EP1398462A1 - Turbine à gaz et pièce de transition - Google Patents

Turbine à gaz et pièce de transition Download PDF

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Publication number
EP1398462A1
EP1398462A1 EP02020693A EP02020693A EP1398462A1 EP 1398462 A1 EP1398462 A1 EP 1398462A1 EP 02020693 A EP02020693 A EP 02020693A EP 02020693 A EP02020693 A EP 02020693A EP 1398462 A1 EP1398462 A1 EP 1398462A1
Authority
EP
European Patent Office
Prior art keywords
coolant
transition component
gas turbine
turbine
working medium
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Withdrawn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
EP02020693A
Other languages
German (de)
English (en)
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 EP02020693A priority Critical patent/EP1398462A1/fr
Publication of EP1398462A1 publication Critical patent/EP1398462A1/fr
Withdrawn legal-status Critical Current

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    • 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
    • F23R3/46—Combustion chambers comprising an annular arrangement of several essentially tubular flame tubes within a common annular casing or within individual casings
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D9/00—Stators
    • F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
    • F01D9/023—Transition ducts between combustor cans and first stage of the turbine in gas-turbine engines; their cooling or sealings
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2260/00—Function
    • F05D2260/20—Heat transfer, e.g. cooling

Definitions

  • the invention relates to a gas turbine with a turbine unit, the one flowing out from a number of burners Working medium can be fed, with each burner on the working medium side via a transition component assigned to it is connected to the turbine unit. It continues to affect such a transition component.
  • Gas turbines are used to drive generators in many areas or used by work machines.
  • the fuel will burned in burners, using an air compressor compressed air is supplied.
  • By burning the Fuel becomes a working medium under high pressure generated with a high temperature. This working medium is in a turbine unit downstream of the burners managed where it relaxes while working.
  • the burner of the gas turbine can be in the manner of a so-called Annular combustion chamber construction in a common, annular Combustion chamber open from which the working medium of the Turbine unit is fed.
  • each burner can have an individual one Be assigned combustion chamber, from which the working medium Turbine unit is supplied, with adjacent combustion chambers are kept decoupled from each other on the media side.
  • each burner is on the working medium side via an associated transition component with the turbine unit connected. This transition component usually has at its end intended to receive the burner, adapted to its shape, a round cross-section.
  • the transition piece is at its end opening into the turbine unit however, for one together with the other transition pieces complete filling of the annular passage cross-section designed in the turbine unit.
  • the transition component will usually made of sheet metal.
  • the production of the transition component in a sheet metal construction can be very complex because the above cross-sectional shape described different metal parts with each other need to be added, which is very time and cost intensive can be. They can also be disadvantageous seams and corners such as the joining process Weld seams have an impact, as they flow through the working medium additional friction on the uneven inside of the transition component can arise, which is disadvantageous affects the efficiency of the gas turbine.
  • the strength of the Transition piece in a construction made of sheet metal is also limited, which leads to a reduction in the life of the Component can lead.
  • the components used are cooled to sufficient dimensional stability with a long service life guarantee.
  • the cooling of the transition piece becomes common through a combination of impingement and film cooling realized.
  • the invention has for its object a gas turbine Above type, especially in "Can - Transition - Construction", specify that with a comparatively simple design is suitable for a particularly high degree of efficiency and moreover has a particularly long lifespan. Furthermore, a particularly suitable transition component can be specified.
  • this object is achieved according to the invention solved by the transition component between the burner and turbine connection executed as a cast part or welded sheet metal part is.
  • the invention is based on the consideration that to ensure a particularly high system efficiency Shaping the transition component to specifications with regard to a appropriate flow division adapted for the working medium should be.
  • the should required continuous change in flow cross-section starting from an approximately circular cross-section towards an approximately rectangular or trapezoidal Cross section, can be provided.
  • the high mechanical life favoring the gas turbine and / or to enable thermal stability should that Molding targeted with regard to its structural properties designed to comply with these boundary conditions his. This is also with only a limited manufacturing effort possible by using the transition component as a cast part or welded Sheet metal part is executed.
  • coolant channels For a particularly effective cooling of the transition component this advantageously provided with coolant channels. These are preferably aligned in the circumferential direction of the component arranged on this.
  • An arrangement of the coolant channels in the circumferential direction has the advantage that through a suitable choice of the local arrangement density of the channels or the size of the local cooling effect Temperature or heating curve adjusted on the transition component can be. Even in the longitudinal direction of the transition component is seen locally different heating an approximately uniform cooling in the longitudinal direction of the whole Transition component reached.
  • neighboring coolant channels can be reached expediently in the opposite direction from the coolant flows through.
  • the coolant heats up as it flows through of the coolant channels through the cooling process increasingly on.
  • To an opposite flow direction to ensure the coolant in adjacent coolant channels is expedient for feeding the coolant channels a corresponding alternating circuit of the Coolant channels with inlet and outlet channels provided.
  • the coolant channels are preferably as in the wall of the Transition component introduced grooves executed with a Cover plate are closed. With this construction of the coolant channels the grooves can already be cast when the transition component is cast be introduced so that the coolant channels time and cost-saving can be attached.
  • the cover plate is expedient welded to the transition component.
  • the cover plate preferably has a U-shaped Cross-section, on the upper edges of which the Transition component is welded.
  • the U-shaped cross section of the cover plate has the advantage that the cover plate is due to sufficient expansion space during the welding process deform due to thermal influences of the welding tool can, and therefore a very accurate and homogeneous Cross section of the coolant channel can be reached without cracks. It can also have flat cross-sectional shapes for the cover plate Find application.
  • the coolant channels assigned a common coolant distributor, through which the individual coolant channels with the coolant be supplied.
  • a common distributor has the advantage that the coolant channels are not through individual lines must be supplied with the coolant, which causes a reliable cooling system with a time and cost saving Manufacturing process can be realized.
  • the coolant distributor are preferably supply and discharge channels integrated, which is essentially parallel to Flow direction of the working medium are oriented.
  • This offers the advantage of over the coolant a short distance to the actual coolant channels or to be able to discharge, and on the other hand enables a alternating with respect to the direction of flow of the coolant Wiring the coolant pipes.
  • the supply and discharge channels at a suitable Dimensioning also for existing gas turbines In "Can - Transition - Construction" existing supply and discharge connections be used for the coolant supply, so this arrangement is also particularly suitable for retrofitting existing systems is suitable.
  • the coolant distributor with the integrated supply channels cast together during the casting of the transition component become.
  • the circuit for feeding the coolant pipes, especially in the opposite direction of flow can advantageously also during the casting process be made with.
  • the supply and discharge channels point a suitably chosen course so that the connection side when wiring the coolant channels alternates.
  • the transition component is expediently via the coolant distributor attached to a support frame.
  • the transition component has a particularly high strength be so that when the transition component is fastened at this point the forces acting on the component without further holding structures can be added.
  • transition component itself, the aforementioned Task solved by this is designed as a casting and preferably further developed in the sense of the concepts mentioned above is.
  • the transition component is therefore particularly suitable Dimensions for equipment of a newly manufactured gas turbine or for retrofitting or upgrading already existing gas turbine plants.
  • the advantages achieved with the invention are in particular in that through the design of the transition component as a cast part or as pressed and welded into shape
  • the geometric transition of the component from a circular to an almost rectangular cross section can be realized particularly precisely because with one Cast the 3-dimensional shape and in particular the change in cross-section made in a smooth transition can be.
  • it can also be done with a small amount Weight achieve a comparatively high strength.
  • By a suitable integration of the coolant channels in the Casting is also in every operating state of the gas turbine a suitable application of the Transitional component with coolant and thus a reliable one Component cooling enabled.
  • the transition piece is thus in especially for gas turbines with comparatively high ones Working fluid temperatures can be used and thus favors their efficiency.
  • the gas turbine 1 has a compressor 2 for Combustion air, a number of combustion chambers 4 and one Turbine 6 for driving the compressor 2 and one not shown Generator or a work machine.
  • a compressor 2 for Combustion air
  • Turbine 6 for driving the compressor 2 and one not shown Generator or a work machine.
  • the turbine 6 and the compressor 2 on a common, also arranged as a turbine rotor 8, with which the generator or the work machine is connected, and which is rotatably mounted about its central axis 9 is.
  • the "Can Transition" type of construction Gas turbine 1 is equipped with a number of burners 10, each of which is assigned an individual combustion chamber 4 is.
  • the combustion chambers 4 are to form an individual Flame or combustion chamber each from an associated Transitional component 11 limits the combustion chambers 4th decoupled from each other on the flow or working medium side holds.
  • a transition component 11 has to accommodate the burner 10 an approximately circular cross section at the end of the burner on while connecting it to the turbine end the turbine has a trapezoidal cross section. Therefore is the transition component 11 in the flow direction of the working medium M from circular to trapezoidal marked changing cross-section.
  • 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 gas turbine 1 is the transition component 11 of each combustion chamber 4 through a suitable choice of shape for the flow pattern of the working medium M flowing through.
  • the cross section of the transition component changes 11 continuously in the direction of flow.
  • the transition component 11 is designed as a cast component.
  • the transition component 11 has due to the cast material high strength and thus a particularly long service life even when used in comparatively adverse operating conditions.
  • the transition component 11 can also as Sheet metal welded part to be executed.
  • the transition component 11 is for the in the combustion chamber 4th continuously occurring combustion temperatures designed and in particular designed coolable.
  • the transition component 11 several substantially perpendicular to Flow direction of the working medium M and thus in the circumferential direction extending coolant channels 24.
  • the coolant channels 24 in the circumferential direction can, in particular with a suitable choice of the arrangement density of the coolant channels 24, the cooling effect the temperature curve of the working medium in the transition component 11 under standard operating conditions be adjusted accordingly so that an even Cooling in the longitudinal direction is particularly favored.
  • Coolant K to supply the coolant channels 24 the coolant channels 24 via a common coolant distributor 25, which is substantially parallel to the direction of flow of the working medium M on the outer wall of the transition component 11 extends.
  • the coolant distributor 25 Through the coolant distributor 25 the coolant K is introduced into the coolant channels 24 and derived from them.
  • FIGS. 4a and 4b are a supply channel 30 and a in the coolant distributor 25 Discharge channel 32 integrated through which the coolant K in the Coolant channels 24 is supplied and discharged.
  • FIGS. 4a and 4b show the coolant distributor 25 with the integrated feed channel 30 and the discharge channel 32 cast together with the casting of the transition component 11.
  • the cover plate 26 is on welded its two ends to the coolant distributor 25.
  • connection point 34 of the coolant distributor 25 Via the connection point 34 of the coolant distributor 25 the coolant K into the feed channel 30 and out of the discharge channel 32 derived.
  • the positioning of the connection points 34 can in particular meet the requirements of existing ones Adapted gas turbines in "Can - Transition - Construction" be so that the transition component 11 is also particularly for Retrofitting in these gas turbines is suitable.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
EP02020693A 2002-09-13 2002-09-13 Turbine à gaz et pièce de transition Withdrawn EP1398462A1 (fr)

Priority Applications (1)

Application Number Priority Date Filing Date Title
EP02020693A EP1398462A1 (fr) 2002-09-13 2002-09-13 Turbine à gaz et pièce de transition

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP02020693A EP1398462A1 (fr) 2002-09-13 2002-09-13 Turbine à gaz et pièce de transition

Publications (1)

Publication Number Publication Date
EP1398462A1 true EP1398462A1 (fr) 2004-03-17

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EP02020693A Withdrawn EP1398462A1 (fr) 2002-09-13 2002-09-13 Turbine à gaz et pièce de transition

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EP (1) EP1398462A1 (fr)

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2915957A1 (fr) * 2014-03-05 2015-09-09 Siemens Aktiengesellschaft Conduit tubulaire coulée pour une turbine à gaz et son procédé de fabrication
GB2554384A (en) * 2016-09-23 2018-04-04 Hieta Tech Limited Combustion chamber and heat exchanger

Citations (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE510847C (de) * 1928-03-02 1930-10-24 E H Hans Holzwarth Dr Ing Brennkammer mit ringfoermigen Kuehlkammern, insbesondere fuer Verpuffungsbrennkraftturbinen
US4195474A (en) * 1977-10-17 1980-04-01 General Electric Company Liquid-cooled transition member to turbine inlet
US4465284A (en) * 1983-09-19 1984-08-14 General Electric Company Scalloped cooling of gas turbine transition piece frame
US5414999A (en) * 1993-11-05 1995-05-16 General Electric Company Integral aft frame mount for a gas turbine combustor transition piece
US5645127A (en) * 1993-05-07 1997-07-08 Mtu Motoren-Und Turbinen-Union Muenchen Gmbh Coolant supply arrangement for jet engine turbine walls
EP0816010A2 (fr) * 1996-06-24 1998-01-07 General Electric Company Procédé de fabrication des composants de turbine à paroi double à partir des ensembles préconsolidés
US6018950A (en) * 1997-06-13 2000-02-01 Siemens Westinghouse Power Corporation Combustion turbine modular cooling panel
EP1001221A2 (fr) * 1998-11-12 2000-05-17 Mitsubishi Heavy Industries, Ltd. Structure de refroidissement pour une chambre de combustion d'une turbine à gaz

Patent Citations (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE510847C (de) * 1928-03-02 1930-10-24 E H Hans Holzwarth Dr Ing Brennkammer mit ringfoermigen Kuehlkammern, insbesondere fuer Verpuffungsbrennkraftturbinen
US4195474A (en) * 1977-10-17 1980-04-01 General Electric Company Liquid-cooled transition member to turbine inlet
US4465284A (en) * 1983-09-19 1984-08-14 General Electric Company Scalloped cooling of gas turbine transition piece frame
US5645127A (en) * 1993-05-07 1997-07-08 Mtu Motoren-Und Turbinen-Union Muenchen Gmbh Coolant supply arrangement for jet engine turbine walls
US5414999A (en) * 1993-11-05 1995-05-16 General Electric Company Integral aft frame mount for a gas turbine combustor transition piece
EP0816010A2 (fr) * 1996-06-24 1998-01-07 General Electric Company Procédé de fabrication des composants de turbine à paroi double à partir des ensembles préconsolidés
US6018950A (en) * 1997-06-13 2000-02-01 Siemens Westinghouse Power Corporation Combustion turbine modular cooling panel
EP1001221A2 (fr) * 1998-11-12 2000-05-17 Mitsubishi Heavy Industries, Ltd. Structure de refroidissement pour une chambre de combustion d'une turbine à gaz

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2915957A1 (fr) * 2014-03-05 2015-09-09 Siemens Aktiengesellschaft Conduit tubulaire coulée pour une turbine à gaz et son procédé de fabrication
GB2554384A (en) * 2016-09-23 2018-04-04 Hieta Tech Limited Combustion chamber and heat exchanger
US11543129B2 (en) 2016-09-23 2023-01-03 Hieta Technologies Limited Combustion chamber and heat exchanger

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