EP3921576A1 - Resonator, method for producing such a resonator, and combustor arrangement equipped with such a resonator - Google Patents
Resonator, method for producing such a resonator, and combustor arrangement equipped with such a resonatorInfo
- Publication number
- EP3921576A1 EP3921576A1 EP20714906.3A EP20714906A EP3921576A1 EP 3921576 A1 EP3921576 A1 EP 3921576A1 EP 20714906 A EP20714906 A EP 20714906A EP 3921576 A1 EP3921576 A1 EP 3921576A1
- Authority
- EP
- European Patent Office
- Prior art keywords
- resonator
- burner
- spring elements
- gas turbine
- annular
- 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
- 238000004519 manufacturing process Methods 0.000 title claims abstract description 10
- 238000009434 installation Methods 0.000 claims abstract description 5
- 239000011214 refractory ceramic Substances 0.000 claims abstract description 5
- 230000007704 transition Effects 0.000 claims description 15
- 238000000034 method Methods 0.000 claims description 4
- 238000000465 moulding Methods 0.000 claims description 3
- 230000002093 peripheral effect Effects 0.000 claims description 3
- 230000003068 static effect Effects 0.000 abstract 1
- 238000002485 combustion reaction Methods 0.000 description 6
- 238000013016 damping Methods 0.000 description 5
- PXHVJJICTQNCMI-UHFFFAOYSA-N Nickel Chemical compound [Ni] PXHVJJICTQNCMI-UHFFFAOYSA-N 0.000 description 2
- 230000000712 assembly Effects 0.000 description 2
- 238000000429 assembly Methods 0.000 description 2
- 238000012423 maintenance Methods 0.000 description 2
- 239000000463 material Substances 0.000 description 2
- 206010037660 Pyrexia Diseases 0.000 description 1
- 230000015572 biosynthetic process Effects 0.000 description 1
- 238000001816 cooling Methods 0.000 description 1
- 238000003745 diagnosis Methods 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 238000009413 insulation Methods 0.000 description 1
- 239000002184 metal Substances 0.000 description 1
- 229910052751 metal Inorganic materials 0.000 description 1
- 229910052759 nickel Inorganic materials 0.000 description 1
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
- F23R3/007—Continuous combustion chambers using liquid or gaseous fuel constructed mainly of ceramic components
-
- 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
- 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
- F23R3/42—Continuous combustion chambers using liquid or gaseous fuel characterised by the arrangement or form of the flame tubes or combustion chambers
- F23R3/60—Support structures; Attaching or mounting means
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2220/00—Application
- F05D2220/30—Application in turbines
- F05D2220/32—Application in turbines in gas turbines
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2240/00—Components
- F05D2240/35—Combustors or associated equipment
-
- 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 an annular resonator with a plurality of perforations for installation in a burner arrangement of a stationary gas turbine system.
- the invention also relates to a method for producing a resonator according to the invention and a burner arrangement for a gas turbine system with a burner having a burner unit, a transition line which is arranged downstream of the burner unit and is designed to feed the hot gas generated by the burner to a turbine conduct, and at least one such resonator.
- Burner arrangements are used in gas turbine systems to generate hot gas and to guide it to the turbine inlet.
- they include a transition line designed as a pipeline, which is also referred to as "transition” in specialist circles.
- the transition line is thermal during operation of the gas turbine system Accordingly, it is made of a high-temperature resistant material, usually a thin-walled nickel-based material with internal cooling channels, and has an internal layer system for thermal insulation (TBC + MCrAlY) so-called “basket” of the burner unit to arrange at least one ring-shaped resonator made of metal.
- the resonator is technically a weak point in the burner arrangement, as it regularly shows cracks and limits the service life of the "basket".
- the new manufacture and replacement of a resonator are very complex and cost-intensive Requirements for gas turbine systems with a further intensification of the diagnosis situation is to be expected, there is an object of the present invention in making the maintenance of burner assemblies easier and cheaper.
- the present invention creates a resonator of the type mentioned, which is characterized in that it is made of refractory ceramic.
- the resonator has a markedly less tendency to crack at the temperatures prevailing during the operation of a burner arrangement, as a result of which the maintenance effort and the costs are markedly reduced.
- the resonator advantageously has an outer circumferential surface that tapers conically in the axial direction, so that it can be inserted into an annular metallic jacket structure with a jacket surface that is also conically tapered and can be attached to it.
- a plurality of spring elements acting in the radial direction are preferably arranged on the outer circumferential surface of the resonator.
- Such spring elements allow radial and axial bracing of the resonator when it is inserted into a metallic shell structure, while maintaining an annular gap between resonator and shell structure, so that differences in thermal expansion can be compensated and the resonator can be fixed with limited force under all operating conditions.
- the spring elements are leaf springs which extend in the axial direction and are bent radially outward. In this way, a simple and inexpensive structure is achieved.
- the spring elements are advantageously uniformly spaced from one another in the circumferential direction, which enables the resonator to be centered within the jacket structure.
- the resonator can be made in one piece or composed of several ring segments.
- the present invention creates a method for producing a resonator according to the invention, in which in the context of the primary molding process of the ring-shaped resonator, preferably additively produced mold inserts are used to form the perforations.
- the perforations can be geometrically adjusted to the desired damping frequencies during the production of the resonator.
- parameters can be varied, such as the hole area ratio, that is, the ratio of all hole areas to the total area, the resonator thickness, the radius of the holes or the like.
- the size of the gap selected between the resonator and a metallic shell structure when installing the resonator also has an influence on the damping frequency.
- the present invention proposes a burner arrangement for a gas turbine system with a burner having the burner unit, a transition line which is arranged downstream of the burner unit and is designed to conduct the hot gas generated by the burner to a turbine, and at least one resonator according to the invention .
- the at least one resonator is preferably accommodated in a ringför-shaped metallic jacket structure with a cross-section that tapers conically in the downstream direction with radial and axial prestress, with spring elements being arranged between the resonator and the jacket structure.
- the radial and axial prestressing is advantageously brought up via a pressure element, in particular an annular pressure element, which is releasably fastened to the shell structure on the front side, in particular is screwed to it.
- This pressure element thus presses axially against the resonator (s) inserted into a jacket structure and tensions the spring elements with the desired pretension.
- the jacket structure can be formed by the burner unit or by the transition line itself or it can be provided as a separate component which is arranged between the burner unit and the transition line.
- Figure 1 is a sectional view of a portion of a known
- FIG. 2 shows a perspective view of a resonator according to a first embodiment of the present invention
- FIG. 3 shows a perspective exploded view of a partial area of a burner arrangement according to the invention which has resonators according to a second embodiment of the present invention.
- FIG. 4 is a sectional view of that shown in FIG.
- FIG. 1 shows an area of a known gas turbine system 1 in which a burner unit 2 is inserted into a housing 3 of the gas turbine system 1.
- the burner unit 2 is connected via a flange 4 to a connection housing 5, which in turn is screwed to the housing 3.
- the flange 4 can also be fastened directly to the housing 3 and accordingly the connection housing 5 can be dispensed with.
- the burner unit 2 comprises a burner 6 and a tubular combustion chamber 7 adjoining this downstream, which is often also referred to as a "basket" becomes.
- a metallic resonator 8 is provided, which is intended to reduce acoustic combustion vibrations.
- the outlet end of the combustion chamber 7 is connected to an inlet end of a transition line 9, also referred to as "transition”, which is held on the housing 3 via an adjusting and fixing device 10 and is designed to stream the hot gas generated by the burner 6 downwardly positioned turbine of the gas turbine arrangement 1.
- the burner unit 2 and the transition line 9 together form a burner arrangement.
- the gas turbine system 1 comprises several of these burner arrangements which supply the turbine with hot gas.
- the burner assemblies are subject to high thermal loads during the operation of the gas turbine system 1.
- the high tempera tures lead to the formation of cracks in the resonators 8, which is why the combustion chambers 7 must be regularly repaired or replaced. This is very time-consuming and costly.
- FIG 2 shows an annular resonator 8 according to a first embodiment of the present invention, which is made of refractory ceramic.
- the resonator 8 has an outer circumferential surface 11 which tapers conically in the axial direction A from an outer diameter D ai to an outer diameter D a 2 and an inner circumferential surface 12, which extends parallel to the outer circumferential surface 11 in front of it and thus also conically in the axial direction from an inner diameter Du is tapered to an inner diameter Di2.
- a plurality of perforations 13 are formed on the outer peripheral surface 11. The size, number, distribution and shape of the individual perforations 13 can be freely selected in the manufacture of the Re sonator 8 to achieve a desired damping frequency.
- FIGS. 3 and 4 show resonators 8 according to a second embodiment of the present invention, which are made of refractory ceramic analogously to the resonator 8 shown in FIG. 2 and are provided with perforations 13.
- the resonators 8 shown in FIG. 3 are not in one piece, but rather are composed of several ring segments 14.
- a plurality of spring elements 15 acting in the radial direction are positioned, which in the present case are designed as leaf springs extending in the axial direction, radially outwardly bent and arranged distributed uniformly over the outer circumferential surface 11.
- Vertie can be formed in the outer peripheral surface 11 of the resonator, although this is not mandatory Lich.
- the two resonators 8 shown in FIG. 3 are inserted axially one behind the other with the smaller outer diameter D a 2 first in a metallic jacket structure 16 so that the spring elements 15 come into engagement with the inner wall of the jacket structure 16.
- the resonators 8 are pushed into the shell structure 16 via a present ring-shaped pressure element 17 against the spring force of the spring elements 15, where up the pressure element 17 is taken using fastening screws 18 on the face of the shell structure 16 fastened.
- the resonators 8 are fixed while maintaining an annular gap 19 between the resonators 8 of the shell structure 16 while exercising a radial and axial bias.
- the size of the annular gap 19 is adjustable within certain limits and also has an effect on the damping frequency or damping frequencies of the resonators 8.
- the jacket structure 16 can basically form part of the combustion chamber 7 of the burner unit 2 or part of the transition line 9 or, as shown in FIGS.
- the resonator 8 shown in FIG. 2 can be mounted using a jacket structure 16, spring elements 15 and a pressure element 17.
Landscapes
- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Ceramic Engineering (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
- Soundproofing, Sound Blocking, And Sound Damping (AREA)
- Gas Burners (AREA)
Abstract
Description
Claims
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
DE102019205540.0A DE102019205540A1 (en) | 2019-04-17 | 2019-04-17 | Resonator, method for producing such and burner arrangement provided with such |
PCT/EP2020/057044 WO2020212039A1 (en) | 2019-04-17 | 2020-03-16 | Resonator, method for producing such a resonator, and combustor arrangement equipped with such a resonator |
Publications (2)
Publication Number | Publication Date |
---|---|
EP3921576A1 true EP3921576A1 (en) | 2021-12-15 |
EP3921576B1 EP3921576B1 (en) | 2023-11-15 |
Family
ID=70050040
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP20714906.3A Active EP3921576B1 (en) | 2019-04-17 | 2020-03-16 | Resonator, method for producing such a resonator, and combustor arrangement equipped with such a resonator |
Country Status (7)
Country | Link |
---|---|
US (1) | US11867103B2 (en) |
EP (1) | EP3921576B1 (en) |
KR (1) | KR102616048B1 (en) |
CN (1) | CN113710960A (en) |
DE (1) | DE102019205540A1 (en) |
PL (1) | PL3921576T3 (en) |
WO (1) | WO2020212039A1 (en) |
Families Citing this family (1)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
DE102020200204A1 (en) | 2020-01-09 | 2021-07-15 | Siemens Aktiengesellschaft | Ceramic resonator for combustion chamber systems and combustion chamber systems |
Family Cites Families (20)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
JPS6038530A (en) * | 1983-08-12 | 1985-02-28 | Hitachi Ltd | Combustor of gas turbine |
JP2647144B2 (en) * | 1988-06-22 | 1997-08-27 | 株式会社日立製作所 | Gas turbine combustor support structure |
US5291733A (en) * | 1993-02-08 | 1994-03-08 | General Electric Company | Liner mounting assembly |
GB2309296B (en) * | 1995-10-11 | 2000-02-09 | Europ Gas Turbines Ltd | Gas turbine engine combuster |
JP3930252B2 (en) * | 2000-01-07 | 2007-06-13 | 三菱重工業株式会社 | Gas turbine combustor |
US6547210B1 (en) * | 2000-02-17 | 2003-04-15 | Wright Medical Technology, Inc. | Sacrificial insert for injection molding |
EP1221574B2 (en) | 2001-01-09 | 2017-12-20 | Mitsubishi Heavy Industries, Ltd. | Gas turbine combustor |
DE102006026969A1 (en) * | 2006-06-09 | 2007-12-13 | Rolls-Royce Deutschland Ltd & Co Kg | Gas turbine combustor wall for a lean-burn gas turbine combustor |
DE102006053277B4 (en) * | 2006-11-03 | 2010-02-18 | Deutsches Zentrum für Luft- und Raumfahrt e.V. | Resonator device and combustion chamber device |
JP5291790B2 (en) * | 2009-02-27 | 2013-09-18 | 三菱重工業株式会社 | Combustor and gas turbine provided with the same |
US9310079B2 (en) * | 2010-12-30 | 2016-04-12 | Rolls-Royce North American Technologies, Inc. | Combustion liner with open cell foam and acoustic damping layers |
JP5804808B2 (en) * | 2011-07-07 | 2015-11-04 | 三菱日立パワーシステムズ株式会社 | Gas turbine combustor and its combustion vibration damping method |
US20160023375A1 (en) * | 2013-05-17 | 2016-01-28 | Core Cast, Llc | Slip mixture for 3d printed molds and 3d printing ceramic material |
EP2881667B1 (en) * | 2013-10-11 | 2017-04-26 | General Electric Technology GmbH | Helmholtz damper with air cooled seal for a gas turbine |
US9592918B2 (en) * | 2014-06-23 | 2017-03-14 | Rohr, Inc. | Acoustic liner |
CN106605103B (en) | 2014-09-09 | 2019-11-26 | 西门子公司 | The acoustic resistance damping system of burner for gas-turbine unit |
EP3048370A1 (en) | 2015-01-23 | 2016-07-27 | Siemens Aktiengesellschaft | Combustion chamber for a gas turbine engine |
DE102015216772A1 (en) * | 2015-09-02 | 2017-03-02 | Siemens Aktiengesellschaft | Method for manufacturing and assembling a resonator for a burner |
US10145561B2 (en) | 2016-09-06 | 2018-12-04 | General Electric Company | Fuel nozzle assembly with resonator |
US10584610B2 (en) * | 2016-10-13 | 2020-03-10 | General Electric Company | Combustion dynamics mitigation system |
-
2019
- 2019-04-17 DE DE102019205540.0A patent/DE102019205540A1/en not_active Withdrawn
-
2020
- 2020-03-16 US US17/602,572 patent/US11867103B2/en active Active
- 2020-03-16 WO PCT/EP2020/057044 patent/WO2020212039A1/en unknown
- 2020-03-16 EP EP20714906.3A patent/EP3921576B1/en active Active
- 2020-03-16 PL PL20714906.3T patent/PL3921576T3/en unknown
- 2020-03-16 CN CN202080028902.XA patent/CN113710960A/en active Pending
- 2020-03-16 KR KR1020217037034A patent/KR102616048B1/en active IP Right Grant
Also Published As
Publication number | Publication date |
---|---|
US20220178284A1 (en) | 2022-06-09 |
EP3921576B1 (en) | 2023-11-15 |
KR20210151206A (en) | 2021-12-13 |
KR102616048B1 (en) | 2023-12-21 |
PL3921576T3 (en) | 2024-04-08 |
DE102019205540A1 (en) | 2020-10-22 |
WO2020212039A1 (en) | 2020-10-22 |
US11867103B2 (en) | 2024-01-09 |
CN113710960A (en) | 2021-11-26 |
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