EP2584146A1 - Method for producing a rotor blade for a fluid flow engine and corresponding rotor blade - Google Patents
Method for producing a rotor blade for a fluid flow engine and corresponding rotor blade Download PDFInfo
- Publication number
- EP2584146A1 EP2584146A1 EP11186202.5A EP11186202A EP2584146A1 EP 2584146 A1 EP2584146 A1 EP 2584146A1 EP 11186202 A EP11186202 A EP 11186202A EP 2584146 A1 EP2584146 A1 EP 2584146A1
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- European Patent Office
- Prior art keywords
- blade
- hollow
- support structure
- hollow blade
- area
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- 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.)
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Classifications
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- 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
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- 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
- F01D5/147—Construction, i.e. structural features, e.g. of weight-saving hollow blades
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- 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
- F01D5/26—Antivibration means not restricted to blade form or construction or to blade-to-blade connections or to the use of particular materials
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- 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
Definitions
- the invention relates to a method for producing a blade for a turbomachine and the blade produced by the method.
- a gas turbine has a compressor, for example in an axial construction, in which air is compressed before it is introduced into a combustion chamber of the gas turbine for combustion.
- the compressor has fixed vanes and rotating blades.
- the vanes and blades are exposed to corresponding stresses during operation of the gas turbine that reduce the life of the vanes and blades.
- the guide vanes and the blades undergo a stress due to vibrations and a centrifugal force load.
- the centrifugal load increases with increasing length and mass of the blades and with increasing speed and is particularly high at the blade roots of the blades.
- cracks can form, which can lead to the failure of the blade during operation of the gas turbine.
- conventionally particularly strong materials e.g. Titanium, superalloys based on nickel or composites, used for the blades.
- the object of the invention is to provide a method for producing a blade for a turbomachine and the blade produced by the method, wherein the blade is easily formed and yet has a high strength.
- the method according to the invention for producing a moving blade for a turbomachine has the following steps Constructing the blade as a hollow blade whose wall thickness decreases radially outwards and dimensioned such that the blade withstands their gas force load and centrifugal load during operation of the turbomachine; Determining at least one region of the hollow blade that is excessively loaded by blade vibrations during operation of the turbomachine; Thickening the hollow blade inwardly at the area and / or providing a support structure in the interior of the hollow blade at the area, so that the strength of the hollow blade is locally increased at this area, whereby the hollow blade resists the blade vibrations during operation of the turbomachine.
- the inventive method is particularly suitable for long blades, because in them the centrifugal load is particularly high.
- the blade By making the blade as the hollow blade, its mass is reduced compared to a full blade, which advantageously reduces its centrifugal load during operation.
- the wall thickness decreases radially outward, it is advantageous in the area of the blade root, ie in the region where the centrifugal force load is highest, advantageously the strongest.
- Another advantage of the method is that the hollow blade can be produced with a low material requirement.
- the hollow blade Due to the fact that the hollow blade has thickenings and / or the support structure on the regions which are excessively loaded by vibrations, it is advantageously reinforced selectively at these areas. At the same time, the hollow blade is made thin at less loaded areas, so that overall the hollow blade can be advantageously completed with a small mass. By the support structure can advantageously be increased, the strength of the hollow blade.
- the method comprises the following step: Completing the blade by a generative manufacturing process.
- the strength of the support structure decreases radially outward. It is preferred that the hollow blade is formed integrally with the support structure. This can be achieved if the hollow blade is manufactured in a single step.
- the support structure preferably has at least one support web extending from the pressure side to the suction side of the hollow blade.
- the support bar can thereby enclose a right angle with the wall of the hollow blade or it can form an acute angle with the wall.
- the angle of the support bar may preferably be adapted to the forces acting on the wall such that the forces are effectively dissipated.
- the support structure has at least two mutually crossing support webs.
- the support structure may also preferably have a truss structure. Due to these two geometries, the strength of the hollow blade is particularly high.
- the support structure preferably has a honeycomb structure. With the honeycomb structure can advantageously be made of a stable support structure with a low material requirement.
- cooling air holes are arranged on the blade tip of the hollow blade. If the hollow blade cooled by cooling air from the inside, the cooling air can be advantageously dissipated by the cooling air holes at the blade tip. Furthermore, the cooling air exiting the cooling air holes blocks the radial gap at the blade tip of the built-in blade so that the leakage through the radial gap is reduced.
- the hollow blade is preferably solid in the region near the hub.
- the hollow blade is advantageously made particularly strong on the areas particularly heavily loaded by centrifugal forces.
- the wall thickness preferably decreases linearly radially outward. In addition, it is preferred that the wall thickness decreases degressively in the region near the hub.
- the additive manufacturing process is selective laser melting and / or selective laser sintering.
- a powder of the material from which the hollow blade is produced is applied in layers to a vertically displaceable piston.
- the areas from which the hollow blade is to be made are selectively irradiated with a laser.
- selective laser melting the laser power is chosen so that the particles of the powder are completely melted.
- selective laser sintering the surface of the particles is melted so far that the particles stick together after solidification of the molten surfaces. After finishing a layer, the flask is guided vertically downwards and another layer is applied.
- the hollow blade is thus built up in layers. Due to the generative manufacturing process can advantageously produce any complex geometries of the hollow blade. In particular, the thickening and the support structures can be so easy to produce advantageous. It is also advantageously possible with the generative manufacturing method to manufacture the hollow blade in one piece and in one step together with the support structure.
- the hollow blade has both areas produced by selective laser melting and by selective laser sintering.
- the outsides of the hollow blade could be made by selective laser melting so that the outsides are solid.
- the insides could be fabricated by selective laser sintering to form a porous structure with some gas permeability. This hollow blade would then be advantageous from the inside effectively cooled with cooling air. Furthermore, this could advantageously further reduce the mass of the hollow blade.
- the blade according to the invention is produced by the method according to the invention.
- FIG. 1 shows a perspective view of a trained as a hollow blade 1 blade of a turbomachine.
- the hollow blade 1 is formed by a blade 2 and a platform 6, which is arranged on the hub side of the blade 2.
- a plurality of blade cross-sections 22 to 26 of the airfoil 2 are shown, which are arranged at different radial positions of the airfoil 2.
- the hollow blade 1 is formed by an outer wall 6 with an outer surface 7.
- the geometry of the outer surface 7 is determined according to an aerodynamic profiling of the blade.
- the airfoil 2 has a blade leading edge 4 and a blade trailing edge 5, and a pressure side 11 and a suction side 12.
- the platform 9 forms in the installed state of the hollow blade 1 a hub contour, wherein on the platform 9 remote and radially outer longitudinal end of the blade 2, a blade tip 3 is formed.
- first blade cross-section 22 The radially inner side, immediately adjacent to the platform 9 arranged, first blade cross-section 22 is solid.
- the first blade cross-section 22 radially adjacently disposed, second blade cross-section 23 has two the inner cavity 8 bridging and secured to the outer wall 6 transverse webs 15, so that the inner cavity 8 of the hollow blade 1 is divided into three of the transverse webs 15.
- the two transverse webs 15 are arranged substantially parallel to one another and the transverse web 15 adjoining the blade leading edge 4 in each case encloses a substantially right angle with the pressure side 11 and the suction side 12.
- the fifth blade cross section 26 arranged radially on the outside, on the blade tip 3, is solidly formed with a plurality of cooling air holes 10 distributed over the blade tip 3.
- FIG. 2 Two embodiments of a wall thickness curve 13 are shown in a diagram. Above the abscissa 21 is the radius and above the ordinate 20, the thickness of the outer wall 6 is plotted as the wall thickness curve 13.
- the wall thickness profile 13 is formed continuously falling with a hub-side maximum. In the area of the hub, the wall thickness progression 13 decreases degressively in order subsequently to decrease linearly up to the blade tip 3.
- the second embodiment of the wall thickness curve 13 differs from the first embodiment in that approximately in the radial middle position a local maximum 14 in the shape of a plateau is formed.
- the local maximum 14 is provided at the point of the blade 2, which is excessively loaded by blade vibrations during operation of the turbomachine.
- the thickness of the outer wall 6 according to the wall thickness curve 13 at the local maximum 14 is less than in the region of the hub, but it is also conceivable that the thickness of the outer wall 6 at the local maximum 14 is greater than in the region of the hub.
- FIGS. 3 to 8 conceivable embodiments of the fourth blade cross-section 25 are shown. In principle, these embodiments can also be applied to the second and the third blade section 23, 24.
- the embodiments according to FIGS. 3 to 5 and according to FIGS. 7 and 8 have a support structure 15, 16, 17, 19.
- the embodiments according to FIGS. 6 and 7 on the other hand have inwardly directed thickening 18 of the outer wall 6.
- the embodiment according to FIG. 3 has a plurality of pairs crossing support webs 16, which form the support structure.
- the intersecting support webs 16 extend in the rear region of the airfoil 2 over about two-thirds of the chord length.
- the support structure according to the in FIG. 3 shown embodiment of the crossbar 15, which bridges the mecanicholraum 8 of the hollow blade 2 from the pressure side 11 to the suction side 12 and is arranged at about one third of the chord length of the blade section 25.
- a truss structure 17 extends as the support structure over the entire chord length of the airfoil 2, which is formed by V-shaped webs.
- the further embodiment according to FIG. 6 has thickenings 18 both in the area of the blade leading edge 4 and in the region of the blade trailing edge 5.
- the embodiment according to FIG. 7 has two thickenings 18 on the pressure side 11 and the suction side 12.
- the transverse web 15 bridging the inner cavity 8 is provided, which is attached to non-thickened points of the outer wall 6.
- the transverse web 15 is attached to the thickenings 18.
- a honeycomb structure 19 is shown as the support structure which extends over the entire inner cavity 8.
- the embodiment of the blade according to FIG. 7 is to be manufactured as follows: Constructing the blade as the hollow blade 1, the wall thickness radially outward according to the first embodiment of the wall thickness curve 13 according to FIG. 2 decreases linearly and is dimensioned such that the blade of their gas load and their centrifugal force load during operation of the turbomachine withstands. Next, regions of the hollow blade 1 that are excessively loaded by blade vibrations during operation of the turbomachine are to be determined. At these areas, the hollow blade 1 is to be designed with thickenings 18 which extend inwardly of the hollow blade 1, so that the strength of the hollow blade 1 is locally increased at these areas, whereby the hollow blade 1 withstands the blade vibrations during operation of the turbomachine.
- the hollow blade 1 is to be constructed in its interior with a support structure which is formed by the transverse web 15, which bridges the pressure side 11 toward the suction side 12 in the front third of the chord length of the hollow blade 1.
- the strength of the crosspiece 15 decreases radially outward.
- the blade is made in one piece by selective laser sintering.
- the manufacturing method for the embodiment of the blade according to FIG. 7 is in principle also applicable to all other described embodiments.
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Abstract
Description
Die Erfindung betrifft ein Verfahren zum Herstellen einer Laufschaufel für eine Strömungsmaschine sowie die mit dem Verfahren hergestellte Laufschaufel.The invention relates to a method for producing a blade for a turbomachine and the blade produced by the method.
Eine Gasturbine weist einen Verdichter beispielsweise in Axialbauweise auf, in dem Luft komprimiert wird, bevor sie zum Verbrennen in eine Brennkammer der Gasturbine eingeleitet wird. Der Verdichter weist feststehende Leitschaufeln sowie rotierende Laufschaufeln auf. Die Leitschaufeln und die Laufschaufeln sind im Betrieb der Gasturbine entsprechenden Belastungen ausgesetzt, die die Lebensdauer der Leitschaufeln und der Laufschaufeln reduzieren. Unter anderem erfahren die Leitschaufeln und die Laufschaufeln eine Beanspruchung durch Schwingungen und eine Fliehkraftbelastung. Die Fliehkraftbelastung nimmt mit zunehmender Länge und zunehmender Masse der Laufschaufeln sowie mit zunehmender Drehzahl zu und ist insbesondere an den Schaufelwurzeln der Laufschaufeln hoch. Hervorgerufen durch diese Belastungen an den Schaufelwurzeln können sich Risse bilden, die zum Versagen der Laufschaufel im Betrieb der Gasturbine führen können. Um derartige Schäden vorzubeugen, werden herkömmlich besonders feste Materialien, wie z.B. Titan, Superlegierungen auf der Basis von Nickel oder Verbundwerkstoffe, für die Laufschaufeln eingesetzt.A gas turbine has a compressor, for example in an axial construction, in which air is compressed before it is introduced into a combustion chamber of the gas turbine for combustion. The compressor has fixed vanes and rotating blades. The vanes and blades are exposed to corresponding stresses during operation of the gas turbine that reduce the life of the vanes and blades. Among other things, the guide vanes and the blades undergo a stress due to vibrations and a centrifugal force load. The centrifugal load increases with increasing length and mass of the blades and with increasing speed and is particularly high at the blade roots of the blades. Caused by these loads on the blade roots, cracks can form, which can lead to the failure of the blade during operation of the gas turbine. In order to prevent such damage, conventionally particularly strong materials, e.g. Titanium, superalloys based on nickel or composites, used for the blades.
Aufgabe der Erfindung ist es, ein Verfahren zum Herstellen einer Laufschaufel für eine Strömungsmaschine sowie die mit dem Verfahren hergestellte Laufschaufel zu schaffen, wobei die Laufschaufel leicht ausgebildet ist und dennoch eine hohe Festigkeit hat.The object of the invention is to provide a method for producing a blade for a turbomachine and the blade produced by the method, wherein the blade is easily formed and yet has a high strength.
Das erfindungsgemäße Verfahren zum Herstellen einer Laufschaufel für eine Strömungsmaschine weist folgende Schritte auf: Konstruieren der Laufschaufel als eine Hohlschaufel, deren Wandstärke radial nach außen abnimmt und derart dimensioniert ist, dass die Laufschaufel ihrer Gaskraftbelastung und ihrer Fliehkraftbelastung im Betrieb der Strömungsmaschine standhält; Ermitteln von mindestens einem durch Schaufelschwingungen im Betrieb der Strömungsmaschine übermäßig belasteten Bereich der Hohlschaufel; Verdicken der Hohlschaufel nach innen an dem Bereich und/oder Versehen einer Stützstruktur im Inneren der Hohlschaufel an dem Bereich, so dass die Festigkeit der Hohlschaufel an diesem Bereich lokal erhöht ist, wodurch die Hohlschaufel den Schaufelschwingungen im Betrieb der Strömungsmaschine standhält.The method according to the invention for producing a moving blade for a turbomachine has the following steps Constructing the blade as a hollow blade whose wall thickness decreases radially outwards and dimensioned such that the blade withstands their gas force load and centrifugal load during operation of the turbomachine; Determining at least one region of the hollow blade that is excessively loaded by blade vibrations during operation of the turbomachine; Thickening the hollow blade inwardly at the area and / or providing a support structure in the interior of the hollow blade at the area, so that the strength of the hollow blade is locally increased at this area, whereby the hollow blade resists the blade vibrations during operation of the turbomachine.
Das erfindungsgemäße Verfahren eignet sich insbesondere für lange Laufschaufeln, weil bei ihnen die Fliehkraftbelastung besonders hoch ist. Indem die Laufschaufel als die Hohlschaufel ausgeführt wird, ist ihre Masse verglichen mit einer Vollschaufel vermindert, wodurch vorteilhaft ihre Fliehkraftbelastung im Betrieb vermindert ist. Indem die Wandstärke radial nach außen abnimmt, ist sie im Bereich des Schaufelfußes, also in dem Bereich, an dem die Fliehkraftbelastung am höchsten ist, vorteilhaft am stärksten. Ein weiterer Vorteil des Verfahrens ist es, dass die Hohlschaufel mit einem geringen Materialbedarf herstellbar ist.The inventive method is particularly suitable for long blades, because in them the centrifugal load is particularly high. By making the blade as the hollow blade, its mass is reduced compared to a full blade, which advantageously reduces its centrifugal load during operation. By the wall thickness decreases radially outward, it is advantageous in the area of the blade root, ie in the region where the centrifugal force load is highest, advantageously the strongest. Another advantage of the method is that the hollow blade can be produced with a low material requirement.
Dadurch, dass die Hohlschaufel an den durch Schwingungen übermäßig belasteten Bereichen Verdickungen und/oder die Stützstruktur aufweist, ist sie vorteilhaft selektiv an diesen Bereichen verstärkt. Gleichzeitig ist die Hohlschaufel an weniger belasteten Bereichen dünn ausgeführt, so dass insgesamt die Hohlschaufel vorteilhaft mit einer geringen Masse fertiggestellt werden kann. Durch die Stützstruktur kann vorteilhaft die Festigkeit der Hohlschaufel erhöht werden.Due to the fact that the hollow blade has thickenings and / or the support structure on the regions which are excessively loaded by vibrations, it is advantageously reinforced selectively at these areas. At the same time, the hollow blade is made thin at less loaded areas, so that overall the hollow blade can be advantageously completed with a small mass. By the support structure can advantageously be increased, the strength of the hollow blade.
Bevorzugt weist das Verfahren folgenden Schritt auf: Fertigstellen der Laufschaufel durch ein generatives Fertigungsverfahren.Preferably, the method comprises the following step: Completing the blade by a generative manufacturing process.
Bevorzugtermaßen nimmt die Stärke der Stützstruktur radial nach außen ab. Es ist bevorzugt, dass die Hohlschaufel zusammen mit der Stützstruktur einstückig ausgebildet ist. Dies kann erreicht werden, wenn die Hohlschaufel in einem einzigen Schritt gefertigt wird. Die Stützstruktur weist bevorzugt mindestens einen von der Druckseite zur Saugseite der Hohlschaufel sich erstreckenden Stützsteg auf. Der Stützsteg kann dabei mit der Wand der Hohlschaufel einen rechten Winkel einschließen oder er kann mit der Wand einen spitzen Winkel einschließen. Der Winkel des Stützstegs kann bevorzugt an die auf die Wand wirkenden Kräfte derart angepasst werden, dass die Kräfte effektiv abgeleitet werden.Preferred dimensions, the strength of the support structure decreases radially outward. It is preferred that the hollow blade is formed integrally with the support structure. This can be achieved if the hollow blade is manufactured in a single step. The support structure preferably has at least one support web extending from the pressure side to the suction side of the hollow blade. The support bar can thereby enclose a right angle with the wall of the hollow blade or it can form an acute angle with the wall. The angle of the support bar may preferably be adapted to the forces acting on the wall such that the forces are effectively dissipated.
Es ist bevorzugt, dass die Stützstruktur mindestens zwei sich paarweise kreuzende Stützstege aufweist. Die Stützstruktur kann auch bevorzugtermaßen eine Fachwerkstruktur aufweisen. Durch diese beiden Geometrien ist die Festigkeit der Hohlschaufel besonders hoch. Die Stützstruktur weist bevorzugt eine Wabenstruktur auf. Mit der Wabenstruktur kann vorteilhaft eine stabile Stützkonstruktion mit einem geringen Materialbedarf hergestellt werden.It is preferred that the support structure has at least two mutually crossing support webs. The support structure may also preferably have a truss structure. Due to these two geometries, the strength of the hollow blade is particularly high. The support structure preferably has a honeycomb structure. With the honeycomb structure can advantageously be made of a stable support structure with a low material requirement.
Bevorzugt sind an der Schaufelspitze der Hohlschaufel Kühlluftlöcher angeordnet. Wird die Hohlschaufel durch Kühlluft von innen gekühlt, kann durch die Kühlluftlöcher an der Schaufelspitze die Kühlluft vorteilhaft abgeführt werden. Des Weiteren sperrt die aus den Kühlluftlöchern austretende Kühlluft den Radialspalt an der Schaufelspitze der eingebauten Laufschaufel, so dass die Leckage durch den Radialspalt vermindert wird.Preferably, cooling air holes are arranged on the blade tip of the hollow blade. If the hollow blade cooled by cooling air from the inside, the cooling air can be advantageously dissipated by the cooling air holes at the blade tip. Furthermore, the cooling air exiting the cooling air holes blocks the radial gap at the blade tip of the built-in blade so that the leakage through the radial gap is reduced.
Die Hohlschaufel ist im nabennahen Bereich bevorzugt massiv ausgebildet. Dadurch ist die Hohlschaufel vorteilhaft an den durch Fliehkräfte besonders stark belasteten Bereichen besonders stark ausgebildet. Die Wandstärke nimmt bevorzugt nach radial außen linear ab. Zusätzlich ist es bevorzugt, dass die Wandstärke im nabennahen Bereich degressiv abnimmt. Durch die beiden Maßnahmen ist vorteilhaft erreicht, dass die Masse der Schaufel gering ist und gleichzeitig die Schaufel an den durch die Fliehkräfte belasteten Bereichen fest ausgebildet ist. Durch das degressive Abnehmen der Wanddicke werden scharfe Kanten vermieden, wodurch die Bildung von Rissen vorteilhaft unterbunden wird. Die Laufschaufel ist bevorzugt eine Verdichterlaufschaufel oder eine Turbinenlaufschaufel insbesondere einer Gasturbine, eine Dampfturbinenlaufschaufel, eine Schaufel einer Wasserturbine oder ein Rotorblatt einer Windturbine.The hollow blade is preferably solid in the region near the hub. As a result, the hollow blade is advantageously made particularly strong on the areas particularly heavily loaded by centrifugal forces. The wall thickness preferably decreases linearly radially outward. In addition, it is preferred that the wall thickness decreases degressively in the region near the hub. By the two measures is advantageously achieved that the mass of Blade is small and at the same time the blade is fixed to the loaded by the centrifugal forces areas. By reducing the wall thickness degressive sharp edges are avoided, whereby the formation of cracks is advantageously prevented. The moving blade is preferably a compressor blade or a turbine blade, in particular a gas turbine, a steam turbine blade, a blade of a water turbine or a rotor blade of a wind turbine.
Bevorzugt ist das generative Fertigungsverfahren selektives Laserschmelzen und/oder selektives Lasersintern. Bei den beiden genannten Verfahren wird ein Pulver aus dem Material, aus dem die Hohlschaufel hergestellt wird, schichtweise auf einen vertikalverschiebbaren Kolben aufgetragen. Die Bereiche, aus denen die Hohlschaufel hergestellt werden soll, werden selektiv mit einem Laser bestrahlt. Bei dem selektiven Laserschmelzen wird die Laserleistung so gewählt, dass die Partikel des Pulvers vollständig geschmolzen werden. Bei dem selektiven Lasersintern wird die Oberfläche der Partikel so weit geschmolzen, dass die Partikel nach Erstarren der geschmolzenen Oberflächen miteinander verkleben. Nach dem Fertigen einer Schicht wird der Kolben vertikal nach unten geführt und eine weitere Schicht aufgetragen. Die Hohlschaufel wird somit schichtweise aufgebaut. Durch das generative Fertigungsverfahren lassen sich vorteilhaft beliebig komplexe Geometrien der Hohlschaufel herstellen. Insbesondere die Verdickungen und die Stützstrukturen lassen sich so vorteilhaft einfach herstellen. Auch ist es mit dem generativen Fertigungsverfahren vorteilhaft einfach möglich, die Hohlschaufel zusammen mit der Stützstruktur einstückig und in einem Schritt zu fertigen.Preferably, the additive manufacturing process is selective laser melting and / or selective laser sintering. In the two methods mentioned, a powder of the material from which the hollow blade is produced is applied in layers to a vertically displaceable piston. The areas from which the hollow blade is to be made are selectively irradiated with a laser. In selective laser melting, the laser power is chosen so that the particles of the powder are completely melted. In selective laser sintering, the surface of the particles is melted so far that the particles stick together after solidification of the molten surfaces. After finishing a layer, the flask is guided vertically downwards and another layer is applied. The hollow blade is thus built up in layers. Due to the generative manufacturing process can advantageously produce any complex geometries of the hollow blade. In particular, the thickening and the support structures can be so easy to produce advantageous. It is also advantageously possible with the generative manufacturing method to manufacture the hollow blade in one piece and in one step together with the support structure.
Denkbar ist, dass die Hohlschaufel sowohl durch selektives Laserschmelzen als auch durch selektives Lasersintern hergestellte Bereiche aufweist. Die Außenseiten der Hohlschaufel könnten durch selektives Laserschmelzen hergestellt werden, so dass die Außenseiten massiv ausgebildet werden. Die Innenseiten könnten durch selektives Lasersintern hergestellt werden, so dass eine poröse Struktur mit einer gewissen Gaspermeabilität ausgebildet wird. Diese Hohlschaufel wäre dann von innen vorteilhaft effektiv mit Kühlluft kühlbar. Des Weiteren könnte dadurch die Masse der Hohlschaufel vorteilhaft weiter vermindert werden.It is conceivable that the hollow blade has both areas produced by selective laser melting and by selective laser sintering. The outsides of the hollow blade could be made by selective laser melting so that the outsides are solid. The insides could be fabricated by selective laser sintering to form a porous structure with some gas permeability. This hollow blade would then be advantageous from the inside effectively cooled with cooling air. Furthermore, this could advantageously further reduce the mass of the hollow blade.
Die erfindungsgemäße Laufschaufel ist mit dem erfindungsgemäßen Verfahren hergestellt.The blade according to the invention is produced by the method according to the invention.
Im Folgenden wird die Erfindung anhand der beigefügten schematischen Zeichnungen erläutert. Es zeigt:
- Figur 1
- eine perspektivische Ansicht einer erfindungsgemäßen Laufschaufel, wobei mehrere Schaufelquerschnitte des Schaufelblatts der Laufschaufel dargestellt sind,
Figur 2- ein Diagramm mit zwei bevorzugten Ausführungsformen an Wandstärkenverläufen der Laufschaufel und
Figuren 3 bis 8- bevorzugte Ausführungsformen der der Laufschaufel.
- FIG. 1
- 3 is a perspective view of a blade according to the invention, wherein a plurality of blade cross-sections of the blade of the blade are shown,
- FIG. 2
- a diagram with two preferred embodiments of wall thickness curves of the blade and
- FIGS. 3 to 8
- preferred embodiments of the blade.
Der radial innenseitig, unmittelbar der Plattform 9 benachbart angeordnete, erste Schaufelquerschnitt 22 ist massiv ausgebildet. Der dem ersten Schaufelquerschnitt 22 radial außenseitig benachbart angeordnete, zweite Schaufelquerschnitt 23 weist zwei den Innenhohlraum 8 überbrückende und an der Außenwand 6 befestigte Querstege 15 auf, so dass der Innenhohlraum 8 der Hohlschaufel 1 von den Querstegen 15 dreigeteilt ist. Die beiden Querstege 15 sind im Wesentlichen parallel zueinander angeordnet und der der Schaufelvorderkante 4 benachbarte Quersteg 15 schließt jeweils mit der Druckseite 11 und der Saugseite 12 einen im Wesentlichen rechten Winkel ein. Vom zweiten Schaufelquerschnitt 23 zum dritten Schaufelschnitt 24 und vom dritten Schaufelschnitt 24 zum vierten Schaufelschnitt 25 verringern sich jeweils die Stärken der Außenwand 6 und der Querstege 15, wodurch die Querschnittserstreckung des Innenhohlraums 8 von Schnitt zu Schnitt sich vergrößert. Der radial außenseitig, an der Schaufelspitze 3 angeordnete fünfte Schaufelquerschnitt 26 ist massiv mit einer Mehrzahl an über die Schaufelspitze 3 verteilten Kühlluftlöchern 10 ausgebildet.The radially inner side, immediately adjacent to the platform 9 arranged,
In
In
Die Ausführungsform gemäß
Im Unterschied zu der Ausführungsform gemäß
Die weitere Ausführungsform gemäß
Neben den hier vorgestellten Ausführungsformen sind weitere Ausführungsformen denkbar, in denen die Querstege 15, die V-förmig angeordneten Stützstege 17, die sich kreuzenden Stützstege 16 und die Wabenstruktur 19 beliebig miteinander kombiniert sind.In addition to the embodiments presented here, further embodiments are conceivable in which the
Die Ausführungsform der Laufschaufel gemäß
Das Herstellungsverfahren für die Ausführungsform der Laufschaufel gemäß
Obwohl die Erfindung im Detail durch das bevorzugte Ausführungsbeispiel näher illustriert und beschrieben wurde, so ist die Erfindung nicht durch die offenbarten Beispiele eingeschränkt und andere Variationen können vom Fachmann hieraus abgeleitet werden, ohne den Schutzumfang der Erfindung zu verlassen.Although the invention has been further illustrated and described in detail by the preferred embodiment, the invention is not limited by the disclosed examples, and other variations can be derived therefrom by those skilled in the art without departing from the scope of the invention.
Claims (15)
wobei die Stärke der Stützstruktur radial nach außen abnimmt.Method according to claim 1 or 2,
wherein the thickness of the support structure decreases radially outward.
wobei die Hohlschaufel (1) zusammen mit der Stützstruktur (15 bis 17, 19) einstückig ausgebildet ist.Method according to one of claims 1 to 4,
wherein the hollow blade (1) is formed integrally with the support structure (15 to 17, 19).
wobei die Stützstruktur mindestens einen von der Druckseite (11) zur Saugseite (12) der Hohlschaufel (1) sich erstreckenden Quersteg (15) aufweist.Method according to one of claims 1 to 4,
wherein the support structure has at least one of the pressure side (11) to the suction side (12) of the hollow blade (1) extending transverse web (15).
wobei die Stützstruktur mindestens zwei sich paarweise kreuzende Stützstege (16) aufweist.Method according to claim 5,
wherein the support structure has at least two mutually crossing support webs (16).
wobei die Stützstruktur eine Fachwerkstruktur (17) aufweist.Method according to one of claims 1 to 6,
wherein the support structure comprises a truss structure (17).
wobei die Stützstruktur eine Wabenstruktur (19) aufweist.Method according to one of claims 1 to 7,
wherein the support structure comprises a honeycomb structure (19).
wobei an der Schaufelspitze (3) der Hohlschaufel (1) Kühlluftlöcher (10) angeordnet werden.Method according to one of claims 1 to 8,
wherein on the blade tip (3) of the hollow blade (1) cooling air holes (10) are arranged.
wobei die Hohlschaufel (1) im nabennahen Bereich massiv ausgebildet wird.Method according to one of claims 1 to 9,
wherein the hollow blade (1) is formed solid in the region near the hub.
wobei die Wandstärke nach radial außen linear abnimmt.Method according to one of claims 1 to 10,
wherein the wall thickness decreases linearly radially outward.
wobei die Wandstärke im nabennahen Bereich degressiv abnimmt.Method according to one of claims 1 to 11,
wherein the wall thickness decreases degressively in the region near the hub.
wobei das generative Fertigungsverfahren selektives Laserschmelzen und/oder selektives Lasersintern ist.Method according to one of claims 2 to 12,
wherein the additive manufacturing process is selective laser melting and / or selective laser sintering.
wobei die Laufschaufel eine Verdichterlaufschaufel oder eine Turbinenlaufschaufel insbesondere einer Gasturbine, eine Dampfturbinenlaufschaufel, eine Schaufel einer Wasserturbine oder ein Rotorblatt einer Windturbine ist.Method according to one of claims 1 to 13,
wherein the blade is a compressor blade or a turbine blade, in particular a gas turbine, a steam turbine blade, a blade of a water turbine or a rotor blade of a wind turbine.
Priority Applications (1)
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EP11186202.5A EP2584146A1 (en) | 2011-10-21 | 2011-10-21 | Method for producing a rotor blade for a fluid flow engine and corresponding rotor blade |
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EP11186202.5A EP2584146A1 (en) | 2011-10-21 | 2011-10-21 | Method for producing a rotor blade for a fluid flow engine and corresponding rotor blade |
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EP3153663A1 (en) | 2015-10-08 | 2017-04-12 | Rolls-Royce Deutschland Ltd & Co KG | Blade for turbomachine, turbofan engine and method for producing a blade |
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EP3480432A3 (en) * | 2017-11-07 | 2019-06-05 | United Technologies Corporation | Modified structural truss for airfoils |
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FR3085418A1 (en) * | 2018-08-29 | 2020-03-06 | Safran Aircraft Engines | TURBOMACHINE BLADE COMPRISING AN INTERNAL HONEYCOMB PART |
US11149550B2 (en) | 2019-02-07 | 2021-10-19 | Raytheon Technologies Corporation | Blade neck transition |
US10871074B2 (en) * | 2019-02-28 | 2020-12-22 | Raytheon Technologies Corporation | Blade/vane cooling passages |
CN110410285A (en) * | 2019-07-12 | 2019-11-05 | 湖南城市学院 | Intelligent anti-freezing wind power generation plant |
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