EP3296636A1 - Paroi de chambre de combustion d'une turbine à gaz pourvue de fixation d'une bardeau de chambre de combustion - Google Patents

Paroi de chambre de combustion d'une turbine à gaz pourvue de fixation d'une bardeau de chambre de combustion Download PDF

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Publication number
EP3296636A1
EP3296636A1 EP17191110.0A EP17191110A EP3296636A1 EP 3296636 A1 EP3296636 A1 EP 3296636A1 EP 17191110 A EP17191110 A EP 17191110A EP 3296636 A1 EP3296636 A1 EP 3296636A1
Authority
EP
European Patent Office
Prior art keywords
combustion chamber
bolt
shingle
chamber wall
combustor
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.)
Withdrawn
Application number
EP17191110.0A
Other languages
German (de)
English (en)
Inventor
Kay Heinze
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
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 EP3296636A1 publication Critical patent/EP3296636A1/fr
Withdrawn legal-status Critical Current

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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

Definitions

  • the invention relates firstly to a combustion chamber shingle of a gas turbine combustion chamber and to a combustion chamber wall of a gas turbine combustion chamber using the combustion chamber shingle according to the invention.
  • Typical combustion chambers of gas turbines consist of an inner and an outer combustion chamber wall. Shingles are fastened to these combustion chamber walls on the side facing the combustion chamber interior. These shingles protect the combustion chamber walls from the high temperatures generated during the combustion process.
  • the shingles in a suitable manner to be attached to the combustion chamber wall, that they are secured in the long term during operation.
  • the shingles are usually screwed by a fixing with the combustion chamber wall.
  • Such fixing elements are formed for example in the form of studs which are connected to the shingles.
  • the combustion chamber walls In order to cool the shingles, the combustion chamber walls have impingement cooling holes through which cooling air is introduced into a space between the combustion chamber wall and the shingle. This air exits through effusion cooling holes, which are provided in the shingle, from the hot, the interior of the combustion chamber facing side of the shingle. The cooling air occurring from the effusion cooling holes settles on the hot side of the shingle as cooling air film and causes it to cool.
  • the invention has for its object to provide a combustion chamber shingle and a combustion chamber, which avoid the disadvantages of the prior art with a simple structure and simple, cost-effective manufacturability and allow a thermally optimized solution with a long service life.
  • the combustion chamber shingle is inventively provided that it is integrally formed with a fastening bolt.
  • the fastening bolt additionally has a bolt washer, which is integrally connected to the fastening bolt such that the bolt washer is spaced from the combustion chamber shingle. The extending from the pin washer free end portion of the mounting bolt is threaded.
  • the combustion chamber shingle according to the invention is characterized by a number of significant advantages.
  • the bolt disc ensures that the combustion chamber shingle does not bear directly against the combustion chamber wall. Rather, the bolt disc forms an abutment which is supported against the combustion chamber wall and by means of a nut which is bolted to the thread of the fastening bolt, is braced.
  • a gap is created between the pin and the combustion chamber shingles, which can be traversed by cooling air. This leads to an improvement in the cooling by the cooling air, which is introduced into the space between the combustion chamber shingle and the combustion chamber wall.
  • the threaded end region of the fastening bolt has a larger diameter than the region of the fastening bolt between the combustion chamber shingle and the bolt disk.
  • the fastening bolt between the combustion chamber shingle and the bolt disc can have a substantially smaller diameter, so that there is a lower accumulation of material, which in turn leads to a reduction in the mass to be cooled.
  • the pin disc can have a conical shape in cross section, so that the introduction of force into the combustion chamber shingle is improved.
  • the bolt disc may be plate-shaped to have a certain elasticity.
  • the mounting plate serves as a biasing spring to additionally secure the screw by means of the mother.
  • the bolt In order to minimize heat transfer into the shingle and to maximize the cooled surface on the hot side, it may be advantageous to provide the bolt, as described, at the transition to the shingle with a smaller diameter than at the threaded portion of the bolt. In addition, it is possible to choose the thickness of the bolt disk such that the bolt disk has a smaller thickness at the radially outer region than at the radially inner region.
  • the invention provides that the nut rests against the combustion chamber wall for fastening the fastening bolt. This results in a load path which extends through the free region of the fastening bolt, through the nut, through the edge region of the associated recess of the combustion chamber wall and through the bolt disk.
  • the attachment region of the fastening bolt to the combustion chamber shingle is thus not burdened by the screw. This results in a significant reduction of mechanical stress in this area. This leads to a lower creep of the material and thus to a reduced susceptibility to failure.
  • a separate washer between the nut and the combustion chamber wall. This can serve, for example, to compensate for dimensional dimensions and to provide a sufficient contact surface of the mother.
  • the washer may be provided with an annular flange which engages around the fastening bolt and extends through the recess of the combustion chamber wall, through which the fastening bolt is guided. This leads to a simplified installation and takes into account dimensional deviations of the recesses of the combustion chamber wall.
  • the outer diameter of the pin washer is substantially equal to the outer diameter of the washer, but other dimensions may be favorable.
  • 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 core engine housing 21 into 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 high pressure turbine 16 and mid 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 rotor blades 24 projecting outwardly from a rotatable hub 27.
  • the compressor drum or compressor disk 26 and the blades 22 disposed thereon and the turbine rotor hub 27 and the turbine rotor blades 24 disposed thereon rotate about the engine axis 1 during operation.
  • the Fig. 2 shows in a partially-sectional perspective view of a combustion chamber shingle 29, which is integrally provided with a fastening bolt 25. It is understood that several such fastening bolts can be provided in the region of a shingle.
  • the fastening bolt 25 is provided at its free end region with a thread 31, on which a nut 33 can be screwed.
  • the bolt has an integral with this bolt washer 30.
  • This is formed in the embodiment shown as a circular disk, but it can also have any other shapes, such as polygonal or rectangular.
  • the reference numeral 32 a combustion chamber wall is shown, which is provided with a recess. Through this recess, the fastening bolt 25 is guided.
  • a washer 34 is interposed, against which the nut 33 is supported.
  • the washer 34 has an annular flange 35, which extends into the free hole space of the combustion chamber wall 32 and can serve, for example, for centering or securing the position of the combustion chamber shingle 29.
  • the Fig. 3 shows in an analogous representation of Fig. 2 the resulting load path.
  • the load for fastening the combustion chamber shingle 29 to the combustion chamber wall 32 thus passes through the free threaded portion 31 of the fastening bolt 25, through the nut 33, through the washer 34, through the combustion chamber wall 32 and through the pin washer 30 in that the transition region 36 is not mechanically stressed by the screw connection, so that the risk of material creep can be largely avoided.
  • the construction according to the invention makes it possible to form additional cooling air slots (not shown) in the pin washer or washer in order to ensure further cooling and to reduce the overall temperature.

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)
EP17191110.0A 2016-09-19 2017-09-14 Paroi de chambre de combustion d'une turbine à gaz pourvue de fixation d'une bardeau de chambre de combustion Withdrawn EP3296636A1 (fr)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
DE102016217876.8A DE102016217876A1 (de) 2016-09-19 2016-09-19 Brennkammerwand einer Gasturbine mit Befestigung einer Brennkammerschindel

Publications (1)

Publication Number Publication Date
EP3296636A1 true EP3296636A1 (fr) 2018-03-21

Family

ID=59858990

Family Applications (1)

Application Number Title Priority Date Filing Date
EP17191110.0A Withdrawn EP3296636A1 (fr) 2016-09-19 2017-09-14 Paroi de chambre de combustion d'une turbine à gaz pourvue de fixation d'une bardeau de chambre de combustion

Country Status (3)

Country Link
US (1) US20180080655A1 (fr)
EP (1) EP3296636A1 (fr)
DE (1) DE102016217876A1 (fr)

Families Citing this family (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP3022424B1 (fr) * 2013-07-16 2019-10-09 United Technologies Corporation Ensemble de panneau en céramique de moteur de turbine à gaz et procédé de fabrication d'un ensemble de panneau en céramique de moteur de turbine à gaz

Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20100263386A1 (en) * 2009-04-16 2010-10-21 General Electric Company Turbine engine having a liner
US20140190166A1 (en) * 2012-12-12 2014-07-10 Rolls-Royce Plc Combustion chamber
EP2886961A1 (fr) * 2013-12-18 2015-06-24 Rolls-Royce Deutschland Ltd & Co KG Rondelle de bardeaux de chambre de combustion d'une turbine à gaz

Family Cites Families (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5265409A (en) * 1992-12-18 1993-11-30 United Technologies Corporation Uniform cooling film replenishment thermal liner assembly
EP1413831A1 (fr) 2002-10-21 2004-04-28 Siemens Aktiengesellschaft Chambre de combustion annulaire pour turbine à gaz et turbine à gaz
US8049529B2 (en) * 2008-07-30 2011-11-01 Raytheon Company Fault triggerred automatic redundancy scrubber
GB0913580D0 (en) 2009-08-05 2009-09-16 Rolls Royce Plc Combustor tile
DE102012016493A1 (de) 2012-08-21 2014-02-27 Rolls-Royce Deutschland Ltd & Co Kg Gasturbinenbrennkammer mit prallgekühlten Bolzen der Brennkammerschindeln
DE102012023297A1 (de) 2012-11-28 2014-06-12 Rolls-Royce Deutschland Ltd & Co Kg Schindelbefestigungsanordnung einer Gasturbinenbrennkammer
DE102013223258A1 (de) 2013-11-14 2015-06-03 Rolls-Royce Deutschland Ltd & Co Kg Brennkammerhitzeabschirmelement einer Gasturbine
GB201322838D0 (en) 2013-12-23 2014-02-12 Rolls Royce Plc A combustion chamber

Patent Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20100263386A1 (en) * 2009-04-16 2010-10-21 General Electric Company Turbine engine having a liner
US20140190166A1 (en) * 2012-12-12 2014-07-10 Rolls-Royce Plc Combustion chamber
EP2886961A1 (fr) * 2013-12-18 2015-06-24 Rolls-Royce Deutschland Ltd & Co KG Rondelle de bardeaux de chambre de combustion d'une turbine à gaz

Also Published As

Publication number Publication date
DE102016217876A1 (de) 2018-03-22
US20180080655A1 (en) 2018-03-22

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