EP2918914A1 - Chambre de combustion d'une turbine à gaz - Google Patents

Chambre de combustion d'une turbine à gaz Download PDF

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Publication number
EP2918914A1
EP2918914A1 EP15158435.6A EP15158435A EP2918914A1 EP 2918914 A1 EP2918914 A1 EP 2918914A1 EP 15158435 A EP15158435 A EP 15158435A EP 2918914 A1 EP2918914 A1 EP 2918914A1
Authority
EP
European Patent Office
Prior art keywords
combustion chamber
chamber wall
wall
shingles
chamber according
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Withdrawn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
EP15158435.6A
Other languages
German (de)
English (en)
Inventor
Imon Kalyan Bagchi
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 EP2918914A1 publication Critical patent/EP2918914A1/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Withdrawn legal-status Critical Current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
    • F23R3/002—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
    • F23R3/42—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 the combustion chamber of a gas turbine.
  • the combustion chamber has an outer combustion chamber wall and an inner combustion chamber wall.
  • the inner, hot combustion chamber wall on the outer, cold combustion chamber wall in a suitable manner.
  • the two combustion chamber walls are spaced apart from one another in order to create a gap for the flow of cooling air.
  • the outer, cold combustion chamber wall in this case has a plurality of impingement cooling holes, through which cooling air impinges on the side facing away from the combustion chamber interior side of the inner, hot combustion chamber wall in order to cool them.
  • the inner, hot combustor wall is provided with a plurality of effusion holes through which cooling air exits which abuts the surface of the inner combustor wall to cool and shield it from the hot combustion gases.
  • Such combustion chambers are arranged between a high-pressure compressor and a high-pressure turbine.
  • the outer, cold combustion chamber wall which forms a support structure, is usually produced by welding prefabricated parts. At the discharge area of the combustion chamber, flanges and combustion chamber suspensions made as separate forgings are welded to support the combustion chamber.
  • the combustion chamber walls themselves are usually designed as sheet metal construction.
  • a combustion chamber head is provided with a base plate usually made as a casting.
  • the inner, hot combustion chamber wall is then inserted.
  • This usually consists of shingles, which are formed like a segment. The shingles are formed as castings and have cast-stud bolts, which are guided by recesses of the outer combustion chamber wall and screwed from the outside via nuts.
  • Such constructions are for example from the US 5,435,139 A or the US 5,758,503 A previously known.
  • the cooling of the shingles in the vicinity of the studs can not be optimally designed because of the material accumulations occurring there. Thus occur at the transition areas from the shingles to the stud higher temperatures that exceed the temperatures in the rest of the shingles.
  • a seal or sealing lip is provided in the region of the outlet nozzle of the combustion chamber, which seals the exhaust gas jet to the surrounding components and feeds them to the guide vanes of the high-pressure turbine. These sealing lips wear out when the shingles become loose or the shingles vibrate. It proves to be disadvantageous that the sealing lip is formed as part of the support structure of the combustion chamber and can not be replaced in a simple manner.
  • the invention has for its object to provide a combustion chamber of a gas turbine of the type mentioned, which has a high level of reliability and a long service life with a simple structure and simple, cost-effective manufacturability.
  • the inner combustion chamber wall at its rear end, relative to the flow direction of the combustion chamber longitudinally displaceable in a groove in the region of a combustion chamber suspension or a Sealing lip for a strip seal to an outlet nozzle guide vane (NGV) is held.
  • NVG outlet nozzle guide vane
  • the internal second, hot combustion chamber wall can be made of a sheet material or in the form of cast segments or shingles.
  • the inner combustion chamber wall shingles
  • This fixation can be done according to the invention, for example by screws or bolts. According to the invention, there is thus a positive fixing at the front region of the inner combustion chamber wall.
  • the inner combustion chamber wall has at least one hook or hook element at its rear end region.
  • the hook is preferably U-shaped, so that the rear portion of the inner combustion chamber is both held by the hook, and is guided longitudinally displaceable.
  • a plurality of hooks are provided around the circumference of the inner combustion chamber wall.
  • the hooks can continue to be elastic for game clearance. They have a spring function to keep the inner combustion chamber wall (shingles) taut on the outer combustion chamber wall.
  • the inner combustion chamber wall is formed segmented, wherein the segments can extend over the entire length of the combustion chamber.
  • the fastening or fixing of the front end of the combustion chamber wall can be adapted in a favorable manner to the respective structural requirements, for example, by screws, which, based on the flow direction or a central axis of the combustion chamber are arranged radially.
  • These stud bolts can be fastened with nuts on the cold side of the combustion head plate.
  • An essential advantage of the invention results from the fact that the cooling of the inner combustion chamber wall can be optimally designed over its entire surface. Since there are no stud bolts, there are no restrictions in terms of heat transfer.
  • the combustion chamber according to the invention and in particular the inner combustion chamber wall according to the invention can be produced preferably by means of an additive manufacturing process, for example by laser deposition welding or electron beam deposition welding.
  • This manufacturability is promoted by the fact that, compared to the prior art, no fastening bolts or the like are required to support the inner combustion chamber wall. As a result, material accumulations and geometries, which make the production more complicated avoided.
  • Another advantage of the embodiment according to the invention is that it is possible to form the sealing lip to the outlet nozzle guide ring so that it can be renewed with an exchange of the inner combustion chamber wall, without the entire combustion chamber construction is affected.
  • 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, 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 disc 125 coupled to hubs 126 of high pressure turbine 116 and intermediate pressure turbine 117, respectively.
  • the turbine sections 116, 117, 118 have similar stages, including an array of fixed vanes 123 projecting radially inward from the housing 121 into the annular flow passage through the turbines 116, 117, 118, and a downstream array of turbine blades 124 projecting 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 with a central axis 25 is shown, 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.
  • For supplying mixed air Zumischlöcher 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.
  • a sealing lip 20 is provided for a strip seal to the outlet nozzle guide vane.
  • the Fig. 3 shows a first embodiment of a combustion chamber according to the invention.
  • This is basically structured as the in Fig. 2 shown combustion chamber. This means that it also has an outer cold combustion chamber wall 7 and an inner, hot combustion chamber wall 6.
  • the storage is also via combustion chamber suspensions 11 and combustion chamber flanges 12. Also the Sealing lip 20 is shown accordingly.
  • a combustion chamber head 3 At the front end, a combustion chamber head 3, a heat shield 2, a base plate 8 and a burner seal 4 are provided.
  • the base plate 8 is provided with a groove 16, preferably an annular groove, in which the head-side end 15 of the inner, hot combustion chamber wall 6 is inserted.
  • the head-side end 15 is fixed by means of fastening screws 17.
  • the fixation is possible as an alternative to the screws with other positive connection elements.
  • the base plate 8 threaded recesses, in which the screws 17 are screwed.
  • the inner combustion chamber wall 6 is provided with radially outwardly directed hooks 18, which are guided longitudinally displaceably in recesses 19 of the outer combustion chamber wall 7.
  • the mounting of the hooks 18 can take place directly on the outer combustion chamber wall 7 or in the region of a sealing lip 20 of a strip seal to an outlet nozzle guide vane (NGV).
  • NVG outlet nozzle guide vane
  • Fig. 4, 5 . 7 and 9 each show different design variants of the storage of the rear end portion of the inner combustion chamber wall 6.
  • Die Fig. 4 clarifies in an enlarged view the in Fig. 3 shown solution. From the back view of the Fig. 6 shows that distributed on the circumference of the inner combustion chamber wall 6 a plurality of hooks 18 may be formed.
  • a securing lug 21 is provided at the free end of the hook 18, which in particular facilitates the assembly of the inner combustion chamber wall 6 and prevents loosening of the hook 18.
  • Fig. 7 A similar embodiment is in Fig. 7 shown.
  • the recess 19 is provided with a stepped cross-section, as it turns out Fig. 8 results.
  • FIGS. 9 and 10 shows a resilient projection 22 which is formed at the free end of the hook 18 and abuts against the outer combustion chamber wall 7 to bias the inner combustion chamber wall backlash.

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)
EP15158435.6A 2014-03-11 2015-03-10 Chambre de combustion d'une turbine à gaz Withdrawn EP2918914A1 (fr)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
DE102014204476.6A DE102014204476A1 (de) 2014-03-11 2014-03-11 Brennkammer einer Gasturbine

Publications (1)

Publication Number Publication Date
EP2918914A1 true EP2918914A1 (fr) 2015-09-16

Family

ID=52633151

Family Applications (1)

Application Number Title Priority Date Filing Date
EP15158435.6A Withdrawn EP2918914A1 (fr) 2014-03-11 2015-03-10 Chambre de combustion d'une turbine à gaz

Country Status (3)

Country Link
US (1) US9335048B2 (fr)
EP (1) EP2918914A1 (fr)
DE (1) DE102014204476A1 (fr)

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP3392567A1 (fr) * 2017-04-18 2018-10-24 United Technologies Corporation Rail d'extrémité de panneau de chemise de chambre de combustion
FR3097028A1 (fr) * 2019-06-07 2020-12-11 Safran Helicopter Engines Procédé de fabrication d’un tube à flamme pour une turbomachine

Families Citing this family (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US10935236B2 (en) 2016-11-10 2021-03-02 Raytheon Technologies Corporation Non-planar combustor liner panel for a gas turbine engine combustor
US10830433B2 (en) 2016-11-10 2020-11-10 Raytheon Technologies Corporation Axial non-linear interface for combustor liner panels in a gas turbine combustor
US10655853B2 (en) 2016-11-10 2020-05-19 United Technologies Corporation Combustor liner panel with non-linear circumferential edge for a gas turbine engine combustor
US10935235B2 (en) 2016-11-10 2021-03-02 Raytheon Technologies Corporation Non-planar combustor liner panel for a gas turbine engine combustor
US20180306113A1 (en) * 2017-04-19 2018-10-25 United Technologies Corporation Combustor liner panel end rail matching heat transfer features
US10941944B2 (en) 2018-10-04 2021-03-09 Raytheon Technologies Corporation Consumable support structures for additively manufactured combustor components

Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB1539035A (en) * 1976-04-22 1979-01-24 Rolls Royce Combustion chambers for gas turbine engines
US5291732A (en) * 1993-02-08 1994-03-08 General Electric Company Combustor liner support assembly
US5435139A (en) 1991-03-22 1995-07-25 Rolls-Royce Plc Removable combustor liner for gas turbine engine combustor
US5758503A (en) 1995-05-03 1998-06-02 United Technologies Corporation Gas turbine combustor
EP1486732A2 (fr) * 2003-06-11 2004-12-15 General Electric Company Chambre de combustion avec un revêtement flottant
EP1777460A1 (fr) * 2005-10-18 2007-04-25 Snecma Fixation d'une chambre de combustion à l'intérieur de son carter

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US3116606A (en) * 1958-07-21 1964-01-07 Gen Motors Corp Combustion can support
CH428324A (de) 1964-05-21 1967-01-15 Prvni Brnenska Strojirna Brennkammer
US3653207A (en) * 1970-07-08 1972-04-04 Gen Electric High fuel injection density combustion chamber for a gas turbine engine
US4912922A (en) * 1972-12-19 1990-04-03 General Electric Company Combustion chamber construction
US4158949A (en) * 1977-11-25 1979-06-26 General Motors Corporation Segmented annular combustor
US4628694A (en) 1983-12-19 1986-12-16 General Electric Company Fabricated liner article and method
DE3424345A1 (de) 1984-07-03 1986-01-09 General Electric Co., Schenectady, N.Y. Brennkammer
US4944151A (en) 1988-09-26 1990-07-31 Avco Corporation Segmented combustor panel
GB2355784B (en) * 1999-10-27 2004-05-05 Abb Alstom Power Uk Ltd Gas turbine
WO2002088601A1 (fr) 2001-04-27 2002-11-07 Siemens Aktiengesellschaft Chambre de combustion, en particulier d'une turbine a gaz
EP1284392A1 (fr) 2001-08-14 2003-02-19 Siemens Aktiengesellschaft Chambre de combustion
DE102004044852A1 (de) * 2004-09-10 2006-03-16 Deutsches Zentrum für Luft- und Raumfahrt e.V. Heißgaskammer und Schindel für eine Heißgaskammer
EP1767835A1 (fr) 2005-09-22 2007-03-28 Siemens Aktiengesellschaft Dispositif d'étanchéité résistant aux hautes températures, en particulier pour turbines à gaz
US7762075B2 (en) 2007-08-14 2010-07-27 General Electric Company Combustion liner stop in a gas turbine
FR2953907B1 (fr) 2009-12-11 2012-11-02 Snecma Chambre de combustion pour turbomachine
EP2402659A1 (fr) 2010-07-01 2012-01-04 Siemens Aktiengesellschaft Coque extérieure pour chambre de combustion
GB201205011D0 (en) * 2012-03-22 2012-05-09 Rolls Royce Plc A thermal barrier coated article and a method of manufacturing a thermal barrier coated article

Patent Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB1539035A (en) * 1976-04-22 1979-01-24 Rolls Royce Combustion chambers for gas turbine engines
US5435139A (en) 1991-03-22 1995-07-25 Rolls-Royce Plc Removable combustor liner for gas turbine engine combustor
US5291732A (en) * 1993-02-08 1994-03-08 General Electric Company Combustor liner support assembly
US5758503A (en) 1995-05-03 1998-06-02 United Technologies Corporation Gas turbine combustor
EP1486732A2 (fr) * 2003-06-11 2004-12-15 General Electric Company Chambre de combustion avec un revêtement flottant
EP1777460A1 (fr) * 2005-10-18 2007-04-25 Snecma Fixation d'une chambre de combustion à l'intérieur de son carter

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP3392567A1 (fr) * 2017-04-18 2018-10-24 United Technologies Corporation Rail d'extrémité de panneau de chemise de chambre de combustion
FR3097028A1 (fr) * 2019-06-07 2020-12-11 Safran Helicopter Engines Procédé de fabrication d’un tube à flamme pour une turbomachine

Also Published As

Publication number Publication date
DE102014204476A1 (de) 2015-10-01
US9335048B2 (en) 2016-05-10
US20150260402A1 (en) 2015-09-17

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