EP3029376B1 - Turbine à gaz avec un amortisseur Helmholtz - Google Patents

Turbine à gaz avec un amortisseur Helmholtz Download PDF

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Publication number
EP3029376B1
EP3029376B1 EP14195660.7A EP14195660A EP3029376B1 EP 3029376 B1 EP3029376 B1 EP 3029376B1 EP 14195660 A EP14195660 A EP 14195660A EP 3029376 B1 EP3029376 B1 EP 3029376B1
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EP
European Patent Office
Prior art keywords
damper
combustor
gas turbine
piston
helmholtz
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.)
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Application number
EP14195660.7A
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German (de)
English (en)
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EP3029376A1 (fr
Inventor
Mirko Ruben Bothien
Andre Theuer
Jost Imfeld
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Ansaldo Energia IP UK Ltd
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Ansaldo Energia IP UK Ltd
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Priority to EP14195660.7A priority Critical patent/EP3029376B1/fr
Priority to US14/934,277 priority patent/US20160153661A1/en
Priority to CN201510863130.2A priority patent/CN105650192B/zh
Publication of EP3029376A1 publication Critical patent/EP3029376A1/fr
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Publication of EP3029376B1 publication Critical patent/EP3029376B1/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
    • F23R3/002—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
    • F23R3/16—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration with devices inside the flame tube or the combustion chamber to influence the air or gas flow
    • 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
    • F23R2900/00013—Reducing thermo-acoustic vibrations by active 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
    • 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 the field of combustion technology. It refers to a gas turbine according to the preamble of claim 1.
  • Fig. 1 shows in a perspective view an exemplary stationary or industrial gas turbine of the GT13 E2 type.
  • the gas turbine 10 comprises in a casing 13 a rotor 12, which rotates around a machine axis and defines within the casing 13 an annular hot gas channel extending in axial direction through the machine.
  • a compressor 14 with several stages of running blades compresses air, which enters the machine through an air inlet 11.
  • the compressed air with a compressor outlet pressure pk2 fills a plenum and enters a combustor 15, where it is mixed with a fuel supplied by a plurality of burners 16.
  • the burners 16 are configured as so-called AEV (or Advanced Environmental Vortex) burners, which are described for example in document WO 2009/109454 .
  • Fig. 2 shows the main parameters of a generic Helmholtz damper configuration.
  • the Helmholtz damper 20 of Fig. 2 comprises a damper volume 21 with a volume V, which is in fluidic connection with a damped space (combustor) 19 via a neck tube 22 of length L N and inner diameter D N ; u denotes the bias mean flow.
  • the resonance frequency f of this damper can be approximately calculated by the formula: f ⁇ c 2 ⁇ A N V L N + d L N with the speed of sound c, and the area A N and length L N of neck tube 22.
  • the frequency of the pulsations within the combustor depends on the operation mode of the gas turbine. Especially, there is a change in pulsation frequency f P , when the gas turbine changes from part load operation to base load operation, and vice versa. For a gas turbine of the type shown in Fig. 1 there can be a change of up to 20% of pulsation frequency f P between part load and base load, with the pulsation frequency increasing with growing load.
  • the resonance frequency of the dampers should stay tuned to the pulsation frequency even if the load conditions of the gas turbine change.
  • the damper volume V should be changed in accordance with a change in the load conditions.
  • Document EP 2 397 761 A1 discloses a Helmholtz damper and a method for regulating the resonance frequency of a Helmholtz damper.
  • it refers to Helmholtz dampers to be connected to lean premixed, low emission combustion systems of gas turbines, whereby said Helmholtz damper comprises an enclosure from which a neck extends, and a pipe is inserted into and fits the neck.
  • an actuator is connected to the pipe to adjust its portion inserted into the neck.
  • Document EP 2 397 760 A1 discloses a damper arrangement that has a first Helmholtz damper connected in series to a second Helmholtz damper. The resonance frequency of the first Helmholtz damper and the resonance frequency of the second Helmholtz damper are shifted from one another in an amount producing a synergic damping effect.
  • Document DE 100 26 121 A1 describes an apparatus for damping acoustic vibrations in a combustor as well as a corresponding combustor arrangement with the apparatus.
  • the apparatus comprises a Helmholtz resonator that can be connected via a connecting channel with a combustor.
  • the Helmholtz resonator contains a hollow body the volume of which can be changed by adding or draining a fluid via a supply line, or is located adjacent to such a hollow body in such a way that the resonance volume of the Helmholtz resonator is changed when the volume of the hollow body is changed.
  • This apparatus makes it possible to adjust the resonance frequency of a Helmholtz resonator arranged inside a pressure container in accordance with the respective current operating point of the combustor to be damped, without having to pass movable components through the pressure container.
  • Document US 8,661,822 B2 discloses a system with a turbine engine, comprising: a compressor; a turbine; a combustor disposed downstream from the compressor and upstream from the turbine; a fluid injection system configured to inject one or more fluids into the combustor; a variable geometry resonator coupled to the fluid injection system; and a controller configured to tune the variable geometry resonator in response to feedback.
  • Document EP 1624250 A1 discloses a Helmholtz damper provided with a resonator neck through which gas can enter into the resonator chamber. Different damping means housed in the resonator are disclosed in order to improve damping characteristics.
  • the Helmholtz damper according to the invention which is especially suitable for damping pulsations in a combustor of a gas turbine, comprises a damper volume, which can be connected to a damped space by means of a neck tube, and further comprises a piston, which is moveable within said damper volume and divides said damper volume into a variable first part on one side of said piston, which variable first part is connected to said neck tube, and a correspondingly variable second part on the other side of said piston. It is characterized in that said piston is driven by a pressure drop between said first and second part of said damper volume and in that said second part of said damper volume is in fluidic connection with the outside of said damper volume.
  • An embodiment of the Helmholtz damper according to the invention is characterized in that the piston is held in an idle position, where the first part of said damper volume is a maximum, by means of a spring, and that said pressure drop drives said piston against the force of said spring.
  • said spring is arranged within said first part of said damper volume.
  • said spring may be arranged outside of said damper volume and acts on said piston via a piston rod, which extends from said piston to the outside of said damper volume.
  • said spring is a helical spring.
  • said damper volume is enclosed by a housing, and said fluidic connection is established by at least one opening in said housing.
  • the gas turbine according to the invention comprises a compressor, at least one combustor and a turbine, whereby said at least one combustor is enclosed by a combustor casing, the outside of which is exposed to the compressor outlet pressure of said compressor, whereby at least one Helmholtz damper is provided at and connected to one combustor in order to damp pulsations within said combustor.
  • said at least one Helmholtz damper is a Helmholtz damper according to the invention, and that a pressure drop between said compressor outlet pressure and the pressure within said combustor is used to drive said piston of said at least one Helmholtz damper.
  • An embodiment of the gas turbine according to the invention is characterized in that said at least one Helmholtz damper is attached to the combustor casing by adaptation means.
  • said at least one Helmholtz damper is connected to said combustor through a hole in said combustor casing, and said adaptation means comprises an insert, which fits into said hole and receives a neck tube of said at least one Helmholtz damper such that said neck tube passes through said insert to open out into said combustor.
  • a neck tube adapter is provided to seal said neck tube against said insert.
  • said neck tube is releasably connected to the damper volume of said at least one Helmholtz damper.
  • Another embodiment of the gas turbine according to the invention is characterized in that said combustor is of an annular configuration, and that a plurality of Helmholtz dampers are circumferentially arranged around said combustor.
  • Fig. 3 shows the results of measurements of the absolute pressure drop ⁇ p as a function of relative gas turbine load for an exemplary gas turbine.
  • the invention seeks to explore this fact in such a way that the volume V of the damper is reduced so that its resonance frequency is continuously adjusted in order to provide highest damping at the required frequency. This is possible due to the fact that the outside of the damper volume is exposed the compressor outlet pressure pk2, whereas the pressure inside the damper is very close to that of the combustion chamber.
  • Fig. 4 shows an embodiment of the Helmholtz damper according to the invention.
  • Fig. 4(a) shows the damper in a starting position with its damper volume being a maximum.
  • Fig. 4(b) shows the damper in an active position, wherein the damper volume has been automatically reduced due to an increased pressure drop ⁇ p between inside and outside of the damper.
  • the Helmholtz damper 24 according to Fig. 4 comprises damper volume 25, which is enclosed by a housing 25a.
  • the damper volume 25 is divided by means of a piston 27 which is moveable within said damper volume 25, into a variable first part V1 on one side of the piston 27, and a correspondingly variable second part V2 on the other side of said piston 27.
  • the variable first part V1 is connected to a neck tube 26 of said Helmholtz damper 24.
  • the variable second part V2 is connected to the outside of Helmholtz damper 24 by means of openings 31 provided in housing 25a.
  • An orifice 32 may be provided through piston 27 to allow the access of some cooling air.
  • FIG. 5 and 6 A more compact design of a Helmholtz damper according to the invention, which is more suitable for being applied to a gas turbine combustor 33, is shown in Fig. 5 and 6 .
  • Helmholtz damper 38 of Fig. 5 and 6 is attached to combustor casing 34 at a place, where the hot gas 39 is guided to combustor outlet 35.
  • Helmholtz damper 38 comprises a damper volume 40 enclosed by a housing 40a, and divided by a piston 44.
  • Housing 40a is on its upper side in fluidic connection with the environment (plenum pressure pk2) by means of a wide opening 46. At its lower side, it is closed by a bowl-like base element 41.
  • a separate neck tube 43 which extends from the combustion chamber into the interior of damper volume 40, connects the damper volume with the combustor.
  • Neck tube 43 is fixed in a neck tube adapter 42, which is held between base element 41 and an insert 37 that is used to mount the damper arrangement in a hole 36 in the combustor casing 34.
  • the neck tube 43 may be of any cross-sectional shape.
  • Piston 44 which has an orifice 47 for cooling purposes, is designed as a free piston.
  • a balancing helical spring 45 is arranged within the damper volume 40. This configuration with a free piston and an internal balancing spring is on one hand very compact, requiring only minimal space, and on the other hand is protected against impacts from outside.
  • Fig.7 schematically illustrates a Helmholtz damper 48 attached to a can combustor 49.
  • Arrow 39 represents the hot gas flow.
  • the damper 48 is circumferentially arranged around the can combustor 49, forming an annular damper volume 40, surrounding the combustion chamber or hot gas path respectively.
  • At least one neck tube 43 of any cross-sectional design connects the space 19, to be damped, with the variable first part V1 of the damper volume 40.
  • At least one opening 46 connects the variable second volume V2 with an environment outside of the Helmholtz damper 48.
  • the variable first part V1 of the damper volume 40 and the variable second part V2 of the damper volume 40 are separated by the piston 44.
  • the piston 44 is arranged and designed to perform a movement parallel to the axis of the combustor 49, thereby interacting with the balancing spring 45 of the helical type, arranged within the damper volume 40 along the lateral surface area of the damper housing 40a.

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Fluid-Damping Devices (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Organic Low-Molecular-Weight Compounds And Preparation Thereof (AREA)

Claims (12)

  1. Turbine à gaz (10) comprenant un compresseur (14), au moins une chambre de combustion (33) et une turbine (17), grâce à quoi ladite ou lesdites chambres de combustion (33) sont entourées par une enveloppe de chambre de combustion (34), dont l'extérieur est exposé à la pression de sortie du compresseur (pk2) dudit compresseur (14), grâce à quoi un amortisseur de Helmholtz (24, 38) au moins est fourni au niveau d'une chambre de combustion (33) et est connecté à celle-ci de façon à amortir les pulsations à l'intérieur de ladite chambre de combustion (33), dans laquelle ledit ou lesdits amortisseurs de Helmholtz (24, 38) sont un amortisseur de Helmholtz (24, 38) qui comprend un volume d'amortisseur (25, 40), qui est connecté à la chambre de combustion (33) à l'aide d'un tube à collet (26, 43), et qui comprend en outre un piston (27, 44), qui est mobile à l'intérieur dudit volume d'amortisseur (25, 40), et qui divise ledit volume d'amortisseur (25, 40) en une première partie variable (V1) d'un côté dudit piston (27, 44), laquelle première partie variable (V1) est connectée audit tube à collet (26, 43), et en une seconde partie variable correspondante (V2) de l'autre côté dudit piston (27, 44), caractérisée en ce que ladite seconde partie (V2) dudit volume d'amortisseur (25, 40) est en connexion de fluide avec l'extérieur dudit volume d'amortisseur (25, 40) qui présente la pression de sortie du compresseur (pk2), et en ce que ledit piston (27, 44) est entraîné par une chute de pression (Δp) entre ladite pression de sortie du compresseur (pk2) et la pression à l'intérieur de ladite chambre de combustion (33).
  2. Turbine à gaz selon la revendication 1, caractérisée en ce que le piston (27, 44) est tenu dans une position de repos, dans laquelle la première partie (V1) dudit volume d'amortisseur (25, 40) est maximum, à l'aide d'un ressort (30, 45), et en ce que ladite chute de pression (Δp) entraîne ledit piston (27, 44) contre la force dudit ressort (30, 45).
  3. Turbine à gaz selon la revendication 2, caractérisée en ce que ledit ressort (45) est agencé à l'intérieur de ladite première partie (V1) dudit volume d'amortisseur (40).
  4. Turbine à gaz selon la revendication 2, caractérisée en ce que ledit ressort (30) est agencé en dehors dudit volume d'amortisseur (25), et agit sur ledit piston (27) par l'intermédiaire d'une tige de piston (28), qui s'étend à partir dudit piston (27) vers l'extérieur dudit volume d'amortisseur (25).
  5. Turbine à gaz selon la revendication 2, caractérisée en ce que ledit ressort (30, 45) est un ressort hélicoïdal.
  6. Turbine à gaz selon la revendication 1, caractérisée en ce que ledit volume d'amortisseur (25, 40) est entouré par un logement (25a, 40a), et en ce que ladite connexion de fluide est établie par une ouverture (31, 46) au moins dans ledit logement (25a, 40a).
  7. Turbine à gaz selon la revendication 1, caractérisée en ce que ledit ou lesdits amortisseurs de Helmholtz (38) sont fixés sur ladite enveloppe de la chambre de combustion (34) par des moyens d'adaptation (37, 41, 42).
  8. Turbine à gaz selon la revendication 7, caractérisée en ce que ledit ou lesdits amortisseurs de Helmholtz (38) sont connectés à ladite chambre de combustion (33) par l'intermédiaire d'un trou (36) dans ladite enveloppe de la chambre de combustion (34), et en ce que lesdits moyens d'adaptation (37, 41, 42) comprennent une pièce rapportée (37), qui s'insère dans ledit trou (36) et qui reçoit un tube à collet (43) dudit ou desdits amortisseurs de Helmholtz (38), de telle sorte que ledit tube à collet (43) passe à travers ladite rapporté (37) de façon à s'ouvrir dans ladite chambre de combustion (33).
  9. Turbine à gaz selon la revendication 8, caractérisée en ce qu'un adaptateur de tube à collet (42) est prévu de façon à sceller ledit tube à collet (43) contre ladite pièce rapportée (37).
  10. Turbine à gaz selon la revendication 8, caractérisée en ce que ledit tube à collet (43) est connecté de manière amovible au volume d'amortisseur (40) dudit ou desdits amortisseurs de Helmholtz (38).
  11. Turbine à gaz selon la revendication 1, caractérisée en ce que ladite chambre de combustion (33) présente une configuration annulaire, et en ce qu'une pluralité d'amortisseurs de Helmholtz (38) sont agencés de manière circonférentielle autour de ladite chambre de combustion (33).
  12. Turbine à gaz selon la revendication 1, caractérisée en ce que ladite ou lesdites chambres de combustion sont du type en bidon, et en ce que l'amortisseur de Helmholtz (48) est agencé de manière circonférentielle autour de la chambre de combustion en bidon (49).
EP14195660.7A 2014-12-01 2014-12-01 Turbine à gaz avec un amortisseur Helmholtz Active EP3029376B1 (fr)

Priority Applications (3)

Application Number Priority Date Filing Date Title
EP14195660.7A EP3029376B1 (fr) 2014-12-01 2014-12-01 Turbine à gaz avec un amortisseur Helmholtz
US14/934,277 US20160153661A1 (en) 2014-12-01 2015-11-06 Helmholtz damper and gas turbine with such a helmholtz damper
CN201510863130.2A CN105650192B (zh) 2014-12-01 2015-12-01 亥姆霍兹减振器和带有这种亥姆霍兹减振器的燃气涡轮

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP14195660.7A EP3029376B1 (fr) 2014-12-01 2014-12-01 Turbine à gaz avec un amortisseur Helmholtz

Publications (2)

Publication Number Publication Date
EP3029376A1 EP3029376A1 (fr) 2016-06-08
EP3029376B1 true EP3029376B1 (fr) 2018-10-03

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EP14195660.7A Active EP3029376B1 (fr) 2014-12-01 2014-12-01 Turbine à gaz avec un amortisseur Helmholtz

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US (1) US20160153661A1 (fr)
EP (1) EP3029376B1 (fr)
CN (1) CN105650192B (fr)

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GB2557264B (en) * 2016-12-02 2020-04-08 Delphi Tech Ip Ltd Multi-Chamber Helmholtz Resonator
RU2687545C1 (ru) * 2018-08-17 2019-05-14 Рафаэль Салихзянович Кашапов Малоэмиссионная камера сгорания и способ подачи в ней топлива
JP7131396B2 (ja) * 2019-01-08 2022-09-06 トヨタ自動車株式会社 トランスミッションの防音装置
US11156164B2 (en) 2019-05-21 2021-10-26 General Electric Company System and method for high frequency accoustic dampers with caps
US11174792B2 (en) 2019-05-21 2021-11-16 General Electric Company System and method for high frequency acoustic dampers with baffles
CN113482777B (zh) * 2021-06-28 2022-09-06 浙江大学 一种带偏流的颈部优化亥姆霍兹消声器及应用
CN116293795A (zh) * 2021-12-06 2023-06-23 通用电气阿维奥有限责任公司 用于燃气涡轮燃烧器应用的圆顶集成声学阻尼器
US11898755B2 (en) * 2022-06-08 2024-02-13 General Electric Company Combustor with a variable volume primary zone combustion chamber
US11867139B1 (en) * 2022-06-17 2024-01-09 Blue Origin, Llc Multi-volume acoustic resonator for rocket engine

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SE458802B (sv) * 1987-04-03 1989-05-08 Stifab Ab Regleranordning foer instaellning av ett spjaell i en ventilationskanal
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US6530221B1 (en) * 2000-09-21 2003-03-11 Siemens Westinghouse Power Corporation Modular resonators for suppressing combustion instabilities in gas turbine power plants
EP1624250A1 (fr) * 2004-08-03 2006-02-08 Siemens Aktiengesellschaft Dispositif pour atténuer les oscillations acoustiques dans les chambres combustion
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EP2397760B1 (fr) * 2010-06-16 2020-11-18 Ansaldo Energia IP UK Limited Agencement d'amortisseur et procédé pour le concevoir
EP2397761B1 (fr) 2010-06-16 2021-10-06 Ansaldo Energia Switzerland AG Amortisseur de Helmholtz
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Also Published As

Publication number Publication date
CN105650192B (zh) 2020-03-03
US20160153661A1 (en) 2016-06-02
CN105650192A (zh) 2016-06-08
EP3029376A1 (fr) 2016-06-08

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