EP0971172A1 - Chambre de combustion pour turbine à gaz avec paroi à structure silencieuse - Google Patents

Chambre de combustion pour turbine à gaz avec paroi à structure silencieuse Download PDF

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Publication number
EP0971172A1
EP0971172A1 EP98810656A EP98810656A EP0971172A1 EP 0971172 A1 EP0971172 A1 EP 0971172A1 EP 98810656 A EP98810656 A EP 98810656A EP 98810656 A EP98810656 A EP 98810656A EP 0971172 A1 EP0971172 A1 EP 0971172A1
Authority
EP
European Patent Office
Prior art keywords
openings
combustion chamber
wall
perforated plate
combustion
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
Application number
EP98810656A
Other languages
German (de)
English (en)
Other versions
EP0971172B1 (fr
Inventor
Jakob Prof. Dr. Keller
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.)
General Electric Technology GmbH
Original Assignee
ABB Alstom Power Switzerland Ltd
ABB Asea Brown Boveri Ltd
Asea Brown Boveri AB
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 ABB Alstom Power Switzerland Ltd, ABB Asea Brown Boveri Ltd, Asea Brown Boveri AB filed Critical ABB Alstom Power Switzerland Ltd
Priority to DE59810343T priority Critical patent/DE59810343D1/de
Priority to EP98810656A priority patent/EP0971172B1/fr
Publication of EP0971172A1 publication Critical patent/EP0971172A1/fr
Application granted granted Critical
Publication of EP0971172B1 publication Critical patent/EP0971172B1/fr
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02M—SUPPLYING COMBUSTION ENGINES IN GENERAL WITH COMBUSTIBLE MIXTURES OR CONSTITUENTS THEREOF
    • F02M35/00—Combustion-air cleaners, air intakes, intake silencers, or induction systems specially adapted for, or arranged on, internal-combustion engines
    • F02M35/12—Intake silencers ; Sound modulation, transmission or amplification
    • F02M35/1255—Intake silencers ; Sound modulation, transmission or amplification using resonance
    • F02M35/1261—Helmholtz resonators
    • 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
    • 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
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02B—INTERNAL-COMBUSTION PISTON ENGINES; COMBUSTION ENGINES IN GENERAL
    • F02B77/00—Component parts, details or accessories, not otherwise provided for
    • F02B77/11—Thermal or acoustic insulation
    • F02B77/13—Acoustic insulation
    • 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
    • F23R3/002—Wall structures
    • 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
    • G10K11/162—Selection of materials
    • G10K11/168—Plural layers of different materials, e.g. sandwiches
    • 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
    • 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
    • F01N2490/00—Structure, disposition or shape of gas-chambers
    • F01N2490/15—Plurality of resonance or dead chambers
    • F01N2490/155—Plurality of resonance or dead chambers being disposed one after the other in flow direction
    • 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
    • F05B2260/20—Heat transfer, e.g. cooling
    • F05B2260/201—Heat transfer, e.g. cooling by impingement of a fluid
    • 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 present invention relates to the field of gas turbines. It affects a combustion chamber for a gas turbine, in which combustion chamber the hot combustion gases a combustion zone are enclosed by inner walls, which are cooled by cooling air supplied outside the inner walls.
  • Such a combustion chamber is in the form of a secondary combustion chamber e.g. from the Document EP-A1 0 669 500 of the applicant is known.
  • Gas turbines can cause pressure vibrations during operation under certain conditions or acoustic vibrations that occur in terms of frequency Range of several kHz, e.g. 1.8 kHz or around 5 kHz. Such Vibrations prove to be disruptive to the operation and are therefore undesirable.
  • a way to dampen or suppress such vibrations consists in providing fluidic means in the combustion chamber, which influence the flow of hot gases in that the acoustic vibrations are not excited or only to a small extent.
  • Helmholtz resonators on the combustion chamber attach to the vibrations as damping elements couple and dampen the vibrations or disappear completely bring.
  • a gas turbine combustor is described in US Pat. No. 5,644,918, in the case of the cooling air leading within the combustion chamber Double jacket and on the front of the combustion chamber in the area of the burner by pulling in additional dividing walls Helmholtz resonators 48 and 56 are formed, the constrictions 50 and 58 in connection with the combustion chamber stand, but are otherwise completely completed, so that a Flow of cooling air through the resonator rooms does not take place.
  • the task is thereby in a combustion chamber of the type mentioned solved that at least in a partial area on the outside of the inner walls one spaced from the inner walls, substantially parallel to the inner walls extending perforated plate is arranged, which together with the associated Inner wall forms a closed damping volume that the inner walls in the region of the damping volume, a plurality of distributed ones has first openings through which the damping volume with the
  • the combustion zone of the combustion chamber communicates with the perforated plate has a plurality of distributed second openings through which Cooling air flows into the damping volume from the outside and acts like a Impact cooling between the first openings on the opposite outside the inner wall hits, and that the distance between the perforated plate and the inner wall and the geometric dimensions of the first openings so are chosen so that the first openings together with the damping volume form a plurality of interconnected Helmholtz resonators and as a silencer for acoustic vibrations in the combustion chamber Act.
  • the essence of the invention is a plurality of interconnected Helmholtz resonators by arranging two parallel ones To create perforated plates.
  • the one perforated plate, the relatively large openings At the same time, the damping tubes of the individual resonators form the inner wall of the Combustion chamber itself.
  • the other, outside perforated plate bounds together with the inner wall the intervening, interconnected damping volumes of the individual resonators.
  • the relatively small openings on the outside Perforated plate is flowed through by cooling air, which on the one hand the resonators stabilized thermally and frequency and on the other hand by impact highly effective impingement cooling of the inner wall on the outside of the inner wall enables.
  • the additional effort to create the resonators exists in doing so - when the large openings in the Inner wall already exist - just from attaching the outer one Perforated plate.
  • a first preferred embodiment of the combustion chamber according to the invention is characterized in that the geometric dimensions of each first openings and the periodic intervals between the first openings are chosen essentially the same.
  • the individual partial resonators are in this case, all tuned to the same damping frequency, so that for the damping arrangement overall a high damping in a relative results in a narrow frequency range.
  • a second preferred embodiment of the combustion chamber according to the invention is characterized in that the geometric dimensions of each first openings and / or the distance between the perforated plate and the inner wall in the Area of the individual first openings and / or the periodic spacing of the individual first openings with each other to produce a widened Damping frequency band selected differently within a range of values become.
  • the distribution of values for the individual partial resonators means that the overall arrangement of the frequency range in which a noticeable attenuation takes place, significantly broadened, which is advantageous when the combustion chamber vibrations scatter more in frequency.
  • the first openings For common frequency values of combustion chamber vibrations in the range of several kHz are the first openings as through holes with a length of a few millimeters and a diameter of a few millimeters.
  • the periodic distance between adjacent first openings is a few millimeters, and the distance of the perforated plate from the inner wall is also a few millimeters.
  • the length of the first openings is about 5 mm, the Diameter of the first openings about 4.3 mm, the periodic spacing of the first openings between each other about 10 mm, and the distance between the Perforated plate and the inner wall about 5 mm.
  • the second openings are chosen so small that there is sufficient Pressure drop for the cooling air flowing through results.
  • the diameter is preferred the second openings are smaller than 1 mm, in particular approximately 0.7 mm.
  • the damping behavior is particularly advantageous if according to another Embodiment the combustion chamber is designed as a secondary combustion chamber, if the combustion chamber is in the combustion zone and an upstream Inflow zone is divided when the inflow zone is in a step-like manner Transition to the combustion zone expanded when the combustion zone in the Area of the step-like transition delimited by a radial inner wall and when the perforated plate is arranged on the outside of the radial inner wall is.
  • a secondary combustion chamber is shown in a simplified longitudinal section, which is known from EP-A1 0 669 500, and which is preferred for implementation the invention is suitable.
  • the combustion chamber 10 includes a combustion zone 23, which of an inner wall extending in the axial direction 12 and a radial inner wall 17 is limited.
  • the inflow zone 20 is delimited by an inner wall 15. Protrudes into the inflow zone 20 a fuel lance 18 from the side, a nozzle at the front end 19 for fuel injection.
  • the inner walls 12, 15 and 17 are from an outer wall 11 extending in the axial direction.
  • a cooling air duct 14 remains free, through what cooling air against the flow direction of the hot gases in between the inner wall 15 and the outer wall 11 formed extended space 16 streams.
  • the inner wall 12 is convectively cooled by the cooling air.
  • the cooling air flows from the space 16 through openings 21 in the inner wall 15 in the inflow zone 20, and through openings 22 in the inner wall 17 into the combustion zone 23, and thereby effects effusion cooling.
  • a Helmholtz resonator arrangement can be integrated, which is simultaneously an effective Cooling of the inner wall 17 ensured.
  • On the outside of the radial inner wall 17 is a perforated plate according to FIG. 2 at a distance (A in FIG. 3) 24 arranged in parallel, which together with the radial inner wall 17 Includes (annular) damping volume 26.
  • the inner wall 17 has one A plurality of more or less regularly distributed openings 27 on the identical to the openings 22 for the effusion cooling in the combustion chamber 1 can be, but also different geometric dimensions can have.
  • openings 27 each act as a damping tube of a Helmholtz partial resonator, which consists of the respective opening 27 and the underlying partial volume of the damping volume 26 is formed.
  • the total damping volume 26 and the entirety of the openings 27 can be understood as individual Helmholtz resonators, their individual damping volumes are interconnected to form the damping volume 26.
  • the perforated plate 24 has two more besides the limitation of the damping volume important tasks.
  • the openings 25 provided in the perforated plate 24 allow cooling air to flow into the damping volume 26 from the space 16.
  • the incoming cooling air cools the Helmholtz resonator arrangement.
  • the openings 25 are relative to the openings 27 offset or arranged "on gap". This hits the damping volume 26 incoming cooling air to the openings 25 opposite Outside of the inner wall 17, which leads to effective impingement cooling of the inner wall 17 leads.
  • the diameter D2 of the openings 25 (FIG. 3) is opposite the diameter D1 is comparatively small. This ensures that the cooling air flowing through suffers a sufficient pressure drop.
  • the resonance frequency of the resonator arrangement or the partial resonators is in the essentially by the distance A, the thickness B of the inner wall 17 or the length of the openings 27, the diameter of the openings 27 and the periodic Distance L (Fig. 3) of the openings 27 determined.
  • the openings 27 are through holes with a length B of a few millimeters and a diameter D1 of a few Millimeters trained.
  • the periodic distance L between neighboring ones Openings 27 is a few millimeters, and the distance A of the perforated plate 24 of the inner wall 17 is also a few millimeters.
  • FIGS. 4 and 5 The damping behavior of the individual for the values from the table Partial resonators is shown in FIGS. 4 and 5.
  • Fig. 4 shows the relative attenuation power over frequency.
  • Fig. 5 shows the displacement amplitude in the damping tube (Opening 27) above the frequency. one can see that both curves are pronounced Have maximum at the desired frequency of 5500 Hz.
  • the resonator arrangement according to FIGS. 2 and 3 requires a cooling air flow that is large enough to withstand a heat-related deviation of the resonance frequency from the prevent constructively determined value. Such a cooling air flow is in everyone Case sufficient for cooling the inner wall 17.
  • the damping capacity of the individual opening 27 is large enough to dampen the overall arrangement to extend to a wider frequency range. This can be done by a certain Scattering range for the values A, B, D1 and L can be chosen to be different Realize resonance frequencies of the individual partial resonators.
  • the length of the Openings 25 are not as important as the pressure drop across them Openings are sufficiently large.
  • the invention results in a combustion chamber which, with good acoustic Damping ensures efficient cooling of the inner walls and at the same time can be made compact. It goes without saying that the Helmholtz resonator arrangement in the context of the invention also on others Place of the inner walls can be arranged.

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  • 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)
  • Turbine Rotor Nozzle Sealing (AREA)
EP98810656A 1998-07-10 1998-07-10 Chambre de combustion pour turbine à gaz avec paroi à structure silencieuse Expired - Lifetime EP0971172B1 (fr)

Priority Applications (2)

Application Number Priority Date Filing Date Title
DE59810343T DE59810343D1 (de) 1998-07-10 1998-07-10 Brennkammer für eine Gasturbine mit schalldämpfender Wandstruktur
EP98810656A EP0971172B1 (fr) 1998-07-10 1998-07-10 Chambre de combustion pour turbine à gaz avec paroi à structure silencieuse

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP98810656A EP0971172B1 (fr) 1998-07-10 1998-07-10 Chambre de combustion pour turbine à gaz avec paroi à structure silencieuse

Publications (2)

Publication Number Publication Date
EP0971172A1 true EP0971172A1 (fr) 2000-01-12
EP0971172B1 EP0971172B1 (fr) 2003-12-03

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DE (1) DE59810343D1 (fr)

Cited By (17)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US6351947B1 (en) * 2000-04-04 2002-03-05 Abb Alstom Power (Schweiz) Combustion chamber for a gas turbine
EP1221574A2 (fr) * 2001-01-09 2002-07-10 Mitsubishi Heavy Industries, Ltd. Chambre de combustion de turbine à gaz
EP1342953A1 (fr) * 2002-03-07 2003-09-10 Siemens Aktiengesellschaft Turbine à gaz
GB2390150A (en) * 2002-06-26 2003-12-31 Alstom Reheat combustion system for a gas turbine including an accoustic screen
WO2004079264A1 (fr) * 2003-03-07 2004-09-16 Alstom Technology Ltd Bruleur de premelange
WO2004101975A1 (fr) * 2003-05-15 2004-11-25 Alstom Technology Ltd Dispositif d'isolation phonique dans un canal d'ecoulement
US6964170B2 (en) 2003-04-28 2005-11-15 Pratt & Whitney Canada Corp. Noise reducing combustor
DE102006026969A1 (de) * 2006-06-09 2007-12-13 Rolls-Royce Deutschland Ltd & Co Kg Gasturbinenbrennkammerwand für eine mager-brennende Gasturbinenbrennkammer
US7549290B2 (en) 2004-11-24 2009-06-23 Rolls-Royce Plc Acoustic damper
EP2273196A2 (fr) 2009-07-08 2011-01-12 Rolls-Royce Deutschland Ltd & Co KG Tête pour chambre de combustion d'une turbine à gaz
WO2014151045A1 (fr) 2013-03-15 2014-09-25 President And Fellows Of Harvard College Feuille auxétique à faible porosité
US9022726B2 (en) 2010-06-25 2015-05-05 Alstom Technology Ltd Thermally loaded, cooled component
WO2016112366A1 (fr) 2015-01-09 2016-07-14 President And Fellows Of Harvard College Structures gaufrées à coefficient de poisson négatif
JP2016520784A (ja) * 2013-03-15 2016-07-14 プレジデント アンド フェローズ オブ ハーバード カレッジ 繰り返しの細長い開口パターンを有するボイド構造
US10603866B2 (en) 2015-01-09 2020-03-31 President And Fellows Of Harvard College Hybrid dimple-and-void auxetic structures with engineered patterns for customized NPR behavior
JPWO2019021483A1 (ja) * 2017-07-28 2020-05-28 イビデン株式会社 吸音部材、車両用部品及び自動車
US10843505B2 (en) 2015-01-09 2020-11-24 President And Fellows Of Harvard College Zero-porosity NPR structure and tuning of NPR structure for particular localities

Families Citing this family (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2559942A1 (fr) 2011-08-19 2013-02-20 Rolls-Royce Deutschland Ltd & Co KG Tête de chambre de combustion d'une turbine à gaz dotée d'un refroidissement et d'un amortissement

Citations (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3848697A (en) * 1972-07-04 1974-11-19 Aerospatiale Acoustic damping and cooling of turbojet exhaust ducts
US4199936A (en) * 1975-12-24 1980-04-29 The Boeing Company Gas turbine engine combustion noise suppressor
FR2447069A1 (fr) * 1979-01-16 1980-08-14 Westeel Guy Perfectionnements aux dispositifs d'insonorisation disposes dans des ecoulements fluides
DE3318863A1 (de) * 1983-05-25 1984-12-13 Erich 8480 Weiden Bielefeldt Kraftmaschine mit gasturbine
DE3700444A1 (de) * 1987-01-09 1988-07-21 Siegfried W Schilling Heizkessel
EP0576717A1 (fr) * 1992-07-03 1994-01-05 Abb Research Ltd. Chambre de combustion de turbine à gaz
US5528904A (en) * 1994-02-28 1996-06-25 Jones; Charles R. Coated hot gas duct liner
EP0843090A2 (fr) * 1996-11-13 1998-05-20 ROLLS-ROYCE plc Chemise pour une tubulure de jet

Patent Citations (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3848697A (en) * 1972-07-04 1974-11-19 Aerospatiale Acoustic damping and cooling of turbojet exhaust ducts
US4199936A (en) * 1975-12-24 1980-04-29 The Boeing Company Gas turbine engine combustion noise suppressor
FR2447069A1 (fr) * 1979-01-16 1980-08-14 Westeel Guy Perfectionnements aux dispositifs d'insonorisation disposes dans des ecoulements fluides
DE3318863A1 (de) * 1983-05-25 1984-12-13 Erich 8480 Weiden Bielefeldt Kraftmaschine mit gasturbine
DE3700444A1 (de) * 1987-01-09 1988-07-21 Siegfried W Schilling Heizkessel
EP0576717A1 (fr) * 1992-07-03 1994-01-05 Abb Research Ltd. Chambre de combustion de turbine à gaz
US5528904A (en) * 1994-02-28 1996-06-25 Jones; Charles R. Coated hot gas duct liner
EP0843090A2 (fr) * 1996-11-13 1998-05-20 ROLLS-ROYCE plc Chemise pour une tubulure de jet

Cited By (32)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US6351947B1 (en) * 2000-04-04 2002-03-05 Abb Alstom Power (Schweiz) Combustion chamber for a gas turbine
US6907736B2 (en) 2001-01-09 2005-06-21 Mitsubishi Heavy Industries, Ltd. Gas turbine combustor having an acoustic energy absorbing wall
EP1221574A2 (fr) * 2001-01-09 2002-07-10 Mitsubishi Heavy Industries, Ltd. Chambre de combustion de turbine à gaz
EP1221574A3 (fr) * 2001-01-09 2003-04-02 Mitsubishi Heavy Industries, Ltd. Chambre de combustion de turbine à gaz
WO2003074936A1 (fr) * 2002-03-07 2003-09-12 Siemens Aktiengesellschaft Turbine a gaz
CN1320314C (zh) * 2002-03-07 2007-06-06 西门子公司 燃气轮机
US7246493B2 (en) 2002-03-07 2007-07-24 Siemens Aktiengesellschaft Gas turbine
EP1342953A1 (fr) * 2002-03-07 2003-09-10 Siemens Aktiengesellschaft Turbine à gaz
GB2390150A (en) * 2002-06-26 2003-12-31 Alstom Reheat combustion system for a gas turbine including an accoustic screen
US6981358B2 (en) 2002-06-26 2006-01-03 Alstom Technology Ltd. Reheat combustion system for a gas turbine
WO2004079264A1 (fr) * 2003-03-07 2004-09-16 Alstom Technology Ltd Bruleur de premelange
US6964170B2 (en) 2003-04-28 2005-11-15 Pratt & Whitney Canada Corp. Noise reducing combustor
WO2004101975A1 (fr) * 2003-05-15 2004-11-25 Alstom Technology Ltd Dispositif d'isolation phonique dans un canal d'ecoulement
US7913936B2 (en) 2003-05-15 2011-03-29 Alstom Technology Ltd Device for sound attenuation in a flow duct
US7549290B2 (en) 2004-11-24 2009-06-23 Rolls-Royce Plc Acoustic damper
DE102006026969A1 (de) * 2006-06-09 2007-12-13 Rolls-Royce Deutschland Ltd & Co Kg Gasturbinenbrennkammerwand für eine mager-brennende Gasturbinenbrennkammer
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
DE102009032277A1 (de) 2009-07-08 2011-01-20 Rolls-Royce Deutschland Ltd & Co Kg Brennkammerkopf einer Gasturbine
EP2273196A2 (fr) 2009-07-08 2011-01-12 Rolls-Royce Deutschland Ltd & Co KG Tête pour chambre de combustion d'une turbine à gaz
US8677757B2 (en) 2009-07-08 2014-03-25 Rolls-Royce Deutschland Ltd & Co Kg Combustion chamber head of a gas turbine
EP2400115B1 (fr) * 2010-06-25 2019-05-29 Ansaldo Energia Switzerland AG Composant chargé de chaleur refroidi
US9022726B2 (en) 2010-06-25 2015-05-05 Alstom Technology Ltd Thermally loaded, cooled component
JP2016520784A (ja) * 2013-03-15 2016-07-14 プレジデント アンド フェローズ オブ ハーバード カレッジ 繰り返しの細長い開口パターンを有するボイド構造
JP2016514781A (ja) * 2013-03-15 2016-05-23 プレジデント アンド フェローズ オブ ハーバード カレッジ 低孔隙率オーゼティックシート
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JPWO2019021483A1 (ja) * 2017-07-28 2020-05-28 イビデン株式会社 吸音部材、車両用部品及び自動車
EP3660834A4 (fr) * 2017-07-28 2021-03-10 Ibiden Co., Ltd Élément absorbant acoustique, composant pour véhicule, et automobile

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EP0971172B1 (fr) 2003-12-03

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