EP0899425A2 - Gas turbine blade - Google Patents

Gas turbine blade Download PDF

Info

Publication number
EP0899425A2
EP0899425A2 EP98810770A EP98810770A EP0899425A2 EP 0899425 A2 EP0899425 A2 EP 0899425A2 EP 98810770 A EP98810770 A EP 98810770A EP 98810770 A EP98810770 A EP 98810770A EP 0899425 A2 EP0899425 A2 EP 0899425A2
Authority
EP
European Patent Office
Prior art keywords
cooling
blade
turbine blade
steam
cooling system
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
Application number
EP98810770A
Other languages
German (de)
French (fr)
Other versions
EP0899425A3 (en
EP0899425B1 (en
Inventor
Wilhelm Dr. Endres
Hans Dr. Wettstein
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
General Electric Technology GmbH
Original Assignee
ABB Schweiz AG
ABB Asea Brown Boveri Ltd
Asea Brown Boveri AB
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 ABB Schweiz AG, ABB Asea Brown Boveri Ltd, Asea Brown Boveri AB filed Critical ABB Schweiz AG
Publication of EP0899425A2 publication Critical patent/EP0899425A2/en
Publication of EP0899425A3 publication Critical patent/EP0899425A3/en
Application granted granted Critical
Publication of EP0899425B1 publication Critical patent/EP0899425B1/en
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

Links

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

Definitions

  • the invention relates to a turbine blade of a gas turbine, according to the preamble of claim 1.
  • gas turbine plants are caused by an increase in temperatures achieved.
  • temperature resistance of the material of the gas turbine is limited components exposed to the highest temperatures must be cooled. This particularly affects the guide and rotor blades of the gas turbine.
  • the turbine blades are at least partially hollow in their interior and have one or more cooling channels.
  • the latter are made by one Cooling fluid flows through, the cooling effect through convective heat transfer arises inside the blade body.
  • An additional film cooling is possible by placing parts of the cooling fluid through openings in the blade body on the Be guided outside of the turbine blade. A film of cooling fluid forms there, which the outside of the turbine blade from the hot working medium shields the turbine (see DE 36 42 789 C2).
  • cooling fluid are from the compressor the gas turbine plant or from an external source and under Overpressurized air or also appropriately treated water vapor are known.
  • Closed steam cooling systems have opposite and also opposite procedural advantages of the hybrid steam cooling systems mentioned.
  • the range of uses such systems are increasing today particularly because of their higher Efficiency.
  • a closed steam cooling system can penetrate of foreign bodies in the cooling channel adjacent to the blade leading edge be severely damaged.
  • a lot of cooling steam escapes that downstream of the impact point is not sufficient Bucket cooling takes place more. This causes the material to overheat, which is why serious consequential damage can occur.
  • the invention tries to avoid all of these disadvantages. You have the task based on creating turbine blades with increased functional reliability.
  • the interior of the blade body in the area the suction side wall, the pressure side wall and the blade exit edge has a closed cooling system with at least one cooling channel.
  • the blade leading edge has a separate, open cooling system at least one cooling channel and several penetrating the blade body Film cooling holes formed.
  • the open cooling system particularly advantageously consists of two parallel to one another arranged and connected to one another via several feed openings Cooling channels.
  • the cooling can also downstream of a leak of the first cooling channel by supplying the cooling medium from the second Cooling channel can be maintained.
  • Adjacent cooling duct is at least approximately circular.
  • the film cooling holes are arranged tangentially starting from this first cooling channel, while the feed openings extend tangentially from the second cooling channel and also lead tangentially into the first cooling channel.
  • This is the cooling medium A rotating movement is impressed in the first cooling channel. This vortex of the cooling medium ensures improved convective cooling in the interior as well as for effective film cooling of the blade body.
  • the film cooling holes face the suction wall and at least approximately in the flow direction of the working fluid of the gas turbine are aligned.
  • the one emerging from the film cooling holes at high speed The desired flow direction is thus already the cooling medium given. This can have a better effect on the suction side Wall of the turbine blade spreading cooling film and thus an improved Film cooling can be achieved.
  • the closed Steam cooling system also consists of at least two arranged parallel to each other Cooling channels, which are connected to each other via connection openings. After foreign objects have been struck, the cooling medium flows through the connection openings to the corresponding impact points, so that the cooling side downstream cooling sections can be filled with cooling medium. On in this way the functional reliability of the turbine blades can be further increased become.
  • the gas turbine system for example, does not show the compressor, the combustion chamber and the guide vanes of the gas turbine.
  • the flow direction the work equipment is marked with arrows.
  • the gas turbine has several rows of rotor and guide blades.
  • one of the blades 1 is shown. It consists of one Blade root 2 and a blade body 3.
  • the blade body 3 of the moving blade 1 has a suction-side wall 4, one opposite, pressure-side Wall 5, a blade leading edge 6 and a blade leading edge 7 on. It has a hollow interior 8 which is in the area of the suction side Wall 4, the pressure side wall 5 and the blade trailing edge 7 a closed Steam cooling system 9, with a cooling channel 10 (Fig. 2).
  • an open cooling system 11 with two in parallel mutually arranged cooling channels 14, 15 are formed.
  • Between the closed Steam cooling system 9 and the open cooling system 11 is a partition 16 arranged.
  • the first cooling channel 14 of the open cooling system 11 is the blade leading edge 6 adjacent, circular and with the second cooling channel 15 over several feed openings 18 arranged in an intermediate wall 17 are connected.
  • the first cooling channel 14 can also have other suitable shapes, such as, for example approximately circular, elliptical or potato-shaped Have training (not shown).
  • the intermediate wall 17 is in the area of Blade root 2 connected to the suction-side wall 4 via a connecting piece 19, wherein in the connector 19 a plurality of cooling holes 20 for local cooling the suction-side wall 4 are arranged.
  • the feed openings 18 arranged in the intermediate wall 17 close tangentially to the two cooling channels 14, 15.
  • a film hole row 21 with each several tangential to the suction side wall 4 and approximately in the flow direction 12 of the working fluid 13 of the gas turbine aligned film cooling holes 22 educated.
  • a plurality of rows of film holes 21 can also be arranged in the blade body 3 be what in Figure 3 by a second, dashed line of film holes 21 is indicated.
  • Air is used as the cooling medium 23.
  • the air 23 is in the blade root 2 arranged supply channel 24 introduced into the second cooling channel 15 and serves there the convective cooling of the blade body 3 Air 23 through the supply openings 18 in the first cooling channel 14, where they Blade body 3 also cools convectively.
  • the air 23 experiences the first cooling channel 14 and its tangential injection a rotating movement, which significantly improves the cooling effect.
  • the air 23 passes from the first cooling duct 14 through the tangential ones Film cooling holes 22 on the suction side wall 4. There it forms a thin Cooling film from which the outer surface of the blade body 3 from shields hot working fluid 13 of the gas turbine. By aligning the film cooling holes 22 the air 23 is already approximately in the direction of flow 12 of the working fluid 13 of the gas turbine, which further improves film cooling.
  • appropriately prepared water vapor can also be used as the cooling medium 23 Find use.
  • both the closed and the open cooling system 9, 11 operated with the same cooling medium 23, 26. Therefore no separate coolant supply is required, so that the partition between the two cooling systems 9, 11 shortened in the area of the blade root 2 can be trained (not shown).
  • the cooling medium that got into the working fluid 13 of the gas turbine during the cooling process 23 of the open cooling system 11 is in the downstream part of the turbine blading relaxed.
  • that in the closed steam cooling system 9 recycled steam used as cooling medium 26 and for example relaxed in the steam circuit of a steam turbine connected to the gas turbine (not shown).
  • the closed steam cooling system 9 designed as a serpentine cooling system. It consists of two parallel to each other arranged cooling channels 27, 28 which extend in the longitudinal direction of the blade from the blade root 2 extend to the tip of the blade 29.
  • the cooling channels 27, 28 are on of the blade tip 29 is deflected in the direction of the blade root 2 of the moving blade 1 (Fig. 3).
  • rib walls 30 Between the two parallel and in the same direction from steam 26 through which cooling channels 27, 28 are arranged are rib walls 30 which have a plurality of connection openings 31.
  • connection openings 31 FIG. 4
  • holes 25 can also be made in the area of the closed steam cooling system 9 can be compensated. It comes to Impact of foreign bodies in this area of the blade 1 flows the cooling medium from the cooling channel 27, 28 not affected by the Connection openings 31 to the corresponding holes 25, so that the Cooling section downstream of the cooling side can again be filled with steam 26.
  • the the Open cooling system 11 related procedures are analogous to the first Embodiment specified.
  • guide vanes can refer to a gas turbine their cooling are formed analog.

Abstract

A cooling system for a gas turbine blade has two sets of cooling ducts; a closed set of ducts (10) which cools the rear part of the blade and an open set of ducts (11) which cools the leading part of the blade. The closed ducts are supplied with a cooling fluid, which can be steam. The open ducts are supplied with air or steam, and the cooling flow is guided over the suction side (4) of the blade via tangential exit vents (22). Other cooling vents (25) are on the leading edge of the blade. The closed ducts are linked at set points, to maintain a good circulation, even with part of a duct blocked. Likewise the two ducts of the open cooling system are linked by connecting ducts (18) spaced along the blade.

Description

Technisches GebietTechnical field

Die Erfindung betrifft eine Turbinenschaufel einer Gasturbine, gemäss dem Oberbegriff des Anspruchs 1.The invention relates to a turbine blade of a gas turbine, according to the preamble of claim 1.

Stand der TechnikState of the art

Die Leistungssteigerung und die Verbesserung des Wirkungsgrades der heutigen Gasturbinenanlagen werden nicht zuletzt durch eine Erhöhung der Temperaturen erzielt. Da die Temperaturfestigkeit des Materials der Gasturbine jedoch begrenzt ist, müssen die den höchsten Temperaturen ausgesetzten Bauteile gekühlt werden. Dies betrifft insbesondere auch die Leit- und Laufschaufeln der Gasturbine.Increasing performance and improving efficiency today Last but not least, gas turbine plants are caused by an increase in temperatures achieved. However, because the temperature resistance of the material of the gas turbine is limited components exposed to the highest temperatures must be cooled. This particularly affects the guide and rotor blades of the gas turbine.

Dazu sind die Turbinenschaufeln in ihrem Inneren zumindest teilweise hohl ausgebildet und weisen einen oder mehrere Kühlkanäle auf. Letztere werden von einem Kühlfluid durchflossen, wobei die Kühlwirkung durch konvektiven Wärmeübergang im Inneren des Schaufelkörpers entsteht. Eine zusätzliche Filmkühlung ist möglich, indem Teile des Kühlfluids durch Öffnungen im Schaufelkörper auf die Aussenseite der Turbinenschaufel geleitet werden. Dort bildet sich ein Kühlfluidfilm, welcher die Aussenseite der Turbinenschaufel vom heissen Arbeitsmedium der Turbine abschirmt (s. DE 36 42 789 C2). Als Kühlfluid sind aus dem Verdichter der Gasturbinenanlage oder aus einer externen Quelle stammende und unter Überdruck stehende Luft oder auch entsprechend aufbereiteter Wasserdampf bekannt.For this purpose, the turbine blades are at least partially hollow in their interior and have one or more cooling channels. The latter are made by one Cooling fluid flows through, the cooling effect through convective heat transfer arises inside the blade body. An additional film cooling is possible by placing parts of the cooling fluid through openings in the blade body on the Be guided outside of the turbine blade. A film of cooling fluid forms there, which the outside of the turbine blade from the hot working medium shields the turbine (see DE 36 42 789 C2). As cooling fluid are from the compressor the gas turbine plant or from an external source and under Overpressurized air or also appropriately treated water vapor are known.

Technisch unterschiedlich sind Dampfkühlsysteme, die den aus einem Dampfkreislauf stammenden Dampf zunächst in einem geschlossenen Kühlkreislauf halten. Der durch den konvektiven Kühlprozess erwärmte Dampf wird erneut dem Dampfkreislauf zugeführt (s. EP 06 98 723 A2). Es sind auch offene Dampfkühlsysteme bekannt, bei denen der erhitzte Dampf über Öffnungen im Schaufelkörper auf die Aussenseite der Turbinenschaufel geleitet wird. Zudem gibt es sogenannte hybride Dampfkühlsysteme mit einem geschlossenen Hauptteil und einem im Bereich der Schaufelhinterkante offenen Kühlsystem, wobei letzteres mit Dampf oder mit Luft betrieben wird.Technically different are steam cooling systems, which come from a steam cycle First of all keep the steam in a closed cooling circuit. The steam heated by the convective cooling process becomes again the Steam circuit supplied (see EP 06 98 723 A2). They are also open steam cooling systems known in which the heated steam through openings in the blade body is directed to the outside of the turbine blade. There are also so-called Hybrid steam cooling systems with a closed body and one in the area of the blade trailing edge open cooling system, the latter with Steam or air is operated.

Geschlossene Dampfkühlsysteme besitzen gegenüber offenen und auch gegenüber den genannten hybriden Dampfkühlsystemen prozessuale Vorteile. Das Einsatzspektrum solcher Systeme steigt heute insbesondere wegen ihres höheren Wirkungsgrades. Jedoch kann ein geschlossenes Dampfkühlsystem durch Eindringen von Fremdkörpern in den der Schaufeleintrittskante benachbarten Kühlkanal stark geschädigt werden. Je nach Anzahl und Grösse der sich beim Aufschlagen der Fremdkörper in der Schaufeleintrittskante bildenden Löcher, kann so viel Kühldampf entweichen, dass stromab der Einschlagstelle keine ausreichende Schaufelkühlung mehr stattfindet. Dadurch wird das Material überhitzt, weshalb gravierende Folgeschäden auftreten können.Closed steam cooling systems have opposite and also opposite procedural advantages of the hybrid steam cooling systems mentioned. The range of uses such systems are increasing today particularly because of their higher Efficiency. However, a closed steam cooling system can penetrate of foreign bodies in the cooling channel adjacent to the blade leading edge be severely damaged. Depending on the number and size of when opening the foreign body can form holes in the blade leading edge a lot of cooling steam escapes that downstream of the impact point is not sufficient Bucket cooling takes place more. This causes the material to overheat, which is why serious consequential damage can occur.

Darstellung der ErfindungPresentation of the invention

Die Erfindung versucht, alle diese Nachteile zu vermeiden. Ihr liegt die Aufgabe zugrunde, Turbinenschaufeln mit erhöhter Funktionssicherheit zu schaffen.The invention tries to avoid all of these disadvantages. You have the task based on creating turbine blades with increased functional reliability.

Erfindungsgemäss wird dies dadurch erreicht, dass bei einer Vorrichtung gemäss dem Oberbegriff des Anspruchs 1, der Innenraum des Schaufelkörpers im Bereich der saugseitigen Wand, der druckseitigen Wand und der Schaufelaustrittskante ein geschlossenes Kühlsystem mit zumindest einem Kühlkanal aufweist. Im Bereich der Schaufeleintrittskante ist dagegen ein separates, offenes Kühlsystem mit zumindest einem Kühlkanal und mehreren den Schaufelkörper durchdringenden Filmkühllöchern ausgebildet. According to the invention, this is achieved in that with a device according to the preamble of claim 1, the interior of the blade body in the area the suction side wall, the pressure side wall and the blade exit edge has a closed cooling system with at least one cooling channel. In the area the blade leading edge, on the other hand, has a separate, open cooling system at least one cooling channel and several penetrating the blade body Film cooling holes formed.

Infolge der Trennung der Schaufelkühlung in zwei getrennte Kühlsysteme, ist bei Fremdkörpereinschlägen der üblichen Grösse nur das der Schaufeleintrittskante benachbarte, offene Kühlsystem betroffen. Die mittels Dampf konvektiv erfolgende Kühlung des Hauptteils des Schaufelkörpers bleibt jedoch gesichert. Im Bereich der Schaufeleintrittskante wird der Schaufelkörper über das offene Kühlsystem ebenfalls konvektiv und zusätzlich filmgekühlt.As a result of the separation of the blade cooling into two separate cooling systems, Foreign body impacts of the usual size only that of the blade leading edge neighboring, open cooling system affected. The convective one using steam However, cooling of the main part of the blade body remains ensured. In the area the blade leading edge becomes the blade body via the open cooling system also convective and additionally film cooled.

Besonders vorteilhaft besteht das offene Kühlsystem aus zwei parallel zueinander angeordneten sowie über mehrere Zuführöffnungen miteinander verbundenen Kühlkanälen. Bei dieser Ausbildung kann die Kühlung auch stromab einer Leckagestelle des ersten Kühlkanals durch Zufuhr des Kühlmedium aus dem zweiten Kühlkanal aufrechterhalten werden.The open cooling system particularly advantageously consists of two parallel to one another arranged and connected to one another via several feed openings Cooling channels. With this design, the cooling can also downstream of a leak of the first cooling channel by supplying the cooling medium from the second Cooling channel can be maintained.

In einer ersten Ausgestaltungsform der Erfindung ist der der Schaufeleintrittskante benachbarte Kühlkanal zumindest annähernd kreisförmig ausgebildet. Die Filmkühllöcher sind tangential von diesem ersten Kühlkanal ausgehend angeordnet, während die Zuführöffnungen tangential vom zweiten Kühlkanal ausgehen und ebenfalls tangential in den ersten Kühlkanal münden. Dadurch wird dem Kühlmedium im ersten Kühlkanal eine rotierende Bewegung aufgeprägt. Dieser Wirbel des Kühlmediums sorgt sowohl für eine verbesserte konvektive Kühlung im Innenraum als auch für eine effektive Filmkühlung des Schaufelkörpers.In a first embodiment of the invention, that is the blade leading edge Adjacent cooling duct is at least approximately circular. The film cooling holes are arranged tangentially starting from this first cooling channel, while the feed openings extend tangentially from the second cooling channel and also lead tangentially into the first cooling channel. This is the cooling medium A rotating movement is impressed in the first cooling channel. This vortex of the cooling medium ensures improved convective cooling in the interior as well as for effective film cooling of the blade body.

Es ist besonders zweckmässig, wenn die Filmkühllöcher zur saugseitigen Wand und zumindest annähernd in Strömungsrichtung des Arbeitsfluids der Gasturbine ausgerichtet sind. Dem mit hoher Geschwindigkeit aus den Filmkühllöchern austretenden Kühlmedium wird somit die gewünschte Strömungsrichtung bereits vorgegeben. Auf diese Weise kann eine bessere Wirkung des sich auf der saugseitigen Wand der Turbinenschaufel ausbreitenden Kühlfilmes und somit eine verbesserte Filmkühlung erreicht werden.It is particularly useful if the film cooling holes face the suction wall and at least approximately in the flow direction of the working fluid of the gas turbine are aligned. The one emerging from the film cooling holes at high speed The desired flow direction is thus already the cooling medium given. This can have a better effect on the suction side Wall of the turbine blade spreading cooling film and thus an improved Film cooling can be achieved.

Bei einer zweiten Ausgestaltungsform der Erfindung besteht das geschlossene Dampfkühlsystem ebenfalls aus zumindest zwei parallel zueinander angeordneten Kühlkanälen, welche über Verbindungsöffnungen miteinander verbunden sind. Nach Einschlägen von Fremdkörpern strömt das Kühlmedium durch die Verbindungsöffnungen zu den entsprechenden Einschlagstellen, so dass sich die kühlseitig stromab liegende Kühlstrecken wieder mit Kühlmedium füllen können. Auf diese Weise kann die Funktionssicherheit der Turbinenschaufeln weiter erhöht werden.In a second embodiment of the invention, the closed Steam cooling system also consists of at least two arranged parallel to each other Cooling channels, which are connected to each other via connection openings. After foreign objects have been struck, the cooling medium flows through the connection openings to the corresponding impact points, so that the cooling side downstream cooling sections can be filled with cooling medium. On in this way the functional reliability of the turbine blades can be further increased become.

Schliesslich wird je nach Verfügbarkeit im offenen Kühlsystem Luft oder, wie im geschlossenen Kühlsystem, Dampf als Kühlmedium eingesetzt.Finally, depending on availability, air or, as in the closed cooling system, steam used as cooling medium.

Kurze Beschreibung der ZeichnungBrief description of the drawing

In der Zeichnung sind zwei Ausführungsbeispiele anhand der Laufschaufel einer Gasturbine dargestellt.In the drawing, two exemplary embodiments based on the rotor blade are one Gas turbine shown.

Es zeigen:

Fig. 1
einen Teillängsschnitt einer Laufschaufel mit einem geschlossenen und einem offenen Kühlsystem;
Fig. 2
einen Querschnitt durch Fig. 1 in der Ebene II-II (vergrössert);
Fig. 3
eine Darstellung analog Fig. 1, jedoch mit zwei parallelen Kühlkanälen;
Fig. 4
einen Querschnitt durch Fig. 3 in der Ebene IV-IV (vergrössert).
Show it:
Fig. 1
a partial longitudinal section of a blade with a closed and an open cooling system;
Fig. 2
a cross section through Figure 1 in the plane II-II (enlarged).
Fig. 3
a representation analogous to Figure 1, but with two parallel cooling channels.
Fig. 4
a cross section through Fig. 3 in the plane IV-IV (enlarged).

Es sind nur die für das Verständnis der Erfindung wesentlichen Elemente gezeigt. Nicht dargestellt sind von der Gasturbinenanlage beispielsweise der Verdichter, die Brennkammer und die Leitschaufeln der Gasturbine. Die Strömungsrichtung der Arbeitsmittel ist mit Pfeilen bezeichnet.Only the elements essential for understanding the invention are shown. The gas turbine system, for example, does not show the compressor, the combustion chamber and the guide vanes of the gas turbine. The flow direction the work equipment is marked with arrows.

Weg zur Ausführung der ErfindungWay of carrying out the invention

Die nicht dargestellte Gasturbine besitzt mehrere Reihen von Lauf- und Leitschaufeln. In Figur 1 ist eine der Laufschaufeln 1 dargestellt. Sie besteht aus einem Schaufelfuss 2 und einem Schaufelkörper 3. Der Schaufelkörper 3 der Laufschaufel 1 weist eine saugseitige Wand 4, eine dieser gegenüberliegende, druckseitige Wand 5, eine Schaufeleintrittskante 6 und eine Schaufelaustrittskante 7 auf. Er besitzt einen hohlen Innenraum 8, welcher im Bereich der saugseitigen Wand 4, der druckseitigen Wand 5 und der Schaufelaustrittskante 7 ein geschlossenes Dampfkühlsystem 9, mit einem Kühlkanal 10 aufnimmt (Fig. 2). Dagegen ist im Bereich der Schaufeleintrittskante 6 ein offenes Kühlsystem 11 mit zwei parallel zueinander angeordneten Kühlkanälen 14, 15 ausgebildet. Zwischen dem geschlossenen Dampfkühlsystem 9 und dem offenen Kühlsystem 11 ist eine Trennwand 16 angeordnet.The gas turbine, not shown, has several rows of rotor and guide blades. In Figure 1, one of the blades 1 is shown. It consists of one Blade root 2 and a blade body 3. The blade body 3 of the moving blade 1 has a suction-side wall 4, one opposite, pressure-side Wall 5, a blade leading edge 6 and a blade leading edge 7 on. It has a hollow interior 8 which is in the area of the suction side Wall 4, the pressure side wall 5 and the blade trailing edge 7 a closed Steam cooling system 9, with a cooling channel 10 (Fig. 2). Against it in the area of the blade leading edge 6 an open cooling system 11 with two in parallel mutually arranged cooling channels 14, 15 are formed. Between the closed Steam cooling system 9 and the open cooling system 11 is a partition 16 arranged.

Der erste Kühlkanal 14 des offenen Kühlsystems 11 ist der Schaufeleintrittskante 6 benachbart, kreisförmig ausgebildet und mit dem zweiten Kühlkanal 15 über mehrere in einer Zwischenwand 17 angeordnete Zuführöffnungen 18 verbunden. Natürlich kann der erste Kühlkanal 14 auch andere geeignete Formen, wie beispielsweise eine annähernd kreisförmige, eine ellipsen- oder eine kartoffelförmige Ausbildung aufweisen (nicht dargestellt). Die Zwischenwand 17 ist im Bereich des Schaufelfusses 2 über ein Verbindungsstück 19 mit der saugseitigen Wand 4 verbunden, wobei im Verbindungsstück 19 mehrere Kühllöcher 20 zur lokalen Kühlung der saugseitigen Wand 4 angeordnet sind.The first cooling channel 14 of the open cooling system 11 is the blade leading edge 6 adjacent, circular and with the second cooling channel 15 over several feed openings 18 arranged in an intermediate wall 17 are connected. Of course, the first cooling channel 14 can also have other suitable shapes, such as, for example approximately circular, elliptical or potato-shaped Have training (not shown). The intermediate wall 17 is in the area of Blade root 2 connected to the suction-side wall 4 via a connecting piece 19, wherein in the connector 19 a plurality of cooling holes 20 for local cooling the suction-side wall 4 are arranged.

Die in der Zwischenwand 17 angeordneten Zuführöffnungen 18 schliessen tangential an die beiden Kühlkanäle 14, 15 an. Ausgehend vom ersten Kühlkanal 14 ist im Schaufelkörper 3, diesen durchdringend, eine Filmlochreihe 21 mit jeweils mehreren tangentialen, zur saugseitigen Wand 4 sowie annähernd in Strömungsrichtung 12 des Arbeitsfluids 13 der Gasturbine ausgerichteten Filmkühllöchern 22 ausgebildet. Im Schaufelkörper 3 können auch mehrere Filmlochreihen 21 angeordnet sein, was in Figur 3 durch eine zweite, gestrichelt dargestellte Filmlochreihe 21 angedeutet ist.The feed openings 18 arranged in the intermediate wall 17 close tangentially to the two cooling channels 14, 15. Starting from the first cooling duct 14 is in the blade body 3, penetrating this, a film hole row 21 with each several tangential to the suction side wall 4 and approximately in the flow direction 12 of the working fluid 13 of the gas turbine aligned film cooling holes 22 educated. A plurality of rows of film holes 21 can also be arranged in the blade body 3 be what in Figure 3 by a second, dashed line of film holes 21 is indicated.

Beim Betrieb der Gasturbinenanlage wird das aus der Brennkammer stammende heisse Arbeitsfluid 13 in die Gasturbine eingeleitet und dort über die Laufschaufeln 1 entspannt. Dabei können feste Partikel in die Gasturbine eindringen und mit deren Bauteilen kollidieren. Weil das offene Kühlsystem 11 im Bereich der Schaufeleintrittskante 6 und damit in Strömungsrichtung 12 des Arbeitsfluids 13 der Gasturbine am weitesten stromauf angeordnet ist, können die im Arbeitsfluid 13 enthaltenen und auf dem Schaufelkörper 3 der Laufschaufel 1 auftreffenden Partikel fast ausschliesslich das offene Kühlsystem 11 beschädigen, während das von diesem getrennte, geschlossene Kühlsystem 9 geschützt ist. Aus diesem Grund ist die Kühlung des Hauptteils des Schaufelkörpers 3 von vornherein abgesichert.When the gas turbine system is in operation, it comes from the combustion chamber hot working fluid 13 is introduced into the gas turbine and there via the blades 1 relaxed. Solid particles can penetrate into the gas turbine and with it their components collide. Because the open cooling system 11 in the area of the blade leading edge 6 and thus in the flow direction 12 of the working fluid 13 Gas turbine is arranged most upstream, the in the working fluid 13th contained and on the blade body 3 of the blade 1 impinging particles almost exclusively damage the open cooling system 11, while the is protected from this separate, closed cooling system 9. For this Reason is the cooling of the main part of the blade body 3 secured from the outset.

Im offenen Kühlsystem 11 wird entweder aus dem Verdichter der Gasturbinenanlage oder aus einer externen Quelle stammende und unter Überdruck stehende Luft als Kühlmedium 23 eingesetzt. Die Luft 23 wird über einen im Schaufelfuss 2 angeordneten Zuführkanal 24 in den zweiten Kühlkanal 15 eingeleitet und dient dort der konvektiven Kühlung des Schaufelkörpers 3. Anschliessend gelangt die Luft 23 über die Zuführöffnungen 18 in den ersten Kühlkanal 14, wo sie den Schaufelkörper 3 ebenfalls konvektiv kühlt. Infolge der kreisförmigen Ausbildung des ersten Kühlkanals 14 und ihrer tangentialen Eindüsung erfährt die Luft 23 eine rotierende Bewegung, was die Kühlwirkung deutlich verbessert. Ausgehend vom ersten Kühlkanal 14 gelangt die Luft 23 durch die ebenfalls tangential angeordneten Filmkühllöcher 22 auf die saugseitige Wand 4. Dort bildet sie einen dünnen Kühlfilm aus, welcher die äussere Oberfläche des Schaufelkörpers 3 vom heissen Arbeitsfluid 13 der Gasturbine abschirmt. Durch die Ausrichtung der Filmkühllöcher 22 wird die Luft 23 bereits annähernd in Strömungsrichtung 12 des Arbeitsfluids 13 der Gasturbine ausgedüst, was die Filmkühlung weiter verbessert.In the open cooling system 11 either the compressor of the gas turbine system or from an external source and under pressure Air is used as the cooling medium 23. The air 23 is in the blade root 2 arranged supply channel 24 introduced into the second cooling channel 15 and serves there the convective cooling of the blade body 3 Air 23 through the supply openings 18 in the first cooling channel 14, where they Blade body 3 also cools convectively. As a result of the circular formation the air 23 experiences the first cooling channel 14 and its tangential injection a rotating movement, which significantly improves the cooling effect. Outgoing The air 23 passes from the first cooling duct 14 through the tangential ones Film cooling holes 22 on the suction side wall 4. There it forms a thin Cooling film from which the outer surface of the blade body 3 from shields hot working fluid 13 of the gas turbine. By aligning the film cooling holes 22 the air 23 is already approximately in the direction of flow 12 of the working fluid 13 of the gas turbine, which further improves film cooling.

Natürlich kann auch entsprechend aufbereiteter Wasserdampf als Kühlmedium 23 Verwendung finden. In diesem Fall werden sowohl das geschlossene als auch das offene Kühlsystem 9, 11 mit dem gleichen Kühlmedium 23, 26 betrieben. Daher ist keine getrennte Kühlmittelzufuhr erforderlich, so dass die Trennwand zwischen den beiden Kühlsystemen 9, 11 im Bereich des Schaufelfusses 2 verkürzt ausgebildet werden kann (nicht dargestellt). Of course, appropriately prepared water vapor can also be used as the cooling medium 23 Find use. In this case, both the closed and the open cooling system 9, 11 operated with the same cooling medium 23, 26. Therefore no separate coolant supply is required, so that the partition between the two cooling systems 9, 11 shortened in the area of the blade root 2 can be trained (not shown).

Die im Arbeitsfluid 13 enthaltenen Partikel treffen mit grosser kinetischer Energie auf die Schaufeleintrittskante 6 der Laufschaufel 1 auf und können diese durchdringen. Dadurch werden in diesem Bereich Löcher 25 in den Schaufelkörper 3 geschlagen (Fig. 1, Fig. 2). Die durch die Löcher 25 entweichende Luft 23 wird durch zusätzliche Zuführung von Luft 23 aus dem zweiten Kühlkanal 15 kompensiert. Eventuell eindringendes heisses Arbeitsfluid 13 der Gasturbine wird zunächst im Zentrum der verwirbelten Luft 23 gehalten und schliesslich mit dieser verdünnt, so dass die Kühlung im offenen Kühlsystem 11 auch nach Einschlag von Partikeln aufrechterhalten werden kann.The particles contained in the working fluid 13 hit with great kinetic energy on the blade leading edge 6 of the blade 1 and can penetrate it. As a result, holes 25 are made in the blade body 3 in this area struck (Fig. 1, Fig. 2). The air 23 escaping through the holes 25 becomes compensated by additional supply of air 23 from the second cooling duct 15. Any penetrating hot working fluid 13 of the gas turbine is initially held in the center of the swirled air 23 and finally with this diluted so that the cooling in the open cooling system 11 even after impact of particles can be maintained.

Das beim Kühlvorgang in das Arbeitsfluid 13 der Gasturbine gelangte Kühlmedium 23 des offenen Kühlsystems 11 wird im stromab liegenden Teil der Turbinenbeschaufelung entspannt. Demgegenüber wird der im geschlossenen Dampfkühlsystem 9 als Kühlmedium 26 eingesetzte Dampf zurückgeführt und beispielsweise im Dampfkreislauf einer mit der Gasturbine verbundenen Dampfturbine entspannt (nicht dargestellt).The cooling medium that got into the working fluid 13 of the gas turbine during the cooling process 23 of the open cooling system 11 is in the downstream part of the turbine blading relaxed. In contrast, that in the closed steam cooling system 9 recycled steam used as cooling medium 26 and for example relaxed in the steam circuit of a steam turbine connected to the gas turbine (not shown).

In einem zweiten Ausführungsbeispiel ist das geschlossene Dampfkühlsystem 9 als Serpentinenkühlsystem ausgebildet. Es besteht aus zwei parallel zueinander angeordneten Kühlkanälen 27, 28, die sich in Schaufellängsrichtung vom Schaufelfuss 2 bis zur Schaufelspitze 29 erstrecken. Die Kühlkanäle 27, 28 werden an der Schaufelspitze 29 in Richtung Schaufelfuss 2 der Laufschaufel 1 umgelenkt (Fig. 3). Zwischen den beiden parallelen und in gleicher Richtung vom Dampf 26 durchströmten Kühlkanälen 27, 28 sind Rippenwände 30 angeordnet, welche mehrere Verbindungsöffnungen 31 aufweisen. Natürlich ist auch zwischen den in entgegengesetzter Richtung durchströmten Kühlkanälen 28, 27 eine Rippenwand 32 angeordnet. Diese besitzt jedoch keine Verbindungsöffnungen 31 (Fig. 4). An der Schaufelspitze 29 befinden sich Austrittsöffnungen 33 für eventuelle Schmutzpartikel oder andere Fremdkörper des Kühlmediums 26. In a second exemplary embodiment, the closed steam cooling system 9 designed as a serpentine cooling system. It consists of two parallel to each other arranged cooling channels 27, 28 which extend in the longitudinal direction of the blade from the blade root 2 extend to the tip of the blade 29. The cooling channels 27, 28 are on of the blade tip 29 is deflected in the direction of the blade root 2 of the moving blade 1 (Fig. 3). Between the two parallel and in the same direction from steam 26 through which cooling channels 27, 28 are arranged are rib walls 30 which have a plurality of connection openings 31. Of course, between the in in the opposite direction, cooling channels 28, 27 flow through a rib wall 32 arranged. However, this has no connection openings 31 (FIG. 4). On the blade tip 29 there are outlet openings 33 for possible dirt particles or other foreign matter of the cooling medium 26.

Beim Betrieb einer solchen Gasturbinenanlage können auch Löcher 25 im Bereich des geschlossenen Dampfkühlsystems 9 kompensiert werden. Kommt es zum Einschlagen von Fremdkörpern in diesem Bereich der Laufschaufel 1, so strömt das Kühlmedium aus dem jeweils nicht betroffenen Kühlkanal 27, 28 durch die Verbindungsöffnungen 31 zu den entsprechenden Löchern 25, so dass sich die kühlseitig stromab liegende Kühlstrecke wieder mit Dampf 26 füllen kann. Die das offene Kühlsystem 11 betreffenden Verfahrensabläufe sind analog den zum ersten Ausführungsbeispiel angegebenen.When operating such a gas turbine system, holes 25 can also be made in the area of the closed steam cooling system 9 can be compensated. It comes to Impact of foreign bodies in this area of the blade 1 flows the cooling medium from the cooling channel 27, 28 not affected by the Connection openings 31 to the corresponding holes 25, so that the Cooling section downstream of the cooling side can again be filled with steam 26. The the Open cooling system 11 related procedures are analogous to the first Embodiment specified.

Natürlich können die nicht dargestellten Leitschaufeln einer Gasturbine bezüglich ihrer Kühlung analog ausgebildet werden.Of course, the guide vanes, not shown, can refer to a gas turbine their cooling are formed analog.

BezugszeichenlisteReference list

11
LaufschaufelBlade
22nd
SchaufelfussBlade root
33rd
SchaufelkörperBlade body
44th
saugseitige Wandsuction side wall
55
druckseitige Wandpressure side wall
66
SchaufeleintrittskanteBlade leading edge
77
SchaufelaustrittskanteBucket trailing edge
88th
hohler Innenraum, von 3hollow interior, from 3
99
Dampfkühlsystem, geschlossenesSteam cooling system, closed
1010th
KühlkanalCooling channel
1111
Kühlsystem, offenesCooling system, open
1212th
StrömungsrichtungFlow direction
1313
ArbeitsfluidWorking fluid
1414
Kühlkanal, ersterCooling channel, first
1515
Kühlkanal, zweiterCooling channel, second
1616
Trennwand partition wall
1717th
ZwischenwandPartition
1818th
ZuführöffnungFeed opening
1919th
VerbindungsstückConnector
2020th
KühllochCooling hole
2121
FilmlochreiheFilm hole row
2222
FilmkühllochFilm cooling hole
2323
Kühlmedium, Luft, WasserdampfCoolant, air, water vapor
2424th
ZuführkanalFeed channel
2525th
Lochhole
2626
Kühlmedium, DampfCooling medium, steam
2727
KühlkanalCooling channel
2828
KühlkanalCooling channel
2929
SchaufelspitzeBlade tip
3030th
Rippenwand, zwischen 27 und 28Rib wall, between 27 and 28
3131
VerbindungsöffnungConnection opening
3232
Rippenwand, zwischen 28 und 27Rib wall, between 28 and 27
3333
AustrittsöffnungOutlet opening

Claims (8)

Turbinenschaufel einer Gasturbine, mit einem aus einer Schaufeleintrittskante (6), einer dieser gegenüberliegenden Schaufelaustrittskante (7), einer saugseitigen sowie einer druckseitigen Wand (4, 5) und einem hohlen Innenraum (8) bestehenden Schaufelkörper (3), in dessen hohlen Innenraum (8) mehrere, zumindest ein Kühlmedium (23, 26) führende Kühlkanäle (10, 14, 15, 27, 28) angeordnet sind, dadurch gekennzeichnet, dass a) der Innenraum (8) im Bereich der saugseitigen Wand (4), der druckseitigen Wand (5) und der Schaufelaustrittskante (7) ein geschlossenes Dampfkühlsystem (9) mit zumindest einem Kühlkanal (10, 27, 28) aufweist, b) im Bereich der Schaufeleintrittskante (6) ein offenes Kühlsystem (11) mit zumindest einem Kühlkanal (14, 15) und mehreren den Schaufelkörper (3) durchdringenden Filmkühllöchern (22) ausgebildet ist. Turbine blade of a gas turbine, with a blade body (3) consisting of a blade inlet edge (6), an opposite blade outlet edge (7), a suction-side and a pressure-side wall (4, 5) and a hollow interior (8), in the hollow interior ( 8) a plurality of cooling channels (10, 14, 15, 27, 28) carrying at least one cooling medium (23, 26) are arranged, characterized in that a) the interior (8) in the area of the suction-side wall (4), the pressure-side wall (5) and the blade outlet edge (7) has a closed steam cooling system (9) with at least one cooling channel (10, 27, 28), b) an open cooling system (11) with at least one cooling channel (14, 15) and a plurality of film cooling holes (22) penetrating the blade body (3) is formed in the region of the blade leading edge (6). Turbinenschaufel nach Anspruch 1, dadurch gekennzeichnet, dass das offene Kühlsystem (11) aus zwei, parallel zueinander angeordneten sowie über mehrere Zuführöffnungen (18) miteinander verbundenen Kühlkanälen (14, 15) besteht.Turbine blade according to claim 1, characterized in that the open Cooling system (11) from two, arranged parallel to each other and Cooling channels connected to one another via a plurality of supply openings (18) (14, 15) exists. Turbinenschaufel nach Anspruch 2, dadurch gekennzeichnet, dass die Filmkühllöcher (22) tangential vom der Schaufeleintrittskante (6) benachbarten, ersten Kühlkanal (14) ausgehend, die Zuführöffnungen (18) tangential vom zweiten Kühlkanal (15) ausgehend und in den ersten Kühlkanal (14) ebenfalls tangential mündend angeordnet sind.Turbine blade according to claim 2, characterized in that the Film cooling holes (22) tangential from the blade leading edge (6) adjacent, starting from the first cooling duct (14), the feed openings (18) tangential starting from the second cooling duct (15) and into the first cooling duct (14) are also arranged tangentially opening. Turbinenschaufel nach Anspruch 3, dadurch gekennzeichnet, dass der erste Kühlkanal (14) zumindest annähernd kreisförmig ausgebildet ist. Turbine blade according to claim 3, characterized in that the first Cooling channel (14) is at least approximately circular. Turbinenschaufel nach Anspruch 4, dadurch gekennzeichnet, dass die Filmkühllöcher (22) zur saugseitigen Wand (4) und zumindest annähernd in Strömungsrichtung (12) des Arbeitsfluids (13) ausgerichtet sind.Turbine blade according to claim 4, characterized in that the Film cooling holes (22) to the suction-side wall (4) and at least approximately in Flow direction (12) of the working fluid (13) are aligned. Turbinenschaufel nach Anspruch 1, dadurch gekennzeichnet, dass das geschlossene Dampfkühlsystem (9) aus zumindest zwei parallel zueinander angeordneten Kühlkanälen (27, 28) besteht, welche über Verbindungsöffnungen (31) miteinander verbunden sind.Turbine blade according to claim 1, characterized in that the closed Steam cooling system (9) from at least two parallel to each other arranged cooling channels (27, 28), which via connection openings (31) are interconnected. Turbinenschaufel nach Anspruch 2 oder 6, dadurch gekennzeichnet, dass als Kühlmedium (23) im offenen Kühlsystem (11) Luft eingesetzt wird.Turbine blade according to claim 2 or 6, characterized in that air is used as the cooling medium (23) in the open cooling system (11). Turbinenschaufel nach Anspruch 2 oder 6, dadurch gekennzeichnet, dass als Kühlmedium (23) im offenen Kühlsystem (11) Dampf eingesetzt wird.Turbine blade according to claim 2 or 6, characterized in that steam is used as the cooling medium (23) in the open cooling system (11).
EP98810770A 1997-09-01 1998-08-11 Gas turbine blade Expired - Lifetime EP0899425B1 (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE19738065 1997-09-01
DE19738065A DE19738065A1 (en) 1997-09-01 1997-09-01 Turbine blade of a gas turbine

Publications (3)

Publication Number Publication Date
EP0899425A2 true EP0899425A2 (en) 1999-03-03
EP0899425A3 EP0899425A3 (en) 2000-07-05
EP0899425B1 EP0899425B1 (en) 2003-12-03

Family

ID=7840791

Family Applications (1)

Application Number Title Priority Date Filing Date
EP98810770A Expired - Lifetime EP0899425B1 (en) 1997-09-01 1998-08-11 Gas turbine blade

Country Status (5)

Country Link
US (1) US6033181A (en)
EP (1) EP0899425B1 (en)
JP (1) JPH11132003A (en)
CN (1) CN1120287C (en)
DE (2) DE19738065A1 (en)

Cited By (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1162355A2 (en) 2000-06-05 2001-12-12 ALSTOM Power N.V. Cooling method for a gas turbine
EP1605136A2 (en) 2004-05-27 2005-12-14 United Technologies Corporation Cooled rotor blade
US7263834B2 (en) 2000-06-05 2007-09-04 Alstom Technology Ltd Method for cooling a gas turbine system and a gas turbine system for performing this method
EP1600605A3 (en) * 2004-05-27 2007-10-03 United Technologies Corporation Cooled rotor blade
DE102012011294A1 (en) 2011-06-16 2012-12-20 Alstom Technology Ltd. Method for cooling gas turbine plant, involves sucking input side inlet air by compressor of gas turbine plant, where compressor compresses inlet air to output side compressor end air
CN103806951A (en) * 2014-01-20 2014-05-21 北京航空航天大学 Turbine blade combining cooling seam gas films with turbulence columns
EP3425165A1 (en) * 2017-07-05 2019-01-09 General Electric Technology GmbH Mechanical component
EP2828484B1 (en) 2012-03-22 2019-05-08 Ansaldo Energia IP UK Limited Turbine blade

Families Citing this family (40)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE59809583D1 (en) * 1998-12-10 2003-10-16 Alstom Switzerland Ltd Process for producing a welded rotor of a turbomachine
DE19902437C5 (en) 1999-01-22 2017-01-12 General Electric Technology Gmbh Method and device for rapid startup and for rapid increase in output of a gas turbine plant
GB0025012D0 (en) * 2000-10-12 2000-11-29 Rolls Royce Plc Cooling of gas turbine engine aerofoils
DE10053356A1 (en) * 2000-10-27 2002-05-08 Alstom Switzerland Ltd Cooled component, casting core for the production of such a component, and method for producing such a component
EP1321627A1 (en) * 2001-12-21 2003-06-25 Siemens Aktiengesellschaft Air and steam-cooled turbine blade and method for cooling a turbine blade
JP2003200936A (en) * 2001-12-28 2003-07-15 Toyo Roki Mfg Co Ltd Water-draining hole shape for container
US6932573B2 (en) * 2003-04-30 2005-08-23 Siemens Westinghouse Power Corporation Turbine blade having a vortex forming cooling system for a trailing edge
US7198468B2 (en) * 2004-07-15 2007-04-03 Pratt & Whitney Canada Corp. Internally cooled turbine blade
EP1621730B1 (en) 2004-07-26 2008-10-08 Siemens Aktiengesellschaft Cooled turbomachinery element and casting method thereof
US7097419B2 (en) * 2004-07-26 2006-08-29 General Electric Company Common tip chamber blade
GB0418914D0 (en) * 2004-08-25 2004-09-29 Rolls Royce Plc Turbine component
US7128533B2 (en) * 2004-09-10 2006-10-31 Siemens Power Generation, Inc. Vortex cooling system for a turbine blade
US7189060B2 (en) * 2005-01-07 2007-03-13 Siemens Power Generation, Inc. Cooling system including mini channels within a turbine blade of a turbine engine
US7217097B2 (en) * 2005-01-07 2007-05-15 Siemens Power Generation, Inc. Cooling system with internal flow guide within a turbine blade of a turbine engine
US7632071B2 (en) * 2005-12-15 2009-12-15 United Technologies Corporation Cooled turbine blade
WO2009016744A1 (en) * 2007-07-31 2009-02-05 Mitsubishi Heavy Industries, Ltd. Wing for turbine
US8376706B2 (en) * 2007-09-28 2013-02-19 General Electric Company Turbine airfoil concave cooling passage using dual-swirl flow mechanism and method
US10286407B2 (en) 2007-11-29 2019-05-14 General Electric Company Inertial separator
US8393157B2 (en) * 2008-01-18 2013-03-12 General Electric Company Swozzle design for gas turbine combustor
US8511968B2 (en) * 2009-08-13 2013-08-20 Siemens Energy, Inc. Turbine vane for a gas turbine engine having serpentine cooling channels with internal flow blockers
DE102010046331A1 (en) * 2010-09-23 2012-03-29 Rolls-Royce Deutschland Ltd & Co Kg Cooled turbine blades for a gas turbine engine
US8840370B2 (en) 2011-11-04 2014-09-23 General Electric Company Bucket assembly for turbine system
WO2016032585A2 (en) 2014-05-29 2016-03-03 General Electric Company Turbine engine, components, and methods of cooling same
US9915176B2 (en) 2014-05-29 2018-03-13 General Electric Company Shroud assembly for turbine engine
US11033845B2 (en) 2014-05-29 2021-06-15 General Electric Company Turbine engine and particle separators therefore
CA2949547A1 (en) 2014-05-29 2016-02-18 General Electric Company Turbine engine and particle separators therefore
US10036319B2 (en) 2014-10-31 2018-07-31 General Electric Company Separator assembly for a gas turbine engine
US10167725B2 (en) 2014-10-31 2019-01-01 General Electric Company Engine component for a turbine engine
CN104696018B (en) * 2015-02-15 2016-02-17 德清透平机械制造有限公司 A kind of efficient gas turbine blade
US10428664B2 (en) 2015-10-15 2019-10-01 General Electric Company Nozzle for a gas turbine engine
US10174620B2 (en) 2015-10-15 2019-01-08 General Electric Company Turbine blade
US9988936B2 (en) 2015-10-15 2018-06-05 General Electric Company Shroud assembly for a gas turbine engine
CN105840315B (en) * 2016-03-15 2017-10-31 哈尔滨工程大学 A kind of eddy flow cold air cavity configuration applied to air film cooling technology
CN105909318B (en) * 2016-04-26 2017-09-26 西北工业大学 One kind is used for turbine blade air film coolant outlet upstream and expands pore structure
US10704425B2 (en) 2016-07-14 2020-07-07 General Electric Company Assembly for a gas turbine engine
FR3062675B1 (en) * 2017-02-07 2021-01-15 Safran Helicopter Engines HELICOPTER TURBINE HIGH PRESSURE VENTILATED VANE INCLUDING UPSTREAM DUCT AND CENTRAL COOLING CAVITY
US10801724B2 (en) * 2017-06-14 2020-10-13 General Electric Company Method and apparatus for minimizing cross-flow across an engine cooling hole
CN109812301A (en) * 2019-03-06 2019-05-28 上海交通大学 A kind of turbo blade double wall cooling structure with horizontal communication hole
CN112483191B (en) * 2020-11-30 2022-07-19 日照黎阳工业装备有限公司 Turbine blade suitable for gas turbine possesses heat convection function
CN115234306A (en) * 2022-09-21 2022-10-25 中国航发燃气轮机有限公司 Gas turbine air-cooled blade

Citations (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE3642789A1 (en) 1985-12-23 1987-06-25 United Technologies Corp FILM-COOLED TURBINE BLADE OR GUIDE BLADE FOR A GAS TURBINE ENGINE
EP0698723A2 (en) 1994-08-23 1996-02-28 General Electric Company Turbine stator vane segment having closed cooling circuit

Family Cites Families (11)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB856983A (en) * 1958-06-18 1960-12-21 Rolls Royce Improvements in the formation of holes by spark erosion
FR90542E (en) * 1965-08-02 1967-12-29 Snecma Improvement in cooling means of turbine blades or other parts
US4565490A (en) * 1981-06-17 1986-01-21 Rice Ivan G Integrated gas/steam nozzle
DE3211139C1 (en) * 1982-03-26 1983-08-11 MTU Motoren- und Turbinen-Union München GmbH, 8000 München Axial turbine blades, in particular axial turbine blades for gas turbine engines
JPS62294703A (en) * 1986-06-13 1987-12-22 Jinichi Nishiwaki Cooling method for steam turbine blade
GB2202907A (en) * 1987-03-26 1988-10-05 Secr Defence Cooled aerofoil components
US5253976A (en) * 1991-11-19 1993-10-19 General Electric Company Integrated steam and air cooling for combined cycle gas turbines
US5320483A (en) * 1992-12-30 1994-06-14 General Electric Company Steam and air cooling for stator stage of a turbine
US5603606A (en) * 1994-11-14 1997-02-18 Solar Turbines Incorporated Turbine cooling system
JP3781832B2 (en) * 1996-08-29 2006-05-31 株式会社東芝 gas turbine
JP4170400B2 (en) * 1997-04-07 2008-10-22 シーメンス アクチエンゲゼルシヤフト Turbine blade, its use and cooling method of turbine blade

Patent Citations (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE3642789A1 (en) 1985-12-23 1987-06-25 United Technologies Corp FILM-COOLED TURBINE BLADE OR GUIDE BLADE FOR A GAS TURBINE ENGINE
EP0698723A2 (en) 1994-08-23 1996-02-28 General Electric Company Turbine stator vane segment having closed cooling circuit

Cited By (13)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1162355A2 (en) 2000-06-05 2001-12-12 ALSTOM Power N.V. Cooling method for a gas turbine
US6532744B1 (en) 2000-06-05 2003-03-18 Alstom (Switzerland) Ltd Method for cooling a gas turbine system and a gas turbine system for performing this method
US7263834B2 (en) 2000-06-05 2007-09-04 Alstom Technology Ltd Method for cooling a gas turbine system and a gas turbine system for performing this method
EP1605136A2 (en) 2004-05-27 2005-12-14 United Technologies Corporation Cooled rotor blade
EP1600605A3 (en) * 2004-05-27 2007-10-03 United Technologies Corporation Cooled rotor blade
EP1605136A3 (en) * 2004-05-27 2009-01-21 United Technologies Corporation Cooled rotor blade
DE102012011294A1 (en) 2011-06-16 2012-12-20 Alstom Technology Ltd. Method for cooling gas turbine plant, involves sucking input side inlet air by compressor of gas turbine plant, where compressor compresses inlet air to output side compressor end air
US9145774B2 (en) 2011-06-16 2015-09-29 Alstom Technology Ltd. Method for cooling a gas turbine plant and gas turbine plant for implementing the method
DE102012011294B4 (en) 2011-06-16 2019-03-14 Ansaldo Energia Switzerland AG Method for cooling a gas turbine plant and gas turbine plant for carrying out the method
EP2828484B1 (en) 2012-03-22 2019-05-08 Ansaldo Energia IP UK Limited Turbine blade
CN103806951A (en) * 2014-01-20 2014-05-21 北京航空航天大学 Turbine blade combining cooling seam gas films with turbulence columns
EP3425165A1 (en) * 2017-07-05 2019-01-09 General Electric Technology GmbH Mechanical component
US10612396B2 (en) 2017-07-05 2020-04-07 General Electric Technology Gmbh Mechanical component

Also Published As

Publication number Publication date
EP0899425A3 (en) 2000-07-05
CN1120287C (en) 2003-09-03
EP0899425B1 (en) 2003-12-03
DE59810315D1 (en) 2004-01-15
US6033181A (en) 2000-03-07
CN1211667A (en) 1999-03-24
JPH11132003A (en) 1999-05-18
DE19738065A1 (en) 1999-03-04

Similar Documents

Publication Publication Date Title
EP0899425B1 (en) Gas turbine blade
EP0798448B1 (en) System and device to cool a wall which is heated on one side by hot gas
DE3248161C2 (en)
DE10001109B4 (en) Cooled shovel for a gas turbine
DE2320581C2 (en) Gas turbine with air-cooled turbine blades
DE10059997B4 (en) Coolable blade for a gas turbine component
DE60018817T2 (en) Chilled gas turbine blade
DE60027679T2 (en) Chilled turbine blade with oblique and rafter-shaped vortex generators
DE69831109T2 (en) Cooling air supply system for the blades of a gas turbine
DE3211139C1 (en) Axial turbine blades, in particular axial turbine blades for gas turbine engines
EP2384392B1 (en) Cooled component for a gas turbine
DE69822100T2 (en) turbine blade
DE60025988T2 (en) Turbomachine blade with multiple impingement cooling
DE69923746T2 (en) Gas turbine blade with serpentine cooling channels
EP1219781B1 (en) Device and method to cool a platform of a turbine blade
DE1601561C3 (en) Cooled airfoil blade for an axial flow machine
WO2003052240A2 (en) Gas turbine system
DE956822C (en) Turbine blade for the rotor of a turbine
DE69908603T2 (en) STEAM-COOLED STATOR BLADE OF A GAS TURBINE
DE60122050T2 (en) Turbine vane with insert with areas for impingement cooling and convection cooling
DE2042947A1 (en) Blade arrangement with cooling device
DE69923914T2 (en) Turbomachine blade with special cooling of the leading edge
DE3248162A1 (en) COOLABLE SHOVEL
DE102005044183A1 (en) Apparatus and method for cooling turbine blade platforms
EP1191189A1 (en) Gas turbine blades

Legal Events

Date Code Title Description
PUAI Public reference made under article 153(3) epc to a published international application that has entered the european phase

Free format text: ORIGINAL CODE: 0009012

AK Designated contracting states

Kind code of ref document: A2

Designated state(s): DE GB

AX Request for extension of the european patent

Free format text: AL;LT;LV;MK;RO;SI

PUAL Search report despatched

Free format text: ORIGINAL CODE: 0009013

AK Designated contracting states

Kind code of ref document: A3

Designated state(s): AT BE CH CY DE DK ES FI FR GB GR IE IT LI LU MC NL PT SE

AX Request for extension of the european patent

Free format text: AL;LT;LV;MK;RO;SI

17P Request for examination filed

Effective date: 20001027

RAP1 Party data changed (applicant data changed or rights of an application transferred)

Owner name: ABB (SCHWEIZ) AG

AKX Designation fees paid

Free format text: DE GB

RAP1 Party data changed (applicant data changed or rights of an application transferred)

Owner name: ALSTOM

17Q First examination report despatched

Effective date: 20020701

RAP1 Party data changed (applicant data changed or rights of an application transferred)

Owner name: ALSTOM (SWITZERLAND) LTD

GRAH Despatch of communication of intention to grant a patent

Free format text: ORIGINAL CODE: EPIDOS IGRA

GRAS Grant fee paid

Free format text: ORIGINAL CODE: EPIDOSNIGR3

GRAA (expected) grant

Free format text: ORIGINAL CODE: 0009210

AK Designated contracting states

Kind code of ref document: B1

Designated state(s): DE GB

REG Reference to a national code

Ref country code: GB

Ref legal event code: FG4D

Free format text: NOT ENGLISH

RAP2 Party data changed (patent owner data changed or rights of a patent transferred)

Owner name: ALSTOM TECHNOLOGY LTD

REF Corresponds to:

Ref document number: 59810315

Country of ref document: DE

Date of ref document: 20040115

Kind code of ref document: P

GBT Gb: translation of ep patent filed (gb section 77(6)(a)/1977)

Effective date: 20040415

PLBE No opposition filed within time limit

Free format text: ORIGINAL CODE: 0009261

STAA Information on the status of an ep patent application or granted ep patent

Free format text: STATUS: NO OPPOSITION FILED WITHIN TIME LIMIT

26N No opposition filed

Effective date: 20040906

REG Reference to a national code

Ref country code: DE

Ref legal event code: R082

Ref document number: 59810315

Country of ref document: DE

Representative=s name: ROESLER, UWE, DIPL.-PHYS.UNIV., DE

Ref country code: DE

Ref legal event code: R081

Ref document number: 59810315

Country of ref document: DE

Owner name: ANSALDO ENERGIA IP UK LIMITED, GB

Free format text: FORMER OWNER: ALSTOM TECHNOLOGY LTD., BADEN, CH

Ref country code: DE

Ref legal event code: R081

Ref document number: 59810315

Country of ref document: DE

Owner name: GENERAL ELECTRIC TECHNOLOGY GMBH, CH

Free format text: FORMER OWNER: ALSTOM TECHNOLOGY LTD., BADEN, CH

PGFP Annual fee paid to national office [announced via postgrant information from national office to epo]

Ref country code: GB

Payment date: 20160819

Year of fee payment: 19

Ref country code: DE

Payment date: 20160822

Year of fee payment: 19

REG Reference to a national code

Ref country code: DE

Ref legal event code: R082

Ref document number: 59810315

Country of ref document: DE

Representative=s name: ROESLER, UWE, DIPL.-PHYS.UNIV., DE

Ref country code: DE

Ref legal event code: R081

Ref document number: 59810315

Country of ref document: DE

Owner name: ANSALDO ENERGIA IP UK LIMITED, GB

Free format text: FORMER OWNER: GENERAL ELECTRIC TECHNOLOGY GMBH, BADEN, CH

REG Reference to a national code

Ref country code: GB

Ref legal event code: 732E

Free format text: REGISTERED BETWEEN 20170824 AND 20170830

REG Reference to a national code

Ref country code: DE

Ref legal event code: R119

Ref document number: 59810315

Country of ref document: DE

GBPC Gb: european patent ceased through non-payment of renewal fee

Effective date: 20170811

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: DE

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20180301

Ref country code: GB

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20170811