EP2022951A1 - Procédé destiné à la fabrication d'un boîtier de turbine et boîtier de turbine - Google Patents

Procédé destiné à la fabrication d'un boîtier de turbine et boîtier de turbine Download PDF

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Publication number
EP2022951A1
EP2022951A1 EP07015627A EP07015627A EP2022951A1 EP 2022951 A1 EP2022951 A1 EP 2022951A1 EP 07015627 A EP07015627 A EP 07015627A EP 07015627 A EP07015627 A EP 07015627A EP 2022951 A1 EP2022951 A1 EP 2022951A1
Authority
EP
European Patent Office
Prior art keywords
housing
layer
outer layer
inner layer
casting
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Withdrawn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
EP07015627A
Other languages
German (de)
English (en)
Inventor
Heinz Dallinger
Kai Dr. Wieghardt
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 EP07015627A priority Critical patent/EP2022951A1/fr
Priority to JP2010519422A priority patent/JP2010535970A/ja
Priority to EP08786470A priority patent/EP2176522A1/fr
Priority to PCT/EP2008/059813 priority patent/WO2009019152A1/fr
Priority to US12/671,069 priority patent/US20100209234A1/en
Priority to CN2008801023249A priority patent/CN101779004B/zh
Publication of EP2022951A1 publication Critical patent/EP2022951A1/fr
Priority to JP2012005323A priority patent/JP5450674B2/ja
Priority to US14/083,866 priority patent/US9358609B2/en
Withdrawn legal-status Critical Current

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Classifications

    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B22—CASTING; POWDER METALLURGY
    • B22D—CASTING OF METALS; CASTING OF OTHER SUBSTANCES BY THE SAME PROCESSES OR DEVICES
    • B22D25/00—Special casting characterised by the nature of the product
    • 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
    • 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
    • F05D2230/20—Manufacture essentially without removing material
    • F05D2230/21—Manufacture essentially without removing material by casting
    • 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
    • F05D2230/30—Manufacture with deposition of material
    • 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
    • F05D2230/30—Manufacture with deposition of material
    • F05D2230/31—Layer deposition
    • 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
    • F05D2230/40—Heat 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
    • F05D2240/00—Components
    • F05D2240/10—Stators
    • F05D2240/14—Casings or housings protecting or supporting assemblies within
    • 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
    • F05D2260/94—Functionality given by mechanical stress related aspects such as low cycle fatigue [LCF] of high cycle fatigue [HCF]
    • 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
    • F05D2260/94—Functionality given by mechanical stress related aspects such as low cycle fatigue [LCF] of high cycle fatigue [HCF]
    • F05D2260/941—Functionality given by mechanical stress related aspects such as low cycle fatigue [LCF] of high cycle fatigue [HCF] particularly aimed at mechanical or thermal stress reduction
    • 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
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
    • Y10T29/00—Metal working
    • Y10T29/49—Method of mechanical manufacture
    • Y10T29/4998—Combined manufacture including applying or shaping of fluent material

Definitions

  • the invention relates to a housing for a thermal turbomachine and to a method for producing an at least two-layer housing for a turbomachine.
  • One of the measures would be to increase the steam inlet temperatures of the steam flowing into the thermal turbomachine, in particular a steam turbine. Efforts are currently underway to increase the steam inlet temperature to up to 700 ° C or even beyond.
  • Nickel-based materials are currently believed to be suitable for high steam inlet temperatures. However, this material is many times more expensive compared to conventional materials.
  • the rotor and the housing in particular the inner housing are thermally stressed.
  • the housing are designed clamshell.
  • the inner housing which is also referred to as inner housing, contains the section of steam expansion where the thermal stress is greatest and is characterized by a comparatively colder steam, such as. flows around the exhaust steam, which in turn receives the outer housing.
  • the outer housing is arranged around the inner housing.
  • the inner casings are designed as cast designs, ie they are made in one piece, so to speak, although only one flow area has to withstand the high thermal stresses. Often, a material is selected that withstands the thermal stresses and subsequently used for the entire inner housing. However, this is not cost-oriented optimal, because relatively high-temperature materials are used for areas that are less thermally stressed and where comparatively low temperatures prevail. At these points less high-temperature materials can be used, which are relatively cheaper.
  • EP 1 033 478 discloses a housing which is formed of different materials and is welded together axially.
  • the invention begins, whose task is to specify an inner housing, which is suitable for high thermal stresses and is also low in the production.
  • the object is achieved by a housing for a thermal turbomachine, wherein the housing is formed at least two layers at least from an inner layer and an outer layer, wherein the inner layer has a higher heat-resistant material than the outer layer.
  • Another object of the invention is to provide a method for producing an at least two-layer housing for a thermal turbomachine.
  • the housing is formed in two layers, wherein the inner layer is referred to as inner layer and is thermally heavily loaded during operation and therefore must be made of a higher heat-resistant material than the outer layer, which is referred to as the outer layer.
  • inner layer is thermally heavily loaded during operation and therefore must be made of a higher heat-resistant material than the outer layer, which is referred to as the outer layer.
  • the entire housing will not be formed from the highly heat-resistant material, but it is sufficient if only a part of the housing is formed with the high-temperature resistant material.
  • the inner layer is formed of a nickel-based material.
  • nickel-based materials are suitable for thermal stresses. Especially It is conceivable that 700 ° C steam turbines could be produced with this material in the future.
  • the inner layer is made of Alloy 625. This material has been proven in tests, which could be shown that this material is inexpensive to manufacture and also withstands thermal stresses.
  • a 10 wt .-% chromium steel is used for the outer layer, which is less expensive compared to the nickel-based material, but less heat-resistant.
  • the outer layer may include the material GX12CrMoVNbN9-1. It has also been shown that this material is suitable for use as an outer layer, since this material is inexpensive.
  • chromium steel in particular GX12CrMoVNbN9-1, can be selected, so to speak as material pair, and for the outer layer, a 1-2% by weight chromium steel, such as, for example,. G17CrMoV5-10.
  • the inner layer is adhesively bonded to the outer layer.
  • the process-directed solution according to the invention is widely formed in which the inner and outer castings are heat-treated during solidification.
  • the inner and outer castings may be heat treated after solidification. Subsequently, the heat treatment is in one stage at the lower tempering temperature of the Both materials of the inner and outer casting and carried out for a period of 8 - 12 hours.
  • the outer casting which uses the inner casting as a wall, mechanically improved to be connected to the inner casting.
  • an inner housing is produced with the materials listed above, with the inner layer being extrusion-welded onto the outer layer.
  • the housing can be heat treated after build-up welding.
  • FIG. 1 the upper half of a housing 1 of a thermal turbomachine is shown.
  • the thermal turbomachine can be, for example, a steam turbine.
  • the housing 1 may be, for example, an inner casing of a steam turbine.
  • steam flows between a rotor (not shown) and the inner housing in a flow direction 2.
  • the steam can reach values above 600 ° C and above 300bar.
  • the steam cools and loses pressure in the direction of flow 2.
  • the housing 1 has at least two layers 4, 5.
  • This in FIG. 1 illustrated embodiment includes an inner layer 4 and disposed around the inner layer 4 outer layer 5 on.
  • the inner layer 4 is formed of a higher heat-resistant material than the outer layer. 5
  • the inner layer 4 is made of a nickel-based material.
  • the outer layer 5 is arranged around the inner layer 4.
  • the housing 1 is arranged substantially around the axis of rotation 6, wherein the outer layer 5 is arranged around the inner layer 4 with respect to these axes of rotation 6.
  • the inner layer 4 may be formed from the material Alloy 625 or from a 10 wt .-% chromium steel.
  • the outer layer 5 may be formed of the material GX12CrMoVNbN9-1. Thus, a pair of materials is given, which is suitable for special thermal loads.
  • the inner layer 4 of a 9 - 10 wt .-% chrome steel and the outer layer 5 would form a 1 - 2 wt .-% chromium steel.
  • the materials GX12CrMoVNbN9-1 and for the outer layer 5 the material G17CrMoV5-10 can be selected here as materials for the inner layer 4.
  • the inner layer 4 is connected to the outer layer 5 cohesively with each other.
  • an inner casting is initially cast, which is formed as an inner layer 4.
  • the outer casting is cast, wherein the inner casting is used as a wall and the outer casting is formed as an outer layer 5.
  • the inner and outer castings are heat treated.
  • the heat treatment may also take place during solidification.
  • the heat treatment is carried out in one stage at a tempering temperature corresponding to the lower tempering temperature of the materials of the inner and outer castings.
  • heat treatment is carried out for a period of 8 to 12 hours at the aforementioned tempering temperature.
  • FIG. 2 is a sectional view of the housing 1 according to FIG. 1 to see.
  • the inner layer 4 is in this case limited only to the front region 3 and, as described above, attached to the outer layer 5.
  • a rear region 7 remote from the front region 3 it is possible to dispense with a two-layered design of the housing 1 when the thermal load is lower.
  • the housing 1 can be made multi-layered, wherein the individual materials to be selected is adapted to the thermal stresses.
  • FIG. 3 is a perspective view of the cut housing FIG. 2 to see.
  • the thickness of the inner layer 4 can be varied at the contact points 8 so that no cracks in the outer layer 5 are caused. Furthermore, the thickness of the inner layer 4 can be varied to counteract the thermal stress, which may vary locally.
  • housing additionally form with thermal barrier coatings to reduce the thermal stress.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Heat Treatment Of Articles (AREA)
EP07015627A 2007-08-08 2007-08-08 Procédé destiné à la fabrication d'un boîtier de turbine et boîtier de turbine Withdrawn EP2022951A1 (fr)

Priority Applications (8)

Application Number Priority Date Filing Date Title
EP07015627A EP2022951A1 (fr) 2007-08-08 2007-08-08 Procédé destiné à la fabrication d'un boîtier de turbine et boîtier de turbine
JP2010519422A JP2010535970A (ja) 2007-08-08 2008-07-25 タービン車室の製造方法とそのタービン車室
EP08786470A EP2176522A1 (fr) 2007-08-08 2008-07-25 Procédé pour fabriquer un carter de turbine et carter de turbine
PCT/EP2008/059813 WO2009019152A1 (fr) 2007-08-08 2008-07-25 Procédé pour fabriquer un carter de turbine et carter de turbine
US12/671,069 US20100209234A1 (en) 2007-08-08 2008-07-25 Method for producing a turbine housing and turbine housing
CN2008801023249A CN101779004B (zh) 2007-08-08 2008-07-25 涡轮机壳体制造方法和涡轮机壳体
JP2012005323A JP5450674B2 (ja) 2007-08-08 2012-01-13 タービン車室の製造方法とそのタービン車室
US14/083,866 US9358609B2 (en) 2007-08-08 2013-11-19 Process for producing a turbine housing and turbine housing

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP07015627A EP2022951A1 (fr) 2007-08-08 2007-08-08 Procédé destiné à la fabrication d'un boîtier de turbine et boîtier de turbine

Publications (1)

Publication Number Publication Date
EP2022951A1 true EP2022951A1 (fr) 2009-02-11

Family

ID=39102941

Family Applications (2)

Application Number Title Priority Date Filing Date
EP07015627A Withdrawn EP2022951A1 (fr) 2007-08-08 2007-08-08 Procédé destiné à la fabrication d'un boîtier de turbine et boîtier de turbine
EP08786470A Withdrawn EP2176522A1 (fr) 2007-08-08 2008-07-25 Procédé pour fabriquer un carter de turbine et carter de turbine

Family Applications After (1)

Application Number Title Priority Date Filing Date
EP08786470A Withdrawn EP2176522A1 (fr) 2007-08-08 2008-07-25 Procédé pour fabriquer un carter de turbine et carter de turbine

Country Status (5)

Country Link
US (2) US20100209234A1 (fr)
EP (2) EP2022951A1 (fr)
JP (2) JP2010535970A (fr)
CN (1) CN101779004B (fr)
WO (1) WO2009019152A1 (fr)

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2013000836A1 (fr) 2011-06-29 2013-01-03 Siempelkamp Giesserei Gmbh Fonte à graphite sphéroïdal, en particulier pour applications à haute température
US8834110B2 (en) 2009-10-28 2014-09-16 Alstom Technology Ltd Steam turbine casing system

Families Citing this family (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN111173576A (zh) * 2020-01-15 2020-05-19 中国能源建设集团广东省电力设计研究院有限公司 一种汽轮机

Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1559872A1 (fr) * 2004-01-30 2005-08-03 Siemens Aktiengesellschaft Turbomachine
EP1586394A1 (fr) * 2004-04-08 2005-10-19 Siemens Aktiengesellschaft Turbine à gaz ou diesel comportant des composants résistants aux contraintes
EP1734145A1 (fr) * 2005-06-13 2006-12-20 Siemens Aktiengesellschaft Composant ayant un revêtement avec une barrière thermique et une couche resistante à l'erosion, procéde de manufacture et méthode pour son utilisation

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US4023613A (en) * 1971-12-29 1977-05-17 Toyo Kogyo Co., Ltd. Method of making a composite metal casting
US4005991A (en) * 1971-12-29 1977-02-01 Toyo Kogyo Co., Ltd. Metal made of steel plate and aluminum material
US4066117A (en) * 1975-10-28 1978-01-03 The International Nickel Company, Inc. Spray casting of gas atomized molten metal to produce high density ingots
JPS52138017A (en) * 1976-05-14 1977-11-17 Taiho Kogyo Co Ltd Compound material of aluminium group casting base and ferrous group annexation and its production method
SE431723B (sv) * 1980-06-23 1984-02-27 Sandvik Ab Svetsbar slitdetalj med hog slitstyrka
US5226469A (en) * 1987-07-01 1993-07-13 Kawasaki Jukogyo Kabushiki Kaisha Composite structures and methods of manufacturing the same
US5143140A (en) * 1991-03-04 1992-09-01 Olin Corporation Spray casting of molten metal
WO1997002947A1 (fr) * 1995-07-13 1997-01-30 Advanced Materials Technologies, Inc. Procede de fixation de revetements servant d'ecran thermique sur des substrats en superalliages
US6135194A (en) * 1996-04-26 2000-10-24 Bechtel Bwxt Idaho, Llc Spray casting of metallic preforms
DE59807765D1 (de) * 1997-11-03 2003-05-08 Siemens Ag Turbinengehäuse sowie verfahren zu dessen herstellung
JP2002194525A (ja) * 2000-12-27 2002-07-10 Ishikawajima Harima Heavy Ind Co Ltd 耐摩耗性を有するツインフロー型タービンハウジング及び該ツインフロー型タービンハウジングの耐摩耗溶射方法
DE10112062A1 (de) * 2001-03-14 2002-09-19 Alstom Switzerland Ltd Verfahren zum Zusammenschweißen zweier thermisch unterschiedlich belasteter Teile sowie nach einem solchen Verfahren hergestellte Turbomaschine
US7066235B2 (en) * 2002-05-07 2006-06-27 Nanometal, Llc Method for manufacturing clad components
EP1712745A1 (fr) * 2005-04-14 2006-10-18 Siemens Aktiengesellschaft Elément pour une turbine à vapeur, turbine à vapeur, utilisation et procédé de production d'un tel élément

Patent Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1559872A1 (fr) * 2004-01-30 2005-08-03 Siemens Aktiengesellschaft Turbomachine
EP1586394A1 (fr) * 2004-04-08 2005-10-19 Siemens Aktiengesellschaft Turbine à gaz ou diesel comportant des composants résistants aux contraintes
EP1734145A1 (fr) * 2005-06-13 2006-12-20 Siemens Aktiengesellschaft Composant ayant un revêtement avec une barrière thermique et une couche resistante à l'erosion, procéde de manufacture et méthode pour son utilisation

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US8834110B2 (en) 2009-10-28 2014-09-16 Alstom Technology Ltd Steam turbine casing system
WO2013000836A1 (fr) 2011-06-29 2013-01-03 Siempelkamp Giesserei Gmbh Fonte à graphite sphéroïdal, en particulier pour applications à haute température
DE102011051446A1 (de) 2011-06-29 2013-01-03 Siempelkamp Giesserei Gmbh Gusseisen mit Kugelgraphit, insbesondere für Hochtemperaturanwendungen

Also Published As

Publication number Publication date
US20100209234A1 (en) 2010-08-19
US9358609B2 (en) 2016-06-07
WO2009019152A1 (fr) 2009-02-12
CN101779004A (zh) 2010-07-14
JP5450674B2 (ja) 2014-03-26
EP2176522A1 (fr) 2010-04-21
JP2010535970A (ja) 2010-11-25
US20140076466A1 (en) 2014-03-20
CN101779004B (zh) 2013-03-06
JP2012140961A (ja) 2012-07-26

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