EP1389714A1 - Chambre à combustion de turbine à gaz - Google Patents

Chambre à combustion de turbine à gaz Download PDF

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Publication number
EP1389714A1
EP1389714A1 EP02018489A EP02018489A EP1389714A1 EP 1389714 A1 EP1389714 A1 EP 1389714A1 EP 02018489 A EP02018489 A EP 02018489A EP 02018489 A EP02018489 A EP 02018489A EP 1389714 A1 EP1389714 A1 EP 1389714A1
Authority
EP
European Patent Office
Prior art keywords
combustion chamber
manhole
manhole cover
gas turbine
wall
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Withdrawn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
EP02018489A
Other languages
German (de)
English (en)
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
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 EP02018489A priority Critical patent/EP1389714A1/fr
Priority to DE50309588T priority patent/DE50309588D1/de
Priority to PCT/EP2003/008548 priority patent/WO2004023042A1/fr
Priority to CNB038188929A priority patent/CN1318805C/zh
Priority to JP2004533306A priority patent/JP4167224B2/ja
Priority to EP03753347A priority patent/EP1529181B1/fr
Priority to US10/524,523 priority patent/US20060037321A1/en
Publication of EP1389714A1 publication Critical patent/EP1389714A1/fr
Withdrawn legal-status Critical Current

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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 that can be closed by a manhole cover as access to a combustion chamber interior.
  • Gas turbines are used to drive generators in many areas or used by work machines.
  • the fuel will To do this, burned in a combustion chamber, using an air compressor compressed air is supplied. That in the combustion chamber generated by the combustion of the fuel, under high Pressure and high temperature working medium is via a turbine unit downstream of the combustion chamber managed where it relaxes while working.
  • An increase in efficiency can basically be used for thermodynamic reasons by increasing the outlet temperature, with which the working medium from the combustion chamber and into the Turbine unit flows. Therefore temperatures of around Desired 1200 ° C to 1300 ° C for such gas turbines and also achieved.
  • the combustion chamber should, for example for inspection purposes, be accessible from the inside.
  • a gas turbine with a combustion chamber at least has a section that has a manhole access is testable.
  • DE 198 09 568 A1 describes a gas turbine known with an annular combustion chamber, one access (Manhole) is provided in the flame chamber through which one Person can get into the flame space.
  • Manhole is provided in the flame chamber through which one Person can get into the flame space.
  • gas turbines with high combustion temperatures from 1,200 ° C to 1,300 ° C
  • to a manhole in the combustion chamber waived, since this is the thermal prevailing there would not withstand loads or at least that could not ensure the tightness of the combustion chamber.
  • the invention has for its object a gas turbine combustion chamber specify that for a gas turbine with particular high combustion temperature is suitable and a simple one Allows entry of one person.
  • this object is achieved by a gas turbine combustion chamber with the features of claim 1 the gas turbine combustor assigns a manhole as an access a combustion chamber interior, which with a manhole cover is closable, this an internal cooling space having.
  • the interior cold room i.e. the cold room inside the Manhole cover, allows targeted cooling of the Manhole cover closing the combustion chamber interior.
  • the Manhole cover is therefore also under high thermal loads usable in the interior of the combustion chamber, without becoming inadmissible Deform extent. A tight seal of the Combustion chamber interior through the manhole cover is in all Operating conditions guaranteed.
  • this is also preferred Combustion chamber wall at least in a thermally special one highly loaded area of the gas turbine combustion chamber, can be cooled internally.
  • the combustion chamber wall has a so-called Wall cold room on.
  • the internal cooling space is preferably of the manhole cover fluidically, for example by means of connecting lines, with the wall cooling room of the Combustion chamber wall connectable. So that are simple on the various components that make up the combustion chamber interior include, especially the manhole cover and this surrounding combustion chamber wall, at least similar thermal Conditions can be created.
  • a fluidic connection between the interior cold room of the manhole cover and the wall cooling chamber of the combustion chamber wall according to a preferred embodiment particularly simple way directly by inserting the manhole cover producible in the manhole. So that is special achievable that the wall cooling chamber of the combustion chamber wall without reducing the cross-section in the inner cooling space of the manhole cover transforms.
  • the entire wall forms the Gas turbine combustor including manhole cover one homogeneous cold room.
  • the manhole cover is or at least one cover part of the manhole cover, for example an inner cover that covers the interior cold room of the manhole cover to the combustion chamber interior, through a fastener to the combustion chamber interior supported out, this fastener at the same time an interior trim element adjacent to the manhole cover stops at the combustion chamber wall.
  • the fastener is a minimization of Number of fasteners in the combustion chamber allows.
  • the fastening element is preferably at least in cross section essentially U-shaped, a first U-leg supports the cover part of the manhole cover and a second U-leg to the interior trim element the combustion chamber wall holds.
  • the entire fastener preferably has the shape of a rail. Through training of the fastener as a U-rail has this both adequate stability and elasticity.
  • the fastening element is preferably such on the combustion chamber wall held that a section, in particular a U-leg, of the fastener protrudes into the manhole and there the inner cover of the manhole cover for Supports combustion chamber interior, and - without loosening the fastener -
  • the manhole cover can be removed from the manhole is.
  • the advantage of the invention is in particular that Manhole cover due to a high thermal indoor cooling Withstands loads, with a very simple weight loss of the manhole cover including its internal cooling space is made possible by the manhole.
  • 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 on.
  • the turbine 6 and the compressor 2 are on a common turbine shaft, also known as a turbine rotor 8 arranged with which the generator or Work machine is connected, and about its central axis 9th is rotatably mounted.
  • the combustion chamber 4 is provided with a number of burners 10 Combustion of a liquid or gaseous fuel. It is still on its inner wall or combustion chamber wall 23 provided with interior trim elements 25.
  • the turbine 6 has a number of with the turbine shaft 8 connected, rotatable blades 12.
  • 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 fixed guide vanes 14, which is also ring-shaped with the formation of Guide vane rows attached to an inner housing 16 of the turbine 6 are.
  • the blades 12 are used to drive the turbine shaft 8 by transfer of momentum from the turbine 6 working medium flowing through M.
  • the guide vanes 14 serve in contrast to the flow of the working medium M between seen two in the flow direction of the working medium M. successive rows of blades or blade rings.
  • a successive pair from a wreath of guide vanes 14 or a row of guide vanes and out a ring of blades 12 or a row of blades is also referred to as the turbine stage.
  • Each guide vane 14 has a vane root 19 which is also designated Platform 18 on which to fix the respective Guide vane 14 on the inner casing 16 of the turbine 6 as a wall element is arranged.
  • the platform 18 is a thermal comparatively heavily loaded component that the outer boundary a hot gas duct for the one flowing through the turbine 6 Working medium M forms.
  • Each blade 12 is in in an analogous manner via a platform 18 Blade root 19 attached to the turbine shaft 8, the Blade root 19 each extends along a blade axis profiled airfoil 20 carries.
  • each guide ring 21 is also hot, flowing through the turbine 6 Working medium M exposed and in the radial direction from the outer end 22 of the blade opposite to it 12 spaced by a gap.
  • the one between neighboring Guide rings 21 arranged guide vane rows serve in particular as cover elements that cover the inner wall 16 or other housing installation parts before a thermal Overuse by the flowing through the turbine 6 protects hot working medium M.
  • the gas turbine 1 for a comparatively high outlet temperature of the working medium emerging from the combustion chamber 4 M designed from about 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 attached to this, the combustion chamber interior 24 surrounding interior trim elements 25 by a wall cooling chamber 26 to the burners 10.
  • This Combustion chamber cooling is the desired at the same time Combustion air heated.
  • FIG. 2 shows sections of the combustion chamber wall in cross section 23 with a manhole 27 in which a manhole cover 28 is inserted.
  • the manhole cover 28 has Lid top part 29, which is comparable to the combustion chamber wall 23 is formed, as well as a lid inner lining 30. Between the upper cover part 29 and the inner cover of the cover 30, which are also referred to as individual cover parts is an internal cooling space 31 of the manhole cover 27 included.
  • Interior trim element 25 includes a wall cooling space 26.
  • the inner cooling space 31 of the manhole cover 27 is with the wall cooling chamber 26 of the combustion chamber wall 23 in such a way connected that the combustion air unhindered, vertical to the level shown, can flow.
  • the upper lid part 29 has a projection 33 on its edge with which this fits into a corresponding holding recess 34 of the combustion chamber wall 23 can be used.
  • the manhole cover 28 has a rectangular basic shape.
  • the Lid top part 29 and the combustion chamber wall 23 are in the area the connection between these two components, i.e. in the area of the projection 33 or the holding recess 34 for Increased stability to the combustion chamber interior 24 thickened educated.
  • this has a contact surface 36, on which the lid inner lining 30 with an inner lining edge 37 rests.
  • the inner trim edge 37 is adjoining an inner lining main surface 38, in one piece trained with this and bent from this.
  • a reinforced surface rests on a contact surface 39 or thickened area 40 of the combustion chamber wall 23 a trim edge 41 of the interior trim element 25 on.
  • the manhole cover 28 becomes the combustion chamber outer side 42 supported by a fastening device, not shown. Both the cover inner lining 30 and the inner lining element 25 become the combustion chamber interior 24 through a fastening element designed as a U-rail 43 supported.
  • a first U-leg 44 is on Inner trim edge 37 of the manhole cover 27 and a second U-leg 45 on the trim edge 41 of the interior trim element 31 at.
  • the U-legs 44,45 are also called Parts of the fastener 43 designated.
  • the fasteners 43 are with Screws 46, which in the reinforced area 40 of the combustion chamber wall 23 intervene, held on this.
  • the screws 46 are from the combustion chamber interior 24 into the Combustion chamber wall 23 screwed in. An additional attachment of the interior trim element 31 on the reinforced area 40 is not required. That with the screws 46 the combustion chamber wall 23 held U-shaped fastening element 43 is sufficient for both the interior trim element 25 to hold on the combustion chamber wall 23 as well Support inner cover 30 to the combustion chamber interior 24.
  • the linings, also known as liners 25, 30 are sealed by the fastening element 43. Escape of cooling air in the area of the fastener 43 is excluded. So much for the interior trim edge 37 or at the edge of the panel 41 cooling air from the wall cold room 26 or the interior cooling space 31 emerge would, this leaked cooling air would be through the U-shaped Fastener 43 prevented from entering the combustion chamber interior 24 pour in. In contrast, this can be done through the U-shaped Fastener 43 retained cooling air unhindered along the fastening element designed as a rail 43 flow to the burners 10.
  • Removing the fastener 43 or loosening the Screws 46 is for removing the manhole cover 27 from Manhole 27 not required. This is made possible by the Interlocking configuration with which the fasteners 43 the interior trim elements 25 and the lid interior trim Support 30 to the combustion chamber interior 24.
  • the Fastening element 43 bridges the manhole cover 28 closed combustion chamber 4 the space between the Inner trim edge 37 of the manhole cover 27 and the trim edge 41 of the interior trim element 31, so that the hot working medium M does not come from the combustion chamber interior 24 from the combustion chamber wall 23 or the lid upper part 29 arrives.
  • the combustion chamber 4 is thus including the manhole cover 28 fully lined.

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)
EP02018489A 2002-08-16 2002-08-16 Chambre à combustion de turbine à gaz Withdrawn EP1389714A1 (fr)

Priority Applications (7)

Application Number Priority Date Filing Date Title
EP02018489A EP1389714A1 (fr) 2002-08-16 2002-08-16 Chambre à combustion de turbine à gaz
DE50309588T DE50309588D1 (de) 2002-08-16 2003-08-01 Gasturbinenbrennkammer
PCT/EP2003/008548 WO2004023042A1 (fr) 2002-08-16 2003-08-01 Chambre de combustion de turbine a gaz
CNB038188929A CN1318805C (zh) 2002-08-16 2003-08-01 燃气轮机燃烧室
JP2004533306A JP4167224B2 (ja) 2002-08-16 2003-08-01 ガスタービン用燃焼室
EP03753347A EP1529181B1 (fr) 2002-08-16 2003-08-01 Chambre de combustion de turbine a gaz
US10/524,523 US20060037321A1 (en) 2002-08-16 2003-08-01 Gas turbine combustion chamber

Applications Claiming Priority (1)

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

Publications (1)

Publication Number Publication Date
EP1389714A1 true EP1389714A1 (fr) 2004-02-18

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 After (1)

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

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2549188A3 (fr) * 2011-07-21 2015-05-13 United Technologies Corporation Insert pour chambre à combustion de moteur à turbine à gaz

Families Citing this family (4)

* 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
CN107003000B (zh) * 2014-09-29 2019-09-24 西门子股份公司 用于燃烧室的隔热罩的隔热元件

Citations (7)

* 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
US5333443A (en) * 1993-02-08 1994-08-02 General Electric Company Seal assembly
US5624256A (en) * 1995-01-28 1997-04-29 Abb Management Ag Ceramic lining for combustion chambers
DE19809568A1 (de) 1998-03-05 1999-08-19 Siemens Ag Ringbrennkammer, Verwendung einer Ringbrennkammer und Einsatz für eine Öffnung in einer Brennkammer
DE19924607A1 (de) 1999-05-28 2000-11-30 Siemens Ag Inspektionsvorrichtung für eine Ringbrennkammer einer Gasturbine und Verfahren zur Inspektion einer Ringbrennkammer einer Gasturbine
US6415724B1 (en) * 1999-01-01 2002-07-09 The Babcock & Wilcox Company Water-jacketed, high-temperature, stretcher-accessible door for a boiler

Family Cites Families (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
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
US5782294A (en) * 1995-12-18 1998-07-21 United Technologies Corporation Cooled liner apparatus

Patent Citations (7)

* 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
US5333443A (en) * 1993-02-08 1994-08-02 General Electric Company Seal assembly
US5624256A (en) * 1995-01-28 1997-04-29 Abb Management Ag Ceramic lining for combustion chambers
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

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2549188A3 (fr) * 2011-07-21 2015-05-13 United Technologies Corporation Insert pour chambre à combustion de moteur à 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

Also Published As

Publication number Publication date
JP4167224B2 (ja) 2008-10-15
CN1675502A (zh) 2005-09-28
US20060037321A1 (en) 2006-02-23
EP1529181B1 (fr) 2008-04-09
WO2004023042A1 (fr) 2004-03-18
EP1529181A1 (fr) 2005-05-11
CN1318805C (zh) 2007-05-30
JP2005535867A (ja) 2005-11-24
DE50309588D1 (de) 2008-05-21

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