EP2483019A2 - Turbinenschaufel und verfahren zu deren herstellung - Google Patents
Turbinenschaufel und verfahren zu deren herstellungInfo
- Publication number
- EP2483019A2 EP2483019A2 EP10754483A EP10754483A EP2483019A2 EP 2483019 A2 EP2483019 A2 EP 2483019A2 EP 10754483 A EP10754483 A EP 10754483A EP 10754483 A EP10754483 A EP 10754483A EP 2483019 A2 EP2483019 A2 EP 2483019A2
- Authority
- EP
- European Patent Office
- Prior art keywords
- blade
- turbine
- turbine blade
- wall
- produced
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Withdrawn
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
- B22F5/04—Manufacture of workpieces or articles from metallic powder characterised by the special shape of the product of 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
- 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
- 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
- B33Y80/00—Products made by additive manufacturing
-
- 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
- Turbine blade and method for the production thereof The invention relates to. a. to a method having the features according to the preamble of patent claim 1.
- the invention has for its object to provide a method for producing a turbine blade, which allows the production of particularly lightweight, yet stable turbine blades.
- the turbine blade is produced by an additive manufacturing process.
- a significant advantage of the method according to the invention is that it allows a great many degrees of freedom in the design of the turbine blade.
- a turbine blade, the cavities and / or grating structures or the like with the inventive method in a very simple manner be produced, having - for example, can - in contrast to the initially described ⁇ metal casting process.
- Such complicated blade designs can be with a metal casting process not, at least not readily realized.
- a further significant advantage of the method according to the invention is that all features of the turbine blade, at least all of the essential features of the turbine blade, can be produced therewith by one and the same method, ie in other words simultaneously.
- ⁇ play as the additive manufacturing process allows the realization of drainage slots heating openings and / or other holes or recesses in the turbine blade even during the blade production without the need for additional tools or other subsequent procedural ⁇ rensinhoe would be necessary.
- the turbine blade can be produced in layers in a particularly simple and thus advantageous manner.
- a first powder layer is melted locally by means of an energy beam to form a first blade layer; subsequently it, so in this first shovel ⁇ layer, layer by layer brought listed more powder coatings which are melted locally in each case to form further blade layers.
- the turbine blade is formed by a plurality of stacked individual layers.
- the liquid layers may be used, which are hardened locally by means of an energy beam so that the turbine blade is assembled in this manner of layers instead of powder layers.
- the turbine blade is particularly preferably produced in a metal ⁇ metallic powder bed with an electron beam or laser beam.
- the laser or electron beam serves to selectively melt the thin powder layers, which form the turbine blade after cooling.
- CAD data are processed which describe the three-dimensional turbine blade by means of a volume model or a surface model.
- CAD data are converted prior to or during the additive manufacturing process is preferably in ⁇ layer data, where each layer corresponds to a cross-section of the turbine blade with finite thickness.
- the cross-sectional geometry of the turbine blade is preferably produced during the additive manufacturing process by a line-like exposure of the outer contours and a planar exposure of the cross sections to be filled.
- the line-like exposure is realized in the case of a point-shaped characteristic of the energy beam, preferably by a corresponding beam movement.
- a sur fa ⁇ chenetti exposure may be effected for example by a Aneinan ⁇ derreihung of line-like exposure operations.
- Turbines for example steam or gas turbines, can have a multiplicity of turbine blades of various types.
- turbines comprise in many cases shovel Leit ⁇ that are similar to the blades shaped and non-rotating or static for example, may have the shape of a support surface. Guiding blades serve primarily to specifically direct the flow of the flow medium within the turbine.
- turbines may include compressor blades for a compressor section of the turbine. For this reason, it is considered advantageous when a rotor blade, a vane or a compressor blade for a Kom ⁇ pressorabêt of the turbine is made as part of the additive manufacturing process as a turbine blade.
- At least one cavity is formed between blade walls of the turbine blade.
- a cavity is preferably at least from ⁇ section-wise filled with a lattice structure.
- a lattice structure is preferably three-dimensional and may include at ⁇ play filigree, open-cellular SD Jardingitterstruktu ⁇ ren.
- the separate by a cavity blade walls, at least portion ⁇ be connected to one another by lattice structures in order to achieve through the grating structures a support of the blade walls with each other.
- the suction-side blade wall of the turbine blade and the réellesei ⁇ term blade wall of the turbine blade are connected by a entspre ⁇ sponding grating structure at least in sections with each other to increase the stability of the turbine blade as a whole.
- At least one drainage slot is produced in the turbine blade within the scope of the additive manufacturing method.
- Such drainage slots are preferably to ver ⁇ turns, water which is condensed out of the current flowing through the turbine steam flow to dissipate from the near-wall flow of the flow medium.
- the ent ⁇ stationary wall by the condensation drops can lead to erosion damage to the rotor blades of the turbine in subsequent turbine stages.
- erosion damage can be reduced if - as proposed - drainage slits are provided, with which the size of the water droplets can be reduced. Thereby, the water droplets undergo a greater velocity and therefore a smaller Relativgeschwindig ⁇ ness to the rotational movement of the rotor blades, whereby the erosion damage is reduced by the water drops.
- the drainage slots are located near the trailing edge of the turbine blade.
- the drainage slots are in the trailing edge of the next third of the pressure-side blade wall.
- the drainage slots are located, for example, in the front third of the leading edge.
- Arranging drainage slots particularly close to the trailing edge becomes possible if a grid structure is provided within the turbine blade, since in such a case a particularly thin blade wall thickness can be used.
- a grid structure is provided within the turbine blade, since in such a case a particularly thin blade wall thickness can be used.
- other characteristics of the turbine can be realized ⁇ scoop during the additive manufacturing process: For example, Behei ⁇ wetting openings for reduction of the water drops in the turbine and / or other holes in the blade wall made ⁇ the.
- the heat transfer between the heating or cooling medium inside the blade is favored by the lattice structure and its large surface area.
- drainage slots Heating with ⁇ openings, other holes or other openings are at least partially provided with grating structures through which a Support takes place.
- the invention also relates to a turbine blade.
- a turbine blade According to the invention in this respect is provided in that between the blade walls of the turbine blade is a cavity, which is at least partially filled with a Git ⁇ ter Design.
- a significant advantage of the turbine blades according to the invention is the fact that it has a high stability with low weight.
- the turbine blade is a vane, a rotor blade or a compressor blade.
- the suction-side blade wall of the turbine blade and the pressure-side blade wall of the turbine show ⁇ fel are connected together by the lattice structure.
- Such a connection can be a support of the blade walls reach each other and thus ensure a particularly high stability.
- vane walls have openings or holes, these are preferably with a lattice structure - provided - partially ⁇ minimum.
- the invention further relates to a turbine, especially a gas turbine or steam turbine, which is, out ⁇ equipped with at least one turbine blade, as described above.
- the turbine blade within the turbine preferably forms a static guide vane, a rotating rotor blade or a compression vane.
- Turbine blade according to the invention in a three-dimensional representation obliquely from the
- FIG. 2 shows the turbine blade according to FIG. 1 in cross-section
- FIG. 5 shows by way of example a hole in a blade wall of the turbine blade according to FIG. cut, with the hole completely with
- FIG. 6 shows an example of a hole in a blade wall of the turbine blade of Figure 1 in cross-section ⁇ , wherein the hole in part with a
- FIG. 7 shows an example of a hole in a blade wall of the turbine blade of Figure 1 in cross-section ⁇ , wherein the hole from below with a
- FIG. 1 shows a turbine blade 10 which comprises a suction-side blade wall 20 and a pressure-side blade wall 30.
- the suction-side blade wall 20 and the pressure-side blade wall 30 are ⁇ as at a front edge 50 joined together at a trailing edge 40th
- the cavity 55 between the two blade walls 20 and 30 is provided with a three-dimensional lattice structure, which is identified by the reference numeral 60.
- the turbine blade 10 illustrated in Figure 1 is made in the context of an additive manufacturing process, in which the suction-side blade wall 20, the pressure-side blade wall 30 and the lattice structure are formed simultaneously from the same Ma ⁇ TERIAL 60th
- the turbine blade 10 is shown according to figure 1 in cross-section ⁇ .
- the pressure-side blade wall 30 Tur ⁇ depicted of 10 according to Figures 1 and 2 in the plan view in further detail.
- the blade ⁇ wall 30 has two slotted holes 100 and 110 has.
- the slot-shaped holes can serve as drainage slots and / or heating openings, with which water is removed from the near-wall flow of the turbine flowing through the flow medium.
- the arrangement of the slot-shaped holes 100 and 110 is selected such that they are as close as possible to the trailing edge 40, ie the leading edge 50 as far as possible. Particularly be ⁇ vorzugt the slot-shaped holes 100 and 110 are arranged within the trailing edge 40 facing half A of the pressure-side blade wall 30th
- FIG. 4 shows by way of example the suction-side blade wall 20 of the turbine blade 10. It can be seen that a slot-shaped hole 120 which extends through the blade wall 20 is arranged in the region of the front edge 50. Specifics ⁇ DERS preferably, the slit-shaped hole 120 within which the leading edge 50 facing half B of the suction-side blade wall 20.
- the grid structure 60 disposed within the turbine window 10 may be disposed outside of the slot-shaped hole 120 or alternatively extend into the slot-shaped hole 120.
- FIG. 5 shows an embodiment in which the lattice structure 60 extends completely into a hole 200 of the blade wall 210 of the turbine blade 10. The hole 200 is thus bridged by the grid structure 60 and supported by this.
- FIG. 6 shows by way of example an embodiment in which the grating structure 60 extends only partially into the hole 200.
- approximately half the wall thickness d of the grating structural ⁇ tur 60 is detected; the other half of the wall thickness remains free of the grid structure 60.
- FIG 7 an embodiment of a hole 200 is shown, which is not ver see ⁇ with a grating structure 60th
- the grid structure 60 extends only to the lower edge 220 of the hole 200 and adjoins the hole 200 without protruding into the hole itself.
- the lattice structure 60 is therefore located only within the turbine blade and not in the region of the hole 200.
Landscapes
- Engineering & Computer Science (AREA)
- Manufacturing & Machinery (AREA)
- Mechanical Engineering (AREA)
- Physics & Mathematics (AREA)
- Plasma & Fusion (AREA)
- Chemical & Material Sciences (AREA)
- Materials Engineering (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
Description
Claims
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
DE102009048665A DE102009048665A1 (de) | 2009-09-28 | 2009-09-28 | Turbinenschaufel und Verfahren zu deren Herstellung |
PCT/EP2010/063443 WO2011036068A2 (de) | 2009-09-28 | 2010-09-14 | Turbinenschaufel und verfahren zu deren herstellung |
Publications (1)
Publication Number | Publication Date |
---|---|
EP2483019A2 true EP2483019A2 (de) | 2012-08-08 |
Family
ID=43037232
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP10754483A Withdrawn EP2483019A2 (de) | 2009-09-28 | 2010-09-14 | Turbinenschaufel und verfahren zu deren herstellung |
Country Status (4)
Country | Link |
---|---|
US (1) | US20130001837A1 (de) |
EP (1) | EP2483019A2 (de) |
DE (1) | DE102009048665A1 (de) |
WO (1) | WO2011036068A2 (de) |
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DE102011108957B4 (de) * | 2011-07-29 | 2013-07-04 | Mtu Aero Engines Gmbh | Verfahren zum Herstellen, Reparieren und/oder Austauschen eines Gehäuses, insbesondere eines Triebwerkgehäuses, sowie ein entsprechendes Gehäuse |
DE102011080187A1 (de) | 2011-08-01 | 2013-02-07 | Siemens Aktiengesellschaft | Verfahren zum Erzeugen einer Schaufel für eine Strömungskraftmaschine und Schaufel für eine Strömungskraftmaschine |
US11000899B2 (en) | 2012-01-29 | 2021-05-11 | Raytheon Technologies Corporation | Hollow airfoil construction utilizing functionally graded materials |
ITFI20120035A1 (it) * | 2012-02-23 | 2013-08-24 | Nuovo Pignone Srl | "produzione di giranti per turbo-macchine" |
US9074482B2 (en) | 2012-04-24 | 2015-07-07 | United Technologies Corporation | Airfoil support method and apparatus |
US20140126995A1 (en) | 2012-11-06 | 2014-05-08 | General Electric Company | Microchannel cooled turbine component and method of forming a microchannel cooled turbine component |
ITCO20120058A1 (it) * | 2012-12-13 | 2014-06-14 | Nuovo Pignone Srl | Metodi per produrre pale divise di turbomacchine mediante produzione additiva, pale di turbomacchina e turbomacchine |
ITCO20120061A1 (it) * | 2012-12-13 | 2014-06-14 | Nuovo Pignone Srl | Metodi per produrre pale di turbomacchina con canali sagomati mediante produzione additiva, pale di turbomacchina e turbomacchine |
ITCO20120059A1 (it) * | 2012-12-13 | 2014-06-14 | Nuovo Pignone Srl | Metodi per produrre pale cave sagomate in 3d di turbomacchine mediante produzione additiva, pale cave di turbomacchina e turbomacchine |
ITCO20120060A1 (it) * | 2012-12-13 | 2014-06-14 | Nuovo Pignone Srl | Metodi per produrre pale di turbomacchine mediante produzione additiva, pale cave in singolo pezzo di turbomacchina e turbomacchine |
US9393620B2 (en) * | 2012-12-14 | 2016-07-19 | United Technologies Corporation | Uber-cooled turbine section component made by additive manufacturing |
US10018052B2 (en) | 2012-12-28 | 2018-07-10 | United Technologies Corporation | Gas turbine engine component having engineered vascular structure |
WO2014105108A1 (en) | 2012-12-28 | 2014-07-03 | United Technologies Corporation | Gas turbine engine component having vascular engineered lattice structure |
EP2815824A1 (de) * | 2013-06-21 | 2014-12-24 | Siemens Aktiengesellschaft | Verfahren zur Herstellung einer Komponente |
EP2843192B1 (de) * | 2013-08-28 | 2021-03-24 | Safran Aero Boosters SA | Verbundstoff-Laufradschaufel, die durch additives Fertigungsverfahren herstellt wird und entsprechendes Herstellungsverfahren |
EP2843193B1 (de) * | 2013-08-28 | 2020-08-12 | Safran Aero Boosters SA | Verbundstoff-laufradschaufel, die durch additive fertigung erzeugt wird und entsprechendes herstellungsverfahren |
WO2015034815A1 (en) * | 2013-09-06 | 2015-03-12 | United Technologies Corporation | Manufacturing method for a dual wall component |
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US10174621B2 (en) | 2013-10-07 | 2019-01-08 | United Technologies Corporation | Method of making an article with internal structure |
DE102013220983A1 (de) | 2013-10-16 | 2015-04-16 | MTU Aero Engines AG | Laufschaufel für eine Turbomaschine |
US20160245519A1 (en) * | 2013-10-18 | 2016-08-25 | United Technologies Corporation | Panel with cooling holes and methods for fabricating same |
WO2015058043A1 (en) | 2013-10-18 | 2015-04-23 | United Technologies Corporation | Multiple piece engine component |
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US10094287B2 (en) | 2015-02-10 | 2018-10-09 | United Technologies Corporation | Gas turbine engine component with vascular cooling scheme |
US10273192B2 (en) | 2015-02-17 | 2019-04-30 | Rolls-Royce Corporation | Patterned abradable coating and methods for the manufacture thereof |
GB201507130D0 (en) | 2015-04-27 | 2015-06-10 | Alcon Components Ltd | Brake caliper body and method of manufacture of a brake caliper body |
DE102015213087A1 (de) | 2015-07-13 | 2017-01-19 | Siemens Aktiengesellschaft | Schaufel für eine Strömungskraftmaschine und Verfahren zu deren Herstellung |
DE102015213090A1 (de) * | 2015-07-13 | 2017-01-19 | Siemens Aktiengesellschaft | Schaufel für eine Strömungskraftmaschine und Verfahren zu deren Herstellung |
US10046416B2 (en) | 2015-10-15 | 2018-08-14 | Siemens Energy, Inc. | Method of weld cladding over openings |
FR3045755B1 (fr) * | 2015-12-22 | 2019-06-21 | Foundation Brakes France | Procede de fabrication d'un corps d'etrier de frein a disque comprenant une operation de fabrication par impression et notamment une fabrication additive laser |
EP3417090B1 (de) | 2016-02-15 | 2021-07-28 | REM Technologies, Inc. | Chemische verarbeitung von generativ gefertigten werkstücken |
US10221694B2 (en) | 2016-02-17 | 2019-03-05 | United Technologies Corporation | Gas turbine engine component having vascular engineered lattice structure |
DE102016204210A1 (de) * | 2016-03-15 | 2017-09-21 | Airbus Operations Gmbh | Grenzschichtbeeinflussendes aerodynamisches Bauteil und Verfahren zur Herstellung desselben |
DE102016213917A1 (de) | 2016-07-28 | 2018-02-01 | General Electric Technology Gmbh | Verfahren zur Herstellung eines Bauteils und nach dem Verfahren hergestelltes Bauteil |
US10815797B2 (en) | 2016-08-12 | 2020-10-27 | Hamilton Sundstrand Corporation | Airfoil systems and methods of assembly |
US10612387B2 (en) * | 2017-05-25 | 2020-04-07 | United Technologies Corporation | Airfoil damping assembly for gas turbine engine |
US10934850B2 (en) | 2017-08-25 | 2021-03-02 | DOOSAN Heavy Industries Construction Co., LTD | Turbine blade having an additive manufacturing trailing edge |
DE102017215371A1 (de) * | 2017-09-01 | 2019-03-07 | Siemens Aktiengesellschaft | Hohlleitschaufel |
DE102017219333A1 (de) * | 2017-10-27 | 2019-05-02 | Siemens Aktiengesellschaft | Verfahren zur Modifikation von Bauteilen unter Einsatz additiver Fertigung |
EP3508690A1 (de) * | 2018-01-09 | 2019-07-10 | Siemens Aktiengesellschaft | Turbinenschaufelblatt, turbinenschaufel und verfahren zu deren herstellung |
DE102018202194A1 (de) * | 2018-02-13 | 2019-08-14 | MTU Aero Engines AG | Rotorkomponente und Verfahren zum Herstellen derselben |
DE102018211158A1 (de) | 2018-07-06 | 2020-01-09 | MTU Aero Engines AG | Schaufelanordnung für eine Gasturbine und Verfahren zum Herstellen der Schaufelanordnung |
US10774653B2 (en) | 2018-12-11 | 2020-09-15 | Raytheon Technologies Corporation | Composite gas turbine engine component with lattice structure |
EP3674519A1 (de) | 2018-12-27 | 2020-07-01 | Siemens Aktiengesellschaft | Kühlbares bauteil für einen strömungsmotor und zugehöriges fertigungsverfahren |
EP3674518A1 (de) | 2018-12-27 | 2020-07-01 | Siemens Aktiengesellschaft | Kühlbares bauteil für einen strömungsmotor und zugehöriges fertigungsverfahren |
DE102019207553A1 (de) * | 2019-05-23 | 2020-11-26 | Siemens Aktiengesellschaft | Herstellungsverfahren mit additivem Herstellen eines Formkörpers, Herstellung einer Form und Wärmebehandlung |
CN114961873B (zh) * | 2021-02-25 | 2024-05-31 | 中国航发商用航空发动机有限责任公司 | 可恢复变形的叶片及包含其的涡扇发动机 |
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2009
- 2009-09-28 DE DE102009048665A patent/DE102009048665A1/de not_active Withdrawn
-
2010
- 2010-09-14 US US13/498,415 patent/US20130001837A1/en not_active Abandoned
- 2010-09-14 WO PCT/EP2010/063443 patent/WO2011036068A2/de active Application Filing
- 2010-09-14 EP EP10754483A patent/EP2483019A2/de not_active Withdrawn
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Also Published As
Publication number | Publication date |
---|---|
WO2011036068A2 (de) | 2011-03-31 |
WO2011036068A3 (de) | 2011-12-01 |
DE102009048665A1 (de) | 2011-03-31 |
US20130001837A1 (en) | 2013-01-03 |
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