EP2865948A1 - Dispositif d'amortissement type quart d'onde pour chambre de combustion d'une turbine à gaz - Google Patents

Dispositif d'amortissement type quart d'onde pour chambre de combustion d'une turbine à gaz Download PDF

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Publication number
EP2865948A1
EP2865948A1 EP20140190194 EP14190194A EP2865948A1 EP 2865948 A1 EP2865948 A1 EP 2865948A1 EP 20140190194 EP20140190194 EP 20140190194 EP 14190194 A EP14190194 A EP 14190194A EP 2865948 A1 EP2865948 A1 EP 2865948A1
Authority
EP
European Patent Office
Prior art keywords
combustor
damping device
casing
quarter wave
damper
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.)
Granted
Application number
EP20140190194
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German (de)
English (en)
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EP2865948B1 (fr
Inventor
Devis Tonon
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
Alstom Technology AG
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Publication date
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Priority to EP14190194.2A priority Critical patent/EP2865948B1/fr
Publication of EP2865948A1 publication Critical patent/EP2865948A1/fr
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    • 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
    • F23R3/02—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • 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
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01N—GAS-FLOW SILENCERS OR EXHAUST APPARATUS FOR MACHINES OR ENGINES IN GENERAL; GAS-FLOW SILENCERS OR EXHAUST APPARATUS FOR INTERNAL COMBUSTION ENGINES
    • F01N1/00—Silencing apparatus characterised by method of silencing
    • F01N1/02—Silencing apparatus characterised by method of silencing by using resonance
    • F01N1/023—Helmholtz resonators
    • 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 damping device for a combustor of a gas turbine. More specifically, the invention relates to a design of a broadband damping device for a low emission combustor having at least one resonator for damping pressure fluctuations in the combustion chamber.
  • Gas turbines are known to comprise at least one combustor, wherein a fuel and air are combusted to generate high pressure hot combustion gases that are expanded in a turbine performing work.
  • the combustion may occur either in a number of combustors circumferentially positioned around a longitudinal axis of the gas turbine or in an annular combustion chamber with a number of burners at its upstream end.
  • gas turbine combustors are usually provided with damping devices, in particular Helmholtz resonators, to damp pressure oscillations.
  • Helmholtz resonators are widely used in this technical field. Their use is disclosed in many prior art publications. Usually a plurality of resonators is coupled to the combustor at its upstream end and/or downstream at its liner in flow communication with the interior of the combustor.
  • Helmholtz resonators require a relatively high volume, but the available space in the region surrounding the combustor is often limited. A consequence are design constraints to install such damping devices. Another significant design consideration is the component weight, Helmholtz resonators are relatively heavy.
  • EP 2402658 discloses a combustor with lean combustion and low emissions for a gas turbine that requires a small mounting space for an acoustic damper that can achieve size reduction.
  • the combustor comprises an acoustic damper that includes an acoustic damper resonance space communicating with the inner combustion chamber.
  • the acoustic damper is provided along a combustor housing extending in a direction intersecting an axial direction of the combustor.
  • the acoustic damping device is disposed widely in the circumferential direction, without concentrating in a particular section of the combustor in its circumferential direction. As a result, the damping device is prevented from protruding toward the outer circumference of the housing, and the space needed outside the combustor can be reduced.
  • a different approach for damping pressure oscillations caused by combustion dynamics is the application of quarter wave dampers.
  • a quarter wave damper includes a resonator tube of a defined length L.
  • a quarter wave damper is tuned to a quarter of the wavelength of an acoustical oscillation.
  • a quarter wavelength damper may absorb a frequency corresponding to a wavelength four times the tube length L.
  • Fig. 1 shows in a rough schematic manner the main features of a quarter wave damper 2 connected to a combustor or a supply line for fuel or air to a combustion chamber.
  • the damper 2 includes a casing 3, usually designed as a tube, fixed to the combustor liner 4 or the fuel or air supply line, the tube 3 having a length 5 and defining a resonator volume 6. Via an opening 7 at its front face the resonator volume 6 is in flow communication with the combustion chamber 8 in which the pressure oscillations, to be damped, may occur.
  • the damper parameter that mainly defines the damped frequency is the tube length 5. Consequently, these geometrical features have to be determined in accordance with the combustion dynamics of the combustor.
  • the frequency of pressure oscillations may slightly change from gas turbine to gas turbine and, in addition, also for the same gas turbine it may slightly change as a function of variations of the operating conditions (for example part load, base load, transition). If narrow band dampers are adopted, each of these frequency shifts will result in a rise of pulsations.
  • this aim is achieved by a damping device according to claim 1.
  • this aim is achieved by a combustor according to claim 15.
  • a damping device particularly a quarter wave damper with a modified new design
  • the damping device comprising a casing, particularly a tubular casing, defining a resonator volume, a hole at a front face of this casing for allowing fluid communication between the resonator volume and the combustion chamber, a rear face with at least one feed hole for feeding a purging fluid into the resonator volume and at least one lateral surface, whereby this lateral surface is equipped with one or more side cavities inside.
  • the feeding hole at the rear face and the hole at the front face define a flow path across the resonator volume inside the quarter wave damper.
  • the at least one side cavity is groove-shaped and runs circumferentially around the lateral surface of the casing.
  • the lateral surface of the damper casing is equipped with two or more circumferential cavities, arranged in a number of rows along the casing between its rear end and its front end.
  • This design is preferably applicable for quarter wave dampers with a circular cross section.
  • the provision of side cavities is limited to one side.
  • a first lateral surface of the e.g. rectangular damper is equipped with a number of consecutively arranged side cavities, whereas a second lateral surface, e.g. the opposite surface, is even.
  • the side cavities extend over the whole width of the said first lateral surface.
  • a mass flow of a purging fluid passes the resonator volume from the feed opening at the rear face towards the front face and exits the resonator volume through the opening there into the combustion chamber.
  • the side cavities in the lateral surface arranged orthogonally or at least essentially orthogonally to the mass flow of the purging fluid, cause flow disturbances. Vortical flows are initiated at each cavity.
  • the formed shear layers roll up, thereby interacting with existing and new shear layers and vortices in a complex interaction.
  • One parameter for controlling the damping quality of a certain damper configuration is the flow velocity of the mass flow of purging fluid through the resonator volume.
  • the damping quality of the damper during operation can be changed by varying the flow velocity.
  • Fig. 1 shows in a rough schematic manner the main features of a quarter wave damper 2 coupled to the liner 4 of a combustor 1 or a supply line of the fluid injection system according to the state of the art.
  • the quarter wave damper 2 includes a casing 3, usually designed as a tube, fixed to the combustor liner 4.
  • the distance between the front face with opening 7 and the rear end face 11 defines the length 5 of the quarter wave damper 2.
  • the damper parameter that mainly defines the damped frequency is its length 5. Consequently, these geometrical features have to be determined in accordance with the combustion dynamics of the combustor.
  • the quarter wave damper 2 is tuned to a quarter of the wavelength of the relevant acoustical oscillations in the combustion chamber 8.
  • Fig. 2 shows in a similar view a damping device with a modified quarter wave damper 2 in accordance with the invention.
  • the combustion chamber 8 is enclosed by the liner 4 of the combustor 1.
  • the modified quarter wave damper 2 is coupled to said liner 4 in a manner, known per se.
  • the quarter wave damper 2 comprises an essentially cylindrical casing 3 with an opening 7 at its front face, a lateral surface 14 and a rear end 11.
  • the opening 7 at the front face enables flow communication between the combustion chamber 8 and the resonator volume 6 inside the casing 3.
  • the lateral surface 14 of the casing 3 is equipped with at least one cavity 9. This cavity 9 may run circumferentially around the inner lateral surface 14. As shown in Fig. 2 , a number of rows of circumferentially running cavities 9 may be arranged along the lateral surface between the front end and the rear end of the casing 3.
  • the rear end 11 of the damper 2 is equipped with an opening 10 for feeding a purging fluid, usually air, into the resonator volume 6.
  • a purging fluid usually air
  • a mass flow 12 of purging air is flowing through the resonator volume 6 from the opening 10 at the rear face 11 towards the front face and exits the resonator volume 6 through the opening 7 into the combustion chamber 8.
  • the groove-shaped cavities 9 in the lateral surface 14 cause flow disturbances, as shown in Fig. 2a .
  • vortical flows 13 are initiated at each cavity 9.
  • the shear layers, formed in the velocity-gradient region, roll up into a spiral, thereby interacting with existing and new shear layers and vortices in a complex interaction. As a consequence these energy dissipating processes absorb acoustic power.
  • Figures 3a and 3b show in an exemplary manner different geometrical options of a modified quarter wave damper 2 according to the invention.
  • Fig. 3a depicts a corrugated damper 2. At least one lateral surface 14 of the casing 3 is provided with a corrugated design. Preferably the cross section of a quarter wave damper 2 according to this design is circular. In this case the casing 3 is made of a corrugated tube from a suitable material.
  • a rectangular cross section can be provided.
  • two opposite lateral surfaces 14 are provided with a corrugated design.
  • the corrugation is disposed orthogonally to the direction of the mass flow 12 of purging air.
  • a respective vortice flow is formed at each cavity 9.
  • Fig. 3b depicts an alternative embodiment, a side branched quarter wave damper.
  • the provision of side cavities 9 is limited to one of the longitudinal sides. This design may preferably be used for dampers 2 with a rectangular cross section.
  • One lateral surface 14' of the rectangular damper is equipped with a number of consecutively arranged side cavities 9, whereas the opposite surface 14" is even.
  • the side cavities 9 extend over the whole width of the surface 14'.
  • the figures 4a and 4b show in a rough schematic manner two basic options regarding the application of a damping device according to the invention to a can combustor of a gas turbine.
  • the quarter wave dampers 2 For the purpose of reducing the required space outside the combustor 1 the quarter wave dampers 2 have to be prevented from protruding toward the outer circumference of the combustor 1.
  • the two basic options comprise an arrangement around the combustion chamber in circumferential direction or in longitudinal direction.
  • a number of quarter wave dampers 2 is folded around the combustor 1 of the gas turbine. This means, the longitudinal axis 15 of the applied dampers 2 is arranged parallel or essentially parallel to the outer surface of the liner 4.
  • the longitudinal axis 15 of the dampers 2 is in line with the circumferential direction of the combustor 1.
  • a number of dampers 2 is coupled to the liner 4 in different axial positions of the combustor 1.
  • the longitudinal axis of the dampers 2 is in line with the longitudinal axis of the combustor 1.
  • a number of dampers 2 is coupled to the liner around the circumference of the combustor at essentially the same axial position.
  • both options offer the possibility of applying quarter wave dampers 2 of different lengths to damp more than one dominant frequency.

Landscapes

  • 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)
EP14190194.2A 2013-10-25 2014-10-24 Chambre de combustion de turbine à gaz avec amortisseur type quart d'onde Active EP2865948B1 (fr)

Priority Applications (1)

Application Number Priority Date Filing Date Title
EP14190194.2A EP2865948B1 (fr) 2013-10-25 2014-10-24 Chambre de combustion de turbine à gaz avec amortisseur type quart d'onde

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
EP13190333 2013-10-25
EP14190194.2A EP2865948B1 (fr) 2013-10-25 2014-10-24 Chambre de combustion de turbine à gaz avec amortisseur type quart d'onde

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EP2865948A1 true EP2865948A1 (fr) 2015-04-29
EP2865948B1 EP2865948B1 (fr) 2018-04-11

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US (1) US20150113991A1 (fr)
EP (1) EP2865948B1 (fr)
CN (1) CN104676646B (fr)

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2963345B1 (fr) * 2014-06-30 2018-09-19 Ansaldo Energia Switzerland AG Amortisseur pour turbine à gaz
WO2019027508A1 (fr) * 2017-02-03 2019-02-07 Siemens Aktiengesellschaft Doublure de chambre de combustion à atténuation de bruit pour moteur à turbine à combustion
US11506382B2 (en) 2019-09-12 2022-11-22 General Electric Company System and method for acoustic dampers with multiple volumes in a combustion chamber front panel

Families Citing this family (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US10197275B2 (en) * 2016-05-03 2019-02-05 General Electric Company High frequency acoustic damper for combustor liners
US10221769B2 (en) 2016-12-02 2019-03-05 General Electric Company System and apparatus for gas turbine combustor inner cap and extended resonating tubes
US10228138B2 (en) 2016-12-02 2019-03-12 General Electric Company System and apparatus for gas turbine combustor inner cap and resonating tubes
US10220474B2 (en) 2016-12-02 2019-03-05 General Electricd Company Method and apparatus for gas turbine combustor inner cap and high frequency acoustic dampers
US10808874B2 (en) 2017-11-30 2020-10-20 General Electric Company Inline fluid damper device
US20220282688A1 (en) * 2021-03-08 2022-09-08 Raytheon Company Attenuators for combustion noise in dual mode ramjets and scramjets
CN114993684B (zh) * 2022-05-30 2023-03-24 浙江大学 一种环形燃烧室振荡抑制试验装置
CN116697181B (zh) * 2023-08-02 2023-10-10 中国航发沈阳发动机研究所 一种管路抑振结构

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JPH04246221A (ja) * 1991-01-31 1992-09-02 Toyoda Gosei Co Ltd 消音装置
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EP2402658A1 (fr) 2009-02-27 2012-01-04 Mitsubishi Heavy Industries, Ltd. Chambre de combustion et turbine à gaz équipée de ladite chambre de combustion

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US8966903B2 (en) * 2011-08-17 2015-03-03 General Electric Company Combustor resonator with non-uniform resonator passages
EP2602549A1 (fr) * 2011-12-09 2013-06-12 Siemens Aktiengesellschaft Chambre de combustion pour une turbine à gaz, turbine à gaz ainsi que procédé
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Patent Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JPH04246221A (ja) * 1991-01-31 1992-09-02 Toyoda Gosei Co Ltd 消音装置
EP1775515A2 (fr) * 2005-10-14 2007-04-18 DLR Deutsches Zentrum für Luft- und Raumfahrt e.V. Dispositif résonant pour chambre de combustion, chambre de combustion et procédé pour ajuster les caractéristiques acoustiques d'une chambre de combustion
DE102006053277A1 (de) * 2006-11-03 2008-05-08 Deutsches Zentrum für Luft- und Raumfahrt e.V. Resonatorvorrichtung und Brennkammervorrichtung
EP2402658A1 (fr) 2009-02-27 2012-01-04 Mitsubishi Heavy Industries, Ltd. Chambre de combustion et turbine à gaz équipée de ladite chambre de combustion

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2963345B1 (fr) * 2014-06-30 2018-09-19 Ansaldo Energia Switzerland AG Amortisseur pour turbine à gaz
US10228134B2 (en) 2014-06-30 2019-03-12 Ansaldo Energia Switzerland AG Damper for gas turbine
WO2019027508A1 (fr) * 2017-02-03 2019-02-07 Siemens Aktiengesellschaft Doublure de chambre de combustion à atténuation de bruit pour moteur à turbine à combustion
US11506382B2 (en) 2019-09-12 2022-11-22 General Electric Company System and method for acoustic dampers with multiple volumes in a combustion chamber front panel

Also Published As

Publication number Publication date
US20150113991A1 (en) 2015-04-30
EP2865948B1 (fr) 2018-04-11
CN104676646B (zh) 2019-08-13
CN104676646A (zh) 2015-06-03

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