WO2019063329A1 - Carter de turbine équipé d'un ajutage et procédé de production d'un carter de turbine équipé d'un ajutage - Google Patents

Carter de turbine équipé d'un ajutage et procédé de production d'un carter de turbine équipé d'un ajutage Download PDF

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Publication number
WO2019063329A1
WO2019063329A1 PCT/EP2018/075021 EP2018075021W WO2019063329A1 WO 2019063329 A1 WO2019063329 A1 WO 2019063329A1 EP 2018075021 W EP2018075021 W EP 2018075021W WO 2019063329 A1 WO2019063329 A1 WO 2019063329A1
Authority
WO
WIPO (PCT)
Prior art keywords
turbine housing
nozzle
cutout
turbine
producing
Prior art date
Application number
PCT/EP2018/075021
Other languages
German (de)
English (en)
Inventor
Holger HERTWIG
Mario Rolle
Original Assignee
Siemens Aktiengesellschaft
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 Aktiengesellschaft filed Critical Siemens Aktiengesellschaft
Publication of WO2019063329A1 publication Critical patent/WO2019063329A1/fr

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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
    • F01D25/30—Exhaust heads, chambers, or the like
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B22—CASTING; POWDER METALLURGY
    • B22F—WORKING METALLIC POWDER; MANUFACTURE OF ARTICLES FROM METALLIC POWDER; MAKING METALLIC POWDER; APPARATUS OR DEVICES SPECIALLY ADAPTED FOR METALLIC POWDER
    • B22F10/00—Additive manufacturing of workpieces or articles from metallic powder
    • B22F10/20—Direct sintering or melting
    • B22F10/25—Direct deposition of metal particles, e.g. direct metal deposition [DMD] or laser engineered net shaping [LENS]
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B22—CASTING; POWDER METALLURGY
    • B22F—WORKING METALLIC POWDER; MANUFACTURE OF ARTICLES FROM METALLIC POWDER; MAKING METALLIC POWDER; APPARATUS OR DEVICES SPECIALLY ADAPTED FOR METALLIC POWDER
    • B22F10/00—Additive manufacturing of workpieces or articles from metallic powder
    • B22F10/20—Direct sintering or melting
    • B22F10/28—Powder bed fusion, e.g. selective laser melting [SLM] or electron beam melting [EBM]
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B22—CASTING; POWDER METALLURGY
    • B22F—WORKING METALLIC POWDER; MANUFACTURE OF ARTICLES FROM METALLIC POWDER; MAKING METALLIC POWDER; APPARATUS OR DEVICES SPECIALLY ADAPTED FOR METALLIC POWDER
    • B22F5/00—Manufacture of workpieces or articles from metallic powder characterised by the special shape of the product
    • B22F5/009—Manufacture of workpieces or articles from metallic powder characterised by the special shape of the product of turbine components other than turbine blades
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B22—CASTING; POWDER METALLURGY
    • B22F—WORKING METALLIC POWDER; MANUFACTURE OF ARTICLES FROM METALLIC POWDER; MAKING METALLIC POWDER; APPARATUS OR DEVICES SPECIALLY ADAPTED FOR METALLIC POWDER
    • B22F7/00—Manufacture of composite layers, workpieces, or articles, comprising metallic powder, by sintering the powder, with or without compacting wherein at least one part is obtained by sintering or compression
    • B22F7/06—Manufacture of composite layers, workpieces, or articles, comprising metallic powder, by sintering the powder, with or without compacting wherein at least one part is obtained by sintering or compression of composite workpieces or articles from parts, e.g. to form tipped tools
    • B22F7/062—Manufacture of composite layers, workpieces, or articles, comprising metallic powder, by sintering the powder, with or without compacting wherein at least one part is obtained by sintering or compression of composite workpieces or articles from parts, e.g. to form tipped tools involving the connection or repairing of preformed parts
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B22—CASTING; POWDER METALLURGY
    • B22F—WORKING METALLIC POWDER; MANUFACTURE OF ARTICLES FROM METALLIC POWDER; MAKING METALLIC POWDER; APPARATUS OR DEVICES SPECIALLY ADAPTED FOR METALLIC POWDER
    • B22F7/00—Manufacture of composite layers, workpieces, or articles, comprising metallic powder, by sintering the powder, with or without compacting wherein at least one part is obtained by sintering or compression
    • B22F7/06—Manufacture of composite layers, workpieces, or articles, comprising metallic powder, by sintering the powder, with or without compacting wherein at least one part is obtained by sintering or compression of composite workpieces or articles from parts, e.g. to form tipped tools
    • B22F7/08—Manufacture of composite layers, workpieces, or articles, comprising metallic powder, by sintering the powder, with or without compacting wherein at least one part is obtained by sintering or compression of composite workpieces or articles from parts, e.g. to form tipped tools with one or more parts not made from powder
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
    • B23P—METAL-WORKING NOT OTHERWISE PROVIDED FOR; COMBINED OPERATIONS; UNIVERSAL MACHINE TOOLS
    • B23P15/00—Making specific metal objects by operations not covered by a single other subclass or a group in this subclass
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B33—ADDITIVE MANUFACTURING TECHNOLOGY
    • B33Y—ADDITIVE MANUFACTURING, i.e. MANUFACTURING OF THREE-DIMENSIONAL [3-D] OBJECTS BY ADDITIVE DEPOSITION, ADDITIVE AGGLOMERATION OR ADDITIVE LAYERING, e.g. BY 3-D PRINTING, STEREOLITHOGRAPHY OR SELECTIVE LASER SINTERING
    • B33Y10/00—Processes of additive manufacturing
    • 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
    • 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
    • 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
    • F05D2230/22—Manufacture essentially without removing material by sintering
    • 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
    • F05D2230/30—Manufacture with deposition of material
    • F05D2230/31—Layer deposition
    • F05D2230/311—Layer deposition by torch or flame spraying
    • 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
    • F05D2230/313—Layer deposition by physical vapour deposition
    • 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
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02P—CLIMATE CHANGE MITIGATION TECHNOLOGIES IN THE PRODUCTION OR PROCESSING OF GOODS
    • Y02P10/00—Technologies related to metal processing
    • Y02P10/25—Process efficiency

Definitions

  • the invention relates to a turbine housing with a connecting piece through which a flow of fluid can flow through a cutout in the door ⁇ binengephaseuse into the turbine housing, wherein the nozzle in the region of the cutout is formed such that the turbinenachsparallele extension of the nozzle is smaller than the extension of Neck, perpendicular to the turbine axis. Furthermore, the invention relates to a method for producing such a nozzle.
  • Generic turbine housings are typical of steam turbine housings, for example. There is a conflict of objectives with regard to two different requirements. One requirement is to design the turbine as short as possible in order to construct material and material
  • the other requirement is to provide the inflowing medium enough surface to flow in order to keep the inflow velocity in a meaningful range and to keep the deflection of the flow as low as possible. This makes it possible to realize a high degree of efficiency combined with low noise development.
  • the two requirements are taken into account that the nozzle is formed on the turbine housing in the region of the cutout in such a way that the turbine- axial extension of the nozzle is smaller than the extension of the nozzle, at right angles to the turbine axis.
  • the production of such a nozzle is associated with great expense.
  • two possible methods were used in particular. In the first method, the nozzle is poured.
  • the casting allows the use of considerable constructive degrees of freedom, whereby the turbine nachsparalle Extension of the nozzle can be greatly reduced, gleichzei ⁇ tig the inflow can be opened wide transversely to the turbine axis.
  • a disadvantage of the casting process is that it is very complicated and expensive. At the same time, there are only a few manufacturers that can produce turbine housings for large turbines.
  • the object is achieved with respect to the turbine housing with Stut ⁇ zen by the features of independent claim 1 ge ⁇ .
  • the object is solved by the features of independent claims 4 and 5. Further embodiments of the invention, which are used individually or in combination with each other, are the subject of the dependent claims.
  • the turbine housing according to the invention with a nozzle, through which a flow fluid can flow through a cutout in the turbine housing ⁇ in the turbine housing, wherein the nozzle is formed in the region of the cutout such that the turbinesachsparallele extension of the nozzle, is smaller than the extension of the nozzle, perpendicular to the turbine axis, is characterized in that the Stut ⁇ zen is formed by an additive manufacturing process.
  • the turbine housing without cutout for the inflow or with a cutout for the inflow but can be made with very large additions.
  • the actual required shape of the cut is then in each case, based on 3D geometry data, etc. This allows a more or less standard housing are used and the respective required or needed in each case fitting can easily, individually, in shape and size to the turbine housing are attached.
  • additive manufacturing processes combine different production methods that have a three-dimensional structure.
  • additive processes are also referred to by the terms "additive manufacturing” or "3D printing”.
  • To produce the connection piece is insbeson ⁇ wider free space method such as build-up welding or cold gas spraying is suitable, as well as powder bed process such as in particular the selective laser melting (SLM) or the selective La ⁇ sersintern (SLS).
  • SLM selective laser melting
  • SLS selective La ⁇ sersintern
  • the free space method is particularly suitable when the nozzle is applied directly to the Victoriage ⁇ housing.
  • the powder bed process are more likely to as ⁇ useful in making the nozzle first individually and then, for example, by means of material-fit, or non-positive connection with the turbine housing to connect.
  • An essential advantage of the invention is that the production can be completely digitized and automated. Furthermore, no complicated Sch detailkonstruktio ⁇ nen or manufacturing by die are necessary, which can be achieved significant cost savings.
  • the shape and size of the nozzle is completely variable and can be easily adapted to the respective requirements. Furthermore, there is an advantage in the variability of the materials used. Thus, different materials can be used in particular for the nozzle and the turbine housing. A location-dependent material thickness can also be achieved.
  • the turbine housing with the connecting piece is characterized by an extremely attrac ⁇ -reaching optics, analogous to a cast execution.
  • An embodiment of the invention provides that the ratio of the turbine-parallel extension a of the nozzle to the extension b of the nozzle perpendicular to the turbine axis a / b ⁇ 0.8 is preferably a / b ⁇ 0.6. This will the Forde ⁇ alloys in the shortest possible design and sufficient
  • Another embodiment of the invention provides that the projection of the cut is essentially a legal ⁇ corner surface.
  • the rectangular area allows the optimal size ratio of short design and large
  • the turbine housing as a kind of standard housing without any cut Herge ⁇ provides are.
  • the cutouts are then subsequently introduced into the turbine housing and the respective neck is formed around the cutout in the turbine housing by means of the additive manufacturing process.
  • the process thus offers a far-reaching individual production and arrangement of the
  • the actual necessary size and shape of the cutout is cut out of the turbine housing based on 3D geo-geometry, for example by means of laser beam or water jet cutting.
  • the cutting out of the cutout can be completely digitized / automated.
  • very precise cutouts can be introduced into the turbine housing.
  • the nozzle is then formed around the cutout in the turbine housing in a further method step. The formation of the nozzle takes place by means of an additive manufacturing process.
  • the process differs from the previously-described case ⁇ NEN method in that cut-outs in the turbine housing are already provided.
  • the cutouts for the inflow in the outer housing are found ⁇ with very large allowances ago and in a further step expanding the cut is made to the final dimensions.
  • the Ver ⁇ cut can be reduced when introducing the cutouts, where ⁇ fail by the manufacturing cost of the turbine housing.
  • the cutouts with the appropriate allowance are provided at the points at which the nozzle is provided later, wherein it is not yet necessary to determine what size of the nozzle to be attached later has.
  • the Aus ⁇ cut is chosen so small that all possible sizes of nozzles can be attached to the turbine housing.
  • An embodiment of the invention provides that the nozzle is applied directly to the turbine housing by means of an additive manufacturing process.
  • additi ves ⁇ manufacturing method for this purpose especially the so-called clearance procedures, in particular deposition welding or cold gas spraying are suitable. Subsequent attachment of the stub to the turbine housing is eliminated.
  • a further embodiment of the invention provides that the nozzle is manufactured separately by means of an additive manufacturing process and is subsequently fastened to the turbine housing.
  • the powder bed process is suitable here as an additive production process, and in particular selective laser melting (SLM) or selective laser sintering (SLS).
  • SLM selective laser melting
  • SLS selective laser sintering
  • An embodiment of the method provides that the nozzle material and / or non-positively on the turbine housing be ⁇ consolidates.
  • brazing or welding of the connection piece on the turbine housing comes into consideration as cohesive connection.
  • a frictional connection between the nozzle and the turbine housing can be realized for example by means of a flange connection.
  • Figure 1 is a plan view of an inventive Turbi ⁇ nengetude with nozzle
  • Figure 2 is a side view of the turbine housing shown in Figure 1 with nozzle.
  • FIG. 1 shows a turbine housing 1, for example a
  • the nozzle 2 is formed in the region of the cutout 3 such that the turbine-axial extension a of the nozzle 2 is smaller than the extent b of the nozzle 2 at right angles to the turbine axis 4.
  • the nozzle 2 is formed by an additive manufacturing method .
  • the nozzle may be applied directly to the turbine housing 1, or initially prepared separately and then attached to the turbine housing 1.
  • the attachment of the nozzle 2 before ⁇ preferably material and / or non-positively.
  • a substance-compatible compound is suitable here
  • a frictional connection can be made in particular via a flange not shown here.
  • the ratio of turbine-parallel extension a of the nozzle 2 to the extension b of the nozzle 2 at right angles to the turbine axis is a / b ⁇ 0.8, preferably a / b ⁇ 0.6. In this way, the requirement is taken into account, on the one hand, to build the turbine housing 1 in the axial direction as short as possible and, on the other hand, to give the flow fluid enough area to flow into the turbine housing 1.
  • the Turbi ⁇ nengepuruse 1 side facing away from the nozzle can be formed in particular for connection of leads as a circular shape.
  • the additive manufacturing process of the nozzle 2 enables light while a fully coming variability both in form and in the size of the nozzle 2.
  • a further advantage of addi ⁇ tive manufacturing process is that the use ⁇ th material can vary and selected according to Anforde ⁇ conclusions can be.
  • a location-dependent material thickness of the nozzle 2 can be realized.
  • a corresponding shape of a nozzle 2 can be seen in particular from FIG.
  • the nozzle 2 is formed the turbine housing 2 facing area at the bottom, that the projection of the section is substantially a right-angled ⁇ surface.
  • rich Be ⁇ 2 is, however, formed in a substantially circular, so that the feed lines which usually have a circular cross section are easily connectable to the connecting piece.
  • the cutout in the turbine housing 1 can be completely digitized / automated and example, ⁇ be formed by laser or water jet cutting. Also, the formation of the nozzle 2 by means of additive manufacturing process can be completely digitized / automated. This significantly reduces the production times and the production costs.
  • a significant advantage of the turbine housing 1 according to the invention with nozzle 2 is that the turbine housing 1 can be largely manufactured as a standard part and the corresponding cutouts can be individually introduced.
  • the formation of the nozzle 2 around the cutouts he ⁇ subsequently also follows completely individual means additive manufacturing process. Form and size of the nozzle 2 are essentially freely selectable, as well as the material to be used, which only needs to be selected to fit the requirements.
  • the turbine housing 1 with ports 2 which is formed by an additive manufacturing method, and optical advantages, since such turbine housing with connection pieces has an extremely attractive appearance analogous to a Gussausnch ⁇ tion.

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  • Engineering & Computer Science (AREA)
  • Manufacturing & Machinery (AREA)
  • Mechanical Engineering (AREA)
  • Chemical & Material Sciences (AREA)
  • Materials Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Physics & Mathematics (AREA)
  • Plasma & Fusion (AREA)
  • Composite Materials (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Powder Metallurgy (AREA)

Abstract

L'invention concerne un carter de turbine (1) équipé d'un ajutage (2) permettant à un écoulement fluidique de pénétrer dans le carter de turbine (1) par une découpe (3) dans le carter de turbine (1). L'ajutage (2) est agencé dans la zone de la découpe (3) de manière que la longueur (a) de cet ajustage (2) parallèlement à l'axe de la turbine soit inférieure à la longueur (b) de cet ajutage (2) perpendiculairement à l'axe de la turbine. L'ajutage (2) selon l'invention est produit par fabrication additive. Cette invention se rapporte en outre à des procédés pour produire un tel carter de turbine (1).
PCT/EP2018/075021 2017-09-26 2018-09-17 Carter de turbine équipé d'un ajutage et procédé de production d'un carter de turbine équipé d'un ajutage WO2019063329A1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE102017217034.4 2017-09-26
DE102017217034.4A DE102017217034A1 (de) 2017-09-26 2017-09-26 Turbinengehäuse mit Stutzen sowie Verfahren zum Herstellen eines Turbinengehäuses mit Stutzen

Publications (1)

Publication Number Publication Date
WO2019063329A1 true WO2019063329A1 (fr) 2019-04-04

Family

ID=63708305

Family Applications (1)

Application Number Title Priority Date Filing Date
PCT/EP2018/075021 WO2019063329A1 (fr) 2017-09-26 2018-09-17 Carter de turbine équipé d'un ajutage et procédé de production d'un carter de turbine équipé d'un ajutage

Country Status (2)

Country Link
DE (1) DE102017217034A1 (fr)
WO (1) WO2019063329A1 (fr)

Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JPS62129506A (ja) * 1985-11-29 1987-06-11 Fuji Electric Co Ltd 蒸気タ−ビンの車室構造
US20040107573A1 (en) * 2002-12-04 2004-06-10 Tomko Andrew John Methods for manufacturing a nozzle box assembly for a steam turbine
US20120087784A1 (en) * 2010-10-12 2012-04-12 General Electric Company Inducer for gas turbine system
EP2783775A2 (fr) * 2013-03-25 2014-10-01 MAHLE International GmbH Utilisation d'un procédé de fabrication additif pour la fabrication d'un composant pour un véhicule automobile
FR3021994A1 (fr) * 2014-06-04 2015-12-11 Snecma Ecope pour un systeme de refroidissement et de controle des jeux d'une turbine de turbomachine
DE102016203901A1 (de) * 2016-03-10 2017-09-14 MTU Aero Engines AG Verfahren und Vorrichtung zum Herstellen zumindest eines Bauteilbereichs eines Bauteils

Family Cites Families (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE102012018649A1 (de) * 2012-09-20 2014-03-20 Liebherr-Aerospace Lindenberg Gmbh Klappenaktuator
DE102013110417A1 (de) * 2013-09-20 2015-03-26 Thyssenkrupp Steel Europe Ag Metallpulver für pulverbasierte Fertigungsprozesse und Verfahren zur Herstellung eines metallischen Bauteils aus Metallpulver
DE102014012480B4 (de) * 2014-08-27 2016-06-09 Rosswag Gmbh Herstellverfahren für eine Beschaufelung einer Strömungsmaschine, Beschaufelung einer Strömungsmaschine und Laufrad
DE102015221166A1 (de) * 2015-10-29 2017-05-04 Mahle International Gmbh Fluidsystem mit Verbindungsbauteil

Patent Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JPS62129506A (ja) * 1985-11-29 1987-06-11 Fuji Electric Co Ltd 蒸気タ−ビンの車室構造
US20040107573A1 (en) * 2002-12-04 2004-06-10 Tomko Andrew John Methods for manufacturing a nozzle box assembly for a steam turbine
US20120087784A1 (en) * 2010-10-12 2012-04-12 General Electric Company Inducer for gas turbine system
EP2783775A2 (fr) * 2013-03-25 2014-10-01 MAHLE International GmbH Utilisation d'un procédé de fabrication additif pour la fabrication d'un composant pour un véhicule automobile
FR3021994A1 (fr) * 2014-06-04 2015-12-11 Snecma Ecope pour un systeme de refroidissement et de controle des jeux d'une turbine de turbomachine
DE102016203901A1 (de) * 2016-03-10 2017-09-14 MTU Aero Engines AG Verfahren und Vorrichtung zum Herstellen zumindest eines Bauteilbereichs eines Bauteils

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Publication number Publication date
DE102017217034A1 (de) 2019-03-28

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