EP2189630A1 - Turbine à gaz, support d'aube directrice pour une telle turbine à gaz, et moteur à turbine à gaz avec une telle turbine à gaz - Google Patents

Turbine à gaz, support d'aube directrice pour une telle turbine à gaz, et moteur à turbine à gaz avec une telle turbine à gaz Download PDF

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Publication number
EP2189630A1
EP2189630A1 EP08020190A EP08020190A EP2189630A1 EP 2189630 A1 EP2189630 A1 EP 2189630A1 EP 08020190 A EP08020190 A EP 08020190A EP 08020190 A EP08020190 A EP 08020190A EP 2189630 A1 EP2189630 A1 EP 2189630A1
Authority
EP
European Patent Office
Prior art keywords
gas turbine
turbine
sectional area
gas
hollow
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Withdrawn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
EP08020190A
Other languages
German (de)
English (en)
Inventor
Francois Dr. Benkler
Tobias Dr. Buchal
Andreas Dr. Böttcher
Martin Hartmann
Patricia Dr. Hülsmeier
Uwe Kahlstorf
Ekkehard Dr. Maldfeld
Dieter Minninger
Michael Neubauer
Peter Schröder
Rotislav Dr. Teteruk
Vyacheslav Veitsman
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 EP08020190A priority Critical patent/EP2189630A1/fr
Priority to EP09827201.6A priority patent/EP2347101B1/fr
Priority to CN200980146179.9A priority patent/CN102216570B/zh
Priority to JP2011535935A priority patent/JP5281167B2/ja
Priority to PL09827201T priority patent/PL2347101T3/pl
Priority to PCT/EP2009/061936 priority patent/WO2010057698A1/fr
Priority to US13/129,633 priority patent/US9074490B2/en
Priority to ES09827201T priority patent/ES2426099T3/es
Publication of EP2189630A1 publication Critical patent/EP2189630A1/fr
Withdrawn legal-status Critical Current

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Classifications

    • 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
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/24—Casings; Casing parts, e.g. diaphragms, casing fastenings
    • F01D25/246—Fastening of diaphragms or stator-rings
    • 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
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/24—Casings; Casing parts, e.g. diaphragms, casing fastenings
    • F01D25/26—Double casings; Measures against temperature strain in casings

Definitions

  • the invention relates to a gas turbine with a number of coaxially arranged, substantially hollow cone-shaped or hollow cylindrical components. It further relates to a guide vane carrier, in particular for a gas turbine.
  • 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 produced in the combustion chamber by the combustion of the fuel, under high pressure and at high temperature, is guided via a turbine unit arranged downstream of the combustion chamber, where it relaxes to perform work.
  • a number of rotor blades which are usually combined into blade groups or rows of blades, are arranged thereon and drive the turbine shaft via a momentum transfer from the working medium.
  • guide vanes are also usually arranged between adjacent rotor blade rows and connected to the turbine housing, which are combined into rows of guide blades. These are attached to a usually hollow cylindrical or hollow cone-shaped vane carrier.
  • the hot gas channel is usually lined by so-called ring segments, which form the inner wall of the hot gas channel. These are usually fastened via hooking elements on the guide blade carrier, so that the entirety of the ring segments in the circumferential direction as well as the guide blade carrier form a hollow conical or hollow cylindrical structure.
  • the components of the gas turbine can deform by different thermal expansion in different operating conditions, which has a direct influence on the size of the radial gap between the blades and the inner wall of the hot gas channel.
  • These radial gaps are differently dimensioned when starting and stopping the turbine than in regular operation.
  • the gas turbine components such as guide vane or inner wall are always to be dimensioned so that the radial gaps are kept sufficiently large in order not to cause damage to the gas turbine in any operating condition.
  • a correspondingly comparatively generous design of the radial gaps leads to considerable losses in the efficiency.
  • the invention is therefore based on the object to provide a gas turbine and a guide vane, which allow a particularly high efficiency while maintaining the greatest possible operational safety and life.
  • At least one of the components or the guide blade carrier in the inoperative state has a substantially elliptical cross-sectional area.
  • the invention is based on the consideration that a particularly high efficiency by reducing the radial gap in normal operation, d. H.
  • full load operation of the gas turbine would be possible.
  • a comparatively large dimension of the radial gaps is necessary in particular because the turbine deforms differently in different operating states.
  • an ovalization of the cylindrical or conically shaped components of the gas turbine occurs, which must be taken into account in the design of the radial gaps.
  • the ovalization in the operation of the gas turbine should be kept as low as possible. This should be achieved by a suitably adapted form of the hollow cone-shaped or hollow cylindrical components of the gas turbine in the inoperative state, d. H.
  • cooled gas turbine This should be designed so that the introduced during the manufacture of the gas turbine deformation compensates for the deformations in the operating condition. This can be achieved by at least one of the components already having a substantially elliptical cross-sectional area in the inoperative state.
  • the length of the main and minor axes of the elliptical cross-sectional area is in each case selected such that the respective component has a substantially circular cross-sectional area due to its thermal deformation in the operating state during the production of the hollow cone-shaped or hollow cylindrical components of the gas turbine or guide vane carrier ,
  • This can be done, for example, by introducing an expected in operation by 90 degrees offset ovalization.
  • the elliptical shape of these components is thus chosen such that the deformations are compensated in the operating state just so that during operation creates a circular cross-section and thus over the entire circumference of the gas turbine same radial gaps are present, ie, the radial column on the scope no longer exhibit variance.
  • the radial gaps can be sized accordingly narrow, which has a higher efficiency of the gas turbine result.
  • Stationary gas turbines are usually arranged lying and the hollow cylindrical or hollow cone-shaped components of the gas turbine consist of two respective semi-cylindrical or semi-conical segments, which are arranged one above the other and are connected to each other, for example via flanges.
  • a deformation occurs during operation in which a standing ellipse is produced in cross-section, ie. h., The main axis of the ellipse is aligned perpendicular to the horizontal.
  • the respective component or the guide blade carrier should advantageously be made such that the axis connecting the vertices of the segments of the elliptical cross-sectional area in the inoperative state is shorter than the axis perpendicular thereto.
  • the cross section represents a substantially horizontal ellipse, d. H. the major axis of the ellipse is aligned parallel to the horizontal, and the illustrated deformation in operation sets a substantially circular cross-section.
  • the guide vane carrier is exposed to the described deformations.
  • the guide blade carrier is a hollow conical or hollow cylindrical component of the gas turbine, to which the guide vanes of the individual turbine stages or compressor stages are attached. He is exposed in operation comparatively high temperatures and is therefore subject to the described deformations particularly strong. Therefore, a targeted elliptical configuration of the cross section is introduced in particular in a guide vane carrier of the gas turbine.
  • the guide blade carrier which is elliptical in cross-section may be comparatively complicated and be associated with great effort.
  • the ring segments form in the axial section of the blades in the circumferential direction, the inner wall of the hot gas path, which thus forms the rotor blades nearest the hollow conical or hollow cylindrical component of the gas turbine. Therefore, in particular, the inner wall of the hot gas path is advantageously produced with a described elliptical cross-sectional area in the inoperative state.
  • the ring segments forming the inner wall of the hot gas path in the axial section of the rotor blades are usually hooked in the guide blade carrier via hooking elements. Since the vane support is a relatively solid component which has a relatively high deformation during operation, the exact shape of these ring segments in the operating condition is often determined by the attachment or tension of the ring segments in the vane support and its deformation during operation. It is therefore not absolutely necessary to produce the cold contour of the inner wall consisting of ring segments even in elliptical shape, since anyway set by the contact points on the Verhakungsettin forced deformation.
  • the compensation of the ovalization of the guide vane carrier can therefore be achieved by advantageously only the individual hooking elements of the ring segments are adapted such that the inner wall has a substantially elliptical cross-sectional area. Since these ring segments are exchangeable service parts, this makes it possible on the one hand to retrofit existing gas turbines, on the other hand to compensate for manufacturing errors in guide vanes and also a particularly simple adaptation to changing driving styles including other modified measures to reduce the radial gap.
  • the interlocking elements are adapted in their radial length and / or for changing the radial Location of the hooking elements arranged in a corresponding retaining groove of the guide rail carrier inserts. These then lie between the hooks of the hooking elements and the retaining groove and thus lead along the circumference to different radial positions of ring segments.
  • the turbine shaft in the cold operating state, can be displaced in the direction of the hot gas flow, so that an enlargement of the radial gap occurs in the case of a hollow conical shape of the inner wall with enlargement of the radius in the direction of the hot gas flow in the cold inoperative state and thus in the cold state (eg when starting up the hot air flow) Gas turbine), the remaining counter-ovalization represents no restriction for the achievable column in the warm state. As a result, an even greater efficiency of the gas turbine can be achieved.
  • such a gas turbine is used in a gas and steam turbine plant.
  • the advantages achieved by the invention are in particular that by a specific design of the hollow cone-shaped or hollow cylindrical components of a gas turbine or the guide vane such that they have a substantially elliptical cross-sectional area in the inoperative state, a particularly high efficiency of the gas turbine by reducing the radial gap reached becomes.
  • a particularly high efficiency of the gas turbine by reducing the radial gap reached becomes.
  • the gas turbine 1 has a compressor 2 for combustion air, a combustion chamber 4 and a turbine unit 6 for driving the compressor 2 and a generator, not shown, or a working machine.
  • the turbine unit 6 and the compressor 2 are arranged on a common, also referred to as a turbine rotor turbine shaft 8, with which the generator or the working machine is connected, and which is rotatably mounted about its turbine axis 9.
  • the executed in the manner of an annular combustion chamber combustion chamber 4 is provided with a number of burners 10 for Combustion of a liquid or gaseous fuel equipped.
  • the turbine unit 6 has a number of rotatable blades 12 connected to the turbine shaft 8.
  • the blades 12 are arranged in a ring on the turbine shaft 8 and thus form a number of blade rows.
  • the turbine unit 6 comprises a number of stationary vanes 14, which are also attached in a donut-like manner to a vane support 16 of the turbine unit 6 to form rows of vanes.
  • the blades 12 serve to drive the turbine shaft 8 by momentum transfer from the turbine unit 6 flowing through the working medium M.
  • the vanes 14, however, serve to guide the flow of the working medium M between two seen in the flow direction of the working medium M consecutive blade rows or blade rings.
  • a successive pair of a ring of vanes 14 or a row of vanes and a ring of blades 12 or a blade row is also referred to as a turbine stage.
  • Each vane 14 has a platform 18 which is arranged to fix the respective vane 14 to a vane support 16 of the turbine unit 6 as a wall element.
  • the platform 18 is a thermally comparatively heavily loaded component which forms the outer boundary of a hot gas channel for the working medium M flowing through the turbine unit 6.
  • Each blade 12 is attached to the turbine shaft 8 in an analogous manner via a platform 19, also referred to as a blade root.
  • each ring segment 21 is arranged on a guide blade carrier 16 of the turbine unit 6 respectively.
  • the inner surface of each ring segment 21 is also exposed to the hot working medium M flowing through the turbine unit 6 and spaced radially from the outer end of the opposed blades 12 by a radial gap.
  • the ring segments 21 arranged between adjacent guide blade rows serve in particular as cover elements which protect the guide blade carrier 16 or other housing built-in components from thermal overload by the hot working medium M flowing through the turbine 6.
  • the combustion chamber 4 is designed in the embodiment as a so-called annular combustion chamber, in which a plurality of circumferentially around the turbine shaft 8 arranged around burners 10 open into a common combustion chamber space.
  • the combustion chamber 4 is configured in its entirety as an annular structure which is positioned around the turbine shaft 8 around.
  • FIG. 2 and FIG. 3 now schematically show the guide vane 16 of the gas turbine 1 in a cross section perpendicular to the turbine axis 9 once left in the inoperative state, ie at cold gas turbine 1, and right in the operating state, ie at operating temperature.
  • the guide vane carrier 16 has a material temperature corresponding to the ambient temperature of the gas turbine.
  • the operating temperature is much higher; beyond 100 ° C.
  • the guide blade carrier 16 is composed of an upper segment 24 and a lower segment 26.
  • the two segments 24, 26 are connected to one another via flanges 28 and each form a connecting joint 30 at their connection point.
  • FIG. 2 4 illustrates a deformation of the prior art vane support 16 such that the distance between the peaks 32 of the respective upper and lower portions 24, 26 increases.
  • the cross section of the guide blade carrier 16 thereby deforms into a vertical ellipse.
  • a circular contour is shown for comparison in dashed line style.
  • the turbine shaft 8 is displaceable along the turbine axis 9.
  • the turbine shaft 8 In the cold state, that is, if there is an elliptical shape of the hot gas channel, then the turbine shaft 8 can be moved in the direction of the hot gas flow direction. As a result of the conical shape of the hot gas channel, this causes an enlargement of the radial gaps. Then, when in operation, a circular cross-section sets by thermal deformation, the turbine shaft 8 is displaced in the reverse direction to optimize the radial gap.
  • the ring segments 21 may be configured by a correspondingly introduced ovalization so that the hot gas channel receives a circular cross-section during operation.
  • the Verhakungsetti for fixing the ring segments 21 on the guide blade carrier 16 may be different lengths, ie be different lengths for different circumferential positions, or inserts between the hook and holding the guide vane 16 are introduced, which influence the radial position of the respective ring segments 21 with the same length Verhakungs instituten.
  • the shape of the inner wall of the hot gas channel formed from the ring segments 21 Namely, is determined by the passed through the Verhakungs institute the ring segments deformation of the vane support 16.
  • the ovalization in the operating state can be avoided.
  • the radial gaps can be designed correspondingly smaller, resulting in a significantly higher overall efficiency of the gas turbine 1 without sacrificing operational safety.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
EP08020190A 2008-11-19 2008-11-19 Turbine à gaz, support d'aube directrice pour une telle turbine à gaz, et moteur à turbine à gaz avec une telle turbine à gaz Withdrawn EP2189630A1 (fr)

Priority Applications (8)

Application Number Priority Date Filing Date Title
EP08020190A EP2189630A1 (fr) 2008-11-19 2008-11-19 Turbine à gaz, support d'aube directrice pour une telle turbine à gaz, et moteur à turbine à gaz avec une telle turbine à gaz
EP09827201.6A EP2347101B1 (fr) 2008-11-19 2009-09-15 Turbine à gaz et moteur à turbine à gaz associé
CN200980146179.9A CN102216570B (zh) 2008-11-19 2009-09-15 燃气涡轮机
JP2011535935A JP5281167B2 (ja) 2008-11-19 2009-09-15 ガスタービン
PL09827201T PL2347101T3 (pl) 2008-11-19 2009-09-15 Turbina gazowa i odpowiednia przemysłowa instalacja turbiny gazowej lub parowej
PCT/EP2009/061936 WO2010057698A1 (fr) 2008-11-19 2009-09-15 Turbine à gaz
US13/129,633 US9074490B2 (en) 2008-11-19 2009-09-15 Gas turbine
ES09827201T ES2426099T3 (es) 2008-11-19 2009-09-15 Turbina de gas e instalación de turbina de gas o de vapor correspondiente

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP08020190A EP2189630A1 (fr) 2008-11-19 2008-11-19 Turbine à gaz, support d'aube directrice pour une telle turbine à gaz, et moteur à turbine à gaz avec une telle turbine à gaz

Publications (1)

Publication Number Publication Date
EP2189630A1 true EP2189630A1 (fr) 2010-05-26

Family

ID=40532518

Family Applications (2)

Application Number Title Priority Date Filing Date
EP08020190A Withdrawn EP2189630A1 (fr) 2008-11-19 2008-11-19 Turbine à gaz, support d'aube directrice pour une telle turbine à gaz, et moteur à turbine à gaz avec une telle turbine à gaz
EP09827201.6A Not-in-force EP2347101B1 (fr) 2008-11-19 2009-09-15 Turbine à gaz et moteur à turbine à gaz associé

Family Applications After (1)

Application Number Title Priority Date Filing Date
EP09827201.6A Not-in-force EP2347101B1 (fr) 2008-11-19 2009-09-15 Turbine à gaz et moteur à turbine à gaz associé

Country Status (7)

Country Link
US (1) US9074490B2 (fr)
EP (2) EP2189630A1 (fr)
JP (1) JP5281167B2 (fr)
CN (1) CN102216570B (fr)
ES (1) ES2426099T3 (fr)
PL (1) PL2347101T3 (fr)
WO (1) WO2010057698A1 (fr)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2405105A3 (fr) * 2010-07-08 2014-04-23 General Electric Company Carter de turbine à vapeur

Families Citing this family (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JP5738127B2 (ja) * 2011-09-01 2015-06-17 三菱日立パワーシステムズ株式会社 蒸気タービン
EP3078448B1 (fr) * 2015-04-10 2018-07-11 Rolls-Royce Deutschland Ltd & Co KG Procédé d'usinage d'un carter pour une turbomachine.
ES2865387T3 (es) * 2017-08-04 2021-10-15 MTU Aero Engines AG Segmento de paletas guía para una turbina
KR102062594B1 (ko) * 2018-05-11 2020-01-06 두산중공업 주식회사 베인 캐리어, 이를 포함하는 압축기 및 가스 터빈

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US4426191A (en) * 1980-05-16 1984-01-17 United Technologies Corporation Flow directing assembly for a gas turbine engine
US5063661A (en) * 1990-07-05 1991-11-12 The United States Of America As Represented By The Secretary Of The Air Force Method of fabricating a split compressor case
EP1022439A1 (fr) * 1999-01-20 2000-07-26 ABB Alstom Power (Schweiz) AG Carter de turbine à vapeur ou à gaz
JP2005042612A (ja) * 2003-07-22 2005-02-17 Ishikawajima Harima Heavy Ind Co Ltd ケーシング及びケーシングの変形防止システム並びにその方法
DE102006038021A1 (de) * 2005-08-24 2007-03-01 Alstom Technology Ltd. Innengehäuse einer rotierenden thermischen Maschine

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JPS5481409A (en) * 1977-12-12 1979-06-28 Hitachi Ltd Turbine casing
US4426191A (en) * 1980-05-16 1984-01-17 United Technologies Corporation Flow directing assembly for a gas turbine engine
US5063661A (en) * 1990-07-05 1991-11-12 The United States Of America As Represented By The Secretary Of The Air Force Method of fabricating a split compressor case
EP1022439A1 (fr) * 1999-01-20 2000-07-26 ABB Alstom Power (Schweiz) AG Carter de turbine à vapeur ou à gaz
JP2005042612A (ja) * 2003-07-22 2005-02-17 Ishikawajima Harima Heavy Ind Co Ltd ケーシング及びケーシングの変形防止システム並びにその方法
DE102006038021A1 (de) * 2005-08-24 2007-03-01 Alstom Technology Ltd. Innengehäuse einer rotierenden thermischen Maschine

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* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2405105A3 (fr) * 2010-07-08 2014-04-23 General Electric Company Carter de turbine à vapeur

Also Published As

Publication number Publication date
PL2347101T3 (pl) 2013-12-31
US9074490B2 (en) 2015-07-07
CN102216570A (zh) 2011-10-12
CN102216570B (zh) 2014-03-05
JP2012508843A (ja) 2012-04-12
ES2426099T3 (es) 2013-10-21
EP2347101A1 (fr) 2011-07-27
US20110280721A1 (en) 2011-11-17
WO2010057698A1 (fr) 2010-05-27
EP2347101B1 (fr) 2013-07-03
JP5281167B2 (ja) 2013-09-04

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