EP1193451A2 - Tête de chambre de combustion d'une turbine à gaz - Google Patents

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

Info

Publication number
EP1193451A2
EP1193451A2 EP01122467A EP01122467A EP1193451A2 EP 1193451 A2 EP1193451 A2 EP 1193451A2 EP 01122467 A EP01122467 A EP 01122467A EP 01122467 A EP01122467 A EP 01122467A EP 1193451 A2 EP1193451 A2 EP 1193451A2
Authority
EP
European Patent Office
Prior art keywords
combustion chamber
base plate
heat shield
chamber head
head according
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Granted
Application number
EP01122467A
Other languages
German (de)
English (en)
Other versions
EP1193451B1 (fr
EP1193451A3 (fr
Inventor
Michael Ebel
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 EP1193451A2 publication Critical patent/EP1193451A2/fr
Publication of EP1193451A3 publication Critical patent/EP1193451A3/fr
Application granted granted Critical
Publication of EP1193451B1 publication Critical patent/EP1193451B1/fr
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

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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
    • F23R3/02—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration
    • F23R3/04—Air inlet arrangements
    • F23R3/10—Air inlet arrangements for primary air
    • 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

Definitions

  • the invention relates to a gas turbine, with at least a combustion chamber, a combustion chamber wall, a base plate, at least one heat shield, at least one cuff and a cover.
  • the prior art shows different designs of designs for combustion chamber heads. These are for example as a one-piece annular combustion chamber made up of several assembled components not releasably connected.
  • the main components are the inner and the outer Combustion chamber wall and the combustion chamber head. This is called Individual part, for example by means of a casting process or also from individual components such as sheet metal, turned parts, etc. manufactured.
  • combustion chamber heads are known, for example, from EP 841 520 A2, US 5,524,430, EP 927 854 A2, US 5,289,687 or US 5,331,815 previously known.
  • the known constructions are characterized by this from that the assembly is very complex.
  • the assembly of the heat shield together with the sleeves the base plate is designed in some of the known constructions as difficult because these assembly operations from the Combustion chamber exit must be carried out. Increase it the assembly costs are therefore very considerable.
  • the known combustion chamber heads have problem areas with regard to the supply of cooling air since the individual Components in parts of the supply of cooling air to the Can block the heat shield.
  • the invention has for its object a combustion chamber head to create the type mentioned above, which with simple Construction simple and inexpensive to manufacture and assemble is and allows good cooling of the heat shield.
  • the object is characterized by the features of Main claim solved, the sub-claims show further advantageous Embodiments of the invention.
  • the combustion chamber head according to the invention is characterized by a A number of significant advantages.
  • the heat shield from the downstream side is mounted on the base plate, while all other components from the upstream side the base plate can be installed.
  • This type of assembly is far easier since it does not require bolt connections or the like from the combustion chamber and fasten.
  • the removable cover results in free, undisturbed access to the assembly areas. Since the Cover as an additional, removable, independent component is manufactured, the entire assembly of the combustion chamber head done in a hassle-free manner. It is not required, as known from the prior art, in the Cover to provide recesses or the like. Much more is the upstream side of the base plate according to the invention freely accessible.
  • the heat shield has stud bolts, which can be carried out by recessing the base plate. It can thus separate bolts or the like can be dispensed with to handle. Furthermore, those attached to the heat shield offer Stud bolts provide a high level of operational safety because there is no risk of parts coming loose during the Operating can get into the combustion chamber.
  • the cuff is preferably attached according to the invention by means of holding elements on the base plate.
  • This Holding elements can in a favorable development of the invention be attached to the studs of the heat shield. Additional Bolts or screw connections can therefore be used entirely omitted.
  • the overall structure of the device is simplified quite considerably.
  • each holding element has two neighboring ones Holds cuffs. This makes it possible to To design holding elements smaller, since these only one Must enclose part of the cuff. This also leads to an improved cooling air supply.
  • a stud is arranged for fastening the cover. This can therefore be simply placed on the stud bolts and screwed from the outside.
  • the base plate as from the state known in the art with a variety of cooling air openings Mistake.
  • the proposed construction according to the invention allows between the outer wall of the cylindrical rim of the cuff and the inner wall of the edge of the heat shield one to leave a defined gap that is radial and circumferential Displacement of a fuel nozzle and the combustion chamber head to each other.
  • the collar of the cuff is around the maximum possible amount of displacement greater than the outer Diameter of the edge of the heat shield is wide, too at the maximum possible displacement of the cuff the space in front of the base plate against the combustion chamber regarding accidental To seal leakage air. So there are a lot advantageous installation and operating conditions.
  • the holding element can thus be designed that, as already mentioned, also as a bracket serves for the cover.
  • FIG. 1 shows an embodiment known from the prior art, in which an outer combustion chamber wall 2 and an inner combustion chamber wall 3 in one piece with a base plate 1 (metering panel) are trained. It is also in one piece a cover 6 (cowling) formed with the base plate 1.
  • a heat shield 4 is not shown in detail Bolt screwed to the base plate. The heat shield 4 holds at the same time a sleeve 5.
  • a collar 16 of the cuff 5 with the interposition of a spacer 17 biased against the base plate 1. In the cuff 5 a burner 15 is used.
  • FIG. 2 to 5 An exemplary embodiment according to the invention is shown in FIG. 2 to 5 described.
  • FIG. 2 shows a schematic side view - in section -
  • a ring combustion chamber with a simplified representation outer combustion chamber wall 2 and an inner combustion chamber wall 3.
  • a base plate is integral with the combustion chamber walls 2 and 3 1 formed, which has corresponding recesses, through which cylindrical edges 13 of a heat shield 4th are feasible (see Fig. 3 and 4).
  • the edge 13 of the heat shield 4 extends in the axial direction upstream.
  • a cuff 5 with an annular Collar 14 lies on the edge 13 of the heat shield 4 on.
  • the collar 14 is, as already mentioned, in its diameter trained to have a lateral displacement of the Cuff 5 relative to the base plate 1 or the Heat shield 4 allows without the risk of cooling air leakage consists.
  • the heat shield has 4 a plurality of stud bolts 7 (only a few of which are shown in FIG Clarification of the representation are shown).
  • the stud bolts 7 reach through recesses of the base plate 1 and the base areas of holding elements 8, so that a common screw the holding elements 8 and the heat shield 4 on the base plate 1 is done.
  • Fig. 6 shows a sectional view, similar to Fig. 4, wherein however the section plane through at least one of the stud bolts 7 of the heat shield 4 is placed to screw the Heat shield 4 by means of the stud 7 on the base plate 1 with the interposition of the holding element 8 to clarify.
  • the holding elements 8 each have a central area a stud 9, as shown in Fig. 4, for attachment the cover 6 is used.
  • Annular grooves 11 are formed on the base plate 1 (see FIG. Fig. 5), in each of which an edge 10 of the cover 6 can be used is (Fig. 3).
  • the base plate is in a known manner with a large number of cooling air openings 12 provided. Due to the construction provided according to the invention there are sufficient gaps between them Supply cooling air to the heat shield 4.
  • the inventive Combustion chamber head provided that cooling air through recesses the cover 6 both directly through the cooling air openings 12 the base plate 1 is supplied to the heat shield 4, as well in the area of the sleeve 5 by from the edge 13 of the heat shield 4 and the collar 14 of the cuff 5 below the Holding element 8 formed spaces 19 through the cooling air openings 12 of the base plate 1 to the heat shield 4 becomes.
  • the construction proposed according to the invention thus enables a simplified assembly of the cuffs by the possibility disassembly of the cover. Furthermore, the Cooling air for the heat shield right up to the central hole be introduced in the heat shield. With that, everyone can Apply efficient cooling to heat shield areas. Furthermore, a heat shield construction is made possible with the one between the heat shield and the base plate Air mass flow the entire rear heat shield area sweeping outside can be directed to there then as a starter film for the combustion chamber walls serve. On the one hand, the advantages are a simplified one Assembly resulting in significant cost savings leads, on the other hand, to better cooling of the heat shield, through which an increased lifespan and the Possibility of cooling air savings results.
  • the comparison cooling air saved in relation to the prior art for example be integrated into the combustion process, which results in a additional pollutant reduction results.
  • the invention relates to a combustion chamber head for a Gas turbine, with at least one combustion chamber wall 2, 3, one Base plate 1, at least one heat shield 4, at least one Cuff 5 and a cover 6, characterized in that the base plate 1 integrally with the outer 2 and the inner 3 combustion chamber wall is formed that the heat shield 4 from the downstream side of the base plate 1 this is mounted so that the cuff 5 from the upstream Side is mounted on the base plate 1 and that the Cover 6 is releasably attached to the base plate 1.

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Portable Nailing Machines And Staplers (AREA)
  • Cylinder Crankcases Of Internal Combustion Engines (AREA)
  • Supercharger (AREA)
EP01122467A 2000-10-02 2001-09-20 Tête de chambre de combustion d'une turbine à gaz Expired - Lifetime EP1193451B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE10048864A DE10048864A1 (de) 2000-10-02 2000-10-02 Brennkammerkopf für eine Gasturbine
DE10048864 2000-10-02

Publications (3)

Publication Number Publication Date
EP1193451A2 true EP1193451A2 (fr) 2002-04-03
EP1193451A3 EP1193451A3 (fr) 2002-05-15
EP1193451B1 EP1193451B1 (fr) 2005-01-26

Family

ID=7658490

Family Applications (1)

Application Number Title Priority Date Filing Date
EP01122467A Expired - Lifetime EP1193451B1 (fr) 2000-10-02 2001-09-20 Tête de chambre de combustion d'une turbine à gaz

Country Status (3)

Country Link
US (1) US6679063B2 (fr)
EP (1) EP1193451B1 (fr)
DE (2) DE10048864A1 (fr)

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2966352A1 (fr) * 2014-07-09 2016-01-13 Rolls-Royce Deutschland Ltd & Co KG Chambre de combustion d'une turbine a gaz dotee de tete de chambre de combustion vissee
EP2503242A3 (fr) * 2011-03-24 2017-11-08 Rolls-Royce Deutschland & Co. KG Tête pour chambre de combustion avec fixation pour les joints d'étanchéité des brûleurs dans des turbines à gaz

Families Citing this family (35)

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US7308794B2 (en) * 2004-08-27 2007-12-18 Pratt & Whitney Canada Corp. Combustor and method of improving manufacturing accuracy thereof
US7748221B2 (en) 2006-11-17 2010-07-06 Pratt & Whitney Canada Corp. Combustor heat shield with variable cooling
US7681398B2 (en) 2006-11-17 2010-03-23 Pratt & Whitney Canada Corp. Combustor liner and heat shield assembly
US7721548B2 (en) 2006-11-17 2010-05-25 Pratt & Whitney Canada Corp. Combustor liner and heat shield assembly
GB0705458D0 (en) * 2007-03-22 2007-05-02 Rolls Royce Plc A Location ring arrangement
US7861530B2 (en) * 2007-03-30 2011-01-04 Pratt & Whitney Canada Corp. Combustor floating collar with louver
US7926280B2 (en) * 2007-05-16 2011-04-19 Pratt & Whitney Canada Corp. Interface between a combustor and fuel nozzle
US9188341B2 (en) * 2008-04-11 2015-11-17 General Electric Company Fuel nozzle
JP4815513B2 (ja) * 2009-07-06 2011-11-16 川崎重工業株式会社 ガスタービン燃焼器
DE102009046066A1 (de) * 2009-10-28 2011-05-12 Man Diesel & Turbo Se Brenner für eine Turbine und damit ausgerüstete Gasturbine
US8943835B2 (en) * 2010-05-10 2015-02-03 General Electric Company Gas turbine engine combustor with CMC heat shield and methods therefor
DE102011014670A1 (de) 2011-03-22 2012-09-27 Rolls-Royce Deutschland Ltd & Co Kg Segmentierter Brennkammerkopf
US9021675B2 (en) 2011-08-15 2015-05-05 United Technologies Corporation Method for repairing fuel nozzle guides for gas turbine engine combustors using cold metal transfer weld technology
US10378775B2 (en) 2012-03-23 2019-08-13 Pratt & Whitney Canada Corp. Combustor heat shield
US9021812B2 (en) 2012-07-27 2015-05-05 Honeywell International Inc. Combustor dome and heat-shield assembly
WO2014163669A1 (fr) 2013-03-13 2014-10-09 Rolls-Royce Corporation Ensemble chambre de combustion pour turbine à gaz
DE102013007443A1 (de) 2013-04-30 2014-10-30 Rolls-Royce Deutschland Ltd & Co Kg Brennerdichtung für Gasturbinen-Brennkammerkopf und Hitzeschild
DE102013222863A1 (de) 2013-11-11 2015-05-13 Rolls-Royce Deutschland Ltd & Co Kg Gasturbinenbrennkammer sowie Verfahren zu deren Herstellung
DE102014204468A1 (de) * 2014-03-11 2015-10-01 Rolls-Royce Deutschland Ltd & Co Kg Gasturbinenbrennkammer sowie Verfahren zu deren Herstellung
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
GB2543803B (en) * 2015-10-29 2019-10-30 Rolls Royce Plc A combustion chamber assembly
DE102015224990A1 (de) * 2015-12-11 2017-06-14 Rolls-Royce Deutschland Ltd & Co Kg Verfahren zur Montage einer Brennkammer eines Gasturbinentriebwerks
US20170176004A1 (en) * 2015-12-18 2017-06-22 Pratt & Whitney Canada Corp. Combustor floating collar assembly
GB201701380D0 (en) 2016-12-20 2017-03-15 Rolls Royce Plc A combustion chamber and a combustion chamber fuel injector seal
US10378770B2 (en) * 2017-01-27 2019-08-13 General Electric Company Unitary flow path structure
US10837640B2 (en) * 2017-03-06 2020-11-17 General Electric Company Combustion section of a gas turbine engine
CN107575889B (zh) * 2017-09-05 2023-05-16 中国联合重型燃气轮机技术有限公司 燃气轮机的燃料喷嘴
GB201715366D0 (en) 2017-09-22 2017-11-08 Rolls Royce Plc A combustion chamber
US10823419B2 (en) * 2018-03-01 2020-11-03 General Electric Company Combustion system with deflector
US11125436B2 (en) * 2019-07-03 2021-09-21 Pratt & Whitney Canada Corp. Combustor floating collar mounting arrangement
US11428410B2 (en) 2019-10-08 2022-08-30 Rolls-Royce Corporation Combustor for a gas turbine engine with ceramic matrix composite heat shield and seal retainer
US11466858B2 (en) 2019-10-11 2022-10-11 Rolls-Royce Corporation Combustor for a gas turbine engine with ceramic matrix composite sealing element
FR3112382B1 (fr) * 2020-07-10 2022-09-09 Safran Aircraft Engines Chambre annulaire de combustion pour une turbomachine d’aeronef
US11892165B2 (en) 2021-05-19 2024-02-06 General Electric Company Heat shield for fuel nozzle

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US5996335A (en) * 1995-04-27 1999-12-07 Bmw Rolls-Royce Gmbh Head part of an annular combustion chamber of a gas turbine having a holding part to secure a burner collar in a bayonet-catch type manner

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Publication number Priority date Publication date Assignee Title
US5129231A (en) * 1990-03-12 1992-07-14 United Technologies Corporation Cooled combustor dome heatshield
US5419115A (en) * 1994-04-29 1995-05-30 United Technologies Corporation Bulkhead and fuel nozzle guide assembly for an annular combustion chamber
US5956955A (en) * 1994-08-01 1999-09-28 Bmw Rolls-Royce Gmbh Heat shield for a gas turbine combustion chamber
US5924288A (en) * 1994-12-22 1999-07-20 General Electric Company One-piece combustor cowl
US5996335A (en) * 1995-04-27 1999-12-07 Bmw Rolls-Royce Gmbh Head part of an annular combustion chamber of a gas turbine having a holding part to secure a burner collar in a bayonet-catch type manner

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2503242A3 (fr) * 2011-03-24 2017-11-08 Rolls-Royce Deutschland & Co. KG Tête pour chambre de combustion avec fixation pour les joints d'étanchéité des brûleurs dans des turbines à gaz
EP2966352A1 (fr) * 2014-07-09 2016-01-13 Rolls-Royce Deutschland Ltd & Co KG Chambre de combustion d'une turbine a gaz dotee de tete de chambre de combustion vissee
US10012390B2 (en) 2014-07-09 2018-07-03 Rolls-Royce Deutschland Ltd & Co Kg Combustion chamber of a gas turbine with bolted combustion chamber head

Also Published As

Publication number Publication date
EP1193451B1 (fr) 2005-01-26
DE10048864A1 (de) 2002-04-11
US6679063B2 (en) 2004-01-20
DE50105179D1 (de) 2005-03-03
US20020038549A1 (en) 2002-04-04
EP1193451A3 (fr) 2002-05-15

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