EP3260663B1 - Structure de diaphragme de turbine axiale - Google Patents

Structure de diaphragme de turbine axiale Download PDF

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Publication number
EP3260663B1
EP3260663B1 EP16290110.2A EP16290110A EP3260663B1 EP 3260663 B1 EP3260663 B1 EP 3260663B1 EP 16290110 A EP16290110 A EP 16290110A EP 3260663 B1 EP3260663 B1 EP 3260663B1
Authority
EP
European Patent Office
Prior art keywords
axial flow
flow turbine
turbine diaphragm
section
diaphragm construction
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.)
Active
Application number
EP16290110.2A
Other languages
German (de)
English (en)
Other versions
EP3260663A1 (fr
Inventor
Julien Lemaire
Arnaud BUGUIN
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.)
GE Vernova GmbH
Original Assignee
General Electric Technology GmbH
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 General Electric Technology GmbH filed Critical General Electric Technology GmbH
Priority to EP16290110.2A priority Critical patent/EP3260663B1/fr
Priority to US16/312,618 priority patent/US20200182076A1/en
Priority to JP2018566573A priority patent/JP6972035B2/ja
Priority to PCT/EP2017/065220 priority patent/WO2017220646A1/fr
Priority to CN201780038742.5A priority patent/CN109312626B/zh
Publication of EP3260663A1 publication Critical patent/EP3260663A1/fr
Application granted granted Critical
Publication of EP3260663B1 publication Critical patent/EP3260663B1/fr
Active legal-status Critical Current
Anticipated expiration legal-status Critical

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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
    • 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
    • F01D9/041—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector using blades
    • 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
    • F01D9/044—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector fixing blades to stators permanently, e.g. by welding, brazing, casting or the like
    • 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
    • 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
    • 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
    • F05D2220/00—Application
    • F05D2220/30—Application in turbines
    • F05D2220/31—Application in turbines in steam turbines
    • 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
    • F05D2230/00—Manufacture
    • F05D2230/20—Manufacture essentially without removing material
    • F05D2230/23—Manufacture essentially without removing material by permanently joining parts together
    • F05D2230/232—Manufacture essentially without removing material by permanently joining parts together by welding
    • 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
    • F05D2240/10—Stators
    • F05D2240/12—Fluid guiding means, e.g. vanes
    • F05D2240/122—Fluid guiding means, e.g. vanes related to the trailing edge of a stator vane
    • 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
    • F05D2240/10—Stators
    • F05D2240/12—Fluid guiding means, e.g. vanes
    • F05D2240/128—Nozzles
    • 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
    • F05D2240/20—Rotors
    • F05D2240/30—Characteristics of rotor blades, i.e. of any element transforming dynamic fluid energy to or from rotational energy and being attached to a rotor
    • F05D2240/304—Characteristics of rotor blades, i.e. of any element transforming dynamic fluid energy to or from rotational energy and being attached to a rotor related to the trailing edge of a rotor blade
    • 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
    • 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
    • F05D2260/00—Function
    • F05D2260/20—Heat transfer, e.g. cooling
    • F05D2260/202—Heat transfer, e.g. cooling by film cooling

Definitions

  • the present invention relates to the construction of rings of static blades for axial flow turbines, and in particular, steam turbines.
  • the present invention relates to turbine diaphragms.
  • a steam turbine is a rotating machine intended to convert the thermal of the steam into mechanical energy for driving an alternator, a pump or any other rotary mechanical receiver.
  • steam turbines comprise a high-pressure module, a medium-pressure module and a low-pressure module.
  • a steam turbine generally comprises symmetrical or non-symmetrical single or double flow inner body enclosing a rotor equipped with mobile blades and supporting fixed or stationary blades forming a diaphragm suspended in said inner body.
  • the diaphragms are adapted to guide the flow of steam in a specific direction towards the mobile blades of the rotor, thereby accelerating the steam flow.
  • the present invention is related to known types of construction diaphragms called “spacer band diaphragms” and “platform diaphragms", as exemplary described in EP 1 847 689 A2 , related to an apparatus and a method of diaphragm assembly, EP 0 018 806 A1 , related to an assembly including an airfoil extending between shroud sections and method of making the same, US 5,474,419 A related to a flowpath assembly for a turbine diaphragm and methods of manufacture, and US 2007/224043 related to a turbine blade and diaphragm construction.
  • the blade aerofoils 11 are fixed radially to an inner ring 12 and to an outer ring 13 by means of inner and outer annular bands 14, 15, which are folded from flat strip.
  • Through-holes 16 are cut in said bands 14, 15, for example by means of laser, to match the cross-section of the aerofoil shape.
  • the ends of the aerofoils 11 are then inserted in said through-holes 16 and fillet welded into place.
  • the inner band 14 is in turn welded to the inner ring 12 and the outer band 15 is in turn welded to the outer ring 13.
  • Such type of construction involves a relatively small amount of machining of the blades compared to other types of construction used in steam turbines.
  • the blade aerofoils 21 has a section substantially in the shape of a vane having its two opposite ends integral with radially inner and outer platforms 22, 23.
  • the blade aerofoils and the platforms are machined from solid bars or by forgings.
  • a complete annulus of static blades is built up by assembling successive combined aerofoil-platforms components between an inner and an outer ring (not shown) and by welding the platforms to said rings. Thanks to the platforms, such diaphragm has better mechanical strength compared to the spacer band type, but has much higher manufacturing costs.
  • the object of the present invention is to remedy the above drawbacks.
  • an axial flow turbine diaphragm construction according to claim 1 is provided.
  • the section of the reinforcement portion preferably has a rounded and enlarged shape corresponding to the leading edge surrounding the leading edge of the aerofoil portion and a thinner part corresponding to the trailing edge surrounding the trailing edge of the aerofoil portion.
  • the static blade may be made of an alloy steel material, for example, comprising 12% of chrome.
  • each reinforcement portions are welded to the corresponding spacer band by welds.
  • the welds are, for example, located at each leading and trailing edges of each reinforcement portions.
  • the inner spacer band is welded to the inner ring and the outer spacer band is welded to the outer ring.
  • a part of a steam turbine diaphragm 30 of a turbine comprises a nozzle unit having a plurality of identical static blade aerofoils 32 fixed radially to an inner ring 34 and to an outer ring 36 by means of inner and outer annular spacer bands 38, 40, which are folded from flat strip.
  • the inner and outer rings 34, 36, as well as the inner and outer spacer bands 38, 40 are concentric.
  • the inner and the outer spacer bands 38, 40 are each provided with through-holes 38a, 40a. As illustrated, the through-holes are open at both ends to receive the static blades.
  • the through-holes 38a, 40a may be, for example, cut in said spacer bands 38, 40, for example by means of laser, to match the cross-section of the aerofoil shape.
  • the ends of the aerofoils 32 are then inserted in said though-holes and fillet welded into place.
  • the inner spacer band 38 is in turn welded to the inner ring 34 and the outer band 40 is in turn welded to the outer ring 36.
  • each static blade 32 has an aerofoil portion 44 having an elongated body having an inner end 32a brought into contact with the inner spacer band 38 and an outer end 32b, opposite to said inner end 32a, brought into contact with the outer spacer band 40.
  • the inner and outer ends 32a, 32b are connected respectively to the inner and outer spacer bands 38, 40 by welding by way of a weld bead arranged between said ends and said spacer bands. In this way each static blade is welded both to the inner spacer band and to the outer spacer band.
  • Each static blade 32 has, for example, a section substantially in the shape of a vane, as shown on Figure 4 , having a rounded and enlarged shape corresponding to the leading edge 44a and a thinner part corresponding to the trailing edge 44b.
  • each reinforcement portion 46, 48 has a section slightly bigger than the section of the aerofoil portion 44, as shown on Figure 4 , having a rounded and enlarged shape corresponding to the leading edge 46a, 48a and a thinner part corresponding to the trailing edge 46b, 48b.
  • Each reinforcement portion 46, 48 surrounds the periphery of the whole section of the corresponding end so as to have a section substantially bigger than the section of the aerofoil portion 44.
  • the shape of the reinforcement portions 46, 48 thus approximates the shape of the section of the aerofoil portion 44 in its whole, i.e at and near the leading and trailing edges 44a, 44b, as well as the suction side and the pressure side of the aerofoil portion 44.
  • the first and second reinforcement portions 46, 48 are slid into their matching through-holes 38a, 40a of the spacer bands 38, 40 as shown on Figure 5 . Once all the static blades 32 have been assembled into the spacer bands 38, 40, they must be securely welded into position. Each leading and trailing edges of each reinforcement portions are welded to the corresponding spacer band by welds 50a, 50b and 52a, 52b. The welds 50a, 50b and 52a, 52b are shown in hatched lines on Figure 4 .
  • the static blades 32 are made of an alloy steel material, having for example, 12% of chrome.
  • the static blade is strengthen.
  • the diaphragm construction has good mechanical strength, while being economical and easy to manufacture.

Landscapes

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

Claims (7)

  1. Construction de membrane de turbine à écoulement axial comprenant :
    a) un anneau d'une pluralité de lames (32) statiques identiques, chaque lame comprenant :
    i) une partie aérodynamique (44) ayant un bord d'attaque (44a), un bord de fuite (44b), un côté de pression et un côté d'aspiration,
    ii) des extrémités intérieure et extérieure (32a, 32b) de chaque lame statique sont pourvues respectivement d'une partie de renforcement intérieure et extérieure (46, 48) solidaire avec ladite partie aérodynamique (44),
    caractérisé en ce que
    (1) une forme des parties de renforcement (46, 48) ressemble à une forme d'une section de la partie aérodynamique (44) dans son ensemble, c'est-à-dire au niveau et à proximité des bords d'attaque et de fuite (44a, 44b) ainsi que du côté d'aspiration et du côté de pression de la partie aérodynamique (44), et dans laquelle
    (2) chaque partie de renforcement (46, 48) entoure la périphérie de toute la section de l'extrémité correspondante de manière à avoir une section plus grande que la section de la partie aérodynamique (44) ;
    b) des bandes d'espacement intérieure et extérieure (38, 40) ayant des trous de passage (38a, 40a) en leurs seins formés pour recevoir les parties de renforcement intérieure et extérieure (46, 48) de chaque lame statique (32) ; et
    c) des anneaux de membrane radialement intérieur et extérieur (34, 36) entourant les bandes d'espacement annulaires (38, 40).
  2. Construction de membrane de turbine à écoulement axial selon la revendication 1, dans laquelle chaque partie de renforcement est soudée à la bande d'espacement correspondante (38, 40) par des soudures (50a, 50b ; 52a, 52b).
  3. Construction de membrane de turbine à écoulement axial selon l'une quelconque des revendications précédentes, dans laquelle les soudures (50a, 50b ; 52a, 52b) sont situées au niveau de chaque bord d'attaque et de fuite (48a, 48b ; 46a, 46b) de chaque partie de renforcement (46, 48).
  4. Construction de membrane de turbine à écoulement axial selon l'une quelconque des revendications précédentes, dans laquelle la bande d'espacement intérieure (38) est soudée à l'anneau intérieur (34) et la bande d'espacement extérieure (40) est soudée à l'anneau extérieur (36).
  5. Construction de membrane de turbine à écoulement axial selon l'une quelconque des revendications précédentes, dans laquelle chaque partie de renforcement (46, 48) a une section sensiblement plus grande que la section de la partie aérodynamique (44), ayant une forme arrondie et élargie correspondant au bord d'attaque (46a, 48a) entourant le bord de fuite (44a) de la partie aérodynamique (44) et une partie plus fine correspondant au bord de fuite (46b, 48b) entourant le bord de fuite (44b) de la partie aérodynamique (44).
  6. Construction de membrane de turbine à écoulement axial selon l'une quelconque des revendications précédentes, dans laquelle chaque lame statique est fabriquée à partir d'un matériau d'alliage d'acier.
  7. Construction de membrane de turbine à écoulement axial selon la revendication précédente, dans laquelle le matériau d'alliage d'acier comprend 12 % de chrome.
EP16290110.2A 2016-06-21 2016-06-21 Structure de diaphragme de turbine axiale Active EP3260663B1 (fr)

Priority Applications (5)

Application Number Priority Date Filing Date Title
EP16290110.2A EP3260663B1 (fr) 2016-06-21 2016-06-21 Structure de diaphragme de turbine axiale
US16/312,618 US20200182076A1 (en) 2016-06-21 2017-06-21 Static blade for a turbine diaphragm and associated turbine diaphragm
JP2018566573A JP6972035B2 (ja) 2016-06-21 2017-06-21 タービンダイアフラム用の静翼および関連するタービンダイアフラム
PCT/EP2017/065220 WO2017220646A1 (fr) 2016-06-21 2017-06-21 Pale statique pour diaphragme de turbine et diaphragme de turbine associé
CN201780038742.5A CN109312626B (zh) 2016-06-21 2017-06-21 用于涡轮隔板的静止叶片及相关联的涡轮隔板

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP16290110.2A EP3260663B1 (fr) 2016-06-21 2016-06-21 Structure de diaphragme de turbine axiale

Publications (2)

Publication Number Publication Date
EP3260663A1 EP3260663A1 (fr) 2017-12-27
EP3260663B1 true EP3260663B1 (fr) 2020-07-29

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Family Applications (1)

Application Number Title Priority Date Filing Date
EP16290110.2A Active EP3260663B1 (fr) 2016-06-21 2016-06-21 Structure de diaphragme de turbine axiale

Country Status (5)

Country Link
US (1) US20200182076A1 (fr)
EP (1) EP3260663B1 (fr)
JP (1) JP6972035B2 (fr)
CN (1) CN109312626B (fr)
WO (1) WO2017220646A1 (fr)

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CN112377278B (zh) * 2020-10-30 2023-04-28 北京国能龙威发电技术有限公司 一种汽轮机自带冠拂配式隔板的整圈装配方法
US11879360B2 (en) * 2020-10-30 2024-01-23 General Electric Company Fabricated CMC nozzle assemblies for gas turbine engines
CN115182789A (zh) * 2021-04-07 2022-10-14 中国航发商用航空发动机有限责任公司 静子组件、制造方法以及包括该静子组件的叶轮机械

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Also Published As

Publication number Publication date
EP3260663A1 (fr) 2017-12-27
JP6972035B2 (ja) 2021-11-24
CN109312626A (zh) 2019-02-05
JP2019518903A (ja) 2019-07-04
CN109312626B (zh) 2022-06-24
WO2017220646A1 (fr) 2017-12-28
US20200182076A1 (en) 2020-06-11

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