US20140345283A1 - Combustion chamber for a gas turbine plant - Google Patents

Combustion chamber for a gas turbine plant Download PDF

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Publication number
US20140345283A1
US20140345283A1 US14/241,149 US201214241149A US2014345283A1 US 20140345283 A1 US20140345283 A1 US 20140345283A1 US 201214241149 A US201214241149 A US 201214241149A US 2014345283 A1 US2014345283 A1 US 2014345283A1
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US
United States
Prior art keywords
combustion chamber
resonator
wall
combustion
delivery port
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
Application number
US14/241,149
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English (en)
Inventor
Bernd Prade
Japp Van Kampen
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Siemens AG
Original Assignee
Siemens AG
Priority date (The priority date 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 date listed.)
Filing date
Publication date
Application filed by Siemens AG filed Critical Siemens AG
Assigned to SIEMENS AKTIENGESELLSCHAFT reassignment SIEMENS AKTIENGESELLSCHAFT ASSIGNMENT OF ASSIGNORS INTEREST (SEE DOCUMENT FOR DETAILS). Assignors: KAMPEN, JAAP VAN, DR., PRADE, BERND, DR.
Publication of US20140345283A1 publication Critical patent/US20140345283A1/en
Abandoned legal-status Critical Current

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    • 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
    • F23R3/02—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration
    • F23R3/16—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration with devices inside the flame tube or the combustion chamber to influence the air or gas flow
    • 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
    • F23R2900/03042—Film cooled combustion chamber walls or domes

Definitions

  • the invention relates to a combustion chamber for a gas turbine plant according to the preamble of claim 1 and to a correspondingly designed gas turbine plant according to claim 7 .
  • Gas turbine plants are composed essentially of a compressor, of a combustion chamber with a burner and of an expansion turbine.
  • a compressor In the compressor, sucked-in air is compressed before it is mixed with fuel in the combustion chamber in the following burner arranged in the compressor plenum, and this mixture is burnt.
  • the expansion turbine following the combustion chamber then extracts thermal energy from the combustion exhaust gases which have occurred in the burner and converts this into mechanical energy.
  • a generator capable of being coupled to the expansion turbine can convert this mechanical energy into electrical energy for current generation.
  • thermoacoustic vibrations of this kind in the combustion chamber present a problem in the design and, in particular, in the operation of gas turbine plants.
  • Helmholtz resonators which are composed of at least one resonator tube and of a resonator volume, are employed nowadays for damping. Helmholtz resonators of this kind damp the amplitude of vibrations with the Helmholtz frequency in specific frequency ranges as a function of the cross-sectional area and the length of the resonator tube and of the resonator volume. Helmholtz resonators as damping devices for limiting thermoacoustic vibrations in combustion chambers are known, for example, from EP 1 605 209 A1 or U.S. 2007/0125089 A1.
  • FIG. 1 shows, for example, the arrangement, known from U.S. 2007/0125089 A1, of Helmholtz resonators 20 on a ring of the combustion chamber wall 10 transversely to the flow direction.
  • the combustion chamber wall 10 is in this case of tubular form and separates the combustion chamber 1 from the surrounding compressor plenum 2 .
  • the perforations 22 in the combustion chamber wall 10 between resonator volume 21 and combustion chamber 1 form the resonator tubes of the Helmholtz resonators.
  • each Helmholtz resonator may have a plurality of resonator tubes or else only a single resonator tube.
  • these delivery ports 23 are arranged on that wall of the resonator volume 21 which lies opposite the resonator tubes 22 . These ports 23 make it possible that compressed air S can flow out of the compressor plenum 2 surrounding the combustion chamber into the resonator volume 21 and from there, via the resonator tubes 22 , into the combustion chamber 1 , thus barring the penetration of hot combustion gases into the resonator tubes 22 .
  • Helmholtz resonators with deliveries of barrier air via the volume body have the disadvantage that this barrier air flowing through the Helmholtz resonator can diminish its damping properties such that instabilities may occur when the burner is in operation.
  • this barrier air flowing through the Helmholtz resonator can diminish its damping properties such that instabilities may occur when the burner is in operation.
  • even a marked reduction in the damping properties has been found with an increasing velocity of the barrier air flowing through the resonator tubes.
  • a specific barrier air velocity in the resonator tubes is necessary in order to bring about a reliable barrier effect with respect to the combustion gases entering the resonator from the combustion chamber.
  • this type of delivery of barrier air makes it necessary to introduce from the compressor plenum a large fraction of air which, however, is then no longer available for actual combustion so as to reduce the flame temperature.
  • the object of the invention is to provide a combustion chamber which overcomes the disadvantages described above.
  • a combustion chamber designed according to the preamble of claim 1 and having at least one Helmholtz resonator has at least one delivery port which is provided in a region of the combustion chamber wall near the resonator tube mouth of the at least one resonator tube and is oriented such that the barrier air flowing through the delivery port flows over the resonator mouth
  • the injection, known from the prior art, of barrier air through the Helmholtz resonator may be dispensed with. Its damping properties are therefore no longer influenced by the barrier air flowing through, with the result that reliable damping of thermoacoustic vibrations is achieved, thus ultimately lengthening the service life of the combustion chamber and therefore of the entire gas turbine plant.
  • the barrier air delivery designed according to the invention less air from the compressor plenum is required, as compared with the known versions, so that, overall, the NOx and CO pollutant emission of the gas turbine plant also becomes lower.
  • a barrier film is built up in front of the resonator tube mouths on the combustion chamber side, and barrier air can thus be used more effectively as a reliable barrier against the inflow of hot combustion gases from the combustion chamber into the Helmholtz resonators, and at the same time the damping properties of the Helmholtz resonators are not influenced by the barrier air.
  • Gas turbine plants equipped with such combustion chambers can thus have as low pollutant emissions as possible in all load ranges, while working at maximum efficiency.
  • FIG. 1 shows diagrammatically a damping device known from the prior art
  • FIG. 2 shows diagrammatically a first version according to the invention of a damping device
  • FIG. 3 shows diagrammatically a second version according to the invention of a damping device
  • FIG. 4 shows diagrammatically a third version according to the invention of a damping device
  • FIG. 5 shows diagrammatically a fourth version according to the invention of a damping device.
  • the barrier air S is not routed through the damping device 20 , but instead delivery ports 23 ′ and/or 23 ′′ are provided and oriented in the combustion chamber wall 10 such that the barrier air S flowing through the delivery ports 23 ′, 23 ′′ flows over the resonator tube mouth M in the region of the combustion chamber inner wall virtually in a similar way to film cooling.
  • FIG. 2 shows a first embodiment in which the resonator tube mouths M are set back in the combustion chamber wall 10 with respect to the combustion chamber inner wall 10 ′ in a defined area 10 ′′ away from the combustion chamber inner space, and the delivery port 23 ′ is oriented such that the barrier air S is injected, virtually parallel to the flow direction of the combustion gases G, into the space between the area 10 ′′ and the combustion chamber inner wall 10 ′ such that it flows completely over the setback resonator tube mouths M of the resonator tubes 22 .
  • a barrier air film is thus formed which, even with a low mass flow of barrier air, very effectively prevents the penetration of hot combustion gases into the Helmholtz resonator 20 .
  • injection of the barrier air takes place, as indicated in FIG. 2 , through a tubular port 23 ′ in the upstream side wall in the downstream direction of the combustion gases, the injected barrier air is entrained by the stream of combustion exhaust gases and an especially effective barrier film is thus obtained.
  • a second delivery port 23 ′′ lying opposite the first delivery port 23 ′ may be provided, as indicated in FIG. 3 , which is oriented such that the barrier air S is injected virtually parallel to and opposite to the flow direction of the combustion exhaust gases G so that even resonators with a greater extent in the flow direction can still be barred effectively.
  • the combustion chamber wall 10 has on the setback area 10 ′′, level with the combustion chamber inner wall 10 ′, an overlap L with the setback areas 10 ′′, the extent of the resonators can likewise be increased, without an additional opposite row of barrier air bores being necessary.
  • the delivery port 23 ′ or else other delivery ports such as, for example, the delivery port 23 ′′, shown in FIG. 3 , is or are arranged in the combustion chamber wall 10 such that their axis A is inclined with respect to the resonator tube mouth M.
  • additional impact cooling of the resonator wall is achieved, which may be expedient particularly in regions of the combustion chamber where an especially large amount of heat is introduced into the combustion chamber wall.
  • FIG. 2 to FIG. 5 show in each case various advantageous embodiments which individually or else in combination implement the idea according to the invention, to be precise that of ensuring an efficient and reliable barrier against the penetration of hot gases from the combustion chamber into the damping devices without the passage of barrier air via the damping device.
  • the invention also embraces embodiments in which, contrary to the exemplary embodiments shown, the deliveries of barrier air lie so near to the resonator tube mouths that they form a direct component of each of the resonator tube mouths and are thus virtually integrated into each resonator tube mouth.

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  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
US14/241,149 2011-09-01 2012-08-14 Combustion chamber for a gas turbine plant Abandoned US20140345283A1 (en)

Applications Claiming Priority (3)

Application Number Priority Date Filing Date Title
DE102011081962.2 2011-09-01
DE102011081962A DE102011081962A1 (de) 2011-09-01 2011-09-01 Brennkammer für eine Gasturbinenanlage
PCT/EP2012/065849 WO2013029981A1 (de) 2011-09-01 2012-08-14 Brennkammer für eine gasturbinenanlage

Publications (1)

Publication Number Publication Date
US20140345283A1 true US20140345283A1 (en) 2014-11-27

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Family Applications (1)

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US14/241,149 Abandoned US20140345283A1 (en) 2011-09-01 2012-08-14 Combustion chamber for a gas turbine plant

Country Status (6)

Country Link
US (1) US20140345283A1 (de)
EP (1) EP2732214A1 (de)
CN (1) CN103765105A (de)
DE (1) DE102011081962A1 (de)
RU (1) RU2014112332A (de)
WO (1) WO2013029981A1 (de)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20150247426A1 (en) * 2014-02-28 2015-09-03 Alstom Technology Ltd Acoustic damping device for chambers with grazing flow

Families Citing this family (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20160003162A1 (en) * 2013-02-28 2016-01-07 Siemens Aktiengesellschaft Damping device for a gas turbine, gas turbine and method for damping thermoacoustic oscillations
CN104566477B (zh) * 2014-12-31 2019-02-01 北京华清燃气轮机与煤气化联合循环工程技术有限公司 用于燃气轮机火焰筒的调频装置及燃气轮机火焰筒
CN104595928B (zh) * 2015-01-23 2020-02-14 北京华清燃气轮机与煤气化联合循环工程技术有限公司 扩散燃烧室声学火焰筒
CN104676649A (zh) * 2015-02-05 2015-06-03 北京华清燃气轮机与煤气化联合循环工程技术有限公司 一种阻尼热声振荡声学火焰筒
WO2016135833A1 (ja) * 2015-02-23 2016-09-01 三菱重工業株式会社 減衰装置、燃焼器及びガスタービン
US10513984B2 (en) 2015-08-25 2019-12-24 General Electric Company System for suppressing acoustic noise within a gas turbine combustor
US10197275B2 (en) 2016-05-03 2019-02-05 General Electric Company High frequency acoustic damper for combustor liners
JP7289752B2 (ja) * 2019-08-01 2023-06-12 三菱重工業株式会社 音響減衰器、筒アッセンブリ、燃焼器、ガスタービン及び筒アッセンブリの製造方法

Citations (1)

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US7926278B2 (en) * 2006-06-09 2011-04-19 Rolls-Royce Deutschland Ltd & Co Kg Gas-turbine combustion chamber wall for a lean-burning gas-turbine combustion chamber

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US4135603A (en) * 1976-08-19 1979-01-23 United Technologies Corporation Sound suppressor liners
US6530221B1 (en) 2000-09-21 2003-03-11 Siemens Westinghouse Power Corporation Modular resonators for suppressing combustion instabilities in gas turbine power plants
JP3962554B2 (ja) * 2001-04-19 2007-08-22 三菱重工業株式会社 ガスタービン燃焼器及びガスタービン
WO2004051063A1 (ja) * 2002-12-02 2004-06-17 Mitsubishi Heavy Industries, Ltd. ガスタービン燃焼器、及びこれを備えたガスタービン
JP2005076982A (ja) * 2003-08-29 2005-03-24 Mitsubishi Heavy Ind Ltd ガスタービン燃焼器
EP1605209B1 (de) 2004-06-07 2010-08-04 Siemens Aktiengesellschaft Brennkammer mit einer Dämpfungseinrichtung zur Dämpfung von thermoakustischen Schwingungen

Patent Citations (1)

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Publication number Priority date Publication date Assignee Title
US7926278B2 (en) * 2006-06-09 2011-04-19 Rolls-Royce Deutschland Ltd & Co Kg Gas-turbine combustion chamber wall for a lean-burning gas-turbine combustion chamber

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20150247426A1 (en) * 2014-02-28 2015-09-03 Alstom Technology Ltd Acoustic damping device for chambers with grazing flow
US9429042B2 (en) * 2014-02-28 2016-08-30 General Electric Technology Gmbh Acoustic damping device for chambers with grazing flow

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Publication number Publication date
EP2732214A1 (de) 2014-05-21
RU2014112332A (ru) 2015-10-10
CN103765105A (zh) 2014-04-30
DE102011081962A1 (de) 2013-03-07
WO2013029981A1 (de) 2013-03-07

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