EP1207268A1 - Gas turbine blade and a process for manufacturing a gas turbine blade - Google Patents
Gas turbine blade and a process for manufacturing a gas turbine blade Download PDFInfo
- Publication number
- EP1207268A1 EP1207268A1 EP00125031A EP00125031A EP1207268A1 EP 1207268 A1 EP1207268 A1 EP 1207268A1 EP 00125031 A EP00125031 A EP 00125031A EP 00125031 A EP00125031 A EP 00125031A EP 1207268 A1 EP1207268 A1 EP 1207268A1
- Authority
- EP
- European Patent Office
- Prior art keywords
- platform
- gas turbine
- slot
- turbine blade
- leading edge
- 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.)
- Granted
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Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- 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
- F01D5/186—Film 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
- F01D5/14—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
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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
- F05D2240/80—Platforms for stationary or moving blades
- F05D2240/81—Cooled platforms
-
- 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
- F05D2260/00—Function
- F05D2260/20—Heat transfer, e.g. cooling
- F05D2260/202—Heat transfer, e.g. cooling by film cooling
Definitions
- the invention relates to a gas turbine blade with a Platform and a profile attached to the platform.
- the invention also relates to a method of manufacture a gas turbine blade.
- DE 26 28 807 A discloses a gas turbine blade such a gas turbine blade is exposed to extremely high temperatures and therefore has to be cooled.
- the gas turbine blade has a platform that delimits a flow channel serves in which the gas turbine blade is installed is.
- the platform is followed by a profile that can be found in the Flow channel protrudes and hot gas flows around it.
- the Platform is exposed to the hot gas.
- the platform will cooled by an impingement cooling system, which one at the bottom the baffle cooling plate arranged on the platform which via baffle cooling openings cooling air to the bottom the platform flows. Then passes over film cooling holes this cooling air from the top of the platform and forms there a cooling film.
- a gas turbine blade Task solved by specifying a gas turbine blade with one platform and one on top of a platform the platform adjoining profile, the platform a leading edge and a trailing edge for the gas turbine blade has hot gas flowing around and wherein the Platform extending parallel to the leading edge Has slot, open into the channels through the Platform through to an opposite of the platform top Guide the underside of the platform.
- the platform is particularly special on its leading edge exposed to high temperatures.
- the leading edge is that edge of the platform facing the inflowing hot gas.
- This area of the platform is difficult to cool, because the profile in front and a thickened, because rounded Transition area between profile and platform one geometry difficult to cool.
- With the invention it is now possible in a production-technically simple manner, efficiently cool the leading edge of the platform. This happens in that cooling air from the underside of the platform through the Channels are directed into the slot where they are in the platform Efficiently cools leading edge area.
- the between that Slit and the leading edge wall is preferred 1-3 mm thick due to this comparatively thin design there is good coolability without a negative Influencing load-bearing areas.
- the slot is in one direction from the underside of the platform inclined towards the top of the platform towards the profile, that a cooling fluid emerging from the slot is a Film cooling of the platform top causes.
- the slot is thus over its height in one direction from the leading edge tilted to the trailing edge.
- the inclination is dimensioned so that escaping under normal operating conditions Cooling fluid, especially cooling air, forming a film on the Brushes along the top of the platform and thus film cooling causes. After cooling the leading edge of the platform due to the cooling fluid, this then also serves a film cooling of the platform top.
- the channels are preferably directed in such a way that they Open the slot in one direction towards the leading edge.
- the gas turbine blade is preferred as a moving blade executed.
- the object is directed to a method solved by specifying a method for producing a Gas turbine blade with one platform and one on a platform top of the platform connecting profile, the platform having a leading edge and a trailing edge for a hot gas flowing around the gas turbine blade, being in the platform parallel to the leading edge extending slot is introduced and wherein channels are introduced into the platform, which can be found in the Slot and the through the platform into one platform underside opposite the platform top to lead.
- the slot is preferably eroded into the platform.
- the channels in the platform are further preferred by means of Laser drilling introduced.
- the leading edge of the adjacent wall of the slot in front of the Completing the laser drilling is a light scattering protection applied so that this wall of the slot is not through the Laser radiation is damaged.
- Figure 1 shows a gas turbine blade 1, the blade is trained.
- a platform 3 is included Profile 5.
- the platform 3 has a platform top 7 that surrounds the profile 5.
- Opposite the platform top 7 is a platform underside 8.
- the platform 3 has a leading edge 9 and a trailing edge 11.
- On the platform underside 8 closes a blade root 13 with which the gas turbine blade 1 with a not closer rotor of a gas turbine shown can be used.
- a slot 15 in the platform 3 anode Between the leading edge 9 and the profile 5 is parallel to Leading edge 9 into platform 3 to platform top 7 opened a slot 15 in the platform 3 anode.
- This slot 15 opens channels 17 through the platform 3rd lead from the underside of the platform 8 to the slot 15.
- the Slot 15 is in one direction from the leading edge 9 to Trailing edge 11 inclined in height.
- the channels 17 lead approximately perpendicular to the wall 21 of the slot 15, which is adjacent to the leading edge 9.
- Cooling fluid 25 In particular cooling air, from an area below the platform 3 through the channels 17 and in the Slot 15 into it. Due to the orientation of the channels 17, of which also provided more than the two channels 17 shown may be, the cooling fluid 25 is perpendicular to the wall 21 of the slot 15 and thus cools this wall 21 and thus the leading edge 9 efficiently with impingement cooling. After a calming of the flow in the slot 15, this then occurs Cooling fluid 25 through the inclination of the slot 15 so from the Slot 15 from that it forms a cooling film over the Platform top 7 flows out.
- FIG. 2 A method of manufacturing such a gas turbine blade 1 is shown in more detail in Figure 2, which in one Longitudinal section shows the leading edge area of the platform 3.
- the one formed between the slot 15 and the leading edge 9 Wall 21 has a maximum thickness D of 1-3 mm.
- the in Slit 15 lying surface 31 of the wall 21 is with a Teflon strips 33 provide light-scattering protection represents.
- This light-scattering protection 33 is used for protection before a laser radiation 37 from a laser 35 with which the Bores 17 are made by laser drilling. At the Passage of the laser radiation 37 through the finished one Channel 17 will not damage wall 21 because of the Teflon strip 33 this radiation 37 scatters.
- the opening of the Slot 15 in the direction of the profile 5 with a slope 41 beveled.
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
- Laser Beam Processing (AREA)
Abstract
Description
Die Erfindung betrifft eine Gasturbinenschaufel mit einer Plattform und einem sich an die Plattform anschließenden Profil. Die Erfindung betrifft auch ein Verfahren zur Herstellung einer Gasturbinenschaufel.The invention relates to a gas turbine blade with a Platform and a profile attached to the platform. The invention also relates to a method of manufacture a gas turbine blade.
Eine Gasturbinenschaufel offenbart die DE 26 28 807 A. Eine solche Gasturbinenschaufel ist extrem hohen Temperaturen ausgesetzt und muss daher gekühlt werden. Die Gasturbinenschaufel weist eine Plattform auf, die der Begrenzung eines Strömungskanals dient, in die die Gasturbinenschaufel eingebaut ist. An die Plattform schließt sich ein Profil an, das in den Strömungskanal ragt und vom Heißgas umströmt wird. Auch die Plattform wird dem Heißgas ausgesetzt. Die Plattform wird durch ein Prallkühlsystem gekühlt, welches ein an der Unterseite der Plattform angeordnetes Prallkühlblech umfasst, aus welchem über Prallkühlöffnungen Kühlluft auf die Unterseite der Plattform strömt. Über Filmkühlbohrungen tritt sodann diese Kühlluft an der Oberseite der Plattform aus und bildet dort einen Kühlfilm.DE 26 28 807 A discloses a gas turbine blade such a gas turbine blade is exposed to extremely high temperatures and therefore has to be cooled. The gas turbine blade has a platform that delimits a flow channel serves in which the gas turbine blade is installed is. The platform is followed by a profile that can be found in the Flow channel protrudes and hot gas flows around it. Also the Platform is exposed to the hot gas. The platform will cooled by an impingement cooling system, which one at the bottom the baffle cooling plate arranged on the platform which via baffle cooling openings cooling air to the bottom the platform flows. Then passes over film cooling holes this cooling air from the top of the platform and forms there a cooling film.
Aufgabe der Erfindung ist die Angabe einer Gasturbinenschaufel, bei die Plattform besonders hohen Temperaturen widersteht, bei einem vergleichsweise geringen Kühlluftbedarf. Weitere Aufgabe der Erfindung ist die Angabe eines Verfahrens zur Herstellung einer solchen Gasturbinenschaufel.The object of the invention is to provide a gas turbine blade, the platform withstands particularly high temperatures, with a comparatively low cooling air requirement. Another object of the invention is to provide a method for the production of such a gas turbine blade.
Erfindungsgemäß wird die auf eine Gasturbinenschaufel gerichtete Aufgabe gelöst durch Angabe einer Gasturbinenschaufel mit einer Plattform und einem sich an eine Plattformoberseite der Plattform anschliessenden Profil, wobei die Plattform eine Anströmkante und eine Abströmkante für ein die Gasturbinenschaufel umströmendes Heißgas aufweist und wobei die Plattform einen sich parallel zur Eintrittskante erstreckenden Schlitz aufweist, in den Kanäle münden, die durch die Plattform hindurch zu einer der Plattformoberseite gegenüberliegenden Plattformunterseite führen.According to the invention, it is directed towards a gas turbine blade Task solved by specifying a gas turbine blade with one platform and one on top of a platform the platform adjoining profile, the platform a leading edge and a trailing edge for the gas turbine blade has hot gas flowing around and wherein the Platform extending parallel to the leading edge Has slot, open into the channels through the Platform through to an opposite of the platform top Guide the underside of the platform.
Die Plattform ist insbesondere an ihrer Anströmkante besonders hohen Temperaturen ausgesetzt. Die Anströmkante ist die dem anströmenden Heißgas entgegengerichtete Kante der Plattform. Dieser Bereich der Plattform ist nur schwer zu kühlen, da das davorliegende Profil und ein aufgedickter, da abgerundeter Übergangsbereich zwischen Profil und Plattform eine schwer kühlbare Geometrie ergeben. Mit der Erfindung ist es nunmehr in einer fertigungstechnisch einfachen Weise möglich, die Plattformanströmkante effizient zu kühlen. Dies geschieht dadurch, dass Kühlluft von der Plattformunterseite durch die Kanäle in den Schlitz geleitet wird, wo sie die Plattform im Eintrittskantenbereich effizient kühlt. Die zwischen dem Schlitz und der Eintrittskante gebildete Wand ist dabei vorzugsweise 1-3 mm dick Durch diese vergleichsweise dünne Ausführung ergibt sich eine gute Kühlbarkeit, ohne eine negative Beeinflussung tragender Bereiche.The platform is particularly special on its leading edge exposed to high temperatures. The leading edge is that edge of the platform facing the inflowing hot gas. This area of the platform is difficult to cool, because the profile in front and a thickened, because rounded Transition area between profile and platform one geometry difficult to cool. With the invention it is now possible in a production-technically simple manner, efficiently cool the leading edge of the platform. this happens in that cooling air from the underside of the platform through the Channels are directed into the slot where they are in the platform Efficiently cools leading edge area. The between that Slit and the leading edge wall is preferred 1-3 mm thick due to this comparatively thin design there is good coolability without a negative Influencing load-bearing areas.
Vorzugsweise ist der Schlitz in einer Richtung von der Plattformunterseite zur Plattformoberseite zum Profil hin so geneigt, dass ein aus dem Schlitz austretendes Kühlfluid eine Filmkühlung der Plattformoberseite bewirkt. Der Schlitz ist also über seine Höhe in einer Richtung von der Anströmkante zur Abströmkante gekippt. Die Neigung ist dabei so dimensioniert, dass unter üblichen Betriebsbedingungen austretendes Kühlfluid, insbesondere Kühlluft, einen Film bildend auf der Plattformoberseite entlangstreicht und somit eine Filmkühlung bewirkt. Nach der Kühlung der Anströmkante der Plattform durch das Kühlfluid dient dieses somit anschließend auch noch einer Filmkühlung der Plattformoberseite.Preferably the slot is in one direction from the underside of the platform inclined towards the top of the platform towards the profile, that a cooling fluid emerging from the slot is a Film cooling of the platform top causes. The slot is thus over its height in one direction from the leading edge tilted to the trailing edge. The inclination is dimensioned so that escaping under normal operating conditions Cooling fluid, especially cooling air, forming a film on the Brushes along the top of the platform and thus film cooling causes. After cooling the leading edge of the platform due to the cooling fluid, this then also serves a film cooling of the platform top.
Bevorzugt sind die Kanäle so gerichtet, dass sie in den Schlitz in einer Richtung auf die Eintrittskante hin münden. The channels are preferably directed in such a way that they Open the slot in one direction towards the leading edge.
Hierdurch wird das aus den Kanälen austretende Kühlfluid gegen die Wand des Schlitzes prallkühlend geführt, die der Anströmkante benachbart ist. Diese Prallkühlung bewirkt eine besonders effiziente Kühlung der Plattformanströmkante.This counteracts the cooling fluid emerging from the channels the wall of the slot is impingement cooling, that of the leading edge is adjacent. This impingement cooling causes one particularly efficient cooling of the leading edge of the platform.
Bevorzugt ist die Gasturbinenschaufel als eine Laufschaufel ausgeführt.The gas turbine blade is preferred as a moving blade executed.
Erfindungsgemäß wird die auf ein Verfahren gerichtete Aufgabe gelöst durch Angabe eines Verfahrens zur Herstellung einer Gasturbinenschaufel mit einer Plattform und einem sich an eine Plattformoberseite der Plattform anschließenden Profil, wobei die Plattform eine Anströmkante und eine Abströmkante für ein die Gasturbinenschaufel umströmendes Heißgas aufweist, wobei in die Plattform ein sich parallel zur Eintrittskante erstreckender Schlitz eingebracht wird und wobei in die Plattform Kanäle eingebracht werden, die in den Schlitz münden und die durch die Plattform hindurch zu einer der Plattformoberseite gegenüberliegenden Plattformunterseite führen.According to the invention, the object is directed to a method solved by specifying a method for producing a Gas turbine blade with one platform and one on a platform top of the platform connecting profile, the platform having a leading edge and a trailing edge for a hot gas flowing around the gas turbine blade, being in the platform parallel to the leading edge extending slot is introduced and wherein channels are introduced into the platform, which can be found in the Slot and the through the platform into one platform underside opposite the platform top to lead.
Die Vorteile eines solchen Verfahrens ergegen sich entsprechend den Ausführungen zu den Vorteilen der Gasturbinenschaufel.The advantages of such a method come together accordingly the explanations of the advantages of the gas turbine blade.
Vorzugsweise wird der Schlitz in die Plattform erodiert.The slot is preferably eroded into the platform.
Weiter bevorzugt werden die Kanäle in die Plattform mittels Laserbohren eingebracht. Bevorzugtermaßen wird dabei auf die der Eintrittskante benachbarte Wand des Schlitzes vor dem Fertigstellen des Laserbohrens ein lichtstreuender Schutz aufgebracht, so dass diese Wand des Schlitzes nicht durch die Laserstrahlung beschädigt wird. Weiter bevorzugt ist dieser lichtstreuende Schutz ein Teflonstreifen. Bei der besonders materialschonenden und effizienten Fertigung der Kanäle durch Laserbohren besteht zunächst die Gefahr, dass beim Durchbohren der Kanäle letztlich die der Eintrittskante benachbarte Wand des Schlitzes durch die am Ende des Fertigungsprozesses aus den Kanälen austretende Laserstrahlung beschädigt wird. Dies wird durch den lichtstreuenden Schutz verhindert, wobei insbesondere das Aufbringen des Teflonstreifens eine einfache und schnelle Methode darstellt.The channels in the platform are further preferred by means of Laser drilling introduced. Preferred is the the leading edge of the adjacent wall of the slot in front of the Completing the laser drilling is a light scattering protection applied so that this wall of the slot is not through the Laser radiation is damaged. This is more preferred light scattering protection a teflon strip. With the particularly material-saving and efficient production of the channels Laser drilling initially involves the risk that when drilling through of the channels ultimately that adjacent to the leading edge Wall of the slot through at the end of the manufacturing process laser radiation emerging from the channels is damaged. This is prevented by the light-scattering protection, whereby in particular the application of the Teflon strip is easy and represents quick method.
Die Erfindung wird in einem Ausführungsbeispiel anhand der Zeichnung näher erläutert. Es zeigen:
- FIG 1
- eine Gasturbinenschaufel und
- FIG 2
- einen Längsschnitt durch den Anströmkantenbereich
der Plattform der Gasturbinenschaufel aus
Figur 1.
- FIG. 1
- a gas turbine blade and
- FIG 2
- 2 shows a longitudinal section through the leading edge region of the platform of the gas turbine blade from FIG. 1.
Gleiche Bezugszeichen haben in den Figuren die gleiche Bedeutung.The same reference numerals have the same meaning in the figures.
Figur 1 zeigt eine Gasturbinenschaufel 1, die als Laufschaufel
ausgebildet ist. An eine Plattform 3 schließt sich ein
Profil 5 an. Die Plattform 3 weist eine Plattformoberseite 7
auf, die das Profil 5 umgibt. Der Plattformoberseite 7 gegenüberliegend
ist eine Plattformunterseite 8. Die Plattform 3
weist eine Anströmkante 9 und eine Abströmkante 11 auf. An
die Plattformunterseite 8 schließt sich ein Schaufelfuß 13
an, mit dem die Gasturbinenschaufel 1 mit einem nicht näher
dargestellten Rotor einer Gasturbine verwendbar ist.Figure 1 shows a
Zwischen der Anströmkante 9 und dem Profil 5 ist parallel zur
Anströmkante 9 in die Plattform 3 zur Plattformoberseite 7
geöffnet ein Schlitz 15 in die Plattform 3 einerodiert. In
diesen Schlitz 15 münden Kanäle 17, die durch die Plattform 3
von der Plattformunterseite 8 bis zum Schlitz 15 führen. Der
Schlitz 15 ist in einer Richtung von der Anströmkante 9 zur
Abströmkante 11 in seiner Höhe geneigt. Die Kanäle 17 führen
etwa senkrecht in Richtung auf die Wand 21 des Schlitzes 15,
die der Anströmkante 9 benachbart ist. Between the leading
Beim Einsatz der Gasturbinenschaufel 1 umströmt ein Heißgas
23 die Gasturbinenschaufel 1, wodurch unter anderem auch die
Plattform 3 und dort besonders die Anströmkante 9 thermisch
hoch belastet wird. Eine besonders effektive Kühlung der Anströmkante
9 ergibt sich durch die Führung von einem
Kühlfluid 25, insbesondere Kühlluft, aus einem Bereich unterhalb
der Plattform 3 durch die Kanäle 17 hindurch und in den
Schlitz 15 hinein. Durch die Orientierung der Kanäle 17, von
denen auch mehr als die gezeigten zwei Kanäle 17 vorgesehen
sein können, wird das Kühlfluid 25 senkrecht auf die Wand 21
des Schlitzes 15 geleitet und kühlt somit diese Wand 21 und
damit die Anströmkante 9 effizient mit einer Prallkühlung.
Nach einer Strömungsberuhigung im Schlitz 15 tritt sodann das
Kühlfluid 25 durch die Neigung des Schlitzes 15 so aus dem
Schlitz 15 aus, dass es einen Kühlfilm bildend über die
Plattformoberseite 7 abströmt.When using the
Ein Verfahren zur Herstellung einer solchen Gasturbinenschaufel
1 ist näher in Figur 2 dargestellt, welche in einem
Längsschnitt den Anströmkantenbereich der Plattform 3 zeigt.
Die zwischen dem Schlitz 15 und der Anströmkante 9 gebildete
Wand 21 weist eine maximale Dicke D von 1 - 3 mm auf. Die im
Schlitz 15 liegende Oberfläche 31 der Wand 21 ist mit einem
Teflonstreifen 33 versehen, der einen lichtstreuenden Schutz
darstellt. Dieser lichtstreuende Schutz 33 dient zum Schutz
vor einer Laserstrahlung 37 aus einem Laser 35, mit dem die
Bohrungen 17 mittels Laserbohren hergestellt werden. Beim
Durchtritt der Laserstrahlung 37 durch den fertig gebohrten
Kanal 17 wird die Wand 21 nicht beschädigt, da der Teflonstreifen
33 diese Strahlung 37 streut.A method of manufacturing such a
Zur Verbesserung einer Filmkühlung ist die Öffnung des
Schlitzes 15 in Richtung auf das Profil 5 mit einer Schräge
41 abgeschrägt.To improve film cooling, the opening of the
Claims (9)
bei der zwischen dem Schlitz (15) und der Eintrittskante (9) eine Wand gebildet ist, die 0,53 mm dick ist.Gas turbine blade (1) according to claim 1,
in which a wall is formed between the slot (15) and the leading edge (9), which is 0.53 mm thick.
bei der der Schlitz (15) in einer Richtung von der Plattformunterseite (8) zur Plattformoberseite (7) zum Profil (5) hin so geneigt ist, daß ein aus dem Schlitz (15) austretendes Kühlfluid (25) eine Filmkühlung der Plattformoberseite (7) bewirkt.Gas turbine blade (1) according to claim 1,
in which the slot (15) is inclined in a direction from the platform underside (8) to the platform top (7) towards the profile (5) such that a cooling fluid (25) emerging from the slot (15) causes film cooling of the platform top (7 ) causes.
bei der die Kanäle (17) in den Schlitz (15) in einer Richtung auf die Eintrittskante (9) hin münden.Gas turbine blade (1) according to claim 1,
in which the channels (17) open into the slot (15) in one direction towards the leading edge (9).
ausgeführt als Laufschaufel.Gas turbine blade (1) according to claim 1
designed as a moving blade.
bei dem der Schlitz (15) in die Plattform (3) erodiert wird.Method according to claim 6,
in which the slot (15) is eroded into the platform (3).
bei dem die Kanäle (17) in die Plattform (3) mittels Laserbohren eingebracht werden.Method according to claim 6,
in which the channels (17) are introduced into the platform (3) by means of laser drilling.
bei dem auf die der Eintrittskante (9) benachbarte Wand (21) des Schlitzes (15) vor dem Fertigstellen des Laserbohrens ein lichtstreuender Schutz (33) aufgebracht wird, so dass diese Wand (21) des Schlitzes (15) nicht durch die Laserstrahlung (37) beschädigt wird.A method according to claim 8,
in which a light-scattering protection (33) is applied to the wall (21) of the slot (15) adjacent to the leading edge (9) before the laser drilling is completed, so that this wall (21) of the slot (15) is not affected by the laser radiation ( 37) is damaged.
Priority Applications (5)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| EP00125031A EP1207268B1 (en) | 2000-11-16 | 2000-11-16 | Gas turbine blade and a process for manufacturing a gas turbine blade |
| DE50009497T DE50009497D1 (en) | 2000-11-16 | 2000-11-16 | Film cooling of gas turbine blades by means of slots for cooling air |
| CA002361978A CA2361978A1 (en) | 2000-11-16 | 2001-11-14 | Gas turbine blade and method for manufacturing a gas turbine blade |
| JP2001350479A JP4040864B2 (en) | 2000-11-16 | 2001-11-15 | Gas turbine blade and manufacturing method thereof |
| US10/004,478 US6719529B2 (en) | 2000-11-16 | 2001-11-16 | Gas turbine blade and method for producing a gas turbine blade |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| EP00125031A EP1207268B1 (en) | 2000-11-16 | 2000-11-16 | Gas turbine blade and a process for manufacturing a gas turbine blade |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| EP1207268A1 true EP1207268A1 (en) | 2002-05-22 |
| EP1207268B1 EP1207268B1 (en) | 2005-02-09 |
Family
ID=8170398
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| EP00125031A Expired - Lifetime EP1207268B1 (en) | 2000-11-16 | 2000-11-16 | Gas turbine blade and a process for manufacturing a gas turbine blade |
Country Status (5)
| Country | Link |
|---|---|
| US (1) | US6719529B2 (en) |
| EP (1) | EP1207268B1 (en) |
| JP (1) | JP4040864B2 (en) |
| CA (1) | CA2361978A1 (en) |
| DE (1) | DE50009497D1 (en) |
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| EP1788192A3 (en) * | 2005-11-21 | 2008-11-12 | General Electric Company | Gas turbine bucket with cooled platform edge and method of cooling platform leading edge |
| EP3232001A1 (en) | 2016-04-15 | 2017-10-18 | Siemens Aktiengesellschaft | Rotor blade for a turbine |
| CN111734497A (en) * | 2020-07-27 | 2020-10-02 | 北京全四维动力科技有限公司 | Turbine rotor blade and gas turbine comprising same |
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|---|---|---|---|---|
| US6634858B2 (en) * | 2001-06-11 | 2003-10-21 | Alstom (Switzerland) Ltd | Gas turbine airfoil |
| US7144215B2 (en) * | 2004-07-30 | 2006-12-05 | General Electric Company | Method and apparatus for cooling gas turbine engine rotor blades |
| US7198467B2 (en) * | 2004-07-30 | 2007-04-03 | General Electric Company | Method and apparatus for cooling gas turbine engine rotor blades |
| US7131817B2 (en) * | 2004-07-30 | 2006-11-07 | General Electric Company | Method and apparatus for cooling gas turbine engine rotor blades |
| US7217096B2 (en) * | 2004-12-13 | 2007-05-15 | General Electric Company | Fillet energized turbine stage |
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2001
- 2001-11-14 CA CA002361978A patent/CA2361978A1/en not_active Abandoned
- 2001-11-15 JP JP2001350479A patent/JP4040864B2/en not_active Expired - Fee Related
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| EP1788192A3 (en) * | 2005-11-21 | 2008-11-12 | General Electric Company | Gas turbine bucket with cooled platform edge and method of cooling platform leading edge |
| EP3232001A1 (en) | 2016-04-15 | 2017-10-18 | Siemens Aktiengesellschaft | Rotor blade for a turbine |
| CN111734497A (en) * | 2020-07-27 | 2020-10-02 | 北京全四维动力科技有限公司 | Turbine rotor blade and gas turbine comprising same |
Also Published As
| Publication number | Publication date |
|---|---|
| DE50009497D1 (en) | 2005-03-17 |
| CA2361978A1 (en) | 2002-05-16 |
| JP2002213203A (en) | 2002-07-31 |
| US20020110454A1 (en) | 2002-08-15 |
| JP4040864B2 (en) | 2008-01-30 |
| US6719529B2 (en) | 2004-04-13 |
| EP1207268B1 (en) | 2005-02-09 |
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