EP3182006A1 - Chambre de combustion de turbine à gaz comprenant une fixation de bardeau au moyen d'éléments d'encliquetage - Google Patents

Chambre de combustion de turbine à gaz comprenant une fixation de bardeau au moyen d'éléments d'encliquetage Download PDF

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Publication number
EP3182006A1
EP3182006A1 EP16202396.4A EP16202396A EP3182006A1 EP 3182006 A1 EP3182006 A1 EP 3182006A1 EP 16202396 A EP16202396 A EP 16202396A EP 3182006 A1 EP3182006 A1 EP 3182006A1
Authority
EP
European Patent Office
Prior art keywords
combustion chamber
shingle
chamber wall
gas turbine
latching
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
EP16202396.4A
Other languages
German (de)
English (en)
Other versions
EP3182006B1 (fr
Inventor
Dr. Kay HEINZE
Stefan Penz
Dr. Ivo SZARVASY
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 EP3182006A1 publication Critical patent/EP3182006A1/fr
Application granted granted Critical
Publication of EP3182006B1 publication Critical patent/EP3182006B1/fr
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Anticipated expiration legal-status Critical

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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23M—CASINGS, LININGS, WALLS OR DOORS SPECIALLY ADAPTED FOR COMBUSTION CHAMBERS, e.g. FIREBRIDGES; DEVICES FOR DEFLECTING AIR, FLAMES OR COMBUSTION PRODUCTS IN COMBUSTION CHAMBERS; SAFETY ARRANGEMENTS SPECIALLY ADAPTED FOR COMBUSTION APPARATUS; DETAILS OF COMBUSTION CHAMBERS, NOT OTHERWISE PROVIDED FOR
    • F23M5/00—Casings; Linings; Walls
    • F23M5/04—Supports for linings
    • 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
    • F23R3/16—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration with devices inside the flame tube or the combustion chamber to influence the air or gas flow
    • 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
    • F23R3/06—Arrangement of apertures along the flame tube
    • 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
    • F23R2900/00—Special features of, or arrangements for continuous combustion chambers; Combustion processes therefor
    • F23R2900/00017—Assembling combustion chamber liners or subparts

Definitions

  • the invention relates to a gas turbine combustor according to the features of the preamble of claim 1.
  • the invention relates to a gas turbine combustor having a combustor wall and at least one shingle attached thereto at a distance from the combustor wall.
  • a gas turbine combustor having a combustor wall and at least one shingle attached thereto at a distance from the combustor wall.
  • the outer combustion chamber wall serves as a shingle carrier.
  • the distance between the shingle and the combustion chamber wall is traversed by cooling air.
  • at least one mixing air hole is provided, which penetrates both the combustion chamber wall and the shingle in order to guide mixed air into the interior of the combustion chamber.
  • the shingle has at its peripheral edge on a shingle edge, which rests against the outer combustion chamber wall.
  • the shingle edge serves in particular to maintain the distance between the combustion chamber wall and the shingle and thus to ensure effective cooling.
  • a construction is previously known, in which a stud bolt is connected to a bonded to the cold side of the combustion chamber shingle element.
  • the stud extends through the combustion chamber wall and is bolted to the outside of the combustion chamber wall.
  • a screw connection by means of a bolt which is mounted from the outside of the combustion chamber wall, also shows the EP 2 295 865 A2 .
  • a screw by means of a piece integrally formed with the shingle bolt is from the EP 2 743 585 A1 previously known.
  • a modified construction in which the foot portion of the bolt is cooled by impingement cooling, shows the EP 2 700 877 A2 ,
  • EP 2 738 470 B1 provides a screw connection of a mixing air hole forming fastener with a flange neck approach the shingle. This may result in the disadvantage that the screw must be additionally secured against loosening. Furthermore, only circular mixing air holes can be formed in this construction.
  • combustion chamber shingles protect the combustion chamber housing from high temperatures that arise during combustion in the combustion chamber. To achieve a sufficient service life of the shingles, these are provided on the hot gas side with a ceramic protective layer.
  • the shingles effusion cooling holes through which can escape from the gap between the combustion chamber wall and the shingle cooling air, which lays as a cooling film on the hot side of the shingle. The cooling of the shingle by the Effusionskühllöcher is an essential aspect that ensures a uniform shingles temperature.
  • the invention has for its object to provide a combustion chamber with Schindelbefestist, which avoids the disadvantages of the prior art with a simple structure and simple, cost manufacturability and in particular allows a good cooling of the combustion chamber shingles.
  • the fastening element is provided on its outer side with first Verrastungsstoffn which are engaged with second Verrastungsstoffn which are formed on a tubular Verrastungselement which braces the combustion chamber shingle with the combustion chamber wall.
  • the solution according to the invention thus provides for latching by means of the fastening element.
  • This latching takes place in such a way that the combustion chamber shingle is clamped to the combustion chamber wall with the application of a prestress.
  • no screws or threaded bolts or the like are required. It therefore need not be provided on the shingle itself any additional components.
  • the shingle can be provided with a constant wall thickness, resulting in optimized cooling properties. Since there is no screw connection according to the invention, there is also no risk that the shingle will come off the combustion chamber, for example due to vibrations during operation of the gas turbine.
  • the existing mixing air holes or mixed air openings are used to introduce a respective fastening element in these mixed air openings, which is tubular and extends in the direction of the combustion chamber shingle or through this and is used for locking the combustion chamber shingle. There is thus a self-locking jamming of the combustion chamber shingle.
  • the latching part is formed integrally with the combustion chamber shingles.
  • the Verrastungselement is also possible to manufacture the Verrastungselement as a separate component and to introduce during assembly in the mixing air hole of the combustion chamber shingles.
  • the first embodiment variant is particularly favorable in the case of combustion chamber shingles, which are produced by means of a casting process or by means of an additive process, for example a laser deposition welding process.
  • shingles which from a Sheet metal material are made, easily and reliably secured to the combustion chamber wall.
  • the latching element according to the invention is preferably tubular and has on its inside the second latching means.
  • the first and / or the second latching means may be in the form of ring-like elevations and / or grooves.
  • either the latching element or the fastening element is elastically formed in the region of the latching means. This can for example be realized by at least one longitudinal slot which extends along the central axis of the mixing air hole. It is particularly advantageous if the provided on the combustion chamber shingle latching element is rigid, while the fastening element is at least partially elastic, for example by means of the above-described slotting.
  • the assembly of the combustion chamber shingle can be carried out according to the invention by manual compression and locking of the fastener and the Verrastungselements. Using suitable tools, it is possible to remove the combustion chamber shingle again, for example for repair or maintenance purposes.
  • a significant advantage of the present invention is that the mixing air hole does not have to be round. Rather, it is also possible to provide elongated or oval mixing air holes and to adjust the fastening elements and the locking elements of the shape of the respective mixing air hole accordingly.
  • the solution according to the invention makes it possible, in an advantageous development, to mount the combustion chamber shingle on the combustion chamber wall without the combustion chamber shingle contacting the combustion chamber wall directly in the region of the mixing air hole. Rather, the combustion chamber shingles with their shingle edges against the combustion chamber wall to ensure sufficient clearance for the introduction of cooling air.
  • the assembly can be carried out according to the invention so that a bias between the shingle and the combustion chamber wall is achieved.
  • the size of the bias voltage is structurally selectable, for example, by the height of the shingle edge and / or by the dimensioning of the fastener and the tubular Verrastungselements. The preload secures the assembly of the combustion chamber shingles.
  • the gas turbine engine 110 is a generalized example of a turbomachine, in which the invention can be applied.
  • the engine 110 is formed in a conventional manner and comprises in succession an air inlet 111, a fan 112 circulating in a housing, a medium pressure compressor 113, a high pressure compressor 114, a combustion chamber 115, a high pressure turbine 116, a medium pressure turbine 117 and a low pressure turbine 118 and a Exhaust nozzle 119 with an outlet cone, which are all arranged around a central engine center axis 101.
  • the intermediate pressure compressor 113 and the high pressure compressor 114 each include a plurality of stages, each of which includes a circumferentially extending array of fixed stationary vanes 120, commonly referred to as stator vanes, that radially inwardly from the engine casing 121 in an annular flow passage through the compressors 113, 114 protrude.
  • the compressors further include an array of compressor blades 122 projecting radially outward from a rotatable drum or disk 125 coupled to hubs 126 of high pressure turbine 116 and intermediate pressure turbine 117, respectively.
  • the turbine sections 116, 117, 118 have similar steps, comprising an array of fixed vanes 123 extending radially inward from the housing 121 into the housing annular flow channel through the turbines 116, 117, 118 project, and a subsequent arrangement of turbine blades 124 which project outwardly from a rotatable hub 126.
  • the compressor drum or compressor disk 125 and the vanes 122 disposed thereon and the turbine rotor hub 126 and turbine blades 124 disposed thereon rotate about the engine centerline 101 during operation.
  • the Fig. 2 shows a longitudinal sectional view of a known from the prior art combustion chamber wall in an enlarged view.
  • a combustion chamber 1 is shown with a central axis 9, which comprises a combustion chamber head 3, a base plate 8 and a heat shield 2.
  • a burner seal is provided with the reference numeral 4.
  • the combustion chamber 1 has an outer cold combustion chamber wall 7, to which an inner, hot combustion chamber wall 6 is attached.
  • mixed air mixing air holes 5 are provided for supplying mixed air mixing air holes 5 are provided. The presentation of impingement cooling holes and effusion holes has been omitted for clarity.
  • the inner combustion chamber wall 6 is provided with bolts 13, which are designed as threaded bolts and are screwed by means of nuts 14.
  • the storage of the combustion chamber 1 takes place via combustion chamber flanges 12 and combustion chamber suspensions 11.
  • Denoted by 10 is a sealing lip.
  • the Fig. 3 shows a schematic sectional view of a first embodiment of the invention.
  • a combustion chamber wall 7 is shown, which forms an outer, cold combustion chamber wall 7 and can also be referred to as a shingle support.
  • the combustion chamber wall 7 is provided with a mixing air hole 5, whose central axis is designated 21.
  • a shingle 6 On the hot side of the combustion chamber wall 7, a shingle 6 is arranged, which, as in the 4 and 5 shown, is provided with a circumferential shingle edge 15. This is analogous to the representation of Fig. 6 , against the inside of the combustion chamber wall 7 and thus forms a gap 22 through which cooling air can be performed in a manner not shown, in particular by un-illustrated impingement cooling holes. The cooling air from the gap 22 is passed through effusion cooling holes (not shown) of the shingle 6 on the hot surface of the shingle 6.
  • the Fig. 3 shows that the shingle 6 is also provided with a mixing air hole, which is delimited by a tubular latching element 20.
  • an annular flange 23 is provided, which extends into the interior of the combustion chamber 1.
  • second latching means 19 are formed, which are latched into first latching means 18, which are formed on a tubular fastening element 17.
  • the tubular fastening element 17 has an outer annular flange 16, with which it abuts against the cold outside of the combustion chamber wall 7.
  • the latching means 18 and 19 may be in the form of sawtooth or trapezoidal elevations and / or recesses which extend annularly around the circumference of both the latching element 20 and the tubular fastening element 17.
  • the fastening element 17 By pressing the fastening element 17 into the latching element 20, the two elements are locked together. Since the shingle 6 rests with its shingle edge 15 against the combustion chamber wall 7, there is a gap between the locking element 20 and the combustion chamber wall 7. The height of the latching element 20 is thus less than the height of the shingle edge 15. This makes it possible to make the assembly of the shingle 6 on the combustion chamber wall 7 under a bias.
  • the 4 and 5 show a perspective view of a shingle 6 in view of the cold side ( Fig. 4 ) and the hot side ( Fig. 5 ).
  • the tubular fastening element 17 is illustrated with the annular flange 16.
  • the Fig. 6 shows a further embodiment in which the latching element 20 is formed as a separate component, which has a flange 24, with which the fastening element 20 is supported by the hot side of the shingle 6 at this.
  • the latching element 20 has second latching means 19, which are latched into first latching means 18 of the fastening element 17. Also from the Fig. 6 It can be seen that the shingle edge 15 bears against the combustion chamber wall 7, while the height of the latching element 20 is less than the height of the shingle edge 15, so that the latching element 20 does not touch the combustion chamber wall 7. As a result, the assembly by means of a bias voltage is possible.

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  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
EP16202396.4A 2015-12-14 2016-12-06 Chambre de combustion de turbine à gaz comprenant une fixation de bardeau au moyen d'éléments d'encliquetage Active EP3182006B1 (fr)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
DE102015225107.1A DE102015225107A1 (de) 2015-12-14 2015-12-14 Gasturbinenbrennkammer mit Schindelbefestigung mittels Rastelementen

Publications (2)

Publication Number Publication Date
EP3182006A1 true EP3182006A1 (fr) 2017-06-21
EP3182006B1 EP3182006B1 (fr) 2019-09-04

Family

ID=57542735

Family Applications (1)

Application Number Title Priority Date Filing Date
EP16202396.4A Active EP3182006B1 (fr) 2015-12-14 2016-12-06 Chambre de combustion de turbine à gaz comprenant une fixation de bardeau au moyen d'éléments d'encliquetage

Country Status (3)

Country Link
US (1) US10060626B2 (fr)
EP (1) EP3182006B1 (fr)
DE (1) DE102015225107A1 (fr)

Families Citing this family (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US11022308B2 (en) * 2018-05-31 2021-06-01 Honeywell International Inc. Double wall combustors with strain isolated inserts
US10808930B2 (en) 2018-06-28 2020-10-20 Raytheon Technologies Corporation Combustor shell attachment
US11566787B2 (en) * 2020-04-06 2023-01-31 Rolls-Royce Corporation Tile attachment scheme for counter swirl doublet
US11840032B2 (en) 2020-07-06 2023-12-12 Pratt & Whitney Canada Corp. Method of repairing a combustor liner of a gas turbine engine

Citations (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE2012949A1 (de) * 1969-04-02 1970-10-08 United Aircraft Corp., East Hartford, Conn. (V.St.A.) Wandkonstruktion und Luftzufuhrlöcher für ein Gasturbinentriebwerk
US4820097A (en) * 1988-03-18 1989-04-11 United Technologies Corporation Fastener with airflow opening
EP1413831A1 (fr) 2002-10-21 2004-04-28 Siemens Aktiengesellschaft Chambre de combustion annulaire pour turbine à gaz et turbine à gaz
DE60221743T2 (de) * 2001-06-06 2008-06-05 Snecma Verdünnungsluftlöcher verwendende Befestigung einer Turbinenbrennkammer aus keramischem Matrix-Verbundwerkstoff
EP2295865A2 (fr) 2009-08-05 2011-03-16 Rolls-Royce plc Montage d'un bouclier thermique dans une chambre de combustion
EP2700877A2 (fr) 2012-08-21 2014-02-26 Rolls-Royce Deutschland Ltd & Co KG Chambre de combustion de turbine à gaz avec boulons refroidis par impact des tuiles de la chambre de combustion
EP2743585A1 (fr) 2012-12-12 2014-06-18 Rolls-Royce plc Chambre de combustion
EP2873921A1 (fr) 2013-11-14 2015-05-20 Rolls-Royce Deutschland Ltd & Co KG Élément de blindage contre la chaleur d'une chambre de combustion d'une turbine à gaz
EP2738470B1 (fr) 2012-11-28 2015-05-27 Rolls-Royce Deutschland Ltd & Co KG Assemblage pour attacher des éléments de bouclier thermique à la paroi d'une chambre de combustion d'une turbine à gaz
EP2886962A1 (fr) 2013-12-23 2015-06-24 Rolls-Royce plc Chambre de combustion

Family Cites Families (8)

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Publication number Priority date Publication date Assignee Title
US4848089A (en) * 1988-02-18 1989-07-18 Avco Corporation Combustor attachment device
US5201799A (en) * 1991-05-20 1993-04-13 United Technologies Corporation Clip attachment for combustor panel
FR2714152B1 (fr) * 1993-12-22 1996-01-19 Snecma Dispositif de fixation d'une tuile de protection thermique dans une chambre de combustion.
FR2726536A1 (fr) * 1994-11-08 1996-05-10 Barre Bernard Dispositif d'obturation a verrouillage auto-activable
FR2817925B1 (fr) * 2000-12-11 2003-09-19 Renault Fixation d'une piece par rapport a une autre, avec positionnement dans les trois axes, notamment pour piece d'habillage de vehicule automobile
DE102004044852A1 (de) * 2004-09-10 2006-03-16 Deutsches Zentrum für Luft- und Raumfahrt e.V. Heißgaskammer und Schindel für eine Heißgaskammer
GB2488975B (en) * 2011-03-02 2014-02-26 Rolls Royce Plc A safety connector
US9261129B2 (en) * 2013-07-08 2016-02-16 Lockon Llc Through-hull fitting

Patent Citations (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE2012949A1 (de) * 1969-04-02 1970-10-08 United Aircraft Corp., East Hartford, Conn. (V.St.A.) Wandkonstruktion und Luftzufuhrlöcher für ein Gasturbinentriebwerk
US4820097A (en) * 1988-03-18 1989-04-11 United Technologies Corporation Fastener with airflow opening
DE60221743T2 (de) * 2001-06-06 2008-06-05 Snecma Verdünnungsluftlöcher verwendende Befestigung einer Turbinenbrennkammer aus keramischem Matrix-Verbundwerkstoff
EP1413831A1 (fr) 2002-10-21 2004-04-28 Siemens Aktiengesellschaft Chambre de combustion annulaire pour turbine à gaz et turbine à gaz
EP2295865A2 (fr) 2009-08-05 2011-03-16 Rolls-Royce plc Montage d'un bouclier thermique dans une chambre de combustion
EP2700877A2 (fr) 2012-08-21 2014-02-26 Rolls-Royce Deutschland Ltd & Co KG Chambre de combustion de turbine à gaz avec boulons refroidis par impact des tuiles de la chambre de combustion
EP2738470B1 (fr) 2012-11-28 2015-05-27 Rolls-Royce Deutschland Ltd & Co KG Assemblage pour attacher des éléments de bouclier thermique à la paroi d'une chambre de combustion d'une turbine à gaz
EP2743585A1 (fr) 2012-12-12 2014-06-18 Rolls-Royce plc Chambre de combustion
EP2873921A1 (fr) 2013-11-14 2015-05-20 Rolls-Royce Deutschland Ltd & Co KG Élément de blindage contre la chaleur d'une chambre de combustion d'une turbine à gaz
EP2886962A1 (fr) 2013-12-23 2015-06-24 Rolls-Royce plc Chambre de combustion

Also Published As

Publication number Publication date
EP3182006B1 (fr) 2019-09-04
DE102015225107A1 (de) 2017-06-14
US10060626B2 (en) 2018-08-28
US20170167730A1 (en) 2017-06-15

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