EP1073827B1 - Turbine blade - Google Patents
Turbine blade Download PDFInfo
- Publication number
- EP1073827B1 EP1073827B1 EP99937814A EP99937814A EP1073827B1 EP 1073827 B1 EP1073827 B1 EP 1073827B1 EP 99937814 A EP99937814 A EP 99937814A EP 99937814 A EP99937814 A EP 99937814A EP 1073827 B1 EP1073827 B1 EP 1073827B1
- Authority
- EP
- European Patent Office
- Prior art keywords
- platform
- hot gas
- load
- turbine
- blading unit
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Expired - Lifetime
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Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/12—Blades
- F01D5/14—Form or construction
- F01D5/147—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
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2240/00—Components
- F05D2240/80—Platforms for stationary or moving blades
Definitions
- the invention relates to a cast turbine blade an airfoil and a platform area.
- DE 26 28 807 A1 describes an impact cooling system for one Gas turbine blade.
- the gas turbine blade is along directed a blade axis and points along the Bucket axis an airfoil and a platform area on.
- In the platform area extends transversely to the blade axis a platform radially outward from the airfoil.
- a such platform forms part of a flow channel for a working fluid that flows through a gas turbine into the the turbine blade is installed. Step on a gas turbine very high temperatures in this flow channel. Thereby becomes the surface of the platform exposed to the hot gas heavily thermally stressed.
- To cool the platform is a perforated in front of the side of the platform facing away from the hot gas Wall element arranged. About the holes in the wall element cooling air enters and impinges on the hot gas Side of the platform. This will make it efficient Impact cooling reached.
- GB-PS 1 289 435 relates to guide elements for gas flows, especially gas turbine blades. There is a on a casting Laminar guide element arranged that by perspiration cooling can be cooled. This setup is for cast turbine blades not applicable.
- DE 26 43 049 A1 describes a cooling arrangement for cooling the platform of a turbine blade. Comparable to the arrangement in the above DE 26 28 807 A1 is before the side of the platform facing away from the hot gas side Plate with openings arranged through the cooling air against the Platform flows.
- the object of the invention is to provide a thermally highly resilient, to specify cast turbine blade, at which only small thermal stresses occur in the platform area.
- this object is achieved by a along Cast turbine blade directed towards a blade axis with one blade in succession along the blade axis and a platform area, the platform area a extending transversely to the blade axis to the Airfoil bordering hot gas platform and one of the hot gas platform opposite load platform, wherein the load platform is designed to absorb forces is caused by a working fluid flowing around the airfoil can be caused.
- a turbine blade is placed over the platform area in the Turbine, in particular attached to the turbine housing.
- the platform must absorb loads due to the airfoil attacking forces are caused.
- Such powers are called by the pressure of the flowing through the turbine Working fluids, e.g. a hot gas or steam.
- the inclusion of these loads requires that the platform has a minimum thickness to the forces without deformation to the To pass the turbine housing.
- the Platform as stated above, from a hot gas flow channel.
- the platform area is as a double platform made of two opposite one another Platforms trained. This ensures that the hot gas platform, which limits the flow channel and the exposed to hot gas that can be run.
- the hot gas platform is in the essential for the limitation of the flow channel and thus responsible for channeling the hot gas.
- the opposite one, unaffected by the hot gas Load platform takes over the through the on the airfoil attacking forces caused loads.
- This separation of functions allows the hot gas platform to be so thin to ensure that the hot gas ducting is guaranteed, without having to intercept essential forces. Because of that won thin version of the hot gas platform results in particular the advantage of being in the hot gas platform form comparatively low thermal stresses.
- the execution of the platform area is a double platform advantageous because at the transition points between the ribs and the platform can also handle high thermal stresses occur.
- the hot gas platform is preferably substantially thinner than the load platform. Since the hot gas platform only one at most comparatively small part of the loads occurring it must be thinner than the load platform. The load platform catches the bulk of the occurring Forces.
- the airfoil is part of a through the platform area extending profile
- the hot gas platform and the load platform preferably each has an inner edge to which they are connected to the profile. Farther they each have an outer edge over which they join together are connected.
- the hot gas platform is further preferred and the load platform only over their respective. inner edge and through their respective outer edge with each other connected. This results in a small connection area between the hot gas platform and the load platform. This small connection area and the connection over the respective outer edge result in a high mechanical stability of the double platform version only low thermal stresses. Thermal expansions are relative due to the small number of connection points freely possible.
- Such guide elements can z. B. Be sheets that cover the space between the platforms divide like a chamber or z. B. also vertically between the Platform-facing channels.
- a cooling medium especially cooling air, efficiently steered against the side of the hot gas platform facing away from the hot gas become. In particular, this can be an efficient Impact cooling are made possible.
- the guide elements are preferably of a wall thickness trained, which is thin compared to the hot gas platform. Due to the thin design of the guide elements, none significant additional thermal stresses caused.
- the load platform preferably has a plurality of the hot gas platform through holes.
- a cooling medium especially cooling air from a compressor a gas turbine, through the load platform and flow against the hot gas platform, making it efficient cool.
- the turbine blade is preferred as a gas turbine blade trained, especially for a stationary gas turbine.
- Figure 1 shows a section of a along a blade axis 3 directed, cast gas turbine blade 1 with a profile 2.
- the profile 2 partially forms an airfoil 5.
- a platform area closes along the blade axis 3 7 on.
- Profile 2 extends through the platform area 7 through.
- the gas turbine blade 1 has inside the profile 2 along the blade axis 3 continuously extending cavity 8.
- a stabilizing wall 6 extends along the blade axis 3 the cavity 8 of the turbine blade 1.
- Transversely to the blade axis 3 connects to the airfoil 5 to the platform area 7 belonging hot gas platform 9.
- the hot gas platform 9 opposite is a load platform 11.
- the hot gas platform 9 has an inner edge 13, over which it with the Profile 2 is connected.
- the platform area 7 is through Cast the entire gas turbine blade 1 in one piece with the Profile 2 connected.
- the hot gas platform 9 continues to point 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 for a large number of similarly constructed turbine blades when installed in a turbine, it widens in the direction of flow Flow channel.
- the load platform 11 has one inner edge 17, which is also limited by the profile 2 and at the same time the edge of an opening of itself is the turbine blade 1 extending cavity 8.
- the Load platform 11 also has an approximately rectangular shape outer edge 19 and has approximately the same curvature on how the hot gas platform 9.
- the hot gas platform 9 has a thickness D1 and the load platform a thickness D2.
- This Thicknesses D1, D2 can optionally also be within the respective Platform vary, in which case with the thicknesses D1, D2 mean thicknesses are meant.
- the load platform 11 and the hot gas platform 9 are above their respective inner ones Edge 13, 17 and the profile 2 connected to each other. Farther are the hot gas platform 9 and the load platform 11 through a connecting element 29 connected. This shows one in Area of the outer edges 15 and 19 arranged first part 29A on. Furthermore, it has an opposite, the first part 29A, also in the area of the outer edges 15, 19 lying second part 29B.
- the connecting element 29 borders from the hot gas platform 9 two opposite one another Holding base 21 and 23 off. Likewise, from the load platform 11 delimited a holding base 25.
- the holding base 25 opposite the load platform 11 still has a step-like Holding base 27 on.
- the hot gas side 10 (see Figure 2) of the hot gas platform 9 through a flow path the gas turbine partially limited. A flowing through the gas turbine Hot working fluid flows around the airfoil 5. This results in high forces on the airfoil 5, which via the platform area 7 to the not shown Gas turbine casing can be transferred. The essential part this load is absorbed by the load platform 11. As a result, the hot gas platform 9 can be made thinner are called the load platform 13, i.e. the thickness D1 of the hot gas platform 9 is less than the thickness D2 of the load platform 11.
- the hot gas side 10 opposite side 12 (see Figure 2) of the hot gas platform 9 can be cooled by a cooling air supply. Therefore is through holes 31 of the load platform 11 - it is only one through bore 31 shown by way of example - cooling air passed through the load platform 11. Guide elements 33 guide the cooling air thus passed on to the hot gas platform 9. This results in efficient prail cooling the hot gas platform 9.
- FIG 2 shows a longitudinal section through the gas turbine blade 1 from Figure 1.
- the cavity 8 is the Turbine blade 1 leading stiffening wall 6 visible.
- the hot gas platform 9 and Load platform 11 are largely independent of each other.
- the hot gas platform 9 takes over the sewerage of the hot working fluid and only needs one at most intercept small part of the forces caused by the working fluid be exerted on the airfoil 5. So that Hot gas platform 9 can be made thin. This gives the great advantage that only low thermal stresses in the Hot gas platform 9 occur.
- the load platform 11 is thicker carried out since it absorbs most of the forces. she is but through the hot gas platform 9 before the hot working fluid protected, so that hardly any thermal in the load platform 11 Tensions occur.
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Architecture (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Description
Die Erfindung betrifft eine gegossene Turbinenschaufel mit einem Schaufelblatt und einem Plattformbereich.The invention relates to a cast turbine blade an airfoil and a platform area.
Aus der DE 26 28 807 A1 geht ein Prallkühlsystem für eine Gasturbinenschaufel hervor. Die Gasturbinenschaufel ist entlang einer Schaufelachse gerichtet und weist entlang der 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 Strömungskanales für ein Arbeitsfluid, welches eine Gasturbine durchströmt, in die die Turbinenschaufel eingebaut ist. Bei einer Gasturbine treten in diesem Strömungskanal sehr hohe Temperaturen auf. Dadurch wird die dem Heißgas ausgesetzte Oberfläche der Plattform stark thermisch belastet. Zur Kühlung der Plattform ist vor der dem Heißgas abgewandten Seite der Plattform ein gelochtes Wandelement angeordnet. Über die Löcher in dem Wandelement tritt Kühlluft ein und trifft auf die dem Heißgas abgewandte Seite der Plattform. Damit wird eine effiziente Prallkühlung erreicht.DE 26 28 807 A1 describes an impact cooling system for one Gas turbine blade. The gas turbine blade is along directed a blade axis and points along the Bucket axis an airfoil and a platform area on. In the platform area extends transversely to the blade axis a platform radially outward from the airfoil. A such platform forms part of a flow channel for a working fluid that flows through a gas turbine into the the turbine blade is installed. Step on a gas turbine very high temperatures in this flow channel. Thereby becomes the surface of the platform exposed to the hot gas heavily thermally stressed. To cool the platform is a perforated in front of the side of the platform facing away from the hot gas Wall element arranged. About the holes in the wall element cooling air enters and impinges on the hot gas Side of the platform. This will make it efficient Impact cooling reached.
Die GB-PS 1 289 435 betrifft Führungselemente für Gasströme,
insbesondere Gasturbinenschaufeln. Auf einem Gußteil ist ein
laminar aufgebautes Führungselement angeordnet, daß durch
eine Transpirationskühlung kühlbar ist. Dieser Aufbau ist für
gegossene Turbinenschaufeln nicht anwendbar.GB-
Aus der DE 26 43 049 A1 geht eine Kühlanordnung zur Kühlung der Plattform einer Turbinenschaufel hervor. Vergleichbar mit der Anordnung in der obengenannten DE 26 28 807 A1 ist vor der der Heißgasseite abgewandten Seite der Plattform eine Platte mit Öffnungen angeordnet, durch die Kühlluft gegen die Plattform strömt.DE 26 43 049 A1 describes a cooling arrangement for cooling the platform of a turbine blade. Comparable to the arrangement in the above DE 26 28 807 A1 is before the side of the platform facing away from the hot gas side Plate with openings arranged through the cooling air against the Platform flows.
Aufgabe der Erfindung ist es, eine thermisch hoch belastbare, gegossene Turbinenschaufel anzugeben, bei der nur geringe thermische Spannungen im Plattformbereich auftreten. Erfindungsgemäß wird diese Aufgabe gelöst durch eine entlang einer Schaufelachse gerichtete, gegossene Turbinenschaufel mit entlang der Schaufelachse aufeinanderfolgend einem Schaufelblatt und einem Plattformbereich, wobei der Plattformbereich eine sich quer zur Schaufelachse erstreckende, an das Schaufelblatt grenzende Heißgasplattform und eine der Heißgasplattform gegenüberliegende Lastplattform umfaßt, wobei die Lastplattform für eine Aufnahme von Kräften ausgelegt ist, die durch ein um das Schaufelblatt strömendes Arbeitsfluid hervorrufbar sind.The object of the invention is to provide a thermally highly resilient, to specify cast turbine blade, at which only small thermal stresses occur in the platform area. According to the invention, this object is achieved by a along Cast turbine blade directed towards a blade axis with one blade in succession along the blade axis and a platform area, the platform area a extending transversely to the blade axis to the Airfoil bordering hot gas platform and one of the hot gas platform opposite load platform, wherein the load platform is designed to absorb forces is caused by a working fluid flowing around the airfoil can be caused.
Eine Turbinenschaufel wird über den Plattformbereich in der Turbine, insbesondere am Turbinengehäuse, 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 Turbinengehäuse durchzuleiten. Gleichzeitig begrenzt die Plattform, wie oben ausgeführt, den von einem heißen Gas durchströmten Strömungskanal. Mit der Erfindung wird ein neuer Weg in der Konstruktion des Plattformbereiches gegossener Turbinenschaufeln beschritten: Der Plattformbereich ist als Doppelplattform aus zwei einander gegenüberliegenden Plattformen ausgebildet. Dadurch wird erreicht, daß die Heißgasplattform, welche den Strömungskanal begrenzt und dem heißen Gas ausgesetzt ist, dunn ausgeführt werden kann. Mit der Ausführung in zwei Plattformen ergibt sich eine Funktionstrennung für die Plattformen. Die Heißgasplattform ist im wesentlichen für die Begrenzung des Strömungskanales 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 auszuführen, daß die Heißgaskanalisierung gewährleistet ist, ohne aber wesentliche Kräfte abfangen zu müssen. Durch die so gewonnene dünne Ausführung der Heißgasplattform ergibt sich insbesondere der Vorteil, daß sich in der Heißgasplattform vergleichsweise geringe thermische Spannungen ausbilden. Auch gegenüber Ausführungen, bei denen eine einstückige Plattform durch Rippen an der heißgasabgewandten Seite versteift ist, ist die Ausführung 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 placed over the platform area in the Turbine, in particular attached to the turbine housing. Thereby the platform must absorb loads due to the airfoil attacking forces are caused. Such powers are called by the pressure of the flowing through the turbine Working fluids, e.g. a hot gas or steam. The inclusion of these loads requires that the platform has a minimum thickness to the forces without deformation to the To pass the turbine housing. At the same time, the Platform, as stated above, from a hot gas flow channel. With the invention new way in the construction of the platform area cast Turbine blades trod: the platform area is as a double platform made of two opposite one another Platforms trained. This ensures that the hot gas platform, which limits the flow channel and the exposed to hot gas that can be run. With The execution in two platforms results in a separation of functions for the platforms. The hot gas platform is in the essential for the limitation of the flow channel and thus responsible for channeling the hot gas. The opposite one, unaffected by the hot gas Load platform takes over the through the on the airfoil attacking forces caused loads. This separation of functions allows the hot gas platform to be so thin to ensure that the hot gas ducting is guaranteed, without having to intercept essential forces. Because of that won thin version of the hot gas platform results in particular the advantage of being in the hot gas platform form comparatively low thermal stresses. Also versus designs where a one piece platform is stiffened by ribs on the side away from the hot gas, is the execution of the platform area as a double platform advantageous because at the transition points between the ribs and the platform can also handle high thermal stresses occur.
Vorzugsweise ist die Heißgasplattform wesentlich dünner als die Lastplattform. Da die Heißgasplattform allenfalls nur einen vergleichsweise geringen Teil der auftretenden Lasten aufnehmen muß, ist sie dünner ausführbar, als die Lastplattform. Die Lastplattform fängt den Hauptteil der auftretenden Kräfte ab.The hot gas platform is preferably substantially thinner than the load platform. Since the hot gas platform only one at most comparatively small part of the loads occurring it must be thinner than the load platform. The load platform catches the bulk of the occurring Forces.
Das Schaufelblatt ist Teil eines sich durch den Plattformbereich erstreckenden Profiles, wobei die Heißgasplattform und die Lastplattform vorzugsweise jeweils einen inneren Rand 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 Heißgasplattform und die Lastplattform nur über ihren jeweiliger. inneren Rand und durch ihren jeweiligen äußeren Rand miteinander verbunden. Damit ergibt sich eine geringe Verbindungsfläche zwischen der Heißgasplattform und der Lastplattform. Durch diese geringe Verbindungsfläche und durch die Verbindung über den jeweiligen äußeren Rand ergeben sich bei einer hohen mechanischen Stabilität der Doppelplattformausführung nur geringe thermische Spannungen. Thermische Ausdehnungen sind durch die geringe Anzahl an Verbindungsstellen relativ frei möglich.The airfoil is part of a through the platform area extending profile, the hot gas platform and the load platform preferably each has an inner edge to which they are connected to the profile. Farther they each have an outer edge over which they join together are connected. The hot gas platform is further preferred and the load platform only over their respective. inner edge and through their respective outer edge with each other connected. This results in a small connection area between the hot gas platform and the load platform. This small connection area and the connection over the respective outer edge result in a high mechanical stability of the double platform version only low thermal stresses. Thermal expansions are relative due to the small number of connection points freely possible.
Bevorzugt sind zwischen der Heißgasplattform und der Lastplattform Führungselemente zur Führung eines Kühlmediums zur Heißgasplattform angeordnet. Solche Führungselemente 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 Führungselemente kann ein Kühlmedium, insbesondere Kühlluft, effizienterweise gegen die heißgasabgewandte Seite der Heißgasplattform gelenkt werden. Insbesondere kann hierdurch eine effiziente Prallkühlung ermöglicht werden.Are preferred between the hot gas platform and the Load platform guide elements for guiding a cooling medium arranged to the hot gas platform. Such guide elements can z. B. Be sheets that cover the space between the platforms divide like a chamber or z. B. also vertically between the Platform-facing channels. Through such leadership elements can use a cooling medium, especially cooling air, efficiently steered against the side of the hot gas platform facing away from the hot gas become. In particular, this can be an efficient Impact cooling are made possible.
Vorzugsweise sind die Führungselemente mit einer Wandstärke ausgebildet, die dünn ist gegenüber der Heißgasplattform. Durch die dünne Ausführung der Führungselemente werden keine wesentlichen, zusätzlichen thermischen Spannungen verursacht.The guide elements are preferably of a wall thickness trained, which is thin compared to the hot gas platform. Due to the thin design of the guide elements, none significant additional thermal stresses caused.
Vorzugsweise weist die Lastplattform eine Vielzahl von auf die Heißgasplattform gerichteten Durchbohrungen auf. Damit kann ein Kühlmedium, insbesondere Kühlluft 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 plurality of the hot gas platform through holes. In order to can be a cooling medium, especially cooling air from a compressor a gas turbine, through the load platform and flow against the hot gas platform, making it efficient cool.
Bevorzugt ist die Turbinenschaufel als eine Gasturbinenschaufel ausgebildet, insbesondere für eine stationäre Gasturbine. The turbine blade is preferred as a gas turbine blade trained, especially for a stationary gas turbine.
Die Erfindung wird anhand der Zeichnung näher erläutert. Es zeigt:
Figur 1- eine perspektivische Darstellung eines Teils einer Gasturbinenschaufel, und
Figur 2- einen Längsschnitt durch die Gasturbinenschaufel
aus
Figur 1.
- Figure 1
- a perspective view of part of a gas turbine blade, and
- Figure 2
- 2 shows a longitudinal section through the gas turbine blade from FIG. 1.
Gleiche Bezugszeichen haben in den einzelnen Figuren die gleiche Bedeutung.The same reference numerals have in the individual figures same meaning.
Figur 1 zeigt einen Ausschnitt einer entlang einer Schaufelachse
3 gerichteten, gegossenen Gasturbinenschaufel 1 mit
einem Profil 2. Das Profil 2 bildet teilweise ein Schaufelblatt
5. An das nur teilweise dargestellte Schaufelblatt 5
schließt sich entlang der Schaufelachse 3 ein Plattformbereich
7 an. Das Profil 2 erstreckt sich durch den Plattformbereich
7 hindurch. Die Gasturbinenschaufel 1 weist im Inneren
des Profils 2 einen sich entlang der Schaufelachse 3
durchgängig erstreckenden Hohlraum 8 auf. Eine Stabilisierungswand
6 erstreckt sich entlang der Schaufelachse 3 durch
den Hohlraum 8 der Turbinenschaufel 1. Quer zur Schaufelachse
3 schließt sich an das Schaufelblatt 5 eine zum Plattformbereich
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 Gasturbinenschaufel 1 einstückig 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 ein sich in Stromungsrichtung erweiternder
Strömungskanal. 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 Turbinenschaufel 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. Die Heißgasplattform 9 weist
eine Dicke D1 und die Lastplattform eine Dicke D2 auf. Diese
Dicken D1, D2 können gegebenenfalls auch innerhalb der jeweiligen
Plattform variieren, in welchem Falle mit den Dicken
D1, 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
ein Verbindungselement 29 verbunden. Dieses weist einen im
Bereich der äußeren Ränder 15 und 19 angeordneten ersten Teil
29A auf. Weiterhin weist es einen dem ersten Teil 29A gegenüberliegenden,
ebenfalls im Bereich der äußeren Ränder 15, 19
liegenden zweiten Teil 29B auf. Das Verbindungselement 29
grenzt von der Heißgasplattform 9 zwei sich gegenüberliegende
Haltesockel 21 und 23 ab. Ebenso wird von der Lastplattform
11 ein 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 Turbinenschaufel 1 in einer nicht dargestellten
Gasturbine gehaltert. Dabei wird durch die Heißgasseite 10
(siehe Figur 2) der Heißgasplattform 9 ein Strömungsweg durch
die Gasturbine teilweise begrenzt. Ein 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
Gasturbinengehäuse übertragen werden. Der wesentliche Teil
dieser Belastung wird dabei durch die Lastplattform 11 aufgenommen.
Dadurch kann die Heißgasplattrorm 9 dünner ausgeführt
werden als die Lastplattform 13, d.h. die Dicke D1 der Heißgasplattform
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 Heißgasplattform
9 ist durch eine Kühlluftzufuhr kühlbar. Dafür
wird durch Durchbohrungen 31 der Lastplattform 11 - es ist
beispielhaft nur eine Durchbohrung 31 gezeigt - Kühlluft
durch die Lastplattform 11 geleitet. Führungselemente 33 führen
die so durchgeleitete Kühlluft weiter auf die Heißgasplattform
9. Dadurch ergibt sich eine effiziente Prailkühlung
der Heißgasplattform 9.Figure 1 shows a section of a along a blade axis
3 directed, cast
Figur 2 zeigt einen Längsschnitt durch die Gasturbinenschaufel
1 aus Figur 1. Dabei ist die durch den Hohlraum 8 der
Turbinenschaufel 1 führende Versteifungswand 6 sichtbar. In
Figur 2 wird deutlich, daß die Heißgasplattform 9 und die
Lastplattform 11 weitgehend unabhängig voneinander sind. Damit
wird 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 Arbeitsfluid
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.Figure 2 shows a longitudinal section through the
Claims (9)
- Cast turbine blading unit (1) directed along a blading unit axis (3), having an aerofoil (5) and a platform region (7) in sequence along the blading unit axis (3), which platform region (7) comprises a hot gas platform (9) extending transverse to the blading unit axis (3) and bounding the aerofoil (5), characterized in that the platform region (7) comprises a load-carrying platform (11) opposite to the hot gas platform (9), the load-carrying platform (11) being designed to accept forces which may be caused by a working fluid flowing around the aerofoil (5).
- Turbine blading unit (1) according to Claim 1, characterized in that the hot gas platform (9) is thinner than the load-carrying platform (11).
- Turbine blading unit (1) according to Claim 1 or 2, characterized in that the aerofoil (5) is part of a profile section (2) extending through the platform region (7), the hot gas platform (9) and the load-carrying platform (11) each having an inner edge (13, 17) by means of which they are connected to the profile section (2).
- Turbine blading unit (1) according to Claim 1, 2 or 3, characterized in that the hot gas platform (9) and the load-carrying platform (11) each have an outer edge (15, 19) at which they are connected to one another.
- Turbine blading unit (1) according to Claim 3, characterized in that the hot gas platform (9) and the load-carrying platform (11) are only connected to one another by means of their respective inner edges (13, 15) and by their respective outer edges (15, 19).
- Turbine blading unit (1) according to one of the preceding claims, characterized in that guide elements (33) for guiding a cooling medium to the hot gas platform (9) are arranged between the hot gas platform (9) and the load-carrying platform (11).
- Turbine blading unit (1) according to claim 6, characterized in that the guide elements (33) are configured as walls with a wall thickness (D3), which wall thickness (D3) is thin relative to the thickness (D1) of the hot gas platform (9).
- Turbine blading unit (1) according to one of the preceding claims, characterized in that the load-carrying platform (11) has a plurality of through holes (31) directed towards the hot gas platform (9).
- Turbine blading unit (1) according to one of the preceding claims, which turbine blading unit is configured as a guide vane (1), in particular for a stationary gas turbine.
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 |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| EP1073827A1 EP1073827A1 (en) | 2001-02-07 |
| EP1073827B1 true EP1073827B1 (en) | 2003-10-08 |
Family
ID=7865335
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| EP99937814A Expired - Lifetime EP1073827B1 (en) | 1998-04-21 | 1999-04-14 | Turbine blade |
Country Status (5)
| Country | Link |
|---|---|
| US (1) | US6533544B1 (en) |
| EP (1) | EP1073827B1 (en) |
| JP (1) | JP2002512334A (en) |
| DE (1) | DE59907300D1 (en) |
| WO (1) | WO1999054597A1 (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US7607889B2 (en) | 2004-01-20 | 2009-10-27 | Siemens Aktiengesellschaft | Turbine blade and gas turbine equipped with a turbine blade |
| US8251665B2 (en) | 2004-01-20 | 2012-08-28 | Siemens Aktiengesellschaft | Turbine blade and gas turbine equipped with a turbine blade |
Families Citing this family (13)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP1099825A1 (en) * | 1999-11-12 | 2001-05-16 | Siemens Aktiengesellschaft | Turbine blade and production method therefor |
| US6375415B1 (en) * | 2000-04-25 | 2002-04-23 | General Electric Company | Hook support for a closed circuit fluid cooled gas turbine nozzle stage segment |
| RU2272151C2 (en) * | 2000-12-28 | 2006-03-20 | Альстом Текнолоджи Лтд | Axial-flow turbine stator blade |
| EP1331361B1 (en) * | 2002-01-17 | 2010-05-12 | Siemens Aktiengesellschaft | Cast turbine stator vane having a hook support |
| DE50202538D1 (en) * | 2002-01-17 | 2005-04-28 | Siemens Ag | Turbine blade with a hot gas platform and a load platform |
| US7255943B2 (en) * | 2003-05-14 | 2007-08-14 | Hoya Corporation | Glass substrate for a magnetic disk, magnetic disk, and methods of producing the glass substrate and the magnetic disk |
| JP2005108578A (en) * | 2003-09-30 | 2005-04-21 | Hitachi Ltd | Mass spectroscope |
| US7216694B2 (en) * | 2004-01-23 | 2007-05-15 | United Technologies Corporation | Apparatus and method for reducing operating stress in a turbine blade and the like |
| US7604456B2 (en) * | 2006-04-11 | 2009-10-20 | Siemens Energy, Inc. | Vane shroud through-flow platform cover |
| US8210819B2 (en) * | 2008-02-22 | 2012-07-03 | Siemens Energy, Inc. | Airfoil structure shim |
| EP2282014A1 (en) * | 2009-06-23 | 2011-02-09 | Siemens Aktiengesellschaft | Ring-shaped flow channel section for a turbo engine |
| US9546557B2 (en) * | 2012-06-29 | 2017-01-17 | General Electric Company | Nozzle, a nozzle hanger, and a ceramic to metal attachment system |
| SG11201508706RA (en) | 2013-06-10 | 2015-12-30 | United Technologies Corp | Turbine vane with non-uniform wall thickness |
Family Cites Families (14)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US2500745A (en) | 1944-09-21 | 1950-03-14 | Gen Electric | Bucket structure for high-temperature turbomachines |
| US3610769A (en) | 1970-06-08 | 1971-10-05 | Gen Motors Corp | Porous facing attachment |
| BE794195A (en) | 1972-01-18 | 1973-07-18 | Bbc Sulzer Turbomaschinen | COOLED STEERING VANE FOR GAS TURBINES |
| GB1605309A (en) * | 1975-03-14 | 1989-02-01 | Rolls Royce | Stator blade for a gas turbine engine |
| IT1079131B (en) | 1975-06-30 | 1985-05-08 | Gen Electric | IMPROVED COOLING APPLICABLE IN PARTICULAR TO ELEMENTS OF GAS TURBO ENGINES |
| DE2643049A1 (en) | 1975-10-14 | 1977-04-21 | United Technologies Corp | SHOVEL WITH COOLED PLATFORM FOR A FLOW MACHINE |
| US4283822A (en) * | 1979-12-26 | 1981-08-18 | General Electric Company | Method of fabricating composite nozzles for water cooled gas turbines |
| US4987736A (en) * | 1988-12-14 | 1991-01-29 | General Electric Company | Lightweight gas turbine engine frame with free-floating heat shield |
| US5076049A (en) | 1990-04-02 | 1991-12-31 | General Electric Company | Pretensioned frame |
| US5249418A (en) * | 1991-09-16 | 1993-10-05 | General Electric Company | Gas turbine engine polygonal structural frame with axially curved panels |
| EP0550126A1 (en) | 1992-01-02 | 1993-07-07 | General Electric Company | Thrust augmentor heat shield |
| FR2707698B1 (en) * | 1993-07-15 | 1995-08-25 | Snecma | Turbomachine provided with an air blowing means on a rotor element. |
| US5396763A (en) | 1994-04-25 | 1995-03-14 | General Electric Company | Cooled spraybar and flameholder assembly including a perforated hollow inner air baffle for impingement cooling an outer heat shield |
| JPH08135402A (en) * | 1994-11-11 | 1996-05-28 | Mitsubishi Heavy Ind Ltd | Gas turbine stationary blade structure |
-
1999
- 1999-04-14 JP JP2000544913A patent/JP2002512334A/en active Pending
- 1999-04-14 WO PCT/DE1999/001109 patent/WO1999054597A1/en active IP Right Grant
- 1999-04-14 DE DE59907300T patent/DE59907300D1/en not_active Expired - Lifetime
- 1999-04-14 EP EP99937814A patent/EP1073827B1/en not_active Expired - Lifetime
- 1999-04-14 US US09/622,596 patent/US6533544B1/en not_active Expired - Lifetime
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US7607889B2 (en) | 2004-01-20 | 2009-10-27 | Siemens Aktiengesellschaft | Turbine blade and gas turbine equipped with a turbine blade |
| US7963746B2 (en) | 2004-01-20 | 2011-06-21 | Siemens Aktiengesellschaft | Turbine blade and gas turbine equipped with a turbine blade |
| US8251665B2 (en) | 2004-01-20 | 2012-08-28 | Siemens Aktiengesellschaft | Turbine blade and gas turbine equipped with a turbine blade |
Also Published As
| Publication number | Publication date |
|---|---|
| WO1999054597A1 (en) | 1999-10-28 |
| DE59907300D1 (en) | 2003-11-13 |
| EP1073827A1 (en) | 2001-02-07 |
| JP2002512334A (en) | 2002-04-23 |
| US6533544B1 (en) | 2003-03-18 |
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