EP1529123B1 - Intermetallic material and use of said material - Google Patents
Intermetallic material and use of said material Download PDFInfo
- Publication number
- EP1529123B1 EP1529123B1 EP20030739941 EP03739941A EP1529123B1 EP 1529123 B1 EP1529123 B1 EP 1529123B1 EP 20030739941 EP20030739941 EP 20030739941 EP 03739941 A EP03739941 A EP 03739941A EP 1529123 B1 EP1529123 B1 EP 1529123B1
- Authority
- EP
- European Patent Office
- Prior art keywords
- intermetallic
- felt
- turbine blade
- intermetallic felt
- blade
- 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.)
- Expired - Fee Related
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Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
- F01D11/08—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator
- F01D11/12—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator using a rubstrip, e.g. erodible. deformable or resiliently-biased part
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- C—CHEMISTRY; METALLURGY
- C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
- C22C—ALLOYS
- C22C19/00—Alloys based on nickel or cobalt
- C22C19/07—Alloys based on nickel or cobalt based on cobalt
-
- C—CHEMISTRY; METALLURGY
- C23—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; CHEMICAL SURFACE TREATMENT; DIFFUSION TREATMENT OF METALLIC MATERIAL; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL; INHIBITING CORROSION OF METALLIC MATERIAL OR INCRUSTATION IN GENERAL
- C23C—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; SURFACE TREATMENT OF METALLIC MATERIAL BY DIFFUSION INTO THE SURFACE, BY CHEMICAL CONVERSION OR SUBSTITUTION; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL
- C23C30/00—Coating with metallic material characterised only by the composition of the metallic material, i.e. not characterised by the coating process
-
- 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
- F01D5/288—Protective coatings for blades
-
- 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
- Y10T428/00—Stock material or miscellaneous articles
- Y10T428/249921—Web or sheet containing structurally defined element or component
- Y10T428/249953—Composite having voids in a component [e.g., porous, cellular, etc.]
-
- 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
- Y10T428/00—Stock material or miscellaneous articles
- Y10T428/249921—Web or sheet containing structurally defined element or component
- Y10T428/249953—Composite having voids in a component [e.g., porous, cellular, etc.]
- Y10T428/249962—Void-containing component has a continuous matrix of fibers only [e.g., porous paper, etc.]
-
- 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
- Y10T428/00—Stock material or miscellaneous articles
- Y10T428/249921—Web or sheet containing structurally defined element or component
- Y10T428/249953—Composite having voids in a component [e.g., porous, cellular, etc.]
- Y10T428/249967—Inorganic matrix in void-containing component
-
- 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
- Y10T428/00—Stock material or miscellaneous articles
- Y10T428/249921—Web or sheet containing structurally defined element or component
- Y10T428/249953—Composite having voids in a component [e.g., porous, cellular, etc.]
- Y10T428/249967—Inorganic matrix in void-containing component
- Y10T428/24997—Of metal-containing material
Definitions
- the invention relates to an intermetallic material according to claims 1 and 2 and the use of this material as a felt and as a high-temperature protective layer according to claims 3 and 4.
- the guide vanes and rotor blades of gas turbines are exposed to heavy loads.
- the impeller of the gas turbine is fitted with a very small clearance to the stator, so that it comes to rub against.
- a honeycomb structure is attached on the stator of the gas turbine.
- the honeycomb structure is made of a heat-resistant metal alloy.
- Another type are smooth, coated or uncoated thermal damper segments (WSS), which radially face the rotating blade at the outer radius. The blade tip then rubs against these heat dam segments.
- WSS thermal damper segments
- the coating has only a limited liability to the turbine blade.
- cooling air bores with which either the heat spreader segment and / or the blade can be provided, are clogged during rubbing.
- EP 132,667 or DE-C2-32 03 869 It is known to use metal felts at various points of gas turbine components, such as at the tip of a turbine blade ( DE-C2-32 03 869 ), between a metal core or a ceramic outer skin ( DE-C2 32 35 230 ) or as a shell of the turbine blade ( EP-B1-132 667 ).
- these embodiments have the disadvantage that the metal felt used has insufficient oxidation resistance. Increases in hot-gas temperatures, for example in gas turbines today, mean that the materials used must always meet higher requirements. However, the metal felts in the mentioned documents no longer meet the requirement of today's standards, in particular with regard to a necessary degree of oxidation resistance.
- EP-A2-0 916 897 and EP-A2-1 076 157 are metal felts, which are composed of an intermetallic alloy, known. These felts are made of sintered and pressed intermetallic fibers and have by the intermetallic phases compared to the above materials significantly improved material properties in terms of strength, oxidation resistance, ductility and abradability. Metallic high temperature fibers have also been described in VDI Report 1151, 1995 (Metallic High Temperature Fibers by Melt Extraction - Fabrication, Properties, Applications).
- US 3,928,026 is a coating for Ni and Co base superalloys known with the following chemical composition (in wt .-%): 11-48 Co, 10-40 Cr, 9-15 Al, 0.1-1.0 reactive metal from the group of Y, Sc, Th, La and other rare earths, balance Ni, with the Ni content being at least 15%.
- the invention solves the problem of further improving the material properties of intermetallic alloys, so that they as a felt or as a high-temperature protective layer of thermal heavily loaded gas turbine components can be used.
- a suitable choice of the composition of the intermetallic alloy it should have sufficient strength, oxidation resistance, deformability, abradability and sufficient vibration damping properties.
- the present invention also relates to an intermetallic material consisting of the following composition (wt .-%) 12 Al, 22 Cr, 36 Co, 0.2 Y, 0.2 Hf, 3 Fe, balance Ni and unavoidable impurities or from 10 Al, 22 Cr , 36 Co, 0.2 Y, 0.2 Hf, 2 Ta, 3 Fe, balance Ni and unavoidable impurities.
- Such an intermetallic material can be used advantageously as a high-temperature coating of, for example, the turbine blades or other components due to the material properties.
- intermetallic felt on frictional components in thermal turbomachinery is conceivable.
- This may be, for example, the rotor or stator, the tip of a turbine blade, the turbine blades arranged opposite heat accumulation segments or the platform of the turbine blade.
- a further advantage arises when the intermetallic felt is coated with a ceramic material, since a very good adhesion of the ceramic material is achieved on the rough surface of the intermetallic felt. This gives, for example, the tip of the guide or blade good protection against thermal and friction-induced mechanical effects.
- Another advantage arises from the fact that cooling air holes are not clogged by the abrasion during operation, since it is a porous material.
- the intermetallic felt also has sufficient vibration-absorbing properties.
- a turbine blade 1 with a tip 11, an airfoil 14, a platform 12 and a blade root 13 is shown. It may be, for example, a guide or a blade of a gas turbine or a compressor.
- an intermetallic felt 2 according to the invention is arranged at the tip 11 of this turbine blade 1.
- the intermetallic felt 2 was made on the basis of a Ni-Co aluminide. To ensure adequate strength, oxidation resistance and to achieve ductility, the elements Ta, Cr, Y are added. Table 1 shows the composition according to the invention of the Ni-Co aluminide (designation IM 28 and IM 29).
- the advantage of the intermetallic felts 2 is the significantly improved oxidation resistance. From the Fig. 7 and 8th For example, the oxidation of various materials can be seen in comparison with the commercial nickel base alloys Hastelloy X, Haynes 230, Haynes 214, and the alloy SV349. Tab. 1 shows the composition of the experimental alloys.
- FIG. 8 shows the increase in weight given in Tab. 2 in [mg / cm 2 ] over a period of 12 hours at a temperature of 1200 ° C.
- the weight gain is representative of the oxidation of the materials applied. From the Fig. 8 It can be seen that the comparative alloy Hastelloy X already after a short time of about 100 min. up to approx. 300 min. has a double weight gain. As the time progresses, Hastelloy X's weight gain continues to increase, while the IM14 and IM15 intermetallic felts are set to a constant between 0.6 - 0.8 mg / cm 2 , while the IM 28 and 29 alloys are even lower.
- the oxidation resistance in the intermetallic felts is significantly improved, since a constant oxide layer has formed.
- the two alloys IM 28 and 29 differ from the alloys IM 14 and IM 15 by a Co content of 36%. This further increases the oxidation resistance of the intermetallic material.
- the Fig. 7 shows one with the Fig. 8 comparable presentation, but the experiments were carried out at a temperature of 1050 ° C.
- the intermetallic felt 2 can be coated with a ceramic material 3, for example with a TBC (Thermal Barrier Coating).
- TBC is a Y stabilized Zr oxide.
- Equivalent materials are also conceivable.
- the ceramic material 3 can be sprayed onto the intermetallic felt 2, it has by the uneven surface of the intermetallic felt 2 a very good grip on it and a good oxidation resistance.
- the ceramic material 3 is a good protection against thermal and mechanical, for example, frictional effects.
- cooling air holes which may be present in the turbine blade 1 or on the rotor / stator 4, do not clog, since the intermetallic felt 2 is a porous material.
- FIG. 2 schematically shows a representation of a gas turbine with a rotor 4a, a stator 4b.
- blades 6, on the stator 7 vanes 7 are attached.
- heat guide segments 8 are usually arranged opposite the guide vanes 6, 7.
- these heat barrier segments 8 may also consist wholly or partly of an intermetallic felt. Due to the porous properties improved cooling at this point is also possible if it has come to an abrasion, as the porous structure of the intermetallic felt prevents clogging.
- the abrasion can be reduced as already described by a layer of TBC.
- the component may also be cooled below the TBC layer, since the cooling medium can escape laterally through the porous felt.
- the FIG. 5 shows a heat recovery segment according to the invention 8 according to the section V in the FIG. 2 ,
- the intermetallic felt 2 was attached to a supporting base structure 5.
- the supporting base structure 5 has fastening means 9, which for attachment to in the FIG. 5 not shown rotor 4a and stator 4b are used.
- the lateral fastening means 9 are interconnected by struts 10. Between the struts 10 is on the side which faces the turbine blades, the intermetallic felt 2 is used and mechanically connected thereto. This can be done for example by soldering, welding or pouring. For reasons of durability, the felt should be firmly bonded to the supporting base structure 5.
- FIG. 6 shows the section VI-VI of FIG. 5 ,
- the struts 10 connecting the two fastening means 9 do not penetrate the intermetallic felt 2, but the intermetallic felt 2 is merely attached to them.
- the intermetallic felt 2 can in turn be coated with a ceramic material 3, for example with a TBC (Thermal Barrier Coating). Equivalent materials are also conceivable.
- a cooling effect is maintained even with abrasion, since there is no clogging of the intermetallic felt 2.
- the intermetallic felt in the embodiment in the FIG. 3 mounted on the platform 12 of the turbine blade 1 of the thermal turbomachinery. Again, it makes sense, as with the Figure 1,2 . 5 and 6 described to coat the felt 2 with a ceramic material 3.
- This has the advantage that the TBC adheres particularly well to the intermetallic felt and the felt is oxidation resistant. There is no additional binding layer (eg MCrA-IY) needed. In the FIG. 3 this is shown next to the right turbine blade 1.
- the TBC also serves as protection against wear.
- FIG. 4 shows a second variant of the embodiment of the detail IV of Figure 3.
- a supporting base structure 5 consisting of a casting or other metal attached.
- the supporting basic structure 5 may also consist of different chambers in order to ensure an optimal air supply to the intermetallic felt 2.
- the intermetallic felt can also be used at points within the gas turbine that are subject to vibration, since the felt in addition to the aforementioned oxidation resistance also has very good vibration damping properties.
- an intermetallic material according to the invention can advantageously also be used as a high-temperature coating 15 on the turbine blades or other components.
- the two alloys also have improved oxidation properties, unlike the SV 349 alloy.
- various prior art coating methods are known for applying the protective layer, for example, a plasma spray method.
- a plasma spray method In this case, an existing of the material to be applied, metallic powder is introduced into a flame or a plasma jet. This powder melts on the spot and is sprayed against the surface to be coated, where the material solidifies and forms a continuous layer.
- a physical (or chemical) vapor deposition process is also possible.
- solid coating material is heated in block form and evaporated (eg with a laser or an electron beam). The vapor settles on the base material and forms a coating there after an adequate time.
- Other, equivalent coating methods are also conceivable.
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- Chemical & Material Sciences (AREA)
- Mechanical Engineering (AREA)
- Materials Engineering (AREA)
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- Chemical Kinetics & Catalysis (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
Description
Die Erfindung betrifft ein intermetallisches Material gemäss den Ansprüchen 1 und 2 und die Verwendung dieses Materials als Filz und als Hochtemperaturschutzschicht gemäss den Ansprüchen 3 und 4.The invention relates to an intermetallic material according to
Die Leit- und Laufschaufeln von Gasturbinen sind starken Belastungen ausgesetzt. Um die Leckageverluste der Gasturbine klein zu halten wird beispielsweise das Laufrad der Gasturbine mit einem sehr kleinen Spiel zum Stator eingepasst, so dass es zum Anstreifen kommt. An dem Stator der Gasturbine ist eine Honigwabenstrukur angebracht. Die Honigwabenstruktur besteht aus einer warmfesten Metallegierung. Eine weitere Bauart sind glatte, beschichtete oder unbeschichtete Wärmestausegmente (WSS), welche der rotierenden Schaufel am Aussenradius radial gegenüberstehen. Die Schaufelspitze reibt dann gegen diese Wärmestausegmente. Um zu verhindern, dass die Schaufelspitze selbst abgerieben wird, kann sie beschichtet sein, um dann in einem grösseren Masse die Wärmestausegmente abzureiben. Nachteilig ist aber bei dieser Ausführungsform, dass die Beschichtung nur eine begrenzte Haftbarkeit an der Turbinenschaufel hat. Zudem ist nachteilig, dass Kühlluftbohrungen, mit welchen entweder das Wärmestausegment und/oder die Schaufel versehen sein können, beim Reiben verstopft werden.The guide vanes and rotor blades of gas turbines are exposed to heavy loads. In order to keep the leakage losses of the gas turbine small, for example, the impeller of the gas turbine is fitted with a very small clearance to the stator, so that it comes to rub against. On the stator of the gas turbine, a honeycomb structure is attached. The honeycomb structure is made of a heat-resistant metal alloy. Another type are smooth, coated or uncoated thermal damper segments (WSS), which radially face the rotating blade at the outer radius. The blade tip then rubs against these heat dam segments. In order to prevent the blade tip itself from being rubbed off, it can be coated to then rub off the heat release segments to a greater extent. A disadvantage, however, in this embodiment, that the coating has only a limited liability to the turbine blade. In addition, it is disadvantageous that cooling air bores, with which either the heat spreader segment and / or the blade can be provided, are clogged during rubbing.
Aus den Schriften
Aus
Aus
Die Erfindung, wie sie in den unabhängigen Ansprüchen gekennzeichnet ist, löst die Aufgabe, die Materialeigenschaften von intermetallischen Legierungen noch weiter zu verbessern, so dass sie als Filz oder als Hochtemperaturschutzschicht an thermisch stark belasteten Gasturbinenbauteilen eingesetzt werden können. Durch eine entsprechende Wahl der Zusammensetzung der intermetallischen Legierung soll sie eine ausreichende Festigkeit, Oxidationsbeständigkeit, Verformbarkeit, Abreibbarkeit und ausreichende schwingungsdämpfende Eigenschaften besitzen.The invention, as characterized in the independent claims, solves the problem of further improving the material properties of intermetallic alloys, so that they as a felt or as a high-temperature protective layer of thermal heavily loaded gas turbine components can be used. By a suitable choice of the composition of the intermetallic alloy, it should have sufficient strength, oxidation resistance, deformability, abradability and sufficient vibration damping properties.
Die vorliegende Erfindung bezieht sich auch auf ein intermetallisches Material bestehend aus folgender Zusammensetzung (Gew.-%) 12 Al, 22 Cr, 36 Co, 0.2 Y, 0.2 Hf, 3 Fe, Rest Ni und unvermeidbare Verunreinigungen oder aus 10 Al, 22 Cr, 36 Co, 0.2 Y, 0.2 Hf, 2 Ta, 3 Fe, Rest Ni und unvermeidbare Verunreinigungen.The present invention also relates to an intermetallic material consisting of the following composition (wt .-%) 12 Al, 22 Cr, 36 Co, 0.2 Y, 0.2 Hf, 3 Fe, balance Ni and unavoidable impurities or from 10 Al, 22 Cr , 36 Co, 0.2 Y, 0.2 Hf, 2 Ta, 3 Fe, balance Ni and unavoidable impurities.
Ein solches intermetallisches Material kann aufgrund der Materialeigenschaften vorteilhaft als Hochtemperaturbeschichtung von beispielsweise den Turbinenschaufeln oder anderen Bauteilen eingesetzt werden.Such an intermetallic material can be used advantageously as a high-temperature coating of, for example, the turbine blades or other components due to the material properties.
Auch die Verwendung als intermetallischer Filz an reibungsbehafteten Komponenten in thermischen Turbomaschinen ist denkbar. Es kann sich dabei beispielsweise um den Rotor oder Stator, die Spitze einer Turbinenschaufel, um die der Turbinenschaufel gegenüberliegend angeordneten Wärmestausegmente oder um die Plattform der Turbinenschaufel handeln. Ein weiterer Vorteil entsteht, wenn der intermetallische Filz mit einem keramischen Material überzogen ist, da auf der rauhen Oberfläche des intermetallischen Filzes eine sehr gute Haftbarkeit des keramischen Materials erzielt wird. Dadurch erhält beispielsweise die Spitze der Leit- oder Laufschaufel einen guten Schutz gegen thermische und gegen durch Reibung bedingte mechanische Einwirkungen. Ein weiterer Vorteil entsteht dadurch, dass Kühlluftbohrungen durch den Abrieb während des Betriebes nicht verstopfen, da es sich um ein poröses Material handelt. Zudem hat der intermetallische Filz auch ausreichende schwingungsabsorbierende Eigenschaften.Also, the use as intermetallic felt on frictional components in thermal turbomachinery is conceivable. This may be, for example, the rotor or stator, the tip of a turbine blade, the turbine blades arranged opposite heat accumulation segments or the platform of the turbine blade. A further advantage arises when the intermetallic felt is coated with a ceramic material, since a very good adhesion of the ceramic material is achieved on the rough surface of the intermetallic felt. This gives, for example, the tip of the guide or blade good protection against thermal and friction-induced mechanical effects. Another advantage arises from the fact that cooling air holes are not clogged by the abrasion during operation, since it is a porous material. In addition, the intermetallic felt also has sufficient vibration-absorbing properties.
Die Erfindung wird an Hand der beiliegenden Zeichnungen erläutert, in denen
- Fig. 1
- eine Ausführungsform einer erfindungsgemässen Turbinenschaufel mit einem intermetallischen Filz an der Spitze zeigt,
- Fig. 2
- eine Ausführungsform einer Gasturbine mit Wärmestausegmenten, welche der Leit- bzw. Laufschaufel gegenüberliegend angeordnet sind und aus ei- nem intermetallischen Filz bestehen, darstellt,
- Fig. 3
- eine zweite Ausführungsform einer erfindungsgemässen Turbinenschaufel, wobei der intermetallische Filz auf der Plattform der Turbinenschaufel an- geordnet ist, darstellt,
- Fig. 4
- eine Variante der zweiten Ausführungsform des Details IV der
, wobei der intermetallische Filz zwischen den Turbinenschaufeln auf den Plattformen der Turbinenschaufeln auf einer tragenden Grundstruktur an- geordnet ist, darstellt,Figur 3 - Fig. 5
- ein erfindungsgemässes Wärmestausegment mit einer tragenden Grund- struktur gemäss dem Ausschnitt V in der
Fig. 2 zeigt, - Fig. 6
- einen Schnitt durch das Wärmestausegment gemäss der Linie VI-VI in der
Fig. 5 darstellt, - Fig. 7
- eine Darstellung des Oxidationsverhaltens von verschiedenen Materialien bei einer Temperatur von 1050°C zeigt und
- Fig. 8
- eine Darstellung des Oxidationsverhaltens von verschiedenen Materialien bei einer Temperatur von 1200°C zeigt.
- Fig. 1
- shows an embodiment of a turbine blade according to the invention with an intermetallic felt at the tip,
- Fig. 2
- an embodiment of a gas turbine with heat spreader segments, which are arranged opposite the guide blade and consist of an intermetallic felt,
- Fig. 3
- A second embodiment of a turbine blade according to the invention, wherein the intermetallic felt is arranged on the platform of the turbine blade,
- Fig. 4
- a variant of the second embodiment of the detail IV of
FIG. 3 in which the intermetallic felt is arranged between the turbine blades on the platforms of the turbine blades on a supporting basic structure, - Fig. 5
- an inventive thermal segment with a supporting basic structure according to the section V in the
Fig. 2 shows, - Fig. 6
- a section through the heat dissipation segment according to the line VI-VI in the
Fig. 5 represents, - Fig. 7
- shows a representation of the oxidation behavior of various materials at a temperature of 1050 ° C and
- Fig. 8
- shows a representation of the oxidation behavior of various materials at a temperature of 1200 ° C.
Es sind nur die für die Erfindung wesentlichen Elemente dargestellt. Gleiche Elemente sind in unterschiedlichen Figuren mit gleichen Bezugszeichen versehen.Only the elements essential to the invention are shown. Identical elements are provided in different figures with the same reference numerals.
In der
Der Vorteil der intermetallischen Filze 2 ist die deutlich verbesserte Oxidationsbeständigkeit. Aus den
Zusammensetzung von Versuchslegierungen (Angaben in Gew.-%)
Die
Die
Um die Festigkeit dieser Turbinenschaufel 1 der
In der
Die
Die
Zu verbesserten Kühlzwecken ist der intermetallische Filz im Ausführungsbeispiel in der
Der intermetallischen Filzes kann auch an Stellen innerhalb der Gasturbine eingesetzt werden, die schwingungsbehaftet sind, da der Filz neben der erwähnten Oxidationsbeständigkeit zudem sehr gute schwingungsdämpfende Eigenschaften besitzt.The intermetallic felt can also be used at points within the gas turbine that are subject to vibration, since the felt in addition to the aforementioned oxidation resistance also has very good vibration damping properties.
Ein erfindungsgemässes intermetallisches Material kann aufgrund der Materialeigenschaften vorteilhaft auch als Hochtemperaturbeschichtung 15 an den Turbinenschaufeln oder anderen Bauteilen eingesetzt werden. Wie aus den beiden
Auch ein physikalisches (oder chemisches) Aufdampf-Verfahren ist möglich. Bei diesem Verfahren wird festes Beschichtungsmaterial in blockförmiger Form erhitzt und evaporiert (z.B. mit einem Laser oder einem Elektronenstrahl). Der Dampf schlägt sich auf dem Grundmaterial nieder und bildet dort nach einer adäquaten Zeit eine Beschichtung. Andere, gleichwertige Beschichtungsverfahren sind ebenso denkbar.A physical (or chemical) vapor deposition process is also possible. In this process, solid coating material is heated in block form and evaporated (eg with a laser or an electron beam). The vapor settles on the base material and forms a coating there after an adequate time. Other, equivalent coating methods are also conceivable.
- 11
- Turbinenschaufelturbine blade
- 22
- Intermetallischer FilzIntermetallic felt
- 33
- Keramischer ÜberzugCeramic coating
- 44
- Rotor bzw. StatorRotor or stator
- 4a4a
- Rotorrotor
- 4b4b
- Statorstator
- 55
- Tragende GrundstrukturCarrying basic structure
- 66
- Laufschaufelblade
- 77
- Leitschaufelvane
- 88th
- WärmestausegmentHeat shield
- 99
- Befestigungsmittelfastener
- 1010
- Strebenpursuit
- 1111
-
Spitze der Turbinenschaufel 1Tip of the
turbine blade 1 - 1212
- Plattformplatform
- 1313
-
Schaufelfuss der Turbinenschaufel 1Blade of the
turbine blade 1 - 1414
-
Schaufelblatt der Turbinenschaufel 1Airfoil of the
turbine blade 1 - 1515
- HochtemperaturbeschichtungHigh temperature coating
Claims (10)
- Intermetallic material, consisting of the following composition (% by weight: 12 Al, 22 Cr, 36 Co, 0.2 Y, 0.2 Hf, 3 Fe, remainder Ni and inevitable impurities.
- Intermetallic material, consisting of the following composition (% by weight): 10 Al, 22 Cr, 36 Co, 0.2 Y, 0.2 Hf, 2 Ta, 3 Fe, remainder Ni and inevitable impurities.
- Use of the intermetallic material according to one of Claims 1 to 2 as a high-temperature coating (15) in thermal turbomachines.
- Use of the intermetallic material according to one of Claims 1 to 2 as a felt on components which are subject to friction in thermal turbomachines.
- Use of the intermetallic felt according to Claim 4, characterized in that the intermetallic felt is arranged on a rotor (4, 4a) or stator (4, 4b).
- Use of the intermetallic felt according to Claim 4, characterized in that the component (1, 8) is a turbine blade or vane (1), and the tip (11) of the turbine blade or vane (1) is equipped with an intermetallic felt (2).
- Use of the intermetallic felt according to Claim 4, characterized in that the component (1, 8) is a turbine blade or vane (1) and the platform (12) of the turbine blade or vane (1) is equipped with an intermetallic felt (2).
- Use of the intermetallic felt according to Claim 4, characterized in that the component (1, 8) is a heat shield segment (8) made partially or completely from an intermetallic felt (2).
- Use of the intermetallic felt according to one of Claims 4 to 7, characterized in that the intermetallic felt (2) is covered with a ceramic material (3).
- Use of the intermetallic felt according to Claim 4, characterized in that the felt is used on components which are subject to vibration in thermal turbomachines.
Applications Claiming Priority (3)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
CH140602 | 2002-08-16 | ||
CH14062002 | 2002-08-16 | ||
PCT/CH2003/000503 WO2004016819A1 (en) | 2002-08-16 | 2003-07-24 | Intermetallic material and use of said material |
Publications (2)
Publication Number | Publication Date |
---|---|
EP1529123A1 EP1529123A1 (en) | 2005-05-11 |
EP1529123B1 true EP1529123B1 (en) | 2011-10-05 |
Family
ID=31722378
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP20030739941 Expired - Fee Related EP1529123B1 (en) | 2002-08-16 | 2003-07-24 | Intermetallic material and use of said material |
Country Status (5)
Country | Link |
---|---|
US (1) | US7141128B2 (en) |
EP (1) | EP1529123B1 (en) |
CN (1) | CN100430499C (en) |
AU (1) | AU2003285270A1 (en) |
WO (1) | WO2004016819A1 (en) |
Families Citing this family (11)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US7316850B2 (en) | 2004-03-02 | 2008-01-08 | Honeywell International Inc. | Modified MCrAlY coatings on turbine blade tips with improved durability |
US7378132B2 (en) * | 2004-12-14 | 2008-05-27 | Honeywell International, Inc. | Method for applying environmental-resistant MCrAlY coatings on gas turbine components |
JP2006291307A (en) | 2005-04-12 | 2006-10-26 | Mitsubishi Heavy Ind Ltd | Component of rotary machine, and rotary machine |
EP1818419A1 (en) * | 2006-01-16 | 2007-08-15 | Siemens Aktiengesellschaft | Alloy, protective layer and component |
GB0807008D0 (en) * | 2008-04-17 | 2008-05-21 | Advanced Interactive Materials | Helicoidal motors for use in down-hole drilling |
US8273148B2 (en) | 2009-01-30 | 2012-09-25 | Untied Technologies Corporation | Nickel braze alloy composition |
EP2374909B1 (en) * | 2010-03-30 | 2015-09-16 | United Technologies Corporation | Improved nickel braze alloy composition |
CN107663605A (en) * | 2016-07-29 | 2018-02-06 | 泰州市艾瑞克新型材料有限公司 | Single crystal turbine blade sawtooth is preced with damping area wear-resistant coating and its preparation technology |
EP3985138A1 (en) * | 2020-10-14 | 2022-04-20 | Siemens Energy Global GmbH & Co. KG | Nicocral based alloy, a powder, a coating and a component |
US11426822B2 (en) * | 2020-12-03 | 2022-08-30 | General Electric Company | Braze composition and process of using |
CN115747607B (en) * | 2023-01-10 | 2023-04-14 | 西安稀有金属材料研究院有限公司 | High-entropy alloy sheet for fiber metal laminate and preparation method thereof |
Family Cites Families (20)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
GB607616A (en) * | 1945-11-28 | 1948-09-02 | Harold Ernest Gresham | Nickel base alloy |
GB1456554A (en) | 1973-03-28 | 1976-11-24 | United Aircraft Corp | High temperature abradable material |
US3928026A (en) * | 1974-05-13 | 1975-12-23 | United Technologies Corp | High temperature nicocraly coatings |
US4101713A (en) * | 1977-01-14 | 1978-07-18 | General Electric Company | Flame spray oxidation and corrosion resistant superalloys |
US4447503A (en) * | 1980-05-01 | 1984-05-08 | Howmet Turbine Components Corporation | Superalloy coating composition with high temperature oxidation resistance |
US4615864A (en) * | 1980-05-01 | 1986-10-07 | Howmet Turbine Components Corporation | Superalloy coating composition with oxidation and/or sulfidation resistance |
DE3203869C2 (en) | 1982-02-05 | 1984-05-10 | MTU Motoren- und Turbinen-Union München GmbH, 8000 München | Turbine rotor blades for turbo machines, in particular gas turbine engines |
JPS58153752A (en) * | 1982-03-08 | 1983-09-12 | Takeshi Masumoto | Ni-cr alloy material |
DE3235230A1 (en) | 1982-09-23 | 1984-03-29 | MTU Motoren- und Turbinen-Union München GmbH, 8000 München | Gas turbine blade having a metal core and a ceramic vane |
DE3327218A1 (en) | 1983-07-28 | 1985-02-07 | MTU Motoren- und Turbinen-Union München GmbH, 8000 München | THERMALLY HIGH-QUALITY, COOLED COMPONENT, IN PARTICULAR TURBINE BLADE |
US5192625A (en) * | 1990-02-28 | 1993-03-09 | General Electric Company | Cobalt-base wrought alloy compositions and articles |
US5536022A (en) * | 1990-08-24 | 1996-07-16 | United Technologies Corporation | Plasma sprayed abradable seals for gas turbine engines |
US5455119A (en) * | 1993-11-08 | 1995-10-03 | Praxair S.T. Technology, Inc. | Coating composition having good corrosion and oxidation resistance |
AU2663797A (en) * | 1996-04-10 | 1997-10-29 | Penn State Research Foundation, The | Improved superalloys with improved oxidation resistance and weldability |
DE19750517A1 (en) | 1997-11-14 | 1999-05-20 | Asea Brown Boveri | Heat shield |
DE19848103A1 (en) * | 1998-10-19 | 2000-04-20 | Asea Brown Boveri | Sealing arrangement |
DE19848104A1 (en) * | 1998-10-19 | 2000-04-20 | Asea Brown Boveri | Turbine blade |
DE19912701B4 (en) | 1999-03-20 | 2006-01-19 | Alstom | combustion chamber wall |
KR100372482B1 (en) * | 1999-06-30 | 2003-02-17 | 스미토모 긴조쿠 고교 가부시키가이샤 | Heat resistant Ni base alloy |
DE19937577A1 (en) * | 1999-08-09 | 2001-02-15 | Abb Alstom Power Ch Ag | Frictional gas turbine component |
-
2003
- 2003-07-24 US US10/524,889 patent/US7141128B2/en not_active Expired - Fee Related
- 2003-07-24 CN CNB038239647A patent/CN100430499C/en not_active Expired - Fee Related
- 2003-07-24 EP EP20030739941 patent/EP1529123B1/en not_active Expired - Fee Related
- 2003-07-24 AU AU2003285270A patent/AU2003285270A1/en not_active Abandoned
- 2003-07-24 WO PCT/CH2003/000503 patent/WO2004016819A1/en not_active Application Discontinuation
Also Published As
Publication number | Publication date |
---|---|
US7141128B2 (en) | 2006-11-28 |
AU2003285270A1 (en) | 2004-03-03 |
CN100430499C (en) | 2008-11-05 |
WO2004016819A1 (en) | 2004-02-26 |
CN1708598A (en) | 2005-12-14 |
US20060127660A1 (en) | 2006-06-15 |
EP1529123A1 (en) | 2005-05-11 |
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