[go: up one dir, main page]

WO2015022222A1 - Écran thermique comportant un résonateur de helmholtz - Google Patents

Écran thermique comportant un résonateur de helmholtz Download PDF

Info

Publication number
WO2015022222A1
WO2015022222A1 PCT/EP2014/066720 EP2014066720W WO2015022222A1 WO 2015022222 A1 WO2015022222 A1 WO 2015022222A1 EP 2014066720 W EP2014066720 W EP 2014066720W WO 2015022222 A1 WO2015022222 A1 WO 2015022222A1
Authority
WO
WIPO (PCT)
Prior art keywords
heat shield
helmholtz resonator
support structure
resonator
expansion
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.)
Ceased
Application number
PCT/EP2014/066720
Other languages
German (de)
English (en)
Inventor
Andreas Böttcher
Sabine GRENDEL
Andre Kluge
Claus Krusch
Thomas-Dieter Tenrahm
Daniel Vogtmann
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
Siemens Corp
Original Assignee
Siemens AG
Siemens Corp
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, Siemens Corp filed Critical Siemens AG
Publication of WO2015022222A1 publication Critical patent/WO2015022222A1/fr
Anticipated expiration legal-status Critical
Ceased legal-status Critical Current

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
    • 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
    • F23R3/42—Continuous combustion chambers using liquid or gaseous fuel characterised by the arrangement or form of the flame tubes or combustion chambers
    • F23R3/60—Support structures; Attaching or mounting 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
    • 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

  • Heat shield with at least one Helmholtz resonator The invention relates to a heat shield for a combustion chamber, in particular a gas turbine.
  • the heat shield comprises a support structure and a number of heat shield elements, wherein the heat shield elements are substantially surface-mounted while leaving expansion gaps, and are fastened detachably to the support structure by means of stone holders.
  • Each heat shield element has a cold side facing the support structure and a hot side which is opposite the cold side and can be charged with a hot medium. The hot side is connected to the cold side over peripheral sides.
  • heat shields are used which must withstand hot gases of 1000 to 1600 degrees.
  • gas turbines such as those used in power-generating power plants and aircraft engines, have correspondingly large shielded by heat shields
  • a gas turbine in the simplest case comprises a compressor, a combustion chamber and a turbine.
  • the compressor there is a compression of sucked air, which is then admixed with a fuel.
  • a combustion of the mixture whereby a hot working gas flow is produced, which is supplied to the turbine. This removes energy from the hot working gas and converts it into mechanical energy.
  • thermoacoustic oscillations In the combustion chamber there may be an interaction of acoustic oscillations and fluctuations in the heat release, which can swell each other.
  • thermoacoustic oscillations which occur in particular in the combustion chamber of the gas turbine, can lead to considerable damage to the components during operation of the gas turbine and force shutdown of the system.
  • the Helmholtz resonators include a resonant volume, a housing surrounding the resonant volume, and at least one resonator throat channel fluidly connecting the resonant volume to the ambient.
  • the resonator neck channel has a diameter and a length, wherein these dimensions can be related to the resonance volume in such a way that the Helmholtz resonator is tunable to a frequency or frequency band.
  • the thermoacoustic vibrations to be damped meet an input opening of the
  • Resonator neck on and are passed over the resonator neck in the interior of the resonant volume.
  • the acoustic vibrations can be coupled into the resonance volume by means of the resonator neck channel.
  • the temperature inside the Helmholtz resonators changes, as a result of which the frequency range damped by the resonator also changes continuously.
  • the known resonators are purged with cooling air during operation of the gas turbine. However, this scavenging air is then no longer available for combustion. This deteriorates the exhaust gas values of the gas turbine.
  • the object of the present invention is to provide an initially mentioned heat shield with at least one Helmholtz resonator, with which the damping of thermoacoustic oscillations in a predetermined frequency range using particularly low cooling air consumption is made possible.
  • a further object of the invention is to specify a Helmholtz resonator for the aforementioned heat shield, a combustion chamber with such a heat shield and a gas turbine with such a combustion chamber, with which the damping of thermoacoustic oscillations in a predetermined frequency range using particularly low cooling Air consumption is enabled.
  • the object is achieved in a heat shield of the type mentioned in that
  • the resonance volume extends along a strain column or a strain column section between peripheral sides of the heat shield elements, wherein the Helmholtz resonator substantially at least partially closes the expansion gaps for protection against hot gases.
  • the inventive design of the Helmholtz resonator leads to a reduced consumption of cooling air in the region of the expansion gaps of the heat shield. Since the expansion column is at least partially closed by the Helmholtz resonator arranged in it, blocking the expansion gaps against hot gas infeed on this section of the expansion column is no longer necessary or only necessary to a very limited extent.
  • the saved cooling air can be used to cool the Helmholtz resonator.
  • the arranged in the expansion column Helmholtz resonator requires only a fraction of cooling air against the open expansion column. For example, the cooling air for cooling the Helmholtz resonator can be guided past this by being guided on both sides by the gap between the peripheral side and Helmholtz resonator housing.
  • the gap may be formed in the form of a labyrinth seal, so that an expansion of the heat shield elements is still possible. Locking the labyrinth seal simultaneously allows cooling of the Helmholtz resonator.
  • the cooling air can, for example, or alternatively as purge air through the helmet holtzresonator be guided.
  • the thus internally cooled Helmholtz resonator is particularly resistant to hot gases.
  • the Helmholtz resonator can occlude the entire expansion column or only a portion of it.
  • the Helmholtz resonator can be arranged, for example, along an axial or radial expansion gap.
  • the expansion gap is an axial gap of an annular combustion chamber, it may be arranged along the outer shell in an axial gap or on the hub along an axial gap.
  • the radial expansion gaps run around a longitudinal axis of the combustion chamber.
  • the Helmholtz resonator is arranged in a radial expansion column, it may, for example, have a semicircular configuration or a circular one in that it is composed of a plurality of circular-segment-shaped Helmholtz resonators.
  • the circular segment-shaped Helmholtz resonators can for example be connected to one another via a dovetail connection.
  • essentially all axial and / or radial gaps can be closed by means of the Helmholtz resonators. This allows a particularly high damping potential.
  • the resonance volume of the Helmholtz resonator is arranged between the peripheral sides of the heat shield elements.
  • the resonance volume is completely in the expansion column and has no protrusions extending below the heat shield.
  • the resonance volume may, for example, have a substantially parallelepipedal shape, with the direction of the longitudinal axis of the Stretching column facing edges can be bent.
  • the helmet-retaining resonator can also be considered advantageous for the helmet-retaining resonator to extend along a number of heat shield elements and to have a shape running in the longitudinal direction of the expansion gap, in particular a curved shape, corresponding to the course of the expansion column. According to this embodiment of the invention, the length of the
  • Helmholtz resonator in the direction of the longitudinal extent of the expansion column greater than the side length of a heat shield stone. This reduces the number of necessary components.
  • the helmet holtz resonator extends in the direction of the hot side substantially to the level of the hot sides of the heat shield bricks. This allows a particularly flat surface of the heat shield.
  • the Helmholtz resonator comprises a heat-insulating layer on its outer side facing the hot gases.
  • the Helmholtz resonator may consist of a metallic material, which may be provided for its protection with such a thermal barrier coating.
  • the thermal barrier coating may be a so-called TBC (Thermal Barrier Coating) layer.
  • TBC Thermal Barrier Coating
  • the layer can also be applied to other areas of the outside of the Helmholtz resonator.
  • Resonator neck channel is arranged on the hot gases facing the outside of the Helmholtz resonator.
  • thermoacoustic oscillations into the resonance volume.
  • the inlet openings of the resonator neck channels can, for example, be arranged successively in a row following the course of the expansion gaps on the outside of the Helmholtz resonator facing the hot gases.
  • the helmet-holding resonator can be flowed through by means of cooling air and encompasses at least one purging air channel opening into the resonance volume.
  • a further advantageous embodiment of the invention can provide that the Helmholtz resonator along the expansion column is formed as a stone holder of the adjacent him heat shield elements and at least one can be arranged on at least one heat shield element holding portion and at least one attachable to the support structure mounting portion.
  • This embodiment of the invention allows a further saving of cooling air, as beyond the Helmholtz resonator addition no further, the heat shield elements holding stone holder must be cooled.
  • the peripheral sides of the heat shield elements adjoining the Helmholtz resonator form at least one retaining bolt with at least one contact surface facing the hot side, wherein the housing of the Helmholtz resonator rests on the contact surface and is braced against the support structure.
  • the area of the Helmholtz resonator housing resting on the support surface can form the at least one holding section.
  • the support surface may be aligned parallel to the hot side of the heat shield element.
  • the housing of the resonator can rest completely on the retaining bolts, wherein the housing is braced with at least one fastening portion on the support structure.
  • the housing is braced with at least one fastening portion on the support structure.
  • Attachment portion be a fastening bolt which is resiliently anchored in the support structure.
  • the helmet-holtz resonator can be attached to the support structure on a fastening groove running in the support structure and underneath the expansion gaps.
  • the mounting groove allows the Helmholtz resonator to be moved along the groove to its intended position.
  • the fastening groove has a groove-shaped recess in the region of the groove bottom along both side walls, so that a widening of the fastening groove is formed.
  • This embodiment of the fastening groove has a particularly simple construction and ensures a secure hold of the fastening section in the groove.
  • the at least one fastening portion of the housing of the fastening groove Tailored to this embodiment of the fastening groove, the at least one fastening portion of the housing of the
  • Helmholtz resonator starting to extend to the support structure and include a T-shaped end portion, the crossbar is threadable into a running in the support structure mounting groove.
  • the attachment portion can be threaded into the groove, for example in the region of a dividing joint which cuts the fastening groove.
  • the Helmholtz resonator can be one or comprise a plurality of such attachment portions. To simplify the construction, exactly one can be provided, which extends bar-shaped below the housing and is threaded with the T-shaped end section over the entire length in the fastening groove. This allows a particularly stable attachment of the stone holder to the support structure.
  • At least one scavenging air duct runs through the fastening section, with at least one inlet opening for scavenging air pointing in the direction of the supporting structure and at least one outlet opening in the resonant volume.
  • the inlet opening of the scavenging air channel can be aligned with the outlet opening of a cooling air channel arranged in the supporting structure.
  • the heat shield according to the invention can extend from an inlet to an exit region of a combustion chamber and comprise axial expansion gaps and radial expansion gaps formed circumferentially perpendicular thereto.
  • the Helmholtz resonator according to the invention can be arranged in such a radial or in an axial expansion column, wherein it can be advantageously provided that the heat shield bricks are formed overlapping along at least one expansion column of the other column type.
  • the heat shield elements can be arranged overlapping along the axial gaps and the radial gaps of Helmholtz resonators invention be closed.
  • This has the advantage that scavenging air emerging from the resonator neck channels distributed along the entire circumference of the combustion chamber can cool the surface of the heat shield elements by means of film cooling.
  • the arrangement could also be reversed. This has the advantage that the
  • Helmholtz resonators along the axial expansion gaps may have a much less curved shape or a straight shape. This allows a further reduction of the cooling air requirement.
  • Another object of the invention is to provide a Helmholtz resonator for the aforementioned heat shield, with which the attenuation of thermoacoustic oscillations in a predetermined frequency range using particularly low cooling air consumption is made possible.
  • a further object of the invention is to specify a combustion chamber lined with a heat shield mentioned at the outset and a gas turbine with which the damping of thermoacoustic oscillations in a predetermined frequency range using particularly low cooling air consumption is made possible.
  • the combustion chamber comprises at least one heat shield according to one of claims 1 to 15 and the gas turbine at least one combustion chamber according to claim 17.
  • Fig.l schematically shows a longitudinal section through a gas turbine according to the prior art
  • FIG. 2 schematically shows a longitudinal section through a section of a heat shield in the region of an invented Helmholtz resonator according to the invention according to one embodiment.
  • FIG. 1 shows a schematic sectional view of a gas turbine 1 according to the prior art.
  • the gas turbine 1 has inside a rotatably mounted about a rotation axis 2 rotor 3 with a shaft 4, which is also referred to as a turbine runner.
  • a turbine runner Along the rotor 3 follow one another an intake housing 6, a compressor 8, a combustion system 9 with a number of combustion chambers 10, a turbine 14 and an exhaust housing 15.
  • the combustion chambers 10 each comprise a burner assembly 11 and a housing 12, which is designed to protect against hot gases is lined with a heat shield 20.
  • the combustion system 9 communicates with an annular hot gas duct, for example.
  • a plurality of successively connected turbine stages form the turbine 14. Each turbine stage is formed of blade rings.
  • the hot runner of a row formed by vanes 17 is followed by a row formed by buckets 18.
  • the guide vanes 17 are fastened to an inner housing of a stator 19, whereas the moving blades 18 of a row are attached to the rotor 3, for example by means of a turbine disk. Coupled to the rotor 3 is, for example, a generator (not shown).
  • FIG. 2 shows a section of a heat shield 30 according to an exemplary embodiment of the invention in a longitudinal section.
  • the heat shield 30 comprises a support structure 32 and, in the region of the section shown, heat shield elements 34a, 34b, which adjoin one another, leaving an expansion gap 36.
  • the heat shield elements 34a, 34b have a hot side 38 which can be acted upon with hot gases and a cold side 40 which lies opposite the hot side.
  • the hot side 38 is connected to the cold side 40 via peripheral sides.
  • the circumferential sides 42 adjoining the expansion gaps 36 form a retaining bolt 44, which in each case has a bearing surface 46 facing the hot side.
  • a Helmholtz resonator 48 according to the invention is arranged in the expansion column 36. This is formed according to the illustrated embodiment in the form of a stone holder 50 of the heat shield elements 34a and 34b.
  • the Helmholtz resonator 48 comprises a resonant volume 54 surrounded by a housing 52.
  • Resonator neck channels 58 are arranged in the housing 52 in the form of bores in the housing wall. The resonator neck channels 58 connect the resonance volume 54 with the interior of the combustion chamber 60, so that over the
  • Resonator neck channels 58 thermoacoustic vibrations are coupled into the resonant volume.
  • the resonator neck channels 58 have inlet openings 62 which are arranged on an outer side 56 of the Helmholtz resonator 48 facing the hot gases.
  • the entrance openings 62 may be disposed on the outside 56 of the housing 52 in a row parallel to a longitudinal direction 64 of the expansion column.
  • the housing 52 and the resonance volume 54 enclosed by it are between the circumferential sides 42 in the expansion gaps 36 arranged and closes them substantially over the length of the Helmholtz resonator 48.
  • the Helmholtz resonator 48 may for example have a length corresponding to the side length of the heat shield element 34a, 34b.
  • the Helmholtz resonator can also have a substantially greater extent and extend, for example, over a section of the radial expansion gaps 36, which substantially corresponds to a ring segment.
  • the radial expansion gap 36 extends perpendicular to a main flow direction 68 of the combustion chamber passing hot gases and circumferentially around a
  • the Helmholtz resonator 48 can advantageously have a curved shape in the longitudinal direction 64 of the expansion gaps 36 in accordance with the curved course of the expansion gap 36. Perpendicular to the support structure, the Helmholtz resonator 48 extends in the direction of the hot side substantially to the level of the hot sides 38 of the heat shield bricks 34a and 34b. According to the illustrated embodiment, the Helmholtz resonator 48 is connected to the housing 52 with a portion of the housing, which may also be referred to with holding portion 70, on the formed from the peripheral sides 42 retaining bolts 44 and is braced against the support structure. For this purpose, a fastening portion 72 of the Helmholtz resonator 48 engages in a below the expansion column 36 in the support structure 32 extending mounting groove 74 a.
  • the fastening groove 74 has a groove-shaped recess 78 in the region of the groove bottom 76 along both side walls, so that a widening of the fastening groove 74 is formed.
  • the mounting portion 72 engages with a T-shaped end portion 80 in this broadening for attachment.
  • the trained as a stone holder Helmholtz resonator 48 can be flowed through with cooling air.
  • the Helmholtz resonator 48 comprises a scavenging air duct 82 extending through the fastening section 72.
  • the scavenging air duct 82 opens into the resonant volume 54 through an outlet opening 86 and becomes supplied with purging air via an inlet opening 84 pointing in the direction of the support structure 32.
  • the inlet opening 84 is positioned, for example, via a cooling air bore 88 arranged in the groove bottom 76 of the fastening groove 74.
  • the stone holder 50 or the Helmholtz resonator 48 may be made of a metallic material.
  • it can be bent from a sheet metal and closed on the end faces in each case by means of a cover plate.
  • a heat-insulating layer can be applied to the exterior side 56 of the Helmholtz resonator 48 facing the hot gases.

Landscapes

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

Abstract

La présente invention concerne un écran thermique (30) destiné à une chambre de combustion (25). L'écran thermique comprend une structure de support (32), un certain nombre d'éléments d'écran thermique et au moins un résonateur de Helmholtz (48). Les éléments d'écran thermique (34a, 34b) sont fixés de manière amovible à la structure de support (32) au moyen de supports en pierre (50) tout en ménageant des interstices de dilatation (36) sensiblement sur toute la surface. Chaque élément d'écran thermique possède un côté froid (40) dirigé vers la structure de support (32), un côté chaud (38) opposé au côté froid et pouvant être alimenté en fluide chaud, et des côtés périphériques (42). Le résonateur de Helmholtz (48) comprend un volume de résonance (54), un boîtier (52) entourant le volume de résonance et au moins un conduit (58) formant goulot de résonateur qui relie fluidiquement le volume de résonance à l'environnement. L'écran thermique de l'invention permet d'amortir des vibrations thermoacoustiques dans une gamme de fréquence prédéterminée avec une consommation d'air de refroidissement particulièrement faible. Pour cela, au moins une partie du volume de résonance s'étend le long d'un interstice de dilatation (36) ou d'une portion d'interstice de dilatation entre les côtés périphériques (42) des éléments d'écran thermique (34a, 34b).
PCT/EP2014/066720 2013-08-15 2014-08-04 Écran thermique comportant un résonateur de helmholtz Ceased WO2015022222A1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE102013216202.2 2013-08-15
DE102013216202 2013-08-15

Publications (1)

Publication Number Publication Date
WO2015022222A1 true WO2015022222A1 (fr) 2015-02-19

Family

ID=51302707

Family Applications (1)

Application Number Title Priority Date Filing Date
PCT/EP2014/066720 Ceased WO2015022222A1 (fr) 2013-08-15 2014-08-04 Écran thermique comportant un résonateur de helmholtz

Country Status (1)

Country Link
WO (1) WO2015022222A1 (fr)

Cited By (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP3410014A1 (fr) * 2017-05-31 2018-12-05 Ansaldo Energia S.p.A. Support de brique pour chambre de combustion d'une turbine à gaz
EP3640544A1 (fr) * 2018-10-15 2020-04-22 United Technologies Corporation Ensemble de fixation de chemise de chambre de combustion pour moteur à turbine à gaz
EP3667165A1 (fr) * 2018-12-12 2020-06-17 Rolls-Royce plc Chambre de combustion, support de dalles et dalle
CN113124419A (zh) * 2019-12-31 2021-07-16 安萨尔多能源公司 燃气涡轮组件及用于其燃烧室的绝热砖瓦的支承装置
US11204204B2 (en) 2019-03-08 2021-12-21 Toyota Motor Engineering & Manufacturing North America, Inc. Acoustic absorber with integrated heat sink
US11255547B2 (en) 2018-10-15 2022-02-22 Raytheon Technologies Corporation Combustor liner attachment assembly for gas turbine engine
DE102023210272A1 (de) 2023-10-19 2025-04-24 Siemens Energy Global GmbH & Co. KG Brennkammer einer Gasturbine mit optimierter Kühlung

Citations (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2548485A (en) * 1946-01-09 1951-04-10 Shell Dev Combustion chamber lining
WO1996004511A1 (fr) * 1994-08-05 1996-02-15 Yanovsky, Ilya Yakovlevich Chambre a combustion a tube a feu en ceramique
US20070151249A1 (en) * 2004-01-27 2007-07-05 Claudia Barbeln Heat shield
US20080295519A1 (en) * 2007-05-31 2008-12-04 Roger James Park Turbine engine fuel injector with Helmholtz resonators
WO2010115980A2 (fr) * 2009-04-11 2010-10-14 Alstom Technology Ltd. Chambre de combustion dotée d'un amortisseur de helmholtz
US8052155B2 (en) * 2003-10-02 2011-11-08 Alstom Technology Ltd. High temperature seal and methods of use
US20130064661A1 (en) * 2011-09-08 2013-03-14 Rolls-Royce Plc Aerofoil assembly

Patent Citations (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2548485A (en) * 1946-01-09 1951-04-10 Shell Dev Combustion chamber lining
WO1996004511A1 (fr) * 1994-08-05 1996-02-15 Yanovsky, Ilya Yakovlevich Chambre a combustion a tube a feu en ceramique
US8052155B2 (en) * 2003-10-02 2011-11-08 Alstom Technology Ltd. High temperature seal and methods of use
US20070151249A1 (en) * 2004-01-27 2007-07-05 Claudia Barbeln Heat shield
US20080295519A1 (en) * 2007-05-31 2008-12-04 Roger James Park Turbine engine fuel injector with Helmholtz resonators
WO2010115980A2 (fr) * 2009-04-11 2010-10-14 Alstom Technology Ltd. Chambre de combustion dotée d'un amortisseur de helmholtz
US20130064661A1 (en) * 2011-09-08 2013-03-14 Rolls-Royce Plc Aerofoil assembly

Cited By (12)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP3410014A1 (fr) * 2017-05-31 2018-12-05 Ansaldo Energia S.p.A. Support de brique pour chambre de combustion d'une turbine à gaz
CN108980894A (zh) * 2017-05-31 2018-12-11 安萨尔多能源公司 用于燃气涡轮的燃烧器的瓦保持器
CN108980894B (zh) * 2017-05-31 2021-11-05 安萨尔多能源公司 用于燃气涡轮的燃烧器的瓦保持器
EP3640544A1 (fr) * 2018-10-15 2020-04-22 United Technologies Corporation Ensemble de fixation de chemise de chambre de combustion pour moteur à turbine à gaz
US11255547B2 (en) 2018-10-15 2022-02-22 Raytheon Technologies Corporation Combustor liner attachment assembly for gas turbine engine
US11293637B2 (en) 2018-10-15 2022-04-05 Raytheon Technologies Corporation Combustor liner attachment assembly for gas turbine engine
EP3667165A1 (fr) * 2018-12-12 2020-06-17 Rolls-Royce plc Chambre de combustion, support de dalles et dalle
US11530817B2 (en) 2018-12-12 2022-12-20 Rolls-Royce Plc Combustor, a tile holder and a tile
US11204204B2 (en) 2019-03-08 2021-12-21 Toyota Motor Engineering & Manufacturing North America, Inc. Acoustic absorber with integrated heat sink
CN113124419A (zh) * 2019-12-31 2021-07-16 安萨尔多能源公司 燃气涡轮组件及用于其燃烧室的绝热砖瓦的支承装置
CN113124419B (zh) * 2019-12-31 2024-05-24 安萨尔多能源公司 燃气涡轮组件及用于其燃烧室的绝热砖瓦的支承装置
DE102023210272A1 (de) 2023-10-19 2025-04-24 Siemens Energy Global GmbH & Co. KG Brennkammer einer Gasturbine mit optimierter Kühlung

Similar Documents

Publication Publication Date Title
WO2015022222A1 (fr) Écran thermique comportant un résonateur de helmholtz
EP2148977B1 (fr) Turbine à gaz
EP2340397B1 (fr) Pièce du brûleur pour une chambre de combustion d'une turbine à gaz et turbine à gaz
EP2787168B1 (fr) Rotor pour une turbomachine avec un arbre creux
DE3428892A1 (de) Schaufel- und dichtspaltoptimierungseinrichtung fuer verdichter von gasturbinentriebwerken, insbesondere gasturbinenstrahltriebwerken
DE2943464A1 (de) Dichtungsvorrichtung fuer ein gasturbinentriebwerk
EP1418319A1 (fr) Turbine à Gaz
EP2342425B1 (fr) Turbine à gaz avec plaque de fixation entre la base d'aube et le disque
EP2711630A1 (fr) Dispositif de refroidissement d'une structure porteuse d'un bouclier thermique et bouclier thermique
EP2084368B1 (fr) Aube de turbine
EP3017253B1 (fr) Bouclier thermique céramique pour une chambre de combustion de turbine à gaz, chambre de combustion pour une turbine à gaz et procédé
EP3132202B1 (fr) Element de bouclier thermique avec contournement
WO1998013584A1 (fr) Compensation de la perte de pression d'une conduite d'air de refroidissement dans une installation de turbine a gaz
EP3954876B1 (fr) Couronne directrice pour un turbocompresseur à gaz d'échappement
DE102011016917A1 (de) Gasturbinenbrennkammer mit einer Halterung einer Dichtung für ein Anbauteil
EP1904717B1 (fr) Element de carter conducteur de gaz chaud, enveloppe de protection d'arbre et systeme de turbine a gaz
EP1926927A1 (fr) Garniture d'etancheite resistant aux temperatures elevees, conçue en particulier pour des turbines a gaz
EP2206885A1 (fr) Turbine à gaz
WO2004090423A1 (fr) Element d'ecran thermique
EP2725203B1 (fr) Conduite d'air froid dans une structure de boîtier d'une turbomachine
EP1724526A1 (fr) Coquille de turbine à gaz, turbine à gaz et procédé de démarrage et d'arrêt d'une turbine à gaz
EP1529181B1 (fr) Chambre de combustion de turbine a gaz
EP2957718A1 (fr) Turbine
EP1731715A1 (fr) Transition d'une chambre de combustion à une turbine
EP1783325B1 (fr) Assemblage de fixation d'un tuyau sur une surface périphérique

Legal Events

Date Code Title Description
121 Ep: the epo has been informed by wipo that ep was designated in this application

Ref document number: 14750339

Country of ref document: EP

Kind code of ref document: A1

NENP Non-entry into the national phase

Ref country code: DE

122 Ep: pct application non-entry in european phase

Ref document number: 14750339

Country of ref document: EP

Kind code of ref document: A1