EP2503242A2 - 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
EP2503242A2
EP2503242A2 EP12002047A EP12002047A EP2503242A2 EP 2503242 A2 EP2503242 A2 EP 2503242A2 EP 12002047 A EP12002047 A EP 12002047A EP 12002047 A EP12002047 A EP 12002047A EP 2503242 A2 EP2503242 A2 EP 2503242A2
Authority
EP
European Patent Office
Prior art keywords
burner
combustion chamber
seal
base plate
recess
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
EP12002047A
Other languages
German (de)
English (en)
Other versions
EP2503242B1 (fr
EP2503242A3 (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.)
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 EP2503242A2 publication Critical patent/EP2503242A2/fr
Publication of EP2503242A3 publication Critical patent/EP2503242A3/fr
Application granted granted Critical
Publication of EP2503242B1 publication Critical patent/EP2503242B1/fr
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
    • F23R3/002—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 detail, the invention relates to a combustion chamber head according to the features of the preamble of claim 1.
  • a gasket around a burner of a gas turbine is shown disposed upstream of a base plate of the combustor, projecting through it and a heat shield into the combustion chamber and performing the same function as described above.
  • the seal can not leave their intended place, but only be moved along the burner in the axial direction.
  • the actual sealing force which is absolutely necessary for the generation and maintenance of the sealing function, is usually not provided by gas turbine combustors 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.
  • a device which is the seal Positioned near the sealing surface without pressing it.
  • the axial positioning is adjusted by a spacer disc, which is located between the base plate of the combustion chamber and the seal.
  • the radial positioning of the seal prior to installation of the Burner is ensured by the shape of the recess in the base plate of the combustion chamber.
  • the positioning of the seal in the radial and axial direction is made possible by crescent-shaped brackets, which are held by the bolts of the heat shield.
  • the in the DE 44 27 222 A1 used shims are adapted to the dimensions of the recess, which slows down the assembly.
  • the in the DE 100 48 864 A1 proposed mounts position two seals, so that when attaching the nuts on the bolts of the heat shields three components must be held, which also makes the assembly difficult.
  • the Indian US 5,419,115 A and the US 5,463,864 A provided joining process in the confined space of the combustion chamber head is a difficult to perform process step with a difficult-to-test result. Overall, all proposed Solutions through the many components to be manufactured and joined complicated, expensive and difficult.
  • the invention has for its object to provide a combustion chamber head of the type mentioned, which has a simple design and simple, cost-effective manufacturability a simple design of the burner seal and is easy and inexpensive to install.
  • 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 regions with walls of the combustion chamber, in particular an inner and an outer wall of an annular combustion chamber (combustion chamber housing).
  • a burner sealing the burner to the edge of the recess is provided.
  • the burner seal according to the invention arranged upstream of the base plate and against a formed on the base plate, the edge of the central recess forming collar for conditioning brought. This seals the burner seal against the base plate.
  • the invention provides that 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 retaining element is engaged with at least one shoulder of the base plate. This approach can be designed for example in the form of a thickening.
  • the annular holding element is provided with at least one locking tab, which is in engagement with the attachment of the base plate (thickening).
  • the tab is preferably arranged on the inner ring of the annular retaining element, according to the invention it is also possible to form the tab on the outer ring of the annular retaining element.
  • this preferably has a recess into which the tab can be introduced, in particular by deformation of the tab.
  • the burner seal is funnel-shaped on its upstream side.
  • the seal as in DE 100 48 864 A1 Provide upstream of the base plate of the combustion chamber, which can be brought to bear on a recess for carrying out the burner seal collar of the base plate to the plant a holder of the burner seal is a simple sheet metal ring with, for example, three outward tabs, which in recesses in the thickenings of Engage the base plate of the combustion chamber.
  • the burner seal at the upstream end has a feed funnel, which facilitates the assembly of the burner and fulfills no further function during operation.
  • the tabs on the annular seal retainer may be attached to the inner or outer edge of the seal retainer.
  • the annular holding element (sheet metal ring) is placed over the burner seal, that the tabs come to rest next to the recesses in the three recesses of the thicker portions of the base plate. Then the tabs of the annular support member are pressed by a correspondingly shaped tool in the direction of the base plate and the annular support member rotated by a small angle. As a result, the tabs engage in the recesses of the thickening (of the approach) of the base plate so that the annular retaining element can not turn back, but the tabs can spring back to their original shape without being under tension.
  • An anti-rotation device for the burner seal itself is not necessary for general operating experience and is therefore not made possible by the here pitched assembly.
  • the integrated feed hopper eliminates the need for an additional component for this function, which in turn would need to be reliably and operationally secured. The costs for the production and installation of an anti-rotation device are saved as this function is not necessary.
  • the gas turbine engine 10 is an example of a turbomachine to which the invention may find application. However, it will be understood from the following that the invention can be used with other turbomachinery as well.
  • the engine 10 is conventionally formed and includes in the flow direction one after another an air inlet 11, a fan 12 circulating 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 nozzle 19, which are all arranged around a central engine axis 1.
  • the intermediate pressure compressor 13 and the high pressure compressor 14 each include a plurality of stages, each of which includes a circumferentially extending array of fixed stationary vanes 20, commonly referred to as stator vanes, that radially inwardly from the engine casing 21 in an annular flow passage through the compressors 13, 14 protrude.
  • the compressors further include an array of compressor blades 22 projecting radially outwardly from a rotatable drum or disc 26 coupled to hubs 27 of the high pressure turbine 16 and the intermediate pressure turbine 17, respectively.
  • the turbine sections 16, 17, 18 have similar steps, comprising an array of fixed vanes 23 extending radially inward from the housing 21 into the housing annular flow channel through the turbines 16, 17, 18 protrude, and a subsequent arrangement of turbine blades 24 which project outwardly from a rotatable hub 27.
  • the compressor drum or compressor disk 26 and the vanes 22 disposed thereon and the turbine rotor hub 27 and the turbine blades 24 disposed thereon rotate about the engine axis 1 during operation.
  • the Fig. 2 shows in a simplified schematic representation of the area of a combustion chamber 108 of a gas turbine.
  • This comprises an inner combustion chamber housing 109 and an outer combustion chamber housing 110.
  • a combustion chamber head 107 is arranged, in which a burner 106 with arm and head is arranged.
  • a compressor 103 is also connected to the drive shaft 102.
  • the reference numeral 104 shows a side stream (bypass channel).
  • the incoming air is passed through a compressor outlet guide 105 with diffuser.
  • the flow exiting the combustion chamber 108 is performed by a turbine nozzle 111 and a turbine runner 112.
  • the Fig. 3 shows a schematic detail view of an embodiment of the inventive solution.
  • a base plate 113 is arranged at the upstream end region of the combustion chamber 108, which is provided with a recess which is delimited by a collar 118. Through the recess of the burner 106 is performed, as in the Fig. 1 and 2 is shown.
  • the base plate 113 is provided with a projection 114 (thickening).
  • the thickening 114 supports in a recess 115 a burner seal 116, which is annular, as known from the prior art.
  • the burner seal 116 is held by a retaining element 117 (retaining ring), as described in the following figures.
  • the Fig. 4 shows a portion of the annular base plate 113, which is provided with the collar 118 which limits the recess 121 for the passage of the burner 106.
  • Distributed around the circumference of the collar 118 are three lugs 114 (thickenings 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 a projection 114 with a recess 115.
  • Die Fig. 6 shows the in Fig. 5 shown arrangement in the mounted state of the annular burner seal 116 and the retaining 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 at the radially outer region of the retaining ring 117, as in the right half of the Fig. 8 is shown. There are three circumferentially distributed locking tabs (tabs) 120 shown.
  • the Fig. 7 shows a variant in which the locking tab 120 is inserted into the recess 115 of the projection 114. It is thus shown the finished assembled state.
  • 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 retaining ring 117, while the variant of the locking tab 120c is arranged on the inside of the retaining 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)
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 true EP2503242A2 (fr) 2012-09-26
EP2503242A3 EP2503242A3 (fr) 2017-11-08
EP2503242B1 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)

Cited By (1)

* 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

Families Citing this family (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
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

Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5419115A (en) 1994-04-29 1995-05-30 United Technologies Corporation Bulkhead and fuel nozzle guide assembly for an annular combustion chamber
US5463864A (en) 1993-12-27 1995-11-07 United Technologies Corporation Fuel nozzle guide for a gas turbine engine combustor
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
DE10048864A1 (de) 2000-10-02 2002-04-11 Rolls Royce Deutschland Brennkammerkopf für eine Gasturbine

Family Cites Families (11)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
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.
US5577379A (en) * 1994-12-15 1996-11-26 United Technologies Corporation Fuel nozzle guide retainer assembly
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

Patent Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
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
DE10048864A1 (de) 2000-10-02 2002-04-11 Rolls Royce Deutschland Brennkammerkopf für eine Gasturbine

Cited By (3)

* 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
EP2799776A1 (fr) 2013-04-30 2014-11-05 Rolls-Royce Deutschland Ltd & Co KG Joint de brûleur pour tête de chambre de combustion de turbines à gaz et bouclier thermique
US10041415B2 (en) 2013-04-30 2018-08-07 Rolls-Royce Deutschland Ltd & Co Kg Burner seal for gas-turbine combustion chamber head and heat shield

Also Published As

Publication number Publication date
US9222675B2 (en) 2015-12-29
US20120240595A1 (en) 2012-09-27
DE102011014972A1 (de) 2012-09-27
EP2503242B1 (fr) 2020-03-04
EP2503242A3 (fr) 2017-11-08

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