EP2503246B1 - Tête de chambre de combustion segmentée - Google Patents

Tête de chambre de combustion segmentée Download PDF

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Publication number
EP2503246B1
EP2503246B1 EP12001992.2A EP12001992A EP2503246B1 EP 2503246 B1 EP2503246 B1 EP 2503246B1 EP 12001992 A EP12001992 A EP 12001992A EP 2503246 B1 EP2503246 B1 EP 2503246B1
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EP
European Patent Office
Prior art keywords
combustion chamber
head
accordance
segments
sealing element
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
EP12001992.2A
Other languages
German (de)
English (en)
Other versions
EP2503246A3 (fr
EP2503246A2 (fr
Inventor
Stefan Penz
Miklos Dr. Gerendas
Sermed Sadig
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 EP2503246A2 publication Critical patent/EP2503246A2/fr
Publication of EP2503246A3 publication Critical patent/EP2503246A3/fr
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Publication of EP2503246B1 publication Critical patent/EP2503246B1/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
    • F23R3/42—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
    • 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
    • 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
    • F23R2900/00—Special features of, or arrangements for continuous combustion chambers; Combustion processes therefor
    • F23R2900/00012—Details of sealing devices
    • 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

Definitions

  • the invention relates to a combustion chamber head according to the features of the preamble of claim 1.
  • the invention relates to a combustor head of a gas turbine having a substantially annular outer combustion chamber wall and at least one substantially annular inner combustion chamber wall and a plurality of burners distributed around the circumference.
  • Prior art annular combustors include a combustor head which is radially bounded by the inner and outer combustor walls.
  • One known construction of the combustor head includes an end wall connected to the inner and outer combustor walls.
  • a heat shield is attached to the inside of the combustion chamber.
  • the heat shields are each positioned around the burner.
  • a sealing element is used for the movable recording of the injection nozzle. This is positioned by means of holders or between the heat shield and the combustion chamber wall. On the outside of the combustion chamber a dome-shaped end wall is attached.
  • the structure of a known from the prior art combustion chamber, in particular of the combustion chamber head, is in DE 44 27 222 A1 described ( Fig. 1 and 4 ).
  • the combustion chamber head consists of a dome-like end wall 101, a front plate 102 extending between the inner and outer combustion chamber walls 107 and 104, a plurality of heat shields 103, a plurality of burners 106 and a sealing element per burner 105. These components are known in the art interconnected, eg welding, screwing or jamming.
  • the heat shields 103 are typically made as segments around the burner positioned and connected to the front panel.
  • DE 100 48 864 A1 ( Fig. 2 and 3 ) also describes the structure of a combustion chamber head.
  • the dome-like end wall 101 is designed as a separate item and mechanically attached to the combustion chamber head.
  • the holding elements 108 act simultaneously as a holder for the dome-like end wall 101 and as a holder of the sealing elements 105th
  • the structural parts are designed as solid rings.
  • These known constructions consist of many individual components that must be mounted. In some cases, additional openings in the dome-shaped end wall are required for installation or this end wall is mounted in an additional operation. The known designs do not form a closed volume, which can be used to dampen acoustic vibrations.
  • the US 5,524,438 A shows a burner head of a gas turbine with a plurality of segmented, circumferentially arranged head segments.
  • the invention has for its object to provide a combustion chamber head of the type mentioned above, which avoids the disadvantages of the prior art with a simple structure and simple, cost-effective manufacturability and assembly. According to the invention the object is achieved by the combination of features of claim 1, the dependent claims show further advantageous embodiments of the invention.
  • a plurality of segment-like, circumferentially arranged head segments are provided, whose number of the number of burners is equal and which in the radial direction between the inner combustion chamber wall and the extend outer combustion chamber wall.
  • the head segments extend in the circumferential direction between radial planes formed by burner center axes.
  • the invention thus describes a solution for constructing a segmented combustion chamber head, in particular for an annular combustion chamber of a gas turbine, in which an overall construction which is simple to produce and very easy to install is provided.
  • the mounted head segments according to the invention form a complete combustion chamber head, including the function of a front panel and the function of a heat shield.
  • the assembled form Head segments a damping volume, which is particularly suitable for soundproofing.
  • the low number of individual components simplifies assembly. Likewise, maintenance and inspection work is easier and less expensive to carry out.
  • the intermediate regions between adjacent head segments are preferably each sealed by at least one sealing element.
  • This may preferably be annular and enclose the burner. It is particularly advantageous if the sealing element is guided in grooves of the burner and / or the head element and thus held and positioned. Remaining radially outer or radially inner intermediate areas can be sealed by additional sealing elements in a simple manner. It is also possible, for example, to provide a fin and a deformable element. Furthermore, it is possible to provide for sealing labyrinth seal-like elements.
  • the solution according to the invention reduces the complexity of the combustion chamber head by combining the combustion chamber head segments with different functions of the individual parts of the conventional combustion chamber head. Furthermore, this construction offers the possibility of providing the volume necessary for damping acoustic vibrations. The operation of such damper is in the DE 10 2009 032 277 A1 described. The required closed volume is provided within a header segment.
  • the Fig. 5 . 6 and 7 show a combustion chamber head, which is not from an annular head element but according to the invention of a plurality of head segments, 201 corresponding to the number of burners 106, constructed. These head segments 201 extend in the radial direction between the inner and outer combustion chamber wall 107 and 104 and are mechanically connected there in a known manner, eg with screws. In the circumferential direction, the head segments 201 each extend in an area between two burners 106. The circumferential division thus always takes place in the burner center axis 208.
  • the movable sealing elements 105 which seal the area around the burner 106 against uncontrolled entry of the compressor air into the combustion chamber 15 and at the same time allow relative movement between burner 106 and combustion head 35 are stored in slots which are integrated in the head segments 201. This reduces the assembly effort and the number of small parts. At the same time, a large area of the gap between two segments is sealed. In the area between the sealing element 105 and the inner or outer combustion chamber wall 107 and 104, the remaining gap is sealed with a sealing strip 202 against uncontrolled air inlet.
  • the gap can also be sealed with a specially shaped sealing element with extensions 203. ( Fig. 8 ).
  • the leakage air flow may also be controlled with a labyrinth 204 formed on the side surfaces of the head segments 201. ( Fig. 9 ).
  • Another possibility of sealing is the formation of mating surfaces on the side walls of the head segments 201.
  • Another possibility of sealing is the formation of one or more fins 206 on one side of the head segment and the application of a readily deformable material 205 on the opposite side of the head segment.
  • This material may be, for example, a metal foam, as in DE 10 360 164 A1 described. ( Fig. 10 ).
  • the assembly of the combustion chamber head is carried out by mating the sealing elements 105, the sealing strip 202 and the head segments 201 to a full ring. Then, the inner and outer combustion chamber walls 107 and 104 are connected to the head segments 201, whereby the sealing members 105 and sealing strips 202 are movably held in position.
  • the socket 207 for receiving the pin can be integrated into individual or all head segments 201 ( Figure 11 ).
  • Fig. 12 shows a schematic representation of a gas turbine engine according to the present invention.
  • 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 outward from a rotatable drum or disc 26 coupled to hubs 27 of high pressure turbine 16 and intermediate pressure turbine 17, respectively.
  • the turbine sections 16, 17, 18 have similar stages, comprising an array of fixed vanes 23 projecting radially inward from the housing 21 into the annular flow passage through the turbines 16, 17, 18, and a downstream array of turbine blades 24 projecting 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. 13 schematically shows compressor outlet blades 31 through which compressor air is introduced into a combustion chamber housing.
  • This comprises a combustion chamber outer housing 32 and a combustion chamber inner housing 33.
  • a burner with arm and head (reference numeral 34) is provided.
  • the reference numeral 35 schematically shows a combustion chamber head, to which a combustion chamber wall 36 connects.
  • the reference numeral 37 schematically turbine inlet blades are shown.

Claims (10)

  1. Tête de chambre de combustion d'une turbine à gaz avec une paroi extérieure de chambre de combustion (104) de forme essentiellement annulaire et au moins une paroi intérieure de chambre de combustion (107) de forme essentiellement annulaire, avec plusieurs brûleurs (106) répartis tout autour de la circonférence, sachant que sont prévus plusieurs segments de tête (201) disposés tout autour de la circonférence, dont le nombre est identique au nombre de brûleurs et qui s'étendent entre la paroi intérieure de chambre de combustion (107) et la paroi extérieure de chambre de combustion (108) dans le sens radial, caractérisée en ce que les segments de tête (201) s'étendent dans le sens circonférentiel entre des plans radiaux (209) formés par les axes médians des brûleurs (208).
  2. Tête de chambre de combustion selon la revendication n° 1, caractérisée en ce qu'au moins un élément d'étanchéité (105, 202, 203) est disposé entre le brûleur (106) et le segment de tête (201).
  3. Tête de chambre de combustion selon la revendication n° 2, caractérisée en ce que l'élément d'étanchéité (105, 203) présente essentiellement une forme annulaire.
  4. Tête de chambre de combustion selon la revendication n° 2 ou n° 3, caractérisée en ce que l'élément d'étanchéité (105, 202, 203) est disposé au moins partiellement dans des rainures du brûleur (106) et/ ou du segment de tête (201).
  5. Tête de chambre de combustion selon une des revendications n° 2 à n° 4, caractérisée en ce que l'élément d'étanchéité comprend au moins une lamelle (206) et un élément déformable (205) pouvant être mis en interaction avec celle-ci.
  6. Tête de chambre de combustion selon une des revendications n° 2 à n° 5, caractérisée en ce que l'élément d'étanchéité comprend au moins une garniture en labyrinthe (204).
  7. Tête de chambre de combustion selon une des revendications n° 1 à n° 6, caractérisée en ce que le segment de tête (201) comprend au moins un coussinet (207) pour interagir avec au moins un élément de support (108).
  8. Tête de chambre de combustion selon une des revendications n° 1 à n° 7, caractérisée en ce que les segments de tête (201) à l'état monté forment au moins un volume d'amortissement.
  9. Tête de chambre de combustion selon une des revendications n° 1 à n° 8, caractérisée en ce que les segments de tête (201) à l'état monté forment une tête de chambre de combustion, notamment avec une plaque frontale (102) et un écran thermique (103).
  10. Tête de chambre de combustion selon une des revendications n° 1 à n° 9, caractérisée en ce que les segments de tête (201) à l'état monté sont reliés, hermétiquement ou avec des ouvertures définies, à la paroi extérieure de chambre de combustion (104) et à la paroi intérieure de chambre de combustion (107).
EP12001992.2A 2011-03-22 2012-03-21 Tête de chambre de combustion segmentée Active EP2503246B1 (fr)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
DE102011014670A DE102011014670A1 (de) 2011-03-22 2011-03-22 Segmentierter Brennkammerkopf

Publications (3)

Publication Number Publication Date
EP2503246A2 EP2503246A2 (fr) 2012-09-26
EP2503246A3 EP2503246A3 (fr) 2014-11-26
EP2503246B1 true EP2503246B1 (fr) 2018-12-05

Family

ID=45932099

Family Applications (1)

Application Number Title Priority Date Filing Date
EP12001992.2A Active EP2503246B1 (fr) 2011-03-22 2012-03-21 Tête de chambre de combustion segmentée

Country Status (3)

Country Link
US (1) US9328926B2 (fr)
EP (1) EP2503246B1 (fr)
DE (1) DE102011014670A1 (fr)

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US10378775B2 (en) * 2012-03-23 2019-08-13 Pratt & Whitney Canada Corp. Combustor heat shield
US9498850B2 (en) * 2012-03-27 2016-11-22 Pratt & Whitney Canada Corp. Structural case for aircraft gas turbine engine
DE102013222863A1 (de) 2013-11-11 2015-05-13 Rolls-Royce Deutschland Ltd & Co Kg Gasturbinenbrennkammer sowie Verfahren zu deren Herstellung
US9677767B2 (en) * 2014-05-29 2017-06-13 Siemens Energy, Inc. Combustion turbine with Siamesed wall paired combustor housings
US9625152B2 (en) 2014-06-03 2017-04-18 Pratt & Whitney Canada Corp. Combustor heat shield for a gas turbine engine
US9534785B2 (en) * 2014-08-26 2017-01-03 Pratt & Whitney Canada Corp. Heat shield labyrinth seal
EP3465008B1 (fr) * 2016-07-25 2021-08-25 Siemens Energy Global GmbH & Co. KG Anneaux de résonateur pour turbine à gaz
GB201701380D0 (en) 2016-12-20 2017-03-15 Rolls Royce Plc A combustion chamber and a combustion chamber fuel injector seal
US10724739B2 (en) 2017-03-24 2020-07-28 General Electric Company Combustor acoustic damping structure
US10415480B2 (en) 2017-04-13 2019-09-17 General Electric Company Gas turbine engine fuel manifold damper and method of dynamics attenuation
US11242804B2 (en) * 2017-06-14 2022-02-08 General Electric Company Inleakage management apparatus
US11149948B2 (en) 2017-08-21 2021-10-19 General Electric Company Fuel nozzle with angled main injection ports and radial main injection ports
US10774685B2 (en) * 2018-04-30 2020-09-15 Ratheon Technologies Corporation Gas turbine engine exhaust component
US11015812B2 (en) * 2018-05-07 2021-05-25 Rolls-Royce North American Technologies Inc. Combustor bolted segmented architecture
US11156162B2 (en) 2018-05-23 2021-10-26 General Electric Company Fluid manifold damper for gas turbine engine
US10823415B2 (en) * 2018-06-01 2020-11-03 Raytheon Technologies Corporation Deflector for combustor of gas turbine engine
US11506125B2 (en) 2018-08-01 2022-11-22 General Electric Company Fluid manifold assembly for gas turbine engine

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Also Published As

Publication number Publication date
US20120240583A1 (en) 2012-09-27
EP2503246A3 (fr) 2014-11-26
DE102011014670A1 (de) 2012-09-27
EP2503246A2 (fr) 2012-09-26
US9328926B2 (en) 2016-05-03

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