EP3410014A1 - Plattenhalter für eine brennkammer einer gasturbine - Google Patents

Plattenhalter für eine brennkammer einer gasturbine Download PDF

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Publication number
EP3410014A1
EP3410014A1 EP17425059.7A EP17425059A EP3410014A1 EP 3410014 A1 EP3410014 A1 EP 3410014A1 EP 17425059 A EP17425059 A EP 17425059A EP 3410014 A1 EP3410014 A1 EP 3410014A1
Authority
EP
European Patent Office
Prior art keywords
tile
tubular body
wall
neck
axis
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
EP17425059.7A
Other languages
English (en)
French (fr)
Other versions
EP3410014B1 (de
Inventor
Giovanni Campa
Sergio Di Liddo
Mirko Ruben Bothien
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.)
Ansaldo Energia Switzerland AG
Ansaldo Energia SpA
Original Assignee
Ansaldo Energia Switzerland AG
Ansaldo Energia SpA
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 Ansaldo Energia Switzerland AG, Ansaldo Energia SpA filed Critical Ansaldo Energia Switzerland AG
Priority to EP17425059.7A priority Critical patent/EP3410014B1/de
Priority to CN201810546456.6A priority patent/CN108980894B/zh
Publication of EP3410014A1 publication Critical patent/EP3410014A1/de
Application granted granted Critical
Publication of EP3410014B1 publication Critical patent/EP3410014B1/de
Active 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
    • F23R3/007—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
    • F23R3/42—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
    • F23R2900/00014—Reducing thermo-acoustic vibrations by passive means, e.g. by Helmholtz resonators
    • 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 present invention relates to a tile holder for a combustor of a gas turbine.
  • acoustic dampers are used for the purpose of mitigating the acoustic pulsations that may occur during operation in specific frequency ranges.
  • Acoustic dampers attenuate acoustic oscillations in respective frequency bands and, when appropriately tuned, may prevent noxious vibrations to the benefit of efficiency, performance and structural integrity.
  • size and location of the acoustic dampers need to be accurately selected and meet several requirements, e.g. in relation to acoustic, thermal and mechanical performance, feasibility and gas turbine efficiency.
  • Coupling acoustic dampers to the combustion chambers of combustors is not a simple task, because combustion chambers must be internally provided with a thermoinsulating coating or heat-shield, due to the high temperatures reached during the machine operation.
  • the heat-shield generally comprises a plurality of tiles made of special metallic alloys or of refractory material and arranged in contiguous rows on the inner surface of the shell of the combustion chamber, so as to define a substantially continuous surface.
  • Providing access to the combustion chamber for acoustic coupling would require modifying the tiles, in other words either making special refractory tiles with access holes or drilling holes in metallic tiles. This would in any case incur additional costs and may also put the mechanical resistance of the tiles at risk.
  • tile holders which are used to retain the tiles against the shell of the combustion chamber, limit the space available for coupling acoustic dampers and the positioning thereof is made difficult if possible at all.
  • the object of the present invention is therefore to provide a tile holder for a combustor of a gas turbine, which allows to overcome or at least reduce the limitations described above.
  • a tile holder for a combustor of a gas turbine comprising:
  • the tile holder therefore provides also the functions of mechanical supporting and acoustic coupling for an acoustic damper.
  • Acoustic dampers can thus be easily fitted to the combustor and acoustically coupled to the combustion chamber and there is no need to modify the tiles. All tiles having a through seat for receiving a tile holder, no matter whether metallic tiles or refractory tiles, can be equally used for the purpose of supporting and acoustically coupling acoustic dampers.
  • the retaining system comprises a retaining member at a tile-coupling end of the tubular body, the retaining member projecting radially outward from the tubular body.
  • the inner end of the tile holder that faces the inside of the combustion chamber, is configured to easily engage and firmly retain a respective tile.
  • the retaining member comprises a retaining ring removably coupled to the tile-coupling end of the tubular body.
  • Removable connection e.g. threaded connection
  • Removable connection simplifies assembling and disassembling of the tile holder and acoustic damper, that is particularly appreciated in maintenance operation for replacement of any of the connector, acoustic damper and tile as required.
  • the retaining system comprises a threaded portion at a wall-coupling end of the tubular body.
  • the threaded portion provides for direct coupling the shell of the combustion chamber, which is usually provided with threaded through seats for receiving conventional tile holders.
  • the retaining system comprises an externally threaded bushing fitted onto the wall-coupling end of the tubular body.
  • Parts of the tile holder can be easily mounted and removed.
  • the tubular body may be extracted and replaced without removing the threaded bushing, which may remain permanently connected to the shell because of high operating temperatures.
  • the neck comprises a securing mechanism configured to secure the neck to the wall.
  • the securing mechanism helps fastening the neck directly and independently to an outer face of the shell of the combustion chamber.
  • Other parts of the tile holder, such as the threaded portion of the retaining system, may be removed (e.g. for the purpose of replacing the tile) without intervening on the acoustic damper.
  • the securing mechanism comprises mounting plates, integral with the neck and provided with mounting holes, and screws through the mounting holes for connecting to seats in the wall.
  • the screws are parallel to the first axis of the tubular body or the screws are parallel to a portion of the neck at an interface with the tubular body.
  • the screws can be easily tightened into respective receiving threaded holes in the outer face of the shell of the combustion chamber.
  • the orientation of the screws may be conveniently selected as desired depending on the freedom to make the receiving holes, namely while manufacturing a new machine or during retrofitting operations.
  • the neck of the acoustic damper comprises a terminal duct, having the damping volume at one end, and an intermediate duct, between the tubular body and the terminal duct.
  • Modular construction of the acoustic damper increases flexibility of use and ease of mount.
  • the intermediate duct is coaxial to the terminal duct.
  • the intermediate duct extends along a third axis which is transverse to the first axis and to the second axis.
  • the configuration of the acoustic damper can be flexibly selected to meet both acoustic requirements and space limitations.
  • the terminal duct and the intermediate duct comprise respective coupling flanges for releasable mutual connection.
  • the coupling through flanges can be easily released for removing and replacing the acoustic damper. Maintenance and retrofit are therefore made simpler.
  • the tubular body has a rounded edge coupled to the neck, whereby a smooth transition is defined between the tubular body and the neck.
  • the smooth transition is beneficial for the properties of the acoustic damper.
  • a combustor of a gas turbine comprises a combustion chamber, having a shell defined by a wall and a heat-shield on an inner surface of the wall, wherein the heat-shield comprises a plurality of tiles and at least one damper connection tile is retained against the wall by a tile holder according to any one of the preceding claims.
  • the wall has a through seat and the connector of the tile holder is fitted in the through seat.
  • the damper connection tile has a rim that delimits at least a portion of a retaining seat and the connector engages the rim to retain the damper connection tile against the wall.
  • the combustor of a gas turbine comprises a combustion chamber, having a shell defined by a wall and a heat-shield on an inner surface of the wall, wherein the heat-shield comprises a plurality of tiles of refractory material and an acoustic damper acoustically coupled to the combustion chamber through the wall and a passage in at least one of the tiles of refractory material.
  • FIGs 1 illustrates a combustor 1 of a gas turbine (with parts removed for the sake of clarity).
  • the combustor 1 comprises an annular combustion chamber 2, extending around an axis A and having a shell defined by an annular wall 3 and a heat-shield 5 on an inner surface of the annular wall 3.
  • the arrangement herein described is given purely by way of example and is not to be considered limiting, however.
  • the combustion chamber may be of any type, such as of the silo or can or cannular type.
  • the heat-shield 5 comprises a plurality of first thermoinsulating tiles 7 of a metallic alloy and a plurality of second thermoinsulating tiles 8 of refractory material, all arranged in adjacent circumferential rows, around the axis A of the combustion chamber 2.
  • the thermoinsulating tiles 7, 8 may be of generally quadrangular shape. Also other shapes are available, however.
  • At least one of the first thermoinsulating tiles 7, selected for the purpose of coupling an acoustic damper, is fastened to the annular wall 3 by a tile holder 10 in accordance with an embodiment of the present invention.
  • the tile holder 10 comprises a connector 11 and an acoustic damper 12 coupled to the inside of the combustor chamber 2 through the connector 11 as described hereinafter.
  • the other first thermoinsulating tiles 7 may be supported by further tile holders 10 or by conventional tile holders, as desired for the purpose of coupling acoustic dampers to the combustion chamber 2.
  • the second thermoinsulating tiles 8 are provided with spring holders 13, which engage circumferential guides 14, which are formed on the inner face of the wall 3 and extend around the axis A.
  • the tile holder 10 comprises a connector 11 and an acoustic damper 12 coupled to the inside of the combustor chamber 2 through the connector 11.
  • the connector 11 comprises a tubular body 15, which extends along a connector axis X1, and a retaining system 17, configured to secure the tubular body 15 in a threaded through seat 18 in the annular wall 3 and to retain the respective first thermoinsulating tile 7 against the annular wall 3.
  • the tubular body may have any suitable cross-section, such as circular, elliptical or polygonal cross-section and the present disclosure is not limited to a specific example.
  • the retaining system 17 comprises a retaining member 20 at a first end of the tubular body 15 coupled to the first thermoinsulating tile 7.
  • the first thermoinsulating tile 7 has a through retaining seat 21 delimited by a rim 22.
  • the retaining seat 21 is provided centrally in the first thermoinsulating tile 7. In other embodiments not shown, however, the retaining seat may be provided between two or more first thermoinsulating tiles. In this case, each first thermoinsulating tile has a rim that delimits a portion of the through retaining seat.
  • the retaining member 20 projects radially outward from the tubular body 15 and engages the rim 22 to retain the first thermoinsulating tile 7 against the annular wall 3.
  • the retaining member 20 comprises a retaining ring removably coupled to the first end of the tubular body 15, e.g. by a threaded coupling.
  • the retaining system 17 comprises a threaded portion 23 at a second end of the tubular body 15 coupled to the annular wall 3.
  • the threaded portion 23 is defined on an outer surface of an externally threaded bushing 25 fitted onto the second end of the tubular body 15. The bushing 25 is inserted into the threaded through seat 18 in the annular wall 3 of the combustion chamber 2 to secure the tile holder 10.
  • the acoustic damper 12 has a damping volume 30 and a neck 31 that extends at least in part along a neck axis X2 and is acoustically coupled to the outside of the acoustic damper 12 through the tubular body 15 of the connector 11.
  • the outside of the acoustic damper 12 is the inside of the combustion chamber 2.
  • the size and shape of the damping volume 30, and the length, the diameter and cross section of the neck 31 are selected to obtain damping effect in a frequency band as desired in connection with operation of the combustor 1.
  • the neck 31 may have any suitable cross-section and the diameter or cross dimension may be either constant or variable along the neck axis X2.
  • the tubular body 15 has also the function of extension of the neck 31, so an equivalent neck length that may be considered, that includes also the length of the tubular body 15.
  • the connector axis X1 and the neck axis X2 are transverse to the one another, so a duct defined by the tubular body 15 and the neck 31 and connecting the combustion chamber 2 and the damper volume 30 forms a bend 33 at an interface of the neck 31 and the connector 11.
  • the angle between the connector axis X1 and the neck axis X2 may be selected to comply with space occupation requirements.
  • the neck 31 is arranged substantially radially with respect to axis A.
  • the neck 31 of the acoustic damper 12 comprises a terminal duct 31a, at one end of which the damping volume 30 is located, and an intermediate duct 31b, between the tubular body 15 and the terminal duct 31a.
  • the intermediate duct 31b is coaxial to the terminal duct 31a.
  • the terminal duct 31a and the intermediate duct 31b comprise respective coupling flanges 31c, 31d for releasable mutual connection.
  • the neck 31 is also provided with a securing mechanism 35 configured to secure the neck 31 to the annular wall 3 of the combustion chamber 2.
  • the securing mechanism 35 comprises mounting plates 36, integral with the intermediate duct 31b of the neck 31 and having mounting holes 37, and screws 38 through the mounting holes 37.
  • the screws 37 are coupled to respective threaded seats in the outer face of the annular wall 3.
  • the screws 37 are parallel to the neck axis X2 in a portion of the neck 31 at an interface with the tubular body 15.
  • the tubular body 15 has a rounded edge 15a coupled to the neck 31, whereby a smooth transition is defined between the tubular body 15 and the neck 31.
  • a belleville washer 39 is arranged between the rounded edge 15a of the tubular body 15 and the threaded bushing 25.
  • the neck 31 of the acoustic damper 12 is provided with a securing mechanism, here indicated by 135, which is configured to secure the neck 31 to the annular wall 3 of the combustion chamber 2 and comprises mounting plates 136, integral with the neck 31 and having mounting holes 137, and screws 138 through the mounting holes 137.
  • the screws 138 are coupled to respective threaded seats in the outer face of the annular wall 3.
  • the screws 138 are parallel to the connector axis X1.
  • Figure 6 shows another embodiment of the invention.
  • the acoustic damper 12 has a neck 231 with a terminal portion 231a which extend along the neck axis X2 and an intermediate duct 231b that extends along an intermediate axis X3, which is transverse both to the connector axis X1 and to the axis.
  • a securing mechanism 235 with screws 238 are parallel to the connector axis X1.
  • a tile holder 310 in combustor 300 of a gas turbine a tile holder 310 comprises a connector 311 and an acoustic damper 312 as described.
  • the tile holder 310 is coupled to a thermoinsulating tiles 308 of refractory material, which has a through retaining seat 321.
  • Second thermoinsulating tiles 8 with a central hole are normally present in annular combustion chamber of gas turbines as closure tiles. While the other second thermoinsulating tiles 308 are slidably inserted along circumferential guides (as circumferential guides 14 of figure 1 ), the closure tiles are inserted last and need to be secured to the annular wall 3 by tile holders. For this reason such tiles are provided with through holes.

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Ceramic Engineering (AREA)
  • Connection Of Plates (AREA)
  • Exhaust Silencers (AREA)
EP17425059.7A 2017-05-31 2017-05-31 Plattenhalter für eine brennkammer einer gasturbine Active EP3410014B1 (de)

Priority Applications (2)

Application Number Priority Date Filing Date Title
EP17425059.7A EP3410014B1 (de) 2017-05-31 2017-05-31 Plattenhalter für eine brennkammer einer gasturbine
CN201810546456.6A CN108980894B (zh) 2017-05-31 2018-05-31 用于燃气涡轮的燃烧器的瓦保持器

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP17425059.7A EP3410014B1 (de) 2017-05-31 2017-05-31 Plattenhalter für eine brennkammer einer gasturbine

Publications (2)

Publication Number Publication Date
EP3410014A1 true EP3410014A1 (de) 2018-12-05
EP3410014B1 EP3410014B1 (de) 2021-01-20

Family

ID=59315570

Family Applications (1)

Application Number Title Priority Date Filing Date
EP17425059.7A Active EP3410014B1 (de) 2017-05-31 2017-05-31 Plattenhalter für eine brennkammer einer gasturbine

Country Status (2)

Country Link
EP (1) EP3410014B1 (de)
CN (1) CN108980894B (de)

Citations (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1596130A1 (de) * 2004-05-14 2005-11-16 Siemens Aktiengesellschaft Vorrichtung zur Dämpfung von thermoakustischen Schwingungen in Brennkammern mit einstellbarer Resonatorfrequenz
EP1605209A1 (de) * 2004-06-07 2005-12-14 Siemens Aktiengesellschaft Brennkammer mit einer Dämpfungseinrichtung zur Dämpfung von thermoakustischen Schwingungen
EP1849974A2 (de) * 2006-04-27 2007-10-31 United Technologies Corporation Tailcone-Resonator für ein Turbinentriebwerk
EP1862740A1 (de) * 2006-05-31 2007-12-05 Siemens Aktiengesellschaft Brennkammerwand
EP2251535A2 (de) * 2009-05-05 2010-11-17 Rolls-Royce plc Dämpfungsanordnung
WO2012057994A2 (en) * 2010-10-29 2012-05-03 Solar Turbines Incorporated Gas turbine combustor with mounting for helmholtz resonators
DE102011075582A1 (de) * 2011-05-10 2012-11-15 Siemens Aktiengesellschaft Dampfkraftanlage, Verwendung eines akustischen Resonators für eine Dampfkraftanlage, und Verfahren zum Anschluss eines akustischen Resonators bei einer Dampfkraftanlage
WO2015022222A1 (de) * 2013-08-15 2015-02-19 Siemens Aktiengesellschaft Hitzeschild mit mindestens einem helmholtzresonator
EP2865947A1 (de) * 2013-10-28 2015-04-29 Alstom Technology Ltd Dämpfer für Gasturbine

Patent Citations (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1596130A1 (de) * 2004-05-14 2005-11-16 Siemens Aktiengesellschaft Vorrichtung zur Dämpfung von thermoakustischen Schwingungen in Brennkammern mit einstellbarer Resonatorfrequenz
EP1605209A1 (de) * 2004-06-07 2005-12-14 Siemens Aktiengesellschaft Brennkammer mit einer Dämpfungseinrichtung zur Dämpfung von thermoakustischen Schwingungen
EP1849974A2 (de) * 2006-04-27 2007-10-31 United Technologies Corporation Tailcone-Resonator für ein Turbinentriebwerk
EP1862740A1 (de) * 2006-05-31 2007-12-05 Siemens Aktiengesellschaft Brennkammerwand
EP2251535A2 (de) * 2009-05-05 2010-11-17 Rolls-Royce plc Dämpfungsanordnung
WO2012057994A2 (en) * 2010-10-29 2012-05-03 Solar Turbines Incorporated Gas turbine combustor with mounting for helmholtz resonators
DE102011075582A1 (de) * 2011-05-10 2012-11-15 Siemens Aktiengesellschaft Dampfkraftanlage, Verwendung eines akustischen Resonators für eine Dampfkraftanlage, und Verfahren zum Anschluss eines akustischen Resonators bei einer Dampfkraftanlage
WO2015022222A1 (de) * 2013-08-15 2015-02-19 Siemens Aktiengesellschaft Hitzeschild mit mindestens einem helmholtzresonator
EP2865947A1 (de) * 2013-10-28 2015-04-29 Alstom Technology Ltd Dämpfer für Gasturbine

Also Published As

Publication number Publication date
CN108980894A (zh) 2018-12-11
CN108980894B (zh) 2021-11-05
EP3410014B1 (de) 2021-01-20

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