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EP1818616B1 - Tubomaschinenbrennkammer mit tangentialen Schlitzen - Google Patents

Tubomaschinenbrennkammer mit tangentialen Schlitzen Download PDF

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Publication number
EP1818616B1
EP1818616B1 EP07101654A EP07101654A EP1818616B1 EP 1818616 B1 EP1818616 B1 EP 1818616B1 EP 07101654 A EP07101654 A EP 07101654A EP 07101654 A EP07101654 A EP 07101654A EP 1818616 B1 EP1818616 B1 EP 1818616B1
Authority
EP
European Patent Office
Prior art keywords
combustion chamber
chamber
chamber bottom
flange
fairing
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.)
Active
Application number
EP07101654A
Other languages
English (en)
French (fr)
Other versions
EP1818616A1 (de
Inventor
Florian Bessagnet
Mario De Sousa
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.)
Safran Aircraft Engines SAS
Original Assignee
SNECMA SAS
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 SNECMA SAS filed Critical SNECMA SAS
Publication of EP1818616A1 publication Critical patent/EP1818616A1/de
Application granted granted Critical
Publication of EP1818616B1 publication Critical patent/EP1818616B1/de
Active legal-status Critical Current
Anticipated expiration legal-status Critical

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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
    • F23R3/28—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
    • 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
    • F23D—BURNERS
    • F23D2211/00—Thermal dilatation prevention or compensation
    • 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
    • F23R2900/00005—Preventing fatigue failures or reducing mechanical stress in gas turbine components

Definitions

  • the present invention relates to the general field of turbomachine annular combustion chambers provided with a one-piece fairing protection of fuel injection systems.
  • An annular turbomachine combustion chamber is generally formed of two longitudinal walls of revolution (an outer wall and an inner wall) which are connected upstream by a transverse wall forming a chamber bottom.
  • the present invention relates more particularly to combustion chambers which also comprise a monobloc fairing mounted upstream of the chamber bottom.
  • the fairing allows in particular to protect the fuel injection systems that are mounted on the chamber floor.
  • the assembly of these different elements of the combustion chamber is performed by means of bolting mounted at the inner and outer walls.
  • the chamber base and the fairing each comprise an internal flange and an external flange on which are fixed by bolting respectively the inner wall and the outer wall of the combustion chamber, these longitudinal walls being interposed between the fairing and the bedroom floor.
  • this type of combustion chamber architecture poses many problems.
  • the various elements of the combustion chamber have significant manufacturing tolerances, which leads to a stack of tolerances resulting in poor docking between these elements during assembly of the combustion chamber, which causes a loss in clamping passing between the flanges.
  • the part of the clamping which is used to deform the chamber is subtracted from the reaction force between its components. When this reaction force decreases, the effort required to slide the pieces together is therefore less.
  • An extra tightening torque is therefore necessary to make up for the games coming from manufacturing tolerances of the components and thus keep the proper tightening force for the passage of sliding forces passing through the connection. Therefore, in operation, the vibrations caused by the combustion of the gases inside the combustion chamber often cause the formation of cracks in the bolting on the shroud and / or the chamber bottom. Such cracks are particularly detrimental to the life of the combustion chamber.
  • the main object of the present invention is therefore to overcome such disadvantages by proposing an annular combustion chamber architecture which is easy to mount and has sufficient flexibility to prevent the formation of cracks while maintaining a useful clamping efficiency.
  • annular turbomachine combustion chamber comprising longitudinal walls connected by a transverse chamber bottom and a one-piece fairing, the chamber bottom and the fairing each comprising an inner flange and an outer flange each pierced by a flange.
  • a plurality of holes for the passage of fastening systems for fastening the shroud to the chamber bottom characterized in that, at each fastening system, is associated at least one slot tangential to the annular geometry of the chamber formed on the corresponding flange of the chamber bottom and / or on the corresponding flange of the fairing, each slot being formed in the immediate vicinity of the corresponding fastening system.
  • the invention also relates to a turbomachine comprising an annular combustion chamber as defined above.
  • FIGS. 1 to 3 illustrate a combustion chamber for a turbomachine according to the invention.
  • Such a turbomachine for example aeronautical, comprises in particular a compression section (not shown) in which air is compressed before being injected into a chamber housing 2, then into a combustion chamber 4 mounted inside. of it.
  • Compressed air is introduced into the combustion chamber and mixed with fuel before being burned.
  • the gases resulting from this combustion are then directed to a high-pressure turbine 5 disposed at the outlet of the combustion chamber.
  • the combustion chamber 4 is of annular type. It is formed of an inner annular wall 6 and an outer annular wall 8 which extend in a substantially longitudinal direction relative to the longitudinal axis X-X of the turbomachine.
  • the combustion chamber also comprises a one-piece fairing 12 (that is to say made in one and the same piece) covering the chamber bottom 10.
  • the main components of the combustion chamber i.e. the longitudinal walls 6, 8, the chamber bottom 10 and the fairing 12 are assembled together by means of a plurality of fixing systems 14 regularly distributed over the entire circumference of the combustion chamber and each formed of a screw 14a and a clamping nut 14b.
  • the chamber bottom 10 has an internal flange 16 and an outer flange 18 extending longitudinally upstream and each provided with holes, 16a and 18a, respectively, for the passage of fastening screws 14a.
  • the one-piece fairing 12 comprises an inner flange 20 and an outer flange 22 which extend longitudinally downstream and which are each provided with holes, 20a and 22a, respectively, for the passage of the fastening screws 14a.
  • the longitudinal walls 6, 8 of the combustion chamber are also drilled at their upstream end of a plurality of holes, respectively 6a and 8a, for the passage of the fixing screws 14a.
  • the chamber bottom 10 and the fairing 12 of the combustion chamber are each provided with a plurality of openings, respectively 24 and 26, for the passage of fuel injection systems 28.
  • each fastening system 14 is associated with at least one tangential slot 30 formed on the corresponding flange 16, 18 of the chamber bottom 10 and / or on the corresponding flange 20, 22 of the fairing 12, each tangential slot. being formed in the immediate vicinity of the corresponding fastening system.
  • Tangential slot means a slot that extends in a substantially tangential (or circumferential) direction relative to the annular general geometry of the combustion chamber.
  • a tangential slot makes it possible to reduce the constraints tangential at each fastening system and thus reduce the risk of formation of cracks.
  • both the inner flange 16 of the chamber bottom and the inner flange 20 of the fairing 12 are provided with a tangential slot 30 formed in the immediate vicinity of the fastening system.
  • the outer flange 18 of the chamber bottom and the outer flange 22 of the shroud 12 are each provided with a tangential slot 30 arranged in the immediate vicinity of the fastening system.
  • the tangential slots 30 are formed in the immediate vicinity of the fastening systems 14, that is to say that they are not intended to be arranged between two adjacent fastening systems for example. Indeed, the presence of these slots makes it possible to provide flexibility in the fastening systems which are at the origin of too great rigidity of the assembly of the components of the combustion chamber. It should also be noted that the longitudinal walls 6, 8 of the combustion chamber are devoid of such tangential slots, which eliminates any risk of leakage and lack of rigidity of these walls.
  • the slots 30 extend tangentially over a distance which is substantially the same on either side of the fixing systems 14.
  • they may have a length (measured tangentially) of approximately ⁇ (3.14) times the assembly diameter divided by 2 times the number of slots (the grooved length is equal to the ungrooved length).
  • each slot dimension and shape
  • the slots are for example obtained by water jet drilling or wire cutting, these operations being controlled by a numerical control.

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Combustion Methods Of Internal-Combustion Engines (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Portable Nailing Machines And Staplers (AREA)
  • Details Of Aerials (AREA)

Claims (2)

  1. Ringförmige Brennkammer einer Turbomaschine, die Längswände (6, 8), welche durch einen querverlaufenden Kammerboden (10) verbunden sind, und eine einstückige Verkleidung (12) umfaßt, wobei der Kammerboden (10) und die Verkleidung (12) jeweils einen inneren Flansch (16, 20) und einen äußeren Flansch (18, 22) umfassen, die jeweils von einer Vielzahl von Löchern (16a bis 22a) für den Durchgriff von Befestigungssystemen (14) für die Befestigung der Verkleidung an dem Kammerboden durchbohrt sind, dadurch gekennzeichnet, daß jedem Befestigungssystem (14) wenigstens ein in Bezug auf die ringförmige Geometrie der Brennkammer tangentialer Schlitz (30) zugeordnet ist, der an dem entsprechenden Flansch (16, 18) des Kammerbodens (10) und/oder an dem entsprechenden Flansch (20, 22) der Verkleidung (12) ausgebildet ist, wobei jeder Schlitz (30) in unmittelbarer Nähe des entsprechenden Befestigungssystems (14) ausgebildet ist.
  2. Turbomaschine, dadurch gekennzeichnet, daß sie eine ringförmige Brennkammer (4) nach Anspruch 1 umfaßt.
EP07101654A 2006-02-08 2007-02-02 Tubomaschinenbrennkammer mit tangentialen Schlitzen Active EP1818616B1 (de)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
FR0650447A FR2897144B1 (fr) 2006-02-08 2006-02-08 Chambre de combustion de turbomachine a fentes tangentielles

Publications (2)

Publication Number Publication Date
EP1818616A1 EP1818616A1 (de) 2007-08-15
EP1818616B1 true EP1818616B1 (de) 2012-12-26

Family

ID=37102162

Family Applications (1)

Application Number Title Priority Date Filing Date
EP07101654A Active EP1818616B1 (de) 2006-02-08 2007-02-02 Tubomaschinenbrennkammer mit tangentialen Schlitzen

Country Status (6)

Country Link
US (1) US7673457B2 (de)
EP (1) EP1818616B1 (de)
CN (1) CN101017000A (de)
CA (1) CA2577527C (de)
FR (1) FR2897144B1 (de)
RU (1) RU2422730C2 (de)

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* Cited by examiner, † Cited by third party
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FR2911668B1 (fr) * 2007-01-18 2009-03-20 Snecma Sa Chambre de combustion d'une turbomachine
FR2914399B1 (fr) * 2007-03-27 2009-10-02 Snecma Sa Carenage pour fond de chambre de combustion.
FR2918443B1 (fr) * 2007-07-04 2009-10-30 Snecma Sa Chambre de combustion comportant des deflecteurs de protection thermique de fond de chambre et moteur a turbine a gaz en etant equipe
US20090090110A1 (en) * 2007-10-04 2009-04-09 Honeywell International, Inc. Faceted dome assemblies for gas turbine engine combustors
FR2929689B1 (fr) * 2008-04-03 2013-04-12 Snecma Propulsion Solide Chambre de combustion de turbine a gaz a parois interne et externe sectorisees
US20100186234A1 (en) * 2009-01-28 2010-07-29 Yehuda Binder Electric shaver with imaging capability
US8511089B2 (en) * 2009-07-31 2013-08-20 Rolls-Royce Corporation Relief slot for combustion liner
FR2964725B1 (fr) * 2010-09-14 2012-10-12 Snecma Carenage aerodynamique pour fond de chambre de combustion
EP2781838B1 (de) * 2011-11-16 2019-04-24 Mitsubishi Hitachi Power Systems, Ltd. Gasturbinenbrennkammer
US9133722B2 (en) * 2012-04-30 2015-09-15 General Electric Company Transition duct with late injection in turbine system
US20160024959A1 (en) * 2013-03-13 2016-01-28 United Technologies Corporation Variable vane drive system
FR3015639B1 (fr) * 2013-12-20 2018-08-31 Safran Aircraft Engines Chambre de combustion dans une turbomachine
FR3017693B1 (fr) * 2014-02-19 2019-07-26 Safran Helicopter Engines Chambre de combustion de turbomachine
DE102015212573A1 (de) * 2015-07-06 2017-01-12 Rolls-Royce Deutschland Ltd & Co Kg Gasturbinenbrennkammer mit integriertem Turbinenvorleitrad sowie Verfahren zu deren Herstellung
DE102015213629A1 (de) * 2015-07-20 2017-01-26 Rolls-Royce Deutschland Ltd & Co Kg Abdeckteil und Brennkammerbaugruppe für eine Gasturbine
DE102015224990A1 (de) * 2015-12-11 2017-06-14 Rolls-Royce Deutschland Ltd & Co Kg Verfahren zur Montage einer Brennkammer eines Gasturbinentriebwerks
JP6763519B2 (ja) * 2016-03-31 2020-09-30 三菱パワー株式会社 燃焼器およびガスタービン
GB201613110D0 (en) 2016-07-29 2016-09-14 Rolls Royce Plc A combustion chamber
US11015812B2 (en) * 2018-05-07 2021-05-25 Rolls-Royce North American Technologies Inc. Combustor bolted segmented architecture
CN111561713B (zh) * 2020-04-16 2021-08-06 中国航发湖南动力机械研究所 直流燃烧室火焰筒
WO2021219445A1 (en) 2020-04-30 2021-11-04 Tk Airport Solutions, S.A. Method for docking a passenger boarding bridge to an aircraft
CN115183277B (zh) * 2022-06-02 2024-05-17 中国航发四川燃气涡轮研究院 一种火焰筒

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Also Published As

Publication number Publication date
CA2577527A1 (fr) 2007-08-08
US7673457B2 (en) 2010-03-09
RU2007104723A (ru) 2008-08-20
CN101017000A (zh) 2007-08-15
CA2577527C (fr) 2014-09-30
FR2897144B1 (fr) 2008-05-02
EP1818616A1 (de) 2007-08-15
FR2897144A1 (fr) 2007-08-10
US20080010997A1 (en) 2008-01-17
RU2422730C2 (ru) 2011-06-27

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