EP2442032A1 - Segment d'usure dans l'accrochage de support d'aube directrice de turbines d'une coque extérieure d'une chambre de combustion annulaire - Google Patents

Segment d'usure dans l'accrochage de support d'aube directrice de turbines d'une coque extérieure d'une chambre de combustion annulaire Download PDF

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Publication number
EP2442032A1
EP2442032A1 EP10187238A EP10187238A EP2442032A1 EP 2442032 A1 EP2442032 A1 EP 2442032A1 EP 10187238 A EP10187238 A EP 10187238A EP 10187238 A EP10187238 A EP 10187238A EP 2442032 A1 EP2442032 A1 EP 2442032A1
Authority
EP
European Patent Office
Prior art keywords
combustion chamber
ring
outer shell
turbine
groove
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Withdrawn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
EP10187238A
Other languages
German (de)
English (en)
Inventor
Thomas Brandenburg
Olga Deiss
Giuseppe Gaio
Sabine GRENDEL
Jens Kleinfeld
Andre Kluge
Thomas Alexis Schneider
Christian Scholz
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.)
Siemens AG
Original Assignee
Siemens AG
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 Siemens AG filed Critical Siemens AG
Priority to EP10187238A priority Critical patent/EP2442032A1/fr
Publication of EP2442032A1 publication Critical patent/EP2442032A1/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Withdrawn legal-status Critical Current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
    • 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 a combustion chamber outer shell, in particular a Turbinenleitschaufelaverhakung an annular combustion chamber outer shell.
  • a gas turbine has a rotor rotatably mounted about a rotation axis with a shaft.
  • a rotor rotatably mounted about a rotation axis with a shaft.
  • an intake housing a compressor, a combustion chamber (for example an annular combustion chamber) with a plurality of coaxially arranged burners, a turbine and an exhaust gas housing.
  • the combustor communicates with a hot gas duct of the turbine at the inlet of which a turbine vane support carrying the vanes is disposed.
  • the combustion chamber outer shell of the gas turbine is fixed in the axial direction on the turbine guide vane carrier.
  • the axial fixation of the combustion chamber outer shell is ensured by means of tongue and groove connection to the turbine guide vane carrier.
  • the spring consisting of ring segments, is screwed to the turbine guide vane carrier and engages from outside into a groove located in the combustion chamber outer shell. Through the fit between the tongue and groove, the axial position of the combustion chamber outer shell is secured to the turbine vane support.
  • the turbine-side end face of the combustion chamber outer shell has run-out deviations. Correlations have been found between measured deviations from plan and wear of the tongue and groove joint, so that the axial runout is considered to be one of the causes of wear.
  • the groove of the combustion chamber outer shell is over-turned and modified ring segments are mounted on the diffuser. This is possible only up to a certain residual thickness of the hook formed by the groove on the turbine guide blade carrier end facing the combustion chamber outer shell, as with considerable reduction of the hook wall thickness there is a risk that the component integrity is no longer guaranteed. As a result, complex repairs in service are necessary, from welding to replacement of the combustion chamber outer shell.
  • the object of the invention is to provide a combustion chamber outer shell for a gas turbine, which avoids the disadvantages described above.
  • the L-ring is used interchangeably. This makes it easier to replace a worn L-ring with a new L-ring.
  • the L-ring in the scope of several parts. At least two-piece design ensures easy assembly and disassembly.
  • groove and L-ring are designed as a snug fit, so that there can be no relative movement between the groove and L-ring.
  • the L-ring is fixed with at least one dowel pin in order to avoid a rotation of the L-ring relative to the groove.
  • a gas turbine includes a combustor outer shell according to the invention and a turbine vane support disposed on the face of the combustor outer wall, wherein ring segments secured to the turbine vane support engage the groove.
  • the introduction of a wear segment into the turbine vane hanger of the outer shell of the combustion chamber provides the following advantages: Wear on the outer shell of the combustion chamber is avoided or at least significantly reduced because wear on a wear segment, i. the L-ring is shifted.
  • the wear segment can be exchanged during the revision.
  • the replacement of the wear segment is much cheaper than an exchange of the combustion chamber outer shell. This concerns both the costs for assembly and disassembly and the component costs. Downtimes due to wear-induced external shell replacement are avoided.
  • FIG. 1 showing a highly schematic sectional view of a gas turbine, explaining the structure and function of a gas turbine.
  • the gas turbine 1 comprises a compressor section 2, a combustion section 3, which in the present embodiment comprises an annular combustion chamber 4 with burners 5, and a turbine section 6.
  • a rotor 7, also called a runner, extends through all sections and carries compressor blade rings 8 and 8 in the compressor section 2 In the turbine section 6 turbine blade rings 9. Between adjacent compressor blade rings 8 and between adjacent turbine blade rings 9 wreaths of compressor vanes 10 and wreaths of turbine vanes 11 are arranged, which extend radially from a housing 12 of the gas turbine 1 in the direction of the rotor 7.
  • the invention relates to the designated 26 area and is in the FIGS. 2 and 3 described.
  • FIG. 2 2 shows schematically and by way of example a part of a combustion chamber outer shell 15 according to the prior art facing the turbine section 6 with a section of a guide blade carrier 16.
  • the combustion chamber outer shell 15 is fixed axially on the turbine guide blade carrier 16.
  • the axial fixation is realized by a tongue and groove connection 17.
  • the spring, consisting of ring segments 18, is screwed to the turbine guide vane carrier 16 and engages from outside into the groove 19 located in the combustion chamber outer shell 15. About the fit between groove 19 and spring (ring segments 18), the axial position of the combustion chamber outer shell 15 is secured to the turbine vane support 16.
  • the combustion chamber outer shell 15 When worn, the combustion chamber outer shell 15 loses its axial fixation. As a first measure, the groove 19 of the combustion chamber outer shell 15 is over-turned and modified ring segments are mounted on the distributor 16. This is possible only up to a certain residual thickness of the hook 20.
  • FIG. 3 shows a combustion chamber outer shell 21 according to the invention, in which the turbine vane support 22 facing end side is extended, so that the groove 23 can be widened.
  • the L-ring 24 is inserted into the groove 23 so that a leg 25 is located in the direction of the end face of the combustion chamber outer shell 21.
  • the L-ring 24 is to perform at least two parts for better assembly and disassembly.
  • groove 23 and L-ring 24 are designed as a snug fit and the L-ring 24 is additionally with dowel pins fixed. It can, for example, a U-ring are inserted into the groove 23, which additionally protects the less loaded upstream side of the groove (23) against wear.
  • the turbine vane support 22 is shortened according to the extension of the combustion chamber outer shell 21 compared with an embodiment of the prior art 15 at the appropriate place.

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)
EP10187238A 2010-10-12 2010-10-12 Segment d'usure dans l'accrochage de support d'aube directrice de turbines d'une coque extérieure d'une chambre de combustion annulaire Withdrawn EP2442032A1 (fr)

Priority Applications (1)

Application Number Priority Date Filing Date Title
EP10187238A EP2442032A1 (fr) 2010-10-12 2010-10-12 Segment d'usure dans l'accrochage de support d'aube directrice de turbines d'une coque extérieure d'une chambre de combustion annulaire

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP10187238A EP2442032A1 (fr) 2010-10-12 2010-10-12 Segment d'usure dans l'accrochage de support d'aube directrice de turbines d'une coque extérieure d'une chambre de combustion annulaire

Publications (1)

Publication Number Publication Date
EP2442032A1 true EP2442032A1 (fr) 2012-04-18

Family

ID=43640545

Family Applications (1)

Application Number Title Priority Date Filing Date
EP10187238A Withdrawn EP2442032A1 (fr) 2010-10-12 2010-10-12 Segment d'usure dans l'accrochage de support d'aube directrice de turbines d'une coque extérieure d'une chambre de combustion annulaire

Country Status (1)

Country Link
EP (1) EP2442032A1 (fr)

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2994216A1 (fr) * 2012-08-02 2014-02-07 Snecma Partie de revolution de carter intermediaire comportant un insert dispose dans une rainure annulaire
WO2018080474A1 (fr) * 2016-10-26 2018-05-03 Siemens Aktiengesellschaft Chemise pour un conduit de transition

Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5265412A (en) * 1992-07-28 1993-11-30 General Electric Company Self-accommodating brush seal for gas turbine combustor
US5749218A (en) * 1993-12-17 1998-05-12 General Electric Co. Wear reduction kit for gas turbine combustors
US20030066292A1 (en) * 2001-10-09 2003-04-10 Mack Brian R. Wear reduction means for a gas turbine combustor transition duct end frame
EP1724526A1 (fr) * 2005-05-13 2006-11-22 Siemens Aktiengesellschaft Coquille de turbine à gaz, turbine à gaz et procédé de démarrage et d'arrêt d'une turbine à gaz
GB2432902A (en) * 2005-12-03 2007-06-06 Alstom Technology Ltd A Support for a Gas Turbine Combustion Liner Segment

Patent Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5265412A (en) * 1992-07-28 1993-11-30 General Electric Company Self-accommodating brush seal for gas turbine combustor
US5749218A (en) * 1993-12-17 1998-05-12 General Electric Co. Wear reduction kit for gas turbine combustors
US20030066292A1 (en) * 2001-10-09 2003-04-10 Mack Brian R. Wear reduction means for a gas turbine combustor transition duct end frame
EP1724526A1 (fr) * 2005-05-13 2006-11-22 Siemens Aktiengesellschaft Coquille de turbine à gaz, turbine à gaz et procédé de démarrage et d'arrêt d'une turbine à gaz
GB2432902A (en) * 2005-12-03 2007-06-06 Alstom Technology Ltd A Support for a Gas Turbine Combustion Liner Segment

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2994216A1 (fr) * 2012-08-02 2014-02-07 Snecma Partie de revolution de carter intermediaire comportant un insert dispose dans une rainure annulaire
US9677425B2 (en) 2012-08-02 2017-06-13 Snecma Axisymmetrical intermediate case part including an insert positioned in an annular groove
GB2507842B (en) * 2012-08-02 2019-11-27 Snecma Axisymmetrical Intermediate Case Part Including an Insert positioned in an Annular Groove
WO2018080474A1 (fr) * 2016-10-26 2018-05-03 Siemens Aktiengesellschaft Chemise pour un conduit de transition

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