EP1073827A1 - Turbine blade - Google Patents

Turbine blade

Info

Publication number
EP1073827A1
EP1073827A1 EP99937814A EP99937814A EP1073827A1 EP 1073827 A1 EP1073827 A1 EP 1073827A1 EP 99937814 A EP99937814 A EP 99937814A EP 99937814 A EP99937814 A EP 99937814A EP 1073827 A1 EP1073827 A1 EP 1073827A1
Authority
EP
European Patent Office
Prior art keywords
platform
hot gas
blade
turbine blade
load
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
EP99937814A
Other languages
German (de)
French (fr)
Other versions
EP1073827B1 (en
Inventor
Peter Tiemann
Ariel Jacala
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.)
Siemens AG
Original Assignee
Siemens AG
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 AG filed Critical Siemens AG
Publication of EP1073827A1 publication Critical patent/EP1073827A1/en
Application granted granted Critical
Publication of EP1073827B1 publication Critical patent/EP1073827B1/en
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

Links

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
    • F01D5/147—Construction, i.e. structural features, e.g. of weight-saving hollow blades
    • 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
    • F01D9/00—Stators
    • F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
    • F01D9/04—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector
    • F01D9/042—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector fixing blades to stators
    • 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

Definitions

  • the invention relates to a cast turbine blade with an airfoil and a platform area.
  • DE 26 28 807 AI shows an impact cooling system for a gas turbine blade.
  • the gas turbine blade is directed along a blade axis and points along the
  • Blade axis on an airfoil and a platform area In the platform area, a platform extends transversely to the blade axis and radially outward away from the blade.
  • a platform forms part of a flow channel for a working fluid which flows through a gas turbine, in which the turbine blade is installed.
  • a gas turbine has very high temperatures in this flow channel.
  • the surface of the platform exposed to the hot gas is subjected to high thermal loads.
  • a perforated wall element is arranged in front of the side of the platform facing away from the hot gas. Cow air enters through the holes in the wall element and hits the side of the platform facing away from the hot gas. This achieves efficient impact cooling.
  • GB-PS 1 289 435 relates to guide elements for gas streams, in particular gas turbine showers.
  • a laminar guide element is arranged on a casting and can be cooled by a perspiration cooling system. This structure cannot be used for cast turbine blades.
  • DE 26 43 049 AI shows a cooling arrangement for cooling the platform of a turbine blade. Comparable to the arrangement of the above DE 26 28 807 AI is in front of the side of the platform facing away from the hot gas side 2 plate with openings arranged through the cooling air against the
  • the object of the invention is to provide a thermally highly resilient, cast turbine blade, in which only low thermal stresses occur in the platform area.
  • this object is achieved by a cast turbine blade directed along a blade axis and having a blade leaf and a platform area in succession along the blade axis, the platform area comprising a hot gas platform which extends transversely to the blade axis and adjoins the blade blade and a load platform opposite the hot gas platform comprises, wherein the load platform is designed to absorb forces which can be caused by a working fluid flowing around the airfoil.
  • a turbine blade is fastened over the platform area m of the turbine, in particular on the turbine housing.
  • the platform must absorb loads caused by forces acting on the airfoil. Such forces are caused by the pressure of the hot working fluid flowing through the turbine, for example a hot gas or steam. The inclusion of these loads requires that the platform have a minimum thickness in order to transmit the forces to the turbine housing without deformation.
  • the platform limits the flow channel through which a hot gas flows.
  • the invention marks a new way in the construction of the platform area of cast turbine blades: the platform area is designed as a double platform made of two opposite platforms. This ensures that the hot gas platform, which delimits the flow channel and is exposed to the hot gas, can be made thin.
  • the execution in two platforms results in a functional 3 Separation for the platforms.
  • the hot gas platform is essentially responsible for the limitation of the flow channel and thus for the channeling of the hot gas.
  • the opposite load platform which is not acted upon by the hot gas, takes over the loads caused by the forces acting on the airfoil.
  • This separation of functions enables the hot gas platform to be made so thin that the hot gas canalization is ensured without having to intercept significant forces.
  • the thin design of the hot gas platform obtained in this way has the particular advantage that comparatively low thermal stresses form in the hot gas platform.
  • the design of the platform area as a double platform is also advantageous compared to designs in which a solid platform is stiffened by ribs on the side facing away from the hot gas, since high thermal stresses can also occur at the transition points between the ribs and the platform.
  • the hot gas platform is preferably substantially thinner than the load platform. Since the hot gas platform only has to absorb a comparatively small part of the loads that occur, it can be carried out thinner than the load platform. The load platform absorbs the majority of the forces that occur.
  • the airfoil is part of a profile extending through the platform area, the hot gas platform and the load platform preferably each having an inner Ran ⁇ , via which they are connected to the profile. Furthermore, they each have an outer edge via which they are connected to one another.
  • the hot gas platform and the load platform are further preferably connected to one another only via their respective inner edge and through their respective outer edge. This results in a low connection 4 flat between the hot gas platform and the load platform.
  • connection area and the connection via the respective outer edge result in only low thermal stresses with a high mechanical stability of the double platform design.
  • Thermal expansion is relatively free due to the small number of connection points.
  • Guide elements for guiding a cooling medium to the hot gas platform are preferably arranged between the hot gas platform and the load platform.
  • Such guide elements can, for. B. be sheets that divide the space between the platforms like a chamber or z. B. also vertically directed channels between the platforms.
  • the guide elements are preferably designed with a wall thickness that is thin compared to the hot gas platform.
  • the thin design of the guide elements does not cause any significant additional thermal stresses.
  • the load platform preferably has a multiplicity of through-holes directed towards the hot gas platform.
  • a cooling medium in particular cooling air from a compressor of a gas turbine, can thus flow through the load platform and against the hot gas platform and thus cool it efficiently.
  • the turbine blade is preferably designed as a gas turbine blade, in particular for a stationary gas turbine. 5
  • the invention is explained in more detail with reference to the drawing. It shows :
  • FIG. 1 shows a perspective illustration of a part of a gas turbine blade
  • FIG. 2 shows a longitudinal section through the gas turbine blade from FIG. 1.
  • FIG. 1 shows a section of a cast gas turbine blade 1 directed along a blade axis 3 and having a profile 2.
  • the profile 2 partially forms an airfoil 5.
  • the blade area 5, which is only partially shown, is followed by a platform region 7 along the blade axis 3.
  • the profile 2 extends through the platform area 7.
  • the gas turbine blade 1 has a cavity 8 which extends continuously along the blade axis 3.
  • a stabilizing wall 6 extends along the blade axis 3 through the cavity 8 of the turbine blade 1.
  • a hot gas platform 9 belonging to the platform area 7 adjoins the blade blade 5.
  • a load platform 11 lies opposite the hot gas platform 9.
  • the hot gas platform 9 has an inner edge 13, via which it is connected to the profile 2.
  • the platform area 7 is integrally connected to the profile 2 by casting the entire gas turbine blade 1.
  • the hot gas platform 9 also has an outer edge 15 which is approximately rectangular.
  • the hot gas platform 9 is curved in the direction of the blade axis 9. This shape of the hot gas platform 9 results in a large number of similarly constructed turbine blades when installed in a turbine in the direction of flow. 6 further flow channel.
  • the load platform 11 has an inner edge 17, which is likewise delimited by the profile 2 and at the same time is the edge of an opening of the cavity 8 extending through the turbine blade 1.
  • the load platform 11 also has an approximately rectangular outer edge 19 and has approximately the same curvature as the hot gas platform 9.
  • the hot gas platform 9 has a thickness D1 and the load platform has a thickness D2. These thicknesses D1, D2 can optionally also vary within the respective platform, in which case with the thicknesses
  • Dl, D2 mean thicknesses are meant.
  • the load platform 11 and the hot gas platform 9 are connected to one another via their respective inner edges 13, 17 and the profile 2. Furthermore, the hot gas platform 9 and the load platform 11 are connected by em connecting element 29. This shows one in
  • first part 29A Area of the outer edges 15 and 19 arranged first part 29A. Furthermore, it has a second part 29B opposite the first part 29A and likewise lying in the region of the outer edges 15, 19.
  • the connecting element 29 delimits from the hot gas platform 9 two opposing holding bases 21 and 23.
  • a holding base 25 is delimited from the load platform 11.
  • the load platform 11 also has a stair-like holding base 27 opposite the holding base 25. With the help of these holding bases 21, 23, 25, 27, the turbine blade 1 n of a gas turbine, not shown, is held.
  • the hot gas platform 9 (see FIG. 2) of the hot gas platform 9 partially limits the flow path through the gas turbine. A hot working fluid flowing through the gas turbine flows around the airfoil 5.
  • FIG. 2 shows a longitudinal section through the gas turbine blade 1 of FIG. 1.
  • the stiffening wall 6 leading through the cavity 8 of the turbine blade 1 is visible.
  • the hot gas platform 9 and the load platform 11 are largely independent of each other. This would result in a separation of functions for the platforms 9, 11.
  • the hot gas platform 9 takes over the channeling of the hot working fluid and only needs to absorb a small part of the forces that are exerted on the airfoil 5 by the working fluid.
  • the hot gas platform 9 can thus be made thin. This gives the great advantage that only low thermal stresses occur in the hot gas platform 9.
  • the load platform 11 is made thicker because it absorbs the majority of the forces. However, it is protected from the hot working fluid by the hot gas platform 9, as a result of which thermal stresses hardly occur in the load platform 11 either.

Abstract

The invention relates to a cast turbine blade (1), comprising a blade (5) and a platform area (7), especially a gas turbine guide blade. The platform area (7) is formed by a hot gas platform (9) on the hot gas side and an opposite load platform (11). The load platform (11) absorbs the forces enabling a thin configuration of the hot gas platform (9). Particularly little heat stress occurs.

Description

Beschreibungdescription
TurbmenschaufelTurbine blade
Die Erfindung betrifft eine gegossene Turbmenschaufel mit einem Schaufelblatt und einem Plattformbereich.The invention relates to a cast turbine blade with an airfoil and a platform area.
Aus der DE 26 28 807 AI geht ein Prallkuhlsystem für eine Gasturbmenschaufel hervor. Die Gasturb enschaufel ist ent- lang einer Schaufelachse gerichtet und weist entlang derDE 26 28 807 AI shows an impact cooling system for a gas turbine blade. The gas turbine blade is directed along a blade axis and points along the
Schaufelachse einen Schaufelblatt und einen Plattformbereich auf. Im Plattformbereich erstreckt sich quer zu Schaufelachse eine Plattform vom Schaufelblatt weg radial nach außen. Eine solche Plattform bildet einen Teil eines Stromungskanales für ein Arbeitsfluid, welches eine Gasturbine durchströmt, in die die Turb enschaufel eingebaut ist. Be einer Gasturbine treten in diesem Stromungskanal sehr hohe Temperaturen auf. Dadurch wird die dem Heißgas ausgesetzte Oberflache der Plattform stark thermisch belastet. Zur Kühlung der Plattform ist vor der dem Heißgas abgewandten Seite der Plattform ein gelochtes Wandelement angeordnet. Über die Locher in dem Wandelement tritt Kuhlluft ein und trifft auf die dem Heißgas abgewandte Seite der Plattform. Damit wird eine effiziente Prallkuhlung erreicht.Blade axis on an airfoil and a platform area. In the platform area, a platform extends transversely to the blade axis and radially outward away from the blade. Such a platform forms part of a flow channel for a working fluid which flows through a gas turbine, in which the turbine blade is installed. A gas turbine has very high temperatures in this flow channel. As a result, the surface of the platform exposed to the hot gas is subjected to high thermal loads. To cool the platform, a perforated wall element is arranged in front of the side of the platform facing away from the hot gas. Cow air enters through the holes in the wall element and hits the side of the platform facing away from the hot gas. This achieves efficient impact cooling.
Die GB-PS 1 289 435 betrifft Fuhrungselemente für Gasstrome, insbesondere Gasturbmenschaufein. Auf einem Gußteil ist ein laminar aufgebautes Fuhrungselement angeordnet, daß durch eine Transpirationskuhlung kuhlbar ist. Dieser Aufbau ist für gegossene Turbinenschaufeln nicht anwendbar.GB-PS 1 289 435 relates to guide elements for gas streams, in particular gas turbine showers. A laminar guide element is arranged on a casting and can be cooled by a perspiration cooling system. This structure cannot be used for cast turbine blades.
Aus der DE 26 43 049 AI geht eine Kuhlanordnung zur Kühlung der Plattform einer Turbmenschaufel hervor. Vergleichbar mit der Anordnung der obengenannten DE 26 28 807 AI ist vor der der Heißgasseite abgewandten Seite der Plattform eine 2 Platte mit Offnungen angeordnet, durch die Kuhlluft gegen dieDE 26 43 049 AI shows a cooling arrangement for cooling the platform of a turbine blade. Comparable to the arrangement of the above DE 26 28 807 AI is in front of the side of the platform facing away from the hot gas side 2 plate with openings arranged through the cooling air against the
Plattform strömt.Platform is streaming.
Aufgabe der Erfindung ist es, eine thermisch hoch belastbare, gegossene Turbmenschaufel anzugeben, bei der nur geringe thermische Spannungen im Plattformbereich auftreten. Erfmdungsgemaß wird diese Aufgabe gelost durch eine entlang einer Schaufelachse gerichtete, gegossene Turbmenschaufel mit entlang der Schaufelachse aufeinanderfolgend einem Schau- felblatt und einem Plattformbereich, wobei der Plattformbereich eine sich quer zur Schaufelachse erstreckende, an das Schaufelblatt grenzende Heißgasplattform und eine der Heiß- gasplattform gegenüberliegende Lastplattform umfaßt, wobei die Lastplattform für eine Aufnahme von Kräften ausgelegt ist, die durch ein um das Schaufelblatt strömendes Arbeits- fluid hervorrufbar sind.The object of the invention is to provide a thermally highly resilient, cast turbine blade, in which only low thermal stresses occur in the platform area. According to the invention, this object is achieved by a cast turbine blade directed along a blade axis and having a blade leaf and a platform area in succession along the blade axis, the platform area comprising a hot gas platform which extends transversely to the blade axis and adjoins the blade blade and a load platform opposite the hot gas platform comprises, wherein the load platform is designed to absorb forces which can be caused by a working fluid flowing around the airfoil.
Eine Turbmenschaufel wird über den Plattformbereich m der Turbine, insbesondere am Turbinengehause, befestigt. Dadurch muß die Plattform Lasten aufnehmen, die durch am Schaufelblatt angreifende Kräfte verursacht werden. Solche Kräfte werden durch den Druck des die Turbine durchströmenden heißen Arbeitsfluides, z.B. einem heißen Gas oder Dampf, hervorgerufen. Die Aufnahme dieser Lasten erfordert, daß die Plattform eine Mindestdicke hat, um die Kräfte ohne Verformung an das Turbinengehause durchzuleiten. Gleichzeitig begrenzt die Plattform, wie oben ausgeführt, den von einem heißen Gas durchströmten Stromungskanal. Mit der Erfindung wird e n neuer Weg in der Konstruktion des Plattformbereiches gegosse- ner Turbinenschaufeln beschriften: Der Plattformbereich ist als Doppelplattform aus zwei einander gegenüberliegenden Plattformen ausgebildet. Dadurch wird erreicht, daß die Heiß- gasplattform, welche den Stromungskanal begrenzt und dem heißen Gas ausgesetzt ist, dünn ausgeführt werden kann. Mit der Ausfuhrung in zwei Plattformen ergibt sich eine Funkti- 3 onstrennung für die Plattformen. Die Heißgasplattform ist im wesentlichen für die Begrenzung des Stromungskanales und damit für die Kanalisierung des heißen Gases verantwortlich. Die gegenüberliegende, vom Heißgas nicht beaufschlagte Lastplattform übernimmt die Aufnahme der durch die am Schaufelblatt angreifenden Kräfte verursachten Lasten. Diese Funktionstrennung ermöglicht es, die Heißgasplattform so dünn auszufuhren, daß die Heißgaskanalisierung gewahrleistet ist, ohne aber wesentliche Kräfte abfangen zu müssen. Durch die so gewonnene dünne Ausfuhrung der Heißgasplattform ergibt sich insbesondere der Vorteil, daß sich m der Heißgasplattform vergleichsweise geringe thermische Spannungen ausbilden. Auch gegenüber Ausfuhrungen, bei denen eine emstuckige Plattform durch Rippen an der heißgasabgewandten Seite versteift ist, ist die Ausfuhrung des Plattformbereiches als Doppelplattform vorteilhaft, denn an den Übergangsstellen zwischen den Rippen und der Plattform können ebenfalls hohe thermische Spannungen auftreten.A turbine blade is fastened over the platform area m of the turbine, in particular on the turbine housing. As a result, the platform must absorb loads caused by forces acting on the airfoil. Such forces are caused by the pressure of the hot working fluid flowing through the turbine, for example a hot gas or steam. The inclusion of these loads requires that the platform have a minimum thickness in order to transmit the forces to the turbine housing without deformation. At the same time, as stated above, the platform limits the flow channel through which a hot gas flows. The invention marks a new way in the construction of the platform area of cast turbine blades: the platform area is designed as a double platform made of two opposite platforms. This ensures that the hot gas platform, which delimits the flow channel and is exposed to the hot gas, can be made thin. The execution in two platforms results in a functional 3 Separation for the platforms. The hot gas platform is essentially responsible for the limitation of the flow channel and thus for the channeling of the hot gas. The opposite load platform, which is not acted upon by the hot gas, takes over the loads caused by the forces acting on the airfoil. This separation of functions enables the hot gas platform to be made so thin that the hot gas canalization is ensured without having to intercept significant forces. The thin design of the hot gas platform obtained in this way has the particular advantage that comparatively low thermal stresses form in the hot gas platform. The design of the platform area as a double platform is also advantageous compared to designs in which a solid platform is stiffened by ribs on the side facing away from the hot gas, since high thermal stresses can also occur at the transition points between the ribs and the platform.
Vorzugsweise ist die Heißgasplattform wesentlich dunner als die Lastplattform. Da die Heißgasplattform allenfalls nur einen vergleichsweise geringen Teil der auftretenden Lasten aufnehmen muß, ist sie dunner ausfuhrbar, als die Lastplattform. Die Lastplattform fangt den Hauptteil der auftretenden Kräfte ab.The hot gas platform is preferably substantially thinner than the load platform. Since the hot gas platform only has to absorb a comparatively small part of the loads that occur, it can be carried out thinner than the load platform. The load platform absorbs the majority of the forces that occur.
Das Schaufelblatt ist Teil eines sich durch den Plattformbereich erstreckenden Profiles, wobei die Heißgasplattform und die Lastplattform vorzugsweise jeweils einen inneren Ranα auf, über den sie mit dem Profil verbunden sind. Weiterhin weisen sie jeweils einen äußeren Rand auf, über den sie miteinander verbunden sind. Weiter bevorzugt sind die Heiß- gasplattform und die Lastplattform nur über ihren jeweiligen inneren Rand und durch ihren jeweiligen äußeren Rand mitem- anαer verbunden. Damit ergibt sich eine geringe Verbmdungs- 4 flache zwischen der Heißgasplattform und der Lastplattform.The airfoil is part of a profile extending through the platform area, the hot gas platform and the load platform preferably each having an inner Ranα, via which they are connected to the profile. Furthermore, they each have an outer edge via which they are connected to one another. The hot gas platform and the load platform are further preferably connected to one another only via their respective inner edge and through their respective outer edge. This results in a low connection 4 flat between the hot gas platform and the load platform.
Durch diese geringe Verbindungsflache und durch die Verbindung über den jeweiligen äußeren Rand ergeben sich bei einer hohen mechanischen Stabilität der Doppelplattformausfuhrung nur geringe thermische Spannungen. Thermische Ausdehnungen sind durch die geringe Anzahl an Verbindungsstellen relativ frei möglich.This small connection area and the connection via the respective outer edge result in only low thermal stresses with a high mechanical stability of the double platform design. Thermal expansion is relatively free due to the small number of connection points.
Bevorzugt sind zwischen der Heißgasplattform und der Lastplattform Fuhrungselemente zur Fuhrung eines Kuhlmediums zur Heißgasplattform angeordnet. Solche Fuhrungselemente können z. B. Bleche sein, die den Raum zwischen den Plattformen kammerartig unterteilen oder z. B. auch vertikal zwischen den Plattformen gerichtete Kanäle. Durch solche Fuhrungselemente kann ein Kuhlmedium, insbesondere Kuhlluft, effizienterweise gegen die he ßgasabgewandte Seite der Heißgasplattform gelenkt werden. Insbesondere kann hierdurch eine effiziente Prallkuhlung ermöglicht werden.Guide elements for guiding a cooling medium to the hot gas platform are preferably arranged between the hot gas platform and the load platform. Such guide elements can, for. B. be sheets that divide the space between the platforms like a chamber or z. B. also vertically directed channels between the platforms. By means of such guide elements, a cooling medium, in particular cooling air, can be efficiently directed against the side of the hot gas platform facing away from the hot gas. In particular, this enables efficient impingement cooling.
Vorzugsweise sind die Fuhrungselemente mit einer Wandstarke ausgebildet, die dünn ist gegenüber der Heißgasplattform. Durch die dünne Ausfuhrung der Fuhrungselemente werden keine wesentlichen, zusätzlichen thermischen Spannungen verursacht.The guide elements are preferably designed with a wall thickness that is thin compared to the hot gas platform. The thin design of the guide elements does not cause any significant additional thermal stresses.
Vorzugsweise weist die Lastplattform eine Vielzahl von auf die Heißgasplattform gerichteten Durchbohrungen auf. Damit kann ein Kuhlmedium, insbesondere Kuhlluft aus einem Verdichter einer Gasturbine, durch die Lastplattform hindurch und gegen die Heißgasplattform strömen und diese damit effizient kühlen.The load platform preferably has a multiplicity of through-holes directed towards the hot gas platform. A cooling medium, in particular cooling air from a compressor of a gas turbine, can thus flow through the load platform and against the hot gas platform and thus cool it efficiently.
Bevorzugt ist die Turbmenschaufel als eine Gasturb enschau- fel ausgebildet, insbesondere für eine stationäre Gasturbine. 5 Die Erfindung wird anhand der Zeichnung naher erläutert. Es zeigt :The turbine blade is preferably designed as a gas turbine blade, in particular for a stationary gas turbine. 5 The invention is explained in more detail with reference to the drawing. It shows :
Figur 1 eine perspektivische Darstellung eines Teils ei- ner Gasturbmenschaufel, undFIG. 1 shows a perspective illustration of a part of a gas turbine blade, and
Figur 2 einen Längsschnitt durch die Gasturbmenschaufel aus Figur 1.FIG. 2 shows a longitudinal section through the gas turbine blade from FIG. 1.
Gleiche Bezugszeichen haben m den einzelnen Figuren die gleiche Bedeutung.The same reference numerals have the same meaning in the individual figures.
Figur 1 zeigt einen Ausschnitt einer entlang einer Schaufelachse 3 gerichteten, gegossenen Gasturbmenschaufel 1 mit einem Profil 2. Das Profil 2 bildet teilweise e Schaufelblatt 5. An das nur teilweise dargestellte Schaufelblatt 5 schließt sich entlang der Schaufelachse 3 em Plattformbereich 7 an. Das Profil 2 erstreckt sich durch den Plattformbereich 7 hindurch. Die Gasturbmenschaufel 1 weist im Inne- ren des Profils 2 einen sich entlang der Schaufelachse 3 durchgangig erstreckenden Hohlraum 8 auf. Eine Stabilisie- rungswand 6 erstreckt sich entlang der Schaufelachse 3 durch den Hohlraum 8 der Turbmenschaufel 1. Quer zur Schaufelachse 3 schließt sich an das Schaufelblatt 5 eine zum Plattformbe- reich 7 gehörende Heißgasplattform 9 an. Der Heißgasplattform 9 gegenüber liegt eine Lastplattform 11. Die Heißgasplattform 9 weist einen inneren Rand 13 auf, über welchen sie mit dem Profil 2 verbunden ist. Der Plattformbereich 7 ist durch Gießen der gesamten Gasturbmenschaufel 1 emstuckig mit dem Profil 2 verbunden. Die Heißgasplattform 9 weist weiterhin einen äußeren Rand 15 auf, der ungefähr rechteckig ist. Die Heißgasplattform 9 ist in Richtung der Schaufelachse 9 gekrümmt. Durch diese Form der Heißgasplattform 9 ergibt sich für eine Vielzahl von ähnlich aufgebauten Turbinenschaufeln bei Einbau in eine Turbine em sich m Stromungsrichtung er- 6 weiternder Stromungskanal . Die Lastplattform 11 weist einen inneren Rand 17 auf, welcher ebenfalls durch das Profil 2 begrenzt und gleichzeitig der Rand einer Öffnung des sich durch die Turbmenschaufel 1 erstreckenden Hohlraumes 8 ist. Die Lastplattform 11 weist ebenfalls einen ungefähr rechteckigen äußeren Rand 19 auf und weist ungefähr die gleiche Krümmung auf, wie die Heißgasplattform 9. D e Heißgasplattform 9 weist eine Dicke Dl und die Lastplattform eine Dicke D2 auf. Diese Dicken Dl, D2 können gegebenenfalls auch innerhalb der jewei- ligen Plattform variieren, in welchem Falle mit den DickenFIG. 1 shows a section of a cast gas turbine blade 1 directed along a blade axis 3 and having a profile 2. The profile 2 partially forms an airfoil 5. The blade area 5, which is only partially shown, is followed by a platform region 7 along the blade axis 3. The profile 2 extends through the platform area 7. In the interior of the profile 2, the gas turbine blade 1 has a cavity 8 which extends continuously along the blade axis 3. A stabilizing wall 6 extends along the blade axis 3 through the cavity 8 of the turbine blade 1. Transversely to the blade axis 3, a hot gas platform 9 belonging to the platform area 7 adjoins the blade blade 5. A load platform 11 lies opposite the hot gas platform 9. The hot gas platform 9 has an inner edge 13, via which it is connected to the profile 2. The platform area 7 is integrally connected to the profile 2 by casting the entire gas turbine blade 1. The hot gas platform 9 also has an outer edge 15 which is approximately rectangular. The hot gas platform 9 is curved in the direction of the blade axis 9. This shape of the hot gas platform 9 results in a large number of similarly constructed turbine blades when installed in a turbine in the direction of flow. 6 further flow channel. The load platform 11 has an inner edge 17, which is likewise delimited by the profile 2 and at the same time is the edge of an opening of the cavity 8 extending through the turbine blade 1. The load platform 11 also has an approximately rectangular outer edge 19 and has approximately the same curvature as the hot gas platform 9. The hot gas platform 9 has a thickness D1 and the load platform has a thickness D2. These thicknesses D1, D2 can optionally also vary within the respective platform, in which case with the thicknesses
Dl, D2 mittlere Dicken gemeint sind. Die Lastplattform 11 und die Heißgasplattform 9 sind über ihren jeweiligen inneren Rand 13, 17 und das Profil 2 miteinander verbunden. Weiterhin sind die Heißgasplattform 9 und die Lastplattform 11 durch em Verbmdungselement 29 verbunden. Dieses weist einen imDl, D2 mean thicknesses are meant. The load platform 11 and the hot gas platform 9 are connected to one another via their respective inner edges 13, 17 and the profile 2. Furthermore, the hot gas platform 9 and the load platform 11 are connected by em connecting element 29. This shows one in
Bereich der äußeren Rander 15 und 19 angeordneten ersten Teil 29A auf. Weiterhin weist es einen dem ersten Teil 29A gegenüberliegenden, ebenfalls im Bereich der äußeren Rander 15, 19 liegenden zweiten Teil 29B auf. Das Verbmdungselement 29 grenzt von der Heißgasplattform 9 zwei sich gegenüberliegende Haltesockel 21 und 23 ab. Ebenso wird von der Lastplattform 11 em Haltesockel 25 abgegrenzt. Dem Haltesockel 25 gegenüber weist die Lastplattform 11 noch einen treppenartigen Haltesockel 27 auf. Mit Hilfe dieser Haltesockel 21, 23, 25, 27 wird die Turbmenschaufel 1 n einer nicht dargestellten Gasturbine gehaltert. Dabei wird durch die Heißgasseite 10 (siehe Figur 2) der Heißgasplattform 9 em Stromungsweg durch die Gasturbine teilweise begrenzt. Em die Gasturbine durchströmendes, heißes Arbeitsfluid umströmt das Schaufelblatt 5. Daraus resultieren hohe Kräfte auf das Schaufelblatt 5, welche über den Plattformbereich 7 an das nicht dargestellte Gasturbinengehause übertragen werden. Der wesentliche Teil dieser Belastung wird dabei durch die Lastplattform 11 aufgenommen. Dadurch kann die Heißgasplattform 9 dunner ausgeführt werden als die Lastplattform 11, d.h. die Dicke Dl der Heiß- gasplattform 9 ist geringer als die Dicke D2 der Lastplattform 11. Dadurch treten nur vergleichsweise geringe thermische Spannungen in der Heißgasplattform 9 auf. Die der Heißgasseite 10 abgewandte Seite 12 (siehe Figur 2) der Heiß- gasplattform 9 ist durch eine Kuhlluftzufuhr kuhlbar. Dafür wird durch Durchbohrungen 31 der Lastplattform 11 - es ist beispielhaft nur eine Durchbohrung 31 gezeigt - Kuhlluft durch die Lastplattform 11 geleitet. Fuhrungselemente 33 fuh¬ ren die so durchgeleitete Kuhlluft weiter auf die Heiß- gasplattform 9. Dadurch ergibt sich eine effiziente Prallkuh- lung der Heißgasplattform 9.Area of the outer edges 15 and 19 arranged first part 29A. Furthermore, it has a second part 29B opposite the first part 29A and likewise lying in the region of the outer edges 15, 19. The connecting element 29 delimits from the hot gas platform 9 two opposing holding bases 21 and 23. Likewise, a holding base 25 is delimited from the load platform 11. The load platform 11 also has a stair-like holding base 27 opposite the holding base 25. With the help of these holding bases 21, 23, 25, 27, the turbine blade 1 n of a gas turbine, not shown, is held. The hot gas platform 9 (see FIG. 2) of the hot gas platform 9 partially limits the flow path through the gas turbine. A hot working fluid flowing through the gas turbine flows around the airfoil 5. This results in high forces on the airfoil 5, which are transmitted via the platform region 7 to the gas turbine housing (not shown). The major part of this load is absorbed by the load platform 11. As a result, the hot gas platform 9 can be made thinner than the load platform 11, ie the thickness D1 of the hot gas platform 9 is less than the thickness D2 of the load platform 11. As a result, only comparatively low thermal stresses occur in the hot gas platform 9. The side 12 of the hot gas platform 9 facing away from the hot gas side 10 (see FIG. 2) can be cooled by a cooling air supply. For this purpose, cooling air is passed through the load platform 11 through perforations 31 in the load platform 11 - only one through hole 31 is shown as an example. Fuhrungselemente 33 fuh ¬ ren so by Kuhlluft led further to the hot gas platform 9. This results in an efficient Prallkuh- development of hot gas platform. 9
Figur 2 zeigt einen Längsschnitt durch die Gasturbmenscha IUi- fei 1 aus Figur 1. Dabei ist die durch den Hohlraum 8 der Turbmenschaufel 1 fuhrende Versteifungswand 6 sichtbar. I [ni Figur 2 wird deutlich, daß die Heißgasplattform 9 und die Lastplattform 11 weitgehend unabhängig voneinander sind. Damit w rd eine Funktionstrennung für die Plattformen 9, 11 erreicht. Die Heißgasplattform 9 übernimmt die Kanalisierung des heißen Arbeitsfluides und braucht nur einen allenfalls geringen Teil der Kräfte abzufangen, die durch das Arbeits- fluid auf das Schaufelblatt 5 ausgeübt werden. Damit kann die Heißgasplattform 9 dünn ausgeführt werden. Dies ergibt den großen Vorteil, daß nur geringe thermische Spannungen in der Heißgasplattform 9 auftreten. Die Lastplattform 11 ist dicker ausgeführt, da sie den Großteil der Kräfte aufnimmt. Sie ist aber durch die Heißgasplattform 9 vor dem heißen Arbeitsfluid geschützt, wodurch auch in der Lastplattform 11 kaum thermische Spannungen auftreten. FIG. 2 shows a longitudinal section through the gas turbine blade 1 of FIG. 1. The stiffening wall 6 leading through the cavity 8 of the turbine blade 1 is visible. I [ni Figure 2 it is clear that the hot gas platform 9 and the load platform 11 are largely independent of each other. This would result in a separation of functions for the platforms 9, 11. The hot gas platform 9 takes over the channeling of the hot working fluid and only needs to absorb a small part of the forces that are exerted on the airfoil 5 by the working fluid. The hot gas platform 9 can thus be made thin. This gives the great advantage that only low thermal stresses occur in the hot gas platform 9. The load platform 11 is made thicker because it absorbs the majority of the forces. However, it is protected from the hot working fluid by the hot gas platform 9, as a result of which thermal stresses hardly occur in the load platform 11 either.

Claims

Patentansprüche claims
1. Entlang einer Schaufelachse (3) gerichtete, gegossene Turbinenschaufel (1) mit entlang der Schaufelachse (3) aufeinan- derfolgend einem Schaufelblatt (5) und einem Plattformbereich (7), d a d u r c h g e k e n n z e i c h n e t, daß der Plattformbereich (7) eine sich quer zur Schaufelachse (3) erstrek- kende, an das Schaufelblatt (5) grenzende Heißgasplattform (9) und eine der Heißgasplattform (9) gegenüberliegende1. A turbine blade (1) directed along a blade axis (3) and having a blade leaf (5) and a platform area (7) in succession along the blade axis (3), characterized in that the platform area (7) is transverse to the blade axis (3) extending hot gas platform (9) bordering the airfoil (5) and one opposite the hot gas platform (9)
Lastplattform (11) umfaßt, wobei die Lastplattform (11) für eine Aufnahme von Kräften ausgelegt ist, die durch ein um das Schaufelblatt (5) strömendes Arbeitsfluid hervorrufbar sind.Load platform (11), the load platform (11) being designed to absorb forces which can be caused by a working fluid flowing around the airfoil (5).
2. Turbinenschaufel (1) 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 die Heißgasplattform (9) dünner ist, als die Lastplattform (11).2. turbine blade (1) 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 the hot gas platform (9) is thinner than the load platform (11).
3. Turbinenschaufel (1) nach Anspruch 1 oder 2, d a d u r c h g e k e n n z e i c h n e t, daß das Schaufelblatt (5) Teil eines sich durch den Plattformbereich (7) erstreckenden Profiles (2) ist, wobei die Heißgasplattform (9) und die Lastplattform (11) jeweils einen inneren Rand (13, 17) aufweisen, über den sie mit dem Profil (2) verbunden sind.3. Turbine blade (1) according to claim 1 or 2, characterized in that the blade (5) is part of a profile (2) extending through the platform area (7), the hot gas platform (9) and the load platform (11) each one have inner edge (13, 17), via which they are connected to the profile (2).
4. Turbinenschaufel (1) nach Anspruch 1,2 oder 3, d a d u r c h g e k e n n z e i c h n e t, daß die Heißgasplattform (9) und die Lastplattform (11) jeweils einen äu- ßeren Rand (15, 19) aufweisen an dem sie miteinander verbunden sind.4. Turbine blade (1) according to claim 1, 2 or 3, so that the hot gas platform (9) and the load platform (11) each have an outer edge (15, 19) at which they are connected to one another.
5. Turbinenschaufel (1) nach Anspruch 3, d a d u r c h g e k e n n z e i c h n e t, daß die Heiß- gasplattform (9) und die Lastplattform (11) nur über ihren jeweiligen inneren Rand (13, 15) und durch ihren jeweiligen äußeren Rand (15, 19) miteinander verbunden sind. 5. turbine blade (1) according to claim 3, characterized in that the hot gas platform (9) and the load platform (11) only via their respective inner edge (13, 15) and through their respective outer edge (15, 19) connected to each other are.
6. Turbinenschaufel (1) nach einem der vorhergehenden Ansprüche, d a d u r c h g e k e n n z e i c h n e t, daß zwischen der Heißgasplattform (9) und der Lastplattform (11) Fuhrungselemente (33) zur Führung eines Kühlmediums zur Heißgasplattform (9) angeordnet sind.6. Turbine blade (1) according to one of the preceding claims, d a d u r c h g e k e n n z e i c h n e t that between the hot gas platform (9) and the load platform (11) guide elements (33) for guiding a cooling medium to the hot gas platform (9) are arranged.
7. Turbinenschaufel (1) nach Anspruch 6, d a d u r c h g e k e n n z e i c h n e t, daß die Führungselemente (33) als Wände mit einer Wandstärke (D3) ausgebildet sind, welche Wandstärke (D3) dünn ist gegenüber der Dicke (Dl) der Heißgasplattform (9) .7. turbine blade (1) according to claim 6, d a d u r c h g e k e n n z e i c h n e t that the guide elements (33) are formed as walls with a wall thickness (D3), which wall thickness (D3) is thin compared to the thickness (Dl) of the hot gas platform (9).
8. Turbinenschaufel (1) nach einem der vorhergehenden Ansprüche, d a d u r c h g e k e n n z e i c h n e t, daß die Lastplattform (11) eine Vielzahl von auf die Heißgasplattform (9) gerichteten Durchbohrungen (31) aufweist.8. turbine blade (1) according to one of the preceding claims, d a d u r c h g e k e n n z e i c h n e t that the load platform (11) has a plurality of on the hot gas platform (9) directed holes (31).
9. Turbinenschaufel (1) nach einem der vorhergehenden Ansprüche, die als eine Leitschaufel (1) ausgebildet ist, insbesondere für eine stationäre Gasturbine. 9. Turbine blade (1) according to one of the preceding claims, which is designed as a guide blade (1), in particular for a stationary gas turbine.
EP99937814A 1998-04-21 1999-04-14 Turbine blade Expired - Lifetime EP1073827B1 (en)

Applications Claiming Priority (3)

Application Number Priority Date Filing Date Title
DE19817820 1998-04-21
DE19817820 1998-04-21
PCT/DE1999/001109 WO1999054597A1 (en) 1998-04-21 1999-04-14 Turbine blade

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EP1073827A1 true EP1073827A1 (en) 2001-02-07
EP1073827B1 EP1073827B1 (en) 2003-10-08

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JP (1) JP2002512334A (en)
DE (1) DE59907300D1 (en)
WO (1) WO1999054597A1 (en)

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US6533544B1 (en) 2003-03-18
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DE59907300D1 (en) 2003-11-13
JP2002512334A (en) 2002-04-23

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