EP1462613A1 - Coolable coating - Google Patents
Coolable coating Download PDFInfo
- Publication number
- EP1462613A1 EP1462613A1 EP03006962A EP03006962A EP1462613A1 EP 1462613 A1 EP1462613 A1 EP 1462613A1 EP 03006962 A EP03006962 A EP 03006962A EP 03006962 A EP03006962 A EP 03006962A EP 1462613 A1 EP1462613 A1 EP 1462613A1
- Authority
- EP
- European Patent Office
- Prior art keywords
- coating
- cooling
- layer system
- coolable
- substrate
- 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.)
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- 238000000576 coating method Methods 0.000 title claims abstract description 38
- 239000011248 coating agent Substances 0.000 title claims abstract description 34
- 238000001816 cooling Methods 0.000 claims abstract description 61
- 239000000758 substrate Substances 0.000 claims description 21
- 239000000463 material Substances 0.000 description 10
- 239000002826 coolant Substances 0.000 description 7
- 238000003801 milling Methods 0.000 description 3
- 238000005229 chemical vapour deposition Methods 0.000 description 2
- 238000005553 drilling Methods 0.000 description 2
- 239000000945 filler Substances 0.000 description 2
- 238000005240 physical vapour deposition Methods 0.000 description 2
- OKTJSMMVPCPJKN-UHFFFAOYSA-N Carbon Chemical compound [C] OKTJSMMVPCPJKN-UHFFFAOYSA-N 0.000 description 1
- 239000000919 ceramic Substances 0.000 description 1
- 238000005524 ceramic coating Methods 0.000 description 1
- 229910017052 cobalt Inorganic materials 0.000 description 1
- 239000010941 cobalt Substances 0.000 description 1
- GUTLYIVDDKVIGB-UHFFFAOYSA-N cobalt atom Chemical compound [Co] GUTLYIVDDKVIGB-UHFFFAOYSA-N 0.000 description 1
- 238000002485 combustion reaction Methods 0.000 description 1
- 229910002804 graphite Inorganic materials 0.000 description 1
- 239000010439 graphite Substances 0.000 description 1
- 238000000227 grinding Methods 0.000 description 1
- 238000009413 insulation Methods 0.000 description 1
- 238000004519 manufacturing process Methods 0.000 description 1
- 229910052751 metal Inorganic materials 0.000 description 1
- 239000002184 metal Substances 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 229910052759 nickel Inorganic materials 0.000 description 1
- 230000000149 penetrating effect Effects 0.000 description 1
- 238000007750 plasma spraying Methods 0.000 description 1
- 229910052761 rare earth metal Chemical group 0.000 description 1
- 150000002910 rare earth metals Chemical group 0.000 description 1
- 229910000601 superalloy Inorganic materials 0.000 description 1
- 230000008646 thermal stress Effects 0.000 description 1
- 229910052727 yttrium Inorganic materials 0.000 description 1
- VWQVUPCCIRVNHF-UHFFFAOYSA-N yttrium atom Chemical group [Y] VWQVUPCCIRVNHF-UHFFFAOYSA-N 0.000 description 1
Images
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
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/12—Blades
- F01D5/14—Form or construction
- F01D5/18—Hollow blades, i.e. blades with cooling or heating channels or cavities; Heating, heat-insulating or cooling means on blades
- F01D5/187—Convection cooling
-
- 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
Definitions
- the invention relates to a coolable layer system according to Preamble of claim 1.
- a layer system is known from US Pat. No. 5,080,557 which has a porous structure underneath a wall, through which a cooling medium flows. This layer structure is relative thick and bad to cool.
- the US-PS 5,820,337, the US-PS 5,640,767 and the US-PS 5,392,515 show turbine blades formed from a substrate, those below an outer wall, the same Material as the substrate has, cooling channels arranged are. Cooling the outermost coating on the outer Wall is often not sufficient.
- EP 1 007 271 B1 shows an impact-cooled gas turbine blade, which, however, have no cooling channels below the outer one Wall.
- the surveys serve to support the outer wall and do not form cooling channels.
- the layer system 1 shows a coolable layer system 1.
- the layer system 1 has a substrate 4.
- the substrate 4 is, for example, a ceramic or a metal, in particular a superalloy (nickel- or cobalt-based) for gas turbine components (turbine blade, combustion chamber lining, ..).
- At least one coating 7 is applied to the substrate 4.
- a ceramic coating for example a thermal insulation layer 9 (FIG. 6), can also be applied to the coating 7.
- At least one cooling channel 10 is formed within the coating 7, ie the cooling channel 10 is formed by removing the material of the coating 7 or by applying the coating 7 while leaving out a corresponding cavity.
- the largest part of the circumferential surface of the cooling channel 10 is formed by the coating 7.
- the surface 22 mostly remains unprocessed.
- a coolant is supplied via a coolant supply 13, which is formed at least in the substrate 4 and leads into at least one cooling channel 10.
- the cooling channels 10 are thus arranged in the immediate vicinity of an outer surface which can come into contact with a hot gas 8.
- the coating 7, which is exposed to higher temperatures than the substrate 4, can thus be cooled better.
- cooling channels 10 are not arranged through channels within the coating 7, but through depressions 23 in the substrate 4.
- the coating 7 forms part of the inner surface of the cooling channel 10 and closes it off from the outside.
- cooling channels 10 both in the substrate 4 and in the coating 7 are arranged.
- the cooling channel 10 can also through a recess 23 (dashed indicated) can be formed in the coating 7.
- the cooling channels 10 according to FIGS. 1, 6 are produced as follows, for example. On the surface 22 of the substrate 4 or the surface of the coating 7, webs are filled with a filler material, which correspond in cross section to the cooling channels 10 to be produced. The substrate 4 or the coating 7 is then coated with the coating 7 or the coating 9 (plasma spraying, physical vapor deposition (PVP), chemical vapor deposition (CVD), .
- PVD physical vapor deposition
- CVD chemical vapor deposition
- the webs with the filling material are then removed.
- the material for the webs consists, for example, of graphite, which after being coated with the coating 7, 9 can be burned out or leached out. Other materials for the filling material are possible.
- corresponding depressions 23 are made in the surface 22 of the substrate.
- the depressions 23 are filled, for example, with a filler material which prevents the material of the coating 7 from penetrating into the cooling channels 10 when the substrate 4 is coated. After the application of the coating 7 or the application of an outer wall, the filling material is removed again, so that the cooling channels 10 are created.
- FIG. 3 shows the arrangement of cooling channels 10 according to FIG. 1, 2 and 6 on a surface of a component 1 (layer system).
- the layer system 1 is, for example, a turbine blade, which extends along a radial direction 16.
- At least one cooling channel 10 extends in an axial Direction 19, perpendicular (90 °) to the radial direction 16.
- the cooling channels 10 can also run at an angle deviating from 90 ° to the radial axis 16 (FIG. 4), for example approximately parallel to the radial direction 16 (0 °). All cooling channels (10) can also extend in one direction. Groups of cooling channels can also run parallel to each other.
- FIG. 4 shows a further arrangement possibility of cooling channels 10 on a surface 22 or a coating 7 a component 1.
- At least two cooling channels 10 intersect and are connected to one another, ie a cooling medium can flow from the cooling channel 10 into another cooling channel 10.
- a cooling medium can flow from the cooling channel 10 into another cooling channel 10.
- complex, meandering cooling channels are superfluous, since the entire surface to be cooled is covered by the cross pattern of the cooling channels 10. If a cooling channel 10 is blocked at one point, the cooling medium can still flow through the other cooling channels.
- the cooling medium K flows through an inlet, for example, into the cooling channels 10 'and 10''. The cooling medium passes directly from the cooling channel 10 "into the cooling channel 10"'and 10 "", etc.
- the cooling channels 10 are here, for example, crosswise in groups arranged to each other, the cooling channels 10 within of a group run parallel to each other.
- the cooling duct 10 is at least partially adjacent to the coating 7 (not shown) or to an outer wall, the cooling duct 10 of the layer system 1 to be produced has an opening 24 on the surface 22 without coatings or without an outer wall.
- the angle ⁇ between the surface 22 and the inner surface of the cooling channel 10 at the opening 24 has a value different from 90 °. This means that the cooling channel 10 has undercuts 26 with respect to the surface 22.
- Such a cooling channel 10 with undercuts 26 can also be arranged in the coating 7 (FIG. 6).
- a cooling channel 10 with undercuts 26 in the substrate 4 is produced, for example, with a milling cutter or grinding head 25, which is spherical, hemispherical or conical at one end.
- a hole is made in the substrate 4 using the milling cutter 25 or another cylindrical drill by moving it in a drilling direction 29 almost perpendicular to the surface 22 of the substrate 4.
- the cutter 25 is moved back and forth in a direction 32 perpendicular to the drilling direction 29, as indicated by the arrow, as a result of which the undercuts 26 are produced in the substrate 4.
- the various positions of the milling cutter 25 during the back and forth movement are indicated by dashed lines.
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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
Description
Die Erfindung betrifft ein kühlbares Schichtsystem gemäß Oberbegriff der Anspruchs 1.The invention relates to a coolable layer system according to Preamble of claim 1.
Aus der US-PS 5,080,557 ist ein Schichtsystem bekannt, bei dem unterhalb einer Wand eine poröse Struktur angeordnet ist, durch die ein Kühlmedium strömt. Dieser Schichtaufbau ist relativ dick und schlecht zu kühlen.A layer system is known from US Pat. No. 5,080,557 which has a porous structure underneath a wall, through which a cooling medium flows. This layer structure is relative thick and bad to cool.
Die US-PS 5,820,337, die US-PS 5,640,767 sowie die US-PS 5,392,515 zeigen aus einem Substrat gebildete Turbinenschaufeln, bei denen unterhalb einer äußeren Wand, die dasselbe Material wie das Substrat aufweist, Kühlkanäle angeordnet sind. Die Kühlung der äußersten Beschichtung auf der äußeren Wand ist vielfach nicht ausreichend.The US-PS 5,820,337, the US-PS 5,640,767 and the US-PS 5,392,515 show turbine blades formed from a substrate, those below an outer wall, the same Material as the substrate has, cooling channels arranged are. Cooling the outermost coating on the outer Wall is often not sufficient.
Die EP 1 007 271 B1 zeigt eine prallgekühlte Gasturbinenschaufel, die allerdings keine Kühlkanäle unterhalb der äußeren Wand aufweist. Die Erhebungen dienen zur Stützung der äußeren Wand und bilden keine Kühlkanäle.EP 1 007 271 B1 shows an impact-cooled gas turbine blade, which, however, have no cooling channels below the outer one Wall. The surveys serve to support the outer wall and do not form cooling channels.
Es ist daher Aufgabe der Erfindung, die Kühlung eines Schichtsystems zu verbessern.It is therefore an object of the invention to cool a To improve the layer system.
Die Aufgabe wird gelöst durch ein kühlbares Schichtsystem gemäss Anspruch 1.The task is solved by a coolable layer system according to Claim 1.
In den Unteransprüchen sind weitere vorteilhafte Maßnahmen zur Verbesserung des gekühlten Schichtsystems aufgelistet.Further advantageous measures are in the subclaims listed to improve the chilled layer system.
Die in den Unteransprüchen aufgelisteten Maßnahmen können in vorteilhafter Weise miteinander kombiniert werden. The measures listed in the subclaims can be found in can advantageously be combined with one another.
Ausführungsbeispiele der Erfindung sind im folgenden erläutert.Embodiments of the invention are explained below.
Es zeigen
- FIG 1
- ein erstes Ausführungsbeispiel des kühlbaren Schichtsystems,
- FIG 2
- ein weiteres Ausführungsbeispiel eines kühlbaren Schichtsystems, und
- die FIG 3, 4, 6
- weitere Modifikationen des kühlbaren Schichtsystems, und
- FIG 5
- einen speziell ausgebildeten Kühlkanal.
- FIG. 1
- a first embodiment of the coolable layer system,
- FIG 2
- another embodiment of a coolable layer system, and
- 3, 4, 6
- further modifications of the coolable layer system, and
- FIG 5
- a specially designed cooling channel.
FIG 1 zeigt ein kühlbares Schichtsystem 1.
Das Schichtsystem 1 weist ein Substrat 4 auf. Das Substrat 4
ist beispielsweise eine Keramik oder ein Metall, insbesondere
eine Superlegierung (nickel- oder kobaltbasiert) für Gasturbinenbauteile
(Turbinenschaufel, Brennkammerauskleidung,..).
Auf dem Substrat 4 ist zumindest eine Beschichtung 7 aufgebracht.
Die Beschichtung 7 kann eine metallische MCrAlY-Beschichtung
sein, wie sie bei Gasturbinenschaufeln verwendet
wird (M= Cr oder Fe oder Ni; Y= Yttrium oder Seltene Erde).
Darüber hinaus kann auf der Beschichtung 7 noch eine keramische
Beschichtung, beispielsweise eine Wärmedämmschicht 9
(FIG 6), aufgebracht sein.1 shows a coolable layer system 1.
The layer system 1 has a
Ausgehend von der Oberfläche 22 des Substrats 4 ist zumindest
ein Kühlkanal 10 innerhalb der Beschichtung 7 ausgebildet,
d.h. der Kühlkanal 10 entsteht durch Entfernen von Material
der Beschichtung 7 oder durch Auftragen der Beschichtung 7
unter Aussparung eines entsprechenden Hohlraums.
Somit wird der größte Teil der Umfangsfläche des Kühlkanals
10 durch die Beschichtung 7 gebildet. Die Oberfläche 22
bleibt meistens unbearbeitet. Starting from the
Thus, the largest part of the circumferential surface of the
Eine Zufuhr von einem Kühlmedium erfolgt über eine Kühlmittelzufuhr
13, die zumindest im Substrat 4 ausgebildet ist und
in zumindest einen Kühlkanal 10 führt.
Die Kühlkanäle 10 sind somit in der unmittelbaren Nähe einer
äußeren Oberfläche, die mit einem Heißgas 8 in Kontakt treten
kann, angeordnet. So kann die Beschichtung 7, die höheren
Temperaturen ausgesetzt ist als das Substrat 4, besser gekühlt
werden.A coolant is supplied via a
The
Die FIG 2 zeigt ein weiteres Ausführungsbeispiel eines kühlbaren
Schichtsystems 1.
Hier sind die Kühlkanäle 10 nicht durch Kanäle innerhalb der
Beschichtung 7, sondern durch Vertiefungen 23 im Substrat 4
angeordnet.
Die Beschichtung 7 bildet einen Teil der Innenfläche des
Kühlkanals 10 und schließt diesen nach außen hin ab.2 shows a further exemplary embodiment of a coolable layer system 1.
Here, the
The
Ebenso ist es möglich, dass die Kühlkanäle 10 sowohl im Substrat
4 als auch in der Beschichtung 7 angeordnet sind.It is also possible that the
FIG 6 zeigt Kühlkanäle 10 zwischen zwei Beschichtungen 7, 9.
Der Kühlkanal 10 kann auch durch eine Vertiefung 23 (gestrichelt
angedeutet) in der Beschichtung 7 ausgebildet sein.6 shows
Die Kühlkanäle 10 gemäss FIG 1, 6 werden beispielsweise wie
folgt hergestellt.
Auf der Oberfläche 22 des Substrats 4 bzw. der Oberfläche der
Beschichtung 7 werden Bahnen mit einem Füllmaterial gelegt,
die im Querschnitt den herzustellenden Kühlkanälen 10 entsprechen.
Das Substrat 4 bzw. die Beschichtung 7 wird dann mit der Beschichtung
7 bzw. der Beschichtung 9 beschichtet (Plasmaspritzen,
Physical Vapour Deposition (PVP), Chemical Vapour
Deposition (CVD),...). The
On the
The
Anschließend werden die Bahnen mit dem Füllmaterial entfernt.
Das Material für die Bahnen besteht beispielsweise aus Graphit,
das nach der Beschichtung mit der Beschichtung 7, 9
ausgebrannt oder ausgelaugt werden kann.
Andere Materialien für das Füllmaterial sind möglich.The webs with the filling material are then removed. The material for the webs consists, for example, of graphite, which after being coated with the
Other materials for the filling material are possible.
Für die Herstellung der Kühlkanäle 10 gemäss FIG 2 werden in
die Oberfläche 22 des Substrats entsprechende Vertiefungen 23
eingebracht. Die Vertiefungen 23 werden bspw. mit einem Füllmaterial
aufgefüllt, das verhindert, dass Material der Beschichtung
7 bei der Beschichtung des Substrats 4 in die
Kühlkanäle 10 eindringt.
Nach der Aufbringung der Beschichtung 7 oder der Aufbringung
einer äußeren Wand wird das Füllmaterial wieder entfernt, so
dass die Kühlkanäle 10 entstehen.For the production of the
After the application of the
FIG 3 zeigt die Anordnung von Kühlkanälen 10 gemäss FIG 1, 2
und 6 auf einer Oberfläche eines Bauteils 1 (Schichtsystem).
Das Schichtsystem 1 ist beispielsweise eine Turbinenschaufel,
die sich entlang einer radialen Richtung 16 erstreckt.
Zumindest ein Kühlkanal 10 erstreckt sich in einer axialen
Richtung 19, senkrecht (90°) zur radialen Richtung 16.3 shows the arrangement of
Die Kühlkanäle 10 können auch in einem von 90° abweichenden
Winkel zur radialen Achse 16 verlaufen (FIG 4), bspw. etwa
parallel zur radialen Richtung 16 (0°).
Es können sich auch alle Kühlkanäle (10) in einer Richtung
erstrecken. Gruppen von Kühlkanälen können auch parallel zueinander
verlaufen.The
All cooling channels (10) can also extend in one direction. Groups of cooling channels can also run parallel to each other.
FIG 4 zeigt eine weitere Anordnungsmöglichkeit von Kühlkanälen
10 auf einer Oberfläche 22 oder einer Beschichtung 7
eines Bauteils 1. 4 shows a further arrangement possibility of
Zumindest zwei Kühlkanäle 10 kreuzen sich und stehen miteinander
in Verbindung, d.h. ein Kühlmedium kann aus den Kühlkanal
10 in einen anderen Kühlkanal 10 strömen. Dadurch sind
aufwendige, mäanderförmige Kühlkanäle überflüssig, da durch
das Kreuzmuster der Kühlkanäle 10 die gesamte zu kühlende
Oberfläche erfasst wird. Wenn ein Kühlkanal 10 an einer
Stelle verstopft ist, kann das Kühlmedium trotzdem über die
anderen Kühlkanäle weiterfliessen.
Das Kühlmedium K strömt über ein Einlass bspw. in die Kühlkanäle
10' und 10'' ein. Aus dem Kühlkanal 10" gelangt das
Kühlmedium unmittelbar in den Kühlkanal 10 ''' und 10'''',
usw..At least two
The cooling medium K flows through an inlet, for example, into the cooling channels 10 'and 10''. The cooling medium passes directly from the cooling
Die Kühlkanäle 10 sind hier beispielsweise in Gruppen kreuzweise
zueinander angeordnet, wobei die Kühlkanäle 10 innerhalb
einer Gruppe parallel zueinander verlaufen.The cooling
Andere Anordnungen von sich kreuzenden Kühlkanälen sind denkbar.Other arrangements of intersecting cooling channels are conceivable.
FIG 5 zeigt ein speziell ausgebildeten Kühlkanal 10, bspw.
ausgehend von FIG 1.
Da der Kühlkanal 10 zumindest teilweise an die nicht dargestellte
Beschichtung 7 oder an eine äußere Wand angrenzt,
weist der Kühlkanal 10 des herzustellenden Schichtsystems 1
ohne Beschichtungen oder ohne äußere Wand an der Oberfläche
22 eine Öffnung 24 auf.
Der Winkel α zwischen der Oberfläche 22 und der Innenoberfläche
des Kühlkanals 10 an der Öffnung 24 weist einen von
90° verschiedenen Wert auf. Dies bedeutet, dass der Kühlkanal
10 gegenüber der Oberfläche 22 Hinterschneidungen 26 aufweist.
Dadurch werden bei einem hohen thermischen Gradient zwischen
äußerer heißer Beschichtung 7,9 oder der Wand und Kühlkanal
10 thermische Spannungen zwischen den Beschichtungen 7, 9
oder der Wand und dem Substrat 4 reduziert. 5 shows a specially designed cooling
Since the cooling
The angle α between the
As a result, with a high thermal gradient between the outer
Ein solcher Kühlkanal 10 mit Hinterschneidungen 26 kann auch
in der Beschichtung 7 angeordnet sein (FIG 6).Such a cooling
Ein Kühlkanal 10 mit Hinterschneidungen 26 in dem Substrat 4
wird beispielsweise mit einem Fräser oder Schleifkopf 25 hergestellt,
der an einem Ende kugel-, halbkugel- oder kegelförmig
ausgebildet ist, hergestellt.
Zuerst wird mit dem Fräser 25 oder einem anderen zylindrischen
Bohrer ein Loch in dem Substrat 4 erzeugt, indem er in
einer Bohrrichtung 29 nahezu senkrecht zur Oberfläche 22 des
Substrats 4 bewegt wird. Dann erfolgt ein durch Hin- und Herbewegen
des Fräsers 25 in einer Richtung 32 senkrecht zur
Bohrrichtung 29, wie durch den Pfeil angedeutet, wodurch die
Hinterschneidungen 26 im Substrat 4 erzeugt werden.
Die verschiedenen Stellungen des Fräsers 25 bei der Hin- und
Herbewegung sind gestrichelt angedeutet.A cooling
First, a hole is made in the
The various positions of the
Claims (7)
zumindest bestehend aus
einem Substrat (4) und
zumindest einer Beschichtung (7) auf dem Substrat (4), wobei Kühlkanäle (10) zur Kühlung verwendet werden, wobei die Kühlkanäle (10) zumindest teilweise an die Beschichtung (7) angrenzen,
dadurch gekennzeichnet, dass
zumindest zwei Kühlkanäle (10) sich kreuzen.Coolable layer system (1),
at least consisting of
a substrate (4) and
at least one coating (7) on the substrate (4), cooling channels (10) being used for cooling, the cooling channels (10) at least partially adjoining the coating (7),
characterized in that
at least two cooling channels (10) intersect.
dadurch gekennzeichnet, dass
das kühlbare Schichtsystem (1) sich in einer radialen Richtung (16) erstreckt, und
dass zumindest ein Kühlkanal (10) einen Winkel von 0° zur radialen Ausrichtung (16) aufweist.Coolable layer system according to claim 1,
characterized in that
the coolable layer system (1) extends in a radial direction (16), and
that at least one cooling duct (10) has an angle of 0 ° to the radial alignment (16).
dadurch gekennzeichnet, dass
das kühlbare Schichtsystem (1) sich in einer radialen Richtung (16) erstreckt, und
dass zumindest ein Kühlkanal (10) einen Winkel von 90° zur radialen Ausrichtung (16) aufweist. Coolable layer system according to claim 1 or 2,
characterized in that
the coolable layer system (1) extends in a radial direction (16), and
that at least one cooling duct (10) has an angle of 90 ° to the radial orientation (16).
dadurch gekennzeichnet, dass
das kühlbare Schichtsystem (1) sich in einer radialen Richtung (16) erstreckt, und
dass zumindest ein Kühlkanal (10) einen Winkel von grösser 0° bis kleiner 90° zur radialen Ausrichtung (16) aufweist.Coolable layer system according to claim 1, 2 or 3,
characterized in that
the coolable layer system (1) extends in a radial direction (16), and
that at least one cooling channel (10) has an angle of greater than 0 ° to less than 90 ° to the radial alignment (16).
dadurch gekennzeichnet, dass
zumindest ein Kühlkanal (10) zumindest teilweise innerhalb der Beschichtung (7) angeordnet ist.Coolable layer system according to claim 1,
characterized in that
at least one cooling duct (10) is arranged at least partially within the coating (7).
dadurch gekennzeichnet, dass
zumindest ein Kühlkanal (10) zwischen zwei Beschichtungen (7, 9) angeordnet ist.Coolable layer system according to one or more of the preceding claims.
characterized in that
at least one cooling channel (10) is arranged between two coatings (7, 9).
dadurch gekennzeichnet, dass
zumindest ein Kühlkanal (10) zumindest eine Hinterschneidung (26) aufweist.Coolable layer system according to claim 1,
characterized in that
at least one cooling channel (10) has at least one undercut (26).
Priority Applications (6)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| EP03006962A EP1462613A1 (en) | 2003-03-26 | 2003-03-26 | Coolable coating |
| PCT/EP2004/002223 WO2004085799A1 (en) | 2003-03-26 | 2004-03-04 | Coolable layer system |
| US10/550,973 US20060222492A1 (en) | 2003-03-26 | 2004-03-04 | Coolable layer system |
| EP04717097A EP1606494B1 (en) | 2003-03-26 | 2004-03-04 | Coolable layer system |
| DE502004003687T DE502004003687D1 (en) | 2003-03-26 | 2004-03-04 | COOLABLE COATING SYSTEM |
| ES04717097T ES2285440T3 (en) | 2003-03-26 | 2004-03-04 | COOLING SYSTEM COOLING. |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| EP03006962A EP1462613A1 (en) | 2003-03-26 | 2003-03-26 | Coolable coating |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| EP1462613A1 true EP1462613A1 (en) | 2004-09-29 |
Family
ID=32798919
Family Applications (2)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| EP03006962A Withdrawn EP1462613A1 (en) | 2003-03-26 | 2003-03-26 | Coolable coating |
| EP04717097A Expired - Lifetime EP1606494B1 (en) | 2003-03-26 | 2004-03-04 | Coolable layer system |
Family Applications After (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| EP04717097A Expired - Lifetime EP1606494B1 (en) | 2003-03-26 | 2004-03-04 | Coolable layer system |
Country Status (5)
| Country | Link |
|---|---|
| US (1) | US20060222492A1 (en) |
| EP (2) | EP1462613A1 (en) |
| DE (1) | DE502004003687D1 (en) |
| ES (1) | ES2285440T3 (en) |
| WO (1) | WO2004085799A1 (en) |
Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US7744348B2 (en) | 2004-12-24 | 2010-06-29 | Alstom Technology Ltd. | Method of producing a hot gas component of a turbomachine including an embedded channel |
| EP2431572A1 (en) * | 2010-09-21 | 2012-03-21 | Siemens Aktiengesellschaft | Thermal barrier coating for a steam turbine component |
| WO2013143886A1 (en) * | 2012-03-29 | 2013-10-03 | Siemens Aktiengesellschaft | Coated gas turbine component for high-temperature applications, having a duct system for protective gas |
| EP3179043A1 (en) * | 2015-12-08 | 2017-06-14 | General Electric Company | Turbine component comprising a cooling passage embedded within the coating |
| EP3179039A1 (en) * | 2015-12-11 | 2017-06-14 | Rolls-Royce plc | Component for a gas turbine engine |
| DE102011055246B4 (en) | 2010-11-10 | 2022-07-21 | General Electric Company | Process for manufacturing and coating components with re-entrant cooling channels |
Families Citing this family (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20110150666A1 (en) * | 2009-12-18 | 2011-06-23 | Brian Thomas Hazel | Turbine blade |
| DE102013109116A1 (en) * | 2012-08-27 | 2014-03-27 | General Electric Company (N.D.Ges.D. Staates New York) | Component with cooling channels and method of manufacture |
| US20160032766A1 (en) * | 2013-03-14 | 2016-02-04 | General Electric Company | Components with micro cooled laser deposited material layer and methods of manufacture |
| US9803939B2 (en) * | 2013-11-22 | 2017-10-31 | General Electric Company | Methods for the formation and shaping of cooling channels, and related articles of manufacture |
| DE102016205320A1 (en) * | 2016-03-31 | 2017-10-05 | Siemens Aktiengesellschaft | Turbine blade with cooling structure |
| US10830058B2 (en) | 2016-11-30 | 2020-11-10 | Rolls-Royce Corporation | Turbine engine components with cooling features |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US2641439A (en) * | 1947-10-01 | 1953-06-09 | Chrysler Corp | Cooled turbine or compressor blade |
| GB803650A (en) * | 1955-11-16 | 1958-10-29 | Birmingham Small Arms Co Ltd | Improvements in or relating to components for operation at high temperature |
| US6214248B1 (en) * | 1998-11-12 | 2001-04-10 | General Electric Company | Method of forming hollow channels within a component |
| EP1215183A1 (en) * | 2000-12-18 | 2002-06-19 | United Technologies Corporation | Ceramic matrix composite parts with channels and process of making the same |
| US20020141872A1 (en) * | 2001-03-27 | 2002-10-03 | Ramgopal Darolia | Process for forming micro cooling channels inside a thermal barrier coating system without masking material |
Family Cites Families (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB1175816A (en) * | 1968-06-24 | 1969-12-23 | Rolls Royce | Improvements relating to the Cooling of Aerofoil Shaped Blades |
| US5405242A (en) * | 1990-07-09 | 1995-04-11 | United Technologies Corporation | Cooled vane |
| US5080557A (en) * | 1991-01-14 | 1992-01-14 | General Motors Corporation | Turbine blade shroud assembly |
| US5653110A (en) * | 1991-07-22 | 1997-08-05 | General Electric Company | Film cooling of jet engine components |
| US5370499A (en) * | 1992-02-03 | 1994-12-06 | General Electric Company | Film cooling of turbine airfoil wall using mesh cooling hole arrangement |
| US5640767A (en) * | 1995-01-03 | 1997-06-24 | Gen Electric | Method for making a double-wall airfoil |
| US5820337A (en) * | 1995-01-03 | 1998-10-13 | General Electric Company | Double wall turbine parts |
| US6617003B1 (en) * | 2000-11-06 | 2003-09-09 | General Electric Company | Directly cooled thermal barrier coating system |
-
2003
- 2003-03-26 EP EP03006962A patent/EP1462613A1/en not_active Withdrawn
-
2004
- 2004-03-04 EP EP04717097A patent/EP1606494B1/en not_active Expired - Lifetime
- 2004-03-04 ES ES04717097T patent/ES2285440T3/en not_active Expired - Lifetime
- 2004-03-04 DE DE502004003687T patent/DE502004003687D1/en not_active Expired - Fee Related
- 2004-03-04 US US10/550,973 patent/US20060222492A1/en not_active Abandoned
- 2004-03-04 WO PCT/EP2004/002223 patent/WO2004085799A1/en active IP Right Grant
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US2641439A (en) * | 1947-10-01 | 1953-06-09 | Chrysler Corp | Cooled turbine or compressor blade |
| GB803650A (en) * | 1955-11-16 | 1958-10-29 | Birmingham Small Arms Co Ltd | Improvements in or relating to components for operation at high temperature |
| US6214248B1 (en) * | 1998-11-12 | 2001-04-10 | General Electric Company | Method of forming hollow channels within a component |
| EP1215183A1 (en) * | 2000-12-18 | 2002-06-19 | United Technologies Corporation | Ceramic matrix composite parts with channels and process of making the same |
| US20020141872A1 (en) * | 2001-03-27 | 2002-10-03 | Ramgopal Darolia | Process for forming micro cooling channels inside a thermal barrier coating system without masking material |
Cited By (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US7744348B2 (en) | 2004-12-24 | 2010-06-29 | Alstom Technology Ltd. | Method of producing a hot gas component of a turbomachine including an embedded channel |
| US8210815B2 (en) | 2004-12-24 | 2012-07-03 | Alstom Technology Ltd. | Hot gas component of a turbomachine including an embedded channel |
| EP2431572A1 (en) * | 2010-09-21 | 2012-03-21 | Siemens Aktiengesellschaft | Thermal barrier coating for a steam turbine component |
| DE102011055246B4 (en) | 2010-11-10 | 2022-07-21 | General Electric Company | Process for manufacturing and coating components with re-entrant cooling channels |
| WO2013143886A1 (en) * | 2012-03-29 | 2013-10-03 | Siemens Aktiengesellschaft | Coated gas turbine component for high-temperature applications, having a duct system for protective gas |
| EP3179043A1 (en) * | 2015-12-08 | 2017-06-14 | General Electric Company | Turbine component comprising a cooling passage embedded within the coating |
| US10731483B2 (en) | 2015-12-08 | 2020-08-04 | General Electric Company | Thermal management article |
| EP3179039A1 (en) * | 2015-12-11 | 2017-06-14 | Rolls-Royce plc | Component for a gas turbine engine |
Also Published As
| Publication number | Publication date |
|---|---|
| DE502004003687D1 (en) | 2007-06-14 |
| WO2004085799A1 (en) | 2004-10-07 |
| US20060222492A1 (en) | 2006-10-05 |
| EP1606494A1 (en) | 2005-12-21 |
| ES2285440T3 (en) | 2007-11-16 |
| EP1606494B1 (en) | 2007-05-02 |
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