EP2242955B1 - Turbine à gaz à chambre de combustion annulaire et procédé d'assemblage - Google Patents

Turbine à gaz à chambre de combustion annulaire et procédé d'assemblage Download PDF

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Publication number
EP2242955B1
EP2242955B1 EP09712985.2A EP09712985A EP2242955B1 EP 2242955 B1 EP2242955 B1 EP 2242955B1 EP 09712985 A EP09712985 A EP 09712985A EP 2242955 B1 EP2242955 B1 EP 2242955B1
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EP
European Patent Office
Prior art keywords
connecting elements
machine according
thermal machine
shell
connecting element
Prior art date
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Active
Application number
EP09712985.2A
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German (de)
English (en)
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EP2242955A1 (fr
Inventor
Remigi Tschuor
Russell Bond Jones
Nilze Isabel Seda-Maurell
Marion Oneil Duggans
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General Electric Technology GmbH
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General Electric Technology GmbH
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Publication date
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Publication of EP2242955A1 publication Critical patent/EP2242955A1/fr
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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D9/00—Stators
    • F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
    • F01D9/023—Transition ducts between combustor cans and first stage of the turbine in gas-turbine engines; their cooling or sealings
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
    • F23R3/002—Wall structures
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
    • F23R3/42—Continuous combustion chambers using liquid or gaseous fuel characterised by the arrangement or form of the flame tubes or combustion chambers
    • F23R3/50—Combustion chambers comprising an annular flame tube within an annular casing
    • 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
    • F05D2260/00—Function
    • F05D2260/30—Retaining components in desired mutual position
    • F05D2260/36—Retaining components in desired mutual position by a form fit connection, e.g. by interlocking
    • 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
    • F05D2260/94—Functionality given by mechanical stress related aspects such as low cycle fatigue [LCF] of high cycle fatigue [HCF]
    • 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
    • F05D2260/94—Functionality given by mechanical stress related aspects such as low cycle fatigue [LCF] of high cycle fatigue [HCF]
    • F05D2260/941—Functionality given by mechanical stress related aspects such as low cycle fatigue [LCF] of high cycle fatigue [HCF] particularly aimed at mechanical or thermal stress reduction
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R2900/00—Special features of, or arrangements for continuous combustion chambers; Combustion processes therefor
    • F23R2900/00017—Assembling combustion chamber liners or subparts
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
    • Y10T29/00—Metal working
    • Y10T29/49—Method of mechanical manufacture
    • Y10T29/49229—Prime mover or fluid pump making

Definitions

  • the present invention relates to the field of thermal machines. It relates to a thermal machine according to the preamble of claim 1 and a method for mounting such a thermal machine.
  • IGT Modern industrial gas turbines
  • IGT are usually designed with annular combustion chambers.
  • Most smaller IGTs are designed as so-called "Can Annular Combustors".
  • An IGT with annular combustion chamber of the combustion chamber is limited by the side walls and the inlet and outlet plane of the hot gas.
  • Such a gas turbine is in the Fig. 1 and 2 shown.
  • the in the Fig. 1 and 2 Gas turbine 10 shown in section has a turbine housing 11 in which a rotor 12 rotating about an axis 27 is accommodated.
  • a compressor 17 On the right side of the rotor 12 a compressor 17 is formed for the compression of combustion and cooling air, on the left side of a turbine 13 is arranged.
  • the compressor 17 compresses air which flows into a plenum 14.
  • annular combustion chamber 15 is arranged, which is closed on the input side by a front plate cooling air 20 cooled front panel 19 and the output side via a hot gas channel 25 with the input of the turbine 13 in connection.
  • burners 16 are arranged in a ring, for example, as a premix burner, as they are preferably made EP-A1-321809 or EP-A1-704,657 emerge, are designed and inject a fuel-air mixture in the combustion chamber 15.
  • the cited documents and the developments derived therefrom form an integral part of this application.
  • the resulting during the combustion of the mixture hot air stream 26 passes through the hot gas channel 25 in the turbine 13 and is relaxed there under work.
  • the combustion chamber 15 with the hot gas channel 25 is outside with a distance surrounded by an outer and innerdehemd 21 and 31, which are fastened by means of fastening elements 24 to the combustion chamber 15, 25 and between them and the combustion chamber 15, 25 each have an outer and inner cooling channel 22 or 32 train.
  • In the cooling channels 22, 32 flows in the opposite direction to the hot gas flow 26 cooling air on the walls of the combustion chamber 15, 25 along a combustion chamber hood 18 and from there into the burner 16 and front plate cooling air 20 directly into the combustion chamber 15th
  • the side walls of the combustion chamber 15, 25 are carried out either as shell elements or as solid shells (outer shell 23, inner shell 33).
  • a parting plane (29 in Fig. 4 ff.), which allows an upper half of the shell 23, 33 (the upper part) to be removed, for example to assemble or disassemble the gas turbine rotor 12.
  • the parting plane 29 accordingly has two parting plane welding seams which are located at the height of the machine axis 27 using the example of the gas turbine engine constructed by the applicant.
  • EP 1 847 685 discloses a thermal machine, which comprises a limited by an outer shell and an inner shell to the outside, annular combustion chamber, wherein the outer shell and inner shell are each divided in a parting plane in an upper half and a lower half and which are welded together in the parting plane.
  • US 3,031,844 describes a method for mounting a thermal machine with the essential steps that the connecting element is inserted into one of the halves, in a second step, the two halves juxtaposed, in a third step, a connecting element is retracted into one of the halves of the respective shell , And the connecting element in the final position is firmly connected to the two halves.
  • CH 342 794 also discloses annular combustors which are composed of halves. According to the doctrine of GB 2 434 199 Seam lines between combustion chamber segments are covered by heat shield.
  • the side walls in the region of the parting planes 29 have a reduced strength and service life.
  • TBC Thermal Barrier Coating Thermal Barrier Coating
  • the thermally very heavily loaded outer and inner shells 23 and 33 act on the four parting planes (29 and others) with high compressive and tensile stresses.
  • the required service life of outer and inner shells 23 and 33 is typically two so-called service intervals (service intervals). An operating interval describes the time between (re) commissioning of the combustion chamber and the reconditioning of the components. Both shells, the outer and inner shell 23, 33, often begin to break at the beginning and end of the parting plane welding seams during operation.
  • connecting element in the form of a bridge that the outer shell and inner shell at the entrance and / or exit of the combustion chamber have a flange that the connecting elements are arranged on the outside of the flange the flange on the outside has a circumferential groove, and that the connecting elements are inserted into the groove.
  • the connecting elements can be releasably connected to the two halves of the outer shell or inner shell.
  • the connecting elements with the two halves of the outer shell or inner shell are then releasably connected by screws or bolts.
  • connecting elements can also be materially connected, in particular welded, to the two halves of the outer shell or inner shell.
  • the invention is characterized in that the groove and the connecting elements are formed such that the connecting elements are held by positive engagement in the groove.
  • the connecting elements have first means for improving the mechanical integrity, wherein throat-shaped incisions are preferably provided as means for improving the mechanical integrity, preferably at the ends.
  • Another embodiment is characterized in that the connecting elements have second means for improving the mountability, wherein as a means for improving the mountability is preferably provided on the top of a cam.
  • Another embodiment is characterized in that the connecting elements have third means for improving the cooling of the connecting elements.
  • the connecting elements fourth means for forming cooling channels between the connecting element and the flange, wherein as a means for forming cooling channels preferably on the bottom of a wavy base is provided.
  • An embodiment of the inventive method is characterized in that the connecting element is loosely inserted in the first step in the upper half and welded in the final position with the two halves.
  • Another embodiment is characterized in that the connecting element is inserted into the upper half in its final position in the first step and secured with screws or bolts, and that in the third step, the upper half is positioned with simultaneous retraction of the connecting element on the lower half.
  • An essential feature of the inventive idea is an additional, mechanical positive connection of the parting plane welding seams between the half shells of the outer shell and / or inner shell of an annular combustion chamber (remark: all following explanations and illustrations relate to the outer shell, but also apply correspondingly to an inner shell).
  • a bridge is used as an additional connecting element on both sides of the parting plane, preferably in a respective already existing flange.
  • this bridge may or may not be designed to continue to permit or permit cooling of the flange portion.
  • the bridge is used on one side, in the upper part of the outer shell, in a flanged groove.
  • the two shells are placed one above the other in the gas turbine (GT) and the bridge is pushed into position or beaten (a cam or a nose on the outer diameter of the bridge can serve as a starting point for a mandrel or hammer.)
  • GT gas turbine
  • the bridge is welded at its top with the flange.
  • the geometric design of the flange and the bridge itself allows preferably the cooling air to flow through the flange under the bridge over - and thus to ensure the conditions for a convective cooling.
  • the bridge is then inserted on one side, in the upper part (in the upper half) of the outer shell, into the flanged groove and positioned with bolts at its destination.
  • the two half shells are placed one above the other in the gas turbine and the bridge is retracted into the lower half shell.
  • the bridge can also be secured in the lower half shell (by bolts and / or screws). For better accessibility when welding the parting line, the bridge can also be removed and reused at any time.
  • the shells 23, 33 of the annular combustion chamber 15, 25 are provided on the burner side and at the turbine end with flanges for connection be used between the combustion chamber and adjacent components.
  • Fig. 3 shows as an example in longitudinal section the turbine-side end of the outer shell 23 of the combustion chamber 15, 25 from Fig. 1 with the attached flange 28.
  • the flange 28 has on the outside a groove 34 which receives the provided for mechanical relief of the parting plane welds bridges.
  • FIG. 7a to 7c The bridge 30 is in the form of an elongate planar strip of rectangular cross section having the slightly curved shape of a circular arc segment.
  • the length of the bridge 30 is selected so that on both sides of the parting plane 29 with sufficient distance two mounting holes 36 can be attached, which serve the screw / Verbolzung the bridge 30 with the two welded half-shells 23 a, 23 b. If the bridge 30 is screwed, according to Fig.
  • a connecting element 40 is preferably used according to FIG Fig. 8-10 or 11 used.
  • the bridge 40 is in its cross-sectional contour ( Fig. 10b ) of the cross-sectional contour of the flange groove 34 adapted so that the bridge 40 can be positively inserted into the groove 34 and thereby engages with a skirt 37 in an undercut in the groove 34.
  • a transversely projecting cam 39 is provided in the middle, at which when driving the bridge 40 into the groove 34 with a striking tool can be recognized.
  • a wave-shaped base 38 is formed ( Fig.
  • novel, positive-locking connecting elements which act as "structural bridges for the combustion chamber shell parting plane" ensure significantly improved force transmission at the ends of the parting plane.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)

Claims (14)

  1. Machine thermique, en particulier turbine à gaz (10), qui comprend une chambre de combustion (15, 25) de forme annulaire, limitée vers l'extérieur par une coque extérieure (23) et une coque intérieure (33), la coque extérieure (23) et la coque intérieure (33) étant à chaque fois divisées dans un plan de séparation (29) en une moitié supérieure (23a) et une moitié inférieure (23b) qui sont soudées l'une à l'autre dans le plan de séparation (29), caractérisée en ce que pour recevoir des forces de traction et de cisaillement agissant sur les flancs de séparation (29), un engagement positif mécanique supplémentaire (30, 40) est prévu au niveau des plans de séparation (29) sous la forme d'un élément de liaison (30, 40) s'étendant en forme de pont par-dessus le plan de séparation (29), en ce que la coque extérieure (23) et la coque intérieure (33) présentent une bride (28) à l'entrée et/ou à la sortie de la chambre de combustion (15, 25) et en ce que les éléments de liaison (30, 40) sont disposés sur le côté extérieur d'une de ces brides (28) de coque extérieure ou même de coque intérieure, en ce que la bride (28) présente sur le côté extérieur une rainure périphérique (34), les éléments de liaison (30, 40) étant insérés dans la rainure (34), et en ce que les éléments de liaison (30, 40) et la rainure (34) sont réalisés de telle sorte que les éléments de liaison pouvant être insérés dans la rainure soient maintenus par engagement positif dans la rainure (34).
  2. Machine thermique selon la revendication 1, caractérisée en ce que les éléments de liaison (30) sont connectés de manière amovible au deux moitiés (23a, 23b) de la coque extérieure (23) ou de la coque intérieure (33).
  3. Machine thermique selon la revendication 2, caractérisée en ce que les éléments de liaison (30) sont connectés de manière amovible aux deux moitiés (23a, 23b) de la coque extérieure (23) ou de la coque intérieure (33) par des vis (35) ou des boulons.
  4. Machine thermique selon l'une quelconque des revendications 2 à 3, caractérisée en ce que les éléments de liaison (40) sont connectés en outre par liaison de matière, notamment par soudage, aux deux moitiés (23a, 23b) de la coque extérieure (23) ou de la coque intérieure (33).
  5. Machine thermique selon l'une quelconque des revendications 1 à 4, caractérisée en ce que les éléments de liaison (30) présentent des premiers moyens (41, 42) pour améliorer l'intégrité mécanique.
  6. Machine thermique selon la revendication 5, caractérisée en ce que les éléments de liaison (40) présentent, en tant que moyens (41, 42) pour améliorer l'intégrité mécanique, des entailles en forme de gorge (41, 42) aux extrémités.
  7. Machine thermique selon l'une quelconque des revendications 1 à 6, caractérisée en ce que les éléments de liaison (40) présentent des deuxièmes moyens (39) pour améliorer la facilité de montage.
  8. Machine thermique selon la revendication 7, caractérisée en ce que les éléments de liaison (40) présentent, en tant que moyens pour améliorer la facilité de montage, une came (39) sur le côté supérieur.
  9. Machine thermique selon l'une quelconque des revendications 1 à 8, caractérisée en ce que les éléments de liaison (30, 40) présentent des troisièmes moyens pour améliorer le refroidissement des éléments de liaison (30, 40).
  10. Machine thermique selon l'une quelconque des revendications 1 à 9, caractérisée en ce que les éléments de liaison (40) présentent des quatrièmes moyens (38) pour réaliser des canaux de refroidissement entre l'élément de liaison (40) et la bride (28).
  11. Machine thermique selon la revendication 10, caractérisée en ce que les éléments de liaison (40) présentent, en tant que moyens pour réaliser de canaux de refroidissement, une surface de base de forme ondulée (38) sur le côté inférieur.
  12. Procédé de montage d'une machine thermique selon l'une quelconque des revendications 1 à 11, caractérisé en ce que dans une première étape, l'élément de liaison (30, 40) est inséré dans la moitié supérieure (23a) de la coque respective (23, 33) divisée en une moitié supérieure (23a) et une moitié inférieure (23b), en ce que dans une deuxième étape, la moitié supérieure et la moitié inférieure (23a, 23b) sont placées l'une sur l'autre, en ce que dans une troisième étape, l'élément de liaison (30, 40) est introduit dans la moitié inférieure (23b) de la coque respective (23, 33), et en ce que l'élément de liaison (30, 40), dans la position finale, est connecté par engagement positif à la moitié supérieure et à la moitié inférieure (23a, 23b).
  13. Procédé selon la revendication 12, caractérisé en ce que l'élément de liaison (40), dans la première étape, est inséré lâchement dans la moitié supérieure (23a) et, dans la position finale, est soudé aux deux moitiés (23a, 23b).
  14. Procédé selon la revendication 12, caractérisé en ce que l'élément de liaison (30), dans la première étape, est inséré dans la moitié supérieure (23a) au niveau de sa position finale et est fixé par des vis (35) ou des boulons, et en ce que dans la troisième étape, la moitié supérieure (23a), avec introduction simultanée de l'élément de liaison (30), est positionnée sur la moitié inférieure (23b) .
EP09712985.2A 2008-02-20 2009-02-12 Turbine à gaz à chambre de combustion annulaire et procédé d'assemblage Active EP2242955B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
CH2452008 2008-02-20
PCT/EP2009/051644 WO2009103658A1 (fr) 2008-02-20 2009-02-12 Turbine à gaz à chambre de combustion annulaire

Publications (2)

Publication Number Publication Date
EP2242955A1 EP2242955A1 (fr) 2010-10-27
EP2242955B1 true EP2242955B1 (fr) 2018-10-17

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EP09712985.2A Active EP2242955B1 (fr) 2008-02-20 2009-02-12 Turbine à gaz à chambre de combustion annulaire et procédé d'assemblage

Country Status (5)

Country Link
US (1) US20110113785A1 (fr)
EP (1) EP2242955B1 (fr)
AU (1) AU2009216857B2 (fr)
MY (1) MY158901A (fr)
WO (1) WO2009103658A1 (fr)

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US8549861B2 (en) * 2009-01-07 2013-10-08 General Electric Company Method and apparatus to enhance transition duct cooling in a gas turbine engine
EP2309099B1 (fr) * 2009-09-30 2015-04-29 Siemens Aktiengesellschaft Conduit de transition
KR101613096B1 (ko) 2011-10-24 2016-04-20 제네럴 일렉트릭 테크놀러지 게엠베하 가스 터빈
US9915428B2 (en) * 2014-08-20 2018-03-13 Mitsubishi Hitachi Power Systems, Ltd. Cylinder of combustor, method of manufacturing of cylinder of combustor, and pressure vessel
US9810434B2 (en) * 2016-01-21 2017-11-07 Siemens Energy, Inc. Transition duct system with arcuate ceramic liner for delivering hot-temperature gases in a combustion turbine engine
US10935235B2 (en) * 2016-11-10 2021-03-02 Raytheon Technologies Corporation Non-planar combustor liner panel for a gas turbine engine combustor
US10655853B2 (en) 2016-11-10 2020-05-19 United Technologies Corporation Combustor liner panel with non-linear circumferential edge for a gas turbine engine combustor
US10830433B2 (en) 2016-11-10 2020-11-10 Raytheon Technologies Corporation Axial non-linear interface for combustor liner panels in a gas turbine combustor
US10935236B2 (en) * 2016-11-10 2021-03-02 Raytheon Technologies Corporation Non-planar combustor liner panel for a gas turbine engine combustor
US11359810B2 (en) * 2017-12-22 2022-06-14 Raytheon Technologies Corporation Apparatus and method for mitigating particulate accumulation on a component of a gas turbine
US10697634B2 (en) * 2018-03-07 2020-06-30 General Electric Company Inner cooling shroud for transition zone of annular combustor liner

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JP3831638B2 (ja) * 2001-08-09 2006-10-11 三菱重工業株式会社 板状体接合方法、接合体、ガスタービン燃焼器用の尾筒、及び、ガスタービン燃焼器
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GB2434199B (en) * 2006-01-14 2011-01-05 Alstom Technology Ltd Combustor liner with heat shield
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AU2009216857A1 (en) 2009-08-27
WO2009103658A1 (fr) 2009-08-27
AU2009216857B2 (en) 2014-01-16
US20110113785A1 (en) 2011-05-19
MY158901A (en) 2016-11-30
EP2242955A1 (fr) 2010-10-27

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