EP0892216A1 - Schwingungsdämpfende Brennkammerwandstruktur - Google Patents
Schwingungsdämpfende Brennkammerwandstruktur Download PDFInfo
- Publication number
- EP0892216A1 EP0892216A1 EP97810489A EP97810489A EP0892216A1 EP 0892216 A1 EP0892216 A1 EP 0892216A1 EP 97810489 A EP97810489 A EP 97810489A EP 97810489 A EP97810489 A EP 97810489A EP 0892216 A1 EP0892216 A1 EP 0892216A1
- Authority
- EP
- European Patent Office
- Prior art keywords
- combustion chamber
- helmholtz
- damping
- multicellular structure
- gas turbine
- 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
Links
Images
Classifications
-
- G—PHYSICS
- G10—MUSICAL INSTRUMENTS; ACOUSTICS
- G10K—SOUND-PRODUCING DEVICES; METHODS OR DEVICES FOR PROTECTING AGAINST, OR FOR DAMPING, NOISE OR OTHER ACOUSTIC WAVES IN GENERAL; ACOUSTICS NOT OTHERWISE PROVIDED FOR
- G10K11/00—Methods or devices for transmitting, conducting or directing sound in general; Methods or devices for protecting against, or for damping, noise or other acoustic waves in general
- G10K11/16—Methods or devices for protecting against, or for damping, noise or other acoustic waves in general
- G10K11/172—Methods or devices for protecting against, or for damping, noise or other acoustic waves in general using resonance effects
-
- 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
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05B—INDEXING SCHEME RELATING TO WIND, SPRING, WEIGHT, INERTIA OR LIKE MOTORS, TO MACHINES OR ENGINES FOR LIQUIDS COVERED BY SUBCLASSES F03B, F03D AND F03G
- F05B2260/00—Function
- F05B2260/96—Preventing, counteracting or reducing vibration or noise
-
- 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 invention relates to a gas turbine combustion chamber Combustion chamber wall at least partially cooled by effusion or film and extends from the combustion chamber inlet to the turbine, and attached to a front panel burner are arranged in the combustion chamber Helmholtz damper are.
- thermoacoustic vibrations often occur in combustion chambers of gas turbines. Thereby, thermoacoustic vibrations are used to denote mutually rocking thermal and acoustic disturbances. High vibration amplitudes can occur, which can lead to undesirable effects such as a high mechanical load on the combustion chamber, increased NO x emissions due to inhomogeneous combustion and even extinguishing the flame.
- the cooling air flowing into the combustion chamber has an important function in conventional combustion chambers, since the cooling air film on the combustion chamber wall has a sound-damping effect and thus contributes to damping thermoacoustic vibrations.
- an increasing proportion of the air is passed through the burners themselves in modern gas turbines, thus reducing the cooling air flow.
- the problems mentioned at the outset which are associated with the undesirable vibrations, occur increasingly in such modern combustion chambers.
- the invention is therefore based on the object of a device for suppressing thermoacoustic combustion chamber vibrations to provide the smallest possible space gets along and also work in tight geometries leaves.
- combustion chamber walls with a multicellular Helmholtz damper structure.
- combustion chamber walls themselves can have a multicellular structure have, or the combustion chamber walls are multicellular Provide mats.
- a multicellular structure means a structure that from many neighboring but separate cells is constructed.
- the individual cells can be any Have shape, but the cells are preferred by Base area and a vertical height marked on it.
- the base area can be triangular, rectangular, hexagonal, generally be polygonal or irregular in shape.
- Prefers are rectangular and hexagonal cells that are simply strung together can be and result in a stable structure.
- the structures are preferred in the direction of the height of the cells only one cell thick, but several cells can also be used be stacked on top of each other.
- the expansion of the multicellular Structure is always in the direction of the height of the cells much smaller so perpendicular to it, in the lateral plane of the Base areas of the cells.
- the number of cells of the entire structure is in the present one Invention between 1,000 and about 200,000, preferred between 5000 and 50,000, particularly preferably between 10,000 and 30,000.
- a lesser or greater number of cells in A structure also makes sense since the number of cells primarily on the frequency spectrum to be attenuated and based on the required damping performance.
- each cell has at least one Opening, preferably two, opposite one another Openings. Located in the structure that is only one cell thick the two openings on the top, for example and bottom of the structure so that the structure and the The cooling air can flow through cells.
- the cell walls in which the openings are located have a not insignificant thickness.
- the openings are therefore hereinafter also referred to as pipes.
- the cells of the entire structure do not all have to be the same Shape, size, number of openings (tubes), length and diameter of pipes etc. Cells with different properties (About size) can serve various purposes, such as: dampen different frequencies.
- each cell forms a (at rinsed through two openings) Helmholtz resonator.
- the resonance frequency of such a Helmholtz resonator is due to the Area and length of the inlet openings and the volume of the Given cell. Flushed Helmholtz resonators offer that Advantage that they are cooled by the cooling air flowing through. Since the resonance frequency of a Helmholtz resonator from depends on the gas temperature, this resonance frequency kept stable.
- the cell volumes and the area and Length of the inlet openings chosen so that their resonance frequency with certain frequencies of the combustion chamber to be damped to match.
- a Helmholtz resonator works in the area of its resonance frequency as a damper there the coupling the vibration to be damped to the resonator volume is particularly good.
- the frequencies to be attenuated are just the frequencies where you want to dampen the vibrations of the combustion chamber, for example because the combustion chamber is too strong at these frequencies (thermo-) acoustic vibrations.
- thermo- thermoacoustic oscillation occurs when the burner at a the natural frequencies of the combustion chamber with fluctuations in the React heat release.
- the frequency of the ensuing Experience has shown that vibration is close to one of the natural frequencies the combustion chamber. These are for typical combustion chambers generally between 40 Hz and 3 kHz. The lowest experience has shown that these natural frequencies are special Meaning. However, it is often also the damping of higher eigenmodes important to the combustion chamber.
- a set of cells with their Properties (shape, volume, length and diameter of the pipes) matched to each of the frequencies to be attenuated.
- the individual cells are generally relatively small, the damping performance of a single cell is relatively low.
- this is offset by the large number of cells because in a first approximation the damping power is proportional to the number of the dampening cells.
- the combustion chamber walls are, for example, in an annular combustion chamber the outer shell, the inner shell and the front panel (i.e. the area where the burners are attached).
- the entire area of the Combustion chamber walls can be equipped with Helmholtz dampers.
- the area required results from the area to be reached Damping performance. For example, only one frequency the combustion chamber are damped, it may be enough, only that To equip the front panel with multicellular Helmholtz dampers and to leave the outer and inner shell unchanged.
- honeycomb mats can be used are made in a variety of different shapes and materials are available.
- the exhaust housing is not shown the gas turbine with exhaust pipe and chimney, the compressor and collecting space of the turbine.
- the flow direction of the work equipment is marked with arrows.
- FIG. 1 is a partial longitudinal section of an annular combustion chamber as an example shown. Although the following embodiment refer to such an annular combustion chamber the invention is not limited to ring combustion chambers, but generally applicable for effusion-cooled combustion chambers.
- the system of which in Fig. 1 only that above the machine axis 30 lying part is shown, is rotationally symmetrical built up around the machine axis 30.
- the system On the side of the Gas turbine 20, the system consists essentially of the Blades 24 bladed rotor 22 and the guide vanes 28 equipped blade carrier 26.
- the blade carrier 26 is about corresponding recordings in the turbine housing (not shown) mounted.
- Compressed air 38 flows from the compressor into the collecting space 39.
- the majority of the air flows through the bypass openings 31 and in particular the cooling channels 30 and 32 in the Combustion chamber hood 34 and from there through the burner 16 into the Combustion chamber 10.
- a smaller part of the air flows as cooling air from the cooling channels 30 and 32 through a variety of Openings in the wall parts 18 in the combustion chamber 10 (effusion cooling).
- the reference numeral 14 marks the exit to Turbine 20.
- the wall parts 18 and the front panel 36 are now according to the invention at least in part as a multicellular Helmholtz damper structure educated.
- FIG. 2 shows a section of a combustion chamber wall according to the invention in detail.
- the actual one Combustion chamber wall 40 with a multi-cell mat from Helmholtz dampers 42 provided.
- the cooling air flows through the entry openings (or entry pipe) 46 into the cell volume 48 and then flows through the outlet openings 44 in the combustion chamber 10. Since the outlet opening 44 has the vapor properties of the damping element will significantly affect it hereinafter also referred to as the damping tube 44.
- the total pressure is p about 30 bar.
- the pressure loss ⁇ p due to the effusion cooling should be around 2%, i.e. around 60,000 Pa.
- the entire mass flow the air in the combustion chamber is 135 kg / s, the Cooling air flow should be about 1% of it, here 1.5 kg / s.
- the temperature of the cooling air is about 720 K, the speed of sound c at this temperature about 550 m / s.
- a frequency of 116 Hz should be damped with the Helmholtz dampers.
- the diameter of the inlet openings is chosen to be 0.35 mm and the diameter of the damping tube is 0.8 mm.
- the length of the damping tube l d is also chosen to be 15 mm
- the height of a resonator cell 62 is 9 cm and the base area of a resonator cell is 2.11 cm 2 .
- the volume V of a Helmholtz damper 62 is then 19 ml (1.9 x 10 -5 m 3 ), so that the required resonance and thus damping frequency is obtained.
- the steam pipes are designed for a length of 15 mm.
- the combustion chamber wall of the exemplary embodiment has only one Thickness of 7.5 mm.
- 20,000 damper cells were used. This reduces the output pressure fluctuation from 100 mbar to a damped pressure fluctuation of around 30 mbar.
- the inlet openings In the first design example, almost the entire pressure loss was provided through the inlet openings. If this is not desired the inlet openings can be made larger. In the second design example, the diameter is accordingly of the inlet openings to 0.7 mm and the diameter of the Damping tube selected to 0.8 mm. Because of the larger inlet diameter the damping in this example is somewhat lower. With the same choice of the remaining parameters as in example 1, in this example there will be an output pressure fluctuation for 20,000 dampers from 100 mbar to a damped pressure fluctuation reduced by around 40 mbar.
Landscapes
- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Physics & Mathematics (AREA)
- Acoustics & Sound (AREA)
- Multimedia (AREA)
- Gas Burners (AREA)
- Combustion Methods Of Internal-Combustion Engines (AREA)
- Cylinder Crankcases Of Internal Combustion Engines (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
Description
- Fig. 1
- in schematisierter Darstellung einen Teillängsschnitt einer Ringbrennkammer;
- Fig. 2
- ein Ausführungsbeispiel der Gestaltung der Brennkammerwand mit einer vielzelligen Struktur von Helmholtz-Dämpfern;
- Fig. 3
- die relative Dämpfleistung eines auf 116 Hz ausgelegten Helmholtzdämpfelements;
- 10
- Brennkammer
- 12
- Brennkammereintritt
- 14
- Brennkammeraustritt
- 16
- Brenner
- 18
- Brennkammerwand
- 20
- Turbine
- 22
- Rotor
- 24
- Turbinenlaufreihe
- 26
- Schaufelträger
- 28
- Turbinenleitreihe
- 30
- innerer Kühlkanal
- 31
- Bypass-Öffnungen
- 32
- äußerer Kühlkanal
- 34
- Haube
- 36
- Frontpanel
- 38
- verdichtete Luft
- 39
- Sammelraum
- 40
- Brennkammerwand
- 42
- Helmholtzdämpfer
- 44
- Austrittsöffnung, Dämpfrohr
- 46
- Eintrittsöffnung, Eintrittsrohr
- 48
- Zellvolumen
Claims (7)
- Gasturbinenbrennkammer mit einer Brennkammer (10) deren Brennkammerwand (18) sich vom Brennkammereintritt (12) bis zur Turbine (20) erstreckt, und bei der an einem Frontpanel (36) Brenner (16) befestigt sind, wobei im Bereich der Brennkammer (10) Helmholtzdämpfer (42) angeordnet sind,
dadurch gekennzeichnet,
dass die Helmholtzdämpfer (42) Elemente einer vielzelligen Struktur sind, wobei die vielzellige Struktur zumindest in Teilbereichen an der Brennkammerwand (18) und/oder am Frontpanel (36) angeordnet ist. - Gasturbinenbrennkammer nach Anspruch 1, dadurch gekennzeichnet, dass zur Bildung der vielzelligen Struktur Matten verwendet werden.
- Gasturbinenbrennkammer nach Anspruch 2, dadurch gekennzeichnet, dass zur Bildung der vielzelligen Struktur unterschiedliche Matten verwendet werden.
- Gasturbinenbrennkammer nach einem der vorstehenden Ansprüche, dadurch gekennzeichnet, dass die Brennkammerwand (18) und/oder das Frontpanel (36) in Teilbereichen als vielzellige Struktur ausgebildet sind.
- Gasturbinenbrennkammer nach einem der vorstehenden Ansprüche, dadurch gekennzeichnet, dass die vielzellige Struktur Helmholtzdämpfer (42) unterschiedlicher Größe aufweist.
- Gasturbinenbrennkammer nach einem der vorstehenden Ansprüche, dadurch gekennzeichnet, dass die Anzahl der Zellen der vielzellige Struktur zwischen 1.000 und etwa 200.000 liegt, bevorzugt zwischen 5.000 und 50.000 und besonders bevorzugt zwischen 10.000 und 30.000 liegt.
- Gasturbinenbrennkammer nach einem der vorstehenden Ansprüche, dadurch gekennzeichnet, dass zumindest ein Teil der Helmholtzdämpfer (42) der vielzelligen Struktur von Kühlluft durchströmt wird, vorzugsweise, dass alle Helmholtzdämpfer (42) der vielzelligen Struktur von Kühlluft durchströmt werden.
Priority Applications (3)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
DE59709276T DE59709276D1 (de) | 1997-07-15 | 1997-07-15 | Schwingungsdämpfende Brennkammerwandstruktur |
AT97810489T ATE232287T1 (de) | 1997-07-15 | 1997-07-15 | Schwingungsdämpfende brennkammerwandstruktur |
EP97810489A EP0892216B1 (de) | 1997-07-15 | 1997-07-15 | Schwingungsdämpfende Brennkammerwandstruktur |
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
EP97810489A EP0892216B1 (de) | 1997-07-15 | 1997-07-15 | Schwingungsdämpfende Brennkammerwandstruktur |
Publications (2)
Publication Number | Publication Date |
---|---|
EP0892216A1 true EP0892216A1 (de) | 1999-01-20 |
EP0892216B1 EP0892216B1 (de) | 2003-02-05 |
Family
ID=8230302
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP97810489A Expired - Lifetime EP0892216B1 (de) | 1997-07-15 | 1997-07-15 | Schwingungsdämpfende Brennkammerwandstruktur |
Country Status (3)
Country | Link |
---|---|
EP (1) | EP0892216B1 (de) |
AT (1) | ATE232287T1 (de) |
DE (1) | DE59709276D1 (de) |
Cited By (12)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
EP0990851A1 (de) * | 1998-09-30 | 2000-04-05 | Asea Brown Boveri AG | Brennkammer für eine Gasturbine |
US6351947B1 (en) | 2000-04-04 | 2002-03-05 | Abb Alstom Power (Schweiz) | Combustion chamber for a gas turbine |
WO2002025174A1 (en) * | 2000-09-21 | 2002-03-28 | Siemens Westinghouse Power Corporation | Modular resonators for suppressing combustion instabilities in gas turbine power plants |
EP1213539A1 (de) * | 2000-12-06 | 2002-06-12 | Mitsubishi Heavy Industries, Ltd. | Gasturbinenbrennkammer, Gasturbine und Düsentriebwerk |
EP1251313A3 (de) * | 2001-04-19 | 2002-11-20 | Mitsubishi Heavy Industries, Ltd. | Gasturbinenverbrennungsanlage |
EP1219900A3 (de) * | 2000-12-26 | 2003-02-05 | Mitsubishi Heavy Industries, Ltd. | Gasturbinenverbrennungsanlage |
US6973790B2 (en) | 2000-12-06 | 2005-12-13 | Mitsubishi Heavy Industries, Ltd. | Gas turbine combustor, gas turbine, and jet engine |
EP1832812A2 (de) * | 2006-03-10 | 2007-09-12 | Rolls-Royce Deutschland Ltd & Co KG | Gasturbinenbrennkammerwand mit Dämpfung von Brennkammerschwingungen |
EP2295864A1 (de) * | 2009-08-31 | 2011-03-16 | Alstom Technology Ltd | Verbrennungsvorrichtung einer Gasturbine |
FR2962586A1 (fr) * | 2010-07-09 | 2012-01-13 | Airbus Operations Sas | Panneau pour le traitement acoustique |
EP2837782A1 (de) | 2013-08-14 | 2015-02-18 | Alstom Technology Ltd | Dämpfer für eine Schwingungsdämpfung in einer Gasturbine |
EP1221574B2 (de) † | 2001-01-09 | 2017-12-20 | Mitsubishi Heavy Industries, Ltd. | Gasturbinenbrennkammer |
Families Citing this family (1)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
DE102006053278A1 (de) * | 2006-11-03 | 2008-05-08 | Deutsches Zentrum für Luft- und Raumfahrt e.V. | Brennkammervorrichtung |
Citations (4)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US4199936A (en) * | 1975-12-24 | 1980-04-29 | The Boeing Company | Gas turbine engine combustion noise suppressor |
US4298090A (en) * | 1978-12-27 | 1981-11-03 | Rolls-Royce Limited | Multi-layer acoustic linings |
EP0597138A1 (de) * | 1992-11-09 | 1994-05-18 | Asea Brown Boveri Ag | Gasturbinen-Brennkammer |
EP0702141A2 (de) * | 1994-09-14 | 1996-03-20 | Mitsubishi Jukogyo Kabushiki Kaisha | Schallabsorber für einen Überschall-Strahlantrieb |
-
1997
- 1997-07-15 EP EP97810489A patent/EP0892216B1/de not_active Expired - Lifetime
- 1997-07-15 AT AT97810489T patent/ATE232287T1/de not_active IP Right Cessation
- 1997-07-15 DE DE59709276T patent/DE59709276D1/de not_active Expired - Lifetime
Patent Citations (4)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US4199936A (en) * | 1975-12-24 | 1980-04-29 | The Boeing Company | Gas turbine engine combustion noise suppressor |
US4298090A (en) * | 1978-12-27 | 1981-11-03 | Rolls-Royce Limited | Multi-layer acoustic linings |
EP0597138A1 (de) * | 1992-11-09 | 1994-05-18 | Asea Brown Boveri Ag | Gasturbinen-Brennkammer |
EP0702141A2 (de) * | 1994-09-14 | 1996-03-20 | Mitsubishi Jukogyo Kabushiki Kaisha | Schallabsorber für einen Überschall-Strahlantrieb |
Cited By (23)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
EP0990851A1 (de) * | 1998-09-30 | 2000-04-05 | Asea Brown Boveri AG | Brennkammer für eine Gasturbine |
US6351947B1 (en) | 2000-04-04 | 2002-03-05 | Abb Alstom Power (Schweiz) | Combustion chamber for a gas turbine |
US7194862B2 (en) | 2000-09-21 | 2007-03-27 | Siemens Power Generation, Inc. | Resonator adopting counter-bored holes and method of suppressing combustion instabilities |
WO2002025174A1 (en) * | 2000-09-21 | 2002-03-28 | Siemens Westinghouse Power Corporation | Modular resonators for suppressing combustion instabilities in gas turbine power plants |
US6530221B1 (en) | 2000-09-21 | 2003-03-11 | Siemens Westinghouse Power Corporation | Modular resonators for suppressing combustion instabilities in gas turbine power plants |
US7549506B2 (en) | 2000-09-21 | 2009-06-23 | Siemens Energy, Inc. | Method of suppressing combustion instabilities using a resonator adopting counter-bored holes |
EP1213539A1 (de) * | 2000-12-06 | 2002-06-12 | Mitsubishi Heavy Industries, Ltd. | Gasturbinenbrennkammer, Gasturbine und Düsentriebwerk |
US6640544B2 (en) | 2000-12-06 | 2003-11-04 | Mitsubishi Heavy Industries, Ltd. | Gas turbine combustor, gas turbine, and jet engine |
US6973790B2 (en) | 2000-12-06 | 2005-12-13 | Mitsubishi Heavy Industries, Ltd. | Gas turbine combustor, gas turbine, and jet engine |
EP1219900A3 (de) * | 2000-12-26 | 2003-02-05 | Mitsubishi Heavy Industries, Ltd. | Gasturbinenverbrennungsanlage |
US6688107B2 (en) | 2000-12-26 | 2004-02-10 | Mitsubishi Heavy Industries, Ltd. | Gas turbine combustion device |
EP1221574B2 (de) † | 2001-01-09 | 2017-12-20 | Mitsubishi Heavy Industries, Ltd. | Gasturbinenbrennkammer |
US6837051B2 (en) | 2001-04-19 | 2005-01-04 | Mitsubishi Heavy Industries, Ltd. | Gas turbine combustor |
US6837050B2 (en) | 2001-04-19 | 2005-01-04 | Mitsubishi Heavy Industries, Ltd. | Gas turbine combustor |
EP1251313A3 (de) * | 2001-04-19 | 2002-11-20 | Mitsubishi Heavy Industries, Ltd. | Gasturbinenverbrennungsanlage |
EP1832812A2 (de) * | 2006-03-10 | 2007-09-12 | Rolls-Royce Deutschland Ltd & Co KG | Gasturbinenbrennkammerwand mit Dämpfung von Brennkammerschwingungen |
EP1832812A3 (de) * | 2006-03-10 | 2012-01-04 | Rolls-Royce Deutschland Ltd & Co KG | Gasturbinenbrennkammerwand mit Dämpfung von Brennkammerschwingungen |
EP2295864A1 (de) * | 2009-08-31 | 2011-03-16 | Alstom Technology Ltd | Verbrennungsvorrichtung einer Gasturbine |
US8839624B2 (en) | 2009-08-31 | 2014-09-23 | Alstom Technology Ltd. | Combustion device of a gas turbine including a plurality of passages and chambers defining helmholtz resonators |
FR2962586A1 (fr) * | 2010-07-09 | 2012-01-13 | Airbus Operations Sas | Panneau pour le traitement acoustique |
EP2837782A1 (de) | 2013-08-14 | 2015-02-18 | Alstom Technology Ltd | Dämpfer für eine Schwingungsdämpfung in einer Gasturbine |
EP2837783A1 (de) | 2013-08-14 | 2015-02-18 | Alstom Technology Ltd | Dämpfer für eine Schwingungsdämpfung in einer Gasturbine |
US9970659B2 (en) | 2013-08-14 | 2018-05-15 | Ansaldo Energia Ip Uk Limited | Damper for combustion oscillation damping in a gas turbine |
Also Published As
Publication number | Publication date |
---|---|
ATE232287T1 (de) | 2003-02-15 |
DE59709276D1 (de) | 2003-03-13 |
EP0892216B1 (de) | 2003-02-05 |
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