EP1029154B1 - Turbinengehäuse sowie verfahren zu dessen herstellung - Google Patents
Turbinengehäuse sowie verfahren zu dessen herstellung Download PDFInfo
- Publication number
- EP1029154B1 EP1029154B1 EP98961038A EP98961038A EP1029154B1 EP 1029154 B1 EP1029154 B1 EP 1029154B1 EP 98961038 A EP98961038 A EP 98961038A EP 98961038 A EP98961038 A EP 98961038A EP 1029154 B1 EP1029154 B1 EP 1029154B1
- Authority
- EP
- European Patent Office
- Prior art keywords
- layer
- outer layer
- pressure
- turbine
- inner layer
- 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.)
- Expired - Lifetime
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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
- F01D25/08—Cooling; Heating; Heat-insulation
- F01D25/14—Casings modified therefor
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B22—CASTING; POWDER METALLURGY
- B22C—FOUNDRY MOULDING
- B22C9/00—Moulds or cores; Moulding processes
- B22C9/10—Cores; Manufacture or installation of cores
-
- 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
- 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 turbine housing with a multilayer housing wall between a one pressure chamber sealing inner layer and a force-bearing outer layer has a pressure-resistant intermediate layer for thermal insulation. she further relates to a method of manufacturing a such housing.
- turbine housing is used here understood the outer casing of a high pressure steam turbine.
- a turbine working as an engine the potential Energy of a flowing working medium, e.g. Gas or steam, converted into mechanical work.
- a flowing working medium e.g. Gas or steam
- the turbine as an essential elements an impeller and a fixed idler.
- a steam turbine as Steam, which serves as a medium for the flow medium, performs work until condensation relaxed.
- the design of the steam turbine is particularly affected by the vapor states, i.e. the steam pressure and the steam temperature.
- the housing parts required for high steam conditions effect temperature-resistant materials with a large wall thickness Considerable given the high cost of such materials Material costs.
- An increase in wall thickness stands but also the aspect of manufacturability, in particular the castability of the alloys at the necessary Wall thicknesses. These are other aspects to consider Operating behavior of the turbine with respect to that of the heating mouth
- the cooling behavior of the housing parts influences the arrival and departure times as well as handling due to the wall thickness increasing mass. It should also be borne in mind that the wall thickness of the turbine housing is not only increasing Pressure increases, but also with increasing temperature the strength of the usual materials decreases.
- a steam turbine From AT-PS 381 367 is also known in the steam room a steam turbine has a metallic insulation body, in particular in the form of metal fibers. Since the im Insulation body provided with the steam chamber as the insulating When the medium serving steam comes into direct contact, the Metal parts, on the one hand, must be large enough to prevent them from Steam flow entrained resulting in the destruction of the turbine to become. On the other hand, it is sufficiently loose Filling of the metal parts required so that the steam the Flow through the insulation body at least approximately unhindered can. Adequate thermal insulation and pressure resistance is not with such a metallic insulation body achieved.
- the invention is therefore based on the object of a multilayer Specify turbine housing for a high pressure turbine, the by using a particularly suitable, pressure-resistant intermediate layer for thermal insulation, a realization of even higher ones Vapor states, i.e. a high pressure and a high temperature, of the flow medium. Furthermore, a particularly suitable process for producing a multi-walled Turbine housing specified for a high-pressure turbine become.
- Turbine housing a three-layer housing wall with a pressure-resistant and heat-insulating liner made of a non-metallic Bulk on the one between the pressure chamber sealing inner layer and a load-bearing outer layer is provided.
- the use of sand as is particularly expedient Bulk for the liner fulfills the function of a heat-insulating in a particularly advantageous manner Layer, its thickness or radial extent the temperature is reduced (temperature gradient).
- the Liner absorbs the compressive forces of the inner layer and conducts this further. It is therefore both pressure resistant also temperature-resistant, but has no sealing function.
- the lowest possible thermal conductivity is Advantage as this is the thickness of the insulation layer and the Heat flow determined. It is essential that when using of sand as an intermediate layer this as opposed to one massive material, such as a metallic Material, achieved a relatively good thermal insulation and itself in terms of the required shape, particularly good to the circumstances adapts.
- the inner position of the housing wall only fulfills the function the sealing of the pressure chamber and separates the medium from the other locations. This is one in relation to the whole Thickness of the wall requires small wall thickness, as this Inner layer is supported on the outer layers and the existing ones Internal pressure only needs to be transferred to this.
- the inner layer consists preferably of a temperature-resistant and stretchable material, as this is the mechanically and thermally conditional strains of the other layers must follow. As a material for the inner layer is therefore expediently more heat resistant Chrome steel or cast steel, preferably 10% chrome steel with a ferritic / bainitic mixed structure.
- the outer layer serves to accommodate the insulation layer pressures passed on due to the medium pressure and carries it through the internal pressure in the turbine housing generated forces.
- the outer layer thus brings the counterforce to the pressure force of the medium.
- As a material for the The outer layer is also expediently a ferritic / bainitic Mixed structure used. Because the supporting outer layer due to the internal thermal insulation layer in shape the poured intermediate layer is clearly below the medium temperature lying temperature, but can here an inexpensive material (GGG or GS) with comparative low or low temperature resistance be used. At the same time, a small wall thickness can be realized as a comparatively low temperature high tolerable voltage is present. So be considerable savings in terms of material costs achieved.
- an outer layer composed of two partial layers these preferably have different coefficients of thermal expansion on.
- the properties the outer layer can be varied, e.g. regarding their Thermal expansion and compliance to Internal pressure of the turbine housing. This can reduce the stresses the inner layer due to thermal expansion and of the internal pressure can be reduced.
- One is also special flexible adjustment of stiffness and thermal expansion taking into account a particularly low load on the inner layer possible for the respective application.
- the outer of the two partial layers can also be made Sheet metal layers can be built up or wound, in which case the relative thin-walled inner partial layer only to separate the Liner serves from the winding layer.
- the structure is preferably reinforced with carbon fibers Material used. Overall, the material concept can the respective, by the pressure and temperature of the medium specific application can be adapted.
- the intermediate layer Insulation material in a prefabricated wall component the space formed and introduced compacted.
- the wall component can already be in one piece or constructed in two parts from the outer layer and from the inner layer his.
- the one that forms the intermediate layer Insulation or filler material during assembly the outer and inner layer in the space.
- the outer and inner layer can then be cast or be formed from a sheet material.
- the advantages achieved with the invention are in particular in that by inserting a heat insulating Liner in the form of a non-metallic, inorganic Bulk material, preferably sand, between a comparatively thin-walled inner layer and a correspondingly thin-walled outer layer a multi-layer turbine housing on the one hand Cracks in the layers due to thermal expansion avoided is.
- a heat insulating Liner in the form of a non-metallic, inorganic Bulk material, preferably sand
- a multi-layer turbine housing on the one hand
- Cracks in the layers due to thermal expansion avoided is.
- sand as an intermediate layer, be simultaneously the tasks of thermal insulation and mechanical Compressive strength met particularly reliably, whereby the sand caused by thermal stresses compared to a solidified intermediate or insulating layer can follow particularly well.
- the one used to apply force Outside location kept at a particularly low temperature level
- each wall layer can be designed to save material and be optimized with regard to their function.
- the inner layer and the outer layer are pretensioned to a certain extent, so that the bulk material is compressed between the outer layer and the inner layer is present.
- the Outer layer in one piece or composed of partial layers, which then preferably have a different coefficient of thermal expansion exhibit. This will remove the from the inner layer elongations to be absorbed, so that this the imprinted by the stretch behavior of the network partners Deformations especially avoiding the risk of cracking can reliably follow. By cooling the outer layer will further reduce their temperature levels achieved.
- the turbine housing constructed in this way therefore also fulfills very high temperatures and operational temperature changes as well as at high steam pressures - and thus at high ones Vapor conditions - reliably the function of sealing the enclosed medium on the one hand and the generation of a Counterforce to the compressive force of the enclosed medium on the other hand.
- the high pressure steam turbine or high pressure turbine 1 comprises a turbine shaft 2 with blades attached to it 4 and an inner casing 8 carrying a guide vanes 6 as well as an outer housing or pressure housing surrounding this 10.
- incoming live steam D is along the guide and Blades 4, 6 guided and relaxed while doing work, causing the turbine shaft 2 to rotate is transferred.
- the relaxed steam D 'leaves the high pressure turbine via an outflow opening 14, for example to a Medium pressure turbine (not shown).
- An between the inner housing 8 and the pressure housing 10 formed pressure chamber 18 is in the embodiment with the live steam D - with a steam temperature T of z. B. 600 ° C at a vapor pressure p of z. B. 300bar - acted upon.
- the housing wall 16 comprises an inner layer 20 which is directly exposed to live steam D. This is temperature-resistant and consists, for example, of heat-resistant steel.
- the inner layer 20 serves to seal the pressure space 18 formed between the inner housing 8 and the pressure housing 10 of the high-pressure steam turbine and separates the steam D from the subsequent layers of the housing wall 16.
- the layer thickness dI of the inner layer 20, ie its expansion in the radial direction R, is compared to the total thickness d of the housing wall 16 is small. Since the inner layer 20 transmits the pressure p of the steam D acting on it, ie its pressure force F p , to the other layers, the material used only has to have the highest possible elasticity and high temperature resistance.
- An intermediate layer 22 which is designed in the form of a bulk material, adjoins the inner layer 20 for thermal insulation.
- sand S is expediently used as bulk material.
- the intermediate layer 22 is pressure-resistant or pressure-resistant, so that an incompressible insulation layer is formed.
- their layer thickness dZ causes the temperature T to decrease, as is illustrated by the temperature diagram on the left in FIG. 2 along the extent in the radial direction R of the housing wall 16.
- the intermediate layer 22, on the other hand serves to receive and transmit the compressive force F p of the steam D acting on the inner layer 20 to an outer layer 24.
- the outer layer 24 forms the force-bearing element of the overall assembly of the housing wall 16 and absorbs the pressures passed on through the intermediate layer 22 as a result of the vapor pressure p in the pressure chamber 18. It thus bears the pressure force F p generated by the internal pressure between the inner housing 8 and the pressure or outer housing 10.
- the temperature to be controlled by the outer layer 24 is - as illustrated in the diagram on the left in FIG. 2 - much lower than the temperature T of the steam D due to the temperature gradient in the radial direction R along the intermediate layer 22.
- the material used for the outer layer 24, e.g. cast iron, can have a low temperature resistance compared to the inner layer 20 exhibit. It can also be a compared to the intermediate layer 22 low wall thickness or layer thickness dA can be realized.
- the basic radial stress curve ⁇ is illustrated in the diagram on the right in FIG. 2.
- An insulating layer 26 can be used for additional thermal insulation be provided for thermal insulation, the outer layer 24 and thus encloses the entire assembly of the housing wall 16.
- a Cooling channel system 28 may be provided, which is from a coolant K, for example, already relaxed steam D ' becomes.
- the cooling channel system 28 can alternatively or additionally also be provided in the intermediate layer 22 or on the outside the outer layer 24. Due to the thickness dW and by the additional cooling of the outer layer 24 and / or the Intermediate layer 22 can set its temperature in such a targeted manner be that on the one hand low heat losses via the Housing wall 16 occur, and that on the other hand, the force-bearing Function is further improved.
- FIG 3 shows a further variant with one of two partial layers 24a and 24b built-up outer layer 24.
- the two partial layers 24a and 24b consist of different materials thermal expansion coefficient (material pairing).
- FIG. 4 also shows a variant in which the outer layer 24 again from a first partial layer 24a 'and a second Partial layer 24b 'is executed.
- the inner, second partial layer 24b ' serves only to separate the Intermediate layer 22 and the wound or with tension element layers provided partial layer 24a 'and can therefore be thin-walled accordingly be executed.
- the partial layer 24a 'can also consist of steel layers (Sheet metal layers) wound or built up.
- FIG. 5 shows a casting mold 100 with a filling opening (feeder) 102 and with an access opening (riser) 103 as well with a number of cores 104a, 104b for.
- the mold 100 forms in connection with the arrangement shown the cores 104a, 104b are rotationally symmetrical and U-shaped Hollow profile 106 with an external cavity or Cavity leg for the later outer layer 24 and an inner one Cavity leg for the later inner layer 20 the housing wall 16.
- the cavity profile 106 to be filled with a casting material G. is by means of a model representing the housing wall 16 in the lost mold 100 made of fine-grained molding material F made. To do this, a sub-box 100a and then an upper box 100b as mold boxes of the mold 100 stamped on the model.
- the mineral Molding material F, the mineral components provided with binders contains, solidified. After the model from the Mold boxes 100a, 100b has been excavated, the Cores 104a, 104b inserted into the mold 100. You can the cores 104a, 104b in the longitudinal and circumferential directions by means of Core iron be reinforced.
- the mold boxes 100a, 100b have been closed is, the casting material G via the filling opening 102 in filled the hollow profile 106, with the riser 103 Flow the casting material G back into the hollow section 106 can.
- a circumferential collar 107 on the core 104b is used for Absorption of forces or moments due to core weight or due to core buoyancy during the casting process may occur.
- the casting mold 100 of the cast housing wall 16 removed. Then be the central one representing the housing interior 108 Core 104a and partially the annular intermediate core 104b away. The between the outer layer 24 and the inner layer 20th the part of the core 104b lying on the housing wall 16 remains as Intermediate layer 22 (FIG 6) in the cast component.
- This along the dashed dividing line 109 separated from the core 104b Part is thus advantageously insulation material at the same time inside the housing wall 16 a manufacturing step regarding the realization of the intermediate layers 22 saved.
- the corresponding one Part of the core 104b as an intermediate layer 22 during the solidification process of the casting material G within the cavity profile 106 between the outer layer 24 and the inner layer 20 of the Housing wall 16 embedded positively and non-positively.
- FIG. 6 shows sections of a preferred additional Core bearing in the apex area of the hollow profile 106 are several, e.g. B. four, distributed over the circumference Pin 110 provided. This over part of its length in the space between the outer layer 24 and the inner layer 20 protruding pins 110 lie on one on the core 104a provided collar 111 on, for. B. in recesses provided there.
- the pins 110 are preferably part of this of the core 104b. Following the casting process, the Pin 110 removed. Can in the resulting openings then appropriate thread for screwing on a housing cover be introduced, which is then tightly welded becomes.
- each wall layer can be designed to save 20 to 24 materials and be optimized in terms of their function. That I the inner layer 20 on the intermediate layer 22 and this on the Outer layer 24 supports and the existing internal pressure only this must be transferred in relation to the whole Wall thickness small wall thickness of the inner layer 20 required.
- the casting material used is preferably 9% to 11% chromium steel, especially 10% chrome steel, with a ferritic / bainitic Mixed structure, used.
- FIG 7 shows a simplified representation of the one above Line of symmetry or axis of rotation 112 lying part of a Mold 100 ', which - analogous to FIG 5 - an upper mold box 100b 'represents.
- the one above the axis of rotation 112 lying part of the housing interior 108 filling core 104a defines an L-shaped cavity profile 120, whose legs 120a and 120b in turn fine-grained molding material F modeled existing mold 100 ' have been.
- the inner layer is first 20 by filling the cavity 120 by means of the casting material G manufactured.
- the outer layer 24 are produced. It makes a difference the mold 100 'of the alternative according to FIG 7 in essentially due to the radial expansion of the core 104a, 104b. This represents the later housing interior 108 and the one required for the inner layer 20 and the intermediate layer 22 Room.
- the provided cavity 121 in turn has an L-shaped profile with a short leg 121a and a long leg 121b.
- Cavity 120 is the short leg 121a on the short legs 120a of the inner layer 20 opposite Arranged side and aligned to the axis of rotation 112.
- FIG. 9 shows the production of the multi-layer housing wall 16 in another manufacturing step in which, together with the housing interior 108 representing core 104a either the 7 in the first manufacturing step prefabricated inner layer 20 or that according to the alternative 8 prefabricated outer layer 24 in the corresponding Mold 100 'is inserted. At the same time it becomes the Core 104b representing intermediate layer 22 in the previously corresponding modeled mold 100 'inserted. Depending on the alternative the cavity 120 for the inner layer 20 or the cavity 121 is formed for the outer layer 24. Subsequently this cavity 120 or 121 is poured out. Even with the Housing wall 16 produced in this way remains Core 104b as an intermediate layer 22 in the cast component.
- Insulation material also in the required wall thickness and Shaping applied to the already prefabricated layer 24, 20 become.
- the insulation material should be like this applied and possibly reinforced that this corresponds to the requirements of the further casting process. to Reinforcement can be used, for example, core iron.
- the shape of the insulation material can also by special Core forms are made into the ones already made or prefabricated layer 24, 20 inserted and with insulation material is reshaped. This way with insulation material formed and inserted into the mold 100 ' Casting then practically forms a core, the one the layers 24, 20 of the later housing wall 10 already contains and after the further casting process in the finished Component remains.
- a reliable connection of the one after the other Castings or layers 24, 20 on the contact surfaces of the Legs 120a and 121b or 120b and 121a are made by positive locking, Non-positive, material or a combination of these inferences.
- a subsequent connection establishment for example, by welding.
- By the casting order is a desired one due to shrinkage Compression of the insulation material between the surrounding Wall parts or wall layers 24, 22 can be reached. This effect can be achieved through appropriate casting technology Measures, for example through targeted cooling, are supported become.
- a U-shaped profile part 106 'as Housing wall 16 according to one of the so-called forming, joining or separating or ablative manufacturing processes manufactured.
- a cylindrical housing wall 16 for producing the U-profile part 106 'with an inner layer 20 and a die Outer layer 24 representing legs are cast.
- a die Outer layer 24 representing legs
- the outer layer 24 With a combination of low-melting material, e.g. GGG, for the outer layer 24 and high-melting material, e.g. Ferrite or austenite is suitable for the inner layer 20 particularly - just like that described with reference to FIGS. 7 to 9 Manufacturing process - that illustrated with reference to FIG 11 Production method.
- the two Layers 24 and 20 separately, e.g. in a reshaping manufacturing process, manufactured and then together Formation of the U-profile part 106 'assembled.
- the composite Profiles of the outer layer 24 and the inner layer 20 can be different.
- the insulation material is in the form of the bulk material S during the joining of the two layers 24 and 20 in the Gap 122 introduced as an intermediate layer 22 and then compacted.
- poured sand S is in contrast to one massive material, such as a metallic Material, achieved a relatively good thermal insulation, whereby the sand S is special in terms of the required shape adapts well to the circumstances.
- the sand S should be compacted State between the outer layer 24 and the inner layer 20. To maintain a minimum pressure on the Sand S, the inner layer 20 and the outer layer 24 are biased.
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- General Engineering & Computer Science (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
- Supercharger (AREA)
Description
- FIG 1
- in Seitenansicht einen Längsschnitt durch eine Hochdruck-Dampfturbine mit einem Innengehäuse und mit einem Außengehäuse,
- FIG 2 bis 4
- einen Ausschnitt II, III bzw. IV des Außengehäuses gemäß FIG 1 mit alternativen Varianten einer mehrlagigen Gehäusewand,
- FIG 5
- 10 in perspektivischer, teilweise aufgeschnittener Darstellung einen mehrlagigen Gehäuseabschnitt in einer Gußform mit mehreren Kernen,
- FIG 6
- im Längsschnitt einen Ausschnitt VI aus FIG 5 mit einer zusätzlichen Kernlagerung,
- FIG 7 bis 9
- im Längsschnitt Gußformen zur stufenweisen Herstellung eines mehrlagigen Gehäuseabschnitts, sowie
- FIG 10 und 11
- die Einbringung einer Zwischenlage in einen doppelwandigen, ein- bzw. mehrteiligen Gehäusewandabschnitt im Längsschnitt.
Claims (10)
- Turbinengehäuse, insbesondere Außengehäuse (10) einer Hochdruckturbine, mit einer mehrlagigen Gehäusewand (16), die zwischen einer einen Druckraum (18) abdichtenden Innenlage (20) und einer krafttragenden Außenlage (24) eine druckfeste Zwischenlage (22) zur Wärmeisolierung aufweist,
dadurch gekennzeichnet, dass die Zwischenlage (22) ein nichtmetallisches Schüttgut (S), vorzugsweise Sand, ist. - Turbinengehäuse nach Anspruch 1,
dadurch gekennzeichnet, dass die Zwischenlage (22) im Vergleich zur Innenlage (20) und zur Außenlage (24) dicker ist. - Turbinengehäuse nach Anspruch 1 oder 2,
dadurch gekennzeichnet, dass die Innenlage (20) und/oder die Außenlage (24) aus warmfestem Metall, vorzugssweise aus 10%-Chrom-Stahl, besteht. - Turbinengehäuse nach einem der Ansprüche 1 bis 3,
dadurch gekennzeichnet, dass die Außenlage (24) aus mindestens zwei Teillagen (24a,24b) unterschiedlicher thermischer Ausdehnungseigenschaften aufgebaut ist. - Turbinengehäuse nach Anspruch 4,
dadurch gekennzeichnet, dass die äußere Teillage (24a') gewickelt ist. - Turbinengehäuse nach einem der Ansprüche 1 bis 5,
dadurch gekennzeichnet, dass eine die Außenlage (24) mindestens teilweise umschließende Isolierschicht (26) vorgesehen ist. - Turbinengehäuse nach einem der Ansprüche 1 bis 6,
dadurch gekennzeichnet, dass Mittel (28,K) zur Kühlung der Außenlage (24) und/oder der Zwischenlage (22) vorgesehen sind. - Verfahren zur Herstellung eines Turbinengehäuses mit einer mehrlagigen Gehäusewand (16) mit einer einen Gehäuseinnenraum (108) abdichtenden Innenlage (20) und mit einer druckfesten Zwischenlage (22) zur Wärmeisolierung sowie mit einer krafttragenden Außenlage (24),
dadurch gekennzeichnet, dass in einen Zwischenraum (122) eines U-förmigen Profilteils (106') ein Füllstoff als Zwischenlage (22) eingebracht wird, wobei als Füllstoff ein nichtmetallisches Schüttgut (S), vorzugsweise Sand, verwendet wird. - Verfahren nach Anspruch 15,
dadurch gekennzeichnet, dass das U-förmige Profilteil (106') mehrteilig ist, wobei während oder nach dem Zusammenfügen der Außenlage (24) und der Innenlage (20) der Füllstoff (E) als Zwischenlage (22) eingebracht wird. - Verfahren nach Anspruch 15 oder 16,
dadurch gekennzeichnet, dass die Außenlage (24) und/oder die Innenlage (20) aus warmfestem Metall, vorzugsweise aus 9%- bis 11%-Chrom-Stahl, gegossen wird.
Applications Claiming Priority (5)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
DE19748540 | 1997-11-03 | ||
DE19748540 | 1997-11-03 | ||
DE19819508 | 1998-04-30 | ||
DE1998119508 DE19819508A1 (de) | 1998-04-30 | 1998-04-30 | Verfahren zur Herstellung eines mehrwandigen Druckgehäuses |
PCT/DE1998/003122 WO1999023359A1 (de) | 1997-11-03 | 1998-10-21 | Turbinengehäuse sowie verfahren zu dessen herstellung |
Publications (2)
Publication Number | Publication Date |
---|---|
EP1029154A1 EP1029154A1 (de) | 2000-08-23 |
EP1029154B1 true EP1029154B1 (de) | 2003-04-02 |
Family
ID=26041297
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP98961038A Expired - Lifetime EP1029154B1 (de) | 1997-11-03 | 1998-10-21 | Turbinengehäuse sowie verfahren zu dessen herstellung |
Country Status (7)
Country | Link |
---|---|
US (1) | US6315520B1 (de) |
EP (1) | EP1029154B1 (de) |
JP (1) | JP4234904B2 (de) |
KR (1) | KR20010072537A (de) |
CN (1) | CN1119507C (de) |
DE (1) | DE59807765D1 (de) |
WO (1) | WO1999023359A1 (de) |
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US10919106B2 (en) * | 2017-06-09 | 2021-02-16 | General Electric Company | Ultrasonic welding of annular components |
US10844744B2 (en) * | 2017-09-01 | 2020-11-24 | Southwest Research Institute | Double wall supercritical carbon dioxide turboexpander |
KR102121800B1 (ko) | 2018-06-15 | 2020-06-11 | 신한대학교 산학협력단 | 사용자화장품을 이용한 메이크업 정보제공시스템 및 그 방법 |
Family Cites Families (10)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
DE564761C (de) | 1930-07-08 | 1932-11-23 | Escher Wyss Maschf Ag | Dampf- oder Gasturbine, insbesondere fuer hohen Druck und hohe Temperatur |
GB1178609A (en) * | 1967-10-16 | 1970-01-21 | Stavebni Isolace Narodni Podni | Improvements in or relating to Thermal Insulation Suitable for Machinery |
JPS5311922B2 (de) * | 1973-07-09 | 1978-04-25 | ||
AT381367B (de) | 1984-06-20 | 1986-10-10 | Jericha Herbert Dipl Ing Dr Te | Innere isolation fuer hochtemperatur-dampfturbinen |
FR2607198B1 (fr) * | 1986-11-26 | 1990-05-04 | Snecma | Carter de compresseur adapte pour le pilotage actif de ses dilatations et son procede de fabrication |
DE3712830A1 (de) * | 1987-04-15 | 1988-11-03 | Mtu Muenchen Gmbh | Turbotriebwerk mit einem berstschutzring |
DE3843663A1 (de) * | 1988-12-23 | 1990-06-28 | Gruenzweig & Hartmann Montage | Waermedaemmung fuer heisse gase fuehrende gussbauteile |
DE4331060C1 (de) * | 1993-09-13 | 1994-06-30 | Gruenzweig & Hartmann Montage | Wärmedämmanordnung |
DE19535227A1 (de) | 1995-09-22 | 1997-03-27 | Asea Brown Boveri | Gehäuse für Strömungsmaschinen |
EP0891471B1 (de) * | 1996-04-11 | 2002-06-26 | Siemens Aktiengesellschaft | Verfahren und vorrichtung zum schubausgleich bei einer turbomaschine |
-
1998
- 1998-10-21 WO PCT/DE1998/003122 patent/WO1999023359A1/de not_active Application Discontinuation
- 1998-10-21 DE DE59807765T patent/DE59807765D1/de not_active Expired - Lifetime
- 1998-10-21 JP JP2000519196A patent/JP4234904B2/ja not_active Expired - Fee Related
- 1998-10-21 EP EP98961038A patent/EP1029154B1/de not_active Expired - Lifetime
- 1998-10-21 KR KR1020007004798A patent/KR20010072537A/ko not_active Application Discontinuation
- 1998-10-21 CN CN98810587A patent/CN1119507C/zh not_active Expired - Fee Related
-
2000
- 2000-05-03 US US09/564,899 patent/US6315520B1/en not_active Expired - Lifetime
Also Published As
Publication number | Publication date |
---|---|
KR20010072537A (ko) | 2001-07-31 |
JP2001522013A (ja) | 2001-11-13 |
WO1999023359A1 (de) | 1999-05-14 |
CN1277652A (zh) | 2000-12-20 |
US6315520B1 (en) | 2001-11-13 |
JP4234904B2 (ja) | 2009-03-04 |
CN1119507C (zh) | 2003-08-27 |
EP1029154A1 (de) | 2000-08-23 |
DE59807765D1 (de) | 2003-05-08 |
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