EP2738470A1 - Assemblage pour attacher des éléments de bouclier thermique à la paroi d'une chambre de combustion d'une turbine à gaz - Google Patents

Assemblage pour attacher des éléments de bouclier thermique à la paroi d'une chambre de combustion d'une turbine à gaz Download PDF

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Publication number
EP2738470A1
EP2738470A1 EP13191950.8A EP13191950A EP2738470A1 EP 2738470 A1 EP2738470 A1 EP 2738470A1 EP 13191950 A EP13191950 A EP 13191950A EP 2738470 A1 EP2738470 A1 EP 2738470A1
Authority
EP
European Patent Office
Prior art keywords
combustion chamber
shingle
chamber wall
annular flange
fastening 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.)
Granted
Application number
EP13191950.8A
Other languages
German (de)
English (en)
Other versions
EP2738470B1 (fr
Inventor
Stefan Penz
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
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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 EP2738470A1 publication Critical patent/EP2738470A1/fr
Application granted granted Critical
Publication of EP2738470B1 publication Critical patent/EP2738470B1/fr
Not-in-force 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
    • F23R3/002—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
    • F23R3/007—Continuous combustion chambers using liquid or gaseous fuel constructed mainly of ceramic components
    • 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
    • F23R2900/00—Special features of, or arrangements for continuous combustion chambers; Combustion processes therefor
    • F23R2900/00017—Assembling combustion chamber liners or subparts
    • 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
    • F23R2900/03042—Film cooled combustion chamber walls or domes
    • 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
    • F23R2900/03044—Impingement cooled combustion chamber walls or subassemblies

Definitions

  • the invention relates to a shingle fastening arrangement of a gas turbine combustor according to the features of the preamble of claim 1.
  • the invention relates to a combustion chamber of a gas turbine, wherein on a combustion chamber wall shingles are attached, which have a distance from the combustion chamber wall.
  • the invention has for its object to provide a Schindelbefest onlysan Aunt a gas turbine combustor, which avoids the disadvantages of the prior art with a simple structure and simple, cost-effective manufacturability and good cooling, especially the shingles allows.
  • the shingle is provided with an annular flange arranged on its side facing the combustion chamber wall.
  • This annular flange is dimensioned to fit a recess of the combustion chamber wall and engages either in this recess or is flush with the edge of the recess on the combustion chamber wall.
  • the fastener extends through the recess of the combustion chamber wall and is mechanically connected to the annular flange. This connection with the annular flange can be done either directly.
  • the annular flange on its inside a thread, which is in engagement with a threaded extension of the fastener.
  • a mixed-air tube which is provided with an internal thread and is screwed to the fastening element.
  • the annular flange is clamped between the Mischluftleitrohr and the fastener, so that the shingle is firmly clamped against the combustion chamber wall.
  • the fastening element is round. It may, unless a Mischluftleitrohr is used, be designed cup-like. That's it particularly favorable if in the central region of the cup-like configuration of the fastening element air passage recesses are provided, through which cooling air can be fed to the shingle.
  • the shingle is also preferably provided adjacent to the central region of the fastener with air passage recesses to pass cooling air to the hot side of the shingle.
  • the embodiment according to the invention it is thus possible to realize an efficient impact-effusion cooling between the shingle and the combustion chamber wall (shingle support). As a result, high temperatures in the region of attachment of the shingle to the combustion chamber wall are avoided.
  • the inventively provided annular flange can be dimensioned so that it requires only a very small area of the shingle, so that there is no disturbance of the cooling air film on the hot side of the shingle during operation.
  • the annular flange can have a very small height. Due to the smaller height of the annular flange compared to a threaded pin, the introduction of effusion cooling air recesses by means of e.g. Laser or electron beam less obstructed. This makes it possible to bring effusion cooling air recesses closer to the joint, i.e. to the annular flange. As a result, the cooling film on the hot side of the shingle is not or only slightly disturbed.
  • the shingle attachment arrangement according to the invention is characterized by a number of significant advantages. On the one hand, it is possible to realize a lower overall height. As a result, it is possible in the sequence to allow smaller combustion chamber or larger combustion chamber volume with the same space. This leads to a lower weight of the combustion chamber and to a saving in material and manufacturing costs. Furthermore, it is possible according to the invention to effectively cool the area of the shingle attachment. As a result, hot areas, as they occur in the prior art, avoided. This leads to a longer service life of the combustion chamber shingles. The longer service life is also due to the fact that a more uniform cooling of the shingles takes place and that the high temperature gradients known from the prior art are avoided.
  • connection with the fastener is ensured by means of the clamping effect occurring by a force flow in the "cold" area. This means that the thermal and mechanical stresses that occur in the area of the shingles and the shingles attachment, do not work together. This is a significant advantage of the solution according to the invention.
  • the Mischluftleitrohr can be formed according to the invention either as a separate part or in one piece with the shingle. In a separate Mischluftleitrohr it may be beneficial that the Effusionsbohrungen in Misch Kunststoffleitrohr are easier and more accurate to produce, so that the Mischluftleitrohr can be better cooled.
  • the fastener may have different thread sizes, depending on the particular sizes and the specific conditions of use. This results in an optimal adaptability of the solution according to the invention to different requirements.
  • the Beer maltationsaus fundamentalungen (Effusionskühlbohrungen) can be formed in the solution according to the invention perpendicular to the median plane or inclined.
  • the invention offers a variety of customization options to the respective design specifications.
  • Another, essential advantage of the invention is that at the attachment point, to which the shingle is fastened by means of the fastening element to the combustion chamber wall, results in a very low clearance. This allows a very good positioning between the shingle and the combustion chamber wall achieved become. This in turn influences the assignment of the air passage recesses, so that they can be arranged in a favorable association with each other.
  • the gas turbine engine 10 is a generalized example of a turbomachine, in which the invention can be applied.
  • the engine 10 is formed in a conventional manner and comprises in succession an air inlet 11, a fan 12 circulating in a housing, a medium pressure compressor 13, a high pressure compressor 14, a combustion chamber 15, a high pressure turbine 16, a medium pressure turbine 17 and a low pressure turbine 18 and a 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 extending radially outward from a rotatable drum or disc 26, which are 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 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. 2 and 3 each show perspective simplified partial sectional views.
  • a combustion chamber wall 29 is shown, on which a shingle 30 is mounted at a distance from the combustion chamber wall 29.
  • the combustion chamber wall 29 has a circular recess 32 in the region of the attachment of the shingle. This recess may also be out of round, for example polygonal.
  • the shingle 30 is provided with an annular flange 31, which is integrally formed on the shingle 30 and is dimensioned so that it according to Fig. 2 the recess 32 passes through.
  • the annular flange is provided on its inside with a thread 34.
  • the shingle In the interior of the annular flange 31, the shingle has on its wall a plurality of Lucas gutsausbrookonne 38. This makes it possible to perform cooling air through the shingle 30 and, as described, form a cooling air film on the hot side of the shingle 30.
  • the Fig. 2 further shows an embodiment of a fastener 33 according to the invention.
  • This is in the form of a round insert body which has a cup-like structure.
  • the fastening element 33 has an external thread which can be screwed to the thread 34 of the annular flange 31.
  • the fastening element 33 is provided with a plurality of Lucas gutsaus traditions 37, through which cooling air to the outside of the shingle 30 can be supplied.
  • the fastener 33 is firmly bolted to the annular flange 31 of the shingle 30.
  • the annular flange 31 is sealingly against the edge of the recess 32 of the combustion chamber wall 29, so that the undesirable passage of leakage flow is avoided.
  • the sealing effect is also ensured by the fact that the fastening element 33, as in Fig. 2 shown, also against the outside of the combustion chamber wall 29 abuts.
  • the outer diameter of the protruding portion of the annular flange 31 and the inner diameter of the recess 32 allow play, so that manufacturing inaccuracies or thermal expansions can be compensated without affecting the sealing effect.
  • a tight clearance fit at individual attachment points can positively influence the positioning of the shingle and thus the mixing air openings within the combustion chamber. Furthermore, a more accurate alignment of the cooling air holes in the shingle support to the cooling air holes in the shingle is possible.
  • the Fig. 3 shows a representation analog Fig. 2 , The same parts are provided with the same reference numbers.
  • the fastening element 33 is tubular. It is not bolted with its thread 34 against the annular flange 31, but clamps the annular flange 31 against a Mischluftleitrohr (chute), which is provided with an internal thread.
  • the fastening element 33 is thus in positive engagement with the Mischluftleitrohr and thus clamps the edge region of the recess 32 of the combustion chamber wall 29 and the annular flange 31 in sealing contact.
  • Mischluftleitrohr 35 it is possible to produce the Mischluftleitrohr 35 in a simple, cost-effective design and stored on the combustion chamber wall 29 and the shingle 30.
  • An optimized design of the inflow region 39 of the fastening element 33 ensures optimized flow guidance.
  • the 4 and 5 show a schematic representation of another embodiment of the invention.
  • the same parts are provided with the same reference numbers.
  • the fastening element 33 is provided with tool engagement means 40 on its outer contour. These can be in the form of a hexagon or other polygonal design or in the form of Holes or the like may be formed for engagement with a suitable tool.
  • the Fig. 5 shows an embodiment in which the Mischluftleitrohr 35 is integrally formed with the shingle 30. By screwing the shingle 30 thus the Mischluftleitrohr 35 is also attached.

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Ceramic Engineering (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
EP13191950.8A 2012-11-28 2013-11-07 Assemblage pour attacher des éléments de bouclier thermique à la paroi d'une chambre de combustion d'une turbine à gaz Not-in-force EP2738470B1 (fr)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
DE102012023297.7A DE102012023297A1 (de) 2012-11-28 2012-11-28 Schindelbefestigungsanordnung einer Gasturbinenbrennkammer

Publications (2)

Publication Number Publication Date
EP2738470A1 true EP2738470A1 (fr) 2014-06-04
EP2738470B1 EP2738470B1 (fr) 2015-05-27

Family

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Family Applications (1)

Application Number Title Priority Date Filing Date
EP13191950.8A Not-in-force EP2738470B1 (fr) 2012-11-28 2013-11-07 Assemblage pour attacher des éléments de bouclier thermique à la paroi d'une chambre de combustion d'une turbine à gaz

Country Status (3)

Country Link
US (1) US9341372B2 (fr)
EP (1) EP2738470B1 (fr)
DE (1) DE102012023297A1 (fr)

Cited By (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2016062977A1 (fr) * 2014-10-24 2016-04-28 Aircelle Ensemble d'une structure fixe interne de nacelle de turboréacteur et d'une protection thermique
EP3043113A1 (fr) * 2015-01-12 2016-07-13 A.S.EN. Ansaldo Sviluppo Energia S.r.l. Dispositif de fixation pour carreau thermo-isolant de chambre de combustion de turbine à gaz
DE102016217876A1 (de) 2016-09-19 2018-03-22 Rolls-Royce Deutschland Ltd & Co Kg Brennkammerwand einer Gasturbine mit Befestigung einer Brennkammerschindel
US10060626B2 (en) 2015-12-14 2018-08-28 Rolls-Royce Deutschland Ltd & Co Kg Gas turbine combustion chamber with a shingle attachment by means of catching elements
EP3385622A1 (fr) * 2017-04-03 2018-10-10 United Technologies Corporation Oeillet d'un panneau de chambre de combustion de turbine à gaz
DE102018204453A1 (de) 2018-03-22 2019-09-26 Rolls-Royce Deutschland Ltd & Co Kg Brennkammerbaugruppe mit unterschiedlichen Krümmungen für eine Brennkammerwand und eine hieran fixierte Brennkammerschindel
EP3587928A1 (fr) * 2018-06-28 2020-01-01 United Technologies Corporation Fixation de coque de chambre de combustion

Families Citing this family (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2735796B1 (fr) * 2012-11-23 2020-01-01 Ansaldo Energia IP UK Limited Paroi située sur la trajectoire des gaz chauds d'une turbine à gaz et procédé pour améliorer le comportement de fonctionnment d'une turbine à gaz
US10100737B2 (en) * 2013-05-16 2018-10-16 Siemens Energy, Inc. Impingement cooling arrangement having a snap-in plate
WO2015100346A1 (fr) * 2013-12-23 2015-07-02 United Technologies Corporation Configuration de trous de dilution à écoulements multiples pour un moteur à turbine à gaz
US9810434B2 (en) * 2016-01-21 2017-11-07 Siemens Energy, Inc. Transition duct system with arcuate ceramic liner for delivering hot-temperature gases in a combustion turbine engine
US10533747B2 (en) * 2017-03-30 2020-01-14 General Electric Company Additively manufactured mechanical fastener with cooling fluid passageways
US20180283689A1 (en) * 2017-04-03 2018-10-04 General Electric Company Film starters in combustors of gas turbine engines
US11566787B2 (en) * 2020-04-06 2023-01-31 Rolls-Royce Corporation Tile attachment scheme for counter swirl doublet

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Publication number Priority date Publication date Assignee Title
GB2173891A (en) * 1985-04-05 1986-10-22 Agency Ind Science Techn Gas turbine combustor
EP1351022A2 (fr) * 2002-04-02 2003-10-08 Rolls-Royce Deutschland Ltd & Co KG Passage d'alimentation en air pour chambre de combustion de turbine comprenant des bardeaux
EP1712840A1 (fr) * 2005-04-13 2006-10-18 Siemens Aktiengesellschaft Bouclier thermique avec boulon de fixation
US20080127652A1 (en) * 2004-12-16 2008-06-05 Heinrich Putz Heat Shield Element
US20110030378A1 (en) * 2009-08-05 2011-02-10 Rolls-Royce Plc Combustor tile mounting arrangement

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GB647302A (en) * 1948-05-14 1950-12-13 Edgar Phillips Peregrine Improvements in or relating to linings for combustion chambers and the like
GB1552132A (en) * 1975-11-29 1979-09-12 Rolls Royce Combustion chambers for gas turbine engines
US4422300A (en) * 1981-12-14 1983-12-27 United Technologies Corporation Prestressed combustor liner for gas turbine engine
DE3664374D1 (en) * 1985-12-02 1989-08-17 Siemens Ag Heat shield arrangement, especially for the structural components of a gas turbine plant
US4820097A (en) * 1988-03-18 1989-04-11 United Technologies Corporation Fastener with airflow opening
US5144793A (en) * 1990-12-24 1992-09-08 United Technologies Corporation Integrated connector/airtube for a turbomachine's combustion chamber walls
DE19751299C2 (de) * 1997-11-19 1999-09-09 Siemens Ag Brennkammer sowie Verfahren zur Dampfkühlung einer Brennkammer
GB2380236B (en) * 2001-09-29 2005-01-19 Rolls Royce Plc A wall structure for a combustion chamber of a gas turbine engine
EP1389690B1 (fr) * 2002-08-16 2007-01-03 Siemens Aktiengesellschaft Vis intérieurement refroidissable

Patent Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2173891A (en) * 1985-04-05 1986-10-22 Agency Ind Science Techn Gas turbine combustor
EP1351022A2 (fr) * 2002-04-02 2003-10-08 Rolls-Royce Deutschland Ltd & Co KG Passage d'alimentation en air pour chambre de combustion de turbine comprenant des bardeaux
US20080127652A1 (en) * 2004-12-16 2008-06-05 Heinrich Putz Heat Shield Element
EP1712840A1 (fr) * 2005-04-13 2006-10-18 Siemens Aktiengesellschaft Bouclier thermique avec boulon de fixation
US20110030378A1 (en) * 2009-08-05 2011-02-10 Rolls-Royce Plc Combustor tile mounting arrangement

Cited By (12)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2016062977A1 (fr) * 2014-10-24 2016-04-28 Aircelle Ensemble d'une structure fixe interne de nacelle de turboréacteur et d'une protection thermique
FR3027630A1 (fr) * 2014-10-24 2016-04-29 Aircelle Sa Ensemble d’une structure fixe interne de nacelle de turboreacteur et d’une protection thermique
US10001064B2 (en) 2014-10-24 2018-06-19 Safran Nacelles Assembly of an inner fixed structure of a turbojet engine nacelle and of a thermal protection
EP3043113A1 (fr) * 2015-01-12 2016-07-13 A.S.EN. Ansaldo Sviluppo Energia S.r.l. Dispositif de fixation pour carreau thermo-isolant de chambre de combustion de turbine à gaz
US10060626B2 (en) 2015-12-14 2018-08-28 Rolls-Royce Deutschland Ltd & Co Kg Gas turbine combustion chamber with a shingle attachment by means of catching elements
DE102016217876A1 (de) 2016-09-19 2018-03-22 Rolls-Royce Deutschland Ltd & Co Kg Brennkammerwand einer Gasturbine mit Befestigung einer Brennkammerschindel
EP3385622A1 (fr) * 2017-04-03 2018-10-10 United Technologies Corporation Oeillet d'un panneau de chambre de combustion de turbine à gaz
DE102018204453A1 (de) 2018-03-22 2019-09-26 Rolls-Royce Deutschland Ltd & Co Kg Brennkammerbaugruppe mit unterschiedlichen Krümmungen für eine Brennkammerwand und eine hieran fixierte Brennkammerschindel
US11320144B2 (en) 2018-03-22 2022-05-03 Rolls-Royce Deutschland Ltd & Co Kg Combustion chamber assembly with different curvatures for a combustion chamber wall and a combustion chamber shingle fixed thereto
DE102018204453B4 (de) 2018-03-22 2024-01-18 Rolls-Royce Deutschland Ltd & Co Kg Brennkammerbaugruppe mit unterschiedlichen Krümmungen für eine Brennkammerwand und eine hieran fixierte Brennkammerschindel
EP3587928A1 (fr) * 2018-06-28 2020-01-01 United Technologies Corporation Fixation de coque de chambre de combustion
US10808930B2 (en) 2018-06-28 2020-10-20 Raytheon Technologies Corporation Combustor shell attachment

Also Published As

Publication number Publication date
US9341372B2 (en) 2016-05-17
US20140144146A1 (en) 2014-05-29
EP2738470B1 (fr) 2015-05-27
DE102012023297A1 (de) 2014-06-12

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