EP1398569A1 - Turbine à gaz - Google Patents

Turbine à gaz Download PDF

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Publication number
EP1398569A1
EP1398569A1 EP02020694A EP02020694A EP1398569A1 EP 1398569 A1 EP1398569 A1 EP 1398569A1 EP 02020694 A EP02020694 A EP 02020694A EP 02020694 A EP02020694 A EP 02020694A EP 1398569 A1 EP1398569 A1 EP 1398569A1
Authority
EP
European Patent Office
Prior art keywords
combustion chamber
coolant
gas turbine
pipes
turbine
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Withdrawn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
EP02020694A
Other languages
German (de)
English (en)
Inventor
Paul-Heinz Jeppel
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
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 EP02020694A priority Critical patent/EP1398569A1/fr
Priority to EP03798881A priority patent/EP1537363A1/fr
Priority to CNB038215306A priority patent/CN100394110C/zh
Priority to JP2004540568A priority patent/JP4181546B2/ja
Priority to US10/525,780 priority patent/US20050247062A1/en
Priority to PCT/EP2003/009703 priority patent/WO2004031656A1/fr
Publication of EP1398569A1 publication Critical patent/EP1398569A1/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Withdrawn legal-status Critical Current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
    • F23R3/005—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
    • F23R2900/00—Special features of, or arrangements for continuous combustion chambers; Combustion processes therefor
    • F23R2900/00012—Details of sealing devices

Definitions

  • the invention relates to a gas turbine with a Combustion chamber in which to generate a working medium supplied fuel with supplied combustion air for Reaction is brought.
  • 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.
  • 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 in the respective burner downstream turbine unit guided where it is working relaxed.
  • Each burner can have a separate one Combustion chamber to be assigned, which is from the combustion chambers outflowing working medium before or in the turbine unit can be merged.
  • the gas turbine but also in a so-called ring combustion chamber design be carried out in which a plurality, in particular all, the burner into a common, usually ring-shaped, Combustion chamber open.
  • the components and parts exposed to this medium exposed to high thermal loads.
  • a comparatively long lifespan It is usually necessary to ensure the affected components cooling the affected components, in particular the combustion chamber, necessary.
  • the aim is usually one if possible to achieve uniform cooling of the components.
  • the Cooling air is usually supplied via a cooling system Pipes and partitions exist for cooling on the outside the inner wall of the combustion chamber.
  • a cooling system constructed in this way has the Disadvantage that the structure of the combustion chamber and the cooling system is very complex.
  • the actual combustion chamber wall a separate one lying on your outside Cooling system, which in turn has to be attached from the outside, assigned.
  • the manufacturing process of such a combustion chamber can therefore be very costly and labor intensive since many Individual parts and joining processes are necessary for production. This further leads to an increased susceptibility to errors the manufacture and operation in the gas turbine. Likewise maintenance and repair work are complicated by the Combustion chamber wall construction difficult.
  • the invention is therefore based on the object of a gas turbine specify that even with a simple structure a special has high efficiency.
  • the invention is based on the consideration that the gas turbine to ensure a particularly high degree of efficiency designed for particularly high media temperatures should be. To reduce the susceptibility to errors to keep a particularly reliable cooling of the thermally loaded components, especially the Combustion chamber, be guaranteed. This is comparatively low effort achievable by the combustion chamber wall on the one hand designed coolable in itself and on the other hand from comparatively simple and flexible molded parts is constructed. These two aspects in the design the combustion chamber are kept in a particularly simple manner, by surrounding the combustion chamber or combustion chamber wall is suitably constructed from pipes. As a coolant in particular cooling air is provided, which after its passage through the coolant tubes as an additional, as a result of Combustion chamber cooling preheated combustion air of the combustion chamber can be supplied.
  • the coolant tubes are advantageously the combustion chamber wall made of cast material, in other words, form one casting each.
  • Another advantage of this choice of materials is that reliable thermal insulation especially is easily made possible by a suitable coating of the casting material with a ceramic protective layer is provided.
  • the coolant tubes are expediently the combustion chamber on carrier rings oriented in the circumferential direction of the combustion chamber attached. These carrier rings pass through your position and shape the shape of itself through the coolant tubes forming annulus of the combustion chamber.
  • kind of like self-supporting structure is using only one small number of other components in addition to the actual pipes producing a mechanically stable Combustion chamber structure enables.
  • the coolant pipes are attached to the carrier rings expediently via cooled screws.
  • the attachment the coolant tubes via screws allow at high Strength a particularly time-saving assembly or disassembly single or multiple coolant tubes from the Hot gas side off, that is, without disassembling the combustion chamber to have to.
  • the carrier rings are advantageously additional to the actual coolant pipes by a number connected by longitudinal ribs.
  • the carrier rings and longitudinal ribs are preferably together welded so that the rings and ribs welded one Form support body.
  • a particularly high degree of flexibility in shaping the Combustion chamber which in particular takes into account flow conditions in the working medium already in the combustion chamber allows, while at the same time a sufficient length and Shape of the coolant pipes can be ensured is achievable by expediently consisting of two or several joined together in their longitudinal direction Pipe segments exist.
  • the advantage of segmenting the Pipes can in particular consist of manufacturing technology Difficulty casting cast iron pipes with a sufficient length and appropriate shape to avoid avoided are.
  • each An assigned transition at its respective pipe end or connector preferably each An assigned transition at its respective pipe end or connector.
  • the shape of the transition pieces are expedient designed for easy connectivity.
  • the Transition pieces in particular chosen such that there are segments have a plug-in connection. If there is a trapezoidal cross section of the coolant tubes, the cross section of the transition piece is expediently so chosen that it extends to the junction or to end of each pipe segment to a circular cross section changed. Such a circular end cross-section enables particularly easy to edit for a precise connection with the subsequent one Pipe segment.
  • this cooling system has the advantage that it is integrated into the Wall construction of the combustion chamber is integrated and therefore only few additional parts required for the construction of the cooling system.
  • the heat input into the coolant for the actual energy conversion process in the gas turbine advantageously the heat input into the coolant for the actual energy conversion process in the gas turbine recovered.
  • This is advantageously a feed those heated during the combustion chamber cooling as a coolant cooling air used is provided in the combustion chamber, the preheated cooling air being exclusive or additional Combustion air can serve.
  • Each coolant tube is to be fed into the combustion chamber preferably on the output side with a collecting space connected, which in turn upstream of the combustion chamber is.
  • the coolant can be passed through this Throttle device with the rest of the compressor mass flow mixed and fed to the combustion process.
  • each burner is preferably included each connected to a collecting room, each collecting room is connected to the same number of coolant pipes.
  • This arrangement has the particular advantage that everyone Burners have approximately the same amount of recirculated cooling air is fed. Especially when designing the combustion chamber as an annular combustion chamber, it therefore occurs in the combustion chamber a particularly even combustion process.
  • the advantages achieved with the invention are in particular in that through the design of the combustion chamber wall than from a plurality of interconnected for which Flow through with a coolant, in particular cooling air, provided coolant pipes with a simple structure a special reliable combustion chamber cooling is made possible.
  • a coolant in particular cooling air
  • the integration of the coolant pipes in a self-supporting Combustion chamber structure, in particular by means of the carrier rings, is also a comparatively easy interchangeability too allows individual, needing maintenance pipes, but still due to the flexibility that can be achieved via the pipe construction also a replacement of existing combustion chamber structures easily possible in existing gas turbines is.
  • the construction of the combustion chamber from pipes is comparative stable and insensitive to vibrations the combustion chamber wall because the coolant tubes stiffen the annulus and solidify.
  • the by building the combustion chamber wall basic flexibility achieved from tubular elements in design and component selection also enables in especially attaching probes or monitoring sensors for monitoring and / or diagnosis of the actual Combustion process in the combustion chamber, in particular through the targeted use of specifically modified pipes, for example the implementation of suitable probes from the outside allow inside the combustion chamber.
  • 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. To do this are the turbine 6 and the compressor 2 on a common, also as a turbine rotor designated turbine shaft 8 arranged with the the generator or the working machine is also connected, and which is rotatably mounted about its central axis 9.
  • the combustion chamber designed in the manner of an annular combustion chamber 4 is with a number of burners 10 for burning one liquid or gaseous fuel. she is continue on their inner wall with not shown Heat shield elements.
  • 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 for a comparatively high outlet temperature of the working medium emerging from the combustion chamber 4 M designed from about 1200 ° C to 1500 ° C.
  • the combustion chamber 4 designed to be coolable.
  • the combustion chamber wall 23 As a tubular structure executed and from a variety of to form the Combustion chamber wall 23, coolant tubes connected to one another in a gas-tight manner 24 built.
  • the combustion chamber 4 is in the embodiment as a so-called 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.
  • the combustion chamber 4 in its entirety as an annular Designed structure that positioned around the turbine shaft 8 is.
  • the Combustion chamber wall 23 is a segment of the combustion chamber in FIG 4 shown in longitudinal section, which is used to form the Combustion chamber 4 continues in a toroidal manner around the turbine shaft 8.
  • the Combustion chamber 4 has an initial or inflow section, in the end of the outlet of the associated burner 10 flows. Seen in the direction of flow of the working medium M. The cross section of the combustion chamber 4 then narrows, whereby the flow profile of the working medium M is taken into account in this area. On the output side the combustion chamber 4 has a curvature in longitudinal section, through which the working medium M flows out of the combustion chamber 4 in one for a particularly high impulse and energy transfer to the first one seen from the flow side Blade row is favored.
  • the Combustion chamber wall 23 both in the outer area of the combustion chamber 4 and also formed in the inner region by coolant tubes 24, with its longitudinal axis essentially parallel to Flow direction of the working medium M in the interior of the Combustion chamber 4 are aligned.
  • the coolant tubes 24 are made of cast material, especially with regard to for a particularly high mechanical and thermal strength the coolant pipes are selected appropriately.
  • each coolant tube 24 in the embodiment by a suitable combination of several successive ones Pipe segments 26 formed.
  • Type and number of pipe segments 26 are selected such that, on the one hand, with regard to Length and shape of each pipe segment 26 and in view a particularly high mechanical on the cast material used Strength of each individual pipe segment 26 guaranteed is, on the other hand, the shape under Taking into account the desired flow path for the Working medium M is selected appropriately.
  • the possibly desired, comparatively strong local curvatures are special due to the segmentation of the coolant tubes 24 simple and reliable way to provide.
  • the coolant tubes 24 are also for a special strength especially with regard to locally varying thermal Exposure and the resulting thermal Designed for voltages.
  • the coolant tubes 24 and in particular the tube segments 26 forming these in cross section essentially trapezoidal like this shown for the center piece of a pipe segment 26 in Figure 3a is.
  • the combustion chamber 4 have the coolant tubes 24 in the Cross section a comparatively longer inside 28 and a comparatively shorter outside 30.
  • a suitable seal for example a brush seal seal 32, provided so that the appropriate Combination of the coolant tubes 24 with one another gas-tight and closed combustion chamber 4 results.
  • the respective transition pieces 34 are present in terms of their central line and compared to the Middle pieces of the respective pipe segments 26 in the outside area the combustion chamber 4 moved in so that under Use of suitable sealing sheets or plates in the inner wall the combustion chamber 4 is essentially continuous smooth surface can be provided.
  • the coolant tubes 24 are common to a number Carrier rings 36 attached in the longitudinal direction or viewed in the flow direction of the working medium M in suitable selected spacing that from the actual coolant tubes 24 enclose combustion chamber 4 formed.
  • the Carrier rings 36 are the respective coolant tubes 24 or the pipe segments 26 forming these via coolable screws 38 attached, as in the embodiment of Figure 3c is shown.
  • the carrier rings 36 are the carrier rings 36 by substantially in the longitudinal direction or oriented in the flow direction of the working medium M. Longitudinal ribs connected together.
  • the combustion chamber 4 By designing the combustion chamber 4 as a tubular structure is an exposure of the combustion chamber wall 23 with a comparatively large amount of cooling air as coolant K with only comparatively low pressure losses possible.
  • To the heating occurs when cooling the combustion chamber wall 23 of the coolant flowing through the coolant tubes 24 in for the thermodynamic efficiency favorably for to make the actual combustion process usable a feed of the emerging from the coolant tubes 24 Coolant K as exclusive or additional combustion air provided in the combustion chamber 4.
  • Coolant K is a feeder for this of the coolant K to the coolant tubes 24 at the other the end associated with the outlet of the combustion chamber 4.
  • the coolant K is the coolant tubes 24 there, as in Figure 2 can be seen, supplied via suitable inflow openings 42.
  • the inflow openings 42 are in terms of their spatial alignment positioned so that in the outlet area the combustion chamber 4 through the one flowing in as coolant K. Cooling air initially impingement cooling of the respective Pipe segment 26 takes place. Then takes place within the a respective deflection of the coolant K instead, and then the coolant K flows through the respective Coolant pipe 24 in its longitudinal direction, the Cooling by contact of the coolant K with the respective one Pipe wall is made.
  • the coolant K thus flows within the coolant tubes 24 from the outlet area of the combustion chamber 4 to its mouth area, in which the respective burner 10 is also arranged.
  • combustion chamber 4 is a symmetrical arrangement of the burners 10 and consequently the most symmetrical setting possible Flow conditions within the combustion chamber 4 usually advantageous.
  • This principle applies to the gas turbine 1 also taken into account on the coolant side, in particular the same number of each burner 10 on the combustion air side Coolant pipes 24 is assigned.

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)
EP02020694A 2002-09-13 2002-09-13 Turbine à gaz Withdrawn EP1398569A1 (fr)

Priority Applications (6)

Application Number Priority Date Filing Date Title
EP02020694A EP1398569A1 (fr) 2002-09-13 2002-09-13 Turbine à gaz
EP03798881A EP1537363A1 (fr) 2002-09-13 2003-09-01 Turbine a gaz
CNB038215306A CN100394110C (zh) 2002-09-13 2003-09-01 燃气轮机
JP2004540568A JP4181546B2 (ja) 2002-09-13 2003-09-01 ガスタービン
US10/525,780 US20050247062A1 (en) 2002-09-13 2003-09-01 Gas turbine
PCT/EP2003/009703 WO2004031656A1 (fr) 2002-09-13 2003-09-01 Turbine a gaz

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP02020694A EP1398569A1 (fr) 2002-09-13 2002-09-13 Turbine à gaz

Publications (1)

Publication Number Publication Date
EP1398569A1 true EP1398569A1 (fr) 2004-03-17

Family

ID=31725437

Family Applications (2)

Application Number Title Priority Date Filing Date
EP02020694A Withdrawn EP1398569A1 (fr) 2002-09-13 2002-09-13 Turbine à gaz
EP03798881A Withdrawn EP1537363A1 (fr) 2002-09-13 2003-09-01 Turbine a gaz

Family Applications After (1)

Application Number Title Priority Date Filing Date
EP03798881A Withdrawn EP1537363A1 (fr) 2002-09-13 2003-09-01 Turbine a gaz

Country Status (5)

Country Link
US (1) US20050247062A1 (fr)
EP (2) EP1398569A1 (fr)
JP (1) JP4181546B2 (fr)
CN (1) CN100394110C (fr)
WO (1) WO2004031656A1 (fr)

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1591725A3 (fr) * 2004-04-30 2014-03-05 Siemens Aktiengesellschaft Joint d'étanchéité pour gaz chaud
EP2574731A3 (fr) * 2011-09-30 2014-04-02 MTU Aero Engines GmbH Composant segmenté

Families Citing this family (7)

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Publication number Priority date Publication date Assignee Title
GB2434199B (en) * 2006-01-14 2011-01-05 Alstom Technology Ltd Combustor liner with heat shield
EP1862740B1 (fr) * 2006-05-31 2015-09-16 Siemens Aktiengesellschaft Paroi de chambre de combustion
US8397512B2 (en) * 2008-08-25 2013-03-19 General Electric Company Flow device for turbine engine and method of assembling same
EP2405200A1 (fr) * 2010-07-05 2012-01-11 Siemens Aktiengesellschaft Appareil de combustion et moteur de 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
WO2015017180A1 (fr) * 2013-08-01 2015-02-05 United Technologies Corporation Système de fixation pour panneau de cloison en céramique
CN104454174A (zh) * 2014-10-13 2015-03-25 罗显平 一种提高燃气发动机动力输出功率的方法

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GB376974A (en) * 1930-09-02 1932-07-21 Bbc Brown Boveri & Cie Improvements in and relating to combustion chambers
FR980028A (fr) * 1942-06-18 1951-05-07 Regent Perfectionnements apportés aux chambres de combustion
DE1025915B (de) * 1953-07-03 1958-03-13 Still Fa Carl Gasbeheizter Roehrenerhitzer mit einem aus Rohren gebildeten selbsttragenden Feuerraum
US3398527A (en) * 1966-05-31 1968-08-27 Air Force Usa Corrugated wall radiation cooled combustion chamber
US5129447A (en) * 1991-05-20 1992-07-14 United Technologies Corporation Cooled bolting arrangement
DE4343332A1 (de) * 1993-12-20 1995-06-22 Abb Management Ag Vorrichtung zur Konvektivkühlung einer dichten Brennkammer
US5832718A (en) * 1995-12-19 1998-11-10 Daimler-Benz Aerospace Airbus Gmbh Combustion chamber especially for a gas turbine engine using hydrogen as fuel

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1591725A3 (fr) * 2004-04-30 2014-03-05 Siemens Aktiengesellschaft Joint d'étanchéité pour gaz chaud
US8695989B2 (en) 2004-04-30 2014-04-15 Siemens Aktiengesellschaft Hot gas seal
EP2574731A3 (fr) * 2011-09-30 2014-04-02 MTU Aero Engines GmbH Composant segmenté
US9399924B2 (en) 2011-09-30 2016-07-26 Mtu Aero Engines Gmbh Segmented component

Also Published As

Publication number Publication date
JP2005538310A (ja) 2005-12-15
CN100394110C (zh) 2008-06-11
WO2004031656A1 (fr) 2004-04-15
CN1682078A (zh) 2005-10-12
US20050247062A1 (en) 2005-11-10
JP4181546B2 (ja) 2008-11-19
EP1537363A1 (fr) 2005-06-08

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