EP1605209B1 - Chambre de combustion avec dispositif d'amortissement des vibrations thermo-acoustiques - Google Patents

Chambre de combustion avec dispositif d'amortissement des vibrations thermo-acoustiques Download PDF

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Publication number
EP1605209B1
EP1605209B1 EP04013404A EP04013404A EP1605209B1 EP 1605209 B1 EP1605209 B1 EP 1605209B1 EP 04013404 A EP04013404 A EP 04013404A EP 04013404 A EP04013404 A EP 04013404A EP 1605209 B1 EP1605209 B1 EP 1605209B1
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EP
European Patent Office
Prior art keywords
combustion chamber
combustion
resonator
mouth
fastening element
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.)
Expired - Lifetime
Application number
EP04013404A
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German (de)
English (en)
Other versions
EP1605209A1 (fr
Inventor
Sven Dr. Bethke
Tobias Dr. Buchal
Michael Dr. Huth
Harald Nimptsch
Bernd Dr. Prade
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Siemens AG
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Siemens AG
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Publication date
Application filed by Siemens AG filed Critical Siemens AG
Priority to DE502004011481T priority Critical patent/DE502004011481D1/de
Priority to EP04013404A priority patent/EP1605209B1/fr
Publication of EP1605209A1 publication Critical patent/EP1605209A1/fr
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Publication of EP1605209B1 publication Critical patent/EP1605209B1/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
    • 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
    • F23R3/06—Arrangement of apertures along the flame tube
    • 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
    • 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
    • F23R2900/03041—Effusion cooled combustion chamber walls or domes
    • 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
    • F23R2900/03044—Impingement cooled combustion chamber walls or subassemblies

Definitions

  • the present invention relates to a combustion chamber with a damping device for damping thermoacoustic oscillations, in particular for a gas turbine, and a gas turbine with such a combustion chamber.
  • a gas turbine plant comprises e.g. a compressor, a combustion chamber and a turbine.
  • a compressor In the compressor there is a compression of sucked air, which is then admixed with a fuel.
  • the combustion chamber In the combustion chamber, the mixture is burned, the combustion exhaust gases are supplied to the turbine. From the turbine thermal energy is extracted from the combustion exhaust gases and converted into mechanical energy.
  • cooling air also serves to block openings, for example gaps between two adjoining heat shield elements of a combustion chamber, i. for preventing hot gas from the combustion chamber from entering the opening.
  • thermoacoustic vibrations can increase. This can lead to a swirling interaction between thermal and acoustic disturbances, which can cause high loads on the combustion chamber and, in turn, rising emissions.
  • thermoacoustic oscillations in the combustors of gas turbines - or turbomachines in general - present a problem in the design and operation of new combustors, combustor parts and burners for such gas turbines.
  • a Helmholtz resonator typically includes a volume of air or other gas therein. The volume is followed by a tube, the so-called resonator tube, which also contains air or gas and which opens into the combustion chamber.
  • the air or the gas in the volume and in the resonator tube form a spring-mass system, wherein the air or the gas in the volume of the spring and the air or the gas in the resonator tube forms the mass.
  • the Helmholtz resonator behaves like an infinite-length aperture which prevents a standing wave can form with the resonance frequency.
  • thermoacoustic oscillations which are substantially standing waves, can thus be effectively suppressed for frequencies corresponding to or near the resonant frequency of the Helmholtz resonator.
  • the US 6,351,947 Bl shows a combustion chamber with such Helmholtz resonators.
  • a combustion chamber according to the invention comprises at least one combustion chamber element to be cooled and at least one damping device for damping thermoacoustic oscillations with an opening open towards the combustion chamber. It is characterized by the fact that the mouth is integrated into the combustion chamber element to be cooled.
  • the damping device is integrated in a combustion chamber element to be cooled, the amount of air entering the combustion chamber increases only slightly, if at all, due to the presence of the damping element. This results from the fact that for cooling the combustion chamber element alone anyway a cooling air flow is necessary, which now also serves to lock the mouth of the damping device at the same time.
  • the combustion temperature - and thus the pollution of the combustion gases - is therefore not or only slightly increased.
  • the mouth in the combustion chamber according to the invention may be associated with a blocking air supply. This then serves as a cooling air supply for the cooling of the combustor element to be cooled.
  • the mouth can also be associated with a fuel supply such that the sealing air fuel is added. The addition of fuel to the sealing air leads to a reduction of the combustion temperature in the main burner and thus to a reduction of the pollutant content of the combustion gases.
  • the combustion chamber has a combustion chamber wall which comprises a combustion chamber shell and a combustion chamber lining fastened to the combustion chamber shell by means of fastening elements to be cooled.
  • the combustion chamber lining may, for example, be a heat shield, in particular a ceramic or metallic heat shield.
  • the mouth of the at least one damping device is integrated in a fastening element for fastening the combustion chamber lining to the combustion chamber shell.
  • the combustor element to be cooled is formed as a fastener for fixing the combustor liner. Since the fasteners are present anyway and require cooling, integrating the mouth in a fastener requires only a redesign of the fastener, for example.
  • the fastening element can also be configured as a fastening element, which comprises at least one sliding seat device.
  • a sliding seat device is often located, for example, at the transition from the so-called “basket” to the so-called “transition piece” in a silo burning chamber.
  • the damping device can also be arranged at the transition from the combustion chamber to the first row Leitschauffel #2. As a rule, quite high blocking air flows are needed there. This applies to ring combustion chambers and also for silo separation chambers.
  • the damping element may in particular be designed such that the combustion chamber element to be cooled forms part of the damping device.
  • a fixing screw with an axial through-bore can form the resonator tube of a Helmholtz resonator.
  • the damping device is designed as a Helmholtz resonator, in particular as a Helmholtz resonator with variable resonance frequency.
  • the variability of the resonant frequency can be achieved by making the volume of the Helmholtz resonator changeable.
  • a volume change may e.g. can be achieved via an adjustable rear wall of the resonator.
  • the Helmholtz resonator may also include a plurality of orifices, each of which is integrated into a combustion chamber element to be cooled.
  • a plurality of resonator tubes of the same Helmholtz resonator can be integrated into different fastening screws.
  • the damping device is designed as a ⁇ / 4 tube, ie as a tube with a quarter of the wavelength of the vibration to be damped.
  • a gas turbine according to the invention comprises at least one combustion chamber according to the invention.
  • Fig. 1 shows as a first embodiment, a section of the combustion chamber wall of a combustion chamber according to the invention in a highly schematic representation.
  • Fig. 2 shows a view of the combustion chamber wall of a second embodiment of the invention seen from the combustion chamber inside.
  • Fig. 3 shows a side view of in Fig. 2 shown Brennschwandung.
  • FIG. 1 is shown as a first embodiment of the invention, a combustion chamber of a gas turbine according to the invention.
  • the figure shows a section of the combustion chamber wall 1, which comprises a combustion chamber shell 3 and a metallic heat shield 4.
  • the metallic heat shield 4 is constructed from a number of heat shield elements 2, which are each fixed by means of a screw 7 as a fastening element at a connection point 5 on the combustion chamber shell 3.
  • the screws 7 are like the heat shield elements 2 by means of cooling air to be cooled combustion chamber elements.
  • this is equipped with at least one damping device, which is formed in the present embodiment as opening into the combustion chamber Helmholtz resonator 6.
  • the Helmholtz resonator 6 is attached to the combustion chamber wall 1 in the region of a connection point 5. It is held by means of a fastening element or a plurality of fastening elements (not shown) on the combustion chamber wall 1.
  • a fastening element or a plurality of fastening elements (not shown) on the combustion chamber wall 1.
  • damping devices may be present.
  • the Helmholtz resonator 6 comprises a resonator chamber 15 and a resonator tube, also called resonator neck.
  • the resonator tube is formed in the present embodiment of the screw 7, which has a through hole 8 for this purpose.
  • One end 9 of the through hole 8 opens into the resonator 15.
  • the other end 10 of the through hole 8 opens into the combustion chamber and represents the mouth of the Helmholtz resonator 6 in the combustion chamber.
  • the damping effect of the Helmholtz resonator 6 is based on that the behaves in the resonator 15 and the resonator tube 8 located air as a spring-mass system.
  • the air in the resonator chamber 15, the spring and the air in the resonator tube 8 is the mass of this system.
  • this spring-mass system oscillates at a resonant frequency, by the volume V of the resonator 15, the cross-sectional area F of the through hole. 8 , And by the length L of the through hole 8 (ie, the screw 7) is determined, the Helmholtz resonator 6 behaves like an opening of infinite length, so that no standing wave can form with the resonance frequency.
  • the generation of thermoacoustic oscillations, which are substantially standing waves, can thus be effectively suppressed for frequencies corresponding to or near the resonant frequency of the Helmholtz resonator.
  • the resonator 6 is designed substantially cylindrically symmetrical to the screw 7.
  • the resonance frequency of the Helmholtz resonator 6 are set. For example, Increasing the volume V of the resonator chamber 15 or the length L of the screw 7 leads to a reduced resonance frequency. Increasing the cross-sectional area F of the through-hole 8, on the other hand, leads to an increased resonance frequency.
  • the rear wall 17 of the Helmholtz resonator 6 can be designed to be adjustable. On the cylindrical side wall 12 of the Helmholtz resonator 6 then, for example, a thread 16 is present, in which a matching mating thread of the rear wall 17 engages.
  • the volume V of the resonator 15 and thus the resonator frequency can be changed in the desired manner.
  • it is also possible to change the volume by exchanging the resonator chamber 15 with a resonator chamber 15 having a different volume.
  • the length L of the screw and / or the cross-sectional area F of the through-hole 8 can be changed.
  • a screw 7 can be used whose bore 8 has a larger cross-sectional area F than the previously used screw 7. It can be used for the same purpose but also a screw 7 with a shorter length L. become.
  • the resonance frequency of the Helmholtz resonator 6 can be influenced.
  • the resonator space 15 is at the cold side, i. attached to the combustion chamber facing away from the outside of the combustion chamber shell 3 and projects into the Kompressplplenum 20 inside.
  • spacers 19 are provided between the resonator chamber 15 and the outside of the combustion chamber shell 3, which ensure a distance between the combustion chamber shell 3 and the resonator chamber 15 and thus a flow of pressurized cooling air between allow the combustion chamber shell 3 and the resonator 15.
  • Cooling air can then be conducted from the compressor plenum 20 along the flow paths 13 to the side facing away from the combustion chamber interior, the so-called cold side of the heat shield elements 2, where it provides for an impingement air cooling of the heat shield elements 2.
  • the impingement air flows into the combustion chamber after hitting the cold sides along the flow paths 23 through gaps between adjacent heat shield elements 2, blocking the gaps against hot gas penetration of the combustion chamber.
  • the cooling of the screw 7 takes place together with the locking of the mouth 10 of the Helmholtz resonator 6 against ingress of hot gas.
  • the air first flows from the compressor plenum 20 through the openings 18 (forming the blocking air supply) in the rear wall 17 of the resonator chamber 15 into the resonator chamber 15 and then through the through-hole 8 of the screw 7 into the combustion chamber (flow path 11).
  • the cooling of Helmholtz resonator 6 and screw 7 is carried out with the same cooling air, the proportion of cooling air, which is guided past the burner, compared to a separate cooling of Helmholtz resonator 6 and screw 7, as necessary would be if the screw 7 was not used at the same time as Resonatorrohr be reduced.
  • FIGS. 2 and 3 a second embodiment is shown very schematically.
  • the same or similar components are provided with the same reference numerals as in the first embodiment for simplicity and for better comparability.
  • Fig. 2 shows, seen from the combustion chamber inside, a section of a combustion chamber 1, which is lined with metallic heat shield plates 21, 22 as heat shield elements.
  • Fig. 3 shows a section through the combustion chamber wall 1 along the line A - A.
  • the heat shield plates 21, 22 are screwed to connecting points 5 by means of screws 7 with the combustion chamber shell 3.
  • Helmholtz resonators 6 are arranged, which are fixed by means of screws 7 on the combustion chamber 1.
  • a passage opening or through-bore 8 in the screws 7 serves, as in the first exemplary embodiment, as a resonator tube of the respective Helmholtz resonator 6.
  • FIG FIG. 3 only one of the Helmholtz resonators 6 shown.
  • a resonator chamber 15 in a modification of the second embodiment, it is also possible for a resonator chamber 15 to expand over a plurality of screws 7.
  • all screws 7, over which the resonator chamber 15 extends can be provided with through-holes and thus form resonator tubes.
  • the adjustment of the resonator volume can be done within operating pauses by means of a suitable tool by hand or during operation.
  • a controller (not shown) is provided, by means of which the adjustment of the resonator volume can be controlled.
  • An automatic adjustment or regulation is possible.
  • an electric motor, a hydraulic adjusting device or a pneumatic adjusting device can be used.
  • the regulation can be done online during operation. With a fully automatic control can take place a continuous or at intervals, adjustment to the strongest vibration frequency.
  • a Helmholtz resonator 6 can be switched off by replacing the screw with through hole against a screw without through hole. Alternatively, the resonator 6 can also be completely removed.
  • the invention is particularly suitable for use in annular combustion chambers with metallic heat shields or in the so-called inlet shells of the combustion chambers with ceramic heat shields ("stones").

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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)

Claims (11)

  1. Chambre de combustion, notamment pour une turbine à gaz ayant au moins un élément ( 7 ) de fixation à refroidir et au moins un dispositif ( 6 ) d'amortissement des oscillations thermo-acoustiques ayant une embouchure ( 10 ) débouchant sur la chambre de combustion, l'embouchure ( 10 ) étant intégrée à l'élément ( 7 ) de fixation de manière à ce que soit nécessaire, pour le refroidissement de l'élément de fixation, seulement pour ainsi dire un courant d'air de refroidissement, qui sert en même temps aussi à obturer l'embouchure du dispositif d'amortissement, caractérisée en ce que la chambre de combustion comprend une paroi ( 1 ) de chambre de combustion, qui comprend une coquille ( 3 ) de chambre de combustion et un revêtement ( 4 ) de chambre de combustion fixé à la coquille ( 3 ) de chambre de combustion au moyen d'éléments ( 7 ) de fixation à refroidir de sorte que l'embouchure ( 10 ) du au moins un dispositif ( 6 ) d'amortissement est intégré dans un élément ( 7 ) de fixation pour la fixation du revêtement ( 4 ) de la chambre de combustion à la coquille ( 3 ) de la chambre de combustion.
  2. Chambre de combustion suivant la revendication 1, caractérisée en ce qu'à l'embouchure ( 10 ) est associée une amenée ( 18 ) d'air d'obturation, pour amener de l'air d'obturation obturant l'embouchure à l'encontre de l'entrée de gaz chaud provenant de la chambre de combustion.
  3. Chambre de combustion suivant la revendication 2, caractérisée en ce qu'à l'embouchure est associée en outre une amenée de combustible de manière à ce que du combustible soit mélangé à l'air d'obturation.
  4. Chambre de combustion suivant l'une des revendications précédentes, caractérisée en ce que l'élément de fixation est une vis ( 7 ) de fixation.
  5. Chambre de combustion suivant l'une des revendications précédentes, caractérisée en ce que l'élément de fixation comprend au moins un dispositif à siège coulissant.
  6. Chambre de combustion suivant l'une des revendications précédentes 4, caractérisée en ce que le revêtement de la chambre de combustion est un bouclier ( 4 ) thermique.
  7. Chambre de combustion suivant l'une des revendications précédentes, caractérisée en ce que le dispositif d'amortissement est réalisé sous la forme d'un résonateur ( 6 ) d'Helmholtz.
  8. Chambre de combustion suivant la revendication 7, caractérisée en ce que le résonateur ( 6 ) d'Helmholtz est conformé en résonateur d'Helmholtz ayant une fréquence de résonance variable.
  9. Chambre de combustion suivant la revendication 7 ou revendication 8, caractérisé en ce que le résonateur ( 6 ) d'Helmholtz comprend plusieurs embouchures ( 10 ) débouchant sur la chambre de combustion, qui sont intégrées respectivement dans un élément ( 7 ) de fixation à refroidir.
  10. Chambre de combustion suivant l'une des revendications 1 à 6, caractérisée en ce qu'au moins un dispositif d'amortissement est constitué sous la forme d'un tube lambda/4.
  11. Turbine à gaz ayant au moins une chambre de combustion suivant l'une des revendications précédentes.
EP04013404A 2004-06-07 2004-06-07 Chambre de combustion avec dispositif d'amortissement des vibrations thermo-acoustiques Expired - Lifetime EP1605209B1 (fr)

Priority Applications (2)

Application Number Priority Date Filing Date Title
DE502004011481T DE502004011481D1 (de) 2004-06-07 2004-06-07 Brennkammer mit einer Dämpfungseinrichtung zur Dämpfung von thermoakustischen Schwingungen
EP04013404A EP1605209B1 (fr) 2004-06-07 2004-06-07 Chambre de combustion avec dispositif d'amortissement des vibrations thermo-acoustiques

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP04013404A EP1605209B1 (fr) 2004-06-07 2004-06-07 Chambre de combustion avec dispositif d'amortissement des vibrations thermo-acoustiques

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EP1605209A1 EP1605209A1 (fr) 2005-12-14
EP1605209B1 true EP1605209B1 (fr) 2010-08-04

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Cited By (2)

* Cited by examiner, † Cited by third party
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CN108980894A (zh) * 2017-05-31 2018-12-11 安萨尔多能源公司 用于燃气涡轮的燃烧器的瓦保持器
WO2020200568A1 (fr) 2019-04-03 2020-10-08 Siemens Aktiengesellschaft Carreau d'écran thermique à fonction d'amortissement

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US7401682B2 (en) 2005-08-10 2008-07-22 United Technologies Corporation Architecture for an acoustic liner
US7311175B2 (en) * 2005-08-10 2007-12-25 United Technologies Corporation Acoustic liner with bypass cooling
EP1816357A1 (fr) * 2006-02-02 2007-08-08 Siemens Aktiengesellschaft Vis pour un environnement chargé thermiquement
GB0610800D0 (en) 2006-06-01 2006-07-12 Rolls Royce Plc Combustion chamber for a gas turbine engine
EP2187125A1 (fr) * 2008-09-24 2010-05-19 Siemens Aktiengesellschaft Dispositif et procédé destinés à l'amortissement d'oscillations de combustion
CH700799A1 (de) * 2009-04-11 2010-10-15 Alstom Technology Ltd Brennkammer mit Helmholtzdämpfer für eine Gasturbine.
EP2299177A1 (fr) * 2009-09-21 2011-03-23 Alstom Technology Ltd Chambre de combustion de turbine à gaz
DE102009046066A1 (de) * 2009-10-28 2011-05-12 Man Diesel & Turbo Se Brenner für eine Turbine und damit ausgerüstete Gasturbine
EP2385303A1 (fr) 2010-05-03 2011-11-09 Alstom Technology Ltd Dispositif de combustion pour turbine à gaz
EP2732215A2 (fr) 2011-09-01 2014-05-21 Siemens Aktiengesellschaft Chambre de combustion pour une installation de turbine à gaz
DE102011081962A1 (de) 2011-09-01 2013-03-07 Siemens Aktiengesellschaft Brennkammer für eine Gasturbinenanlage
EP3227611A1 (fr) * 2014-12-01 2017-10-11 Siemens Aktiengesellschaft Résonateurs comprenant des tubes de mesure interchangeables pour des turbines à gaz
DE102015224524A1 (de) * 2015-12-08 2017-06-08 Siemens Aktiengesellschaft Brennkammer mit Resonatoren
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
US11698192B2 (en) * 2021-04-06 2023-07-11 Raytheon Technologies Corporation CMC combustor panel attachment arrangement
CN115682033B (zh) * 2021-07-28 2024-09-24 北京航空航天大学 防振燃烧室以及燃烧室防振方法

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US6351947B1 (en) * 2000-04-04 2002-03-05 Abb Alstom Power (Schweiz) Combustion chamber for a gas turbine
DE50212871D1 (de) * 2001-09-07 2008-11-20 Alstom Technology Ltd Dämpfungsanordnung zur reduzierung von brennkammerpulsationen in einer gasturbinenanlage
GB2390150A (en) * 2002-06-26 2003-12-31 Alstom Reheat combustion system for a gas turbine including an accoustic screen
EP1389690B1 (fr) * 2002-08-16 2007-01-03 Siemens Aktiengesellschaft Vis intérieurement refroidissable
GB2396687A (en) * 2002-12-23 2004-06-30 Rolls Royce Plc Helmholtz resonator for combustion chamber use

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN108980894A (zh) * 2017-05-31 2018-12-11 安萨尔多能源公司 用于燃气涡轮的燃烧器的瓦保持器
CN108980894B (zh) * 2017-05-31 2021-11-05 安萨尔多能源公司 用于燃气涡轮的燃烧器的瓦保持器
WO2020200568A1 (fr) 2019-04-03 2020-10-08 Siemens Aktiengesellschaft Carreau d'écran thermique à fonction d'amortissement

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EP1605209A1 (fr) 2005-12-14
DE502004011481D1 (de) 2010-09-16

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