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EP2194236A1 - Carter de turbine - Google Patents

Carter de turbine Download PDF

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Publication number
EP2194236A1
EP2194236A1 EP08020993A EP08020993A EP2194236A1 EP 2194236 A1 EP2194236 A1 EP 2194236A1 EP 08020993 A EP08020993 A EP 08020993A EP 08020993 A EP08020993 A EP 08020993A EP 2194236 A1 EP2194236 A1 EP 2194236A1
Authority
EP
European Patent Office
Prior art keywords
turbine
turbine housing
segments
heat
housing
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Withdrawn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
EP08020993A
Other languages
German (de)
English (en)
Inventor
Tobias Dr. Buchal
Björn Burbach
Christoph Buse
Andreas Dr. Böttcher
Patricia Dr. Hülsmeier
Uwe Kahlstorf
Ekkehard Dr. Maldfeld
Torsten Matthias
Michael Neubauer
Oliver Dr. Schneider
Rostislav Dr. Teteruk
Norbert Thamm
Vyacheslav Veitsnam
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 EP08020993A priority Critical patent/EP2194236A1/fr
Publication of EP2194236A1 publication Critical patent/EP2194236A1/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Withdrawn legal-status Critical Current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
    • F01D25/26—Double casings; Measures against temperature strain in 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
    • F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
    • F01D11/08—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator
    • F01D11/14—Adjusting or regulating tip-clearance, i.e. distance between rotor-blade tips and stator casing
    • F01D11/16—Adjusting or regulating tip-clearance, i.e. distance between rotor-blade tips and stator casing by self-adjusting means
    • F01D11/18—Adjusting or regulating tip-clearance, i.e. distance between rotor-blade tips and stator casing by self-adjusting means using stator or rotor components with predetermined thermal response, e.g. selective insulation, thermal inertia, differential expansion
    • 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
    • F01D25/08—Cooling; Heating; Heat-insulation
    • F01D25/14—Casings modified therefor
    • F01D25/145—Thermally insulated casings
    • 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
    • F05D2230/00—Manufacture
    • F05D2230/90—Coating; Surface treatment
    • 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
    • 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
    • F05D2260/221—Improvement of heat transfer
    • 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
    • F05D2260/85—Starting
    • 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
    • F05D2300/00—Materials; Properties thereof
    • F05D2300/50—Intrinsic material properties or characteristics
    • F05D2300/502—Thermal properties
    • F05D2300/5024—Heat conductivity

Definitions

  • the invention relates to a turbine housing, which consists of a plurality of interconnected segments.
  • 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.
  • For guiding the flow of the working medium in the turbine unit also commonly associated between adjacent blade rows with the turbine housing and combined into rows of guide vanes are arranged.
  • the combustion chamber of the gas turbine may be embodied as a so-called annular combustion chamber, in which a plurality of circumferentially arranged around the turbine shaft burners in a common, surrounded by a high temperature resistant surrounding wall combustion chamber space.
  • the combustion chamber is designed in its entirety as an annular structure.
  • a single combustion chamber can also be provided a plurality of combustion chambers.
  • first row of guide vanes of a turbine unit which, together with the blade row immediately downstream in the flow direction of the working medium, forms a first turbine stage of the turbine unit, which is usually followed by further turbine stages.
  • the vanes are fixed in each case via a blade root, also referred to as a platform, on a guide vane carrier of the turbine unit.
  • the guide blade carrier for securing the platforms of the guide vanes comprise an insulation segment.
  • a guide ring on the guide vane support of the turbine unit is arranged in each case.
  • Such a guide ring is spaced by a radial gap of the blade tips of the fixed at the same axial position on the turbine shaft blades of the associated blade row.
  • the invention is therefore based on the object to provide a turbine housing, which achieves a reduction of the radial gaps and thus a particularly high efficiency while maintaining the greatest possible operational safety.
  • the invention is based on the consideration that a particularly high efficiency by reducing the radial gaps would be possible in regular operation of the gas turbine.
  • a comparatively large dimension of the radial gaps is necessary in particular because the turbine deforms differently in different operating states.
  • the deformation of the housing due to assembly-related bias and uneven heating is responsible for the temporal change of the radial gaps. Accordingly, a reduction of the radial gaps could be possible by avoiding the deformation of the turbine housing.
  • the deformation of the turbine housing is characterized by the different warm-up and cooling properties of different areas of the turbine housing, d. H. caused by the different heat capacity of these areas. Certain areas heat up faster or cool faster than others, resulting in different rates of thermal expansion. Therefore, these differences should be compensated.
  • This can be achieved by a respective layer is disposed in regions on the inner wall of the turbine housing, wherein the respective layer is adapted in its heat conduction properties of the heat capacity of the respective region of the turbine housing.
  • a layer can be provided for example in the form of prefabricated plates, which are then connected to the inner wall of the turbine housing or it can be applied directly to a corresponding coating on the inner wall of the turbine housing.
  • the respective layer is arranged in a connection region of a number of segments or in a central region of a segment, since these regions have the comparatively largest differences in their cooling and heating behavior. Since the segments of the turbine housing are connected by flanges, they are made comparatively massive. In contrast, the central regions of the segments, ie the regions of the segment furthest away from the edges of the segment are, no additional connection means such as flanges and are designed correspondingly less massive. Accordingly, an adjustment of the heat conduction properties should be carried out by applying a corresponding layer, especially in these areas.
  • the turbine housing consists of two interconnected, substantially in sections semicircular and / or semi-cylindrical segments.
  • This allows a particularly simple construction of the turbine housing.
  • the turbine housing in which the turbine housing is composed of two parts, which essentially constitute a lower and an upper housing, exists on each side of a long connecting joint, which runs along the turbine shaft.
  • this connecting flanges flanges are provided, with which the two turbine housing segments are connected.
  • These areas are therefore particularly massive.
  • the areas furthest from the connecting flanges are d.
  • the areas offset by 90 ° with respect to the turbine shaft along the apex of the half-cylinder and / or half-cone are far less solid than the areas near the connecting joints. Therefore, the respective layer should be arranged in the region of the joints of the segments or in the region of the apex of the segments, since these are the regions with the comparatively largest differences in their cooling and heating behavior.
  • a heat-input-promoting, ie heat-conducting, layer should advantageously be provided in the connection regions, which accelerate the warm-up process when starting up the gas turbine and thus reduce the differences in the thermal deformation.
  • a heat-insulating layer should be provided in the central regions of the segments in order to slow down the heating and further reduce or even avoid the differences in the thermal deformation.
  • a heat-insulating layer should advantageously be provided in the connecting regions, so that the residual heat from the interior of the gas turbine does not additionally slow down the cooling process and thus overall faster cooling is achieved.
  • a heat input-promoting, d. H. thermally conductive layer may be provided to slow down the cooling and reduce the differences in the thermal deformation during shutdown.
  • the respective heat-insulating layer contains a ceramic material.
  • Ceramic materials can be adapted particularly well to the respective application by deliberately influencing the microstructures during the production processes with regard to starting materials, shaping and firing.
  • the thermal conductivity of a ceramic material can be influenced particularly well, and a particularly good thermal insulation by means of a correspondingly produced ceramic material is possible.
  • ceramic materials are characterized by a particularly high heat resistance, abrasion and wear resistance and corrosion resistance, making them particularly well suited for use in a gas turbine.
  • the respective heat-conducting layer contains copper.
  • Copper is an excellent conductor of heat and is therefore particularly suitable for a heat-conducting layer.
  • copper is particularly malleable because it is a relatively soft metal.
  • such a gas turbine is used in a gas and steam turbine plant.
  • the advantages associated with the invention are, in particular, that a number of segments on the inner wall of the turbine housing, the differential thermal expansion of solid and less massive parts of the turbine housing can be reduced or reduced by the arrangement of a heat-insulating layer in the connecting region and thus a reduction of Radial column in the construction of the gas turbine and an associated increase in efficiency is achieved.
  • By targeted application of heat-insulating and heat-conducting layers on the inner wall of the turbine housing thus deformation of the housing can be prevented.
  • when starting and stopping the gas turbine thus less consideration must be given to a different development of the radial gaps and there may be an overall tighter design of the radial gaps in the construction process.
  • 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 non-illustrated Generator or a working machine.
  • the turbine unit 6 and the compressor 2 are arranged on a common, also called turbine rotor turbine shaft 8, with which the generator or the working machine is connected, and which is rotatably mounted about its central axis 9.
  • the running in the manner of an annular combustion chamber 4 is equipped with a number of burners 10 for the combustion of a liquid or gaseous fuel.
  • 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.
  • a guide ring 21 is arranged on a guide blade carrier 16 of the turbine unit 6.
  • the outer surface of each guide ring 21 is also exposed to the hot, the turbine unit 6 flowing through the working medium M and spaced in the radial direction from the outer end of the opposite blades 12 through a gap.
  • the guide rings 21 arranged between adjacent guide blade rows serve in particular as cover elements which protect the inner housing in the guide blade carrier 16 or other housing built-in components against thermal overstress 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 schematically shows the turbine housing 30 of the gas turbine 1 schematically in a section perpendicular to the central axis 9.
  • the turbine housing 30 is composed of an upper part 32 and a lower part 34.
  • the two parts 32, 34 are connected to each other via flanges 36 and form their joint a respective joint 38.
  • heat-conducting layers 42 are arranged in the connection region at the joints 38. These layers may be provided either as plates or directly as a coating of the inner wall of the turbine housing 30 and may, for example, contain copper. As a result, the connection areas heat up faster.
  • heat-insulating layers 44 which may contain, for example, a ceramic material, are arranged in each case in the region of the apexes 40. These provide for a slower warming here.
  • the different thermal conduction properties of the areas at the joints 38 and vertex 40 are balanced by the layers 42, 44 and the deformation of the turbine housing 30 is reduced or prevented.
  • the heat-insulating layers 44 and the heat-conducting layers 42 can be interchanged in order to utilize the residual heat from the inner region of the gas turbine 1 to compensate for the different cooling of the turbine housing 30.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
EP08020993A 2008-12-03 2008-12-03 Carter de turbine Withdrawn EP2194236A1 (fr)

Priority Applications (1)

Application Number Priority Date Filing Date Title
EP08020993A EP2194236A1 (fr) 2008-12-03 2008-12-03 Carter de turbine

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP08020993A EP2194236A1 (fr) 2008-12-03 2008-12-03 Carter de turbine

Publications (1)

Publication Number Publication Date
EP2194236A1 true EP2194236A1 (fr) 2010-06-09

Family

ID=40823057

Family Applications (1)

Application Number Title Priority Date Filing Date
EP08020993A Withdrawn EP2194236A1 (fr) 2008-12-03 2008-12-03 Carter de turbine

Country Status (1)

Country Link
EP (1) EP2194236A1 (fr)

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN110847983A (zh) * 2019-11-25 2020-02-28 东方电气集团东方汽轮机有限公司 一种汽缸壁温控制方法
DE102020206269A1 (de) 2020-05-19 2021-11-25 Forschungszentrum Jülich GmbH Betrieb einer Gasturbine bei hoher Temperatur und Gasturbinenanordnung
CN119347323A (zh) * 2024-10-23 2025-01-24 中国航发南方工业有限公司 锻件对半轴流机匣的加工方法

Citations (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
SU580334A1 (ru) * 1972-10-30 1977-11-15 Ленинградский Дважды Ордена Ленина Металлический Завод Им. Ххп Съезда Кпсс Защитный экран
DE4117362A1 (de) * 1990-05-31 1991-12-05 Gen Electric Gasturbinentriebwerksstator und verfahren zum steuern des radialen spiels zwischen stator und rotor
US5605438A (en) * 1995-12-29 1997-02-25 General Electric Co. Casing distortion control for rotating machinery
US5645399A (en) * 1995-03-15 1997-07-08 United Technologies Corporation Gas turbine engine case coated with thermal barrier coating to control axial airfoil clearance
DE19806809C1 (de) * 1998-02-18 1999-03-25 Siemens Ag Turbinengehäuse
EP1541810A1 (fr) * 2003-12-11 2005-06-15 Siemens Aktiengesellschaft Utilisation de revêtement de barrière thermique pour un élément d'une turbine à vapeur et une turbine à vapeur
WO2008012195A1 (fr) * 2006-07-24 2008-01-31 Siemens Aktiengesellschaft Procédé pour dévisser une moitié annulaire d'un distributeur de forme globale annulaire hors d'une moitié inférieure de boîtier d'une turbomachine stationnaire à écoulement axial, dispositif de montage, assemblage de dispositif de montage et demi-secteur annulaire auxiliaire

Patent Citations (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
SU580334A1 (ru) * 1972-10-30 1977-11-15 Ленинградский Дважды Ордена Ленина Металлический Завод Им. Ххп Съезда Кпсс Защитный экран
DE4117362A1 (de) * 1990-05-31 1991-12-05 Gen Electric Gasturbinentriebwerksstator und verfahren zum steuern des radialen spiels zwischen stator und rotor
US5645399A (en) * 1995-03-15 1997-07-08 United Technologies Corporation Gas turbine engine case coated with thermal barrier coating to control axial airfoil clearance
US5605438A (en) * 1995-12-29 1997-02-25 General Electric Co. Casing distortion control for rotating machinery
DE19806809C1 (de) * 1998-02-18 1999-03-25 Siemens Ag Turbinengehäuse
EP1541810A1 (fr) * 2003-12-11 2005-06-15 Siemens Aktiengesellschaft Utilisation de revêtement de barrière thermique pour un élément d'une turbine à vapeur et une turbine à vapeur
WO2008012195A1 (fr) * 2006-07-24 2008-01-31 Siemens Aktiengesellschaft Procédé pour dévisser une moitié annulaire d'un distributeur de forme globale annulaire hors d'une moitié inférieure de boîtier d'une turbomachine stationnaire à écoulement axial, dispositif de montage, assemblage de dispositif de montage et demi-secteur annulaire auxiliaire

Non-Patent Citations (1)

* Cited by examiner, † Cited by third party
Title
DATABASE WPI Derwent World Patents Index; AN 1978-H8276A, SHCHETININ, A: "Turbine casing protective screen" *

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN110847983A (zh) * 2019-11-25 2020-02-28 东方电气集团东方汽轮机有限公司 一种汽缸壁温控制方法
DE102020206269A1 (de) 2020-05-19 2021-11-25 Forschungszentrum Jülich GmbH Betrieb einer Gasturbine bei hoher Temperatur und Gasturbinenanordnung
US12385415B2 (en) 2020-05-19 2025-08-12 Forschungszentrum Jülich GmbH Operation of a gas turbine at a high temperature and gas turbine assembly
CN119347323A (zh) * 2024-10-23 2025-01-24 中国航发南方工业有限公司 锻件对半轴流机匣的加工方法

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