EP2503242B1 - Tête pour chambre de combustion avec fixation pour les joints d'étanchéité des brûleurs dans des turbines à gaz - Google Patents

Tête pour chambre de combustion avec fixation pour les joints d'étanchéité des brûleurs dans des turbines à gaz Download PDF

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Publication number
EP2503242B1
EP2503242B1 EP12002047.4A EP12002047A EP2503242B1 EP 2503242 B1 EP2503242 B1 EP 2503242B1 EP 12002047 A EP12002047 A EP 12002047A EP 2503242 B1 EP2503242 B1 EP 2503242B1
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EP
European Patent Office
Prior art keywords
combustion chamber
burner
seal
base plate
holder
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
EP12002047.4A
Other languages
German (de)
English (en)
Other versions
EP2503242A3 (fr
EP2503242A2 (fr
Inventor
Miklós Dr.-Ing. Gerendás
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.)
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Publication date
Application filed by Rolls Royce Deutschland Ltd and Co KG filed Critical Rolls Royce Deutschland Ltd and Co KG
Publication of EP2503242A2 publication Critical patent/EP2503242A2/fr
Publication of EP2503242A3 publication Critical patent/EP2503242A3/fr
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Publication of EP2503242B1 publication Critical patent/EP2503242B1/fr
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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
    • F23R3/002—Wall structures
    • 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
    • F23R2900/00012—Details of sealing devices

Definitions

  • the invention relates to a combustion chamber head of a gas turbine, in particular the invention relates to a combustion chamber head according to the features of the preamble of claim 1.
  • a seal is shown around a burner of a gas turbine, which is arranged upstream of a base plate of the combustion chamber, projects through it and a heat shield into the combustion chamber and fulfills the same function as described above.
  • the seal can no longer leave its intended place, but can only be moved in the axial direction along the burner.
  • the actual sealing force which is absolutely necessary for generating and maintaining the sealing function, is usually not provided in gas turbine combustion chambers by a spring element, but by the pressure difference between the combustion chamber outside and the combustion chamber inside, which acts on the effective surface of the seal.
  • this anti-rotation device for guiding the burner and its seal is shown, some of which are made in one piece with the base plate of the combustion chamber or are fixed or movably fastened thereon.
  • this anti-rotation device is represented by a sheet metal ring with radial tabs which engage in recesses in adjacent ring-shaped components. These radial tabs are not used as elastic elements during assembly.
  • US 5 222 358 A a system for the releasable mounting of a pre-evaporator pot on a combustion chamber of a gas turbine engine.
  • EP 1 193 451 A2 a combustor head of a gas turbine with a heat shield and a sleeve, which is held in position with holding elements, is known.
  • WO 96/18853 A1 shows a holder of a fuel nozzle of a gas turbine burner.
  • the invention has for its object to provide a combustion chamber head of the type mentioned, which has a simple design and simple, inexpensive to manufacture, a simple design of the burner seal and is simple and inexpensive to assemble.
  • the combustion chamber head has a base plate which is provided with a central recess in which at least one burner is arranged.
  • the base plate is connected at its radially inner and outer areas to walls of the combustion chamber, in particular an inner and an outer wall of an annular combustion chamber (combustion chamber housing).
  • a burner seal sealing the burner to the edge of the recess is provided according to the invention.
  • the burner seal is arranged upstream of the base plate and can be brought into abutment against a collar formed on the base plate and forming the edge of the central recess. This creates a seal between the burner seal and the base plate.
  • a holding element of the burner seal is designed in the form of a ring and is arranged upstream of the burner seal.
  • the annular holding element is in engagement with at least one shoulder of the base plate.
  • This approach can be designed, for example, in the form of a thickening.
  • the ring-shaped holding element is provided with at least one locking tab which engages with the attachment of the base plate (thickening).
  • the tab is preferably arranged on the inner ring of the annular holding element; according to the invention it is also possible to form the tab on the outer ring of the annular holding element.
  • the tab In order to bring the tab into engagement with the extension, it has a recess into which the tab can be inserted, in particular by deforming the tab.
  • the burner seal is funnel-shaped on its upstream side.
  • the seal as in DE 100 48 864 A1 to be provided upstream of the base plate of the combustion chamber, which can be brought to bear on a collar of the base plate which runs around the recess for carrying out the burner seal, and a holder for the burner seal is a simple sheet metal ring with, for example, three outwardly projecting tabs, which are formed in recesses in thickened areas Engage the base plate of the combustion chamber.
  • the burner seal has a feed funnel at the upstream end, which simplifies the assembly of the burner and no longer fulfills any other function during operation.
  • the tabs on the annular seal holder can be attached to the inner or outer edge of the seal holder.
  • the ring-shaped holding element (sheet metal ring) is placed over the burner seal in such a way that the tabs come to rest next to the recesses in the three recesses of the thickened base plate. Then the tabs of the ring-shaped holding element are pressed in the direction of the base plate by a correspondingly shaped tool and the ring-shaped holding element is rotated by a small angle. As a result, the tabs engage in the recesses of the thickening (of the attachment) of the base plate in such a way that the annular holding element can no longer turn back, but the tabs can spring back into their original shape without being under tension.
  • An anti-twist device for the burner seal itself is not necessary according to general operating experience and is therefore not made possible by the installation described here.
  • the burner seal is kept close to the combustion chamber head during the entire operating time.
  • the sealing force is generated by the pressure difference between the air flowing around the combustion chamber and the air in the combustion chamber and not by the holder of the burner seal. Thanks to the integrated feed hopper, no additional component is required for this function, which in turn would have to be attached reliably and reliably. The costs for the manufacture and assembly of an anti-rotation device are saved since this function is not necessary.
  • the gas turbine engine 10 is an example of a turbomachine to which the invention can be applied. However, it is clear from the following that the invention can also be used in other turbomachinery.
  • the engine 10 is designed in a conventional manner and comprises an air inlet 11, a fan 12 rotating in a housing, an intermediate pressure compressor 13, a high pressure compressor 14, combustion chambers 15, a high pressure turbine 16, an intermediate pressure turbine 17 and a low pressure turbine 18 and an exhaust gas nozzle in the flow direction 19, which are all arranged around a central engine axis 1.
  • the intermediate pressure compressor 13 and the high pressure compressor 14 each comprise a plurality of stages, each of which has a circumferential arrangement of fixed stationary guide vanes 20, which are generally referred to as stator vanes, and which extend radially inward from the engine housing 21 in an annular flow channel through the compressors 13, 14 protrude.
  • the compressors also have an arrangement of compressor blades 22 which protrude radially outward from a rotatable drum or disk 26 which are coupled to hubs 27 of the high-pressure turbine 16 or the intermediate-pressure turbine 17.
  • the turbine sections 16, 17, 18 have similar steps, comprising an arrangement of fixed guide vanes 23 which extend radially inward from the housing 21 into the annular flow channel project through the turbines 16, 17, 18, and a subsequent array of turbine blades 24 projecting outwardly from a rotatable hub 27.
  • the compressor drum or compressor disk 26 and the blades 22 arranged thereon and the turbine rotor hub 27 and the turbine rotor blades 24 arranged thereon rotate during operation about the engine axis 1.
  • the Fig. 2 shows the area of a combustion chamber 108 of a gas turbine in a simplified schematic representation.
  • This includes an inner combustion chamber housing 109 and an outer combustion chamber housing 110.
  • a combustion chamber head 107 is arranged upstream of the combustion chamber 108, in which a burner 106 with arm and head is arranged.
  • the air supply to the combustion chamber 8 takes place via a front fan 101 (fan) which is driven by a drive shaft 102.
  • a compressor 103 is also connected to the drive shaft 102.
  • Reference numeral 104 shows a bypass flow (bypass flow channel).
  • the incoming air is directed via a compressor outlet stator 105 with a diffuser.
  • the flow emerging from the combustion chamber 108 is carried out by a turbine stator 111 and a turbine impeller 112.
  • the Fig. 3 shows a schematic detailed view of an embodiment of the solution according to the invention.
  • a base plate 113 is arranged on the upstream end region of the combustion chamber 108 and is provided with a recess which is delimited by a collar 118.
  • the burner 106 is passed through the recess, as shown in FIGS Fig. 1 and 2 is shown.
  • the base plate 113 is provided with an extension 114 (thickening).
  • the thickening 114 supports a burner seal 116 in a recess 115, which is ring-shaped, as is known from the prior art.
  • the burner seal 116 is held by a holding element 117 (holding ring), as is described in the following figures.
  • the Fig. 4 shows a part of the annular base plate 113, which is provided with the collar 118, which delimits the recess 121 for the passage of the burner 106.
  • Distributed around the circumference of the collar 118 are three lugs 114 (thickening of the base plate 113).
  • the Fig. 5 shows a schematic partial side sectional view of the base plate 113 with the collar 118 and an approach 114 with a recess 115.
  • Die Fig. 6 shows the in Fig. 5 Arrangement shown in the assembled state of the annular burner seal 116 and the holding element 117 (retaining ring).
  • the holding element 117 shows a locking tab (tab) 120, as will be described below.
  • the Fig. 6 shows the arrangement of the locking tab 120 on the radially outer region of the retaining ring 117, as shown in the right half of the figure Fig. 8 is shown. There are three locking tabs (tabs) 120 distributed around the circumference.
  • the Fig. 7 shows a variant in which the locking tab 120 is introduced into the recess 115 of the extension 114. The fully assembled state is thus shown.
  • the right half of the picture Fig. 8 shows variants of the locking tabs, namely a locking tab 120a of the seal holder (retaining ring 117).
  • the variant of the locking tab 120b is arranged on the outside of the holding ring 117, while the variant of the locking tab 120c is arranged on the inside of the holding ring 117.
  • the locking tabs 120b and 120c are each shown in the bent state.

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)

Claims (3)

  1. Tête de chambre de combustion d'une turbine à gaz comprenant une plaque de base (113) qui est pourvue d'un évidement central (121) dans lequel est disposé au moins un brûleur (106), la plaque de base (113) étant connectée à des parois de la chambre de combustion (108), et comprenant un joint d'étanchéité de brûleur (116) étanchéifiant le brûleur (106) par rapport au bord de l'évidement (121), le joint d'étanchéité de brûleur (116) étant disposé en amont de la plaque de base (113) et pouvant être amené en appui contre un collet (118) réalisé au niveau de la plaque de base (113), formant le bord de l'évidement central (121), et un élément de retenue (117) du joint d'étanchéité de brûleur (116) étant réalisé sous la forme d'un anneau en tôle et étant disposé en amont du joint d'étanchéité de brûleur (116) et étant en prise sans tension avec au moins un appendice (114) de la plaque de base (113), caractérisée en ce que l'élément de retenue (117) est pourvu d'au moins une patte de verrouillage (120a, 120b, 120c) qui est en prise sans tension avec l'appendice (114),
    l'appendice (114) étant pourvu d'au moins un évidement (115) pour l'engagement de la patte de verrouillage (120a, 120b, 120c), et
    le joint d'étanchéité de brûleur (113) étant réalisé au niveau de son côté situé en amont en forme d'entonnoir en vue de l'introduction du brûleur (106).
  2. Tête de chambre de combustion selon la revendication 1, caractérisée en ce que la patte (120a, 120b, 120c) est disposée au niveau du bord intérieur de l'élément de retenue de forme annulaire (117).
  3. Tête de chambre de combustion selon la revendication 1, caractérisée en ce que la patte (120a, 120b, 120c) est disposée au niveau du bord extérieur de l'élément de retenue de forme annulaire (117).
EP12002047.4A 2011-03-24 2012-03-22 Tête pour chambre de combustion avec fixation pour les joints d'étanchéité des brûleurs dans des turbines à gaz Active EP2503242B1 (fr)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
DE102011014972A DE102011014972A1 (de) 2011-03-24 2011-03-24 Brennkammerkopf mit Halterungen für Dichtungen an Brennern in Gasturbinen

Publications (3)

Publication Number Publication Date
EP2503242A2 EP2503242A2 (fr) 2012-09-26
EP2503242A3 EP2503242A3 (fr) 2017-11-08
EP2503242B1 true EP2503242B1 (fr) 2020-03-04

Family

ID=45932107

Family Applications (1)

Application Number Title Priority Date Filing Date
EP12002047.4A Active EP2503242B1 (fr) 2011-03-24 2012-03-22 Tête pour chambre de combustion avec fixation pour les joints d'étanchéité des brûleurs dans des turbines à gaz

Country Status (3)

Country Link
US (1) US9222675B2 (fr)
EP (1) EP2503242B1 (fr)
DE (1) DE102011014972A1 (fr)

Families Citing this family (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE102013007443A1 (de) 2013-04-30 2014-10-30 Rolls-Royce Deutschland Ltd & Co Kg Brennerdichtung für Gasturbinen-Brennkammerkopf und Hitzeschild
EP3039344B1 (fr) * 2013-08-30 2018-08-08 United Technologies Corporation Interface de montage de coupelle de turbulence pour une chambre de combustion de turbine à gaz
GB201321193D0 (en) 2013-12-02 2014-01-15 Rolls Royce Plc A combustion chamber assembly
FR3015639B1 (fr) * 2013-12-20 2018-08-31 Safran Aircraft Engines Chambre de combustion dans une turbomachine
GB2543803B (en) * 2015-10-29 2019-10-30 Rolls Royce Plc A combustion chamber assembly
GB2547906B (en) * 2016-03-02 2019-07-03 Rolls Royce Plc A bladed rotor 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

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US4870818A (en) * 1986-04-18 1989-10-03 United Technologies Corporation Fuel nozzle guide structure and retainer for a gas turbine engine
FR2662784B1 (fr) * 1990-06-05 1992-08-14 Snecma Ensemble d'injection pour turbomachine, comprenant un bol de prevaporisation.
FR2679010B1 (fr) * 1991-07-10 1993-09-24 Snecma Chambre de combustion de turbomachine a bols de prevaporisation demontables.
US5463864A (en) 1993-12-27 1995-11-07 United Technologies Corporation Fuel nozzle guide for a gas turbine engine combustor
US5419115A (en) 1994-04-29 1995-05-30 United Technologies Corporation Bulkhead and fuel nozzle guide assembly for an annular combustion chamber
DE4427222A1 (de) 1994-08-01 1996-02-08 Bmw Rolls Royce Gmbh Hitzeschild für eine Gasturbinen-Brennkammer
US5524438A (en) 1994-12-15 1996-06-11 United Technologies Corporation Segmented bulkhead liner for a gas turbine combustor
US5577379A (en) * 1994-12-15 1996-11-26 United Technologies Corporation Fuel nozzle guide retainer assembly
DE10048864A1 (de) 2000-10-02 2002-04-11 Rolls Royce Deutschland Brennkammerkopf für eine Gasturbine
US7140189B2 (en) * 2004-08-24 2006-11-28 Pratt & Whitney Canada Corp. Gas turbine floating collar
US7131273B2 (en) * 2004-12-17 2006-11-07 General Electric Company Gas turbine engine carburetor with flat retainer connecting primary and secondary swirlers
US7628019B2 (en) * 2005-03-21 2009-12-08 United Technologies Corporation Fuel injector bearing plate assembly and swirler assembly
US7617689B2 (en) * 2006-03-02 2009-11-17 Honeywell International Inc. Combustor dome assembly including retaining ring
FR2903171B1 (fr) * 2006-06-29 2008-10-17 Snecma Sa Agencement a liaison par crabot pour chambre de combustion de turbomachine
US7926280B2 (en) * 2007-05-16 2011-04-19 Pratt & Whitney Canada Corp. Interface between a combustor and fuel nozzle
US8689563B2 (en) * 2009-07-13 2014-04-08 United Technologies Corporation Fuel nozzle guide plate mistake proofing

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Also Published As

Publication number Publication date
DE102011014972A1 (de) 2012-09-27
US9222675B2 (en) 2015-12-29
US20120240595A1 (en) 2012-09-27
EP2503242A3 (fr) 2017-11-08
EP2503242A2 (fr) 2012-09-26

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