WO2001006096A1 - Gas turbine blade - Google Patents

Gas turbine blade Download PDF

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Publication number
WO2001006096A1
WO2001006096A1 PCT/DE2000/002435 DE0002435W WO0106096A1 WO 2001006096 A1 WO2001006096 A1 WO 2001006096A1 DE 0002435 W DE0002435 W DE 0002435W WO 0106096 A1 WO0106096 A1 WO 0106096A1
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WO
WIPO (PCT)
Prior art keywords
grooves
gas turbine
blades
gas
flow
Prior art date
Application number
PCT/DE2000/002435
Other languages
German (de)
French (fr)
Inventor
Jörg SEUME
Original Assignee
Siemens Aktiengesellschaft
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Filing date
Publication date
Application filed by Siemens Aktiengesellschaft filed Critical Siemens Aktiengesellschaft
Publication of WO2001006096A1 publication Critical patent/WO2001006096A1/en

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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F15—FLUID-PRESSURE ACTUATORS; HYDRAULICS OR PNEUMATICS IN GENERAL
    • F15D—FLUID DYNAMICS, i.e. METHODS OR MEANS FOR INFLUENCING THE FLOW OF GASES OR LIQUIDS
    • F15D1/00—Influencing flow of fluids
    • F15D1/10—Influencing flow of fluids around bodies of solid material
    • F15D1/12—Influencing flow of fluids around bodies of solid material by influencing the boundary layer
    • 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
    • F01D5/141—Shape, i.e. outer, aerodynamic form
    • F01D5/145—Means for influencing boundary layers or secondary circulations
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/66—Combating cavitation, whirls, noise, vibration or the like; Balancing
    • F04D29/68—Combating cavitation, whirls, noise, vibration or the like; Balancing by influencing boundary layers
    • F04D29/681—Combating cavitation, whirls, noise, vibration or the like; Balancing by influencing boundary layers especially adapted for elastic fluid pumps
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/26—Rotors specially for elastic fluids
    • F04D29/32—Rotors specially for elastic fluids for axial flow pumps
    • F04D29/321—Rotors specially for elastic fluids for axial flow pumps for axial flow compressors
    • F04D29/324—Blades
    • 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
    • F05D2240/10—Stators
    • F05D2240/12—Fluid guiding means, e.g. vanes
    • F05D2240/126—Baffles or ribs
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2260/00—Function
    • F05D2260/20—Heat transfer, e.g. cooling
    • F05D2260/221—Improvement of heat transfer
    • F05D2260/2214—Improvement of heat transfer by increasing the heat transfer surface
    • F05D2260/22141—Improvement of heat transfer by increasing the heat transfer surface using fins or ribs
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T50/00—Aeronautics or air transport
    • Y02T50/60—Efficient propulsion technologies, e.g. for aircraft

Definitions

  • the invention relates to a gas turbine with a plurality of blade rings, each having a plurality of blades.
  • Gas turbines are used to convert thermal energy into rotational energy and are used for stationary energy generation or to power aircraft.
  • a gas turbine is characterized by a high rotational speed of. characterized in its axially arranged blade rings and a high gas flow rate. In order to achieve a high energy yield, the gas flow inside the gas turbine should be perfected.
  • a gas turbine has a compressor part with stator blades and between these rotating compressor blade rings, which are mounted on a continuous shaft which also carries the drive blades.
  • a burner part in which gas expands by combustion, is arranged between the compressor part and the drive part.
  • stator blades and rotor blades are provided.
  • the present invention is based on the object of friction losses in a gas turbine of the type mentioned due to the interaction of the gas flow with the surface of gas turbine parts.
  • blades of at least one blade ring to improve the flow properties on their surface have grooves extending essentially in the direction of the gas flow.
  • An advantageous embodiment of the invention provides that the grooves are circular sector-shaped in cross section.
  • Such shaped grooves result in a particularly favorable influence on the flow conditions.
  • triangular, rectangular or trapezoidal grooves are also advantageously conceivable in cross section.
  • a further advantageous embodiment of the invention provides that the blades having grooves are arranged in the compressor part of the gas turbine.
  • the blade surface can be designed and machined relatively easily in relation to the blades arranged in the drive part of the turbine.
  • the proportion of dirt in the incoming air is particularly high, so that the self-cleaning defect is particularly noticeable here.
  • the invention can also be advantageously configured in that the grooves have a width of less than 0.1 mm.
  • the grooves have a depth of less than 0.1 mm.
  • the invention can also be advantageously configured in that the grooves are introduced into the surface by surface etching.
  • Surface etching is a method with which grooves of a certain orientation and depth and in the desired cross-sectional shape can be easily and reproducibly introduced into the surface of blades.
  • a further advantageous embodiment of the invention provides that the grooves each run parallel to sections of a helix surrounding the longitudinal axis of the gas turbine and extending helically from the drive part to the compressor part.
  • Such an alignment of the grooves requires that gas flowing through the annular flow channel of the compressor surrounding the shaft flows through the rotating blade ring in such a way that it flows tangentially along the surface of the individual blades and parallel to the grooves.
  • the individual grooves in the turbine blades run parallel to the windings of a helix, which is thought to run in the ring channel and surround the axis of rotation of the turbine.
  • the individual grooves are thus essentially helicoidal with respect to the turbine axis.
  • Figure 1 schematically in a longitudinal section of a gas turbine system
  • Figure 2 schematically in cross section different forms of grooves.
  • FIG. 1 schematically shows a gas turbine system in a longitudinal section with a housing 1, in which fixed guide blades 3, 4 are fastened, and a rotor 2, on which
  • Blades 5, 6 are attached.
  • the fuel injected via the burners 14, 15 is burned with the air from the compressor part 16.
  • Compressor part 16 is the input part of the gas turbine system in which inflowing air (lines 17, 18) is compressed before it flows into combustion chamber 7.
  • a generator 20 for generating electrical energy is driven by means of the connecting shaft 19.
  • grooves 22, 23, 24 are shown schematically by way of example, which in their projection onto the drawing plane m in the direction of the arrows 17, 18 run conically on the shaft 19.
  • the grooves are particularly easy to make in the surface, since there is usually no coating of the blades with heat-insulating layers.
  • the introduction of grooves in such a thermal insulation layer is also conceivable.
  • Grooves can be made particularly favorably by anisotropic etching in the surface of the blades, if they have a crystal structure.
  • FIG. 2 shows different groove cross-sections, namely a cross-sectional shape in the form of a sector, a triangular cross-section and a rectangular cross-section of a groove, the groove width in each case being approximately 0.02 mm and the depth being approximately 0.01 mm in each case.

Abstract

According to the invention, the turbine blades (21) on at least one blade ring (26) in a gas turbine having blade rings (25, 26) are provided with grooves (22, 23, 24) extending substantially in the direction of the gas flow to improve flow characteristics on the surfaces thereof.

Description

GASTURBINENSCHAUFEL GAS TURBINE BLADE
Die Erfindung bezieht sich auf eine Gasturbine mit mehreren Schaufelkränzen, die jeweils mehrere Schaufeln aufweisen.The invention relates to a gas turbine with a plurality of blade rings, each having a plurality of blades.
Gasturbinen dienen zur Umwandlung von Wärmeenergie in Rotationsenergie und werden zur stationären Energieerzeugung bzw. zum Antrieb von Flugzeugen verwendet. Eine Gasturbine ist durch eine hohe Rotationsgeschwindigkeit von. in ihr axial angeordneten Schaufelkränzen und eine hohe Gasströmungsgeschwindigkeit gekennzeichnet. Dabei ist zur Erzielung einer hohen Energieausbeute die Perfektionierung der Gasströmung im Inneren der Gasturbine anzustreben.Gas turbines are used to convert thermal energy into rotational energy and are used for stationary energy generation or to power aircraft. A gas turbine is characterized by a high rotational speed of. characterized in its axially arranged blade rings and a high gas flow rate. In order to achieve a high energy yield, the gas flow inside the gas turbine should be perfected.
Eine Gasturbine weist einen Verdichterteil mit Statorschaufeln und zwischen diesen rotierenden Verdichterschaufelkränzen auf, die auf einer durchgehenden Welle gelagert sind, die auch die Antriebsschaufeln trägt. Zwischen dem Verdichterteil und dem Antriebsteil ist ein Brennerteil angeordnet, in dem Gas durch Verbrennung expandiert.A gas turbine has a compressor part with stator blades and between these rotating compressor blade rings, which are mounted on a continuous shaft which also carries the drive blades. A burner part, in which gas expands by combustion, is arranged between the compressor part and the drive part.
Um Verwirbelungen der Gasströmung in der Gasturbine zu mini- mieren, wird eine geeignete Formgebung und Ausrichtung von Statorschaufeln und Laufschaufeln angestrebt.In order to minimize turbulence in the gas flow in the gas turbine, suitable shaping and alignment of stator blades and rotor blades is sought.
Zur Vermeidung von Reibungsverlusten an den Oberflächen der angeströmten Turbinenteile wurde bislang eine möglichst glat- te Oberflächenbeschaffenheit angestrebt, in dem Sinn, daß jede Art von mikroskopischen oder makroskopischen Rauhigkeiten möglichst beseitigt wurde.,In order to avoid frictional losses on the surfaces of the flowed turbine parts, the smoothest possible surface finish has so far been attempted in the sense that any type of microscopic or macroscopic roughness has been eliminated as far as possible.
Der vorliegenden Erfindung liegt die Aufgabe zu Grunde, bei einer Gasturbine der eingangs genannten Art Reibungsverluste infolge von Wechselwirkung der Gasströmung mit der Oberfläche von Gasturbinenteilen weiter zu minimieren.The present invention is based on the object of friction losses in a gas turbine of the type mentioned due to the interaction of the gas flow with the surface of gas turbine parts.
Die Aufgabe wird erfindungsgemäß dadurch gelöst, daß Schaufeln wenigstens eines Schaufelkranzes zur Verbesserung der Strömungseigenschaften an ihrer Oberfläche im wesentlichen in Richtung der Gasanströmung verlaufende Nuten aufweisen.The object is achieved in that blades of at least one blade ring to improve the flow properties on their surface have grooves extending essentially in the direction of the gas flow.
Aus der allgemeinen wissenschaftlichen Literatur beispielsweise zur Bionik ist bekannt (vergleiche D. W. Bechert et al. "Experiments on drag-reducing surfaces and their optimization with an adjustable geometry, Fluid Mechanics (1997) vol. 338 pp 59-87, AIAA 97-1960 Biological surfaces and their techno- logical application - laboratory and flight experiments on drag reduction and Separation control, D. W. Bechert et al . , sowie D. W. Bechert et al: The viscous flow on surfaces with longitudinal ribs" Fluid Mechanics (1989) vol. 206 pp 105 - 129) sowie DE 196 50 439 Cl,) bei von einem Fluid umströmten Körpern in Strömungsrichtung verlaufende Nuten bzw. Rillen vorzusehen, die für eine Beruhigung der Strömung an dem jeweiligen Körper sorgen und somit Reibungsverluste verringern.From the general scientific literature, for example on bionics, is known (compare DW Bechert et al. "Experiments on drag-reducing surfaces and their optimization with an adjustable geometry, Fluid Mechanics (1997) vol. 338 pp 59-87, AIAA 97-1960 Biological surfaces and their technological application - laboratory and flight experiments on drag reduction and separation control, DW Bechert et al., and DW Bechert et al: The viscous flow on surfaces with longitudinal ribs "Fluid Mechanics (1989) vol. 206 pp 105 - 129) and DE 196 50 439 Cl,) to provide grooves or grooves running in the direction of flow of a fluid around the body, which provide a calming of the flow on the respective body and thus reduce friction losses.
Dies wurde beispielsweise auch schon durch Anbringen von Nu- ten an der Außenoberfläche von Flugzeugrümpfen realisiert.This has already been achieved, for example, by making grooves on the outer surface of aircraft fuselages.
Für in einem gasförmigen Medium rotierende Bauteile wurde dieses Mittel bislang noch nicht eingesetzt. Im Einzelfall besteht das Problem darin, daß für die Anwendung eine im we- sentlichen laminare Strömung vorliegen muß und , daß die Strömungsrichtung relativ zur Oberfläche des umströmten Gegenstandes bekannt sein muß. Allgemein strukturierte Oberflächen an Strömungsmaschinen sind aus US 4,720,239, DE 23 58 521 C2 und DE 43 19 628 AI bekannt. In bezug auf diese Parameter sind die Verhältnisse innerhalb einer Gasturbine komplizierter als bei einem frei umströmten ortsfesten Körper.This agent has not previously been used for components rotating in a gaseous medium. In individual cases, the problem is that an essentially laminar flow must be present for the application and that the direction of flow relative to the surface of the object flowing around must be known. Generally structured surfaces on turbomachines are known from US 4,720,239, DE 23 58 521 C2 and DE 43 19 628 AI. With regard to these parameters, the conditions within a gas turbine are more complicated than with a freely flowing, stationary body.
Durch die Anordnung solcher Nuten bzw. Rillen auf der Oberfläche von Schaufeln kann einerseits durch Herabsetzung der Reibung eine höhere Energieausbeute erzielt werden, die zu einer Verbesserung des Wirkungsgrades im Bereich von Prozenten führt, andererseits tritt auch eine Selbstreinigungswir- kung der Schaufeln durch die verbesserten Strömungsverhältnisse ein, die eine Reinigung erheblich seltener notwendig macht als bisher.By arranging such grooves or grooves on the surface of the blades, a higher energy yield can be achieved on the one hand by reducing the friction, which leads to an improvement in the efficiency in the range of percentages, on the other hand the blades also have a self-cleaning effect due to the improved flow conditions a, which makes cleaning much less necessary than before.
Wenn im Zusammenhang mit der Erfindung von Nuten oder Rillen die Rede ist, so kann dies auch bedeuten, daß Stege auf der Oberfläche einer Turbinenschaufel vorgesehen sind, zwischen denen entsprechende Nuten gebildet sind.If there is talk of grooves or grooves in connection with the invention, this can also mean that webs are provided on the surface of a turbine blade, between which corresponding grooves are formed.
Eine vorteilhafte Ausgestaltung der Erfindung sieht vor, daß die Nuten im Querschnitt kreissektorförmig ausgebildet sind.An advantageous embodiment of the invention provides that the grooves are circular sector-shaped in cross section.
Derart geformte Nuten ergeben eine besonders günstige Beeinflussung der Strömungsverhältnisse. Es sind jedoch auch im Querschnitt dreieckförmige, rechteckige oder trapezförmige Nuten vorteilhaft denkbar.Such shaped grooves result in a particularly favorable influence on the flow conditions. However, triangular, rectangular or trapezoidal grooves are also advantageously conceivable in cross section.
Eine weitere vorteilhafte Ausgestaltung der Erfindung sieht vor, daß die Nuten aufweisenden Schaufeln im Verdichterteil der Gasturbine angeordnet sind.A further advantageous embodiment of the invention provides that the blades having grooves are arranged in the compressor part of the gas turbine.
In diesem Bereich ist die Schaufeloberfläche im Verhältnis zu den im Antriebsteil der Turbine angeordneten Schaufeln relativ einfach gestaltbar und bearbeitbar. Außerdem ist hier der Schmutzanteil in der anströmenden Luft besonders hoch, so daß der Selbstreinigungsefekt sich hier besonders vorteilhaft bemerkbar macht.In this area, the blade surface can be designed and machined relatively easily in relation to the blades arranged in the drive part of the turbine. In addition, the proportion of dirt in the incoming air is particularly high, so that the self-cleaning defect is particularly noticeable here.
Die Erfindung kann außerdem vorteilhaft dadurch ausgestaltet werden, daß die Nuten eine Breite von weniger als 0,1 mm aufweisen.The invention can also be advantageously configured in that the grooves have a width of less than 0.1 mm.
Vorteilhaft kann außerdem vorgesehen sein, daß die Nuten eine Tiefe von weniger als 0,1 mm aufweisen.It can also be advantageously provided that the grooves have a depth of less than 0.1 mm.
In bezug auf die Viskosität, Strömungsgeschwindigkeit und Teilchengröße des eine Gasturbine durchströmenden Gases erscheinen die angegebenen Größenordnungen besonders günstig zur Verbesserung der Strömungsverhältnisse.With regard to the viscosity, flow velocity and particle size of the gas flowing through a gas turbine, the stated magnitudes appear to be particularly favorable for improving the flow conditions.
Die Erfindung kann außerdem vorteilhaft dadurch ausgestaltet werden, daß die Nuten durch Oberflächenätzung in die Oberfläche eingebracht sind.The invention can also be advantageously configured in that the grooves are introduced into the surface by surface etching.
Die Oberflächenätzung stellt eine Methode dar, mit der auf einfache Weise reproduzierbar Nuten bestimmter Ausrichtung und Tiefe und in der gewünschten Querschnittsform in die 0- berfläche von Schaufeln einbringbar sind.Surface etching is a method with which grooves of a certain orientation and depth and in the desired cross-sectional shape can be easily and reproducibly introduced into the surface of blades.
Es ist jedoch auch denkbar, durch spanende Bearbeitung bzw. gezieltes Schleifen entsprechende Nuten in die Oberfläche von Turbinenschaufeln einzubringen. Als weitere Verfahren kommen das EDM (Electron Discharge Machining) , elektroerosive Verfahren, Laserbearbeitung und die Bearbeitung mittels Hoch- druckwasserstrahl in Frage.However, it is also conceivable to provide corresponding grooves in the surface of turbine blades by machining or targeted grinding. Other processes that can be used are EDM (Electron Discharge Machining), electroerosive processes, laser processing and high pressure water jet processing.
Eine weitere vorteilhafte Ausgestaltung der Erfindung sieht vor, daß die Nuten jeweils parallel zu Abschnitten einer die Längsachse der Gasturbine umgebenden, sich vom Antriebsteil zum Verdichterteil spiralförmig erweiternde Helix verlaufen. Eine derartige Ausrichtung der Nuten bedingt, daß durch den ringförmigen, die Welle umgebenden Strömungskanal des Verdichters strömendes Gas durch den rotierenden Schaufelkranz derart hindurchströmt, daß es tangential an der Oberfläche der einzelnen Schaufeln entlang und parallel zu den Nuten strömt. Die einzelnen Nuten in den Turbinenschaufeln verlaufen parallel zu den Windungen einer in dem Ringkanal gedacht verlaufenden, die Rotationsachse der Turbine umgebenden He- lix. Die einzelnen Nuten verlaufen somit in bezug auf die Turbinenachse im wesentlichen helizoidal.A further advantageous embodiment of the invention provides that the grooves each run parallel to sections of a helix surrounding the longitudinal axis of the gas turbine and extending helically from the drive part to the compressor part. Such an alignment of the grooves requires that gas flowing through the annular flow channel of the compressor surrounding the shaft flows through the rotating blade ring in such a way that it flows tangentially along the surface of the individual blades and parallel to the grooves. The individual grooves in the turbine blades run parallel to the windings of a helix, which is thought to run in the ring channel and surround the axis of rotation of the turbine. The individual grooves are thus essentially helicoidal with respect to the turbine axis.
Im folgenden wird die Erfindung anhand eines Ausführungsbeispiels in einer Zeichnung gezeigt und anschließend beschrie- ben.In the following, the invention is shown on the basis of an exemplary embodiment in a drawing and then described.
Dabei zeigtIt shows
Figur 1 schematisch in einem Längsschnitt eine Gasturbinenanlage, Figur 2 schematisch im Querschnitt verschiedene Formen von Nuten.Figure 1 schematically in a longitudinal section of a gas turbine system, Figure 2 schematically in cross section different forms of grooves.
Die Figur 1 zeigt schematisch eine Gasturbinenanlage in einem Längsschnitt mit einem Gehäuse 1, in dem feststehende Leit- schaufeln 3, 4 befestigt sind , sowie einem Rotor 2, an demFIG. 1 schematically shows a gas turbine system in a longitudinal section with a housing 1, in which fixed guide blades 3, 4 are fastened, and a rotor 2, on which
Laufschaufeln 5, 6 befestigt sind. In dem Brennkammergehäuse 7 wird der über die Brenner 14, 15 eingespritzte Brennstoff mit der Luft aus dem Verdichterteil 16 verbrannt. Als Verdichterteil 16 wird dabei der Eingangsteil der Gasturbinenan- läge bezeichnet, in dem einströmende Luft (Zeile 17, 18) vor dem Einströmen in die Brennkammer 7 komprimiert wird.Blades 5, 6 are attached. In the combustion chamber housing 7, the fuel injected via the burners 14, 15 is burned with the air from the compressor part 16. Compressor part 16 is the input part of the gas turbine system in which inflowing air (lines 17, 18) is compressed before it flows into combustion chamber 7.
Die Expansion der Verbrennungsgase treibt die Turbine an. Mittels der Verbindungswelle 19 wird ein Generator 20 zur Er- zeugung elektrischer Energie angetrieben. Bei zwei Laufschaufeln 6, 21 sind schematisch beispielhaft Nuten 22, 23, 24 dargestellt, die in ihrer Projektion auf die Zeichenebene m Richtung der Pfeile 17, 18 konisch auf die Welle 19 zu verlaufen.The expansion of the combustion gases drives the turbine. A generator 20 for generating electrical energy is driven by means of the connecting shaft 19. In the case of two moving blades 6, 21, grooves 22, 23, 24 are shown schematically by way of example, which in their projection onto the drawing plane m in the direction of the arrows 17, 18 run conically on the shaft 19.
Der reale Verlauf der Nuten 22, 23, 24 auf den Laufschaufeln 6, 21 ist parallel zu einer die Welle 19 umgebenden und sich zu dem Generator 20 hin spiraig erweiternden Helix.The real course of the grooves 22, 23, 24 on the rotor blades 6, 21 is parallel to a helix surrounding the shaft 19 and widening towards the generator 20.
Im Bereich der Verdichterschaufeln 6, 21 sind die Nuten besonders einfach in die Oberflache einzubringen, da dort üblicherweise keine Beschichtung der Schaufeln mit warmedammenden Schichten vorgesehen ist. Jedoch ist auch das Einbringen von Nuten m eine derartige Warmedammschicht denkbar.In the area of the compressor blades 6, 21, the grooves are particularly easy to make in the surface, since there is usually no coating of the blades with heat-insulating layers. However, the introduction of grooves in such a thermal insulation layer is also conceivable.
Nuten lassen sich besonders gunstig durch anisotropes Atzen in die Oberflache der Schaufeln einbringen, wenn diese em- kristallm aufgebaut sind.Grooves can be made particularly favorably by anisotropic etching in the surface of the blades, if they have a crystal structure.
Im übrigen ist jedoch auch eine spanende Bearbeitung oder ein Einschleifen von Nuten in die Oberflache der Schaufeln möglich.For the rest, however, machining or grinding of grooves into the surface of the blades is also possible.
Figur 2 zeigt verschiedene Nutenquerschnitte, und zwar einen kreissektorformigen Querschnitt, einen dreieckformigen Querschnitt und einen rechteckigen Querschnitt einer Nut, wobei die Nutbreite jeweils etwa 0,02 mm und die Tiefe etwa jeweils 0, 01 mm betragt . FIG. 2 shows different groove cross-sections, namely a cross-sectional shape in the form of a sector, a triangular cross-section and a rectangular cross-section of a groove, the groove width in each case being approximately 0.02 mm and the depth being approximately 0.01 mm in each case.

Claims

Patentansprüche claims
1. Gasturbine mit mehreren Schaufelkränzen (25,26), die jeweils mehrere Turbinenschaufeln (3,4,6,21) aufweisen, d a d u r c h g e k e n n z e i c h n e t , daß Turbinenschaufeln wenigstens eines Schaufelkranzes zur Verbesserung der Strömungseigenschaften an ihrer Oberfläche im wesentlichen in Richtung der Gasanströmung verlaufende Nuten (22,23,24) aufweisen.1. Gas turbine with a plurality of blade rings (25, 26), each having a plurality of turbine blades (3, 4, 6, 21), characterized in that turbine blades of at least one blade ring to improve the flow properties on its surface are grooves which run essentially in the direction of the gas flow ( 22, 23, 24).
2. Gasturbine 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 Nuten (22,23,24) im Querschnitt kreissektorförmig ausgebildet sind.2. Gas turbine according to claim 1, so that the grooves (22, 23, 24) are circular sector-shaped in cross section.
3. Gasturbine 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 die Nuten (22,23,24) aufweisenden Turbinenschaufeln (4,6,2,1) im Verdichterteil (16) der Gasturbine angeordnet sind.3. Gas turbine according to claim 1 or 2, so that the grooves (22, 23, 24) having turbine blades (4, 6, 2, 1) are arranged in the compressor part (16) of the gas turbine.
4. Gasturbine nach einem der vorangehenden Ansprüche, d a d u r c h g e k e n n z e i c h n e t , daß die Nuten (22,23,24) eine Breite von weniger als 0,1 mm aufweisen.4. Gas turbine 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 grooves (22,23,24) have a width of less than 0.1 mm.
5. Gasturbine nach einem der vorangehenden Ansprüche, d a d u r c h g e k e n n z e i c h n e t , daß die Nuten (22,23,24) eine Tiefe von weniger als 0,1 mm aufweisen.5. Gas turbine 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 grooves (22,23,24) have a depth of less than 0.1 mm.
6. Gasturbine nach einem der vorangehenden Ansprüche, d a d u r c h g e k e n n z e i c h n e t , daß die Nuten (22,23,24) durch Oberflächenätzung in die Oberfläche eingebracht sind. 6. Gas turbine according to one of the preceding claims, characterized in that the grooves (22,23,24) are introduced into the surface by surface etching.
7. Gasturbine nach einem der vorangehenden Ansprüche, d a d u r c h g e k e n n z e i c h n e t , daß die Nuten (22,23,24) jeweils parallel zu Abschnitten einer die Längsachse der Gasturbine umgebenden, sich vom An- triebsteil (27) zum Verdichterteil (16) spiralförmig erweiternden Helix verlaufen. 7. Gas turbine according to one of the preceding claims, so that the grooves (22, 23, 24) each run parallel to sections of a helix that extends from the drive part (27) to the compressor part (16) in a spiral shape and surrounds the longitudinal axis of the gas turbine.
PCT/DE2000/002435 1999-07-19 2000-07-19 Gas turbine blade WO2001006096A1 (en)

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