EP3239467A1 - Flow machine, rotor blade and housing - Google Patents
Flow machine, rotor blade and housing Download PDFInfo
- Publication number
- EP3239467A1 EP3239467A1 EP16167263.9A EP16167263A EP3239467A1 EP 3239467 A1 EP3239467 A1 EP 3239467A1 EP 16167263 A EP16167263 A EP 16167263A EP 3239467 A1 EP3239467 A1 EP 3239467A1
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- EP
- European Patent Office
- Prior art keywords
- coating
- blade
- housing
- mcc
- turbomachine
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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
- F01D5/28—Selecting particular materials; Particular measures relating thereto; Measures against erosion or corrosion
- F01D5/288—Protective coatings for 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
- 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
- F01D11/122—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 with erodable or abradable material
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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
- F05D2230/30—Manufacture with deposition of material
- F05D2230/31—Layer deposition
- F05D2230/312—Layer deposition by plasma spraying
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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
- F05D2230/30—Manufacture with deposition of material
- F05D2230/31—Layer deposition
- F05D2230/313—Layer deposition by physical vapour deposition
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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
- F05D2230/90—Coating; Surface treatment
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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
- F05D2240/00—Components
- F05D2240/20—Rotors
- F05D2240/30—Characteristics of rotor blades, i.e. of any element transforming dynamic fluid energy to or from rotational energy and being attached to a rotor
- F05D2240/307—Characteristics of rotor blades, i.e. of any element transforming dynamic fluid energy to or from rotational energy and being attached to a rotor related to the tip of a rotor blade
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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
- F05D2300/00—Materials; Properties thereof
- F05D2300/50—Intrinsic material properties or characteristics
- F05D2300/514—Porosity
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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
- F05D2300/00—Materials; Properties thereof
- F05D2300/50—Intrinsic material properties or characteristics
- F05D2300/516—Surface roughness
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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
- F05D2300/00—Materials; Properties thereof
- F05D2300/60—Properties or characteristics given to material by treatment or manufacturing
- F05D2300/608—Microstructure
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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
- F05D2300/00—Materials; Properties thereof
- F05D2300/60—Properties or characteristics given to material by treatment or manufacturing
- F05D2300/611—Coating
Definitions
- the present invention relates to a turbomachine, in particular a gas turbine, having a housing and a rotor extending in the longitudinal direction of the housing, on which at least one rotor blade ring having a plurality of rotor blades is arranged, wherein a region of the housing surrounding the at least one rotor blade ring are each provided with a blade coating with an inlet lining and facing it the blade blade tips of the blades. Furthermore, the present invention relates to a blade with such a blade coating and a housing with such an inlet lining.
- the efficiency of turbomachines is directly dependent on the proportion of the guided through the housing of the turbomachine fluid flow, which drives the blades. If an existing between the stationary housing and the rotating blades gap is too large, it will lead to leakage losses, which cause a reduction in the efficiency of the turbomachine.
- One of these approaches is to provide the housing in a region circumferentially surrounding a blade ring with an inlet liner and the blade airfoils of the blade facing that inlet liner each with a blade coating, wherein the inlet coating is less wear resistant than the blade coatings. Touch the inlet lining and the blade coatings during normal operation of the turbomachine each other, so the inlet lining should be abraded while setting an optimal gap width and the airfoil tips are protected from wear by the blade coatings.
- the present invention provides a turbomachine of the type mentioned, which is characterized in that the inlet lining a HHP coating and the blade coatings each having an MCC coating. Thanks to this specific pairing, optimal results are achieved. While the Homogeneous High Porosity Coating (HHP) coating is easily abradable due to its high porosity, the segmented cracked MCC (Micro Cracked Coating) coating, which has hairline cracks extending transversely or vertically to the coating, is characterized by is dense, hard and difficult to remove, thereby effectively counteracting damage to the blade tips. Accordingly, the life of the blades is increased, resulting in extended maintenance and repair intervals.
- HHP Homogeneous High Porosity Coating
- MCC Micro Cracked Coating
- both HHP and MCC coatings are comparatively simple and inexpensive to produce, for example using an LPPS process (Low Pressure Plasma Spray), a PVD process (Physical Vapor Deposition), a HVOF process (High Velocity Oxy-Fuel ) or similar.
- the HHP coating and the MCC coatings are arranged directly opposite one another so that they form a direct friction pairing.
- the HHP coating and / or the MCC coating is / are advantageously produced from 8YSZ (yttria-stabilized zirconia), different coating methods or process parameters being used for the application of the coatings.
- 8YSZ yttria-stabilized zirconia
- the MCC coatings preferably have metal oxides and / or metal carbides and / or nitrides, whereby a high strength is ensured.
- the thickness of the HHP coating is advantageously in the range between 0.4 mm to 1.4 mm and / or the thickness of the MCC coating is at most 0.1 mm. Very good results were achieved with this coating thickness.
- the present invention further provides a blade with an airfoil, which is provided at its blade tip with a blade coating, wherein the blade coating according to the invention comprises an MCC coating, in particular an outer surface of the blade coating defines the further features already described above can have.
- the present invention provides a housing for a turbomachine, which on its inside with at least a circumferential inlet lining is provided, wherein the inlet lining has an HHP coating, which in particular defines an outer surface of the inlet lining and may have the further features already described above.
- the turbomachine 1 which in the present case is a gas turbine, comprises a housing 2 and a rotor 3 accommodated in the latter and extending in the longitudinal direction L of the housing 2, on which a plurality of moving blades 4 are arranged, which in a known manner have a number of rotor blades Forming blade stages, the longitudinal direction L are arranged spaced from each other.
- the rotor blades 4 circumferentially surrounding regions of the housing 2 are each provided with an inlet lining 5 and the inlet coverings 5 facing blade tips of the blades 4 each having a blade coating 6.
- the inlet coverings 5 each have an HHP coating 7, and the rotor blade coatings 6 each comprise an MCC coating 8, wherein the HHP coatings 7 and the MCC coatings 8 preferably form direct friction pairings, ie are arranged radially opposite each other directly.
- the HHP coatings 7 as well as the MCC coatings 8 are produced here from 8 YSZ, wherein during the application of the HHP coatings 7 on the one hand and the MCC coatings 8 on the other hand, different coating methods or at least different process parameters are used.
- the MCC coatings 7 advantageously have metal oxides and / or metal carbides and / or nitrides.
- HHP coatings 7 and MCC coatings 8 a represent optimal friction pair for the formation of a leakage leakage gap 9 between housing 2 and blades 4, which supports the formation of a minimum gap 9, a low wear of the blade tips entails and is associated with low cost.
- the inlet pads 5 each consist of an HHP coating 7 and the blade coatings 6 each consist of an MCC coating 8, the inlet pads 5 and / or the blade coatings 6 may also have other layers.
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Materials Engineering (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
Die Erfindung betrifft eine Strömungsmaschine (1), insbesondere Gasturbine, mit einem Gehäuse (2) und einem darin aufgenommen, sich in Längsrichtung (L) des Gehäuses (2) erstreckenden Läufer (3), an dem zumindest ein eine Vielzahl von Laufschaufeln (4) aufweisender Laufschaufelkranz angeordnet ist, wobei ein den zumindest einen Laufschaufelkranz umfänglich umgebender Bereich des Gehäuses (2) mit einem Einlaufbelag (5) und die diesem zugewandten Schaufelblattspitzen der Laufschaufeln (4) jeweils mit einer Laufschaufelbeschichtung (6) versehen sind, dadurch gekennzeichnet, dass der Einlaufbelag (5) eine HHP-Beschichtung (7) und die Laufschaufelbeschichtungen (6) jeweils eine MCC-Beschichtung (8) aufweisen. Ferner betrifft die Erfindung eine Laufschaufel (4) mit einer solchen Laufschaufelbeschichtung (6) sowie ein Gehäuse (2) mit einem solchen Einlaufbelag (5).The invention relates to a turbomachine (1), in particular a gas turbine, having a housing (2) and a rotor (3) extending in the longitudinal direction (L) of the housing (2), on which at least one plurality of moving blades (4 ) is arranged, wherein a the at least one blade ring circumferentially surrounding region of the housing (2) with an inlet lining (5) and the facing blade tips of the blades (4) each provided with a blade coating (6), characterized in that the inlet lining (5) has an HHP coating (7) and the rotor blade coatings (6) each have an MCC coating (8). Furthermore, the invention relates to a blade (4) with such a blade coating (6) and a housing (2) with such an inlet lining (5).
Description
Die vorliegende Erfindung betrifft eine Strömungsmaschine, insbesondere Gasturbine, mit einem Gehäuse und einem darin aufgenommen, sich in Längsrichtung des Gehäuses erstreckenden Läufer, an dem zumindest ein eine Vielzahl von Laufschaufeln aufweisender Laufschaufelkranz angeordnet ist, wobei ein den zumindest einen Laufschaufelkranz umfänglich umgebender Bereich des Gehäuses mit einem Einlaufbelag und die diesem zugewandten Schaufelblattspitzen der Laufschaufeln jeweils mit einer Laufschaufelbeschichtung versehen sind. Ferner betrifft die vorliegende Erfindung eine Laufschaufel mit einer solchen Laufschaufelbeschichtung sowie ein Gehäuse mit einem solchen Einlaufbelag.The present invention relates to a turbomachine, in particular a gas turbine, having a housing and a rotor extending in the longitudinal direction of the housing, on which at least one rotor blade ring having a plurality of rotor blades is arranged, wherein a region of the housing surrounding the at least one rotor blade ring are each provided with a blade coating with an inlet lining and facing it the blade blade tips of the blades. Furthermore, the present invention relates to a blade with such a blade coating and a housing with such an inlet lining.
Der Wirkungsgrad von Strömungsmaschinen ist unmittelbar abhängig von demjenigen Anteil des durch das Gehäuse der Strömungsmaschine geleiteten Fluidstroms, der die Laufschaufeln antreibt. Wird ein zwischen dem ortsfesten Gehäuse und den rotierenden Laufschaufeln vorhandener Spalt zu groß, so kommt es zu Leckageverlusten, die eine Reduzierung des Wirkungsgrads der Strömungsmaschine bewirken. Derzeit gibt es unterschiedliche Ansätze, eine Fluidleckage aufgrund eines zwischen dem Gehäuse und den Laufschaufeln vorhandenen Spalts zu verringern. Einer dieser Ansätze besteht darin, das Gehäuse in einem einen Laufschaufelkranz umfänglich umgebenden Bereich mit einem Einlaufbelag und die diesem Einlaufbelag zugewandten Schaufelblattspitzen der Laufschaufel jeweils mit einer Laufschaufelbeschichtung zu versehen, wobei die Einlaufbeschichtung weniger verschleißfest als die Laufschaufelbeschichtungen ausgebildet ist. Berühren der Einlaufbelag und die Laufschaufelbeschichtungen während des bestimmungsgemäßen Betriebs der Strömungsmaschine einander, so soll der Einlaufbelag unter Einstellung einer optimalen Spaltbreite abgerieben und die Schaufelblattspitzen durch die Laufschaufelbeschichtungen vor einem Verschleiß geschützt werden.The efficiency of turbomachines is directly dependent on the proportion of the guided through the housing of the turbomachine fluid flow, which drives the blades. If an existing between the stationary housing and the rotating blades gap is too large, it will lead to leakage losses, which cause a reduction in the efficiency of the turbomachine. Currently, there are various approaches to reducing fluid leakage due to a gap existing between the housing and the blades. One of these approaches is to provide the housing in a region circumferentially surrounding a blade ring with an inlet liner and the blade airfoils of the blade facing that inlet liner each with a blade coating, wherein the inlet coating is less wear resistant than the blade coatings. Touch the inlet lining and the blade coatings during normal operation of the turbomachine each other, so the inlet lining should be abraded while setting an optimal gap width and the airfoil tips are protected from wear by the blade coatings.
Untersuchungen haben allerdings ergeben, dass mit bislang vorgeschlagenen Reibpaarungen von Einlaufbelag und Laufschaufelbeschichtungen insbesondere ein Verschleiß der Schaufelblattspitzen der Laufschaufeln nicht hinreichend verhindert werden kann, weshalb die Lebensdauer der Laufschaufeln weiterhin relativ gering ist, was zu kurzen Wartungs- und Reparaturintervallen führt. Darüber hinaus wird der Spalt durch den unerwünschten Verschleiß an der Laufschaufelspitze vergrößert, was zu einer Erhöhung der Leckageverluste beiträgt. Auch sind die bislang verwendeten Reibpaarungen aus Einlaufbelag und Laufschaufelbeschichtungen sehr teuer.Investigations have shown, however, that with previously proposed friction pairings of inlet lining and blade coatings in particular wear of the blade tips of the blades can not be adequately prevented, which is why the life of the blades is still relatively low, resulting in short maintenance and repair intervals. In addition, the gap is increased by the unwanted wear on the blade tip, which contributes to an increase in the leakage losses. Also, the previously used friction pairings of inlet lining and blade coatings are very expensive.
Ausgehend von diesem Stand der Technik ist es eine Aufgabe der vorliegenden Erfindung, eine Strömungsmaschine der eingangs genannten Art mit einem alternativen Aufbau zu schaffen, ebenso wie eine entsprechende Laufschaufel und ein entsprechendes Strömungsmaschinengehäuse.Based on this prior art, it is an object of the present invention to provide a turbomachine of the type mentioned above with an alternative structure, as well as a corresponding blade and a corresponding turbomachine housing.
Zur Lösung dieser Aufgabe schafft die vorliegende Erfindung eine Strömungsmaschine der eingangs genannten Art, die dadurch gekennzeichnet ist, dass der Einlaufbelag eine HHP-Beschichtung und die Laufschaufelbeschichtungen jeweils eine MCC-Beschichtung aufweisen. Dank dieser spezifischen Paarung werden optimale Ergebnisse erzielt. Während die HHP-Beschichtung (Homogeneous High Porosity Coating) aufgrund ihrer hohen Porosität leicht abreibbar ist, zeichnet sich die segmentiert gerissene MCC-Beschichtung (Micro Cracked Coating), die sich quer bzw. vertikal zur Beschichtung erstreckende Haarrisse aufweist, dadurch aus, dass sie dicht, hart und schwierig abzutragen ist, wodurch einer Beschädigung der Laufschaufelspitzen effektiv entgegengewirkt wird. Entsprechend wird die Lebensdauer der Laufschaufeln erhöht, was dazu führt, dass Wartungs- und Reparaturintervalle verlängert werden. Darüber hinaus werden auch Leckageverluste minimiert, die auf eine Spaltvergrößerung aufgrund eines Verschleißes der Laufschaufelspitzen zurückzuführen sind. Zudem sind sowohl HHP- als auch MCC-Beschichtungen vergleichsweise einfach und preiswert herzustellen, beispielsweise unter Einsatz eines LPPS-Verfahrens (Low Pressure Plasma Spray), eines PVD-Verfahrens (Physical Vapor Deposition), eines HVOF-Verfahrens (High Velocity Oxy-Fuel) oder dergleichen.To achieve this object, the present invention provides a turbomachine of the type mentioned, which is characterized in that the inlet lining a HHP coating and the blade coatings each having an MCC coating. Thanks to this specific pairing, optimal results are achieved. While the Homogeneous High Porosity Coating (HHP) coating is easily abradable due to its high porosity, the segmented cracked MCC (Micro Cracked Coating) coating, which has hairline cracks extending transversely or vertically to the coating, is characterized by is dense, hard and difficult to remove, thereby effectively counteracting damage to the blade tips. Accordingly, the life of the blades is increased, resulting in extended maintenance and repair intervals. In addition, leakage losses are minimized due to a gap enlargement due to wear the blade tips are due. In addition, both HHP and MCC coatings are comparatively simple and inexpensive to produce, for example using an LPPS process (Low Pressure Plasma Spray), a PVD process (Physical Vapor Deposition), a HVOF process (High Velocity Oxy-Fuel ) or similar.
Gemäß einer bevorzugten Ausgestaltung der vorliegenden Erfindung sind die HHP-Beschichtung und die MCC-Beschichtungen einander unmittelbar gegenüberliegend angeordnet, so dass sie eine direkte Reibpaarung bilden.According to a preferred embodiment of the present invention, the HHP coating and the MCC coatings are arranged directly opposite one another so that they form a direct friction pairing.
Vorteilhaft ist/sind die HHP-Beschichtung und/oder die MCC-Beschichtung aus 8YSZ (Yttria-stabilised Zirconia) hergestellt, wobei zum Auftragen der Beschichtungen unterschiedliche Beschichtungsverfahren beziehungsweise Prozessparameter verwendet werden.The HHP coating and / or the MCC coating is / are advantageously produced from 8YSZ (yttria-stabilized zirconia), different coating methods or process parameters being used for the application of the coatings.
Die MCC-Beschichtungen weisen bevorzugt Metalloxide und/oder Metallcarbide und/oder Nitride auf, wodurch eine hohe Festigkeit sichergestellt ist.The MCC coatings preferably have metal oxides and / or metal carbides and / or nitrides, whereby a high strength is ensured.
Die Dicke der HHP-Beschichtung liegt vorteilhaft im Bereich zwischen 0,4 mm bis 1,4 mm und/oder die Dicke der MCC-Beschichtung beträgt maximal 0,1 mm. Mit dieser Beschichtungsdicke wurden sehr gute Resultate erzielt.The thickness of the HHP coating is advantageously in the range between 0.4 mm to 1.4 mm and / or the thickness of the MCC coating is at most 0.1 mm. Very good results were achieved with this coating thickness.
Zur Lösung der eingangs genannten Aufgabe schafft die vorliegende Erfindung ferner eine Laufschaufel mit einem Schaufelblatt, das an seiner Schaufelblattspitze mit einer Laufschaufelbeschichtung versehen ist, wobei die Laufschaufelbeschichtung erfindungsgemäß eine MCC-Beschichtung aufweist, die insbesondere eine Außenfläche der Laufschaufelbeschichtung definiert die zuvor bereits beschriebenen weiteren Merkmale aufweisen kann.To achieve the object mentioned, the present invention further provides a blade with an airfoil, which is provided at its blade tip with a blade coating, wherein the blade coating according to the invention comprises an MCC coating, in particular an outer surface of the blade coating defines the further features already described above can have.
Darüber hinaus schafft die vorliegende Erfindung ein Gehäuse für eine Strömungsmaschine, das an seiner Innenseite mit zumindest einem umlaufenden Einlaufbelag versehen ist, wobei der Einlaufbelag eine HHP-Beschichtung aufweist, die insbesondere eine Außenfläche des Einlaufbelags definiert und die zuvor bereits beschriebenen weiteren Merkmale aufweisen kann.In addition, the present invention provides a housing for a turbomachine, which on its inside with at least a circumferential inlet lining is provided, wherein the inlet lining has an HHP coating, which in particular defines an outer surface of the inlet lining and may have the further features already described above.
Weitere Merkmale und Vorteile der vorliegenden Erfindung werden anhand der nachfolgenden Beschreibung einer Ausführungsform einer erfindungsgemäßen Strömungsmaschine unter Bezugnahme auf die beiliegende Zeichnung deutlich, die eine schematische, teilweise geschnittene Teilansicht der Strömungsmaschine zeigt.Further features and advantages of the present invention will become apparent from the following description of an embodiment of a turbomachine according to the invention with reference to the accompanying drawings, which shows a schematic, partially sectioned partial view of the turbomachine.
Die Strömungsmaschine 1, bei der es sich vorliegend um eine Gasturbine handelt, umfasst ein Gehäuse 2 und einen in diesem aufgenommen, sich in Längsrichtung L des Gehäuses 2 erstreckenden Läufer 3, an dem eine Vielzahl von Laufschaufeln 4 angeordnet ist, die in bekannter Weise mehrere Laufschaufelstufen bilden, die Längsrichtung L voneinander beabstandet angeordnet sind. Die Laufschaufeln 4 umfänglich umgebende Bereiche des Gehäuses 2 sind jeweils mit einem Einlaufbelag 5 und die den Einlaufbelägen 5 zugewandten Schaufelblattspitzen der Laufschaufeln 4 jeweils mit einer Laufschaufelbeschichtung 6 versehen. Erfindungsgemäß weisen die Einlaufbeläge 5 jeweils eine HHP-Beschichtung 7 auf, und die Laufschaufelbeschichtungen 6 umfassen jeweils eine MCC-Beschichtung 8, wobei die HHP-Beschichtungen 7 und die MCC-Beschichtungen 8 bevorzugt direkte Reibpaarungen bilden, also radial einander unmittelbar gegenüber angeordnet sind. Die HHP-Beschichtungen 7 ebenso wie die MCC-Beschichtungen 8 sind vorliegend aus 8 YSZ hergestellt, wobei während des Auftragens der HHP-Beschichtungen 7 einerseits und der MCC-Beschichtungen 8 andererseits unterschiedliche Beschichtungsverfahren oder zumindest unterschiedliche Prozessparameter verwendet werden. Die MCC-Beschichtungen 7 weisen vorteilhaft Metalloxide und/oder Metallcarbide und/oder Nitride auf.The
Der wesentliche Vorteil der dargestellten Anordnung besteht darin, dass HHP-Beschichtungen 7 und MCC-Beschichtungen 8 eine optimale Reibpaarung für die Ausbildung eines leckageverlustarmen Spaltes 9 zwischen Gehäuse 2 und Laufschaufeln 4 darstellen, welche die Ausbildung eines minimalen Spaltes 9 unterstützt, einen geringen Verschleiß der Laufschaufelspitzen nach sich zieht und mit geringen Kosten einhergeht.The main advantage of the illustrated arrangement is that HHP coatings 7 and MCC coatings 8 a represent optimal friction pair for the formation of a
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. Insbesondere sei darauf hingewiesen, dass, auch wenn im Ausführungsbeispiel die Einlaufbeläge 5 jeweils aus einer HHP-Beschichtung 7 und die Laufschaufelbeschichtungen 6 jeweils aus einer MCC-Beschichtung 8 bestehen, die Einlaufbeläge 5 und/oder die Laufschaufelbeschichtungen 6 auch weitere Schichten aufweisen kann.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. In particular, it should be noted that, although in the embodiment, the
Claims (7)
dadurch gekennzeichnet, dass
die HHP-Beschichtung (7) und die MCC-Beschichtungen (8) einander unmittelbar gegenüberliegend angeordnet sind.Turbomachine (1) according to claim 1,
characterized in that
the HHP coating (7) and the MCC coatings (8) are arranged directly opposite each other.
dadurch gekennzeichnet, dass
die HHP-Beschichtung (7) und/oder die MCC-Beschichtung aus 8 YSZ hergestellt ist/sind.Turbomachine (1) according to one of the preceding claims,
characterized in that
the HHP coating (7) and / or the MCC coating is / are made from 8 YSZ.
dadurch gekennzeichnet, dass
die MCC-Beschichtungen (8) Metalloxide und/oder Metallcarbide und/oder Nitride aufweisen.Turbomachine (1) according to one of the preceding claims,
characterized in that
the MCC coatings (8) comprise metal oxides and / or metal carbides and / or nitrides.
dadurch gekennzeichnet, dass
die Dicke der HHP-Beschichtung (7) im Bereich zwischen 0,4 mm bis 1,4 mm liegt und/oder die Dicke der MCC-Beschichtung (8) maximal 0,15 mm beträgt.Turbomachine (1) according to one of the preceding claims,
characterized in that
the thickness of the HHP coating (7) is in the range between 0.4 mm to 1.4 mm and / or the thickness of the MCC coating (8) is a maximum of 0.15 mm.
dadurch gekennzeichnet, dass
die Laufschaufelbeschichtung (6) eine MCC-Beschichtung (8) aufweist, die insbesondere eine Außenfläche der Laufschaufelbeschichtung (6) definiert.Blade (4) having an airfoil provided with a blade coating (6) at its airfoil tip,
characterized in that
the blade coating (6) comprises an MCC coating (8), which in particular defines an outer surface of the blade coating (6).
dadurch gekennzeichnet, dass
der Einlaufbelag (5) eine HHP-Beschichtung (7) aufweist, die insbesondere eine Außenfläche des Einlaufbelags (5) definiert.Housing (2) for a turbomachine (1), which is provided on its inside with at least one circumferential inlet lining (5),
characterized in that
the inlet lining (5) has an HHP coating (7) which in particular defines an outer surface of the inlet lining (5).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| EP16167263.9A EP3239467A1 (en) | 2016-04-27 | 2016-04-27 | Flow machine, rotor blade and housing |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| EP16167263.9A EP3239467A1 (en) | 2016-04-27 | 2016-04-27 | Flow machine, rotor blade and housing |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| EP3239467A1 true EP3239467A1 (en) | 2017-11-01 |
Family
ID=55854680
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| EP16167263.9A Withdrawn EP3239467A1 (en) | 2016-04-27 | 2016-04-27 | Flow machine, rotor blade and housing |
Country Status (1)
| Country | Link |
|---|---|
| EP (1) | EP3239467A1 (en) |
Citations (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5630314A (en) * | 1992-09-10 | 1997-05-20 | Hitachi, Ltd. | Thermal stress relaxation type ceramic coated heat-resistant element |
| EP0916744A2 (en) * | 1997-11-18 | 1999-05-19 | Sermatech International Inc. | Strain tolerant ceramic coating |
| US20040156724A1 (en) * | 2001-06-15 | 2004-08-12 | Taiji Torigoe | Thermal barrier coating material method of production thereof, gas turbine member using the thermal barrier coating material, and gas turbine |
| WO2005071228A1 (en) * | 2004-01-21 | 2005-08-04 | Mtu Aero Engines Gmbh | Layer system for a rotor/stator seal of a turbine machine, especially a gas turbine |
| WO2007112783A1 (en) * | 2006-04-06 | 2007-10-11 | Siemens Aktiengesellschaft | Layered thermal barrier coating with a high porosity, and a component |
| EP2063072A2 (en) * | 2007-11-23 | 2009-05-27 | MTU Aero Engines GmbH | Sealing arrangement of a turbomachine and method of applying a protecting layer on a component of this turbomachine |
| EP2149623A2 (en) * | 2008-07-29 | 2010-02-03 | General Electric Company | Thermal barrier coatings and methods of producing same |
| DE102011081323B3 (en) * | 2011-08-22 | 2012-06-21 | Siemens Aktiengesellschaft | Fluid-flow machine i.e. axial-flow gas turbine, has abradable abrasion layer arranged at blade tip adjacent to radial inner side of housing and made of specific mass percent of zirconium oxide stabilized ytterbium oxide |
| US20150044035A1 (en) * | 2013-08-08 | 2015-02-12 | Solar Turbines Incorporated | High porosity abradable coating |
| EP2905426A1 (en) * | 2014-02-11 | 2015-08-12 | Siemens Aktiengesellschaft | Component with an abradable coating and a method for coating the abradable coating |
-
2016
- 2016-04-27 EP EP16167263.9A patent/EP3239467A1/en not_active Withdrawn
Patent Citations (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5630314A (en) * | 1992-09-10 | 1997-05-20 | Hitachi, Ltd. | Thermal stress relaxation type ceramic coated heat-resistant element |
| EP0916744A2 (en) * | 1997-11-18 | 1999-05-19 | Sermatech International Inc. | Strain tolerant ceramic coating |
| US20040156724A1 (en) * | 2001-06-15 | 2004-08-12 | Taiji Torigoe | Thermal barrier coating material method of production thereof, gas turbine member using the thermal barrier coating material, and gas turbine |
| WO2005071228A1 (en) * | 2004-01-21 | 2005-08-04 | Mtu Aero Engines Gmbh | Layer system for a rotor/stator seal of a turbine machine, especially a gas turbine |
| WO2007112783A1 (en) * | 2006-04-06 | 2007-10-11 | Siemens Aktiengesellschaft | Layered thermal barrier coating with a high porosity, and a component |
| EP2063072A2 (en) * | 2007-11-23 | 2009-05-27 | MTU Aero Engines GmbH | Sealing arrangement of a turbomachine and method of applying a protecting layer on a component of this turbomachine |
| EP2149623A2 (en) * | 2008-07-29 | 2010-02-03 | General Electric Company | Thermal barrier coatings and methods of producing same |
| DE102011081323B3 (en) * | 2011-08-22 | 2012-06-21 | Siemens Aktiengesellschaft | Fluid-flow machine i.e. axial-flow gas turbine, has abradable abrasion layer arranged at blade tip adjacent to radial inner side of housing and made of specific mass percent of zirconium oxide stabilized ytterbium oxide |
| US20150044035A1 (en) * | 2013-08-08 | 2015-02-12 | Solar Turbines Incorporated | High porosity abradable coating |
| EP2905426A1 (en) * | 2014-02-11 | 2015-08-12 | Siemens Aktiengesellschaft | Component with an abradable coating and a method for coating the abradable coating |
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