WO2015158506A1 - Procédé de montage d'un moyen d'étanchéité entre une chambre de combustion tubulaire de turbine à gaz et une pièce de transition - Google Patents

Procédé de montage d'un moyen d'étanchéité entre une chambre de combustion tubulaire de turbine à gaz et une pièce de transition Download PDF

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Publication number
WO2015158506A1
WO2015158506A1 PCT/EP2015/056324 EP2015056324W WO2015158506A1 WO 2015158506 A1 WO2015158506 A1 WO 2015158506A1 EP 2015056324 W EP2015056324 W EP 2015056324W WO 2015158506 A1 WO2015158506 A1 WO 2015158506A1
Authority
WO
WIPO (PCT)
Prior art keywords
combustion chamber
gas turbine
sealing device
inlet end
transition channel
Prior art date
Application number
PCT/EP2015/056324
Other languages
German (de)
English (en)
Inventor
Thorsten Drogan
Fabian Niederbremer
Original Assignee
Siemens Aktiengesellschaft
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 Aktiengesellschaft filed Critical Siemens Aktiengesellschaft
Publication of WO2015158506A1 publication Critical patent/WO2015158506A1/fr

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Classifications

    • 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
    • F23R3/60—Support structures; Attaching or mounting means
    • 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
    • F01D25/285—Temporary support structures, e.g. for testing, assembling, installing, repairing; Assembly methods using such structures
    • 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
    • F23R3/42—Continuous combustion chambers using liquid or gaseous fuel characterised by the arrangement or form of the flame tubes or combustion chambers
    • F23R3/46—Combustion chambers comprising an annular arrangement of several essentially tubular flame tubes within a common annular casing or within individual casings
    • 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

Definitions

  • the present invention relates to a method for assembling a gas turbine burner arrangement with a gas turbine burner, which has a tubular combustion chamber, a tubular transition channel, the combustion chamber leaving combustion Ver ⁇ combustion gases to a turbine of the gas turbine arrangement passes, wherein an outlet end of the combustion chamber in beticiansge ⁇ MAESSEN state ⁇ inserted into an inlet end of the transition duct and concentrically aligned thereto, and a resiliently formed sealing means in a predetermined state, between the outlet end of the
  • the present invention relates ⁇ a gas turbine combustor.
  • Gas turbine assemblies are known in the art. They include a compressor, multiple gas turbine burners and a turbine. During operation, ambient air is compressed using the compressor and supplied to the gas turbine ⁇ burners in which mixed the compressed air with fuel ⁇ substance and the mixture to produce combustion gases is burned. The combustion gases leave the combustion chambers of the gas turbine burners and are passed through transition channels, which are each connected to the combustion chambers of Gasturbi ⁇ nenbrenner to the turbine, the blades are driven in rotation by the combustion gases.
  • the alignment device comprises a dial gauge, by means of which then within a predetermined tolerance range ⁇ semi aligned, the inlet end of the associated transition duct who can ⁇ . After alignment, the transition channel is fixed in the aligned position and the alignment removed again, after which the gas turbine burner mounted under the introduction of the outlet end of its combustion chamber in the inlet end of the aligned transitional channel ⁇ who can.
  • a disadvantage of the use of such an alignment ⁇ device is that this is associated with much effort and high costs.
  • proper alignment due to the added tolerances can not always be guaranteed, so that proper operation can not be guaranteed and damage to the sealing device can not be safely ruled out. Based on this prior art, it is an object of the present invention to provide an alternative method for assembling a gas turbine burner assembly of the type mentioned, which can be carried out easily and inexpensively and prevents installation-related damage to the sealing device.
  • the present invention provides a method of the type mentioned above, comprising the steps:
  • step b) ensures that the sealing device can only be compressed to a defined extent during insertion of the outlet end of the combustion chamber into the inlet end of an associated transition channel, as further compression by the filler material is prevented.
  • a concen ⁇ generic orientation of the combustion chamber and transfer channel is automatically ensured without additional alignment device during the insertion of the outlet end of the combustion chamber into the inlet end of the transition duct. Accordingly, the installation of a gas turbine burner can be performed quickly, easily and inexpensively. After the insertion process, only the transition duct and the gas turbine burner still need to be fixed to the housing.
  • this system ⁇ peratur employmente movements between the outlet end of the
  • Combustion chamber and the inlet end of the transition channel can compensate ⁇ chen.
  • the sealing device according to an embodiment of the method according to the invention before the implementation of Schrit tes b) biased ⁇ reducing its outer diameter ⁇ .
  • the outer diameter of the cavity, which is filled in step b) with the filling material, and thus the accuracy of the coaxial alignment is ⁇ sets.
  • a clamping ring is preferably used for biasing the sealing device. Such a clamping ring is placed around the sealing device in order then to introduce the filling material in the pretensioned state of the sealing device into the at least one cavity.
  • the clamping ring can also be mounted during transport of the gas turbine burner lead ⁇ ben to protect the sealing device from external damage. Only shortly before the installation of the gas turbine burner, the clamping ring must be removed.
  • the filler material is a wax, a polymer or a resin.
  • natural waxes, synthetic waxes, natural resins, synthetic resins or the like can be used.
  • care must be taken to ensure that it does not adversely affect the operation of the gas turbine arrangement in the molten state.
  • the sealing device has spring elements which protrude radially outwards from the outer surface of the combustion chamber and in the proper state are in sealing engagement with the inner circumference of the inlet end of the transitional channel.
  • ⁇ constricting invention further provides a gas turbine combustor, comprising a tubular combustion chamber having an outlet end, at its outer periphery a resiliently designed Dichtungsein- direction is arranged in the intended state a between the outlet of the combustion chamber and an inlet end a sealing ring arranged in a housing of a gas turbine arrangement seals annular gap, characterized in that at least one existing between the sealing device and the combustion chamber, the
  • Spring cavity of the sealing device defining cavity is at least partially filled with a sealing device abstüt ⁇ zenden filling material whose flash point below the operating temperature of the gas turbine burner is in the region of the sealing device.
  • the sealing means preferably comprises spring elements comprises up, are projecting from the outer surface of the combustion chamber radially from ⁇ Wind lake and in the predetermined state with the inner circumference of the inlet end of the transition duct sealingly engaged.
  • the spring elements are advantageously arranged on a spring element ring held on the outer circumference of the combustion chamber. In this way, a simple structure is achieved.
  • the filler material is preferably a wax, a polymer or a resin.
  • Figure 1 is a schematic cross-sectional view of a Gastur ⁇ binenanssen showing a gas turbine burner and a transition duct in the assembled state;
  • FIG. 1 shows a region of a gas turbine arrangement in which a gas turbine burner 1 is inserted into a housing 2 of the gas turbine arrangement.
  • the gas turbine burner 1 is connected via a flange 3 with a connecting housing 4, which in turn is screwed to the housing 2.
  • a connecting housing 4 which in turn is screwed to the housing 2.
  • gas turbine arrangements of the flange 3 but can also be attached directly to the housing 2, thus dispenses with the connector housing.
  • the Gasturbinenbren- ner 1 has a tubular combustion chamber 5, the capacity utilization ⁇ broadcasting with an inlet end of a positioned in the housing 2 of the gas turbine arrangement ⁇ tubular transition duct
  • the outlet end of the combustion chamber 5 is inserted into the inlet end of the transition ⁇ channel 6, wherein between the combustion chamber 5 and the transition channel 6, a sealing device is arranged, which provided by on the outer circumference of the outlet end of the combustion chamber 5 on a spring element ring, radially outward projecting spring elements 8 is formed, which are sealingly engaged with the inner ⁇ circumference of the inlet end of the transition channel 6.
  • the spring elements 8 serve to seal the annular space existing between the combustion chamber 5 and the transition channel 6. On the other hand, they compensate for temperature-related movements between the combustion chamber 5 and the transition duct 6.
  • the transition channel 6 is made using the adjusting and fixing device 7 in the region of its well-adjusted position within the housing 2 roughly pre-adjusted.
  • the Vorjustage can be done for example by a lo ⁇ ckeres tightening adjustment and fixing screws 9 of the adjusting and fixing device 7.
  • the gas turbine burner 1 by a through the housing 2 and the connecting housing 4 extending
  • Transition channel 6, if necessary, positioned manually with respect to the outlet end of the combustion chamber 5, so as to allow the insertion of the outlet end of the combustion chamber 5 in the inlet end of the transition channel 6.
  • the adjusting and Fixierschrau ⁇ Ben 9 are tightened to fix the inlet end of the transition channel 6.
  • the gas turbine burner 1 is screwed to the connection housing 4.
  • the gas turbine combustor 1 is in advance as described below prepared as described with reference to Figures 2 to 8:
  • FIG. 2 shows the outlet end of the combustion chamber 5 in a state in which no external forces act on the spring elements 8.
  • the spring elements 8 are biased to reduce its outer diameter such that the existing between the combustion ⁇ chamber 5 and the spring elements 8 annular cavity has a predetermined outer diameter.
  • the annular cavity between the spring elements 8 and the outer surface of the combustion chamber 5, which in the prestressed state according to FIG. represents, as shown in Figure 4 filled with a supporting Gu ⁇ material 12 whose flame temperature is below the operating temperature of the gas turbine combustor 1 in the region of the spring elements 8.
  • the filler material 12 may be, for example, a wax, a polymer or a resin, to name just a few examples.
  • FIGS. 6 to 8 show different degrees of filling of the filling material 12 in the axial direction.
  • a low degree of filling is selected, in the zwi ⁇ tween the filler material 12 and a ring stop 14 with L-shaped cross-section, which limits the radial
  • the degree of filling is chosen such that between the filler material 12 and the ring stop 14 no annular gap is no longer present.
  • this medium degree of filling is the
  • the essential advantage associated with filling the annular cavity between the spring elements 8 and the outer surface of the combustion chamber 5 with a filling material 12 supporting the spring elements 8 is that upon insertion of the outlet end of the combustion chamber 5 into the inlet end of the transitional channel 6 automatically an accurate coaxial alignment of combustion chamber 5 and transition channel 6 takes place, since a compression of the spring elements 8 beyond the filler material is not possible. Accordingly, the assembly of the gas turbine burner 1 is fast, simple and prob ⁇ lemlos feasible without separate alignment devices.
  • the accuracy of the coaxial alignment can be adjusted by suitable adjustment of the outer diameter of the filling material to be filled with the cavity cavity in the context of Vorspan ⁇ nens and by a suitable choice of the filling height of the filler material.
  • the filling material melts, so that the proper functioning of the sealing device is not impaired by the filling material.

Landscapes

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

Abstract

L'invention concerne un procédé de montage d'un système de brûleur de turbine à gaz comprenant un brûleur de turbine à gaz (1) qui comporte une chambre de combustion tubulaire (5), un conduit de transition tubulaire (6) qui dirige les gaz de combustion quittant la chambre de combustion (5) vers une turbine du système de turbine à gaz, une extrémité de sortie de la chambre de combustion (5) étant introduite dans l'état de fonctionnement dans une extrémité d'entrée du conduit de transition (6) et orientée concentriquement à celui-ci, et un moyen d'étanchéité élastique qui réalise dans l'état de fonctionnement l'étanchéité au niveau d'une fente annulaire ménagée entre l'extrémité de sortie de la chambre de combustion (5) et l'extrémité d'entrée du conduit de transition (6). Le procédé comprend les étapes consistant à : a) disposer le moyen d'étanchéité sur la périphérie extérieure de l'extrémité de sortie de la chambre de combustion (5) ; b) remplir au moins partiellement une ou plusieurs cavités, qui sont présentes entre le moyen d'étanchéité et la chambre de combustion (5) et qui définissent le débattement élastique du moyen d'étanchéité, avec un matériau de remplissage (12) qui supporte le moyen d'étanchéité et dont la température d'inflammation est inférieure à la température de fonctionnement du brûleur de turbine à gaz (1) au niveau du moyen d'étanchéité ; c) insérer l'extrémité de sortie de la chambre de combustion (5) dans l'extrémité d'entrée du conduit de transition (6) disposé dans un boîtier du système de turbine à gaz ; et d) fixer le conduit de transition (6) et la chambre de combustion (5).
PCT/EP2015/056324 2014-04-14 2015-03-25 Procédé de montage d'un moyen d'étanchéité entre une chambre de combustion tubulaire de turbine à gaz et une pièce de transition WO2015158506A1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
EP14164562.2A EP2933562A1 (fr) 2014-04-14 2014-04-14 Procédé de montage d'un joint entre une chambre de combustion tubulaire d'une turbine à gaz et une pièce de transition
EP14164562.2 2014-04-14

Publications (1)

Publication Number Publication Date
WO2015158506A1 true WO2015158506A1 (fr) 2015-10-22

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PCT/EP2015/056324 WO2015158506A1 (fr) 2014-04-14 2015-03-25 Procédé de montage d'un moyen d'étanchéité entre une chambre de combustion tubulaire de turbine à gaz et une pièce de transition

Country Status (2)

Country Link
EP (1) EP2933562A1 (fr)
WO (1) WO2015158506A1 (fr)

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN110494256A (zh) * 2017-03-03 2019-11-22 西门子股份公司 用于安装和/或拆卸的方法、应用于该方法的设备、燃烧器适配器、过渡部适配器、装置以及机器人的应用
CN111140873A (zh) * 2018-11-01 2020-05-12 三菱日立电力系统株式会社 燃气轮机燃烧器及过渡段组装体

Citations (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE102009003674A1 (de) * 2008-03-27 2009-10-01 General Electric Co. Schwimmender Bund einer Brennkammerkappe mit E-Dichtung
EP2144003A2 (fr) * 2008-07-10 2010-01-13 United Technologies Corporation Chemise de combustion pour moteur à turbine à gaz

Patent Citations (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE102009003674A1 (de) * 2008-03-27 2009-10-01 General Electric Co. Schwimmender Bund einer Brennkammerkappe mit E-Dichtung
EP2144003A2 (fr) * 2008-07-10 2010-01-13 United Technologies Corporation Chemise de combustion pour moteur à turbine à gaz

Cited By (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN110494256A (zh) * 2017-03-03 2019-11-22 西门子股份公司 用于安装和/或拆卸的方法、应用于该方法的设备、燃烧器适配器、过渡部适配器、装置以及机器人的应用
CN110494256B (zh) * 2017-03-03 2022-10-14 西门子能源全球有限两合公司 用于安装和/或拆卸的方法、应用于该方法的设备、燃烧器适配器、过渡部适配器、装置以及机器人的应用
CN111140873A (zh) * 2018-11-01 2020-05-12 三菱日立电力系统株式会社 燃气轮机燃烧器及过渡段组装体
CN111140873B (zh) * 2018-11-01 2021-06-11 三菱动力株式会社 燃气轮机燃烧器及过渡段组装体
US11377971B2 (en) 2018-11-01 2022-07-05 Mitsubishi Heavy Industries, Ltd. Gas turbine combustor

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Publication number Publication date
EP2933562A1 (fr) 2015-10-21

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