EP1429077A1 - Turbine à gaz - Google Patents

Turbine à gaz Download PDF

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Publication number
EP1429077A1
EP1429077A1 EP02027495A EP02027495A EP1429077A1 EP 1429077 A1 EP1429077 A1 EP 1429077A1 EP 02027495 A EP02027495 A EP 02027495A EP 02027495 A EP02027495 A EP 02027495A EP 1429077 A1 EP1429077 A1 EP 1429077A1
Authority
EP
European Patent Office
Prior art keywords
combustion chamber
wall
turbine
gas turbine
annular
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
EP02027495A
Other languages
German (de)
English (en)
Other versions
EP1429077B1 (fr
Inventor
Wilhelm Schulten
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 DE50212581T priority Critical patent/DE50212581D1/de
Priority to EP02027495A priority patent/EP1429077B1/fr
Priority to ES02027495T priority patent/ES2307704T3/es
Priority to US10/719,958 priority patent/US7007489B2/en
Priority to CNB2003101188611A priority patent/CN1320313C/zh
Priority to JP2003404199A priority patent/JP2004191041A/ja
Publication of EP1429077A1 publication Critical patent/EP1429077A1/fr
Application granted granted Critical
Publication of EP1429077B1 publication Critical patent/EP1429077B1/fr
Anticipated expiration legal-status Critical
Expired - Lifetime 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
    • F23R3/005—Combined with pressure or heat exchangers
    • 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
    • F23R3/50—Combustion chambers comprising an annular flame tube within an annular casing
    • 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

Definitions

  • the invention relates to a gas turbine with a Annular combustion chamber, the combustion chamber of an annular outer wall on the one hand and an annular one arranged therein Inner wall on the other hand is limited.
  • Gas turbines are used to drive generators in many areas or used by work machines.
  • the fuel will burned in a number of burners, one of them Air compressor compressed air is supplied. Through the Combustion of the fuel becomes a high pressure one Working medium generated at a high temperature.
  • This Working medium is placed in a burner downstream of the respective burner Turbine unit guided where it is working relaxed.
  • Each burner can have a separate combustion chamber be assigned, the one flowing out of the combustion chambers Working medium merged before or in the turbine unit can be.
  • the gas turbine can also be in a so-called annular combustion chamber design to be carried out in the a plurality, especially all, of the burners in a common, usually annular, combustion chamber open.
  • 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 1500 ° C for such gas turbines and also achieved.
  • the combustion chamber in the direction of flow of the working medium subsequent turbine unit usually comprises a turbine shaft with a number of rotatable ones Blades is connected to the ring-shaped rows of blades form.
  • the turbine unit further comprises a number of fixed guide vanes, which are also ring-shaped forming vane rows on the inner casing the turbine are attached.
  • the blades serve thereby to drive the turbine shaft by pulse transmission of the working medium flowing through the turbine unit while the guide vanes for the flow guidance of the working medium between two in the flow direction of the working medium seen successive rows of blades or blade rings serve.
  • the combustion chamber is on the one hand of an annular outer wall and an annular inner wall disposed therein on the other hand limited.
  • the inner wall of the combustion chamber is there usually from two or more individual parts on their side facing the turbine shaft are screwed.
  • this structure of the annular combustion chamber has some disadvantages on, because the inner wall of the combustion chamber for maintenance is not accessible. So for maintenance work on the inner wall the upper parts of the compressor and turbine blade carriers be dismantled so that the turbine shaft with the inner wall of the combustion chamber can thus be removed to allow access to said inner wall.
  • the assembly work are therefore very labor and time consuming.
  • the invention is therefore based on the object of a gas turbine of the type mentioned above, in which the inner wall the combustion chamber can be removed comparatively quickly and easily is.
  • the inner wall the combustion chamber from a number of to one Support structure of the inner wall fastened wall elements formed is, the support structure of a number of on a horizontal Joint formed abutting sections is sloping in the area of the parting line over a number of screw connections aligned with the inner wall surface are connected.
  • the change elements in particular form the hot gas wetted Surface of the combustion chamber, the changing elements expediently on the actual supporting structure of the inner wall are attached.
  • This support structure includes in particular also an upper and a lower half that over the screw connections aligned at an angle to the part joining plane are interconnected.
  • the invention is based on the consideration that the attachment of the various wall elements of the combustion chamber inner wall be accessible to each other from the combustion chamber should and the combustion chamber inner wall also from this to be dismantled.
  • the different Portions of the inner wall of the combustion chamber Load-bearing structure that meet at their horizontal parting line, be connected to each other by a fastening, which are joined together by a vertical force on the joint combines.
  • These two functions are supported by the Screw connections aligned at an angle to the inner wall surface met, in addition to accessibility from the combustion chamber a sufficiently large vertical force component for connection of the two supporting structure halves.
  • Screw connection is expediently assigned a feather key.
  • the feather key prevents the screwed together Wall elements on the horizontal parting line the horizontal force component of the screw connection to each other move.
  • the feather key advantageously runs for this along the horizontal parting line and is in each case Grooves of the adjoining wall elements are precisely fitted, so that they don't move against each other can, and preferably only those for attachment the vertical force component of the screw connection Screw connection occurs on the horizontal parting line.
  • the annular combustion chamber advantageously carried out in two parts and a lower part cooperating with an upper part educated.
  • the upper part is expedient screwed to the lower part so that the combustion chamber outer wall can be removed.
  • the combustion chamber outer wall is the combustion chamber interior and therefore the screw connections of the combustion chamber inner wall elements are also accessible.
  • the inside and outside wall of the Combustion chamber expediently with one of a number of Provide heat shield elements formed lining. This are preferably with particularly heat-resistant protective layers Mistake.
  • the heat shield elements are advantageously via a system with tongue and groove on the inner wall and on the outer wall attached to the combustion chamber.
  • Heat shield elements are on their edges preferably shaped in such a way that they pass through form a double bend towards the combustion chamber, which are in a recess in the combustion chamber wall, which forms the groove, anchor it and fasten it with it.
  • the recess in the combustion chamber wall is expedient summarized for adjacent heat shield elements, so that adjacent heat shield elements on their butt against each other due to the bend and so a seal for the combustion chamber and the inside represent flowing working medium.
  • the gas turbine 1 has a compressor 2 for Combustion air, a combustion chamber 4 and a turbine 6 for Drive the compressor 2 and a generator, not shown or a work machine.
  • a compressor 2 for Combustion air
  • a combustion chamber 4 for Drive the compressor 2 and a generator, not shown or a work machine.
  • the turbine 6 and the compressor 2 on a common, also called Turbine rotor designated turbine shaft 8 arranged with which also connects the generator or the working machine is, and which is rotatably mounted about its central axis 9.
  • the Combustion chamber 4 designed in the manner of an annular combustion chamber is with a number of burners 10 for burning one liquid or gaseous fuel.
  • 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 serve 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 from one Wreath of blades 12 or a row of blades is also referred to as the turbine stage.
  • Each guide vane 14 has one which is also referred to as a blade root Platform 18, which is used to fix the respective guide vane 14 on the inner housing 16 of the turbine 6 as a wall element is arranged.
  • the platform 18 is a thermal comparison heavily loaded component that the outer boundary a heating gas channel for the one flowing through the turbine 6 Working medium M forms.
  • Each blade 12 is analog Way over a platform 20 also referred to as a blade root attached to the turbine shaft 8.
  • 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 combustion chamber 4 is so-called in the exemplary embodiment Annular combustion chamber designed in which a variety of in Arranged circumferentially around the turbine shaft 8 Burners 10 open into a common combustion chamber space. To is the combustion chamber 4 in its entirety as an annular Designed structure that positioned around the turbine shaft 8 is.
  • the combustion chamber 4 is shown in section, the continues like a torus around the turbine shaft 8. How can be seen in the illustration, the combustion chamber 4 has a Beginning or inflow section, in the end of the Outlet of the respectively assigned burner 10 opens. In the direction of flow seen of the working medium M then narrows the cross-section of the combustion chamber 4, the adjoining Flow profile of the working medium M in this Space area is taken into account.
  • the Combustion chamber 4 On the output side, the Combustion chamber 4 has a curvature in longitudinal section through which the outflow of the working medium M from the combustion chamber 4 in one for a particularly high impulse and energy transfer to the first row of moving blades as seen on the flow side is favored.
  • the Combustion chamber 24 of combustion chamber 4 on the one hand, from the annular one Combustion chamber outer wall 26 and, on the other hand, from one therein arranged annular combustion chamber inner wall 28 limited.
  • the combustion chamber 4 is designed for the combustion chamber inner wall 28 for example for maintenance work on special can be easily removed without the turbine shaft 8 and the upper part of the directly adjoining the combustion chamber 4 To remove guide vanes 14 of the turbine 6.
  • the combustion chamber inner wall 28 consists of a number of wall elements on two sections 30 one Support structure are attached, the sections 30 under Formation of an essentially horizontal parting line 31 are joined to the combustion chamber inner wall 28.
  • the combustion chamber 4 is designed in particular for the wall elements and the sections 30 of the combustion chamber inner wall carrying these 28 to be able to disassemble from the combustion chamber 24.
  • the sections 30 on the horizontal formed by them Partition 31 with oblique to the inner surface of the combustion chamber inner wall 28 extending screw connections 32 connected.
  • each Screw connection 32 essentially comprises one obliquely to the surface formed by the combustion chamber inner wall 28 guided screw 33 with one in one of the wall elements 30 incorporated thread 34 cooperates.
  • a key 35 is assigned to the screw connection 32. This runs in a position close to the respective screw connection 32 along the horizontal parting line 31 of the sections 30 and is in grooves of the sections 30 of Combustion chamber inner wall 28 fitted.
  • the combustion chamber outer wall 26 consists of an upper part 36 and a lower part 38, as can be seen in FIG. 3.
  • the upper part 36 and the lower part 38 are in contrast to the Connection of sections 30 of combustion chamber inner wall 28 supporting structure with perpendicular to the partial joining plane Provide screw connections as there are no problems here in terms of accessibility.
  • the combustion chamber 4 for a comparatively high temperature of the working medium M from about 1200 ° C to 1300 ° C.
  • This also applies to these operating parameters, which are unfavorable for the materials to enable a comparatively long operating time are, as shown in Figure 5, the combustion chamber outer wall 26 and the combustion chamber inner wall 28 each their side facing the working medium M with one Heat shield elements 40 provided lining.
  • each The heat shield element 40 is the one facing the working medium M.
  • heat shield elements 40 are via a system fixed with tongue and groove on the combustion chamber inner wall 28.
  • heat shield elements 40 are of such a type on their edges shaped that by a double bend towards the combustion chamber form an anchor that is in a recess the combustion chamber inner wall 28, which forms the groove, anchor it and fix it with it.
  • FIG. 5 shows neighboring heat shield elements 40 attached to combined grooves so that they are mutually touch and so the combustion chamber 24 of the combustion chamber 4th caulk.

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)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Portable Nailing Machines And Staplers (AREA)
EP02027495A 2002-12-10 2002-12-10 Turbine à gaz Expired - Lifetime EP1429077B1 (fr)

Priority Applications (6)

Application Number Priority Date Filing Date Title
DE50212581T DE50212581D1 (de) 2002-12-10 2002-12-10 Gasturbine
EP02027495A EP1429077B1 (fr) 2002-12-10 2002-12-10 Turbine à gaz
ES02027495T ES2307704T3 (es) 2002-12-10 2002-12-10 Turbina de gas.
US10/719,958 US7007489B2 (en) 2002-12-10 2003-11-21 Gas turbine
CNB2003101188611A CN1320313C (zh) 2002-12-10 2003-12-01 燃气轮机
JP2003404199A JP2004191041A (ja) 2002-12-10 2003-12-03 ガスタービン

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP02027495A EP1429077B1 (fr) 2002-12-10 2002-12-10 Turbine à gaz

Publications (2)

Publication Number Publication Date
EP1429077A1 true EP1429077A1 (fr) 2004-06-16
EP1429077B1 EP1429077B1 (fr) 2008-07-30

Family

ID=32319565

Family Applications (1)

Application Number Title Priority Date Filing Date
EP02027495A Expired - Lifetime EP1429077B1 (fr) 2002-12-10 2002-12-10 Turbine à gaz

Country Status (6)

Country Link
US (1) US7007489B2 (fr)
EP (1) EP1429077B1 (fr)
JP (1) JP2004191041A (fr)
CN (1) CN1320313C (fr)
DE (1) DE50212581D1 (fr)
ES (1) ES2307704T3 (fr)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1707758A1 (fr) * 2005-03-23 2006-10-04 Siemens Aktiengesellschaft Elément de coque pour chambre combustion et chambre combustion

Families Citing this family (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1443275B1 (fr) * 2003-01-29 2008-08-13 Siemens Aktiengesellschaft Chambre de combustion
WO2008017550A1 (fr) * 2006-08-07 2008-02-14 Alstom Technology Ltd Chambre de combustion d'une installation de combustion
EP2049841B1 (fr) * 2006-08-07 2016-12-28 General Electric Technology GmbH Chambre de combustion d'une installation d'incinération
FR2911669B1 (fr) * 2007-01-23 2011-09-16 Snecma Carenage pour chambre de combustion, chambre de combustion en etant equipee et turboreacteur les comportant.
JP4850105B2 (ja) * 2007-03-23 2012-01-11 日立オートモティブシステムズ株式会社 熱式流量計
US11694876B2 (en) 2021-12-08 2023-07-04 Applied Materials, Inc. Apparatus and method for delivering a plurality of waveform signals during plasma processing

Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4158949A (en) * 1977-11-25 1979-06-26 General Motors Corporation Segmented annular combustor
DE4114768A1 (de) * 1990-05-17 1991-11-21 Siemens Ag Keramischer hitzeschild fuer eine heissgasfuehrende struktur
DE19643715A1 (de) * 1996-10-23 1998-04-30 Asea Brown Boveri Gekühltes Flammrohr für eine Brennkammer
DE19809568A1 (de) * 1998-03-05 1999-08-19 Siemens Ag Ringbrennkammer, Verwendung einer Ringbrennkammer und Einsatz für eine Öffnung in einer Brennkammer

Family Cites Families (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE58908665D1 (de) * 1988-06-13 1995-01-05 Siemens Ag Hitzeschildanordnung mit geringem kühlfluidbedarf.

Patent Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4158949A (en) * 1977-11-25 1979-06-26 General Motors Corporation Segmented annular combustor
DE4114768A1 (de) * 1990-05-17 1991-11-21 Siemens Ag Keramischer hitzeschild fuer eine heissgasfuehrende struktur
DE19643715A1 (de) * 1996-10-23 1998-04-30 Asea Brown Boveri Gekühltes Flammrohr für eine Brennkammer
DE19809568A1 (de) * 1998-03-05 1999-08-19 Siemens Ag Ringbrennkammer, Verwendung einer Ringbrennkammer und Einsatz für eine Öffnung in einer Brennkammer

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1707758A1 (fr) * 2005-03-23 2006-10-04 Siemens Aktiengesellschaft Elément de coque pour chambre combustion et chambre combustion

Also Published As

Publication number Publication date
CN1320313C (zh) 2007-06-06
US20050000229A1 (en) 2005-01-06
ES2307704T3 (es) 2008-12-01
DE50212581D1 (de) 2008-09-11
EP1429077B1 (fr) 2008-07-30
US7007489B2 (en) 2006-03-07
JP2004191041A (ja) 2004-07-08
CN1512040A (zh) 2004-07-14

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