WO2010089125A2 - Élément annulaire de guidage pour turbines et procédé de fabrication correspondant - Google Patents

Élément annulaire de guidage pour turbines et procédé de fabrication correspondant Download PDF

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Publication number
WO2010089125A2
WO2010089125A2 PCT/EP2010/000708 EP2010000708W WO2010089125A2 WO 2010089125 A2 WO2010089125 A2 WO 2010089125A2 EP 2010000708 W EP2010000708 W EP 2010000708W WO 2010089125 A2 WO2010089125 A2 WO 2010089125A2
Authority
WO
WIPO (PCT)
Prior art keywords
ring element
guide ring
segment plates
ribs
guide
Prior art date
Application number
PCT/EP2010/000708
Other languages
German (de)
English (en)
Other versions
WO2010089125A3 (fr
Inventor
Jürgen Krummel
Original Assignee
Hobis 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 Hobis Ag filed Critical Hobis Ag
Publication of WO2010089125A2 publication Critical patent/WO2010089125A2/fr
Publication of WO2010089125A3 publication Critical patent/WO2010089125A3/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
    • 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
    • F01D25/30—Exhaust heads, chambers, 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
    • 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
    • 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
    • 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
    • F05D2230/238—Soldering
    • 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
    • F05D2240/11—Shroud seal segments

Definitions

  • the invention relates to a guide ring element for turbines and to a method for producing a guide ring element.
  • the flow medium such as the steam of a steam turbine
  • the steam usually passes on the input side via steam inlet nozzles to the first impeller of the steam turbine and from here via shelves with guide vanes, which are referred to as Turbinenleitkränze, to the next impeller.
  • Turbinenleitkränze In the intermediate floors transitions for Dampfab- or -ein admir be provided in a pipe.
  • the flow medium is discharged through a diffuser.
  • the flow channels of the steam inlet nozzles are largely similar to those in the intermediate floors or on the diffuser before to be seen flow channels. In all cases the juxtaposed flow channels are in a ring arranged, which is referred to below as a guide ring.
  • Turbinenleitkränze in which the vanes are attached only on one side to a turbine housing in communication with the outer ring and lie with their free ends between the blades, and other Turbinenleitkränze, especially those with long vanes in the turbine output stages, which in addition to stabilize a Have inner ring.
  • the guide vanes are thus fixed by the two rings on both sides at their ends and together with these form a flow channel.
  • the various guide rings of a turbine are usually assembled during assembly of the turbine from two half rings or possibly more ring parts, which are referred to below as a guide ring elements.
  • the present invention solves the technical problem of specifying a guide ring element for turbines and a method for the production thereof, wherein the guide ring element has a low weight and is easy to manufacture, but nevertheless meets all stability requirements.
  • the flow surfaces of the guide ring element are constructed in relation to the guide ring element small segment plates.
  • the guide ring element thus has a lower compared to the prior art Weight on and is easily produced from the individual segment plates.
  • the individual segment plates can each have a separation geometry which is adapted to the local requirements, for example in the case of shape transitions.
  • ribs and / or support ring elements can be provided, which are connected to each other and / or with the segment plates, so that there is a stable, yet lightweight construction.
  • the term support ring element is intended to cover all components which are not as strongly segmented as the segment plates.
  • the segment plates and / or the ribs and / or the support ring elements are adapted in material type and / or material thickness and / or shape design to the local requirements.
  • the turbine segment plates can be installed with greater material thickness.
  • the weight of the guide ring element can be further reduced and at the same time the stability in heavily loaded areas can be increased.
  • it is possible to make the segment plates in the flow for example, in the range of Dampfab- or -eintechnischen in a pipe.
  • the segment plates are welded to each other and / or to the ribs and / or to the support ring elements by means of a soldering process, a beam welding process, an arc welding process or a combination of these processes. It should be pointed out again that ribs or support ring element are only provided if this is necessary by the requirements for stability or construction.
  • segment plates results when the separation of the segment plates takes place through a plane which runs parallel to the rotor axis of the turbine.
  • the segment plates are shaped and / or mechanically processed on the flow side.
  • segment plates are made flat, which allows a particularly simple production of the segment plates.
  • the ribs may be put on, i. the segment plates are connected directly to each other and the ribs are placed on the segment plates.
  • the ribs connect the segment plates as intermediate elements, i. the segment plates are applied to both sides of a rib and connected to the rib.
  • the guide ring element is designed as a turbine guide ring element by guide vanes are provided.
  • the vanes can be in a known manner hollow or massive blades.
  • the vanes can be provided with the segment plates as head and / or foot plates, the vanes either first connected to the segment plates and then the segment plates are interconnected or the vanes can be connected to the already annularly interconnected segment plates. Further details of the various production methods are explained below for the method according to the invention.
  • the individual segment plates can each one
  • connection contour of the guide vanes lies completely or at least largely on the segment plate, so that the interior of a hollow guide vane is completely covered.
  • the number of the segment plates and / or the ribs substantially corresponds to the number of guide vanes.
  • segment plates may be adapted to the vanes so that the attachment contour of each vane lies entirely on a segment plate.
  • each Leitschaufei can be connected to exactly one segment plate.
  • connection of the vanes to the segment plates may also be by means of a soldering process, a beam welding process, an arc welding process or a combination of these processes.
  • the guide ring element is designed as a diffuser element.
  • the individual elements in the implementation of the method may be segment plates and / or ribs and / or support ring elements.
  • the segment plates are welded together. If available, the welded segment panels are then welded to support ring elements. If, in addition, ribs are provided, finally, the ribs are welded to the segment plates and possibly the support ring elements. In this case, there is a structural connection of the segment plates with each other, whereby support ring elements can be saved or at least made thinner. The dimensioning of the individual elements can be chosen so that weight and cost can be saved.
  • the support ring elements and ribs are first welded together to form a Untersch experienceffle. Subsequently, the segment plates are welded together and with the Untersch experiencerios.
  • the requirements for the accuracy of the division surfaces of the segment plates are smaller, so that a less complex design is possible.
  • a structural weld is located between the segment plates and the support ring elements. Due to the rigidity of the support ring elements less distortion occurs during welding.
  • a fourth variant of the method for producing a guide ring element according to the invention the segment plates and ribs are first welded together to form a Untersch passcuba. Subsequently, this Untersch doneruct is welded to the support ring elements.
  • this variant it is possible to completely structurally connect the segment plates with the ribs, even if a support ring element is structurally located axially within the segment plates.
  • This variant can be used particularly advantageously if the ribs are provided as intermediate elements between the segment plates.
  • the fourth and fifth variants of the method for producing a guide ring element according to the invention are particularly advantageously used in beam welding, since there are no remote welds.
  • guide vanes can be provided as further individual elements.
  • the segment plates serve in this case as top plates and / or base plates of the vanes.
  • a further guide ring element can be provided as a further individual element.
  • a first variant of the method for producing a Turbinenleitkranzelements invention is first an outer ring element made of segment plates as contrastplatten and, if available, ribs and support ring elements and an inner ring element of segment plates as head plates and, if available, ribs and support ring elements. Subsequently, the guide vanes are welded into the outer and inner ring elements. In this method, the requirements on the accuracy of the division surfaces of the segment plates are lower and the segment plates can be made simple in their trim contour.
  • the guide vanes are first welded to the segment plates as head and foot plates. Subsequently, the guide vanes are welded together with segment plates.
  • wear ring elements are welded in the outer and inner regions and finally, if present, welded ribs.
  • segment plates there is a structural connection of the segment plates with each other, whereby support ring elements can be saved or at least made thinner.
  • the dimensioning of the individual elements can be chosen so that weight and cost can be saved.
  • the structural weld between the segment plates can be made as head and foot plates and the vanes on a low cost welding machine. The weld is easily accessible and thus cleaner and high quality executable. At the same time occur less radial stresses when welding the vanes with the segment plates as head and foot plates and during operation of the turbine.
  • a third variant of the method for producing a turbine guide ring element according to the invention first the guide vanes are welded to the segment plates as head and foot plates. Subsequently, the support ring elements are welded in the outer area with ribs. Finally, the vanes are welded to the segment plates with the support ring elements with ribs and the inner ring.
  • a structural weld is located between the segment plates and the Support ring elements. Due to the rigidity of the support ring elements less distortion occurs during welding.
  • the structural weld between the segment plates can be made as head and foot plates and the vanes on a low cost welding machine. The weld is easily accessible and thus cleaner and high quality executable. At the same time occur less radial stresses when welding the vanes with the segment plates as head and foot plates and during operation of the turbine.
  • the guide vanes are first welded to segment plates as base plates. Subsequently, the segment plates of the guide vanes are welded together.
  • a Untersch pooren inner ring element is made of support ring elements and segment plates as head plates and, if available, ribs. Finally, the guide vanes are welded with segment plates with outer support ring elements and the Untersch frequently comprise inner ring member.
  • the structurally particularly important weld seam between the guide blade and the segment plate can be made simple and high-quality as a foot plate. A possible delay between Head and foot are avoided. The requirements for the accuracy of the division surfaces of the segment plates is reduced.
  • the head end of the vane can be machined prior to welding to the segment plate as a top plate because it is already fixed.
  • connection of the individual elements is advantageously carried out in the various variants of the method by means of a soldering method, a beam welding method, an arc welding method or a combination of these methods.
  • a heat treatment and / or mechanical processing can take place between and / or after the individual working steps.
  • Fig. 1 is a side view of an outer ring of a
  • FIG. 2 is a view in the direction of arrow II of FIG. 1,
  • FIG. 3 is a view in the direction of arrow III of Fig. 1,
  • FIGS. 6 and 7 are perspective views of a vane with
  • Segment plates as head plate and foot plate
  • FIG. 8 is a perspective view of another vane with segment plates as the top plate and base plate
  • FIG. 9 is a view of a turbine guide ring, 10 is a view from the back of Fig. 9,
  • FIG. 13 is a perspective view of a guide ring
  • Fig. 15 is an enlarged detail view of another
  • FIG. 17 is a view in the direction of arrow XVII of Fig. 16 and
  • Fig. 18 is an enlarged rear view of the
  • the outer ring 1 consists of two outer ring elements Ia, which are interconnected.
  • the outer ring elements Ia consist of two support ring elements 2, 3, which are welded to a plurality of ribs 4.
  • the connection of the outer ring elements Ia is made via connecting ribs 4a, which can be done in a known manner, such as by screwing.
  • the support ring elements 2, 3 are made of relatively thick sheet material, whereas the ribs 4 are formed of relatively thin sheet material.
  • the material thickness of the support ring elements 2, 3 and the ribs 4 is adapted to the local requirements.
  • the outer ring member Ia has not least due to the configuration of the ribs 4, all of a same shape have a high stability with low weight. If necessary, the ribs can be adjusted in material type, material thickness and / or shape design. It is also clear that the welds for the connection of the ribs 4 with the support ring elements 2, 3 are easily accessible and have a simple design, so that the manufacturing process for the outer ring member Ia is well automatable.
  • the ribs 4 are arranged where, in operation, the maximum stresses are introduced into the segment plates by the guide vanes in the finished turbine guide ring.
  • the ribs 4 have in the middle special contact surfaces 5, at which the foot plates of the vane elements with the ribs 4 are welded.
  • the outer ring element Ia can be used both for the production of a turbine guide ring element with and without inner ring.
  • the outer ring 1 has been assigned an inner ring 11 of inner ring elements IIa.
  • the inner ring elements 11 consist of two support ring elements 12, 13, which are welded in the interior in each case with a sheet metal half cylinder 14.
  • the vane elements 21 shown in FIGS. 6 and 7 comprise a vane 22, which is made in a known manner as a hollow or solid vane 22.
  • the vane 22 is with segment plates as the top plate 23rd and foot plate 24 welded. As can be seen from the views, the welds for the vane elements 21 can easily be made automated because they are easily accessible from all sides and for a turbine nozzle a plurality of identical vane elements 21 are made.
  • top plate 23 and base plate 24 are designed to be suitable for conducting a flow medium by being shaped and / or machined on the flow side.
  • design of the segment plates as head plate 23 and foot plate 24 is adapted to the vanes 22 so that the attachment contour of each vane lies completely on a segment plate as the top plate 23 and base plate 24.
  • FIG. 8 another vane element 25 is shown, which consists of a guide blade 26 with segment plates as the top plate 27 and base plate 28.
  • the segment plates as the top plate 27 and base plate 28 are configured such that the separation of the segment plates in the turbine is done by a plane parallel to the rotor axis of the turbine. This results in that the connection contour of each vane 26 is not completely on a segment plate as the top plate 27 and base plate 28. The vanes 26 are thus about the top plate 27 and foot plate 28 partially out.
  • top plates 23 and 27 and base plates 24 and 28 of a plurality of vane elements 21 and 25 can be a ring merge, as can be seen from the following figures.
  • the turbine guide vane 31 illustrated in FIGS. 9 to 11 comprises two turbine nozzle elements 31 a each having an outer ring element 1 a, an inner ring element 11 a and a plurality of guide vane elements 21.
  • the vane elements 21 are welded with their foot plates 24 to the support ring elements 2, 3 and welded with their top plates 23 to the support ring elements 12, 13.
  • the joints of the top plates 23 and base plates 24 are welded together. This welding process can be automated due to the location and shape of the welds.
  • FIG. 11 the position of the head plates 27 and base plates 28 of the other guide blade elements 25 are indicated by dashed lines.
  • the separation of Segment plates as head plates 27 and foot plates 28 are made by a plane which is parallel to the rotor axis of the turbine.
  • FIG. 12 shows another turbine guide ring 41.
  • the turbine guide ring 41 comprises an outer ring 42, which in addition to the support ring elements 2, 3, which in turn are welded to ribs 4, another support ring member 43 has.
  • the support ring elements 3, 43 are welded together by ribs 44.
  • a guide ring member 45 is welded to the flow medium.
  • the support ring element 2 is welded via ribs 46 with a guide ring element 47.
  • the support ring elements 2, 3, 43 are welded to the ribs 4, 44, 46 and the guide ring elements 45, 47.
  • Leitschaufeletti 21 are then welded with their foot plates 24 for the preparation of the turbine guide ring.
  • the vanes 22 together with the base plates 24 and the guide ring elements 45, 47 form the flow channel for the flow medium.
  • FIGs. 13 and 14 another guide ring 51 is shown as a further embodiment of the invention, which consists of two guide ring elements 51a.
  • the Leitringieri 51a consist of welded together segment plates 52, 53, in the region of the segment plates 52, 53 connecting welds in Outside ribs 54 are placed and welded.
  • the guide ring 51 has a transition 55 of vapor discharge into a tube in the turbine.
  • the segment plates 53 are adapted in shape design to the pipe transition, as is particularly clear from Fig. 14.
  • the material thickness of the segment plate 53 is greater than the material thickness of the segment plates 52.
  • the material thickness of the transition 55 is compared to the material thickness of the segment plate 53 increases. This ensures that the guide ring 51 has grown during operation to the increased stresses in the field of Dampfab- or -eintechnisch, and yet has the lowest possible total weight.
  • FIG. 15 shows a detailed view of another guide ring element 61a which, without ribs, consists only of segment plates 62, 63 welded together.
  • the guide ring member 61a has a transition 65 of steam discharge into a pipe in the turbine.
  • the segment plates 63 are adapted in shape design to the pipe transition and the material thickness of the segment plate 63 is greater than the material thickness of the segment plates 62.
  • the material thickness of the transition 65 is compared to the material thickness of the segment plate 63 increased.
  • a diffuser element 71a is shown, which is the lower half of the diffuser of a turbine.
  • the diffuser element 71a consists of segment plates 72, 73, between which ribs 74 are located as intermediate elements.
  • the segment plates 72, 73 are welded to the ribs 74.
  • At the two ends of the diffuser element 71a are connecting ribs 74a, with which the two halves of the diffuser are connected to each other during assembly of the turbine.
  • the segment plates 73 have recesses 75 for receiving the bearings of the turbine. With regard to the loads occurring in the region of the bearings of the turbine, the material thickness of the segment plates 73 is greater than the material thickness of the segment plates 72, as can be seen from the representation of FIG. It can also be seen in FIG. 18 that the material thickness of the segment plates 72 located directly next to the segment plates 73 is greater than the material thickness of the remaining segment plates 72. Overall, it is achieved that the diffuser element 71a in the turbine can cope with all operating stresses and nevertheless has the lowest possible weight.

Landscapes

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

Abstract

L'invention concerne un élément annulaire de guidage (1a, 51a, 61a, 71a) pour turbines et un procédé de fabrication correspondant, cet élément étant de faible poids et de fabrication aisée tout en répondant à toutes les exigences posées en termes de stabilité. Les surfaces d'écoulement d'air de l'élément annulaire de guidage (1a, 51a, 61a, 71a) sont faites de plaques segmentées (23, 24, 27, 28, 52, 53, 62, 63, 72, 73) de petites dimensions relativement à l'élément annulaire de guidage (1a, 51a, 61a, 71a). L'élément annulaire de guidage (1a, 51a, 61a, 71a) est fabriqué par assemblage d'éléments individuels, les différentes étapes d'assemblage des éléments individuels entre eux et éventuellement avec d'autres éléments individuels étant exécutées soit simultanément soit l'une après l'autre dans un ordre quelconque.
PCT/EP2010/000708 2009-02-07 2010-02-05 Élément annulaire de guidage pour turbines et procédé de fabrication correspondant WO2010089125A2 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE102009007999.8 2009-02-07
DE200910007999 DE102009007999A1 (de) 2009-02-07 2009-02-07 Leitringelement für Turbinen und Verfahren zu dessen Herstellung

Related Child Applications (1)

Application Number Title Priority Date Filing Date
US13/480,521 Continuation US8574036B2 (en) 2009-11-27 2012-05-25 Machining station and apparatus for machining a workpiece

Publications (2)

Publication Number Publication Date
WO2010089125A2 true WO2010089125A2 (fr) 2010-08-12
WO2010089125A3 WO2010089125A3 (fr) 2011-06-16

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ID=42317460

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Application Number Title Priority Date Filing Date
PCT/EP2010/000708 WO2010089125A2 (fr) 2009-02-07 2010-02-05 Élément annulaire de guidage pour turbines et procédé de fabrication correspondant

Country Status (2)

Country Link
DE (1) DE102009007999A1 (fr)
WO (1) WO2010089125A2 (fr)

Families Citing this family (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN109695481A (zh) * 2018-11-27 2019-04-30 德阳九鼎电气有限公司 一种用于汽轮机排气缸的导流器

Family Cites Families (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2316813A (en) * 1939-07-22 1943-04-20 Holzwarth Gas Turbine Co Bearer for the stationary vanes of rotary motors
US2638743A (en) * 1949-04-29 1953-05-19 Ruston & Hornsby Ltd Construction of turbine-inlet and stator elements of gas turbines
GB1038661A (en) * 1961-12-05 1966-08-10 Ass Elect Ind Improvements relating to metallic gas turbine combustion chambers
US3335483A (en) * 1961-12-19 1967-08-15 Gen Electric Method of manufacturing a stator assembly for turbomachines
FR2073239A1 (fr) * 1969-12-01 1971-10-01 Snecma
DE4329623A1 (de) * 1993-09-02 1995-03-09 Abb Management Ag Abgasdiffusor
DE10051223A1 (de) * 2000-10-16 2002-04-25 Alstom Switzerland Ltd Verbindbare Statorelemente
SE519781C2 (sv) * 2001-08-29 2003-04-08 Volvo Aero Corp Förfarande för framställning av en stator-eller rotorkomponent
US7997860B2 (en) * 2006-01-13 2011-08-16 General Electric Company Welded nozzle assembly for a steam turbine and related assembly fixtures
US7427187B2 (en) * 2006-01-13 2008-09-23 General Electric Company Welded nozzle assembly for a steam turbine and methods of assembly

Non-Patent Citations (1)

* Cited by examiner, † Cited by third party
Title
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Publication number Publication date
WO2010089125A3 (fr) 2011-06-16
DE102009007999A1 (de) 2010-08-12

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