EP2933562A1 - Procédé de montage d'un joint entre une chambre de combustion tubulaire d'une turbine à gaz et une pièce de transition - Google Patents

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

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Publication number
EP2933562A1
EP2933562A1 EP14164562.2A EP14164562A EP2933562A1 EP 2933562 A1 EP2933562 A1 EP 2933562A1 EP 14164562 A EP14164562 A EP 14164562A EP 2933562 A1 EP2933562 A1 EP 2933562A1
Authority
EP
European Patent Office
Prior art keywords
gas turbine
combustion chamber
sealing device
combustor
inlet end
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.)
Withdrawn
Application number
EP14164562.2A
Other languages
German (de)
English (en)
Inventor
Thorsten Drogan
Fabian Niederbremer
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 AG
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
Priority to EP14164562.2A priority Critical patent/EP2933562A1/fr
Priority to PCT/EP2015/056324 priority patent/WO2015158506A1/fr
Publication of EP2933562A1 publication Critical patent/EP2933562A1/fr
Withdrawn legal-status Critical Current

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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 of assembling a gas turbine combustor assembly with a gas turbine combustor having a tubular combustor, a tubular transition duct, which directs combustion gases exiting the combustor to a turbine of the gas turbine assembly, wherein an exhaust end of the combustor is inserted in an intended condition into an inlet end of the transition duct and is aligned concentrically with this, and a resiliently formed sealing means which seals in the intended condition an existing between the outlet end of the combustion chamber and the inlet end of the transitional channel annular gap. Furthermore, the present invention relates to a gas turbine burner.
  • 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 combustors, where the compressed air is mixed with fuel and the mixture is burned to produce combustion gases. The combustion gases leave the combustion chambers of the gas turbine combustors and are passed through transition channels, which are respectively connected to the combustion chambers of the gas turbine combustors, to the turbine, the blades of which are rotationally driven by the combustion gases.
  • the exhaust end of the combustors of the gas turbine combustor must be inserted into the inlet end of the associated transfer passage, which is already disposed in a housing of the gas turbine assembly.
  • the outlet end of the combustion chamber and the inlet end to align the transition channel concentric.
  • the sealing device will be damaged during operation of the gas turbine arrangement, which should be avoided.
  • the use of an alignment device is known, which is introduced in a first step instead of a gas turbine combustor in the housing of a gas turbine assembly and secured thereto.
  • the alignment device comprises a dial gauge, with the help of which then the inlet end of the associated transition channel can be aligned within a predetermined tolerance range. After alignment, the transition channel is fixed in the aligned position and the alignment device is removed, whereupon the gas turbine combustor can be mounted by introducing the outlet end of its combustion chamber into the inlet end of the aligned transition channel.
  • 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 adding tolerances can not always be guaranteed, so that proper operation can not be guaranteed and damage to the sealing device can not be safely excluded.
  • 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 concentric alignment of combustion chamber and transitional channel is automatically ensured without additional alignment device. 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.
  • the filler material melts and completely releases the sealing device so that it can compensate for temperature-induced movement between the outlet end of the combustion chamber and the inlet end of the transition channel.
  • the sealing device is biased in accordance with an embodiment of the method according to the invention before the implementation of step b) to reduce its outer diameter. In this way, the outer diameter of the cavity, which is filled in step b) with the filling material, and thus the accuracy of the coaxial alignment can be adjusted.
  • a clamping ring is preferably used for biasing the sealing device.
  • a clamping ring is placed around the sealing device in order then to introduce the filling material in the prestressed state of the sealing device into the at least one cavity.
  • the tension ring may also remain mounted during transport of the gas turbine combustor to protect the seal assembly 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 when selecting the filler material 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.
  • the present invention further provides a gas turbine combustor having a tubular combustion chamber with an outlet end, on the outer periphery of a resiliently formed sealing means is arranged in the normal state between the outlet end of the combustion chamber and an inlet end of a housing a gas turbine arrangement arranged transition channel seals existing annular gap, characterized in that at least one existing between the sealing means and the combustion chamber, the spring travel of the sealing device defining cavity is at least partially filled with a sealing device supporting the filling material whose flash point below the operating temperature of the gas turbine burner is in the region of the sealing device.
  • the sealing device preferably has spring elements which protrude radially outwards from the outer surface of the combustion chamber and in the intended state are sealingly engaged with the inner circumference of the inlet end of the transition channel.
  • 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.
  • FIG. 1 shows a portion of a gas turbine assembly in which a gas turbine combustor 1 is inserted into a housing 2 of the gas turbine assembly.
  • 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.
  • the flange 3 can also be fastened directly to the housing 2, that is, the connection housing 4 can be dispensed with.
  • the gas turbine combustor 1 has a tubular combustion chamber 5, the outlet end of which is connected to an inlet end of a tubular transition channel 6 positioned in the housing 2 of the gas turbine arrangement, which is held on the housing 2 via an adjusting and fixing device 7.
  • 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 transitional channel 6, a sealing device is provided, which formed by radially outwardly projecting spring elements 8 provided on the outer circumference of the outlet end of the combustion chamber 5 on a spring element ring which are sealingly engaged with the inner periphery of the inlet end of the transition channel 6.
  • the spring elements 8 serve on the one hand to seal the existing between the combustion chamber 5 and the transition channel 6 annulus. On the other hand, they compensate for temperature-induced movements between the combustion chamber 5 and the transition channel. 6
  • the arrangement shown is in a first step, the transition channel 6 using the adjusting and fixing device 7 in the region of its intended Position roughly pre-adjusted inside the housing 2.
  • the Vorjustage can be done for example by a loose tightening of adjusting and fixing screws 9 of the adjusting and fixing device 7.
  • the gas turbine combustor 1 is inserted into the housing 2 through a passage opening 10 extending through the housing 2 and the connecting housing 4, wherein the outlet end of the combustion chamber 5 is inserted into the inlet end of the transitional passage 6 with partial compression of the spring elements 8.
  • the inlet end of the transitional passage 6, if required, is manually positioned with respect to the outlet end of the combustion chamber 5 so as to allow insertion of the outlet end of the combustion chamber 5 into the inlet end of the transitional passage 6.
  • the adjusting and fixing screws 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 will be preconfigured as described below with reference to FIGS FIGS. 2 to 8 described prepared:
  • FIG. 2 shows the outlet end of the combustion chamber 5 in a state in which act on the spring elements 8 no external forces.
  • the spring elements 8 are biased to reduce their outer diameter such that the present between the combustion chamber 5 and the spring elements 8 annular cavity has a predetermined outer diameter.
  • a clamping ring 11 is pushed with a correspondingly selected inner diameter, as in FIG. 3 is shown.
  • 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. 3 sets, as in FIG.
  • 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 filling levels of the filling material 12 in the axial direction.
  • a low degree of filling is selected, in which an annular gap 15 remains between the filling material 12 and an annular stop 14 with L-shaped cross section, which serves to limit the radial inward movement of the spring elements 8.
  • Such a low degree of filling is characterized by a small contact surface between the spring elements 8 and the filling material 12, by a predetermined bending stress on the spring elements during insertion into the inlet end of the transition channel 6 and by the possibility of axial movement of the filler material 12.
  • 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.
  • the contact area between the spring elements 8 and the filling material 12 is greater and the bending stress of the spring elements during assembly is lower than in the FIG. 6 shown low degree of filling.
  • only a slight axial movement of the filler 12 is allowed.
  • more wax is needed than in the variant described above in this average degree of filling.
  • the degree of filling of the filler material 12 is chosen so high that the ring stop 14 is completely embedded in the filler material 12. At this high degree of filling, the largest contact area between the spring elements 8 and the filling material 12 is achieved. An axial movement of the filler 12 is almost completely prevented, since the ring stop 14 prevents such. Furthermore, the spring elements 8 experience no bending stress during assembly. The disadvantage, however, is that in this variant more filler 12 is needed.
  • the main advantage associated with filling the annular cavity between the spring elements 8 and the outer surface of the combustion chamber 5 with a spring material 8 supporting filler 12, is that upon insertion of the outlet end of the combustion chamber 5 in the inlet end of the transition channel 6 automatically exact 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 installation of the gas turbine burner 1 is fast, easy and easy to perform 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 in the context of biasing and by a suitable choice of the filling height of the filler material.
  • the filler material melts, so that the proper functioning of the sealing device is not affected by the filling material.

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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)
EP14164562.2A 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 Withdrawn EP2933562A1 (fr)

Priority Applications (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
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

Applications Claiming Priority (1)

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

Publications (1)

Publication Number Publication Date
EP2933562A1 true EP2933562A1 (fr) 2015-10-21

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EP14164562.2A Withdrawn 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

Country Status (2)

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

Families Citing this family (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE102017203465A1 (de) * 2017-03-03 2018-09-06 Siemens Aktiengesellschaft Verfahren zur Montage und/oder Demontage, Vorrichtung zur Verwendung in dem Verfahren, Brenner-Adapter, Transition-Adapter, Anordnung sowie Verwendung eines Roboters
JP7149807B2 (ja) 2018-11-01 2022-10-07 三菱重工業株式会社 ガスタービン燃焼器

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

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Publication number Publication date
WO2015158506A1 (fr) 2015-10-22

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