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WO2003085235A1 - Turbine blade - Google Patents

Turbine blade Download PDF

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Publication number
WO2003085235A1
WO2003085235A1 PCT/DE2003/000909 DE0300909W WO03085235A1 WO 2003085235 A1 WO2003085235 A1 WO 2003085235A1 DE 0300909 W DE0300909 W DE 0300909W WO 03085235 A1 WO03085235 A1 WO 03085235A1
Authority
WO
WIPO (PCT)
Prior art keywords
turbine blade
cooling
insert
blade
leg
Prior art date
Application number
PCT/DE2003/000909
Other languages
German (de)
French (fr)
Inventor
Peter Tiemann
Original Assignee
Siemens Aktiengesellschaft
Priority date (The priority date 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 date listed.)
Filing date
Publication date
Application filed by Siemens Aktiengesellschaft filed Critical Siemens Aktiengesellschaft
Publication of WO2003085235A1 publication Critical patent/WO2003085235A1/en

Links

Classifications

    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
    • B23P—METAL-WORKING NOT OTHERWISE PROVIDED FOR; COMBINED OPERATIONS; UNIVERSAL MACHINE TOOLS
    • B23P15/00—Making specific metal objects by operations not covered by a single other subclass or a group in this subclass
    • B23P15/04—Making specific metal objects by operations not covered by a single other subclass or a group in this subclass turbine or like blades from several pieces
    • 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
    • F01D5/188—Convection cooling with an insert in the blade cavity to guide the cooling fluid, e.g. forming a separation wall
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2230/00—Manufacture
    • F05D2230/20—Manufacture essentially without removing material
    • F05D2230/21—Manufacture essentially without removing material by casting
    • 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
    • F05D2250/00—Geometry
    • F05D2250/70—Shape
    • 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
    • F05D2250/00—Geometry
    • F05D2250/70—Shape
    • F05D2250/71—Shape curved
    • 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
    • F05D2250/00—Geometry
    • F05D2250/70—Shape
    • F05D2250/71—Shape curved
    • F05D2250/712—Shape curved concave

Definitions

  • the invention relates to a turbine blade according to the preamble of claim 1.
  • Turbine blades often have cooling channels in a meandering shape on the inside.
  • meandering forms are not easy to produce in the casting process for producing the turbine blade, so that the meandering form often has openings in order to be able to remove a core of the casting form, which forms the cooling channel, after the casting, the opening then being closed again in order to to achieve the desired meander shape.
  • the object of the invention is therefore to show cooling channels of a turbine blade with which a meandering shape can be produced in a simplified manner.
  • the turbine blade has a simple shape on the inside and the meandering shape can be produced by a simple component that can be easily retrofitted.
  • Figure 2 known cooling channels in a meandering shape within a turbine blade, and 3, 4, 5 turbine blades according to the invention.
  • FIG. 1 shows a perspective view of a turbine blade, in particular a moving blade 1, which extends in the radial direction along a radial longitudinal axis 4.
  • the rotor blade 1 has, in succession along the longitudinal axis 4, a fastening area 7, an adjoining blade platform 10 and an airfoil area 16.
  • a blade root 13 is formed, which serves to fasten the moving blade 1 to a shaft (not shown) of a turbomachine, not shown.
  • the blade root 13 is designed, for example, as a hammer head. Other configurations, for example as a fir tree or dovetail foot, are possible. Metallic materials are used for the blade 1 in all areas 7, 10 and 16.
  • the rotor blade 1 can be manufactured by a casting process, a forging process, a milling process or a combination thereof.
  • FIG. 2 shows an example of a meandering shape 28 of cooling channels 19 within the turbine blade according to the prior art, the cooling channels 19 being arranged mainly in the blade area 16, for example.
  • the blade 1 has a leading edge 31, at which an outer medium flows past.
  • the cooling channels 19 are formed by at least two cooling channel walls 22, which can also be outer walls of the turbine blade.
  • a cooling medium in the interior of the turbine blade must be deflected in deflection areas 25. This takes place, for example, in the area of the blade root 13 as well as at the radial end of the airfoil region 16.
  • Blade base 13 prepares the above when casting
  • FIG. 3 shows a section of FIG. 2, but of a rotor blade 1 designed according to the invention.
  • the cooling channels 19 are formed by cooling channel walls 22 which, for example, extend at least partially in parallel along the longitudinal axis 4 and, for example, end at the same height in the radial direction and also have outer walls Turbine blade 1 can be.
  • the cooling medium should flow from the cooling walls 22 shown in FIG. 3 around the central cooling wall 22, as is indicated by the arrow 59.
  • the insert 34 is V-shaped 37 at one radial end and bears with its first V-leg 40 against the cooling duct wall 22 on the left in the drawing and with its second V-leg 43 against the right, ie in the axial direction 58, which runs perpendicular to the longitudinal axis 4, next to the cooling channel wall 22.
  • the inner surface 46 of the insert 34 which now forms the cooling duct 19 with the cooling duct walls 22, is formed in the deflection region 25, for example, in a concave manner, in particular in terms of flow technology.
  • the insert 34 extends along the longitudinal axis 4 and is fastened in the area of the blade root 13, which is easily accessible.
  • the cooling medium flows in the radial direction 4, for example, from the airfoil area 16 to the deflection area 25, is deflected there by more than 90 °, here, for example, by 180 °, and flows back in the opposite radial direction 4, for example, into the airfoil area 16.
  • FIG. 4 shows a section of FIG. 3.
  • the insert can, but does not have to, be firmly connected to the cooling channel walls 22 in the region of its V-legs 40, 43. There are various options for how the insert 34 bears against the cooling duct wall 22. In FIG.
  • the cooling duct wall 22 has, at a radial end 49, an incision 55 against which a radial end 52 of the first V-leg 40 comes into positive contact, ie the insert 34 is supported on the cooling duct wall 22 in this area, so that there is no swirling of the flowing cooling medium.
  • FIG. 5 A further exemplary embodiment for the application of the insert 34 to the cooling duct wall 22 is shown in FIG. 5.
  • the cooling duct wall 22 has a round shape at its radial end 49, which is enclosed by a complementary radial end 52 of the V-leg 40 of the insert 34, so that the insert 34 is also supported on the cooling duct wall 22 here.
  • the turbine blade can be a rotor or guide blade of any turbine, in particular a steam or gas turbine.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)

Abstract

Meandering cooling channels inside a turbine blade are difficult to produce in one piece by using casting techniques. The inventive turbine blade (1) comprises cooling channel walls (22), which are easy to produce by using manufacturing techniques and which later form the cooling channels (19), whereby the meandering shape is attained by an additional V-shaped insert after completion of the production process of the turbine blade.

Description

Turbinenschaufelturbine blade
Die Erfindung bezieht sich auf eine Turbinenschaufel gemäss Gattungsbegriff des Anspruchs 1.The invention relates to a turbine blade according to the preamble of claim 1.
Turbinenschaufeln weisen im Innern oft Kühlkanäle in einer Mäanderform auf. Solche Mäanderformen sind jedoch im Gussverfahren zur Herstellung der Turbinenschaufel nicht einfach herzustellen, so dass die Mäanderform oft Öffnungen aufweist, um einen Kern der Gussform, der den Kühlkanal bildet, nach dem Giessen wieder entfernen zu können, wobei die Öffnung danach wieder verschlossen wird, um die gewünschte Mäanderform zu erreichen.Turbine blades often have cooling channels in a meandering shape on the inside. However, such meandering forms are not easy to produce in the casting process for producing the turbine blade, so that the meandering form often has openings in order to be able to remove a core of the casting form, which forms the cooling channel, after the casting, the opening then being closed again in order to to achieve the desired meander shape.
Aufgabe der Erfindung ist es daher, Kühlkanäle einer Turbinenschaufel aufzuzeigen, mit denen sich eine Mäanderform vereinfacht herstellen lässt.The object of the invention is therefore to show cooling channels of a turbine blade with which a meandering shape can be produced in a simplified manner.
Die Aufgabe wird dadurch den Anspruch 1 gelöst, indem die Turbinenschaufel im Innern eine einfache Form aufweist und die Mäanderform durch ein einfaches nachträglich leicht einzubauendes Bauteil herstellbar ist.The object is achieved by claim 1 in that the turbine blade has a simple shape on the inside and the meandering shape can be produced by a simple component that can be easily retrofitted.
In den Unteransprüchen sind weitere vorteilhafte Ausbildungen der Turbinenschaufel gemäss Anspruch 1 aufgelistet.Further advantageous embodiments of the turbine blade according to claim 1 are listed in the subclaims.
Ein Ausführungsbeispiel der Erfindung ist in den Zeichnungen vereinfacht dargestellt.An embodiment of the invention is shown in simplified form in the drawings.
Es zeigen Figur 1 eine Turbinenschaufel,1 shows a turbine blade,
Figur 2 bekannte Kühlkanäle in Mäanderform innerhalb einer Turbinenschaufel, und Figur 3, 4, 5 erfindungsgemässe Turbinenschaufeln.Figure 2 known cooling channels in a meandering shape within a turbine blade, and 3, 4, 5 turbine blades according to the invention.
Figur 1 zeigt in perspektivischer Ansicht eine Turbinenschaufel, insbesondere eine Laufschaufel 1, die sich entlang einer radialen Längsachse 4 in radialer Richtung erstreckt .FIG. 1 shows a perspective view of a turbine blade, in particular a moving blade 1, which extends in the radial direction along a radial longitudinal axis 4.
Die Laufschaufel 1 weist entlang der Längsachse 4 aufeinanderfolgend einen Befestigungsbereich 7, eine daran angrenzende Schaufelplattform 10 sowie einen Schaufelblattbereich 16 auf.The rotor blade 1 has, in succession along the longitudinal axis 4, a fastening area 7, an adjoining blade platform 10 and an airfoil area 16.
Im Befestigungsbereich 7 ist ein Schaufelfuss 13 gebildet, der zur Befestigung der Laufschaufel 1 an einer Welle (nicht dargestellt) einer nicht dargestellten Strömungsmaschine dient.In the fastening area 7, a blade root 13 is formed, which serves to fasten the moving blade 1 to a shaft (not shown) of a turbomachine, not shown.
Der Schaufelfuss 13 ist beispielsweise als Hammerkopf ausgestaltet. Andere Ausgestaltungen, beispielsweise als Tannenbaum- oder Schwalbenschwanzfuß sind möglich. Für die Laufschaufel 1 werden in allen Bereichen 7, 10 und 16 metallische Werkstoffe verwendet. Die Laufschaufei 1 kann hierbei durch ein Gussverfahren, durch ein Schmiedeverfahren, durch ein Fräsverfahren oder einer Kombination daraus gefertigt sein.The blade root 13 is designed, for example, as a hammer head. Other configurations, for example as a fir tree or dovetail foot, are possible. Metallic materials are used for the blade 1 in all areas 7, 10 and 16. The rotor blade 1 can be manufactured by a casting process, a forging process, a milling process or a combination thereof.
Figur 2 zeigt beispielhaft eine Mäanderform 28 von Kühlkanälen 19 innerhalb der Turbinenschaufel nach dem Stand der Technik, wobei die Kühlkanäle 19 bspw. hauptsächlich im Schaufelblattbereich 16 angeordnet sind. Die Laufschaufel 1 weist eine Anströmkante 31 auf, an der ein äusseres Medium vorbeiströmt. Die Kühlkanäle 19 werden durch zumindest zwei Kühlkanalwände 22 gebildet, die auch Aussenwände der Turbinenschaufel sein können.FIG. 2 shows an example of a meandering shape 28 of cooling channels 19 within the turbine blade according to the prior art, the cooling channels 19 being arranged mainly in the blade area 16, for example. The blade 1 has a leading edge 31, at which an outer medium flows past. The cooling channels 19 are formed by at least two cooling channel walls 22, which can also be outer walls of the turbine blade.
Um eine Mäanderform 28 zu erreichen, muss ein Kühlmedium im Inneren der Turbinenschaufel in Umlenkbereichen 25 umgelenkt werden. Dies findet bspw. im Bereich des Schaufelfusses 13 sowie an dem radialen Ende des Schaufelblattbereichs 16 statt .In order to achieve a meandering shape 28, a cooling medium in the interior of the turbine blade must be deflected in deflection areas 25. This takes place, for example, in the area of the blade root 13 as well as at the radial end of the airfoil region 16.
Insbesondere der Umlenkbereich 25 in der Nähe desIn particular, the deflection area 25 near the
Schaufelfusses 13 bereitet beim Giessen oben geschilderteBlade base 13 prepares the above when casting
Probleme .Problems.
Figur 3 zeigt einen Ausschnitt der Figur 2, aber einer erfindungsgemäss ausgebildeten Laufschaufei 1. Die Kühlkanäle 19 werden durch Kühlkanalwände 22 gebildet, die sich bspw. zumindest teilweise parallel entlang der Längsachse 4 erstrecken und beispielsweise in radialer Richtung auf gleicher Höhe enden und auch Aussenwände einer Turbinenschaufel 1 sein können.FIG. 3 shows a section of FIG. 2, but of a rotor blade 1 designed according to the invention. The cooling channels 19 are formed by cooling channel walls 22 which, for example, extend at least partially in parallel along the longitudinal axis 4 and, for example, end at the same height in the radial direction and also have outer walls Turbine blade 1 can be.
Das Kühlmedium soll von den in Figur 3 dargestellten Kühlwänden 22 um die mittlere Kühlwand 22 strömen, wie es durch den Pfeil 59 angedeutet ist. Dies wird ermöglicht durch einen Einsatz 34. Der Einsatz 34 ist an einem radialen Ende v-förmig 37 ausgebildet und liegt mit seinem ersten V-Schenkel 40 an der hier in der Zeichnung linken Kühlkanalwand 22 an und mit seinem zweiten V-Schenkel 43 an der rechten, d.h. in axialer Richtung 58, die senkrecht zur Längsachse 4 verläuft, übernächsten Kühlkanalwand 22 an.The cooling medium should flow from the cooling walls 22 shown in FIG. 3 around the central cooling wall 22, as is indicated by the arrow 59. This is made possible by an insert 34. The insert 34 is V-shaped 37 at one radial end and bears with its first V-leg 40 against the cooling duct wall 22 on the left in the drawing and with its second V-leg 43 against the right, ie in the axial direction 58, which runs perpendicular to the longitudinal axis 4, next to the cooling channel wall 22.
Die Innenfläche 46 des Einsatzes 34, die nun mit den Kühlkanalwänden 22 den Kühlkanal 19 bildet, ist im Umlenkbereich 25 beispielsweise konkav, insbesondere strömungstechnisch optimiert, ausgebildet. Der Einsatz 34 erstreckt sich entlang der Längsachse 4 und ist im Bereich des Schaufelfusses 13 befestigt, der leicht zugänglich ist.The inner surface 46 of the insert 34, which now forms the cooling duct 19 with the cooling duct walls 22, is formed in the deflection region 25, for example, in a concave manner, in particular in terms of flow technology. The insert 34 extends along the longitudinal axis 4 and is fastened in the area of the blade root 13, which is easily accessible.
Das Kühlmedium strömt in radialer Richtung 4 bspw. aus dem Schaufelblattbereich 16 bis zum Umlenkbereich 25, wird dort um mehr als 90° umgelenkt, hier bspw. um 180°, und strömt in entgegengesetzter radialer Richtung 4 bspw. in den Schaufelblattbereich 16 zurück. Figur 4 zeigt einen Ausschnitt der Figur 3. Der Einsatz kann, muss aber nicht, im Bereich seiner V- Schenkel 40, 43 mit den Kühlkanalwänden 22 fest verbunden sein. Dabei gibt es verschiedene Möglichkeiten, wie der Einsatz 34 an der Kühlkanalwand 22 anliegt. In der Figur 4 weist die Kühlkanalwand 22 an einem radialen Ende 49 einen Einschnitt 55 auf, an dem ein radiales Ende 52 des ersten V- Schenkels 40 formschlüssig zum Anliegen kommt, d.h. der Einsatz 34 stützt sich in diesem Bereich an der Kühlkanalwand 22 ab, so dass keine Verwirbelungen des strömenden Kühlmediums entstehen.The cooling medium flows in the radial direction 4, for example, from the airfoil area 16 to the deflection area 25, is deflected there by more than 90 °, here, for example, by 180 °, and flows back in the opposite radial direction 4, for example, into the airfoil area 16. FIG. 4 shows a section of FIG. 3. The insert can, but does not have to, be firmly connected to the cooling channel walls 22 in the region of its V-legs 40, 43. There are various options for how the insert 34 bears against the cooling duct wall 22. In FIG. 4, the cooling duct wall 22 has, at a radial end 49, an incision 55 against which a radial end 52 of the first V-leg 40 comes into positive contact, ie the insert 34 is supported on the cooling duct wall 22 in this area, so that there is no swirling of the flowing cooling medium.
Ein weiteres Ausführungsbeispiel für die Anlage des Einsatzes 34 an die Kühlkanalwand 22 ist in der Figur 5 gezeigt. Dort weist die Kühlkanalwand 22 an ihrem radialen Ende 49 eine runde Form auf, die von einem komplementär ausgebildeten radialen Ende 52 des V-Schenkels 40 des Einsatz 34 umschlossen wird, so dass auch hier der Einsatz 34 sich an der Kühlkanalwand 22 abstützt.A further exemplary embodiment for the application of the insert 34 to the cooling duct wall 22 is shown in FIG. 5. There, the cooling duct wall 22 has a round shape at its radial end 49, which is enclosed by a complementary radial end 52 of the V-leg 40 of the insert 34, so that the insert 34 is also supported on the cooling duct wall 22 here.
Die Turbinenschaufel kann eine Lauf- oder Leitschaufel jeder beliebigen Turbine, insbesondere einer Dampf- oder Gasturbine sein. The turbine blade can be a rotor or guide blade of any turbine, in particular a steam or gas turbine.

Claims

Patentansprüche claims
1. Turbinenschaufel, die innen zumindest teilweise hohl ausgebildet ist, wobei zumindest drei Kühlkanalwände im Inneren der Turbinenschaufel vorhanden sind, die Kühlkanäle bilden,1. turbine blade which is at least partially hollow on the inside, at least three cooling duct walls being present in the interior of the turbine blade and forming cooling ducts,
d a d u r c h g e k e n n z e i c h n e t, dassd a d u r c h g e k e n n z e i c h n e t that
durch einen Einsatz (34) in die Turbinenschaufel (1) zumindest zwei Kühlkanalwände (22) so miteinander verbunden sind, dass ein Umlenkbereich (25) an zumindest einem radialen Ende (49) zumindest einer Kühlkanalwand (22) für ein in den Kühlkanälen (19) strömendes Medium gebildet ist.at least two cooling duct walls (22) are connected to one another by an insert (34) in the turbine blade (1) such that a deflection region (25) on at least one radial end (49) of at least one cooling duct wall (22) for one in the cooling ducts (19 ) flowing medium is formed.
2. Turbinenschaufel nach Anspruch 1, d a d u r c h g e k e n n z e i c h n e t, dass2. Turbine blade according to claim 1, d a d u r c h g e k e n n z e i c h n e t that
der Einsatz (34) eine V-Form (37) aufweist, wobei sich ein erster V-Schenkel (40) der V-Form (37) an der Kühlkanalwand (22) anliegt und ein zweiter V-Schenkel (43) der V-Form (37) an der zumindest in axialer Richtung (58) übernächsten Kühlkanalwand (22) anliegt.the insert (34) has a V-shape (37), a first V-leg (40) of the V-shape (37) abutting the cooling channel wall (22) and a second V-leg (43) of the V- Form (37) on which at least in the axial direction (58) next to the cooling channel wall (22).
3. Turbinenschaufel nach Anspruch 1, d a d u r c h g e k e n n z e i c h n e t, dass3. turbine blade according to claim 1, d a d u r c h g e k e n n z e i c h n e t that
durch den Einsatz (34) die Kühlkanäle (19) mäanderförmig ausgebildet sind. through the insert (34) the cooling channels (19) are meandering.
Turbinenschaufel nach Anspruch 1, d a d u r c h g e k e n n z e i c h n e t, dass Turbine blade according to claim 1, characterized in that
sich der Einsatz (34) in radialer Richtung (4) erstreckt und zumindest im Bereich eines Schaufelfusses (13) der Turbinenschaufel (1) befestigt ist.the insert (34) extends in the radial direction (4) and is attached to the turbine blade (1) at least in the region of a blade root (13).
5. Turbinenschaufel nach Anspruch 1, d a d u r c h g e k e n n z e i c h n e t, dass5. turbine blade according to claim 1, d a d u r c h g e k e n n z e i c h n e t that
zumindest ein V-Schenkel (40) an seinem radialen Ende (52) formschlüssig an einem radialen Ende (49) der Kühlkanalwand (22) anliegt.at least one V-leg (40) bears at its radial end (52) in a form-fitting manner against a radial end (49) of the cooling channel wall (22).
6. Turbinenschaufel nach Anspruch 1, d a d u r c h g e k e n n z e i c h n e t, dass6. turbine blade according to claim 1, d a d u r c h g e k e n n z e i c h n e t that
zumindest zwei Kühlkanäle (19) in dem einem Schaufelfuss (13) der Turbinenschaufel (1) zugewandten Bereich offen sind und sich etwa parallel zu einer radialen Richtung (4) der Turbinenschaufel (1) erstrecken. at least two cooling channels (19) are open in the area facing a blade root (13) of the turbine blade (1) and extend approximately parallel to a radial direction (4) of the turbine blade (1).
PCT/DE2003/000909 2002-04-08 2003-03-19 Turbine blade WO2003085235A1 (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE10215375.2 2002-04-08
DE2002115375 DE10215375A1 (en) 2002-04-08 2002-04-08 Turbine blade

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WO2003085235A1 true WO2003085235A1 (en) 2003-10-16

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Families Citing this family (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1843007A1 (en) * 2006-04-06 2007-10-10 Siemens Aktiengesellschaft Turbine blade with separate closing element

Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3369792A (en) * 1966-04-07 1968-02-20 Gen Electric Airfoil vane
JPS60182302A (en) * 1984-02-28 1985-09-17 Toshiba Corp Gas turbine cooling blade
US5624231A (en) * 1993-12-28 1997-04-29 Kabushiki Kaisha Toshiba Cooled turbine blade for a gas turbine
DE19963716A1 (en) * 1999-12-29 2001-07-05 Alstom Power Schweiz Ag Baden Cooled flow deflection device for a turbomachine operating at high temperatures

Patent Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3369792A (en) * 1966-04-07 1968-02-20 Gen Electric Airfoil vane
JPS60182302A (en) * 1984-02-28 1985-09-17 Toshiba Corp Gas turbine cooling blade
US5624231A (en) * 1993-12-28 1997-04-29 Kabushiki Kaisha Toshiba Cooled turbine blade for a gas turbine
DE19963716A1 (en) * 1999-12-29 2001-07-05 Alstom Power Schweiz Ag Baden Cooled flow deflection device for a turbomachine operating at high temperatures

Non-Patent Citations (1)

* Cited by examiner, † Cited by third party
Title
PATENT ABSTRACTS OF JAPAN vol. 010, no. 025 (M - 450) 31 January 1986 (1986-01-31) *

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