US20150101332A1 - Combustion chamber of a gas turbine with improved acoustic damping - Google Patents
Combustion chamber of a gas turbine with improved acoustic damping Download PDFInfo
- Publication number
- US20150101332A1 US20150101332A1 US14/510,501 US201414510501A US2015101332A1 US 20150101332 A1 US20150101332 A1 US 20150101332A1 US 201414510501 A US201414510501 A US 201414510501A US 2015101332 A1 US2015101332 A1 US 2015101332A1
- Authority
- US
- United States
- Prior art keywords
- chamber
- dampers
- acoustic
- gas turbine
- section
- 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.)
- Abandoned
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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
- F23R3/02—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration
- F23R3/26—Controlling the air 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
- F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
-
- 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
- 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 is related to the acoustic damping of combustions dynamics.
- Combustion dynamics in the meaning of this application comprises pulsations, acoustic oscillations, pressure and velocity fluctuations and what is called in the everyday language noise.
- the terms “combustions dynamics” and “noise” are sometimes used synonymously.
- Combustion dynamics occur for example in gas turbines at different places or chambers, where combustion dynamics occur.
- places or chambers are the combustor chamber, a mixing chamber, a plenum and air channels.
- the term “chamber” is used and comprises all locations where combustion dynamics occur.
- a gas for example a mixture of fuel and air or exhaust gas
- Burning air and fuel in the combustion chamber causes further combustion dynamics.
- acoustic damping devices like a Helmholtz resonator, a half-wave tube, a quarter-wave tube or other types of damping devices with or without flow through of gas.
- acoustic damping devices have one or more resonance frequencies. If under operation of the gas turbine the combustions dynamics stimulate the resonance frequencies of the acoustic damping devices, the combustion dynamics are reduced or damped.
- a chamber of a gas turbine with combustion dynamics comprising several acoustic dampers circumferentially being arranged around an opening of the chamber by arranging at least two acoustic dampers of the same type in one section of the chamber covering an angle of 60°.
- the acoustic dampers are arranged in an annular ring around the opening.
- dampers that are tuned to the same damping frequency, for example 90 Hz+ ⁇ 2%, are of the same type.
- Helmholtz dampers and quarter-wave dampers may be of the same type in the meaning of the claimed invention.
- a further advantageous embodiment is characterized in that an angle between two adjacent acoustic dampers is equal to or greater than 10°.
- Another advantageous embodiment is characterized in that in one section of the chamber at least six burners and uppermost ten burners are arranged.
- these burners are selected from the group of dual fuel burners for gas turbines.
- the applicable acoustic dampers are not restricted to Helmholtz dampers with one or more damping volumes but may be half-wave length dampers, quarter-wave length dampers and other acoustic dampers with one or more damping volumes.
- the claimed invention may be applied to combustion chambers, mixing chambers, a plenum and/or air channels of a gas turbine.
- FIG. 1 a first embodiment of the claimed invention
- FIG. 2 a second embodiment of the claimed invention.
- T1 for example may be tuned to a damping frequency of 90 Hz
- T2 for example may be tuned to a damping frequency of 100 Hz and so on.
- dual fuel burners B1 for gas turbines are arranged in each section 1, 2, 3, 4, 5, 6 in the annular ring 14 besides the several types of acoustic dampers T1, T2, T3, T4, T5 and T6.
- acoustic dampers T1, T2, T3, T4, T5 and T6 are arranged in each section.
- eight burners B1 are arranged in section 4 of FIG. 1 and FIG. 2 for example.
- only one burner B1 is marked with an own reference numeral.
- the sections 4, 5 and 6 each comprise in clockwise direction one T4-, T5-, T1- and T3-type damper.
- each comprise in clockwise direction a T6, a T1-, a T6- and a T5-type damper.
Landscapes
- 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)
- Gas Burners (AREA)
Abstract
A combustion chamber of a gas turbine includes an optimized arrangement of acoustic dampers.
Description
- This application claims priority to European Patent Application 13188229.2 filed Oct. 11, 2013, the contents of which are hereby incorporated in its entirety.
- The invention is related to the acoustic damping of combustions dynamics. Combustion dynamics in the meaning of this application comprises pulsations, acoustic oscillations, pressure and velocity fluctuations and what is called in the everyday language noise. The terms “combustions dynamics” and “noise” are sometimes used synonymously.
- Combustion dynamics occur for example in gas turbines at different places or chambers, where combustion dynamics occur. Examples for such places or chambers are the combustor chamber, a mixing chamber, a plenum and air channels. For reasons of simplification subsequently the term “chamber” is used and comprises all locations where combustion dynamics occur. In these chambers a gas (for example a mixture of fuel and air or exhaust gas) flows with high velocity which causes combustion dynamics. Burning air and fuel in the combustion chamber causes further combustion dynamics.
- To reduce these combustion dynamics it is well known in the art, to install acoustic damping devices like a Helmholtz resonator, a half-wave tube, a quarter-wave tube or other types of damping devices with or without flow through of gas.
- These acoustic damping devices have one or more resonance frequencies. If under operation of the gas turbine the combustions dynamics stimulate the resonance frequencies of the acoustic damping devices, the combustion dynamics are reduced or damped.
- It is an objective of the claimed invention to place the acoustic damping devices to achieve optimal damping under given constraints.
- This objective is achieved by a chamber of a gas turbine with combustion dynamics, comprising several acoustic dampers circumferentially being arranged around an opening of the chamber by arranging at least two acoustic dampers of the same type in one section of the chamber covering an angle of 60°. Advantageously the acoustic dampers are arranged in an annular ring around the opening.
- By arranging the dampers in this manner the combustion dynamics of the gas turbine in operation could be damped more effectively.
- It is advantageous to place in one section of the chamber covering an angle of 60° at uppermost six (6) acoustic dampers
- Further it is possible to place in one section one, two, three, four, five or six types of acoustic dampers. All dampers that are tuned to the same damping frequency, for example 90 Hz+−2%, are of the same type. This means that Helmholtz dampers and quarter-wave dampers may be of the same type in the meaning of the claimed invention.
- A further advantageous embodiment is characterized in that an angle between two adjacent acoustic dampers is equal to or greater than 10°.
- Another advantageous embodiment is characterized in that in one section of the chamber at least six burners and uppermost ten burners are arranged. Advantageously these burners are selected from the group of dual fuel burners for gas turbines.
- Arranging the dampers of each section of an opening in this way, has led to improved reduction of combustion dynamics.
- The applicable acoustic dampers are not restricted to Helmholtz dampers with one or more damping volumes but may be half-wave length dampers, quarter-wave length dampers and other acoustic dampers with one or more damping volumes.
- The claimed invention may be applied to combustion chambers, mixing chambers, a plenum and/or air channels of a gas turbine.
- Further advantages and details of the claimed invention are subsequently described in conjunction with the drawings and their description.
- The figures show:
-
FIG. 1 a first embodiment of the claimed invention, -
FIG. 2 a second embodiment of the claimed invention. - Both figures illustrate a front view of a
combustor chamber 10 of a gas turbine. Thecombustor chamber 10 comprises anopening 12 covering a center angle of 360°. This center angle is divided in sixsections - Distributed in the claimed manner are several types T1, T2, T3, T4, T4 and T6 of acoustic dampers in an
annular ring 14. The type T1 for example may be tuned to a damping frequency of 90 Hz, whereas the type T2 for example may be tuned to a damping frequency of 100 Hz and so on. - In both figures dual fuel burners B1 for gas turbines are arranged in each
section annular ring 14 besides the several types of acoustic dampers T1, T2, T3, T4, T5 and T6. Advantageously depending on the number of acoustic dampers in one section between six and ten burners are arranged in each section. Insection 4 ofFIG. 1 andFIG. 2 for example, eight burners B1 are arranged. For the sake of lucidity, insections - In
FIG. 1 thesections - In
FIG. 2 for example thesections - In
FIG. 2 for example thesections - By adapting the patterns of dampers in each section to a specific gas turbine a great reduction of combustion dynamics may be achieved.
Claims (8)
1. A chamber of a gas turbine comprising several acoustic dampers circumferentially arranged around an opening of the chamber, wherein in one section of the chamber covering an angle (α) of 60° at least two acoustic dampers are arranged.
2. The chamber according to claim 1 , wherein in one section of the chamber covering an angle (α) of 60° at uppermost six acoustic dampers are arranged.
3. The chamber according to claim 1 , wherein in one section up to six types of acoustic dampers are arranged.
4. The chamber according to claim 1 , wherein in an angle (β) between two adjacent acoustic dampers is equal to or greater than 10°.
5. The chamber according to claim 1 , wherein in one section of the chamber at least six burners and uppermost ten burners are arranged.
6. The chamber according to claim 1 , wherein the acoustic dampers are selected from a group comprising Helmholtz dampers, half-wave length dampers, quarter-wave length dampers.
7. The chamber according to claim 1 , wherein the acoustic dampers comprise one or more damping volumes.
8. The chamber according to claim 1 , further comprising a combustion chamber, a mixing chamber, a plenum and/or air channels of a gas turbine.
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
EP13188229.2A EP2860451A1 (en) | 2013-10-11 | 2013-10-11 | Combustion chamber of a gas turbine with improved acoustic damping |
EP13188229.2 | 2013-10-11 |
Publications (1)
Publication Number | Publication Date |
---|---|
US20150101332A1 true US20150101332A1 (en) | 2015-04-16 |
Family
ID=49354497
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
US14/510,501 Abandoned US20150101332A1 (en) | 2013-10-11 | 2014-10-09 | Combustion chamber of a gas turbine with improved acoustic damping |
Country Status (3)
Country | Link |
---|---|
US (1) | US20150101332A1 (en) |
EP (1) | EP2860451A1 (en) |
CN (1) | CN104676645A (en) |
Cited By (1)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US20170292709A1 (en) * | 2014-10-06 | 2017-10-12 | Siemens Aktiengesellschaft | Combustor and method for damping vibrational modes under high-frequency combustion dynamics |
Families Citing this family (2)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US10941939B2 (en) | 2017-09-25 | 2021-03-09 | General Electric Company | Gas turbine assemblies and methods |
EP3760925A1 (en) * | 2019-07-01 | 2021-01-06 | Ansaldo Energia Switzerland AG | Damper for a combustor assembly of a gas turbine assembly, combustor assembly comprising said damper and method for manufacturing a damper for a combustor assembly |
Citations (18)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US6464489B1 (en) * | 1997-11-24 | 2002-10-15 | Alstom | Method and apparatus for controlling thermoacoustic vibrations in a combustion system |
US20020152740A1 (en) * | 2001-04-24 | 2002-10-24 | Mitsubishi Heavy Industries Ltd. | Gas turbine combustor having bypass passage |
US20020152751A1 (en) * | 2001-04-19 | 2002-10-24 | Mitsubishi Heavy Industries, Ltd. | Gas turbine combustor |
US6530221B1 (en) * | 2000-09-21 | 2003-03-11 | Siemens Westinghouse Power Corporation | Modular resonators for suppressing combustion instabilities in gas turbine power plants |
US20050034918A1 (en) * | 2003-08-15 | 2005-02-17 | Siemens Westinghouse Power Corporation | High frequency dynamics resonator assembly |
US20070169992A1 (en) * | 2006-01-25 | 2007-07-26 | Siemens Power Generation, Inc. | Acoustic resonator with impingement cooling tubes |
US20070283700A1 (en) * | 2006-06-09 | 2007-12-13 | Miklos Gerendas | Gas-turbine combustion chamber wall for a lean-burning gas-turbine combustion chamber |
US20080041058A1 (en) * | 2006-08-18 | 2008-02-21 | Siemens Power Generation, Inc. | Resonator device at junction of combustor and combustion chamber |
US20080087019A1 (en) * | 2006-06-01 | 2008-04-17 | Macquisten Michael A | Combustion chamber for a gas turbine engine |
US20090094985A1 (en) * | 2007-09-14 | 2009-04-16 | Siemens Power Generation, Inc. | Non-Rectangular Resonator Devices Providing Enhanced Liner Cooling for Combustion Chamber |
US20090282831A1 (en) * | 2008-05-15 | 2009-11-19 | Adnan Eroglu | Method for reducing emissions from a combustor |
US20110302924A1 (en) * | 2010-06-11 | 2011-12-15 | Ching-Pang Lee | Cooled conduit for conveying combustion gases |
US20120006028A1 (en) * | 2010-07-08 | 2012-01-12 | Ching-Pang Lee | Damping resonator with impingement cooling |
US20120102963A1 (en) * | 2010-10-29 | 2012-05-03 | Robert Corr | Gas turbine combustor with mounting for helmholtz resonators |
US20120198854A1 (en) * | 2011-02-09 | 2012-08-09 | Reinhard Schilp | Resonator system with enhanced combustor liner cooling |
US20130074501A1 (en) * | 2011-09-23 | 2013-03-28 | Siemens Energy, Inc. | Combustor resonator section with an internal thermal barrier coating and method of fabricating the same |
US8631656B2 (en) * | 2008-03-31 | 2014-01-21 | General Electric Company | Gas turbine engine combustor circumferential acoustic reduction using flame temperature nonuniformities |
US20150020498A1 (en) * | 2013-07-19 | 2015-01-22 | Reinhard Schilp | Cooling cover for gas turbine damping resonator |
Family Cites Families (4)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US7584617B2 (en) * | 2006-03-17 | 2009-09-08 | Siemens Energy, Inc. | Monitoring health of a combustion dynamics sensing system |
US8408004B2 (en) * | 2009-06-16 | 2013-04-02 | General Electric Company | Resonator assembly for mitigating dynamics in gas turbines |
US8413443B2 (en) * | 2009-12-15 | 2013-04-09 | Siemens Energy, Inc. | Flow control through a resonator system of gas turbine combustor |
US20130074471A1 (en) * | 2011-09-22 | 2013-03-28 | General Electric Company | Turbine combustor and method for temperature control and damping a portion of a combustor |
-
2013
- 2013-10-11 EP EP13188229.2A patent/EP2860451A1/en not_active Withdrawn
-
2014
- 2014-10-09 US US14/510,501 patent/US20150101332A1/en not_active Abandoned
- 2014-10-10 CN CN201410856317.5A patent/CN104676645A/en active Pending
Patent Citations (18)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US6464489B1 (en) * | 1997-11-24 | 2002-10-15 | Alstom | Method and apparatus for controlling thermoacoustic vibrations in a combustion system |
US6530221B1 (en) * | 2000-09-21 | 2003-03-11 | Siemens Westinghouse Power Corporation | Modular resonators for suppressing combustion instabilities in gas turbine power plants |
US20020152751A1 (en) * | 2001-04-19 | 2002-10-24 | Mitsubishi Heavy Industries, Ltd. | Gas turbine combustor |
US20020152740A1 (en) * | 2001-04-24 | 2002-10-24 | Mitsubishi Heavy Industries Ltd. | Gas turbine combustor having bypass passage |
US20050034918A1 (en) * | 2003-08-15 | 2005-02-17 | Siemens Westinghouse Power Corporation | High frequency dynamics resonator assembly |
US20070169992A1 (en) * | 2006-01-25 | 2007-07-26 | Siemens Power Generation, Inc. | Acoustic resonator with impingement cooling tubes |
US20080087019A1 (en) * | 2006-06-01 | 2008-04-17 | Macquisten Michael A | Combustion chamber for a gas turbine engine |
US20070283700A1 (en) * | 2006-06-09 | 2007-12-13 | Miklos Gerendas | Gas-turbine combustion chamber wall for a lean-burning gas-turbine combustion chamber |
US20080041058A1 (en) * | 2006-08-18 | 2008-02-21 | Siemens Power Generation, Inc. | Resonator device at junction of combustor and combustion chamber |
US20090094985A1 (en) * | 2007-09-14 | 2009-04-16 | Siemens Power Generation, Inc. | Non-Rectangular Resonator Devices Providing Enhanced Liner Cooling for Combustion Chamber |
US8631656B2 (en) * | 2008-03-31 | 2014-01-21 | General Electric Company | Gas turbine engine combustor circumferential acoustic reduction using flame temperature nonuniformities |
US20090282831A1 (en) * | 2008-05-15 | 2009-11-19 | Adnan Eroglu | Method for reducing emissions from a combustor |
US20110302924A1 (en) * | 2010-06-11 | 2011-12-15 | Ching-Pang Lee | Cooled conduit for conveying combustion gases |
US20120006028A1 (en) * | 2010-07-08 | 2012-01-12 | Ching-Pang Lee | Damping resonator with impingement cooling |
US20120102963A1 (en) * | 2010-10-29 | 2012-05-03 | Robert Corr | Gas turbine combustor with mounting for helmholtz resonators |
US20120198854A1 (en) * | 2011-02-09 | 2012-08-09 | Reinhard Schilp | Resonator system with enhanced combustor liner cooling |
US20130074501A1 (en) * | 2011-09-23 | 2013-03-28 | Siemens Energy, Inc. | Combustor resonator section with an internal thermal barrier coating and method of fabricating the same |
US20150020498A1 (en) * | 2013-07-19 | 2015-01-22 | Reinhard Schilp | Cooling cover for gas turbine damping resonator |
Cited By (2)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US20170292709A1 (en) * | 2014-10-06 | 2017-10-12 | Siemens Aktiengesellschaft | Combustor and method for damping vibrational modes under high-frequency combustion dynamics |
US10775043B2 (en) * | 2014-10-06 | 2020-09-15 | Siemens Aktiengesellschaft | Combustor and method for damping vibrational modes under high-frequency combustion dynamics |
Also Published As
Publication number | Publication date |
---|---|
CN104676645A (en) | 2015-06-03 |
EP2860451A1 (en) | 2015-04-15 |
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AS | Assignment |
Owner name: ALSTOM TECHNOLOGY LTD, SWITZERLAND Free format text: ASSIGNMENT OF ASSIGNORS INTEREST;ASSIGNORS:BOTHIEN, MIRKO RUBEN;SCHUERMANS, BRUNO;SIGNING DATES FROM 20141105 TO 20141106;REEL/FRAME:034134/0088 |
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Owner name: GENERAL ELECTRIC TECHNOLOGY GMBH, SWITZERLAND Free format text: CHANGE OF NAME;ASSIGNOR:ALSTOM TECHNOLOGY LTD;REEL/FRAME:039714/0578 Effective date: 20151102 |
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STCB | Information on status: application discontinuation |
Free format text: ABANDONED -- FAILURE TO RESPOND TO AN OFFICE ACTION |