EP2918913A1 - 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
EP2918913A1
EP2918913A1 EP15158432.3A EP15158432A EP2918913A1 EP 2918913 A1 EP2918913 A1 EP 2918913A1 EP 15158432 A EP15158432 A EP 15158432A EP 2918913 A1 EP2918913 A1 EP 2918913A1
Authority
EP
European Patent Office
Prior art keywords
combustion chamber
chamber wall
wall
shingles
end portion
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
EP15158432.3A
Other languages
German (de)
English (en)
Other versions
EP2918913B1 (fr
Inventor
Miklós Dr.-Ing. Gerendás
Carsten Dr.-Ing. Clemen
Thomas Dr.-Ing. Dörr
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 EP2918913A1 publication Critical patent/EP2918913A1/fr
Application granted granted Critical
Publication of EP2918913B1 publication Critical patent/EP2918913B1/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
    • 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
    • F23R2900/00012—Details of sealing devices

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 front end, relative to the flow direction of the combustion chamber longitudinally displaceable in a groove in the region of a base plate, which a Assigns combustion chamber head is held.
  • the inner combustion chamber wall is fixed to the outer combustion chamber wall.
  • the first, cold combustion chamber wall as is known from the prior art, namely as a joined sheet metal part.
  • 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 according to the invention, for example, by screws or a 360 ° extending clamping ring or similar solutions, such as claws done. According to the invention, there is thus a positive fixing at the rear area of the inner 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 front end region of the inner combustion chamber wall is formed like a seal, for example by means of an additional annular flange or the like.
  • a seal is additionally ensured, but does not affect the longitudinal displacement of the front end portion of the inner combustion chamber wall.
  • the attachment or fixation of the rear end of the combustion chamber wall can be adapted in a favorable manner to the respective structural requirements, for example by means of screws, which are arranged radially or axially relative to the direction of flow or a central axis of the combustion chamber.
  • 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. There no Stud bolts are present, there are no restrictions on the heat transfer.
  • 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 extend radially inward 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.
  • mixed air Zumischlöcher 5 provided for supplying mixed air Zumischlöcher 5 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.
  • the storage is also via combustion chamber suspensions 11 and combustion chamber flanges 12.
  • 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.
  • a groove 16 is formed on the base plate 8, in which a front end 15 of the inner combustion chamber wall 6 is inserted longitudinally displaceable.
  • the rear portion of the inner combustion chamber wall 6 is fixed to the outer combustion chamber wall 7 by means of fastening screws 19 a. In this area, cooling no longer plays such a crucial role, so that this area is not subjected to extreme thermal stress.
  • the base plate 8 has an annular groove 16.
  • the groove 16 is the front end of the inner combustion chamber wall 6 inserted longitudinally displaceable.
  • the groove 16 is formed by a circumferential ridge 17, as well as in the embodiment of Fig. 6 is apparent.
  • the groove 16 is incorporated as a circumferential annular groove in the material of the base plate 8.
  • the front end of the inner combustion chamber wall 6 has a ring-like thickening, which serves both for storage and for sealing.
  • an impingement cooling hole 9 and an effusion hole 10 are shown.
  • the head-side end 15 of the inner combustion chamber wall 6 also formed as a circumferential ring land and also serves for sealing and support.
  • the reference numeral 24 designates an additional air hole in the base plate 8.
  • Fig. 6 shows an angled configuration of the head-side end 15 of the inner combustion chamber wall 6. This is mounted in the groove 16 formed by the circumferential ridge 17.
  • Fig. 7 to 12 show different embodiments of the rear bearing of the inner combustion chamber wall 6.
  • a solution is shown in which a fastening screw 19a is screwed in the radial direction.
  • the sealing lip 20 is formed on the outer combustion chamber wall 7.
  • the Fig. 8 an embodiment in which the sealing lip 20 is formed on the inner combustion chamber wall 6 and has an angled ring shape, which rests against the end of the outer combustion chamber wall 7.
  • the fastening screw 19b is inserted in the axial direction in each case.
  • the inner combustion chamber wall 6 is formed angled.
  • the Fig. 10 shows a design variant in which two sealing lips 20 are provided.
  • an additional clamping ring 21 is provided, which is designed as a peripheral ring or can be configured as a segmented claw.
  • the clamping ring 21 carries the Sealing lip 20.
  • an overhang 23 is provided to protect the clamping ring 21 or the groove 22 from hot gases.
  • the Fig. 13 shows a further embodiment in an analogous representation to Fig. 3 ,
  • the front, head-side end 15 of the inner, hot combustion chamber wall 6 between the outer, cold combustion chamber wall 7 and the heat shield 2 is guided longitudinally displaceable in a slot formed between these components.
  • the outer cold combustion chamber wall 7 can be constructed conventionally.
  • the inner (hot) combustion chamber wall 6 is formed of sheet metal (360 °) or (possibly cast or sintered) segments (or shingles), which are characterized in that the hot gas side panel front between the base plate 8 or the cold combustion chamber wall 7 and the Heat shield 2 is guided around the burner so that a longitudinal displacement is possible.
  • the hot combustion chamber wall 6 is fixed, for example by screws or a clamping ring (360 °) or claws (individual segments). Since a cavity 29 must be formed between the two combustion chamber walls 6, 7, it is advantageous to thicken the head-side end 15 of the shingle 6 in order to set this distance.
  • FIGS. 14 and 15 are shown a variety of design variants for this purpose.
  • a support ring 28 is formed, which supports the inner combustion chamber wall 6.
  • Fig. 14 is the head end 15 thickened formed, as well as in Fig. 4 shown.
  • the Fig. 15 shows a variant of the bent portion 26, while the Fig. 16 represents a wave stamping. Similar details can also be introduced in the cast or sintered variant. Also at the turbine end of the hot combustion chamber wall 6, the distance to the cold side must be bridged.
  • a step can be embossed in the hot side, so that the attachment (ring or segment) is not exposed as a projecting stage of hot gas flow, as in the FIGS. 17 and 18 is shown.
  • a circumferential groove could also be used be introduced hot gas component, so that the retaining clip does not carry the full temperature load and thus can be made of a cheaper material.

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)
EP15158432.3A 2014-03-11 2015-03-10 Chambre de combustion d'une turbine à gaz Active EP2918913B1 (fr)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
DE102014204481.2A DE102014204481A1 (de) 2014-03-11 2014-03-11 Brennkammer einer Gasturbine

Publications (2)

Publication Number Publication Date
EP2918913A1 true EP2918913A1 (fr) 2015-09-16
EP2918913B1 EP2918913B1 (fr) 2017-11-15

Family

ID=52633150

Family Applications (1)

Application Number Title Priority Date Filing Date
EP15158432.3A Active EP2918913B1 (fr) 2014-03-11 2015-03-10 Chambre de combustion d'une turbine à gaz

Country Status (3)

Country Link
US (1) US9506653B2 (fr)
EP (1) EP2918913B1 (fr)
DE (1) DE102014204481A1 (fr)

Families Citing this family (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP3044444B1 (fr) * 2013-09-13 2019-11-06 United Technologies Corporation Chambre de combustion pour une turbine à gaz avec un panneau de chemisage hermétiquement scellé
GB201518345D0 (en) * 2015-10-16 2015-12-02 Rolls Royce Combustor for a gas turbine engine
US10935236B2 (en) * 2016-11-10 2021-03-02 Raytheon Technologies Corporation Non-planar combustor liner panel 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
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
US10816213B2 (en) 2018-03-01 2020-10-27 General Electric Company Combustor assembly with structural cowl and decoupled chamber
US11402096B2 (en) * 2018-11-05 2022-08-02 Rolls-Royce Corporation Combustor dome via additive layer manufacturing
US11226099B2 (en) * 2019-10-11 2022-01-18 Rolls-Royce Corporation Combustor liner for a gas turbine engine with ceramic matrix composite components
DE102020203017A1 (de) * 2020-03-10 2021-09-16 Siemens Aktiengesellschaft Brennkammer mit keramischem Hitzeschild und Dichtung

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US4628694A (en) * 1983-12-19 1986-12-16 General Electric Company Fabricated liner article and method
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
US20050086945A1 (en) * 2001-04-27 2005-04-28 Peter Tiemann Combustion chamber, in particular of a gas turbine
EP1767835A1 (fr) * 2005-09-22 2007-03-28 Siemens Aktiengesellschaft Dispositif d'étanchéité résistant aux hautes températures, en particulier pour turbines à gaz
WO2011070273A1 (fr) * 2009-12-11 2011-06-16 Snecma Chambre de combustion pour turbomachine
EP2402659A1 (fr) * 2010-07-01 2012-01-04 Siemens Aktiengesellschaft Coque extérieure pour chambre de combustion

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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
US20050086945A1 (en) * 2001-04-27 2005-04-28 Peter Tiemann Combustion chamber, in particular of a gas turbine
EP1767835A1 (fr) * 2005-09-22 2007-03-28 Siemens Aktiengesellschaft Dispositif d'étanchéité résistant aux hautes températures, en particulier pour turbines à gaz
WO2011070273A1 (fr) * 2009-12-11 2011-06-16 Snecma Chambre de combustion pour turbomachine
EP2402659A1 (fr) * 2010-07-01 2012-01-04 Siemens Aktiengesellschaft Coque extérieure pour chambre de combustion

Also Published As

Publication number Publication date
US9506653B2 (en) 2016-11-29
DE102014204481A1 (de) 2015-09-17
EP2918913B1 (fr) 2017-11-15
US20150260401A1 (en) 2015-09-17

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