EP3280559A1 - Verfahren zum fertigen einer turbinenschaufel mittels elektronenstrahlschmelzen - Google Patents
Verfahren zum fertigen einer turbinenschaufel mittels elektronenstrahlschmelzenInfo
- Publication number
- EP3280559A1 EP3280559A1 EP16719389.5A EP16719389A EP3280559A1 EP 3280559 A1 EP3280559 A1 EP 3280559A1 EP 16719389 A EP16719389 A EP 16719389A EP 3280559 A1 EP3280559 A1 EP 3280559A1
- Authority
- EP
- European Patent Office
- Prior art keywords
- blade
- section
- blade root
- airfoil
- emb
- 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.)
- Ceased
Links
Classifications
-
- 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
-
- 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
-
- 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
- B22F5/04—Manufacture of workpieces or articles from metallic powder characterised by the special shape of the product of turbine blades
-
- 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
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/12—Blades
-
- 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
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/12—Blades
- F01D5/14—Form or construction
-
- 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
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/12—Blades
- F01D5/14—Form or construction
- F01D5/18—Hollow blades, i.e. blades with cooling or heating channels or cavities; Heating, heat-insulating or cooling means on blades
-
- 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
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/12—Blades
- F01D5/28—Selecting particular materials; Particular measures relating thereto; Measures against erosion or corrosion
-
- 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
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/30—Fixing blades to rotors; Blade roots ; Blade spacers
-
- 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]
-
- 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
- F05D2230/23—Manufacture essentially without removing material by permanently joining parts together
- F05D2230/232—Manufacture essentially without removing material by permanently joining parts together by welding
-
- 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
- F05D2230/23—Manufacture essentially without removing material by permanently joining parts together
- F05D2230/232—Manufacture essentially without removing material by permanently joining parts together by welding
- F05D2230/234—Laser welding
-
- 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
- F05D2300/00—Materials; Properties thereof
- F05D2300/10—Metals, alloys or intermetallic compounds
- F05D2300/17—Alloys
- F05D2300/175—Superalloys
-
- 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
- F05D2300/10—Metals, alloys or intermetallic compounds
- F05D2300/17—Alloys
- F05D2300/177—Ni - Si alloys
-
- 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 present invention relates to a method for manufacturing a turbine blade having a blade root, an adjoining the blade root blade ⁇ sheet section and an adjoining the airfoil portion blade tip portion, said blade root portion, the airfoil portion and the vane tip sections are cohesively connected to one another, and wherein at least one extends as a cooling channel serving ⁇ hollow space through the blade foot and in the display ⁇ felblattabites.
- Turbine blades of the type mentioned. The one
- Blade root portion, an airfoil portion and a blade tip portion are known in the art in a variety of configurations and are installed, for example, in gas turbines as blades, where they converted the flow energy of relaxing hot gas in Ro ⁇ tations energie.
- Massively formed turbine blades are not subject to practical limitations in terms of their manufacture because they can be made by machining a blank alone. Cooled turbine blades, however, are usually made by casting because of their complex shapes caused by the cavities.
- at least one core for generating the at least one cavity is inserted into a casting mold defining the outer surface of the turbine blade. This is aligned with positioning in the mold to set the required wall thickness of the turbine show ⁇ fel. Then, the space remaining between the mold and the core is filled with heated liquid casting material. After solidification of the casting material of the core may then be removed chemically, for example using a suitable solvent, to expose this Wei ⁇ se the cavity.
- LMD laser metal deposition
- metallic materials with a very high y x content can not or only very poorly be processed, for example nickel-base alloys from which turbine blades subject to high thermal stress are frequently produced.
- EBM method Electro Beam Melting
- the present invention provides a method for manufacturing a turbine blade of the type mentioned, which is characterized in that at least ⁇ the blade section using an EMB process is produced in layers, and that of the blade tip portion after removing baked-powder material the at least one cavity is produced under a set ⁇ a different manufacturing technology.
- the blade airfoil portion is first generated without the blade tip ⁇ section using an EMB method, at least one cavity, which is defined by the Schaufelblattab ⁇ section remains open at least at the top and thus accessible for removal of baked powder material. Accordingly, the blade section using the method of the invention from almost any metal ⁇ metallic materials or alloys can be produced quickly and inexpensively, which is particularly in the prototype production of great advantage. That's how it works
- manufacture a blade section from a superalloy for example, a nickel-base superalloy.
- a superalloy for example, a nickel-base superalloy.
- Blade root portion and the airfoil portion together in layers using an EMB process Herge ⁇ provides.
- This variant is characterized by the fact that a large part of the turbine blade can be generated almost directly from a CAD drawing.
- the blade root is made be ⁇ riding as a prefabricated component, wherein the airfoil section is constructed using an EMB method in layers on the Schaufelfußab ⁇ cut, or wherein the blade section in advance using a EMB method layerwise Her ⁇ made and then connected to the blade root section material ⁇ conclusively, in particular welded.
- the airfoil portion and the blade root portion are made of made of a first material
- the Schaufelspitzenab ⁇ section is made of a second material which is different from the first material, wherein the second material is in particular a material having a better oxidation resistance than the first material.
- the blade tip section In the blade tip section is rather ei ⁇ ne high oxidation resistance in the foreground.
- the blade tip section can be made of IN738LC.
- the blade root and the blade ⁇ blade portion of a superalloy are advantageously prepared, and in particular from a nickel-based alloy.
- Superalloys, and especially nickel-based alloys have proven to be materials in particular for gas turbine blades in the past.
- insbeson ⁇ particular using an LMD method is for the production of blade tip portion wige ⁇ from advantage that using the LMD method, the material can be applied directly to the airfoil section, without it requires the formation of a powder bed.
- the turbine blade 1 comprises a blade root section 2, which adjoins the blade root section 2
- the cavity 5 is presently divided by a partition 6, which extends radially outwardly from the blade root section 2 in the direction of the Schau ⁇ felspitzenabiteses 4, whereby the cavity 5 is formed substantially U-shaped overall. It should be understood, however, that the shape and position of the partition 6 as well as the partition 6 itself are optional. Also, of course, a plurality of partitions 6 may be provided which divide the cavity 5 in a different manner.
- the turbine blade 1 in the present case is a rotor blade of a gas turbine.
- Grundsharm ⁇ Lich the turbine blade 1 but can also be used in other turbine nen.
- the root portion 2 and the Schaufelblattab be ⁇ section 3 together using a method EMB-layers of a super alloy, in the present of a nickel-base superalloy.
- the blade root section 2 and then the Schaufelblattab ⁇ section 3 layer by layer of a superalloy particulate kel having powder bed generated by melting regions of the powder bed using an electron beam in a known manner be ⁇ and solidified in accordance with the ⁇ .
- the powder bed is also baked in areas in which no component layer is generated, in order to prevent in this way the "smoke effect" already described above.
- cooling fluid outlet openings 8 can already be produced during the additive production of the airfoil section 3. Alternatively, however, they can also be introduced later, for example by means of drilling or the like.
- the blade root section 2 can alternatively already be provided as a prefabricated component.
- the Schau ⁇ felfußabites 2 for example, be provided as a casting.
- the blade tip section 4 is manufactured in a further step using a different manufacturing technology.
- a material is used which differs from the material of the blade 2 and Schaufelfußabêtes ⁇ sheet section. 3
- the material of the show felspitzenabiteses 4 is in particular such a material that has a better oxidation resistance than the material of the blade root section 2 and the Schau ⁇ felblattabiteses 3.
- IN738LC is used as the material of the blade tip section 4.
- the blade tip portion 4 is constructed in the present case in layers using a method LMD at the free end of the actor ⁇ felblattabiteses. 3
- an alternative additive Ferti ⁇ transmission method can be used, as long as this is not is a powder bed based method.
- Al ternatively ⁇ it is also possible to use the blade tip section 4 as a prefabricated component, for example in the form of a casting, cohesively with the blade 3 to verbin ⁇ to weld in particular.
- a significant advantage of the method according to the invention consists in the fact that turbine blades, cut off their Schaufelfuß- and airfoil sections of materials of ho ⁇ hem Y x consist stake, in particular superalloys, are easy and inexpensive to produce in very short time intervals, which is particularly suited for rapid prototyping is beneficial.
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Manufacturing & Machinery (AREA)
- Chemical & Material Sciences (AREA)
- Materials Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Composite Materials (AREA)
- Physics & Mathematics (AREA)
- Plasma & Fusion (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
- Powder Metallurgy (AREA)
Abstract
Description
Claims
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
DE102015210744.2A DE102015210744A1 (de) | 2015-06-12 | 2015-06-12 | Verfahren zum Fertigen einer Turbinenschaufel |
PCT/EP2016/059412 WO2016198210A1 (de) | 2015-06-12 | 2016-04-27 | Verfahren zum fertigen einer turbinenschaufel mittels elektronenstrahlschmelzen |
Publications (1)
Publication Number | Publication Date |
---|---|
EP3280559A1 true EP3280559A1 (de) | 2018-02-14 |
Family
ID=55860849
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP16719389.5A Ceased EP3280559A1 (de) | 2015-06-12 | 2016-04-27 | Verfahren zum fertigen einer turbinenschaufel mittels elektronenstrahlschmelzen |
Country Status (5)
Country | Link |
---|---|
US (1) | US20180161872A1 (de) |
EP (1) | EP3280559A1 (de) |
CN (1) | CN107708896A (de) |
DE (1) | DE102015210744A1 (de) |
WO (1) | WO2016198210A1 (de) |
Families Citing this family (10)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
EP3028793A1 (de) * | 2014-12-04 | 2016-06-08 | Siemens Aktiengesellschaft | Verfahren zur Herstellung einer Laufschaufel |
DE102016206547A1 (de) | 2016-04-19 | 2017-10-19 | Siemens Aktiengesellschaft | Verfahren zur modularen additiven Herstellung eines Bauteils und Bauteil |
US10337341B2 (en) | 2016-08-01 | 2019-07-02 | United Technologies Corporation | Additively manufactured augmentor vane of a gas turbine engine with additively manufactured fuel line extending therethrough |
US10436447B2 (en) * | 2016-08-01 | 2019-10-08 | United Technologies Corporation | Augmentor vane assembly of a gas turbine engine with an additively manufactured augmentor vane |
US20180093414A1 (en) * | 2016-10-03 | 2018-04-05 | Gerald Martino | Method for making vehicular brake components by 3d printing |
DE102017215209A1 (de) * | 2017-08-31 | 2019-02-28 | MTU Aero Engines AG | Additiv hergestelltes Bauteil, insbesondere für eine Gasturbine, sowie Verfahren zu dessen Herstellung |
DE102018200287A1 (de) | 2018-01-10 | 2019-07-11 | Siemens Aktiengesellschaft | Turbomaschineninnengehäuse |
JP6964544B2 (ja) * | 2018-03-16 | 2021-11-10 | 株式会社神戸製鋼所 | 造形物の製造方法及び造形物 |
CN108757555B (zh) * | 2018-03-28 | 2020-06-05 | 中国航空制造技术研究院 | 一种航空发动机的空心叶片结构及其设计方法 |
DE102019201085A1 (de) * | 2019-01-29 | 2020-07-30 | Siemens Aktiengesellschaft | Herstellungsverfahren für ein Bauteil mit integrierten Kanälen |
Family Cites Families (12)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
DE102006049216A1 (de) * | 2006-10-18 | 2008-04-24 | Mtu Aero Engines Gmbh | Hochdruckturbinen-Rotor und Verfahren zur Herstellung eines Hochdruckturbinen-Rotors |
EP2522810A1 (de) * | 2011-05-12 | 2012-11-14 | MTU Aero Engines GmbH | Verfahren zum generativen Herstellen eines Bauteils, insbesondere eines Verdichterschaufelelements, sowie ein derartiges Bauteil |
DE102011111011A1 (de) * | 2011-08-18 | 2013-02-21 | Mtu Aero Engines Gmbh | Verstellschaufelelement und Verfahren zum Ausbilden, Reparieren und/oder Austauschen eines derartigen Verstellschaufelelements |
US9266170B2 (en) * | 2012-01-27 | 2016-02-23 | Honeywell International Inc. | Multi-material turbine components |
WO2014052323A1 (en) * | 2012-09-28 | 2014-04-03 | United Technologies Corporation | Uber-cooled turbine section component made by additive manufacturing |
US9393620B2 (en) * | 2012-12-14 | 2016-07-19 | United Technologies Corporation | Uber-cooled turbine section component made by additive manufacturing |
US20150034266A1 (en) * | 2013-08-01 | 2015-02-05 | Siemens Energy, Inc. | Building and repair of hollow components |
US20150086408A1 (en) * | 2013-09-26 | 2015-03-26 | General Electric Company | Method of manufacturing a component and thermal management process |
DE102013220467A1 (de) * | 2013-10-10 | 2015-05-07 | MTU Aero Engines AG | Rotor mit einem Rotorgrundkörper und einer Mehrzahl daran angebrachter Laufschaufeln |
DE102013220983A1 (de) * | 2013-10-16 | 2015-04-16 | MTU Aero Engines AG | Laufschaufel für eine Turbomaschine |
EP3068975B1 (de) * | 2013-11-11 | 2020-11-25 | United Technologies Corporation | Bauteil eines gasturbinentriebwerks und zugehörige herstellungsverfahren |
US20160319690A1 (en) * | 2015-04-30 | 2016-11-03 | General Electric Company | Additive manufacturing methods for turbine shroud seal structures |
-
2015
- 2015-06-12 DE DE102015210744.2A patent/DE102015210744A1/de not_active Withdrawn
-
2016
- 2016-04-27 EP EP16719389.5A patent/EP3280559A1/de not_active Ceased
- 2016-04-27 US US15/578,896 patent/US20180161872A1/en not_active Abandoned
- 2016-04-27 CN CN201680034139.5A patent/CN107708896A/zh active Pending
- 2016-04-27 WO PCT/EP2016/059412 patent/WO2016198210A1/de active Application Filing
Also Published As
Publication number | Publication date |
---|---|
WO2016198210A1 (de) | 2016-12-15 |
US20180161872A1 (en) | 2018-06-14 |
CN107708896A (zh) | 2018-02-16 |
DE102015210744A1 (de) | 2016-12-15 |
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Legal Events
Date | Code | Title | Description |
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