EP4058729A1 - Ceramic resonator for combustion chamber systems and combustion chamber system - Google Patents
Ceramic resonator for combustion chamber systems and combustion chamber systemInfo
- Publication number
- EP4058729A1 EP4058729A1 EP20828976.9A EP20828976A EP4058729A1 EP 4058729 A1 EP4058729 A1 EP 4058729A1 EP 20828976 A EP20828976 A EP 20828976A EP 4058729 A1 EP4058729 A1 EP 4058729A1
- Authority
- EP
- European Patent Office
- Prior art keywords
- ceramic
- resonator
- ceramic resonator
- cavities
- combustion chamber
- 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.)
- Pending
Links
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
- 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 resonator, in particular a Helmholtz resonator, which is used in combustion chambers, in particular in combustion chamber systems of turbines, in particular gas turbines.
- Tube and combustion chamber systems of stationary gas turbines generally consist of one or more combustion chamber components connected axially one behind the other between the burner outlet and the turbine inlet.
- the tube combustion chamber types from Siemens AG have a system made up of "Basket” and “Transition”. This system directs the combustion gases from the burner towards the turbine inlet. Due to the high combustion temperatures, the tubular combustion chamber components are usually based on thin-walled Ni-based materials with internal cooling channels and a layer system for thermal insulation (ceramic + metallic bonding layer).
- the Rohrbrennkam mersystems In or behind the flame area, the Rohrbrennkam mersystems have circumferentially arranged resonators to reduce acoustic combustion vibrations.
- the resonator area limits the service life of the respective component ("basket” or “transition”).
- the manufacture of the resonators is complex and expensive.
- the resonator area has relatively large cooling air surfaces and is intensively cooled or flowed through.
- the cooling air requirement is relatively high in relation to the overall Rohrbrennkam mersystem.
- the object is achieved by a ceramic resonator according to claim 1 and a combustion chamber system according to claim 16.
- the subclaims list further advantageous measures that can be combined with one another as required in order to achieve further advantages.
- Figure 1 shows a ceramic resonator
- Figure 2 shows a cross section according to Figure 1 and
- FIG. 3 shows a cross section of the ceramic resonator in the installed state of a combustion chamber system.
- the ceramic resonator according to the invention based on the Helmholtz principle replaces a metallic welded construction of a resonator system of a tubular combustion chamber.
- the ceramic resonator 1 according to the invention (Fig. 1) is a ceramic component that is ring-shaped (oval, circular) or as a one-piece ring, segmented or as a segmented ring, with internal cavities 16 ', 16 ", ... (Fig .2) is formed from.
- cavities 16 ', 16 ", ... are open to the inner surface 7, the hot gas side, in order to enable damping according to the Helmholtz principle.
- the size, shape, number, distribution and / or resonator necks of the cavities 16 ', 16'', ... are to be adapted and designed for the frequency to be damped. Size, shape, number, distribution development, resonator necks can be varied within the ceramic Resona sector 1.
- FIG. 1 shows a ceramic resonator 1 which, viewed preferably in the axial direction 10 (flow direction), is formed as a ring or ring-shaped with a circular or oval cross-section.
- the ceramic resonator 1 can also have a segmented structure, i.e. it can consist of two half-shells or several segments (not shown in each case).
- the ceramic resonator 1 has an outer surface 4 (cold gas side) and an inner surface 7 (hot gas side), with openings 13, 13 'on the inner surface 7 of resonator necks 14', ... which, in particular radially, in the ceramic Resonator 1 protrude and open into cavities 16 ', 16 ", ..., (Fig. 2, Fig. 3) are present.
- the inner surface 7 delimits a hot gas flow that flows in the axial flow direction 10 through the ceramic resonator 1 flows and with respect to it the ceramic resonator is preferably aligned concentrically.
- cavities 16 ', 16' ', ... which are preferably spherical and / or oval, cuboid and / or cube-shaped or have an otherwise curved surface and / or a different type of angular and angular geometry.
- the geometry of the cavities 16 ′, 16 ′′, ... used can be the same for each ceramic resonator 1, but can also be varied within the ceramic resonator 1.
- the cavities 16 ', 16 ",... are preferably arranged uniformly, as shown in FIGS. 1, 2, or unevenly distributed (not shown) and preferably have the same or different geometries with regard to the diameter of the resonator necks 14',. .., the length of the resonator necks 14 ', ... and / or the shape of the cavity 16', 16 ". Other distributions that deviate from the figures are possible.
- the cavities 16 ', 16' ', ... in the circumferential direction 12 are offset from one another and evenly arranged.
- the side surfaces 19 ', 19''of the ceramic resonator 1 are preferably conical and / or at right angles to the inner 7 and outer surface 4 in order to allow installation in a combustion chamber. chamber system 20 or resonator housing 23 (Fig. 3) to enable chen.
- the ceramic resonator 1 is or is preferably arranged in a corresponding bulge 29 as part of a metallic support structure 29 of the resonator housing 23 for the ceramic resonator 1 of a combustion chamber system 20 (FIG. 3). Again, the axial flow direction 10 of the hot gas is shown, whereas the direction 26 shows the direction of the cooling air starting from the compressor in the opposite direction.
- a refractory ceramic is preferably used as the ceramic for the resonator 1, preferably an Al 2 O 3 refractory ceramic.
- the porosity of the ceramic resonator 1 is preferably ⁇ 2 vol% and in particular ⁇ 20 vol%.
- the dimensions of an exemplary ceramic resonator 1 are preferably: inner diameter 400 mm, thickness 30 ... 40 mm, length 200 mm.
Landscapes
- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Ceramic Engineering (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Soundproofing, Sound Blocking, And Sound Damping (AREA)
- Physical Or Chemical Processes And Apparatus (AREA)
Abstract
Description
Claims
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
DE102020200204.5A DE102020200204A1 (en) | 2020-01-09 | 2020-01-09 | Ceramic resonator for combustion chamber systems and combustion chamber systems |
PCT/EP2020/085479 WO2021139958A1 (en) | 2020-01-09 | 2020-12-10 | Ceramic resonator for combustion chamber systems and combustion chamber system |
Publications (1)
Publication Number | Publication Date |
---|---|
EP4058729A1 true EP4058729A1 (en) | 2022-09-21 |
Family
ID=74003806
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP20828976.9A Pending EP4058729A1 (en) | 2020-01-09 | 2020-12-10 | Ceramic resonator for combustion chamber systems and combustion chamber system |
Country Status (4)
Country | Link |
---|---|
US (1) | US20230041092A1 (en) |
EP (1) | EP4058729A1 (en) |
DE (1) | DE102020200204A1 (en) |
WO (1) | WO2021139958A1 (en) |
Family Cites Families (18)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
GB2396687A (en) * | 2002-12-23 | 2004-06-30 | Rolls Royce Plc | Helmholtz resonator for combustion chamber use |
US7080514B2 (en) * | 2003-08-15 | 2006-07-25 | Siemens Power Generation,Inc. | High frequency dynamics resonator assembly |
JP2005076982A (en) * | 2003-08-29 | 2005-03-24 | Mitsubishi Heavy Ind Ltd | Gas turbine combustor |
US7984787B2 (en) * | 2009-01-23 | 2011-07-26 | Dresser-Rand Company | Fluid-carrying conduit and method with noise attenuation |
GB0907578D0 (en) * | 2009-05-05 | 2009-06-10 | Rolls Royce Plc | A damping assembly |
EP2282120A1 (en) * | 2009-06-26 | 2011-02-09 | Siemens Aktiengesellschaft | Combustion chamber assembly for dampening thermoacoustic oscillations, gas turbine and method for operating such a gas turbine |
US9310079B2 (en) * | 2010-12-30 | 2016-04-12 | Rolls-Royce North American Technologies, Inc. | Combustion liner with open cell foam and acoustic damping layers |
FR2980776B1 (en) * | 2011-10-03 | 2014-08-22 | Airbus Operations Sas | AIRCRAFT NACELLE COMPRISING A PANEL FOR ACOUSTIC TREATMENT INTEGRATING HOT AIR CHANNELS AND AT LEAST ONE ANNULAR CHANNEL |
US9163837B2 (en) * | 2013-02-27 | 2015-10-20 | Siemens Aktiengesellschaft | Flow conditioner in a combustor of a gas turbine engine |
FR3039147B1 (en) * | 2015-07-24 | 2017-08-25 | Aircelle Sa | ACOUSTICAL ATTENUATION PANEL IN CERAMIC OXIDE COMPOSITE MATERIAL WITH ELECTROCHIMICALLY CONVERTED METALLIC MATERIAL |
WO2018021996A1 (en) * | 2016-07-25 | 2018-02-01 | Siemens Aktiengesellschaft | Gas turbine engine with resonator rings |
US10145561B2 (en) * | 2016-09-06 | 2018-12-04 | General Electric Company | Fuel nozzle assembly with resonator |
US10612464B2 (en) * | 2017-03-07 | 2020-04-07 | United Technologies Corporation | Flutter inhibiting intake for gas turbine propulsion system |
EP3655636B1 (en) * | 2017-07-21 | 2021-11-24 | Dresser Rand Company | Acoustic attenuator for a turbomachine and methodology for additively manufacturing said acoustic attenuator |
EP3438540A1 (en) * | 2017-07-31 | 2019-02-06 | Siemens Aktiengesellschaft | A burner including an acoustic damper |
EP3674081B1 (en) * | 2018-12-31 | 2022-02-23 | Ansaldo Energia Switzerland AG | High-temperature resistant tiles and manufacturing method thereof |
DE102019204746A1 (en) * | 2019-04-03 | 2020-10-08 | Siemens Aktiengesellschaft | Heat shield tile with damping function |
DE102019205540A1 (en) * | 2019-04-17 | 2020-10-22 | Siemens Aktiengesellschaft | Resonator, method for producing such and burner arrangement provided with such |
-
2020
- 2020-01-09 DE DE102020200204.5A patent/DE102020200204A1/en not_active Withdrawn
- 2020-12-10 US US17/788,905 patent/US20230041092A1/en active Pending
- 2020-12-10 EP EP20828976.9A patent/EP4058729A1/en active Pending
- 2020-12-10 WO PCT/EP2020/085479 patent/WO2021139958A1/en unknown
Also Published As
Publication number | Publication date |
---|---|
DE102020200204A1 (en) | 2021-07-15 |
US20230041092A1 (en) | 2023-02-09 |
WO2021139958A1 (en) | 2021-07-15 |
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