by welding together adjacent inner and outer platforms that have only a single aerofoil blade extending therebetween, or by casting a multi-bladed blade unit in a mould.
  • Each platform 16,18 is in the general form of a segment of a cylinder or frustum of a hollow cone and when the annulus of blade units 12 is assembled the inner platforms 16 combine to create an inner cylinder or frustum and the outer platforms 18 combine to create an outer cylinder or frustum, which respectively define the radially inner and outer walls of the air path through the diaphragm.
  • the outer platforms 18 are not exactly cylindrical but are slightly tapered to form a shallow frustum.
  • the outer ring 6 is forced over the annulus of blade units 12, as described in US 2008/0170939.
  • the outer ring 6 is fixedly connected to the annulus of blade units 12 by welds 20 (Fig. 2) formed between the outer ring 6 and the outer platforms 18.
  • the blade units could be secured to the outer ring by a suitable mechanical fixing; for example, the outer platforms could be formed as inverted "L" shapes, each platform therefore having an axial projection that would hook into a complimentarily- shaped recess in an outer ring.
  • the inner ring 2 is not welded to the blade units 12 but mechanically engages them in such as manner as to prevent relative movement therebetween in the direction of arrow 22, i.e., parallel to the diaphragm's major axis , but to allow relative radial movement therebetween in directions perpendicular to the axis (shown by arrow 23).
  • Such relative radial movement will of course be restricted, being governed by the relative rates of thermal expansion of the inner and outer rings 2 and 6 and the blade units 12 during operation of the steam turbine of which the diaphragm is a part.
  • FIG. 2A shows one form of the mechanical engagement between the inner ring 2 and the blade units 12, in which a circumferential rib 24 projecting radially outwards from the inner ring 2 is located in a circumferentially aligned groove 25 formed in an inwards facing surface of each inner platform 16.
  • Fig. 2B shows an alternative form of the mechanical engagement in which a circumferential rib 26 projecting radially inwards from each inner platform 16 is located in a circumferential groove 27 formed in an outwards facing surface of the inner ring 2.
  • This alternative form may be preferred because the lack of a re-entrant groove 25 in the inner platform 16, when viewed in the axial direction, facilitates machining of the blade unit 12 in a single operation.
  • the outer ring 6 is formed from two semicircular halves 7,8, which are releasably bolted to one another.
  • the ring 6 has a pair of bolt holes 30, which are oriented tangentially to the ring 6 and pass through the mutually abutting end faces of the respective halves 7,8.
  • the inner ring 2 is similarly formed from two semicircular halves 3,4, which are releasably bolted to one another via a pair of bolt holes 32, visible in Fig. 3B.
  • Figures 3A-3D show a sequence of steps for assembling the diaphragm. The method of assembly allows the diaphragm to be built around the rotor of a turbo-machine but, for clarity, neither the rotor nor the necessary seals between the rotor and the inner ring 2 are shown in the drawings.
  • FIG. 3A the lower half 8 of the outer ring 6 has already been manufactured the blade units 12 have been welded to it. , and it is suitably oriented for the assembly to begin. (The orientation shown in the drawings is not the only possible one.)
  • Fig. 3B the lower half 4 of the inner ring 2 is lowered into engagement with the lower half-annulus of blade units 12, such that the radially projecting rib 24 on the inner half-ring 4 locates in the circumferential groove 25 (best seen in Figs. 2A and 3A) formed by the assembly of inner platforms 16 of the blade units 12. The blade units 12 are thereby prevented from moving axially relative to the inner ring 2.
  • radial dowels 34 are fitted in at least two locations in the lower half 4 of the inner ring 2.
  • the dowels 34 pass through bores 35 in the inner ring and extend into shallow blind radial bores (not visible in the drawings) created in the inner surface of certain of the inner platforms 16 in order to prevent relative movement between the inner ring 2 and the annulus of blade units 12 in the circumferential direction. Without the dowels 34 (or equivalent means for preventing such movement), the inner ring 2 would tend to rotate about the major axis of the diaphragm independently of the annulus of blade units 12, due to the high rotational forces exerted by the working fluid during use of the turbine.
  • the radial dowels are secured in the inner ring bores 35 by any appropriate means, e.g., by arranging an interference fit in the bores 35.
  • the shallow blind radial bores mentioned above are sized to allow the required radial movement of the inner platforms 16 relative to the dowels 34 and the inner ring 2.
  • a further function of the radial dowels is to ensure that the inner ring 2 remains concentric with the outer ring 6 during differential thermal growth of the two components.
  • a single vertical radial dowel 34 may be inserted into the top half 3 of inner ring 2, although this is not essential due to the secure bolting of the top half 3 of the inner ring to the bottom half 4 of the inner ring. If this vertical dowel is used then it must be fitted in a similar manner to the bottom half dowels in a pre-assembly process, prior to fitting the diaphragm around the rotor.
  • Fig. 3C the upper half 3 of the inner ring 2 is then lowered onto the lower half- ring4, thereby encircling the rotor (not shown).
  • the two halves 3,4 are then bolted together by means of bolts passing through tangential bolt holes 32 that intersect the mutually abutting end faces of the two halves 3,4.
  • the two halves 7,8 of the outer ring 6 are then bolted together by means of bolts 31 passing through the tangential bolt holes 30 that intersect the mutually abutting end faces of the two half-rings 7,8.
  • Figs. 4A and 4B illustrate an alternative arrangement, in which radial dowels are replaced by vertically and horizontally extending radial keys 36, 38, respectively.
  • the keys 36, 38 take the form of protruding rectangular lands, though as will be apparent to the skilled person, other shapes of keys may be adopted.
  • inset A is an enlarged view of area A, showing the vertical key 36 formed on the radially inner surface of one of the inner static blade platforms 16.
  • vertical key 36 protrudes into a corresponding complementarily- shaped recess (not shown) on the external surface of the half -ring 4.
  • the vertical key could be formed on the external surface of the half-ring 4 and would protrude into a corresponding complementarily- shaped recess on the radially inner surface of one of the inner static blade platforms 16.
  • FIG. 4B shows two horizontal keys 38, provided at the horizontal joint of the diaphragm, at diametrically opposite ends of the lower half 4 of the inner ring 2.
  • Inset C shows an enlarged view of one of the horizontal keys 38 in area C at one end of the half -ring 4.
  • horizontal keys 38 fit into complementarily- shaped recesses 40 provided on the inner surface of platforms 16; see inset B, which shows an enlarged view of one of the recesses 40 in area B of Fig. 4A.
  • the horizontal keys 38 are then secured by the action of bolting together the top and bottom halves of the inner and outer rings. It is at the option of the skilled person to configure the keys in different ways.
  • the three radially extending keys may comprise a first vertically directed key and diametrically opposed second and third horizontally directed keys, and it can be arranged that the keys protrude either from the inner ring or from the platform portions into corresponding complementarily- shaped recesses provided on the opposing radially adjacent surface of the other component.

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

Abstract

L'invention porte sur un diaphragme pour une turbine qui comprend une bague externe (6) et une bague interne (2), avec un espace annulaire composé d'unités d'aube (12) du type plateforme entre les deux. La bague externe (6) est soudée ou fixée d'une autre façon aux plateformes externes (18) des unités d'aube (12) d'une façon classique, mais la bague interne (2) n'est pas soudée aux plateformes internes (16) des unités d'aube (12). Au contraire, il y a des prises mécaniques entre la plateforme interne (16) de chaque unité d'aube (12) et la bague interne (2), qui ont pour action, premièrement, de limiter le mouvement relatif entre l'unité d'aube (12) et la bague (2) dans une direction parallèle à l'axe mais qui permet un mouvement relatif entre l'unité d'aube (12) et la bague (2) dans des directions perpendiculaires à l'axe et, deuxièmement, pour empêcher le mouvement circonférentiel relatif entre les unités d'aube et la bague et pour maintenir la concentricité de la bague interne avec la bague externe pendant la dilatation thermique différentielle des deux composants. Les prises mécaniques peuvent comprendre une nervure (24, 26) faisant saillie radialement sur une partie qui se loge dans une rainure circonférentielle (25, 27) de l'autre partie et des chevilles (34) s'étendant radialement, ou des clavettes, qui forment une liaison radiale entre les parties de plateforme interne des unités d'aube et la bague. La bague interne (2) peut être formée de deux moitiés semi-circulaires (3, 4) qui peuvent être boulonnées l'une à l'autre pendant l'assemblage du diaphragme autour du rotor d'une turbomachine.
PCT/EP2010/061451 2009-08-08 2010-08-05 Diaphragmes de turbine WO2011018413A1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
GB0913885A GB0913885D0 (en) 2009-08-08 2009-08-08 Turbine diaphragms
GB0913885.0 2009-08-08

Publications (1)

Publication Number Publication Date
WO2011018413A1 true WO2011018413A1 (fr) 2011-02-17

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Family Applications (1)

Application Number Title Priority Date Filing Date
PCT/EP2010/061451 WO2011018413A1 (fr) 2009-08-08 2010-08-05 Diaphragmes de turbine

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WO (1) WO2011018413A1 (fr)

Cited By (13)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE102012008723A1 (de) 2011-05-05 2012-11-08 Alstom Technology Ltd. Leitrad für Turbomaschinen und Herstellungsverfahren
WO2012153037A1 (fr) * 2011-05-09 2012-11-15 Snecma Virole annulaire de moteur d'aeronef comportant une fenetre d'introduction d'aubes
RU2510464C1 (ru) * 2012-08-01 2014-03-27 Вячеслав Аркадьевич Хаимов Поворотная регулирующая диафрагма теплофикационной паровой турбины
EP2787176A1 (fr) 2013-04-02 2014-10-08 MTU Aero Engines GmbH Ensemble d'aube directrice
CN105252178A (zh) * 2015-11-17 2016-01-20 宜昌船舶柴油机有限公司 多层环板轴向焊接的同心度控制方法
EP3284919A1 (fr) * 2016-08-16 2018-02-21 General Electric Technology GmbH Turbine à flux axial comportant un diaphragme divisé en deux moitiés au niveau d'un plan de séparation
JP2018184946A (ja) * 2017-04-27 2018-11-22 ジン・ヤン・ティービーエックス・カンパニー・リミテッド タービン用ノズルプレートアセンブリー
WO2020261628A1 (fr) * 2019-06-27 2020-12-30 三菱重工業株式会社 Anneau de support d'aubes de stator et turbine associée
CN113202569A (zh) * 2021-06-16 2021-08-03 中国航发沈阳发动机研究所 一种发动机静子结构
CN113202568A (zh) * 2021-06-16 2021-08-03 中国航发沈阳发动机研究所 一种发动机静子结构及其装配方法
CN113513374A (zh) * 2021-07-26 2021-10-19 中国船舶重工集团公司第七0三研究所 船舶燃气轮机可方便拆卸式压气机静叶环及其装配方法
CN113847105A (zh) * 2021-10-26 2021-12-28 中国航发沈阳发动机研究所 一种发动机奇数可调静子叶片静子部件装配结构及其方法
RU2793871C1 (ru) * 2022-06-10 2023-04-07 Акционерное общество "Силовые машины - ЗТЛ, ЛМЗ, Электросила, Энергомашэкспорт" (АО "Силовые машины") Наборная диафрагма паровой турбины

Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0384166A2 (fr) * 1989-02-21 1990-08-29 Westinghouse Electric Corporation Construction de diaphragme de compresseur
US5788456A (en) * 1997-02-21 1998-08-04 Dresser-Rand Company Turbine diaphragm assembly and method thereof
EP1408198A1 (fr) * 2001-07-19 2004-04-14 Toshiba Carrier Corporation Membrane de buse de type a assembler et procede d'assemblage
US20080170939A1 (en) 2007-01-12 2008-07-17 Bryan Roy Palmer Diaphragm for Turbomachines and Method of Manufacture

Patent Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0384166A2 (fr) * 1989-02-21 1990-08-29 Westinghouse Electric Corporation Construction de diaphragme de compresseur
US5788456A (en) * 1997-02-21 1998-08-04 Dresser-Rand Company Turbine diaphragm assembly and method thereof
EP1408198A1 (fr) * 2001-07-19 2004-04-14 Toshiba Carrier Corporation Membrane de buse de type a assembler et procede d'assemblage
US20080170939A1 (en) 2007-01-12 2008-07-17 Bryan Roy Palmer Diaphragm for Turbomachines and Method of Manufacture

Cited By (26)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE102012008723A1 (de) 2011-05-05 2012-11-08 Alstom Technology Ltd. Leitrad für Turbomaschinen und Herstellungsverfahren
JP2012233479A (ja) * 2011-05-05 2012-11-29 Alstom Technology Ltd ターボ機械用ダイヤフラム及びその製造方法
US9127559B2 (en) 2011-05-05 2015-09-08 Alstom Technology Ltd. Diaphragm for turbomachines and method of manufacture
WO2012153037A1 (fr) * 2011-05-09 2012-11-15 Snecma Virole annulaire de moteur d'aeronef comportant une fenetre d'introduction d'aubes
FR2975124A1 (fr) * 2011-05-09 2012-11-16 Snecma Virole annulaire de moteur d’aeronef comportant une fenetre d’introduction d’aubes
GB2504883A (en) * 2011-05-09 2014-02-12 Snecma Aircraft engine annular shroud comprising an opening for the insertion of blades
GB2504883B (en) * 2011-05-09 2017-12-13 Snecma Aircraft engine annular shroud comprising an opening for the insertion of blades
US9879549B2 (en) 2011-05-09 2018-01-30 Snecma Aircraft engine annular shroud comprising an opening for the insertion of blades
RU2510464C1 (ru) * 2012-08-01 2014-03-27 Вячеслав Аркадьевич Хаимов Поворотная регулирующая диафрагма теплофикационной паровой турбины
EP2787176A1 (fr) 2013-04-02 2014-10-08 MTU Aero Engines GmbH Ensemble d'aube directrice
CN105252178A (zh) * 2015-11-17 2016-01-20 宜昌船舶柴油机有限公司 多层环板轴向焊接的同心度控制方法
WO2018033408A1 (fr) * 2016-08-16 2018-02-22 General Electric Technology Gmbh Turbine à flux axial ayant un diaphragme fendu en deux moitiés au niveau d'un plan de joint horizontal
CN109477398B (zh) * 2016-08-16 2022-02-15 通用电器技术有限公司 具有在水平接合平面处分成两个半部的导流盘的轴流式涡轮
CN109477398A (zh) * 2016-08-16 2019-03-15 通用电器技术有限公司 具有在水平接合平面处分成两个半部的导流盘的轴流式涡轮
US10934892B2 (en) 2016-08-16 2021-03-02 General Electric Technology Gmbh Axial flow turbine having a diaphragm split in two halves at a horizontal joint plane
EP3284919A1 (fr) * 2016-08-16 2018-02-21 General Electric Technology GmbH Turbine à flux axial comportant un diaphragme divisé en deux moitiés au niveau d'un plan de séparation
JP2018184946A (ja) * 2017-04-27 2018-11-22 ジン・ヤン・ティービーエックス・カンパニー・リミテッド タービン用ノズルプレートアセンブリー
WO2020261628A1 (fr) * 2019-06-27 2020-12-30 三菱重工業株式会社 Anneau de support d'aubes de stator et turbine associée
JP2021004598A (ja) * 2019-06-27 2021-01-14 三菱重工業株式会社 静翼支持リング及びタービン
JP7349274B2 (ja) 2019-06-27 2023-09-22 三菱重工業株式会社 静翼支持リング及びタービン
CN113202569A (zh) * 2021-06-16 2021-08-03 中国航发沈阳发动机研究所 一种发动机静子结构
CN113202568A (zh) * 2021-06-16 2021-08-03 中国航发沈阳发动机研究所 一种发动机静子结构及其装配方法
CN113513374A (zh) * 2021-07-26 2021-10-19 中国船舶重工集团公司第七0三研究所 船舶燃气轮机可方便拆卸式压气机静叶环及其装配方法
CN113513374B (zh) * 2021-07-26 2022-10-21 中国船舶重工集团公司第七0三研究所 船舶燃气轮机可方便拆卸式压气机静叶环及其装配方法
CN113847105A (zh) * 2021-10-26 2021-12-28 中国航发沈阳发动机研究所 一种发动机奇数可调静子叶片静子部件装配结构及其方法
RU2793871C1 (ru) * 2022-06-10 2023-04-07 Акционерное общество "Силовые машины - ЗТЛ, ЛМЗ, Электросила, Энергомашэкспорт" (АО "Силовые машины") Наборная диафрагма паровой турбины

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