EP1529181A1 - Chambre de combustion de turbine a gaz - Google Patents

Chambre de combustion de turbine a gaz

Info

Publication number
EP1529181A1
EP1529181A1 EP03753347A EP03753347A EP1529181A1 EP 1529181 A1 EP1529181 A1 EP 1529181A1 EP 03753347 A EP03753347 A EP 03753347A EP 03753347 A EP03753347 A EP 03753347A EP 1529181 A1 EP1529181 A1 EP 1529181A1
Authority
EP
European Patent Office
Prior art keywords
combustion chamber
manhole
manhole cover
gas turbine
cover
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
EP03753347A
Other languages
German (de)
English (en)
Other versions
EP1529181B1 (fr
Inventor
Peter Tiemann
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
Siemens Corp
Original Assignee
Siemens AG
Siemens Corp
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, Siemens Corp filed Critical Siemens AG
Priority to EP03753347A priority Critical patent/EP1529181B1/fr
Publication of EP1529181A1 publication Critical patent/EP1529181A1/fr
Application granted granted Critical
Publication of EP1529181B1 publication Critical patent/EP1529181B1/fr
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

Links

Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23M—CASINGS, LININGS, WALLS OR DOORS SPECIALLY ADAPTED FOR COMBUSTION CHAMBERS, e.g. FIREBRIDGES; DEVICES FOR DEFLECTING AIR, FLAMES OR COMBUSTION PRODUCTS IN COMBUSTION CHAMBERS; SAFETY ARRANGEMENTS SPECIALLY ADAPTED FOR COMBUSTION APPARATUS; DETAILS OF COMBUSTION CHAMBERS, NOT OTHERWISE PROVIDED FOR
    • F23M7/00—Doors
    • F23M7/04—Cooling doors or door frames
    • 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
    • F23R3/005—Combined with pressure or heat exchangers

Definitions

  • the invention relates to a gas turbine combustion chamber with a manhole which can be closed by a manhole cover as access to a combustion chamber interior.
  • Gas turbines are used in many areas to drive generators or work machines.
  • the energy content of a fuel is used to generate a rotational movement of a turbine shaft.
  • the fuel is burned in a combustion chamber, compressed air being supplied by an air compressor.
  • the working medium generated in the combustion chamber by the combustion of the fuel which is under high pressure and at high temperature, is guided over a turbine unit downstream of the combustion chamber, where it relaxes while performing work.
  • a combustion chamber exposed to these temperatures during operation of the gas turbine should be accessible from the inside, for example for inspection purposes.
  • a gas turbine with a combustion chamber is known, which has at least a partial area that can be checked via a manhole access.
  • a gas turbine with an annular combustion chamber is known from DE 198 09 568 AI, with an access
  • Manhole is provided in the flame chamber through which a person can get into the flame chamber.
  • gas turbines with high combustion temperatures of 1,200 ° C to 1,300 ° C
  • there is no manhole in the combustion chamber since this would not be able to withstand the thermal loads there or could at least not guarantee the tightness of the combustion chamber.
  • liners In order to allow a person to enter the combustion chamber, extremely complex dismantling work is required.
  • the invention is based on the object of specifying a gas turbine combustion chamber which is suitable for a gas turbine with a particularly high combustion temperature and which enables a person to get started easily.
  • the gas turbine combustion chamber has a manhole as an access to a combustion chamber interior, which can be closed with a Mannloc lid, the latter having an internal cooling space.
  • the interior cold room, i.e. the cooling space inside the manhole cover enables targeted cooling of the manhole cover that closes the combustion chamber interior.
  • the manhole cover can therefore also be used under high thermal loads in the combustion chamber interior, without deforming to an unacceptable extent. A tight seal of the combustion chamber interior through the manhole cover is guaranteed in all operating conditions.
  • Combustion chamber wall at least in an area of the gas turbine combustion chamber which is particularly thermally highly stressed, can be cooled internally.
  • the combustion chamber wall has a so-called wall cooling room.
  • the inner cooling space of the manhole cover can preferably be connected to the wall cooling space of the combustion chamber wall in terms of flow technology, for example by means of connecting lines. So that is simple at least similar thermal conditions can be produced on the various components that enclose the combustion chamber interior, in particular the manhole cover and the combustion chamber wall surrounding it.
  • a fluidic connection between the inner cooling space of the manhole cover and the wall cooling space of the combustion chamber wall can be established in a particularly simple manner by inserting the manhole cover into the manhole in a particularly simple manner. In this way it can be achieved in particular that the wall cooling space of the combustion chamber wall merges into the inner cooling space of the manhole cover without a reduction in cross section.
  • the entire wall of the gas turbine combustion chamber, including the manhole cover, preferably forms a homogeneous cooling space.
  • the manhole cover or at least one individual lid part of the manhole cover for example a cover inside the cover, which closes off the inner cooling space of the manhole cover from the combustion chamber interior, is supported by a fastening element towards the combustion chamber interior, this fastening element also affixing an interior trim element adjacent to the manhole cover the combustion chamber wall holds.
  • This multiple function of the fastening element enables the number of fastening elements in the combustion chamber to be minimized.
  • the fastening element is preferably at least essentially U-shaped in cross section, a first one
  • U-leg supports the lid part of the manhole cover and a second U-leg holds the interior trim element on the combustion chamber wall.
  • the entire fastening element preferably has the shape of a rail. Due to the design of the fastening element as a U-rail, it has both sufficient stability and elasticity.
  • the fastening element is preferably held on the combustion chamber wall in such a way that a section, in particular a U-leg, of the fastening element projects into the manhole and supports the inner cover of the manhole cover towards the combustion chamber interior, and - without loosening the fastening element - the manhole cover can be removed from the manhole ,
  • This has the advantage that all the fastening elements that hold both the inner lining element and the inner lid lining on the combustion chamber wall or the manhole cover only have to be fastened once and entry into the gas turbine combustion chamber is possible through the manhole without removing one of these fastening elements.
  • the advantage of the invention is, in particular, that the manhole cover withstands high thermal loads due to an internal cooling space, wherein a very simple removal of the manhole cover including its inner cooling space is made possible from the manhole.
  • FIG. 1 shows a half section through a gas turbine
  • FIG. 2 shows sections of the gas turbine combustion chamber of the gas turbine according to FIG. 1 in cross section.
  • the gas turbine 1 has a compressor 2 for combustion air, a combustion chamber or gas turbine combustion chamber 4 and a turbine 6 for driving the compressor 2 and a generator (not shown) or a work machine.
  • the turbine 6 and the compressor 2 are arranged on a common turbine shaft 8, also referred to as a turbine rotor, with which the generator or the Machine is connected, and which is rotatably mounted about its central axis 9.
  • the combustion chamber 4 is equipped with a number of burners 10 for burning a liquid or gaseous fuel. It is also provided on its inner wall or combustion chamber wall 23 with inner lining elements 25.
  • the turbine 6 has a number of rotatable rotor blades 12 connected to the turbine shaft 8.
  • the blades 12 are arranged in a ring shape on the turbine shaft 8 and thus form a number of rows of blades.
  • the turbine 6 comprises a number of stationary guide vanes 14, which are also attached to an inner casing 16 of the turbine 6 in a ring shape, with the formation of rows of guide vanes.
  • the blades 12 serve to drive the turbine shaft 8 by means of impulse transmission from the working medium M flowing through the turbine 6.
  • the guide vanes 14, serve to guide the flow of the working medium M between two successive rows of blades or rotor blades as seen in the flow direction of the working medium M.
  • a successive pair of a ring of guide blades 14 or a row of guide blades and a ring of blades 12 or a row of rotor blades is also referred to as a turbine stage.
  • Each guide vane 14 has a platform 18, also referred to as a blade root 19, which is arranged as a wall element for fixing the respective guide vane 14 to the inner housing 16 of the turbine 6.
  • the platform 18 is a thermally comparatively heavily loaded component that forms the outer boundary of a hot gas channel for the working medium M flowing through the turbine 6.
  • Each rotor blade 12 is fastened in an analogous manner to the turbine shaft 8 by means of a blade root 19, also referred to as platform 18, the blade root 19 each carrying a profiled blade 20 extending along a blade axis.
  • a guide ring 21 is arranged on the inner casing 16 of the turbine 6 between the spaced-apart platforms 18 of the guide vanes 14 of two adjacent rows of guide vanes.
  • each guide ring 21 is also exposed to the hot working medium M flowing through the turbine 6 and is spaced in the radial direction from the outer end 22 of the rotor blade 12 lying opposite it by a gap.
  • the guide rings 21 arranged between adjacent rows of guide vanes serve in particular as cover elements which protect the inner wall 16 or other housing installation parts against thermal overloading by the hot working medium M flowing through the turbine 6.
  • the gas turbine 1 is designed for a comparatively high outlet temperature of the working medium M emerging from the combustion chamber 4 of approximately 1200 ° C. to 1300 ° C.
  • the combustion chamber wall 23 is internally cooled.
  • combustion air flows in counterflow to the working medium M, i.e. the combustion gases, between the combustion chamber wall 23 and the inner lining elements 25 attached to it and surrounding the combustion chamber interior 24 through a wall cooling space 26 to the burners 10.
  • the combustion air is simultaneously and intentionally heated by this combustion chamber cooling.
  • the manhole cover 28 has an upper cover part 29, which is designed comparable to the combustion chamber wall 23, and an inner cover 30. Between the upper cover part 29 and the inner cover 30, which are also referred to as individual cover parts, an internal cooling space 31 of the cover hole 27 is enclosed. In a corresponding way, see the combustion chamber wall 23 and a wall cladding element 25 fastened to this enclosed a wall cooling space 26.
  • the inner cooling space 31 of the manhole cover 27 is connected to the wall cooling space 26 of the combustion chamber wall 23 in such a way that the combustion air can flow freely, perpendicular to the plane shown.
  • the upper lid part 29 has a projection 33 on its edge, with which it can be inserted into a corresponding holding recess 34 in the combustion chamber wall 23.
  • the manhole cover 28 has an overall rectangular shape.
  • the top cover part 29 and the combustion chamber wall 23 are in the area of the connection between these two components, i.e. in the region of the projection 33 or the holding recess 34 to increase the stability towards the combustion chamber interior 24.
  • this has an abutment surface 36, on which the cover inner lining 30 rests with an inner lining edge 37.
  • the inner lining edge 37 is, following an inner lining main surface 38, formed in one piece with it and bent from it.
  • a cladding edge 41 of the interior cladding element 25 bears against a contact surface 39 of a reinforced or thickened area 40 of the combustion chamber wall 23.
  • the manhole cover 28 is supported towards the combustion chamber outside 42 by a fastening device, not shown. Both the cover inner lining 30 and the inner lining element 25 are supported towards the combustion chamber interior 24 by a fastening element 43 designed as a U-rail.
  • a first U-leg 44 abuts the interior trim edge 37 of the manhole cover 27 and a second U-leg 45 abuts the trim edge 41 of the interior trim element 31.
  • the U-legs 44, 45 are also referred to as sections of the fastening element 43.
  • the fastening elements 43 are held on the latter by screws 46 which engage in the reinforced area 40 of the combustion chamber wall 23.
  • the screws 46 are screwed into the combustion chamber wall 23 from the combustion chamber interior 24. An additional fastening of the interior trim element 31 to the reinforced area 40 is not necessary.
  • the U-shaped fastening element 43 held with the screws 46 on the combustion chamber wall 23 is sufficient both to hold the inner lining element 25 on the combustion chamber wall 23 and to support the inner cover lining 30 towards the combustion chamber interior 24.
  • the linings 25, 30 also referred to as liners are sealed by the fastening element 43. A escape of cooling air in the area of the fastening element 43 is excluded.

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Incineration Of Waste (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Heat-Exchange Devices With Radiators And Conduit Assemblies (AREA)
  • Air Supply (AREA)

Abstract

La présente invention concerne une chambre de combustion de turbine à gaz (4) qui présente un trou d'homme (27) qui peut être refermé par un couvercle (28) et permet l'accès à l'espace intérieur (24) de la chambre de combustion. Le trou d'homme (27) présente une chambre de refroidissement interne (31) et peut grâce à celle-ci résister à des charges thermiques particulièrement élevées.
EP03753347A 2002-08-16 2003-08-01 Chambre de combustion de turbine a gaz Expired - Lifetime EP1529181B1 (fr)

Priority Applications (1)

Application Number Priority Date Filing Date Title
EP03753347A EP1529181B1 (fr) 2002-08-16 2003-08-01 Chambre de combustion de turbine a gaz

Applications Claiming Priority (4)

Application Number Priority Date Filing Date Title
EP02018489 2002-08-16
EP02018489A EP1389714A1 (fr) 2002-08-16 2002-08-16 Chambre à combustion de turbine à gaz
PCT/EP2003/008548 WO2004023042A1 (fr) 2002-08-16 2003-08-01 Chambre de combustion de turbine a gaz
EP03753347A EP1529181B1 (fr) 2002-08-16 2003-08-01 Chambre de combustion de turbine a gaz

Publications (2)

Publication Number Publication Date
EP1529181A1 true EP1529181A1 (fr) 2005-05-11
EP1529181B1 EP1529181B1 (fr) 2008-04-09

Family

ID=30470278

Family Applications (2)

Application Number Title Priority Date Filing Date
EP02018489A Withdrawn EP1389714A1 (fr) 2002-08-16 2002-08-16 Chambre à combustion de turbine à gaz
EP03753347A Expired - Lifetime EP1529181B1 (fr) 2002-08-16 2003-08-01 Chambre de combustion de turbine a gaz

Family Applications Before (1)

Application Number Title Priority Date Filing Date
EP02018489A Withdrawn EP1389714A1 (fr) 2002-08-16 2002-08-16 Chambre à combustion de turbine à gaz

Country Status (6)

Country Link
US (1) US20060037321A1 (fr)
EP (2) EP1389714A1 (fr)
JP (1) JP4167224B2 (fr)
CN (1) CN1318805C (fr)
DE (1) DE50309588D1 (fr)
WO (1) WO2004023042A1 (fr)

Families Citing this family (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1398569A1 (fr) * 2002-09-13 2004-03-17 Siemens Aktiengesellschaft Turbine à gaz
EP1862740B1 (fr) * 2006-05-31 2015-09-16 Siemens Aktiengesellschaft Paroi de chambre de combustion
EP2426321A1 (fr) 2010-09-03 2012-03-07 Siemens Aktiengesellschaft Boîtier pour une turbine à gaz
US9534783B2 (en) * 2011-07-21 2017-01-03 United Technologies Corporation Insert adjacent to a heat shield element for a gas turbine engine combustor
EP3134680B1 (fr) * 2014-09-29 2018-07-04 Siemens Aktiengesellschaft Élément de bouclier thermique pour bouclier thermique d'une chambre de combustion

Family Cites Families (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB626249A (en) * 1946-05-23 1949-07-12 Babcock & Wilcox Ltd Improvements in or relating to closure means for openings in walls of chambers arranged to contain gas under pressure
US4480436A (en) * 1972-12-19 1984-11-06 General Electric Company Combustion chamber construction
US3978662A (en) * 1975-04-28 1976-09-07 General Electric Company Cooling ring construction for combustion chambers
US4189352A (en) * 1975-08-14 1980-02-19 Krupp-Koppers, Gmbh Coke oven door
US5333443A (en) * 1993-02-08 1994-08-02 General Electric Company Seal assembly
DE19502730A1 (de) * 1995-01-28 1996-08-01 Abb Management Ag Keramische Auskleidung
US5782294A (en) * 1995-12-18 1998-07-21 United Technologies Corporation Cooled liner apparatus
DE19809568A1 (de) 1998-03-05 1999-08-19 Siemens Ag Ringbrennkammer, Verwendung einer Ringbrennkammer und Einsatz für eine Öffnung in einer Brennkammer
US6415724B1 (en) * 1999-01-01 2002-07-09 The Babcock & Wilcox Company Water-jacketed, high-temperature, stretcher-accessible door for a boiler
DE19924607A1 (de) 1999-05-28 2000-11-30 Siemens Ag Inspektionsvorrichtung für eine Ringbrennkammer einer Gasturbine und Verfahren zur Inspektion einer Ringbrennkammer einer Gasturbine

Non-Patent Citations (1)

* Cited by examiner, † Cited by third party
Title
See references of WO2004023042A1 *

Also Published As

Publication number Publication date
US20060037321A1 (en) 2006-02-23
CN1675502A (zh) 2005-09-28
CN1318805C (zh) 2007-05-30
WO2004023042A1 (fr) 2004-03-18
EP1389714A1 (fr) 2004-02-18
JP4167224B2 (ja) 2008-10-15
EP1529181B1 (fr) 2008-04-09
DE50309588D1 (de) 2008-05-21
JP2005535867A (ja) 2005-11-24

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