EP1606494B1 - Coolable layer system - Google Patents
Coolable layer system Download PDFInfo
- Publication number
- EP1606494B1 EP1606494B1 EP04717097A EP04717097A EP1606494B1 EP 1606494 B1 EP1606494 B1 EP 1606494B1 EP 04717097 A EP04717097 A EP 04717097A EP 04717097 A EP04717097 A EP 04717097A EP 1606494 B1 EP1606494 B1 EP 1606494B1
- Authority
- EP
- European Patent Office
- Prior art keywords
- layer system
- cooling
- coating
- cooling channels
- coolable
- 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 - Lifetime
Links
- 238000001816 cooling Methods 0.000 claims abstract description 69
- 238000000576 coating method Methods 0.000 claims description 34
- 239000011248 coating agent Substances 0.000 claims description 30
- 239000000758 substrate Substances 0.000 claims description 21
- 239000011253 protective coating Substances 0.000 abstract 1
- 239000002826 coolant Substances 0.000 description 7
- 239000000463 material Substances 0.000 description 7
- 239000000945 filler Substances 0.000 description 3
- 238000005229 chemical vapour deposition Methods 0.000 description 2
- 238000005553 drilling Methods 0.000 description 2
- 238000005240 physical vapour deposition Methods 0.000 description 2
- 229910052727 yttrium Inorganic materials 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
- 229910052804 chromium Inorganic materials 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
- 229910002804 graphite Inorganic materials 0.000 description 1
- 239000010439 graphite Substances 0.000 description 1
- 238000000227 grinding Methods 0.000 description 1
- 229910052742 iron Inorganic materials 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
- 238000003801 milling Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 229910052759 nickel Inorganic materials 0.000 description 1
- 230000000149 penetrating effect Effects 0.000 description 1
- 230000002093 peripheral effect Effects 0.000 description 1
- 238000007750 plasma spraying Methods 0.000 description 1
- 229910052761 rare earth metal Chemical group 0.000 description 1
- 229910000601 superalloy Inorganic materials 0.000 description 1
- 239000012720 thermal barrier coating Substances 0.000 description 1
- 230000008646 thermal stress Effects 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 the preamble of claim 1.
- EP 1 007 271 B1 shows a gas turbine blade which has a full cooling, but which does not have cooling channels below the outer wall. The elevations serve to support the outer wall and do not form cooling channels.
- US 2002/0141872 A1 discloses a coolable layer system according to the preamble of claim 1.
- FIG. 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, B-rennhuntausposition, ..).
- At least one coating 7 is applied to the substrate 4.
- a ceramic coating for example a thermal barrier coating 9 (FIG. 6), may be applied to the coating 7.
- At least one cooling channel 10 is formed here, for example, 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, leaving a corresponding cavity.
- the cooling channel 10 is formed by removing the material of the coating 7 or by applying the coating 7, leaving a corresponding cavity.
- most of the peripheral surface of the cooling passage 10 is formed by the coating 7.
- the surface 22 remains mostly unprocessed.
- a supply of a cooling medium takes place 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 be cooled better.
- FIG. 2 shows a further exemplary embodiment of a coolable layer system 1.
- the cooling channels 10 are not arranged by channels within the coating 7, but for example.
- the coating 7 forms part of the inner surface of the cooling channel 10 and closes it to the outside.
- cooling channels 10 are arranged both in the substrate 4 and in the coating 7.
- FIG. 6 shows cooling channels 10 between two coatings 7, 9.
- the cooling channel 10 may also be formed by a recess 23 (indicated by dashed lines) in the coating 7.
- the cooling channels 10 according to FIGS. 1, 6 are produced, for example, as follows. On the surface 22 of the substrate 4 and the surface of the coating 7 webs are placed with a filler, 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), ). Subsequently, the webs are removed with the filler.
- the material for the webs consists for example of graphite, which can be burned out or leached after coating with the coating 7, 9. Other materials for the filler are possible.
- corresponding depressions 23 are introduced into the surface 22 of the substrate.
- the recesses 23 are, for example, filled with a filling material which prevents material of the coating 7 from penetrating into the cooling channels 10 during the coating of the substrate 4. 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 formed.
- FIG. 3 shows the arrangement of cooling channels 10 according to FIGS. 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 extend in an angle deviating from 90 ° to the radial axis 16 (FIG. 4), for example, approximately parallel to the radial direction 16 (0 °). It can also extend all the cooling channels (10) in one direction. Groups of cooling channels can also run parallel to each other.
- FIG. 4 shows another possible arrangement of cooling channels 10 according to FIGS. 1, 2 and 6 on a surface 22 or a coating 7 of a component 1.
- At least two cooling channels 10 intersect and communicate with each other, 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 at least partially, in particular the entire surface to be cooled of the component 1 is detected by the cross pattern of the cooling channels 10, ie the cross pattern and the intersections of the cooling channels extends at least partially or completely above or below the surface to be cooled Surface.
- FIG. 4 for example, eight intersections of cooling channels 10 are present.
- the surface to be cooled may be a partial area or the entire surface of a blade of a turbine blade (component 1). If a cooling channel 10 is clogged at one point, the cooling medium can still continue to flow over the other cooling channels.
- the cooling medium K flows into the cooling channels 10 'and 10 "via an inlet, for example. From the cooling channel 10", the cooling medium passes directly into the cooling channels 10''' and 10 ''''
- the cooling channels 10 are arranged here, for example, in groups crosswise to each other, wherein the cooling channels 10 within a group parallel to each other.
- intersecting cooling channels 10 can detect a surface to be cooled by connecting meandering cooling channels to intersecting cooling channels.
- FIG. 5 shows a specially designed cooling channel 10, for example, starting from FIG. Since the cooling channel 10 is at least partially adjacent to the coating 7, not shown, or to an outer wall, the cooling channel 10 of the layer system 1 to be produced without coatings or without outer wall on the surface 22 an opening 24.
- the angle ⁇ between the surface 22 and the inner surface of the cooling passage 10 at the opening 24 has a value different from 90 °. This means that the cooling channel 10 relative to the surface 22 undercuts 26 has.
- thermal stresses between the coatings 7, 9 or the wall and the substrate 4 are reduced at a high thermal gradient between the outer hot coating 7, 9 or the wall and the cooling channel 10.
- Such a cooling channel 10 with undercuts 26 may also be arranged in the coating 7 (FIG. 6).
- a cooling channel 10 with undercuts 26 in the substrate 4 is made, for example, with a milling cutter or grinding head 25, which is formed at one end spherical, hemispherical or conical.
- a hole is made in the substrate 4 by being moved in a drilling direction 29 nearly perpendicular to the surface 22 of the substrate 4.
- a back and forth movement of the cutter 25 in a direction 32 perpendicular to the drilling direction 29, as indicated by the arrow whereby the undercuts 26 are generated in the substrate 4.
- the different positions of the cutter 25 in the reciprocating motion are indicated by dashed lines.
Abstract
Description
Die Erfindung betrifft ein kühlbares Schichtsystem gemäß Oberbegriff des Anspruchs 1.The invention relates to a coolable layer system according to the preamble of
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.From US-PS 5,080,557 a layer system is known in which a porous structure is arranged below a wall through which a cooling medium flows. This layer structure is relatively thick and difficult 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.US Pat. No. 5,820,337, US Pat. No. 5,640,767 and US Pat. No. 5,392,515 show turbine blades formed from a substrate in which cooling channels are arranged below an outer wall which has the same material as the substrate. The cooling of the outermost coating on the outer wall is often insufficient.
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.
Die US 2002/0141872 A1 offenbart ein kühlbares Schichtsystem gemäss dem Oberbegriff des Anspruchs 1.US 2002/0141872 A1 discloses a coolable layer system according to the preamble of
Es ist daher Aufgabe der Erfindung, die Kühlung eines Schichtsystems zu verbessern.It is therefore an object of the invention to improve the cooling of a layer system.
Die Aufgabe wird gelöst durch ein kühlbares Schichtsystem gemäss Anspruch 1.The object is achieved by a coolable layer system according to
In den Unteransprüchen sind weitere vorteilhafte Maßnahmen zur Verbesserung des gekühlten Schichtsystems aufgelistet.In the subclaims, further advantageous measures for improving the cooled layer system are listed.
Die in den Unteransprüchen aufgelisteten Maßnahmen können in vorteilhafter Weise miteinander kombiniert werden.The measures listed in the subclaims can be combined with each other in an advantageous manner.
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
- a further embodiment of a coolable layer system, and
- FIGS. 3, 4, 6
- Further modifications of the coolable layer system, and
- FIG. 5
- a specially designed cooling channel.
Figur 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, B-rennkammerauskleidung,..). 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 Seltenes Erdelement).
Darüber hinaus kann auf der Beschichtung 7 noch eine keramische Beschichtung, beispielsweise eine Wärmedämmschicht 9 (Fig. 6), aufgebracht sein.FIG. 1 shows a
The
In addition, a ceramic coating, for example a thermal barrier coating 9 (FIG. 6), may be applied to the
Ausgehend von der Oberfläche 22 des Substrats 4 ist hier ) zumindest ein Kühlkanal 10 bspw. 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, most of the peripheral 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 supply of a cooling medium takes place via a
The
Die Figur 2 zeigt ein weiteres Ausführungsbeispiel eines kühlbaren Schichtsystems 1.
Hier sind die Kühlkanäle 10 nicht durch Kanäle innerhalb der Beschichtung 7, sondern bspw. 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.FIG. 2 shows a further exemplary embodiment of a
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
Figur 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.FIG. 6 shows
The
Die Kühlkanäle 10 gemäss Figuren 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),...).
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
On the
The
Subsequently, the webs are removed with the filler. The material for the webs consists for example of graphite, which can be burned out or leached after coating with the
Other materials for the filler are possible.
Für die Herstellung der Kühlkanäle 10 gemäss Figur 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
Figur 3 zeigt die Anordnung von Kühlkanälen 10 gemäss Figuren 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.FIG. 3 shows the arrangement of
The
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 cooling
It can also extend all the cooling channels (10) in one direction. Groups of cooling channels can also run parallel to each other.
Figur 4 zeigt eine weitere Anordnungsmöglichkeit von Kühlkanälen 10 gemäss Figuren 1, 2 und 6 auf einer Oberfläche 22 oder einer Beschichtung 7 eines Bauteils 1.FIG. 4 shows another possible arrangement of cooling
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 zumindest teilweise, insbesondere die gesamte zu kühlende Oberfläche des Bauteils 1 erfasst wird, d.h. das Kreuzmuster und die Kreuzungen der Kühlkanäle erstreckt sich zumindest teilweise oder ganz über oder unterhalb der zu kühlenden Oberfläche.
In Figur 4 sind bspw. acht Kreuzungen von Kühlkanälen 10 vorhanden.
Die zu kühlende Oberfläche kann ein Teilbereich oder die gesamte Oberfläche eines Schaufelblatts einer Turbinenschaufel (Bauteil 1) sein.
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 cooling
In FIG. 4, for example, eight intersections of cooling
The surface to be cooled may be a partial area or the entire surface of a blade of a turbine blade (component 1).
If a cooling
The cooling medium K flows into 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 10 sind denkbar.
Auch können sich kreuzende Kühlkanäle 10 und mäanderförmige Kühlkanäle 10 eine zu kühlende Oberfläche erfassen, indem sich mäanderförmige Kühlkanäle an sich kreuzende Kühlkanäle anschliessen.Other arrangements of intersecting
Also, intersecting cooling
Figur 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.
Ein solcher Kühlkanal 10 mit Hinterschneidungen 26 kann auch in der Beschichtung 7 angeordnet sein (FIG 6).FIG. 5 shows a specially designed
Since the cooling
The angle α between the
As a result, thermal stresses between the
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, with the
The different positions of the
Claims (7)
- Coolable layer system (1),
at least comprising
a substrate (4) and
at least one coating (7) on the substrate (4),
cooling passages (10) being used for cooling purposes, the cooling passages (10) at least partially adjoining the coating (7),
characterized in that
at least two cooling passages (10) cross one another, so that the surface which is to be cooled is covered by the cooling passages (10) which cross one another. - Coolable layer system according to claim 1, characterized in that
the coolable layer system (1) extends in a radial direction (16), and
in that at least one cooling passage (10) is at an angle of 0° to the radial orientation (16). - Coolable layer system according to claim 1 or 2,
characterized in that
the coolable layer system (1) extends in a radial direction (16), and
in that at least one cooling passage (10) is at an angle of 90° to the radial orientation (16). - 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
in that at least one cooling passage (10) is at an angle of greater than 0° to less than 90° to the radial orientation (16). - Coolable layer system according to claim 1, characterized in that
at least one cooling passage (10) is arranged at least partially within the coating (7). - Coolable layer system according to one or more of the preceding claims,
characterized in that
at least one cooling passage (10) is arranged between two coatings (7, 9). - Coolable layer system according to claim 1, characterized in that
at least one cooling passage (10) includes at least one undercut (26).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| EP04717097A EP1606494B1 (en) | 2003-03-26 | 2004-03-04 | Coolable layer system |
Applications Claiming Priority (4)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| EP03006962 | 2003-03-26 | ||
| EP03006962A EP1462613A1 (en) | 2003-03-26 | 2003-03-26 | Coolable coating |
| EP04717097A EP1606494B1 (en) | 2003-03-26 | 2004-03-04 | Coolable layer system |
| PCT/EP2004/002223 WO2004085799A1 (en) | 2003-03-26 | 2004-03-04 | Coolable layer system |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| EP1606494A1 EP1606494A1 (en) | 2005-12-21 |
| EP1606494B1 true EP1606494B1 (en) | 2007-05-02 |
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 Before (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| EP03006962A Withdrawn EP1462613A1 (en) | 2003-03-26 | 2003-03-26 | Coolable coating |
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) |
Families Citing this family (12)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2006069941A1 (en) | 2004-12-24 | 2006-07-06 | Alstom Technology Ltd | Component comprising an embedded channel, in particular a hot gas component of a turbomachine |
| US20110150666A1 (en) * | 2009-12-18 | 2011-06-23 | Brian Thomas Hazel | Turbine blade |
| EP2431572A1 (en) * | 2010-09-21 | 2012-03-21 | Siemens Aktiengesellschaft | Thermal barrier coating for a steam turbine component |
| US8387245B2 (en) | 2010-11-10 | 2013-03-05 | General Electric Company | Components with re-entrant shaped cooling channels and methods of manufacture |
| DE102012205055B4 (en) * | 2012-03-29 | 2020-08-06 | Detlef Haje | Gas turbine component for high temperature applications, and method for operating and producing such a gas turbine component |
| 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 |
| US10731483B2 (en) | 2015-12-08 | 2020-08-04 | General Electric Company | Thermal management article |
| GB201521862D0 (en) * | 2015-12-11 | 2016-01-27 | Rolls Royce Plc | Cooling arrangement |
| 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 |
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| US2641439A (en) * | 1947-10-01 | 1953-06-09 | Chrysler Corp | Cooled turbine or compressor blade |
| NL212036A (en) * | 1955-11-16 | |||
| 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 |
| US5820337A (en) * | 1995-01-03 | 1998-10-13 | General Electric Company | Double wall turbine parts |
| US5640767A (en) * | 1995-01-03 | 1997-06-24 | Gen Electric | Method for making a double-wall airfoil |
| US6214248B1 (en) * | 1998-11-12 | 2001-04-10 | General Electric Company | Method of forming hollow channels within a component |
| US6617003B1 (en) * | 2000-11-06 | 2003-09-09 | General Electric Company | Directly cooled thermal barrier coating system |
| US6627019B2 (en) * | 2000-12-18 | 2003-09-30 | David C. Jarmon | Process for making ceramic matrix composite parts with cooling channels |
| US6551061B2 (en) * | 2001-03-27 | 2003-04-22 | General Electric Company | Process for forming micro cooling channels inside a thermal barrier coating system without masking material |
-
2003
- 2003-03-26 EP EP03006962A patent/EP1462613A1/en not_active Withdrawn
-
2004
- 2004-03-04 WO PCT/EP2004/002223 patent/WO2004085799A1/en active IP Right Grant
- 2004-03-04 ES ES04717097T patent/ES2285440T3/en not_active Expired - Lifetime
- 2004-03-04 US US10/550,973 patent/US20060222492A1/en not_active Abandoned
- 2004-03-04 DE DE502004003687T patent/DE502004003687D1/en not_active Expired - Fee Related
- 2004-03-04 EP EP04717097A patent/EP1606494B1/en not_active Expired - Lifetime
Non-Patent Citations (1)
| Title |
|---|
| None * |
Also Published As
| Publication number | Publication date |
|---|---|
| US20060222492A1 (en) | 2006-10-05 |
| ES2285440T3 (en) | 2007-11-16 |
| EP1462613A1 (en) | 2004-09-29 |
| WO2004085799A1 (en) | 2004-10-07 |
| DE502004003687D1 (en) | 2007-06-14 |
| EP1606494A1 (en) | 2005-12-21 |
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