EP0285778A1 - Procédé de fabrication d'une pale de turbine composite comprenant un pied, une pale et un couvercle, dans laquelle la pale est formée d'un superalliage à base de nickel durci par dispersion et pale de turbine obtenue selon ce procédé - Google Patents

Procédé de fabrication d'une pale de turbine composite comprenant un pied, une pale et un couvercle, dans laquelle la pale est formée d'un superalliage à base de nickel durci par dispersion et pale de turbine obtenue selon ce procédé Download PDF

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Publication number
EP0285778A1
EP0285778A1 EP88102415A EP88102415A EP0285778A1 EP 0285778 A1 EP0285778 A1 EP 0285778A1 EP 88102415 A EP88102415 A EP 88102415A EP 88102415 A EP88102415 A EP 88102415A EP 0285778 A1 EP0285778 A1 EP 0285778A1
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EP
European Patent Office
Prior art keywords
weight
airfoil
temperature
cover plate
rest
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Granted
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EP88102415A
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German (de)
English (en)
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EP0285778B1 (fr
Inventor
Clemens Dr. Verpoort
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BBC Brown Boveri AG Switzerland
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BBC Brown Boveri AG Switzerland
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    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B22—CASTING; POWDER METALLURGY
    • B22D—CASTING OF METALS; CASTING OF OTHER SUBSTANCES BY THE SAME PROCESSES OR DEVICES
    • B22D19/00—Casting in, on, or around objects which form part of the product
    • 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
    • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
    • Y10T29/00—Metal working
    • Y10T29/49—Method of mechanical manufacture
    • Y10T29/49316—Impeller making
    • Y10T29/49336—Blade making
    • Y10T29/49337—Composite blade
    • 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
    • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
    • Y10T29/00—Metal working
    • Y10T29/49—Method of mechanical manufacture
    • Y10T29/4998—Combined manufacture including applying or shaping of fluent material
    • Y10T29/49988—Metal casting

Definitions

  • the invention relates to the further development of mechanically and / or thermally highly stressed gas turbine blades, the advantageous properties of dispersion-hardened alloys for certain types of stress being optimally combined with those of non-dispersion-hardened alloys.
  • a method for producing a composite gas turbine blade consisting of a foot piece, airfoil and cover plate or shroud, the airfoil consisting of an oxide dispersion-hardened nickel-base superalloy in the state of longitudinally coarse stem crystals.
  • It also relates to a composite gas turbine blade consisting of a base piece, an airfoil and a cover plate or a shroud, the airfoil consisting of an oxide dispersion-hardened nickel-based superalloy in the state of longitudinally coarse stem crystals.
  • cover plates and / or cover strips at least in certain stages.
  • cover plates and / or cover strips at least in certain stages.
  • the reasons for this are both fluidic, thermal and geometric in nature. These measures are intended to improve and make the aerodynamics, thermodynamics and mechanics of the machine safer.
  • countless embodiments and material combinations of cover plates and cover bands and their manufacture or fastening at the head end of the blade - also monolithic constructions, forming a whole with the blade - have become known.
  • the following literature can be cited: - Walter Traupel, Thermal Turbomachinery, 2nd Vol. Control Behavior, Strength and Dynamic Problems, Springer Verlag 1960 - H. Petermann, construction and belt elements of fluid machines, Springer Verlag 1960 - Fritz Dietzel, steam turbines, Georg Liebermann Verlag 1950 - Fritz Dietzel, steam turbines, calculation, construction, Carl Hauser Verlag.
  • Oxide dispersion-hardened nickel-based superalloys have recently been proposed as blade materials for highly stressed gas turbines, since they have higher operating temperatures than conventional cast and kneading superalloys.
  • components made from these alloys with elongated, coarse crystallites oriented in the blade axis are used.
  • the workpiece sini-finished or strength
  • the workpiece generally has to go through a zone annealing process.
  • the cross-sectional dimensions of such blade materials are limited in the coarse-grained state. This also limits the blade dimensions.
  • the blade and cover plate of certain dimensions can no longer be made monolithically from one piece. The same applies to the root part of the blade, which can be very voluminous in the relative dimensions. If oxide dispersion-hardened superalloys are to be used successfully and in general, there is therefore a requirement for a division into the airfoil on the one hand and the cover plate and foot piece on the other. There are other reasons for such a division, which depend on the strength and the material stress at the clamping points.
  • a purely mechanical fastening of the cover plate at the head end of the airfoil can solve the problem in principle, but is complex, requires additional fastening elements and can lead to additional voltages that are difficult to control during operation.
  • a welded joint is ruled out because the structure of the oxide dispersion-hardened material is largely destroyed by local melting.
  • a connection by soldering or diffusion joining requires very clean machined contact surfaces and is technologically difficult.
  • the invention has for its object to provide a composite gas turbine blade consisting of a foot piece, airfoil and cover plate or shroud and a method for their production, whereby on the one hand more consideration is given to the use of oxide-dispersion-hardened nickel-based superalloys, their only limited cross-sectional dimensions in the state of longitudinally coarse stem crystals for the Bucket blade made optimal use and on the other hand, through an appropriate choice of material and constructive design of the foot piece and the cover plate or the cover band, as well as their manufacture, an optimal assignment to the bucket blade and thus a composite construction that is well suited to all thermal and mechanical operating conditions is to be achieved.
  • both the head end and the foot end of the airfoil on the lateral surface are provided with depressions and / or elevations in the method mentioned at the outset, that the airfoil is inserted into a mold having the negative shape of the cover plate and of the base piece in such a way that the head end and the foot end protrude into the cavity of the mold, that the airfoil is preheated to a temperature which is 50 to 300 ° C below the solidus temperature of the deep-melting phase of the airfoil material, and that the cavity of the mold with the melt is one for the
  • the cover plate and the base piece of non-dispersion hardened nickel-based superalloy are filled with a casting temperature that is at most 100 ° C above the liquidus temperature of the highest melting phase of this alloy in such a way that the head end and the foot end of the airfoil are completely cast and cast and that the temperature of the melt after the end of the casting process and during solidification and that of the airfoil is controlled in such
  • the foot piece and the cover plate consist of a non-dispersion hardened nickel-base cast superalloy and that the foot piece and the cover plate have depressions and / or elevations on The foot end and at the head end of the outer surface of the airfoil are secured mechanically by casting and pouring in while maintaining a metallic interruption and without any metallurgical bond.
  • a schematic longitudinal section (elevation) is made by a casting device for the head end of an airfoil to be poured.
  • 1 is the airfoil made of an oxide dispersion hardened nickel-based superalloy, the longitudinal axis of which is in a vertical position.
  • the or the head 2 to be cast is at the top. It is offset in the transverse dimensions from the active profile of the airfoil 1 and has a circumferential recess 4 and a similar elevation 5 for the purpose of better mechanical anchoring of the cover plate to be produced and fastened by casting (reference number 6 in FIG. 2).
  • 8 is the casting mold made of ceramic, which corresponds on its concave side to the shape of the cover plate to be produced (negative mold).
  • 2 shows a schematic longitudinal section through an assembled guide vane for a gas turbine.
  • 1 is the vane blade consisting of an oxide dispersion-hardened nickel-base superalloy and having coarse stem crystals oriented in the longitudinal direction by zone annealing.
  • 2 is the head end, 3 the foot end of the airfoil 1, both of which each have a circumferential recess 4 and an elevation 5 of the same type.
  • 6 is the cover plate or cover band
  • 7 is the casting of the blade. Both consist of a non-dispersion hardened nickel-based casting superalloy. 6 and 7 generally have - depending on the composition, casting temperature and cooling conditions - fine-grained to medium-grained crystal structure.
  • FIG 3 shows a schematic longitudinal section through the foot part of a guide vane for a gas turbine, the foot piece having cooling channels and an intermediate layer being located between the foot piece and the airfoil.
  • 15 are cooling channels in the foot piece 7 the shovel.
  • 16 is an oxide, heat-insulating oxide layer that prevents the metallurgical bond between the airfoil 1 and the base piece 7. This can be a naturally occurring oxide layer of the airfoil 1 of a few ⁇ m thickness or a layer of an oxide specially applied to this jacket part of the airfoil 1 selected from the elements Cr, Al, Si, Ti, Rz with a thickness of 5 to 200 ⁇ m .
  • FIG. 4 shows a schematic longitudinal section through a composite rotor blade for a gas turbine. Basically, all reference numerals correspond to those of the previous figures. Only the shapes of the components are different.
  • the base part of the blade has double fir-tree teeth, which ensures a good countersinking in the rotor body of the turbine.
  • Fig. 5 shows a schematic longitudinal section through a composite blade with intermediate layer and cooling channels in the foot part.
  • the individual components and reference numerals basically correspond to those in FIG. 4.
  • the cover plate 6 which is made of a non-oxide-dispersion-hardened nickel-base casting superalloy, with depressions 4 and elevations 5 for the purpose of anchoring.
  • the foot end 3 of the airfoil 1 is designed in the form of a fir tree with depressions 4 and elevations 5 and in turn is inserted in a fir tree-shaped foot piece 7 made of a nickel-based cast superalloy.
  • the foot piece 7 is provided with cooling channels 15.
  • an intermediate layer made of an oxide which is up to 200 ⁇ m thick. This serves for the elastic absorption of clamping forces and expansion differences in rapidly changing operating conditions (thermal shock, etc.) and for thermal insulation between the blade and the rotor body.
  • a blade 1 for a gas turbine guide blade was produced from an oxide dispersion-hardened nickel-based superalloy by mechanical processing.
  • the material was in the form of a prismatic semi-finished product with a rectangular cross-section 100 mm wide and 32 mm thick in the zone-annealed, recrystallized, coarse-grained state.
  • the longitudinal stem crystals have an average length of 20 mm, a width of 6 mm and a thickness of 3 mm.
  • the head end 2 of the airfoil 1 was set down on its outer surface.
  • the offset part had a recess 4 in the form of a circumferential rounded groove 4 mm deep and 2.5 mm wide. As a result, an elevation 5 was formed at the extreme end.
  • the airfoil 1 was then heated to a temperature of 1140 ° C. and placed in the likewise preheated casting mold 8 made of ceramic, so that the head end 2 protruded into the cavity of the latter.
  • the mold 8 was sealed against the airfoil 1 by means of a seal 12 made of ceramic adhesive.
  • a melt made of a superalloy was then poured into the cavity of the casting mold 8 via the pouring funnel 9, the part 14 subsequently forming the cover plate enclosing the head end 2 of the airfoil 1.
  • This alloy has a liquidus temperature of approx. 1315 ° C.
  • the casting temperature was a maximum of 1380 ° C.
  • the workpiece was slowly cooled. Thanks to the low casting temperature, a mild to fine-grained structure was achieved for the cover plate 6.
  • the finished blade was subjected to a 5 min cycle between the temperature limits of approx. 200 ° C and approx. 1000 ° C in order to test its sensitivity to thermal shock. After 500 cycles, no cracks and no loosening of the cover plate 6 from the airfoil 1 were found. The natural oxide skin between these two parts already acted as a heat insulation layer, so that the cover plate can only reach a temperature of 800 ° C. This also has an advantageous effect during operation, especially in the case of shutdowns or load shedding on the generator side.
  • the preheating temperature of the airfoil 1 should be 1140 to 1180 ° C. and the casting temperature of the melt 13 should not exceed 1380 ° C.
  • an airfoil 1 was produced from an oxide dispersion-hardened nickel-based superalloy.
  • the alloy composition and the dimensions corresponded exactly to Example 1.
  • the airfoil 1 was preheated to a temperature of 1160 ° C. and inserted with its head end 2 into a casting mold 8 according to FIG. 1 and with its foot end 3 into a corresponding casting mold (not shown!) .
  • the cavities of both casting molds were filled simultaneously with a melt 13 made of a non-dispersion hardened nickel-base casting superalloy with the trade name IN 939 from INCO.
  • This alloy has a liquidus temperature of approx. 1340 ° C.
  • the maximum casting temperature was 1400 ° C. Otherwise, the procedure was exactly the same as that given in Example 1.
  • the investigation showed that there was no metallurgical bond between the airfoil 1 on the one hand and the cover plate 6 or foot piece 7.
  • the test for resistance to temperature changes showed no cracks and no detachment of the cover plate 6 or the foot piece 7 from the airfoil 1.
  • the preheating temperature of the airfoil 1 is generally 1160 to 1200 ° C. and the pouring temperature of the melt 13 is at most 1400 ° C.
  • a blade 1 for a gas turbine guide blade was produced from an oxide dispersion-hardened nickel-based superalloy by mechanical processing.
  • the semifinished product in the coarse-grained, longitudinally oriented stem crystals as the starting material and the finished airfoil had the same dimensions as in Example 1.
  • the foot end 3 of the airfoil 1 was offset on its outer surface and had a rectangular depression 4 10 mm deep and 14 mm wide and a corresponding elevation 5 10 mm thick and 13 mm wide.
  • the entire surface of the foot end 3 of the airfoil 1 was provided by the plasma spraying process with an approximately 150 ⁇ m thick intermediate layer 16 made of Al2O3.
  • Example 2 The procedure was the same as that given in Example 1.
  • the airfoil 1 was heated to a temperature of 1120 ° C. and placed in an appropriate ceramic mold.
  • the IN 738 cast superalloy used corresponded exactly to that of Example 1.
  • the maximum casting temperature was 1380 ° C.
  • this was equipped with cooling channels 15.
  • the intermediate layer 16 the mechanical bond between the airfoil 1 and the base piece 7 was very good.
  • the thermal shock resistance was excellent. No cracks were found after 1000 cycles.
  • the intermediate layer 16 proved to be excellent as a thermal insulation layer. With an average temperature of the airfoil of 1000 ° C, the foot piece only reached approx. 700 ° C.
  • the preheating temperature of the airfoil 1120 to 1160 ° C. and the pouring temperature of the melt 13 should not exceed 1380 ° C.
  • a blade 1 for a gas turbine rotor blade was produced from an oxide dispersion-hardened nickel-based superalloy by mechanical processing.
  • the material was in the form of a prismatic semi-finished product with a rectangular cross-section 100 mm wide and 30 mm thick in the zone-annealed, recrystallized, coarse-grained state.
  • the longitudinal stem crystals had an average length of 25 mm, a width of 8 mm and a thickness of 3.5 mm.
  • the semi-finished product was subjected to a heat treatment prior to mechanical processing in order to increase the ductility perpendicular to the longitudinal direction of the stem crystals, which resulted in an annealing at or just above the lowest possible solution annealing temperature for the ⁇ phase in the ⁇ matrix, followed by cooling with a cooling rate of existed at most 5 ° C / min.
  • the material corresponded exactly to the composition according to Example 3.
  • the head end 2 of the airfoil 1 was set down on its surface.
  • the offset part had depressions 4 in the form of circumferential grooves 2 mm deep and 2 mm wide which are rounded in the base.
  • the elevations 5 located between the grooves had similar dimensions.
  • the airfoil 1 was now preheated to a temperature of 1120 ° C. and placed in a likewise preheated mold similar to 8 in FIG. 1.
  • Example 2 The further procedure corresponded to that in Example 1.
  • the cast superalloy IN 939 corresponding to the composition according to Example 2 was used.
  • the maximum casting temperature was 1400 ° C.
  • the solidification took place in a relatively short time, which resulted in a fine-grained structure.
  • the workpiece was slowly cooled.
  • the natural oxide layer between airfoil 1 and cover plate 6 had an average thickness of 3 to 5 ⁇ m.
  • the preheating temperature of the airfoil 11 is generally 1120 to 1160 ° C. and the casting temperature of the melt 13 is at most 1400 ° C.
  • an airfoil 1 was produced from an oxide dispersion-hardened nickel-based superalloy.
  • Example 4 In contrast to Example 4, however, the semi-finished product had not previously been subjected to a heat treatment to increase the ductility.
  • the dimensions of the airfoil corresponded to those of Example 4.
  • the foot end 3 of the airfoil 1 had - seen in the axial plane of the turbine rotor - a fir tree-like shape with 3 depressions 4 and 3 elevations 5, which ensured excellent anchoring in the foot piece 7 (see FIG. 4!).
  • the airfoil 1 was preheated to a temperature of 1130 ° C. and inserted with its head end 2 and its foot end 3 into a corresponding preheated mold and sealed with ceramic adhesive.
  • the cavities of both casting molds were simultaneously filled with a melt 13 made of the cast superalloy IN 738 with the composition according to Example 1.
  • the casting temperature was 1380 ° C. Otherwise, the procedure was the same as in the previous examples.
  • the casting mold for the foot piece 7 was constructed in such a way that the latter also had a fir tree shape in the final state - in the axial section of the rotor. 5 depressions alternated with 5 elevations, the closer to the foot end 3 of the airfoil 1 approximately opposite the corresponding depressions 4 and elevations 5. Excellent intermeshing of the airfoil 1 / base 7 / rotor body was achieved, although there was no metallurgical bond.
  • the preheating temperature of the airfoil 1 should be 1130 to 1170 ° C. and the casting temperature of the melt 13 should not exceed 1380 ° C.
  • An airfoil 1 for a gas turbine rotor blade was produced by mechanical processing from an oxide dispersion-hardened nickel-base superalloy which had not been pretreated by a heat treatment to increase the ductility in accordance with Example 5.
  • the composition of the material and the dimensions and shape of the airfoil correspond exactly to the values given in Example 5.
  • the entire surface of the fir tree-shaped foot end 3 of the airfoil 1 was provided by the plasma spraying process with an average 80 ⁇ m thick intermediate layer 16 made of 1% Y2O3 doped ZrO2.
  • the airfoil 1 was then heated to a temperature of 1180 ° C. in order to dissolve as much of the ⁇ phase as possible in the ⁇ matrix of the material.
  • the foot end 3 of the airfoil 1 was then brought into a corresponding preheated mold provided with cores and sealed with ceramic adhesive.
  • the cast superalloy IN 939 with the composition of Example 2 with a liquidus temperature of approximately 1340 ° C. was used as the melt 13.
  • the casting temperature was 1380 ° C. Thanks to the cores intended for the cooling channels 15, an inadmissible accumulation of material in the area of the foot piece 7 was avoided. This allowed the solidification process to be optimally designed and a fine-grained one Structure can be achieved. The further cooling of the workpiece was carefully monitored.
  • the thermal shock test of 1000 cycles between 100 and 1000 ° C airfoil temperature with cyclical tensile stress applied at the same time showed the excellent thermal, mechanical and thermomechanical behavior of this non-metallic connection under dynamic conditions.
  • the intermediate layer 16 not only acted as a thermal insulation layer, but also took over an important mechanical function as a transmission element for elastic clamping in the reduction of voltage peaks.
  • an almost ideal composite body was created for the various types of stress: Blade 1 with coarse grain for high creep resistance at the highest temperatures; Base 7 with fine grain for high mechanical alternating loads at medium temperatures; no metallurgical bond between 1 and 7 with a critical transition zone that disturbs the structure.
  • the preheating temperature of the airfoil 1 is generally 1160 to 1180 ° C. and the casting temperature of the melt 13 is at most 1400 ° C.
  • an airfoil 1 was produced from an oxide dispersion-hardened nickel-based superalloy.
  • the alloy composition and dimensions corresponded to the values given in Example 5.
  • the airfoil 1 was heated to a temperature of 1180 ° C. and its head end 2 and foot end 3 were placed in a correspondingly preheated mold and sealed with ceramic adhesive.
  • the cavities in the casting molds were simultaneously filled with a melt 13 made of the cast superalloy IN 738 with the composition according to Example 1.
  • the casting temperature was 1370 ° C.
  • the cooling was controlled in such a way that after the melt 13 had solidified successfully, the temperature range from 1200 ° C. down to 600 ° C. was passed through in only 2 hours. An increase in the ductility of the airfoil material was thus achieved.
  • the finished workpiece was then subjected to further compaction in the area of the cover plate 6 and the foot piece 7.
  • the workpiece was first brought to a temperature of 1140 ° C without applying pressure. This temperature was in the range which was at least 100 ° C, but at most 150 ° C lower than the recrystallization temperature of the airfoil material as well as that of the cover plate 6 and the base piece 7. Thereupon the workpiece was exposed to an all-round pressure of 2000 bar and thus for 3 h hot isostatically pressed. The cooling took place at a rate of 5 ° C / min. As a result, the highest possible ductility in the transverse direction of the blade 1 was achieved. The investigation showed that a density of 100% of the theoretical value was achieved for the cover plate 6 and the foot piece 7.
  • oxide-dispersion-hardened nickel-base superalloys for the airfoil 1 and non-oxide-dispersion-hardened nickel-base superalloys can also be used for the cover plate (the cover band) 6 and the foot piece 7 of compositions other than those specified.
  • the preheating temperature for the airfoil 1 should fall in the range of 50 to 300 ° C below the solidus temperature of the low-melting phase of the airfoil material, the casting temperature of the melt 13 of the non-dispersion hardened nickel-based superalloy should be at most 100 ° C above the liquidus temperature of the high-melting phase of this alloy.
  • the temperature of the melt 13 after the end of the casting process and during solidification and that of the airfoil 1 is to be controlled in such a way that any melting of the airfoil 1 and any metallurgical bond between the airfoil 1 and cover plate 6 or airfoil 1 and foot piece 7 is avoided.
  • the entire workpiece must then be cooled down specifically to room temperature.
  • the airfoil material (semi-finished product) or the airfoil 1 itself is advantageously subjected to a heat treatment prior to casting, which involves annealing at or just above the longitudinal annealing temperature of the ⁇ phase in the ⁇ matrix of the airfoil material, followed by cooling at a maximum of 5 ° C / min.
  • the airfoil 1 can be preheated to a temperature which reaches at least a value of 50 ° C. below the lowest possible solution annealing temperature of the ⁇ phase. After casting, the speed of cooling of the airfoil 1 down to 600 ° C should not exceed 5 ° C / min.
  • the workpiece can then be cooled down to room temperature at any cooling rate.
  • the airfoil 1 can preferably be provided, at least at the head end 2 and at the foot end 3, with a 5 to 200 ⁇ m thick intermediate layer 16 made of an oxide of at least one of the elements Cr, Al, Si, Ti, Zr before the encapsulation.
  • the entire workpiece is advantageously brought to a temperature of 1050 to 1200 ° C. again after cooling to room temperature and at least 6 and / or 7 hot isostatically pressed by heating the workpiece to a temperature, which is at least 100 ° C, but at most 150 ° C lower than the recrystallization temperature of the material of both the airfoil 1 and the cover plate 6 and the foot piece 7 and that kept under a pressure of 1000 to 3000 bar at this temperature for 2 to 24 h and then cooled at a maximum of 5 ° C / min to at least 600 ° C.
  • the interruption can consist partly of the natural oxide layer, partly of cavities and have a maximum width of 5 ⁇ m.
  • an intermediate layer 16 consisting of an oxide of at least one of the elements Cr, Al, Si, Ti, Zr with a thickness of 5 to 200 ⁇ m. The latter is preferably carried out as a firmly adhering layer on the airfoil 1 of at least 100 microns thick, predominantly made of Al2O3 or ZrO2 stabilizing with Y2O3.
  • the airfoil 1 consists of an oxide dispersion-hardened, non-precipitation hardened nickel-based superalloy with increased ductility perpendicular to the longitudinal direction of the stem crystals.
  • the additional precipitation hardening is deliberately avoided in the interest of flexibility.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
EP88102415A 1987-03-19 1988-02-19 Procédé de fabrication d'une pale de turbine composite comprenant un pied, une pale et un couvercle, dans laquelle la pale est formée d'un superalliage à base de nickel durci par dispersion et pale de turbine obtenue selon ce procédé Expired - Lifetime EP0285778B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
CH1055/87A CH670406A5 (fr) 1987-03-19 1987-03-19
CH1055/87 1987-03-19

Publications (2)

Publication Number Publication Date
EP0285778A1 true EP0285778A1 (fr) 1988-10-12
EP0285778B1 EP0285778B1 (fr) 1990-08-22

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EP88102415A Expired - Lifetime EP0285778B1 (fr) 1987-03-19 1988-02-19 Procédé de fabrication d'une pale de turbine composite comprenant un pied, une pale et un couvercle, dans laquelle la pale est formée d'un superalliage à base de nickel durci par dispersion et pale de turbine obtenue selon ce procédé

Country Status (5)

Country Link
US (1) US4869645A (fr)
EP (1) EP0285778B1 (fr)
JP (1) JPS63252663A (fr)
CH (1) CH670406A5 (fr)
DE (1) DE3860472D1 (fr)

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EP1905954A1 (fr) * 2006-09-20 2008-04-02 Siemens Aktiengesellschaft Aube de turbine
US7874791B2 (en) 2005-09-15 2011-01-25 Alstom Technology Ltd. Turbomachine
EP2468434A1 (fr) * 2010-12-23 2012-06-27 General Electric Company Procédé de fabrication de composants contenans de matériaux à base ceramique et métallique
CN111070562A (zh) * 2018-10-18 2020-04-28 发那科株式会社 注塑成型机的机座

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US5238046A (en) * 1990-09-20 1993-08-24 Magotteaux International Method of manufacturing a bimetal casting and wearing part produced by this method
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FR2712307B1 (fr) * 1993-11-10 1996-09-27 United Technologies Corp Articles en super-alliage à haute résistance mécanique et à la fissuration et leur procédé de fabrication.
US5778960A (en) * 1995-10-02 1998-07-14 General Electric Company Method for providing an extension on an end of an article
US5676191A (en) * 1996-06-27 1997-10-14 General Electric Company Solidification of an article extension from a melt using an integral mandrel and ceramic mold
US5673744A (en) * 1996-06-27 1997-10-07 General Electric Company Method for forming an article extension by melting of a mandrel in a ceramic mold
US5673745A (en) * 1996-06-27 1997-10-07 General Electric Company Method for forming an article extension by melting of an alloy preform in a ceramic mold
US5743322A (en) * 1996-06-27 1998-04-28 General Electric Company Method for forming an article extension by casting using a ceramic mold
US5820348A (en) 1996-09-17 1998-10-13 Fricke; J. Robert Damping system for vibrating members
US5822852A (en) * 1997-07-14 1998-10-20 General Electric Company Method for replacing blade tips of directionally solidified and single crystal turbine blades
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EP0285778B1 (fr) 1990-08-22
JPS63252663A (ja) 1988-10-19
DE3860472D1 (de) 1990-09-27
CH670406A5 (fr) 1989-06-15
US4869645A (en) 1989-09-26

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