EP3760925A1 - Amortisseur pour ensemble de chambre de combustion d'un ensemble de turbine à gaz, ensemble de chambre de combustion comportant ledit amortisseur et procédé de fabrication d'un amortisseur pour un ensemble de chambre de combustion - Google Patents

Amortisseur pour ensemble de chambre de combustion d'un ensemble de turbine à gaz, ensemble de chambre de combustion comportant ledit amortisseur et procédé de fabrication d'un amortisseur pour un ensemble de chambre de combustion Download PDF

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Publication number
EP3760925A1
EP3760925A1 EP19183732.7A EP19183732A EP3760925A1 EP 3760925 A1 EP3760925 A1 EP 3760925A1 EP 19183732 A EP19183732 A EP 19183732A EP 3760925 A1 EP3760925 A1 EP 3760925A1
Authority
EP
European Patent Office
Prior art keywords
damping
damper
openings
axial length
volumes
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.)
Pending
Application number
EP19183732.7A
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German (de)
English (en)
Inventor
Frédéric BOUDY
Mirko Ruben Bothien
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.)
Ansaldo Energia Switzerland AG
Original Assignee
Ansaldo Energia Switzerland 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 Ansaldo Energia Switzerland AG filed Critical Ansaldo Energia Switzerland AG
Priority to EP19183732.7A priority Critical patent/EP3760925A1/fr
Priority to CN202010619065.XA priority patent/CN112178695A/zh
Publication of EP3760925A1 publication Critical patent/EP3760925A1/fr
Pending 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
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23M—CASINGS, LININGS, WALLS OR DOORS SPECIALLY ADAPTED FOR COMBUSTION CHAMBERS, e.g. FIREBRIDGES; DEVICES FOR DEFLECTING AIR, FLAMES OR COMBUSTION PRODUCTS IN COMBUSTION CHAMBERS; SAFETY ARRANGEMENTS SPECIALLY ADAPTED FOR COMBUSTION APPARATUS; DETAILS OF COMBUSTION CHAMBERS, NOT OTHERWISE PROVIDED FOR
    • F23M20/00—Details of combustion chambers, not otherwise provided for, e.g. means for storing heat from flames
    • F23M20/005—Noise absorbing means
    • 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
    • F23R3/04—Air inlet arrangements
    • 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
    • F23R2900/00014—Reducing thermo-acoustic vibrations by passive means, e.g. by Helmholtz resonators

Definitions

  • the present invention relates to a damper for a combustor assembly of a gas turbine assembly and to a combustor assembly of a gas turbine comprising said damper.
  • the present invention relates to a damper for a sequential combustor assembly.
  • the present invention relates also to a method for manufacturing a damper for a combustor assembly.
  • a gas turbine power plant comprises a compressor, a combustor assembly and a turbine.
  • the compressor is supplied with air and comprises a plurality of blades compressing the supplied air.
  • the compressed air leaving the compressor flows into a plenum, i.e. a closed volume delimited by an outer casing, and from there into the combustor assembly.
  • a plenum i.e. a closed volume delimited by an outer casing
  • the compressed air and at least one fuel are combusted.
  • the resulting hot gas leaves the combustor assembly and is expanded in the turbine performing work.
  • sequential combustor assemblies can be used.
  • a sequential combustor assembly comprises two combustors in series: a first-stage combustor and a second-stage combustor, which is arranged downstream the first-stage combustor along the gas flow.
  • a combustor assembly with a single combustion stage can be also used.
  • Known dampers comprise one damper volume that acts as a resonator volume and a neck fluidly connecting the damper volume to at least one inner chamber of the combustor assembly.
  • dampers are not sufficiently flexible and are not able to damp broad frequency ranges.
  • the object of the present invention is therefore to provide a damper for a combustor assembly, which is flexible, simple and economical, both from the functional and the constructive point of view.
  • a damper for a combustor assembly of a gas turbine assembly comprising:
  • the structure of the damper according to the invention is flexible and can be also compact.
  • the flexibility is given by the possibility of damping different frequencies, as the damping volumes can be sized opportunely depending on the needs.
  • At least one of the damping bodies comprises at least one inlet configured to be in fluidic communication with at least one source of air.
  • air contributes to cool damper bodies and avoid hot gas ingestion, which would de-tune damper bodies and could cause damages to damper bodies.
  • the at least two damping volumes are interconnected in parallel.
  • the at least two damping volumes are interconnected in series.
  • At least one of the damping volumes is a quarter wave tube.
  • At least one of the damping volumes is a Helmholtz resonator.
  • the damper comprises a first damping body extending along an extension axis and having a first axial length and a second damping body extending along an extension axis and having a second axial length; the ratio between the greater axial length between the first axial length and the second axial length and the smaller between the first axial length and the second axial lengths being substantially integer, preferably even.
  • the present invention relates to a combustor assembly according to claim 9.
  • reference numeral 1 indicates a gas turbine assembly.
  • the gas turbine assembly 1 comprises a compressor 2, a sequential combustor assembly 3 and a turbine 5.
  • the compressor 2 and the turbine 5 extend along a main axis A.
  • an airflow compressed in the compressor 2 is mixed with fuel and is burned in the sequential combustor assembly 3.
  • the burned mixture is then expanded in the turbine 5 and converted in mechanical power by a shaft 6, which is connected to an alternator (not shown).
  • the sequential combustor assembly 3 comprises a first-stage combustor 8 and a second-stage combustor 9 sequentially arranged along the gas flow direction G.
  • the second stage combustor 9 is arranged downstream the first stage combustor 8 along the gas flow direction G.
  • a mixer 11 is arranged between the first stage combustor 8 and the second stage combustor 9 .
  • the first stage combustor 8 defines a first combustion chamber 14, the second stage combustor 9 defines a second combustion chamber 16, while the mixer 11 defines a mixing chamber 17.
  • the first combustion chamber 14, the second combustion chamber 16 and the mixing chamber 17 are in fluidic communication and are defined by a liner 18 (see figure 2 wherein the liner 18 is partially visible), which extends along a longitudinal axis B.
  • a supply assembly 20 is arranged in the second combustion chamber 16 of the second stage combustor 9 .
  • the supply assembly 20 comprises a central body 21 provided with a plurality of fingers 22 (schematically represented also in figure 3 ).
  • the fingers 22 are preferably defined by streamlined bodies, each of which is provided with a plurality of nozzles 24 and is supplied with air and at least one fuel.
  • the second stage combustor 9 comprises at least one damper 30.
  • the second stage combustor 9 comprises a plurality of dampers 30 (in the example here illustrated the dampers are sixteen). Using more than one damper 30 gives the possibility to increase the damping amplitude.
  • the dampers 30 are arranged about the central body 21 of the supply assembly 20. More preferably, the dampers 30 are evenly distributed about the central body 21.
  • the dampers 30 are preferably coupled to a panel 26 surrounding the central body 21 of the supply assembly 20.
  • the panel 26 is also provided with a plurality of cooling holes 25 evenly distributed along the panel 26.
  • damper 30 can be arranged also in another portion of the combustor assembly 3.
  • damper 30 can be coupled to the liner 18, preferably to the portion of the liner 18 facing the second combustion chamber 16. Damper 30 can also be arranged so as to face into the first combustion chamber 14.
  • the damper 30 extends along an extension axis C and comprises a first damper body 31 having a first cavity defining a first damping volume 32, a second damper body 34 having a second cavity defining a second damping volume 35, a perforated connecting plate 36 connecting the first damping volume 32 and the second damping volume 35 and at least one perforated end plate 38.
  • the perforated end plate 38 is configured to connect the first damping volume 32 with the outside of the damper 30 which is in fluidic communication with the first combustion chambers 14 and/or the second combustion chamber 16 of the combustor assembly 3.
  • the first damping volume 32 and the second damping volume 35 are interconnected in fluidic communication by the perforated connecting plate 36.
  • first damping volume 32 and the second damping volume 35 are interconnected in series.
  • the first damping volume 32 and the second damping volume 35 are interconnected in parallel.
  • the second damper body 34 is provided with at least one inlet 40 configured to be in fluidic communication with at least one source of air.
  • the inlet 40 is connected to a plenum (not visible in the attached figures) receiving air from the compressor 2.
  • the second damper body 34 is provided with two or more inlets 40 arranged at the bottom of the second cavity.
  • the air enters through the inlets 40, flows into the second damping volume 35, passes through the perforated connecting plate 36, flows into the first damping volume 32 and exits through the perforated end plate 38 into the first combustion chambers 14 and/or the second combustion chamber 16 of the combustor assembly 3.
  • the air contributes to cool the first damper body 31 and the second damper body 34 and avoid hot gas ingestion, which would de-tune the first damper body 31 and the second damper body 34 and could cause damages to the first damping body 31 and the second damper body 34.
  • the inlets 40 are arranged on opposite sides of the second damper body 34.
  • the perforated connecting plate 36 and the perforated end plate 38 have a similar structure. Both the perforated connecting plate 36 and the perforated end plate 38 are provided with a plurality of openings 42.
  • the openings 42 have a circular shape.
  • shape of the openings can be different, for example polygonal or oval or oblong, etc.
  • the perforated connecting plate 36 and the perforated end plate 38 are both designed so as to operate in a low Strouhal regime.
  • the Strouhal regime is defined by the value of the Strouhal number.
  • the openings 42 of the perforated connecting plate 36 and of the perforated end plate 38 are dimensioned according to the following condition: ⁇ ⁇ RH / Ub ⁇ 0 , 5 wherein
  • the perforated end plate 38 faces directly the first combustion chambers 14 and/or the second combustion chamber 16 and therefore is designed to resist to high temperatures. Thickness and material of the perforated end plate 38 are therefore chosen to guarantee high reliability.
  • the perforated connecting plate 36 is subjected to high temperatures too although in a lesser way than the perforated end plate 38.
  • the perforated connecting plate 36 and the perforated end plate 38 are made of the same material.
  • the perforated connecting plate 36 and the perforated end plate 38 are made with a high temperature resistant material, for example a superalloy as Hastelloy X.
  • the perforated connecting plate 36 and the perforated end plate 38 have a different thickness.
  • the perforated end plate 38 is preferably thicker than perforated connecting plate 36 as facing the combustion chamber.
  • the openings 42 are substantially arranged according to a cross mesh pattern.
  • the openings 42 can be substantially arranged according to a square mesh pattern or according to a rectangular mesh pattern or other patterns.
  • the mesh pattern of the perforated connecting plate 36 is identical to the mesh pattern of the perforated end plate 38. In this way the openings 42 of the perforated connecting plate 36 are aligned with the openings 42 of the perforated end plate 38.
  • the mesh pattern of the perforated connecting plate 36 and of the perforated end plate 38 can be different from each other and the openings 42 of the perforated connecting plate 36 can be misaligned with the openings 42 of the perforated end plate 38.
  • Such a solution is useful when the distance between the perforated connecting plate 36 and the perforated end plate 38 is lower than a threshold.
  • the openings 42 of the perforated connecting plate 36 are misaligned with openings 42 of the perforated end plate 38 when the length L1 of the first cavity is lower than a threshold.
  • the openings 42 of the perforated connecting plate 36 and of the perforated end plate 38 are arranged so as to extend perpendicularly to the plane a 1 a 2 along which the respective perforated connecting plate 36 or the perforated end plate 38 extends.
  • the first cavity of the first damper body 31 and the second cavity of the second damper body 34 are dimensioned so as to give to the damper 30 a desired damping effect.
  • the first cavity of the first damper body 31 and the second cavity of the second damper body 34 are cylindrical. According to variants not shown, the first cavity of the first damper body 31 and the second cavity of the second damper body 34 can be also prismatic or can have a shape adjusted on the basis of the space available in the combustor assembly 3.
  • the first cavity of the first damper body 31 and of the second cavity of the second damper body 34 are designed so as to be a quarter wave tube.
  • the dimensioning can be made according to a derivation of the above quarter wave tube formula.
  • first cavity of the first damper body 31 and of the second cavity of the second damper body 34 are designed so as to be a Helmholtz resonator.
  • the dimensioning can be made according to a derivation of the above Helmholtz formula.
  • the dimensioning is preferably made with the quarter wave formula as it is independent from the features of the respective perforated plates.
  • the dimensioning is made using the Helmholtz formula.
  • the first cavity of the first damper body 31 is dimensioned to damp a first frequency while the second cavity of the second damper body 34 is dimensioned to damp a second frequency different from the first frequency.
  • the damper 30 so dimensioned and designed is able to dampen a broad band of frequencies.
  • the damper 30, in fact, is able to damp at least three frequencies: the one depending from the dimensions of the first cavity, the one depending from the dimensions of the second cavity and the one depending from the dimensions of the first cavity plus the second cavity.
  • the reflection coefficient in fact, is mainly driven by the eigenmode of the two cavities together (i.e. L2+L1), while the response is modulated by the dimensions of each cavity L1 and L2.
  • the ratio is defined as "substantially integer”.
  • the trends shown in figure 5 are relating to values of the lengths L1 and L2, which are inverted.
  • dotted line represents a solution wherein L2>L1
  • continuous line represents a solution wherein the same lengths are inverted (i.e. L2 ⁇ L1).
  • the concordance of modes is between the eigenmode of the first cavity L1 and of the second cavity L2.
  • the damping and the reflection coefficient is mainly driven by the eigenmode of the 2 cavities together (i.e. L2+L1), it is when the eigenmode of the first cavity or of the second cavity has the same frequency as the eigenmode of the two cavities together (i.e. L2+L1) that the damping gets the best increase.

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  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Soundproofing, Sound Blocking, And Sound Damping (AREA)
EP19183732.7A 2019-07-01 2019-07-01 Amortisseur pour ensemble de chambre de combustion d'un ensemble de turbine à gaz, ensemble de chambre de combustion comportant ledit amortisseur et procédé de fabrication d'un amortisseur pour un ensemble de chambre de combustion Pending EP3760925A1 (fr)

Priority Applications (2)

Application Number Priority Date Filing Date Title
EP19183732.7A EP3760925A1 (fr) 2019-07-01 2019-07-01 Amortisseur pour ensemble de chambre de combustion d'un ensemble de turbine à gaz, ensemble de chambre de combustion comportant ledit amortisseur et procédé de fabrication d'un amortisseur pour un ensemble de chambre de combustion
CN202010619065.XA CN112178695A (zh) 2019-07-01 2020-07-01 阻尼器、包括阻尼器的燃烧器组件及制造阻尼器的方法

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP19183732.7A EP3760925A1 (fr) 2019-07-01 2019-07-01 Amortisseur pour ensemble de chambre de combustion d'un ensemble de turbine à gaz, ensemble de chambre de combustion comportant ledit amortisseur et procédé de fabrication d'un amortisseur pour un ensemble de chambre de combustion

Publications (1)

Publication Number Publication Date
EP3760925A1 true EP3760925A1 (fr) 2021-01-06

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Application Number Title Priority Date Filing Date
EP19183732.7A Pending EP3760925A1 (fr) 2019-07-01 2019-07-01 Amortisseur pour ensemble de chambre de combustion d'un ensemble de turbine à gaz, ensemble de chambre de combustion comportant ledit amortisseur et procédé de fabrication d'un amortisseur pour un ensemble de chambre de combustion

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EP (1) EP3760925A1 (fr)
CN (1) CN112178695A (fr)

Families Citing this family (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN115682033A (zh) * 2021-07-28 2023-02-03 北京航空航天大学 防振燃烧室以及燃烧室防振方法

Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE19640980A1 (de) * 1996-10-04 1998-04-16 Asea Brown Boveri Vorrichtung zur Dämpfung von thermoakustischen Schwingungen in einer Brennkammer
US20110179795A1 (en) * 2009-07-08 2011-07-28 General Electric Company Injector with integrated resonator
EP2397759A1 (fr) * 2010-06-16 2011-12-21 Alstom Technology Ltd Agencement d'amortisseur
US20150159870A1 (en) * 2010-05-03 2015-06-11 Alstom Technology Ltd Combustion device for a gas turbine
US20180313540A1 (en) * 2017-05-01 2018-11-01 General Electric Company Acoustic Damper for Gas Turbine Engine Combustors

Family Cites Families (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE2728778B2 (de) * 1977-06-25 1979-08-30 Bayer Ag, 5090 Leverkusen Verfahren zur Geräuschminderung bei der Drosselung von Dampf- und Gasstromen
JP4592513B2 (ja) * 2004-09-30 2010-12-01 三菱重工業株式会社 ガスタービン制御装置、及びガスタービンシステム
US20120180500A1 (en) * 2011-01-13 2012-07-19 General Electric Company System for damping vibration in a gas turbine engine
EP2831504B1 (fr) * 2012-03-30 2018-12-26 Ansaldo Energia IP UK Limited Segments d'étanchéité de chambre de combustion équipés de dispositifs d'amortissement
US10088165B2 (en) * 2015-04-07 2018-10-02 General Electric Company System and method for tuning resonators
EP2860451A1 (fr) * 2013-10-11 2015-04-15 Alstom Technology Ltd Chambre de combustion d'une turbine à gaz avec amortissement acoustique amélioré
EP3153777B1 (fr) * 2015-10-05 2021-03-03 Ansaldo Energia Switzerland AG Ensemble amortisseur pour une chambre de combustion

Patent Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE19640980A1 (de) * 1996-10-04 1998-04-16 Asea Brown Boveri Vorrichtung zur Dämpfung von thermoakustischen Schwingungen in einer Brennkammer
US20110179795A1 (en) * 2009-07-08 2011-07-28 General Electric Company Injector with integrated resonator
US20150159870A1 (en) * 2010-05-03 2015-06-11 Alstom Technology Ltd Combustion device for a gas turbine
EP2397759A1 (fr) * 2010-06-16 2011-12-21 Alstom Technology Ltd Agencement d'amortisseur
US20180313540A1 (en) * 2017-05-01 2018-11-01 General Electric Company Acoustic Damper for Gas Turbine Engine Combustors

Also Published As

Publication number Publication date
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