EP3390784B1 - Turbomachine à plusieurs étages d'aubes directrices et procédé pour démonter en partie une telle turbomachine - Google Patents

Turbomachine à plusieurs étages d'aubes directrices et procédé pour démonter en partie une telle turbomachine Download PDF

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Publication number
EP3390784B1
EP3390784B1 EP17705106.7A EP17705106A EP3390784B1 EP 3390784 B1 EP3390784 B1 EP 3390784B1 EP 17705106 A EP17705106 A EP 17705106A EP 3390784 B1 EP3390784 B1 EP 3390784B1
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EP
European Patent Office
Prior art keywords
guide vane
guide
turbomachine
carrier
stage
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
EP17705106.7A
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German (de)
English (en)
Other versions
EP3390784A1 (fr
Inventor
Stefan Bärow
Oliver Dominka
Guido Ederer
Christian Felsmann
Florian Fuchs
Robert Herfurth
Jose Angel Hernandez Maza
Michael Kluck
Eike Kohlhoff
Kay Krabiell
Khaled Maiz
Behnam Nouri
Andre Willmann
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.)
Siemens Energy Global GmbH and Co KG
Original Assignee
Siemens AG
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 AG filed Critical Siemens AG
Publication of EP3390784A1 publication Critical patent/EP3390784A1/fr
Application granted granted Critical
Publication of EP3390784B1 publication Critical patent/EP3390784B1/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
    • 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
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/28—Supporting or mounting arrangements, e.g. for turbine casing
    • 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
    • F01D5/14—Form or construction
    • F01D5/147—Construction, i.e. structural features, e.g. of weight-saving hollow 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
    • F05D2220/00—Application
    • F05D2220/40—Application in turbochargers
    • 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
    • F05D2260/30—Retaining components in desired mutual position

Definitions

  • the present invention relates to a turbomachine with the features of claim 1, namely with at least one ring-shaped guide vane carrier, which is composed of at least one lower part and an upper part releasably connected thereto, and at least three guide vane stages held on the inner circumference of the at least one guide vane carrier
  • Direction of flow are arranged axially one behind the other and each have a plurality of substantially radially extending guide vanes, each guide vane comprising a guide vane blade which extends between a base plate and a top plate, each base plate being held in a form-fitting manner directly on the guide vane carrier and in this way against one Displacement in the radial and axial direction is secured, at least some base plates of guide vanes of each guide vane stage by at least one additional securing element against displacement in the circumferential direction are secured, the base plates of adjoining guide vanes of axially adjacent guide blade stages each engage in a form-fitting manner directly in one another and partially overlap one another, and between the base
  • the invention relates to a method for partial disassembly of a turbomachine according to claim 9, wherein in the turbomachine of the type mentioned the upper part of the guide vane carrier is removed and guide vanes of a single guide vane stage are removed from the guide vane carrier.
  • Turbomachines of the type mentioned are basically known in the prior art.
  • the guide vanes of the axially successive turbine stages can be assembled one after the other in a guide vane carrier.
  • the turbine guide vanes comprise a base plate for attachment to the guide vane carrier, an adjacent airfoil and a radially inner head plate. Hooks arranged radially on the outside of the base plates can be inserted into the circumferential grooves of the vane carrier which are open to the side for fastening. So-called shroud blades are arranged between the guide blades of adjacent turbine stages.
  • the Figures 1 and 2nd show, by way of example, the construction of a partial area of a turbomachine 1 from Siemens AG with a ring-shaped guide vane carrier 2, which is divided in the middle into an upper part and a lower part, wherein in Figure 1 a section through the lower part 3 is shown without a runner.
  • a total of four guide vane stages 4a to 4d are held on the inner circumference of the guide vane carrier 2 and are arranged axially one behind the other in the flow direction.
  • the guide vane stage 4a forms on the far left in Figure 1 the first stage and the guide vane stage 4d on the far right in Figure 1 the fourth stage.
  • Each vane stage 4a 4 to 4d have a plurality of essentially radially extending guide blades 5, the guide blade blades 6 of which extend between ring-shaped base plates 7 and ring-shaped head plates 8.
  • the base plates 7 each comprise first retaining projections 9a projecting in the axial direction, which engage in annular grooves 10a formed on the guide vane carrier 2 and secure the guide vanes 5 in the radial direction. More precisely, the base plates 7 of the guide blades 5 of the first three guide blade stages 4a, 4b and 4c are each provided on one side with first retaining projections 9, via which the base plates 7 are supported on one side on the guide blade carrier 2.
  • first retaining projections 9a are formed on both sides of the base plates 7 of the guide blades 5 of the fourth guide blade stage 4d, so that these base plates 7 are supported on both sides of the guide blade carrier 2 or are fixed thereon.
  • the base plates 7 each comprise second retaining projections 9b protruding in the radial direction, which engage in annular grooves 10b formed on the guide vane carrier 2 and secure the guide vanes 5 in the axial direction, the second retaining projections 9b in the present case being arranged directly adjacent to the first retaining projections 9a.
  • securing elements 11 in the form of securing pins are furthermore provided, which are arranged in bores 12 which extend radially through both a first retaining projection 9 a and through the guide vane carrier 2.
  • the mutually facing axial end regions of the base plates of the guide vanes of adjacent guide blade stages are each provided with axially protruding overlapping projections 13 which overlap one another in such a way that the base plates 7 of the first guide blade stage 4a on those of the second guide blade stage 4b, and the base plates 7 of the second guide blade stage 4b on them of the third guide vane stage 4c and the base plates 7 of the third guide vane stage 4c directly support those of the fourth guide vane stage 4d.
  • the base plates 7 of the guide blades 5 of the first to third guide blade stages 4a to 4c are each held on the guide blade carrier 2 on the one hand and on at least one base plate 7 of a guide blade 5 of an adjacent guide blade stage on the other hand.
  • the construction described above is characterized in particular by the fact that the guide blades 5 are held directly on the guide blade carrier 2 and directly against one another, and that the foot plates 7 alone define the radially outer wall of the flow path. Accordingly, the construction dispenses with additional intermediate rings or the like, which gives it a very simple and inexpensive construction. Due to the design and arrangement of the guide vane carrier 2 and the guide vane stages 4a to 4d described above, the guide vane stages 4a to 4d must be assembled in sequence in a predetermined order when the turbomachine 1 is assembled, starting with the guide vanes 5 of the fourth guide vane stage 4d, which be firmly connected to the guide vane carrier 2.
  • the present invention provides a turbomachine with the features of claim 1, which is characterized in that at least some of the securing elements are inaccessible from an outside of the guide vane carrier and are positioned such that they can be reached by the maintenance personnel via the intermediate space in the maintenance state and can be assembled and disassembled.
  • This has the significant advantage that there is no particular sequence to be followed with regard to the assembly and / or disassembly of the guide vanes of the individual guide vane stages, since the securing elements are always freely accessible, which in particular simplifies, shortens and reduces maintenance and / or repair work and requires little cost can.
  • the form fit between the base plates and the guide vane carrier is preferably brought about by projections protruding radially and / or axially from the base plates, which engage in assigned circumferential grooves of the guide vane carrier. A simple structure is achieved in this way.
  • the projections are advantageously formed in the axial end regions of the foot plates, which results in a stable construction.
  • At least the base plates of the guide vanes of the first or last guide blade stage each have two axially spaced apart projections, which engage positively in the associated circumferential grooves of the guide blade carrier and secure the base plates against displacement in the radial direction.
  • the securing elements are preferably formed by securing pins which are received on the one hand in a recess formed on a base plate and on the other hand in a recess formed on the guide vane carrier, preferably at least one of the recesses being formed by a cylindrical bore.
  • the axial component of a direction vector of the main direction of extent of each securing element within a plane that extends radially through the securing element is advantageously larger than the radial component. In this way, particularly good accessibility of the securing elements is ensured, so that they can be easily installed and removed.
  • the present invention furthermore provides a method having the features of claim 9 for the partial disassembly of a turbomachine of the type mentioned at the outset is characterized in that the individual guide vane stage, the guide vanes of which are dismantled, can be freely selected.
  • the method according to the invention is distinguished from the prior art described at the outset in that there is no particular sequence to be followed when dismantling guide vanes in relation to the guide vane stages. Accordingly, maintenance and repair work on individual guide vanes or guide vane stages can be considerably simplified and shortened, which can result in large cost savings.
  • the individual guide vane stage, the guide vanes of which are dismantled is a guide vane stage which is arranged between the outermost guide vane stages.
  • a support device is preferably installed which holds at least one of the adjacent guide vane stages in position while the method is being carried out. Accordingly, it is prevented that the position of this adjacent guide vane step can change during the disassembly of the guide vane step to be removed, which facilitates both the disassembly and the reassembly.
  • the support device is preferably screwed or pinned to the at least one adjacent guide vane stage which is to be held in position, in particular to at least one head plate of one of its guide vanes, in order to ensure secure positioning.
  • Figure 3 shows a sectional view of a partial area of a turbomachine 1 according to an embodiment of the present invention with the upper part of a guide vane carrier 2 removed and the rotor already dismantled.
  • the structure of the Figure 3 Fluid machine 1 shown largely corresponds to that of the in Figure 1 shown and previously described fluid machine 1, which is why the same or similar components are designated by the same reference numerals and will not be described again below.
  • the securing elements 11 in the in Figure 3 are positioned such that after removal of the upper part of the guide vane carrier 2 they are easily accessible via the spaces 14 between the base plates 7 and the guide vane carrier 2 and can accordingly be easily dismantled and reassembled. More specifically, the securing elements 11, which are formed here by securing pins, are each accommodated in the embodiment shown, on the one hand in a recess 15 formed on a base plate 7 and on the other hand in a recess 15 formed on the guide vane carrier 2, which in the present case are designed as aligned bores.
  • a support device 17 is advantageously attached at least to the third guide vane stage 4c, preferably to the first three guide vane stages 4a to 4c, which surrounds the respective head plates 8 of the guide vanes 5 of the first three guide vane stages 4a to 4c, see Figure 5 .
  • the support device 17 has ring segment-shaped support elements 18 which protrude radially outward from a base element 19 and each receive the head plates 8 of a guide vane stage 4a, 4b or 4c between them.
  • the support elements 18 can be mechanically connected to the head plates 8 or tensioned, for example using appropriate screws or pins, even if this is not absolutely necessary.
  • the securing elements 11 of a guide vane 5 of the fourth guide vane stage 4d arranged at the very top can be released, whereupon the corresponding guide vane 5 can be removed.
  • the holding projections 9a and 9b of the base plate 7 of the guide vane 5 are moved in the circumferential direction and in this way are brought out of engagement with the associated ring grooves 10a and 10b.
  • the support device 17 ensures during the removal of the guide vanes 5 of the fourth guide vane stage 4d that the positioning of the guide vanes 5 of the adjacent guide vane stage 4c is maintained despite the fact that the engagement between the overlapping projections 13 is released. In this way, problem-free disassembly and reassembly of the guide vanes 5 of the fourth guide vane stage 4d is ensured.
  • the guide vanes 5 of the other guide vane stages 4a to 4c can also be individually dismantled and reassembled without having to remove adjacent guide vane stages.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Architecture (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)

Claims (12)

  1. Turbomachine (1), comprenant au moins un support (2) d'aube directrice, constitué de manière annulaire et composé au moins d'une partie inférieure et d'une partie supérieure, reliée de manière amovible à celle-ci, et au moins trois étages (4a-d) d'aubes directrices, qui sont retenues au pourtour intérieur du au moins un support (2) d'aube directrice, qui sont disposés les uns derrière les autres axialement dans le sens d'écoulement et qui ont chacun une pluralité d'aubes (5) directrices s'étendant radialement, chaque aube (5) directrice comprenant un plateau (7) d'emplanture et un plateau (8) de tête, ainsi qu'un corps (6) d'aube directrice s'étendant entre eux, et dans laquelle
    - chaque plateau (7) d'emplanture est retenu directement à complémentarité de forme sur le support (2) d'aube directrice et est ainsi empêché de se déplacer dans la direction radiale et axiale,
    - au moins certains plateaux (7) d'emplanture d'aube (5) directrice de chaque étage (4a-d) d'aube directrice sont empêchés de se déplacer dans la direction périphérique par au moins un élément (11) de fixation supplémentaire,
    - les plateaux (7) d'emplanture d'aubes (5) directrices voisines d'étages (4a-d) d'aube directrice voisins axialement s'interpénètrent directement à complémentarité de forme, respectivement, et se chevauchent en partie les uns les autres, et
    - entre les plateaux (7) d'emplanture de chaque étage (4a-d) d'aube directrice et le côté intérieur du support (2) d'aube directrice est laissé, respectivement, un espace (14) intermédiaire sensiblement annulaire, qui est accessible au personnel d'entretien dans un état d'entretien dans lequel la partie inférieure et la partie supérieure du support d'aube directrice sont séparées l'une de l'autre,
    dans lequel au moins certains des éléments de fixation sont placés en étant inaccessibles du côté extérieur du support (2) d'aube directrice et de manière à pouvoir être atteints, ainsi que montés et démontés, dans l'état d'entretien par le personnel d'entretien, par l'espace (14) intérieur.
  2. Turbomachine (1) suivant la revendication 1,
    caractérisée en ce que
    le support (2) d'aube directrice comprend des rainures de pourtour associées aux plateaux (7) d'emplanture et
    la complémentarité de forme entre les plateaux (7) d'emplanture et le support (2) d'aube directrice est obtenue par des saillies (9a, 9b) faisant saillie radialement et/ou axialement des plateaux (7) d'emplanture, qui pénètrent dans les rainures (10, 10b) périphériques associées du support (2) d'aube directrice.
  3. Turbomachine suivant la revendication 2,
    caractérisée en ce que
    les saillies (9a, 9b) sont constituées dans des parties d'extrémités axiales des plateaux (7) d'emplanture.
  4. Turbomachine suivant la revendication 2 u 3,
    caractérisée en ce que
    au moins les plateaux (7) d'emplanture des aubes (5) directrices du premier ou du dernier étage (4a, 4d) d'aube directrice ont chacun deux saillies, disposées à distance l'une de l'autre axialement, qui pénètrent à complémentarité de forme dans les rainures périphériques associées du support (2) d'aube directrice et empêche les plateaux (7) d'emplanture de se déplacer dans la direction radiale.
  5. Turbomachine (1) suivant l'une des revendications précédentes,
    caractérisée en ce que
    les éléments (11) de fixation, notamment tous les éléments (11) de fixation, sont formés par des broches de fixation, qui sont logées, d'une part, dans un évidement (15) constitué sur un plateau (7) d'emplanture, et d'autre part, dans un évidement (15) constitué sur le support (2) d'aube directrice.
  6. Turbomachine suivant la revendication 5,
    caractérisée en ce que
    l'un des évidements (15) est formé d'un trou cylindrique.
  7. Turbomachine (1) suivant l'une des revendications précédentes,
    caractérisée en ce que
    la composante (a) axiale d'un vecteur (16) de référence de la direction d'étendue principale de chaque élément (11) de fixation dans un plan, qui s'étend radialement dans l'élément (11) de fixation, est plus grande que la composante (r) radiale.
  8. Turbomachine (1) suivant la revendication 7,
    caractérisée en ce que
    la composante (a) axiale est de deux à quatre fois plus grande que la composante (r) radiale.
  9. Procédé de démontage en partie d'une turbomachine (1) suivant l'une des revendications précédentes, dans lequel, dans la turbomachine (1) suivant l'une des revendications précédente, on retire la partie supérieure du support (2) d'aube directrice et on démonte des aubes (5) directrices d'un étage individuel d'aubes directrices du support (2) d'aube directrice, caractérisé en ce que l'étage d'aube directrice, dont les aubes (5) directrices sont démontées, peut être choisi librement.
  10. Procédé suivant la revendication 9,
    caractérisé en ce que l'étage d'aube directrice, dont les aubes directrices sont démontées, est un étage d'aube directrice, qui est disposé entre les étages d'aube directrice les plus à l'extérieur.
  11. Procédé suivant la revendication 9 ou 10,
    caractérisé en ce qu'
    avant le démontage de l'étage d'aube directrice, on monte un dispositif (17) d'appui, qui maintient en position les étages d'aube directrice voisins pendant que l'on effectue le procédé.
  12. Procédé suivant la revendication 11,
    caractérisé en ce que
    l'on visse ou l'on goupille le dispositif (17) d'appui avec les étages d'aube directrice voisins.
EP17705106.7A 2016-03-04 2017-02-14 Turbomachine à plusieurs étages d'aubes directrices et procédé pour démonter en partie une telle turbomachine Active EP3390784B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE102016203567.3A DE102016203567A1 (de) 2016-03-04 2016-03-04 Strömungsmaschine mit mehreren Leitschaufelstufen und Verfahren zur teilweisen Demontage einer solchen Strömungsmaschine
PCT/EP2017/053226 WO2017148695A1 (fr) 2016-03-04 2017-02-14 Turbomachine à plusieurs étages d'aubes directrices et procédé pour démonter en partie une telle turbomachine

Publications (2)

Publication Number Publication Date
EP3390784A1 EP3390784A1 (fr) 2018-10-24
EP3390784B1 true EP3390784B1 (fr) 2020-04-01

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EP17705106.7A Active EP3390784B1 (fr) 2016-03-04 2017-02-14 Turbomachine à plusieurs étages d'aubes directrices et procédé pour démonter en partie une telle turbomachine

Country Status (6)

Country Link
US (1) US10844747B2 (fr)
EP (1) EP3390784B1 (fr)
DE (1) DE102016203567A1 (fr)
RU (1) RU2709899C1 (fr)
SA (1) SA518392323B1 (fr)
WO (1) WO2017148695A1 (fr)

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Publication number Priority date Publication date Assignee Title
US11085309B2 (en) * 2017-09-22 2021-08-10 General Electric Company Outer drum rotor assembly
CN112302739B (zh) * 2020-10-30 2023-01-17 中国航发沈阳发动机研究所 一种可在试验台架上更换的整流机匣结构
US11428160B2 (en) 2020-12-31 2022-08-30 General Electric Company Gas turbine engine with interdigitated turbine and gear assembly

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GB804922A (en) 1956-01-13 1958-11-26 Rolls Royce Improvements in or relating to axial-flow fluid machines for example compressors andturbines
GB2226365B (en) * 1988-12-22 1993-03-10 Rolls Royce Plc Turbomachine clearance control
GB2239678B (en) * 1989-12-08 1993-03-03 Rolls Royce Plc Gas turbine engine blade shroud assembly
GB2313161B (en) 1996-05-14 2000-05-31 Rolls Royce Plc Gas turbine engine casing
DE10312956B4 (de) * 2003-03-22 2011-08-11 MTU Aero Engines GmbH, 80995 Anordnung für das axiale und radiale Festlegen einer Leitschaufelbaugruppe in dem Gehäuse eines Turbinentriebwerkes
US7094029B2 (en) * 2003-05-06 2006-08-22 General Electric Company Methods and apparatus for controlling gas turbine engine rotor tip clearances
FR2875535B1 (fr) 2004-09-21 2009-10-30 Snecma Moteurs Sa Module de turbine pour moteur a turbine a gaz
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FR2968030B1 (fr) 2010-11-30 2013-01-11 Snecma Turbine basse-pression de turbomachine d'aeronef, comprenant un distributeur sectorise
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JP5962915B2 (ja) * 2012-10-29 2016-08-03 株式会社Ihi タービンノズルの固定部構造及びこれを用いたタービン
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Also Published As

Publication number Publication date
WO2017148695A1 (fr) 2017-09-08
US10844747B2 (en) 2020-11-24
EP3390784A1 (fr) 2018-10-24
US20190055856A1 (en) 2019-02-21
RU2709899C1 (ru) 2019-12-23
DE102016203567A1 (de) 2017-09-07
SA518392323B1 (ar) 2022-03-28

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