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, according to current knowledge, 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 replaced by a comparatively colder steam, such as e.g. 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-optimal because relatively high-temperature materials are used for areas that are less prone to thermal stress and where comparatively low temperatures prevail. At these points less high-temperature materials can be used, which are relatively cheaper.
• EP 1 033 478 a housing is disclosed, 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 the two-layer housing.
• 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 from a nickel-based material.
• nickel-based materials are suitable for thermal stresses.
• 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 in particular be the material GX12CrMoVNbN9-l. It has also been shown that this material is suitable for use as an outer layer, since this material is inexpensive.
• chromium chromium steel in particular GX12CrMoVNbN9-1
• material pair 9-10% chromium steel in particular GX12CrMoVNbN9-1
• chromium chromium steel e.g. G17CrMoV5-10.
• the inner layer is joined to the outer layer in a materially bonded manner.
• 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 the solidification.
• the heat treatment will be carried out in one stage at the lower tempering temperature of the two materials of the inner and outer castings and for a period of 8 to 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 shows a perspective view of the upper half of a housing for a turbomachine
• FIG. 2 shows a sectional view through the housing of FIG. 1 in side view
• Figure 3 is a perspective view of the cut-open housing shown in Figure 2.
• FIG. 1 shows the upper half of a housing 1 of a thermal turbomachine.
• 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 may assume values of about 600 0 C and 300 bar.
• the steam cools and loses pressure in the direction of flow 2.
• the housing 1 has at least two layers 4, 5.
• the exemplary embodiment illustrated in FIG. 1 comprises an inner layer 4 and an outer layer 5 arranged around the inner layer 4.
• 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-l. 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-l 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 joined to the outer layer 5 in a substance-tight manner.
• 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 which corresponds 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 shows a sectional view of the housing 1 according to FIG.
• 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.
• Figure 3 is a perspective view of the cut housing of Figure 2 can be seen.
• 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 in order to counteract the thermal load, which may be locally different borrowed. It is useful that in Figures 1 - 3 form shown Ge ⁇ housing with additional 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)

Priority Applications (5)

Applications Claiming Priority (2)

Related Child Applications (2)

Publications (1)

Family

ID=39102941

Family Applications (1)

Country Status (5)

Families Citing this family (3)

Citations (3)

Family Cites Families (14)

• 2007
  • 2007-08-08 EP EP07015627A patent/EP2022951A1/de not_active Withdrawn
• 2008
  • 2008-07-25 WO PCT/EP2008/059813 patent/WO2009019152A1/de not_active Ceased
  • 2008-07-25 US US12/671,069 patent/US20100209234A1/en not_active Abandoned
  • 2008-07-25 JP JP2010519422A patent/JP2010535970A/ja not_active Withdrawn
  • 2008-07-25 EP EP08786470A patent/EP2176522A1/de not_active Withdrawn
  • 2008-07-25 CN CN2008801023249A patent/CN101779004B/zh not_active Expired - Fee Related
• 2012
  • 2012-01-13 JP JP2012005323A patent/JP5450674B2/ja not_active Expired - Fee Related
• 2013
  • 2013-11-19 US US14/083,866 patent/US9358609B2/en not_active Expired - Fee Related

Patent Citations (3)

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