EP2273196A2 - Tête pour chambre de combustion d'une turbine à gaz - Google Patents

Tête pour chambre de combustion d'une turbine à gaz Download PDF

Info

Publication number
EP2273196A2
EP2273196A2 EP10004499A EP10004499A EP2273196A2 EP 2273196 A2 EP2273196 A2 EP 2273196A2 EP 10004499 A EP10004499 A EP 10004499A EP 10004499 A EP10004499 A EP 10004499A EP 2273196 A2 EP2273196 A2 EP 2273196A2
Authority
EP
European Patent Office
Prior art keywords
combustion chamber
head according
wall
recesses
boundary
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.)
Withdrawn
Application number
EP10004499A
Other languages
German (de)
English (en)
Other versions
EP2273196A3 (fr
Inventor
Sermed Sadig
Miklos Dr. Gerendàs
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.)
Rolls Royce Deutschland Ltd and Co KG
Original Assignee
Rolls Royce Deutschland Ltd and Co KG
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 Rolls Royce Deutschland Ltd and Co KG filed Critical Rolls Royce Deutschland Ltd and Co KG
Publication of EP2273196A2 publication Critical patent/EP2273196A2/fr
Publication of EP2273196A3 publication Critical patent/EP2273196A3/fr
Withdrawn legal-status Critical Current

Links

Images

Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
    • F23R3/02—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration
    • F23R3/04—Air inlet arrangements
    • 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
    • F23R3/28—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply
    • F23R3/283—Attaching or cooling of fuel injecting means including supports for fuel injectors, stems, or lances
    • 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
    • F23R2900/03041—Effusion 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
    • F23R2900/03042—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
    • F23R2900/03043—Convection cooled combustion chamber walls with means for guiding the cooling air flow

Definitions

  • the invention relates to a combustion chamber head of a gas turbine and more particularly to a combustion chamber head having the features of the preamble of claim 1.
  • combustion chamber head which consists of a end wall, a front panel and a heat shield.
  • This is a three walled construction of a combustor head with an open volume between the end and front panels. The function of the end wall is to guide the flow of air coming from the compressor.
  • the principle of the impact-cooled combustion chamber wall has been extended by the aspect of damping of combustion chamber vibrations.
  • the effusion wells together with the volume enclosed by the walls containing the impact and effusion bores, form a plurality of interconnected Helmholtz resonators. So can high-frequency oscillations in the range around 5kHz be steamed.
  • the distance between the damping holes and the distance between the walls are made variable in order to produce a broad attenuation spectrum.
  • Plenum flow in this context means that there are no significant pressure or velocity fluctuations in this volume (it does not resonate!), In contrast to a Helmholtz resonator. Also, because of the broadband nature of the effect, the volume need not be tuned to the frequency to be damped, as in a Helmholtz resonator. Also, the volume used in the damper is significantly smaller than calculated from the equation known for resonator volume and frequency.
  • the CA 26 27 627 A shows a heat shield with ribs on the side facing away from the combustion chamber.
  • the ribs are connected together at one end and have with their open side to the inner and outer combustion chamber wall. It bounces cooling air between the ribs and is guided by means of the ribs to the combustion chamber walls. This is to prevent the impact cooling jets from influencing each other too strongly. The effects of the incoming cross flow should be avoided.
  • the Indian DE 44 27 222 A illustrated combustion chamber head with the additional flow-leading end plate has the disadvantage that the volume between the end and front plate is not decoupled from the burner, closed volume. It may thus be the case that pressure fluctuations in this volume affect the stability of the burner.
  • the end plate is thus intended only as a flow-conducting element.
  • the invention has for its object to provide a combustion chamber head of the type mentioned, which meets the thermal requirements with a simple structure and simple, cost-effective manufacturability and ensures a high degree of damping.
  • the combustion chamber head forms a volume which is delimited by a wall relative to the combustion chamber, wherein on the flammenabgewandten side of this boundary of the air flow for cooling the boundary and the air flow through the wall for damping the vibrations without possibility of mixing cross.
  • combustion chamber head in conjunction with a schematic representation of a gas turbine in connection with Fig. 1 described.
  • the combustion chamber head consists of a perforated wall 210 facing the hot gas and a boundary 206 terminating the volume 207.
  • a closed volume 207 is formed.
  • the perforated wall 210 has ribs 201. Holes 202 in the wall 210 preferably extend through the ribs 201.
  • the air jet will lift off the wall 210 after a characteristic run length and enter the volume 207.
  • the flow channel 218, which is formed by ribs or heat transfer elements (see FIGS. 4a and 4b), can be supplemented by a cover 219, resulting in a partially closed flow channel.
  • the air jet is guided near the wall 210 and adjacent to the ribs 201.
  • the flow thus initially runs parallel to the wall 210, lifts off from the wall 210 (combustion chamber side boundary) and enters the volume 207 from where it leaves the combustion chamber head through the holes 202 in the wall.
  • the incoming and outgoing air mass flows cross in their direction of movement, but are separated by walls and therefore do not mix. There is a clear separation of the cooling and damping function by the different direction of movement and flow control of the air jet in the combustion chamber head.
  • the volume 207 is preferably dimensioned so that a plenumnahe flow is ensured for the outlet holes 202. This occurs in the event that the flow of the outlet holes 202 is no longer affected by the supply air. It can be a distance of a minimum of 2mm to a maximum of the length of the burner 102 can be selected.
  • the size of the damping volume unlike Helmholtz resonators regardless of expected resonance frequencies selected.
  • a 0 is the speed of sound
  • f is the resonant frequency
  • So is the cross-sectional area of the resonator neck
  • l eff is the resonator neck length. It is frequency-dependent and significantly larger than the volume 207 required here.
  • the volume 207 can be designed as a circumferentially continuous volume.
  • the volume 207 can be segmented by additional partitions into individual mutually closed volumes. In the case of a segmented volume 207, the volumes may be the same size or different sizes.
  • the height of the ribs 201 is preferably chosen so that the lifting of the air jet from the inlet bores 203 as far as possible downstream of the Zu Kunststofflöcher 203 takes place in order to allow the highest possible cooling effect along the entire wall 210.
  • heights of 1mm - 10mm are considered advantageous.
  • individual or groups of exit holes 202 may pass through individual rib members 227 and 228.
  • the rib elements can be arranged arbitrarily.
  • the cross section of the rib elements can be arbitrarily shaped. The function is not affected by this. Illustrated in FIG 3d illustration and 4d an aerodynamic profile and in Figure 3e and 4e a circular profile. Rectangular, diamond-shaped, hexagonal, elliptical, prismatic profiles are also conceivable. Also, a combination of the above profiles can be used, as well as profiles formed by the intersection of circle segments.
  • the ports may also be selectively placed near the combustor 102 via the inner sidewall of the combustor head 213, and then flow along the ribs toward the outer sidewall of the combustor head 112.
  • the construction can be integrally combined as an integral component, or several pieces of several components, with a sufficient seal is to pay attention.
  • the combustion chamber head is attached to the combustion chamber wall, preferably via in each case at least one fastening element.
  • the effective area of the exit holes 202 is preferably larger than that of the supply holes 203 by a factor of 2-10.
  • an initial cooling film may be placed on the combustion chamber wall 204.
  • an effusion hole 217 set in the direction of the combustion chamber wall can be integrated in the wall 210 (eg Figure 3b and 5a ) which replaces the function of a first cooling film.
  • the outer side wall of the combustion head plate lies on the outer combustion chamber wall.
  • the effusion hole can optionally through the wall 210 or the rib 201 lead. Another option is to drill additional holes 215 (see Figure 3c ) in the combustion chamber wall 204.
  • the wall 213b can be made at an angle ⁇ relative to the burner axis 208. It may also optionally be a fillet in place or in addition to the angle.
  • the combustion chamber wall 204 can alternatively also be designed as a two-walled construction, comprising an inner wall 221 facing the hot gas and a side 226 facing the cold outer flow.
  • the outer and inner combustion chamber walls can optionally be perforated (see reference numerals 222 and 223 in FIG Figure 5c ).
  • the volume 225 formed between the outer and inner combustion chamber walls may be connected to the volume 207 through a flow passage 224.
  • the structure described here makes it possible to integrate an effectively highly acoustically damping, sufficiently cooled damper element in the top plate of a combustion chamber.
  • dampers optimized for low frequencies require a large volume of construction.
  • the structure used here makes it possible to effectively use the given space in a combustion chamber to allow a broadband attenuation, especially in the low-frequency range (frequencies below 2000Hz).
  • the broadband damping effect of perforated walls which usually turns out to be low, with that of a Helmholtz resonator whose effect is large, connected.
  • the skillful utilization of the volume lying between the burner heads to approach a plenum-like flow for the damping holes, a particularly high damping effect can be achieved. As a result, the already high damping effect of a Helmholtz resonator can be far exceeded.
  • the solution according to the invention thus combines the oppositely behaving claims of cooling and damping design with simple and practical for use funds. It is possible in a double-walled construction to integrate a large volume and still achieve a high cooling effect through a changed inflow into the volume.

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Spray-Type Burners (AREA)
EP10004499.9A 2009-07-08 2010-04-28 Tête pour chambre de combustion d'une turbine à gaz Withdrawn EP2273196A3 (fr)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
DE102009032277A DE102009032277A1 (de) 2009-07-08 2009-07-08 Brennkammerkopf einer Gasturbine

Publications (2)

Publication Number Publication Date
EP2273196A2 true EP2273196A2 (fr) 2011-01-12
EP2273196A3 EP2273196A3 (fr) 2017-11-01

Family

ID=42935567

Family Applications (1)

Application Number Title Priority Date Filing Date
EP10004499.9A Withdrawn EP2273196A3 (fr) 2009-07-08 2010-04-28 Tête pour chambre de combustion d'une turbine à gaz

Country Status (3)

Country Link
US (1) US8677757B2 (fr)
EP (1) EP2273196A3 (fr)
DE (1) DE102009032277A1 (fr)

Cited By (4)

* 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
WO2014113007A1 (fr) * 2013-01-17 2014-07-24 United Technologies Corporation Ensemble revêtement pour chambre de combustion de turbine à gaz équipé d'un profil hyperbolique convergent
US9958160B2 (en) 2013-02-06 2018-05-01 United Technologies Corporation Gas turbine engine component with upstream-directed cooling film holes
US10174949B2 (en) 2013-02-08 2019-01-08 United Technologies Corporation Gas turbine engine combustor liner assembly with convergent hyperbolic profile

Families Citing this family (27)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE102011014670A1 (de) 2011-03-22 2012-09-27 Rolls-Royce Deutschland Ltd & Co Kg Segmentierter Brennkammerkopf
US9447970B2 (en) * 2011-05-12 2016-09-20 General Electric Company Combustor casing for combustion dynamics mitigation
US20140311151A1 (en) * 2011-11-16 2014-10-23 Mitsubishi Hitachi Power Systems, Ltd. Gas turbine combustor
US9243801B2 (en) * 2012-06-07 2016-01-26 United Technologies Corporation Combustor liner with improved film cooling
US9869279B2 (en) * 2012-11-02 2018-01-16 General Electric Company System and method for a multi-wall turbine combustor
US9366438B2 (en) * 2013-02-14 2016-06-14 Siemens Aktiengesellschaft Flow sleeve inlet assembly in a gas turbine engine
US9400108B2 (en) * 2013-05-14 2016-07-26 Siemens Aktiengesellschaft Acoustic damping system for a combustor of a gas turbine engine
DE102013213860A1 (de) * 2013-07-16 2015-01-22 Siemens Aktiengesellschaft Brennerdüsenträger mit Resonatoren
EP3026346A1 (fr) * 2014-11-25 2016-06-01 Alstom Technology Ltd Chemise de chambre de combustion
US10132498B2 (en) * 2015-01-20 2018-11-20 United Technologies Corporation Thermal barrier coating of a combustor dilution hole
US10513984B2 (en) * 2015-08-25 2019-12-24 General Electric Company System for suppressing acoustic noise within a gas turbine combustor
JP6484546B2 (ja) * 2015-11-13 2019-03-13 三菱日立パワーシステムズ株式会社 ガスタービン燃焼器
DE102015225505A1 (de) 2015-12-16 2017-06-22 Rolls-Royce Deutschland Ltd & Co Kg Wand eines mittels Kühlluft zu kühlenden Bauteils, insbesondere einer Gasturbinenbrennkammerwand
US10260750B2 (en) * 2015-12-29 2019-04-16 United Technologies Corporation Combustor panels having angled rail
US20170191664A1 (en) * 2016-01-05 2017-07-06 General Electric Company Cooled combustor for a gas turbine engine
GB201701380D0 (en) * 2016-12-20 2017-03-15 Rolls Royce Plc A combustion chamber and a combustion chamber fuel injector seal
GB201715366D0 (en) * 2017-09-22 2017-11-08 Rolls Royce Plc A combustion chamber
US10941939B2 (en) * 2017-09-25 2021-03-09 General Electric Company Gas turbine assemblies and methods
DE102018212394B4 (de) * 2018-07-25 2024-03-28 Rolls-Royce Deutschland Ltd & Co Kg Brennkammerbaugruppe mit Strömungsleiteinrichtung aufweisendem Wandelement
JP2020056542A (ja) * 2018-10-02 2020-04-09 川崎重工業株式会社 航空機用のアニュラ型ガスタービン燃焼器
US11174792B2 (en) * 2019-05-21 2021-11-16 General Electric Company System and method for high frequency acoustic dampers with baffles
US11156164B2 (en) * 2019-05-21 2021-10-26 General Electric Company System and method for high frequency accoustic dampers with caps
US11371699B2 (en) * 2019-11-12 2022-06-28 General Electric Company Integrated front panel for a burner
US11543128B2 (en) * 2020-07-28 2023-01-03 General Electric Company Impingement plate with cooling tubes and related insert for impingement plate
US11499480B2 (en) 2020-07-28 2022-11-15 General Electric Company Combustor cap assembly having impingement plate with cooling tubes
DE102021207484A1 (de) 2021-07-14 2023-01-19 Rolls-Royce Deutschland Ltd & Co Kg Brennkammerbaugruppe mit einem Düsenkopf einer Kraftstoffdüse zum Eindüsen von Kraftstoff in Richtung eines Brennkammerkopfes
US11761632B2 (en) 2021-08-05 2023-09-19 General Electric Company Combustor swirler with vanes incorporating open area

Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO1992016798A1 (fr) 1991-03-22 1992-10-01 Rolls-Royce Plc Bruleur de turbine a gaz
EP0576717A1 (fr) 1992-07-03 1994-01-05 Abb Research Ltd. Chambre de combustion de turbine à gaz
DE4427222A1 (de) 1994-08-01 1996-02-08 Bmw Rolls Royce Gmbh Hitzeschild für eine Gasturbinen-Brennkammer
EP0971172A1 (fr) 1998-07-10 2000-01-12 Asea Brown Boveri AG Chambre de combustion pour turbine à gaz avec paroi à structure silencieuse
US20070169992A1 (en) 2006-01-25 2007-07-26 Siemens Power Generation, Inc. Acoustic resonator with impingement cooling tubes
CA2627627A1 (fr) 2007-06-22 2008-12-22 Honeywell International Inc. Protecteurs thermiques pour utilisation dans des chambres de combustion

Family Cites Families (15)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE3022206C2 (de) 1980-06-13 1983-08-11 M.A.N. Maschinenfabrik Augsburg-Nürnberg AG, 4200 Oberhausen Axialverdichter mit verschobener Pumpgrenze
EP0153842B1 (fr) * 1984-02-29 1988-07-27 LUCAS INDUSTRIES public limited company Chambre de combustion pour turbines à gaz
FR2596102B1 (fr) * 1986-03-20 1988-05-27 Snecma Dispositif d'injection a vrille axialo-centripete
US4686823A (en) * 1986-04-28 1987-08-18 United Technologies Corporation Sliding joint for an annular combustor
GB9018013D0 (en) * 1990-08-16 1990-10-03 Rolls Royce Plc Gas turbine engine combustor
GB9112324D0 (en) * 1991-06-07 1991-07-24 Rolls Royce Plc Gas turbine engine combustor
CA2070518C (fr) * 1991-07-01 2001-10-02 Adrian Mark Ablett Ensemble dome pour chambre de combustion
US5363654A (en) 1993-05-10 1994-11-15 General Electric Company Recuperative impingement cooling of jet engine components
DE4444961A1 (de) * 1994-12-16 1996-06-20 Mtu Muenchen Gmbh Einrichtung zur Kühlung insbesondere der Rückwand des Flammrohrs einer Brennkammer für Gasturbinentriebwerke
US5623827A (en) * 1995-01-26 1997-04-29 General Electric Company Regenerative cooled dome assembly for a gas turbine engine combustor
FR2753779B1 (fr) * 1996-09-26 1998-10-16 Systeme d'injection aerodynamique d'un melange air carburant
US6018950A (en) * 1997-06-13 2000-02-01 Siemens Westinghouse Power Corporation Combustion turbine modular cooling panel
US6546733B2 (en) * 2001-06-28 2003-04-15 General Electric Company Methods and systems for cooling gas turbine engine combustors
FR2893390B1 (fr) 2005-11-15 2011-04-01 Snecma Fond de chambre de combustion avec ventilation
DE102006048933A1 (de) 2006-10-17 2008-04-24 Mtu Aero Engines Gmbh Anordnung zur Strömungsbeeinflussung

Patent Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO1992016798A1 (fr) 1991-03-22 1992-10-01 Rolls-Royce Plc Bruleur de turbine a gaz
EP0576717A1 (fr) 1992-07-03 1994-01-05 Abb Research Ltd. Chambre de combustion de turbine à gaz
DE4427222A1 (de) 1994-08-01 1996-02-08 Bmw Rolls Royce Gmbh Hitzeschild für eine Gasturbinen-Brennkammer
EP0971172A1 (fr) 1998-07-10 2000-01-12 Asea Brown Boveri AG Chambre de combustion pour turbine à gaz avec paroi à structure silencieuse
US20070169992A1 (en) 2006-01-25 2007-07-26 Siemens Power Generation, Inc. Acoustic resonator with impingement cooling tubes
CA2627627A1 (fr) 2007-06-22 2008-12-22 Honeywell International Inc. Protecteurs thermiques pour utilisation dans des chambres de combustion

Cited By (4)

* 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
WO2014113007A1 (fr) * 2013-01-17 2014-07-24 United Technologies Corporation Ensemble revêtement pour chambre de combustion de turbine à gaz équipé d'un profil hyperbolique convergent
US9958160B2 (en) 2013-02-06 2018-05-01 United Technologies Corporation Gas turbine engine component with upstream-directed cooling film holes
US10174949B2 (en) 2013-02-08 2019-01-08 United Technologies Corporation Gas turbine engine combustor liner assembly with convergent hyperbolic profile

Also Published As

Publication number Publication date
US20110005233A1 (en) 2011-01-13
US8677757B2 (en) 2014-03-25
EP2273196A3 (fr) 2017-11-01
DE102009032277A1 (de) 2011-01-20

Similar Documents

Publication Publication Date Title
EP2273196A2 (fr) Tête pour chambre de combustion d'une turbine à gaz
EP2559942A1 (fr) Tête de chambre de combustion d'une turbine à gaz dotée d'un refroidissement et d'un amortissement
DE60017063T2 (de) Heissluftabfuhrvorrichtung für die Lufteinlasshaube eines Strahltriebwerkes mit Enteisungskreislauf
EP2423599B1 (fr) Procédé de fonctionnement d'un agencement de brûleur ainsi qu'agencement de brûleur destiné à la mise en oeuvre du procédé
EP3182011B1 (fr) Paroi d'un composant à refroidir à l'aide d'air de refroidissement, en particulier paroi de chambre de combustion de turbine à gaz
DE602005001682T2 (de) Helmholtzresonator für eine Brennkammer eines Gasturbinentriebwerks
EP2770260B1 (fr) Chambre de combustion de turbine à gaz avec bardeau à refroidissement par impact effusion
DE69817127T2 (de) Heissluftabfuhrvorrichtung für die Lufteinlasshaube eines Strahltriebwerkes mit Enteisungskreislauf
EP2154431B1 (fr) Machine thermique
CH680523A5 (fr)
EP1423645A1 (fr) Ensemble amortisseur concu pour reduire les pulsations d'une chambre de combustion dans une installation de turbine a gaz
EP1213538B1 (fr) Dispositif pour gaz d'échappement comprenant un résonateur de Helmholtz
DE102010060286A1 (de) Brennkammereinrichtung für eine Gasturbine, mit verbesserter Kühlung
EP2407659A2 (fr) Cône de gaz d'échappement de turbine à gaz
DE202010016820U1 (de) Diffusor für einen Ventilator sowie Ventilatoranordnung mit einem derartigen Diffusor
EP2334558A2 (fr) Silencieux pour un groupe auxiliaire d'un avion
EP1342953A1 (fr) Turbine à gaz
DE112016002108T5 (de) Brennkammer und Gasturbine
EP0971172B1 (fr) Chambre de combustion pour turbine à gaz avec paroi à structure silencieuse
DE4446541A1 (de) Brennkammer
EP0990851B1 (fr) Chambre de combustion pour une turbine à gaz
EP2414639B1 (fr) Elément refroidi pour une turbine à gaz
EP3117148B1 (fr) Système de combustion avec résonateur
DE102004010620B4 (de) Brennkammer zur wirksamen Nutzung von Kühlluft zur akustischen Dämpfung von Brennkammerpulsation
EP2584148A1 (fr) Aube de turbine refroidie par film pour une turbomachine

Legal Events

Date Code Title Description
PUAI Public reference made under article 153(3) epc to a published international application that has entered the european phase

Free format text: ORIGINAL CODE: 0009012

AK Designated contracting states

Kind code of ref document: A2

Designated state(s): AT BE BG CH CY CZ DE DK EE ES FI FR GB GR HR HU IE IS IT LI LT LU LV MC MK MT NL NO PL PT RO SE SI SK SM TR

AX Request for extension of the european patent

Extension state: AL BA ME RS

PUAL Search report despatched

Free format text: ORIGINAL CODE: 0009013

AK Designated contracting states

Kind code of ref document: A3

Designated state(s): AT BE BG CH CY CZ DE DK EE ES FI FR GB GR HR HU IE IS IT LI LT LU LV MC MK MT NL NO PL PT RO SE SI SK SM TR

AX Request for extension of the european patent

Extension state: AL BA ME RS

RIC1 Information provided on ipc code assigned before grant

Ipc: F23M 99/00 00000000ALI20170927BHEP

Ipc: F23R 3/28 20060101ALI20170927BHEP

Ipc: F23R 3/04 20060101AFI20170927BHEP

STAA Information on the status of an ep patent application or granted ep patent

Free format text: STATUS: THE APPLICATION IS DEEMED TO BE WITHDRAWN

18D Application deemed to be withdrawn

Effective date: 20180503