WO2019027508A1 - Doublure de chambre de combustion à atténuation de bruit pour moteur à turbine à combustion - Google Patents

Doublure de chambre de combustion à atténuation de bruit pour moteur à turbine à combustion Download PDF

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Publication number
WO2019027508A1
WO2019027508A1 PCT/US2018/021102 US2018021102W WO2019027508A1 WO 2019027508 A1 WO2019027508 A1 WO 2019027508A1 US 2018021102 W US2018021102 W US 2018021102W WO 2019027508 A1 WO2019027508 A1 WO 2019027508A1
Authority
WO
WIPO (PCT)
Prior art keywords
acoustic
combustion
panel
resonant
channel
Prior art date
Application number
PCT/US2018/021102
Other languages
English (en)
Inventor
Francois-Xavier Jette
Marc Furi
Original Assignee
Siemens Aktiengesellschaft
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
Priority claimed from PCT/US2017/016420 external-priority patent/WO2018144008A1/fr
Priority claimed from PCT/US2017/016391 external-priority patent/WO2018144006A1/fr
Application filed by Siemens Aktiengesellschaft filed Critical Siemens Aktiengesellschaft
Publication of WO2019027508A1 publication Critical patent/WO2019027508A1/fr

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
    • F23R3/005—Combined with pressure or heat exchangers
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/08—Cooling; Heating; Heat-insulation
    • F01D25/12—Cooling
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02K—JET-PROPULSION PLANTS
    • F02K1/00—Plants characterised by the form or arrangement of the jet pipe or nozzle; Jet pipes or nozzles peculiar thereto
    • F02K1/78—Other construction of jet pipes
    • F02K1/82—Jet pipe walls, e.g. liners
    • F02K1/822—Heat insulating structures or liners, cooling arrangements, e.g. post combustion liners; Infrared radiation suppressors
    • 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
    • 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
    • F05D2230/00—Manufacture
    • F05D2230/30—Manufacture with deposition of material
    • 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
    • F05D2230/00—Manufacture
    • F05D2230/50—Building or constructing in particular ways
    • F05D2230/53—Building or constructing in particular ways by integrally manufacturing a component, e.g. by milling from a billet or one piece construction
    • 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
    • F05D2260/00—Function
    • F05D2260/20—Heat transfer, e.g. cooling
    • F05D2260/221—Improvement of heat transfer
    • F05D2260/2212—Improvement of heat transfer by creating turbulence
    • 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
    • F05D2260/00—Function
    • F05D2260/20—Heat transfer, e.g. cooling
    • F05D2260/221—Improvement of heat transfer
    • F05D2260/2214—Improvement of heat transfer by increasing the heat transfer surface
    • 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
    • F23R2900/00018—Manufacturing combustion chamber liners or subparts
    • 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
    • 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
    • F23R2900/03044—Impingement cooled combustion chamber walls or subassemblies
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T50/00—Aeronautics or air transport
    • Y02T50/60—Efficient propulsion technologies, e.g. for aircraft

Definitions

  • the meta-material or meta-structure constructions that are employed in the exemplary acoustic combustor liners, including anechoic combustor liners, disclosed herein, allow the collective, coupled groups of resonant structures to damp acoustic waves of frequencies, including frequencies below or equal to 1000 Hertz, even though individual resonant structures have cavity volumes and dimensions that are smaller than that of corresponding, known single-chamber Helmholtz resonator.
  • FIG. 1 A block diagram illustrating an exemplary embodiment of the invention.
  • FIG. 1 A block diagram illustrating an exemplary embodiment of the invention.
  • FIG. 1 A block diagram illustrating an exemplary embodiment of the invention.
  • FIG. 1 A block diagram illustrating an exemplary embodiment of the invention.
  • FIG. 1 A block diagram illustrating an exemplary embodiment of the invention.
  • FIG. 1 A block diagram illustrating an exemplary embodiment of the invention.
  • FIG. 1 A combustion turbine engine, having compressor, combustion, and turbine section stages.
  • FIG. 1 A block diagram illustrating an exemplary embodiments of the invention.
  • FIG. 1 A block diagram illustrating an exemplary embodiments of the invention.
  • FIG. 1 A block diagram illustrating an exemplary embodiments of the invention.
  • FIG. 1 A block diagram illustrating an exemplary embodiments of the invention.
  • FIG. 1 A block diagram illustrating an exemplary embodiment of the invention.
  • FIG. 1 A block diagram illustrating an exemplary embodiment of the invention.
  • FIG. 1 A block diagram illustrating an exemplary embodiment of the
  • FIG. 4 is a cross-sectional, elevational view of meta-structure resonant structures, incorporating sub -wavelength, quarter-wave resonant tubes, of the panel of FIG. 3, taken along 4-4 thereof;
  • portions of the air-cooled combustor liner has a monolithic, three-dimensional lattice structure of selectively oriented metallic surfaces, and webs with locally varying lattice density, and asymmetrical- and serpentine-shaped passages formed between the metallic webs for providing acoustic compliance for incident pressure waves.
  • the component lattice structure locally varies one or more of channel size, shape, volume, or arrangement, for locally varying vibration damping properties of the component.
  • at least portions of the acoustic damper are incorporated within three-dimensional lattice structure, by forming solid surfaces that define interior boundaries of the meta-structure, resonant structures.
  • the combustion section 26 comprises a plurality of equally circumferentially spaced combustors 38. Longitudinal axes of the combustors 38 are arranged to extend generally in the radial directions.
  • the combustors 38 are encased within a combustor liner 38 A. Respectively, the inlets of the combustors 38 are at their radially outermost ends and their outlets are at their radially innermost ends of the combustor liner 38 A.
  • the casing of the combustion section 26 incorporates an air intake plenum, which is in communication with the compressor section compressed air output, for providing compressed air to the inlets of the combustors 38.
  • the second face 304 includes a plurality of channels 308 that are formed in the panel 302; each respectively defining a channel cavity,
  • the air cooling passages 310 in the second face 304 of the panel 302 transport pressurized cooling air from the first side 306, directly through the panel or via internal passages formed within the panel, toward the combustion gasses.
  • the cavities of the resonant structures of the resonant tubes 322, 324, and 326 are in communication with their common channel cavity 321.
  • the channel cavity 321 is a main quarter-wave resonator tube, to which are coupled secondary resonant quarter-wave resonator tubes 322, 324, and 326.
  • the channel cavity 321 and each of the respective resonant structure cavities of resonant tubes 322, 324, and 326 define cavity dimensions LR, WR and VR that are all smaller than the wavelength(s) of the damped acoustic wave or the bandwidth of acoustic waves in the combustion gas that correspond to frequencies below or equal to 1000 Hertz.
  • a resonant structure having internal cavity dimensions of 2mm X 6mm X 30-40mm attenuates a 660 Hertz-frequency acoustic wave.
  • the resonators 342, 346, and 350 are shown having cylindrical cross-sections, some embodiments have non-cylindrical cross sections.
  • the cavities of the resonant structures of the Helmholtz resonators 342, 346 and 350 are in communication with their common channel cavity 341.
  • the channel cavity 341 is a main quarter-wave resonator tube, to which are coupled secondary Helmholtz resonators 342, 346 and 350.
  • construction of an exemplary air- cooled panel is initiated by placing, and optionally securing on a work surface 701, such as workpiece welding surface of an additive-manufacture, laser welder, a flat, first planar sheet 702, having an outer surface 704, and an inner surface 706.
  • the first planar sheet 702 has optional array of pre-formed cooling and/or acoustic damper channel holes 760.
  • a three- dimensional lattice structure 710 is formed on the inner surface 706 of the first planar sheet 702, by building up a web of solid surfaces with filaments 712, 713, 714, 715, 716, 718, 719, such as by an additive manufacture process. Interstices or spaces between those solid surfaces form asymmetrical- and serpentine-shaped passages 720, 722, 724 that can comprise resonant structure cavities for one or more acoustic dampers.
  • step 804 these modeled engine structures of step 802 are used in a computer workstation, running commercially available computational fluid-dynamics (CFD) software to perform simulations of intake air flow from the compressor section, 24 localized mass flow of cooling-air bleed from the compressor section 24 to the ACL 300, fuel and air mixture in its combustor premixers and combustion gas flow dynamics within its combustion chamber formed within the ACL 300, as well as the transition 39.
  • the modeled combustion gas flow dynamics include, by way of non-limiting example combustion backpressure dynamics within the combustor liner and upstream into the premixer and acoustic emissions generated during combustion.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Soundproofing, Sound Blocking, And Sound Damping (AREA)

Abstract

Doublure de chambre de combustion acoustique destinée à un moteur à turbine à combustion atténuant les vibrations d'ondes acoustiques générées par des variations de pression dynamique dans le gaz de combustion. Un panneau renferme un amortisseur acoustique à méta-structure, également appelée méta-matière, qui comprend un canal formé dans le panneau, qui est en communication avec le gaz de combustion. Le canal délimite une cavité de canal. Une pluralité de structures résonantes sont formées dans le canal, délimitant respectivement des cavités de structure résonante qui sont en communication avec la cavité de canal. La cavité de canal et chacune des cavités de structure résonante respectives délimitent des dimensions de cavité qui sont toutes inférieures à la(aux) longueur(s) d'onde des ondes acoustiques amorties. Les méta-structures des amortisseurs acoustiques ralentissent la vitesse de son perçu à travers leurs cavités de canal et de structure ramifiée. Le son perçu inférieur est atténué par la combinaison structurale composite de cavités individuelles plus petites que celles qui seraient autrement nécessaires pour une atténuation par des résonateurs classiques à chambre unique.
PCT/US2018/021102 2017-02-03 2018-03-06 Doublure de chambre de combustion à atténuation de bruit pour moteur à turbine à combustion WO2019027508A1 (fr)

Applications Claiming Priority (4)

Application Number Priority Date Filing Date Title
PCT/US2017/016420 WO2018144008A1 (fr) 2017-02-03 2017-02-03 Chambre de combustion avec pré-mélangeur en treillis tridimensionnel
PCT/US2017/016391 WO2018144006A1 (fr) 2017-02-03 2017-02-03 Procédé pour normaliser un mélange carburant-air au sein d'une chambre de combustion
PCT/US2017/044827 WO2018144065A1 (fr) 2017-02-03 2017-08-01 Composant refroidi par air pour moteur à turbine, à réseau tridimensionnel monolithique à densité variable
USPCT/US2017/044827 2017-08-01

Publications (1)

Publication Number Publication Date
WO2019027508A1 true WO2019027508A1 (fr) 2019-02-07

Family

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Family Applications (3)

Application Number Title Priority Date Filing Date
PCT/US2017/044827 WO2018144065A1 (fr) 2017-02-03 2017-08-01 Composant refroidi par air pour moteur à turbine, à réseau tridimensionnel monolithique à densité variable
PCT/US2017/044792 WO2018144064A1 (fr) 2017-02-03 2017-08-01 Panneau refroidi par air pour turbine, à treillis tridimensionnel monolithique, et son procédé de fabrication
PCT/US2018/021102 WO2019027508A1 (fr) 2017-02-03 2018-03-06 Doublure de chambre de combustion à atténuation de bruit pour moteur à turbine à combustion

Family Applications Before (2)

Application Number Title Priority Date Filing Date
PCT/US2017/044827 WO2018144065A1 (fr) 2017-02-03 2017-08-01 Composant refroidi par air pour moteur à turbine, à réseau tridimensionnel monolithique à densité variable
PCT/US2017/044792 WO2018144064A1 (fr) 2017-02-03 2017-08-01 Panneau refroidi par air pour turbine, à treillis tridimensionnel monolithique, et son procédé de fabrication

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CN108796205B (zh) * 2018-09-12 2023-08-04 珠海格力电工有限公司 一种退火线的风冷装置和退火方法
US11753952B2 (en) * 2019-10-04 2023-09-12 Raytheon Technologies Corporation Support structure for a turbine vane of a gas turbine engine
US11466593B2 (en) 2020-01-07 2022-10-11 Raytheon Technologies Corporation Double walled stator housing
FR3111414B1 (fr) * 2020-06-15 2022-09-02 Safran Helicopter Engines Production par fabrication additive de pièces complexes
EP4006306B1 (fr) * 2020-11-27 2024-05-15 Ansaldo Energia Switzerland AG Conduit de transition pour une chambre de combustion de turbine à gaz

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EP1568869A1 (fr) * 2002-12-02 2005-08-31 Mitsubishi Heavy Industries, Ltd. Chambre de combustion de turbine a gaz et turbine a gaz equipee de cette chambre de combustion
EP1666795A1 (fr) * 2004-11-24 2006-06-07 Rolls-Royce Plc Atténuateur acoustique
EP2385303A1 (fr) * 2010-05-03 2011-11-09 Alstom Technology Ltd Dispositif de combustion pour turbine à gaz
US20140053559A1 (en) * 2012-07-31 2014-02-27 Alstom Technology Ltd Near-wall roughness for damping devices reducing pressure oscillations in combustion systems
EP2865948A1 (fr) * 2013-10-25 2015-04-29 Alstom Technology Ltd Dispositif d'amortissement type quart d'onde pour chambre de combustion d'une turbine à gaz
EP2977679A1 (fr) * 2014-07-22 2016-01-27 United Technologies Corporation Paroi de chambre de combustion pour un moteur à turbine à gaz et procédé d'amortissement acoustique

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Publication number Publication date
WO2018144065A1 (fr) 2018-08-09
WO2018144064A1 (fr) 2018-08-09

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