EP3921577B1 - Système de chambre de combustion à tubes et installation de turbine à gaz pourvue d'un tel système de chambre de combustion à tubes - Google Patents

Système de chambre de combustion à tubes et installation de turbine à gaz pourvue d'un tel système de chambre de combustion à tubes Download PDF

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Publication number
EP3921577B1
EP3921577B1 EP20711063.6A EP20711063A EP3921577B1 EP 3921577 B1 EP3921577 B1 EP 3921577B1 EP 20711063 A EP20711063 A EP 20711063A EP 3921577 B1 EP3921577 B1 EP 3921577B1
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EP
European Patent Office
Prior art keywords
lining
combustion chamber
turbine
chamber system
hot gas
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Active
Application number
EP20711063.6A
Other languages
German (de)
English (en)
Other versions
EP3921577A1 (fr
Inventor
Matthias Gralki
Claus Krusch
Daniel Schmidt
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Siemens Energy Global GmbH and Co KG
Original Assignee
Siemens AG
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Siemens AG filed Critical Siemens AG
Publication of EP3921577A1 publication Critical patent/EP3921577A1/fr
Application granted granted Critical
Publication of EP3921577B1 publication Critical patent/EP3921577B1/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
    • F23R3/02—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration
    • 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
    • F23R3/007—Continuous combustion chambers using liquid or gaseous fuel constructed mainly of ceramic components
    • 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

Definitions

  • the present invention relates to a combustor can system for a gas turbine plant having a plurality of annularly arranged transition ducts which are designed to be connected at their upstream ends to a combustor and to direct hot gas generated by the combustors to a turbine. Furthermore, the present invention relates to a gas turbine system with a plurality of burners arranged in a ring, a turbine and a tubular combustion chamber system of the type described above, which connects the burners to the turbine.
  • a prior art combustor can system is known from US Pat US 9,618,207 B1 known.
  • Tubular combustion chamber systems of the type mentioned above are used in gas turbine systems to conduct hot gas from the burners to the turbine inlet.
  • they include transition lines designed as pipelines, which are also referred to as "transitions" in professional circles.
  • the transition lines are thermally highly stressed during operation of the gas turbine system. Accordingly, they are made of high-temperature-resistant materials.
  • they are made of thin-walled nickel-based materials with internal cooling channels and an inner layer system for thermal insulation (TBC + MCrAlY). Sealing systems are provided at the turbine inlet interface to reduce leakage of compressed air into the combustion system and allow for relative movement between the combustor can system and the turbine and between the individual transition ducts.
  • the lateral seals are subject to severe abrasion wear.
  • the transition lines and their inner layer system also wear out due to the high thermal load, primarily in the outlet area as a result of layer aging and sealing groove wear.
  • the flow to the turbine is not uniform due to the non-continuous inflow cross-section at the interface between the transition lines and the turbine.
  • the uneven inflow caused by the shadowing by the side walls and seals of the outlet area of the transition lines causes high-frequency temperature and speed changes with negative effects on the service life of the turbine blades.
  • the service life of the transition lines is limited by the layer system and the seals to the turbine.
  • the internal cooling channels are manufactured by joining several metal sheets and is therefore associated with a great deal of effort. Additive manufacturing has so far been ruled out due to the size and volume limits of available 3D printers.
  • Additive manufacturing has so far been ruled out due to the size and volume limits of available 3D printers.
  • the reprocessing also includes the decoating of the complete layer system and the recoating. The costs of this complex preparation are therefore close to the new part costs.
  • the life cycle costs of new or existing gas turbine systems are primarily determined by the service life and maintenance intervals of the hot gas components.
  • significantly longer maintenance intervals are required for new gas turbine systems with simultaneous increased thermal stress.
  • constructive solutions are required that eliminate or at least significantly improve the weak points of current designs.
  • an object of the present invention is to create a tubular combustion chamber system of the type mentioned at the beginning with an improved design.
  • the present invention provides a combustor can system according to claim 1.
  • the combustor can system includes a hot gas manifold adapted for connection to the turbine and defining an annular duct open to the turbine into which the downstream ends of the transition ducts open.
  • a hot gas manifold adapted for connection to the turbine and defining an annular duct open to the turbine into which the downstream ends of the transition ducts open.
  • the transition ducts and the hot gas manifold are made of metal and lined internally with a refractory lining, particularly a ceramic lining. Thanks to such a lining, the thermal stress on the metallic components, i.e. the hot gas distributor and the transition lines, is significantly reduced. The associated lower expansion differences in the area of the seals to the turbine and the seals between the transition lines lead to less wear in this area and enable more solid joining concepts between the tubular combustion chamber system and the turbine. In addition, the refractory lining entails lower high-temperature requirements for the materials of the metallic components, which means that costs can be saved.
  • the transition lines can be designed without an inner layer system, which significantly reduces the effort for repair and reprocessing, since the transition lines do not have to be stripped and recoated.
  • the use of a refractory lining also reduces the need for cooling of the metallic components of the can combustor system. Compared to tubular combustion chamber systems without a ceramic lining, the cooling air requirement according to current Calculations can be reduced by up to 50%, which entails an increase in the performance of the gas turbine plant.
  • each transition pipe tapers conically in the downstream direction, the refractory lining of the transition pipe having at least one annular lining section with an outer diameter tapering conically in the downstream direction, which is held on the transition pipe with radial and axial pretension.
  • a prestress which can be implemented, for example, by positioning spring and/or damping elements between the refractory lining and the corresponding transition line, thermal expansion differences between the metal transition lines and their ceramic lining are compensated.
  • the ceramic lining is fixed with limited force under all operating conditions.
  • the at least one ring-shaped lining section can be formed by a single lining element, ie by a ring-shaped lining element with a conical outer surface.
  • the at least one ring-shaped lining section using a plurality of ring-segment-shaped lining elements which are braced against one another in the circumferential direction.
  • the refractory lining of the hot gas distributor advantageously has a large number of lining elements which are fastened under radial pretension to the surfaces of the hot gas distributor which are arranged radially on the inside and on the outside.
  • the lining elements of the hot gas distributor should be installed with as few gaps as possible between the individual lining elements in order to reduce the cooling air requirement, which is made possible by the radial prestressing.
  • the transition lines and the hot gas distributor are preferably made from a high-temperature-resistant metal material, in particular from a thin-walled, high-temperature-resistant material like a tin.
  • a high-temperature-resistant metal material in particular from a thin-walled, high-temperature-resistant material like a tin.
  • the outer peripheral side and/or the inner peripheral side of the hot gas distributor is/are advantageously provided with a fastening flange, which is designed for fastening to the turbine. In this way a very simple construction is achieved.
  • the present invention provides a gas turbine system with a plurality of burners arranged in a ring, a turbine and a tubular combustion chamber system according to the invention, which connects the burners to the turbine.
  • the figures show a combustor can system 1 according to an embodiment of the present invention, which is connected to a turbine 2 of a gas turbine plant 3 .
  • the can combustor system 1 comprises a plurality of annularly arranged transition lines 4, which are designed to be connected with their upstream ends to a burner 10 and to conduct hot gas generated by the burners 10 to the turbine 2, wherein in figure 1 exemplary only a single burner 10 is shown.
  • the tubular combustion chamber system 1 comprises a hot gas distributor 5 which is designed for connection to the turbine 2 and which defines an annular duct 6 which is open towards the turbine 2 and into which the downstream ends of the transition lines 4 open.
  • the transition lines 4 as well as the hot gas distributor 5 are made of metal, for example a high-temperature metal alloy.
  • the transition lines 4 each include a refractory lining 7, which is preferably made of a ceramic material.
  • the transition lines 4 each have a cross section that tapers conically in the downstream direction.
  • the refractory lining 7 of the transition lines 4 each comprises a plurality of ring-shaped lining sections with an outer diameter that tapers conically in the downstream direction, which in the present case are formed by ring-shaped lining elements 7a.
  • the lining elements 7a of a transition line 4 are pushed axially into the transition line 4, starting from the upstream end of the transition line 4, with spring and/or damping elements (not shown in detail) being positioned along the circumference between the lining elements 7a and the inner wall of the transition line 4 are guided in a form-fitting manner on the outer circumference of the lining elements 7a or on the inner wall of the transition line 4 . Due to the conical design of the transition line 4 and the lining elements 7a, the lining elements 7a are braced radially and axially in such a way that they are held on the transition line 4 with radial and axial pretension.
  • Tension is maintained here by an annular compression member 8 which is inserted into the transition pipe 4 at the upstream end, pressed against the face of the adjacent lining member 7a and then secured to the transition pipe 4 to provide the desired compression force.
  • the attachment can be done for example by means of screws.
  • the refractory Lining 7 of the hot gas distributor 5 is realized via a multiplicity of lining elements 7b, which are advantageously also fastened under radial pretension to the surfaces of the hot gas distributor 5 arranged radially on the inside and outside.
  • the outer peripheral side and the inner peripheral side of the hot gas distributor 5 are provided with fastening flanges 9 at the free end of the hot gas distributor 5 pointing towards the turbine 2, which are designed for fastening to the turbine 2 by means of screws.
  • the arrangement described above is advantageous in that, thanks to the additional hot gas distributor 5 of the tubular combustion chamber system 1 according to the invention, a very uniform hot gas flow to the turbine 2 is achieved, which significantly reduces high-frequency temperature and speed changes. This has a very positive effect on the service life of the turbine blades.
  • the refractory lining 7 of the transition lines 4 and the hot gas distributor 5 is significantly reduced.
  • the associated lower expansion differences in the area of the seals to the turbine 2 and the seals between the transition lines 4 lead to less wear in this area and enable more solid joining concepts between the tubular combustion chamber system 1 and the turbine 2.
  • the refractory lining 7 attracts lower high-temperature requirements the materials of the metallic components 4 and 5 after it, whereby costs can be saved.
  • the transition lines 4 can be designed without an inner layer system, which significantly reduces the effort for repair and reprocessing, since the transition lines 4 do not have to be stripped and recoated.
  • the use of a refractory lining 7 further reduces the cooling requirement of the metal components 4 and 5 of the can combustor system 1. Compared to can combustor systems without a ceramic lining, the cooling air requirement can be reduced by up to 50% according to current calculations, which results in an increase in the output of the gas turbine system 3.

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

Claims (7)

  1. Système (1) de chambre de combustion à tubes pour une installation (3) de turbine à gaz ayant plusieurs lignes (4) de passage disposées annulairement,
    qui sont conçues,
    pour être raccordées respectivement à un brûleur (10) par leur extrémité du côté en amont et pour envoyer à une turbine (2) du gaz chaud produit par le brûleur (10),
    dans lequel le système (1) de chambre de combustion à tubes a un répartiteur (5) de gaz chaud, qui est conçu pour le raccordement à la turbine (2) et qui définit un conduit (6) annulaire ouvert vers la turbine (2), dans lequel débouchent les extrémités en aval des lignes (4) de passage,
    dans lequel la section transversale de chaque ligne (4) de passage se rétrécit coniquement dans le sens vers l'aval,
    dans lequel les lignes (4) de passage et le répartiteur (5) de gaz chaud sont en métal et sont pourvus à l'intérieur d'un garnissage (7) réfractaire, notamment d'un garnissage céramique,
    dans lequel
    le garnissage (7) réfractaire de la ligne de passage a au moins une partie de garnissage annulaire ayant un diamètre extérieur, qui se rétrécit coniquement dans la direction vers l'aval,
    et
    dans lequel les lignes (4) de passage et le répartiteur (5) de gaz sont en métal et sont pourvus à l'intérieur d'un garnissage (7) réfractaire,
    notamment d'un garnissage céramique,
    caractérisé en ce que
    la partie de garnissage est maintenue sur la ligne (4) de passage avec une précontrainte radiale et axiale.
  2. Système (1) de chambre de combustion à tubes suivant la revendication 1,
    caractérisé en ce que
    la au moins une partie de garnissage annulaire est formée par un seul élément (7a) de garnissage.
  3. Système (1) de chambre de combustion à tubes suivant la revendication 1,
    caractérisé en ce qu'
    au moins une partie de garnissage annulaire est formée par plusieurs éléments de garnissage en forme de segments d'anneau, qui sont bloqués les uns par rapport aux autres dans la direction périphérique.
  4. Système (1) de chambre de combustion à tubes suivant l'une des revendications 1 à 3,
    caractérisé en ce que
    le garnissage (7) réfractaire du répartiteur (5) de gaz chaud a une pluralité d'éléments (7b) de garnissage, qui sont fixés sous précontrainte radiale aux surfaces intérieure et extérieure radialement du répartiteur (5) de gaz chaud.
  5. Système (1) de chambre de combustion à tubes suivant l'une des revendications 1 à 4,
    caractérisé en ce que
    les lignes (4) de passage et le répartiteur (5) de gaz chaud sont en un matériau métallique très résistant à la chaleur, notamment en un matériau métallique très résistant à la chaleur à paroi mince à la manière d'une tôle.
  6. Système (1) de chambre de combustion à tubes suivant l'une des revendications 1 à 5,
    caractérisé en ce que
    la face périphérique extérieure et/ou la face périphérique intérieure du répartiteur (5) de gaz chaud est/sont pourvues d'une bride (9) de fixation, qui est conçue pour la fixation à la turbine (2) .
  7. Installation (3) de turbine à gaz ayant plusieurs brûleurs (10) disposés de manière annulaire, une turbine (2) et un système (1) de chambre de combustion à tubes suivant l'une des revendications précédentes, qui relie le brûleur (10) à la turbine (2) .
EP20711063.6A 2019-04-01 2020-03-03 Système de chambre de combustion à tubes et installation de turbine à gaz pourvue d'un tel système de chambre de combustion à tubes Active EP3921577B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE102019204544.8A DE102019204544A1 (de) 2019-04-01 2019-04-01 Rohrbrennkammersystem und Gasturbinenanlage mit einem solchen Rohrbrennkammersystem
PCT/EP2020/055501 WO2020200609A1 (fr) 2019-04-01 2020-03-03 Système de chambre de combustion à tubes et installation de turbine à gaz pourvue d'un tel système de chambre de combustion à tubes

Publications (2)

Publication Number Publication Date
EP3921577A1 EP3921577A1 (fr) 2021-12-15
EP3921577B1 true EP3921577B1 (fr) 2023-07-05

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EP20711063.6A Active EP3921577B1 (fr) 2019-04-01 2020-03-03 Système de chambre de combustion à tubes et installation de turbine à gaz pourvue d'un tel système de chambre de combustion à tubes

Country Status (4)

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US (1) US11852344B2 (fr)
EP (1) EP3921577B1 (fr)
DE (1) DE102019204544A1 (fr)
WO (1) WO2020200609A1 (fr)

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* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE102019204544A1 (de) * 2019-04-01 2020-10-01 Siemens Aktiengesellschaft Rohrbrennkammersystem und Gasturbinenanlage mit einem solchen Rohrbrennkammersystem

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Also Published As

Publication number Publication date
EP3921577A1 (fr) 2021-12-15
DE102019204544A1 (de) 2020-10-01
WO2020200609A1 (fr) 2020-10-08
US20220186928A1 (en) 2022-06-16
US11852344B2 (en) 2023-12-26

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