EP1462614B1 - Axial-flow thermal turbomachine - Google Patents

Axial-flow thermal turbomachine Download PDF

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Publication number
EP1462614B1
EP1462614B1 EP04101054.7A EP04101054A EP1462614B1 EP 1462614 B1 EP1462614 B1 EP 1462614B1 EP 04101054 A EP04101054 A EP 04101054A EP 1462614 B1 EP1462614 B1 EP 1462614B1
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EP
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Prior art keywords
rotor
blade
blades
density
turbomachine
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EP04101054.7A
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German (de)
French (fr)
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EP1462614A2 (en
EP1462614A3 (en
Inventor
Claus Paul Gerdes
Mohamed Yousef Nazmy
Hans Wettstein
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General Electric Technology GmbH
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Alstom Technology AG
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    • 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
    • F01D5/28—Selecting particular materials; Particular measures relating thereto; Measures against erosion or corrosion
    • 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
    • F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
    • F01D11/005—Sealing means between non relatively rotating elements
    • F01D11/006—Sealing the gap between rotor blades or blades and rotor
    • F01D11/008—Sealing the gap between rotor blades or blades and rotor by spacer elements between the blades, e.g. independent interblade platforms
    • 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
    • F01D5/02—Blade-carrying members, e.g. rotors
    • 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
    • F01D5/30—Fixing blades to rotors; Blade roots ; Blade spacers
    • 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
    • F05D2300/00—Materials; Properties thereof
    • F05D2300/50—Intrinsic material properties or characteristics
    • 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
    • F05D2300/00—Materials; Properties thereof
    • F05D2300/60—Properties or characteristics given to material by treatment or manufacturing
    • F05D2300/606—Directionally-solidified crystalline structures

Definitions

  • the invention relates to the field of power plant technology. It relates to an axial flow thermal turbomachine according to the preamble of claim 1, which has a reduced rotor weight compared to the known prior art.
  • Thermal turbomachinery As high-pressure compressor for gas turbines or turbines consist essentially of a rotor equipped with blades and a stator, are hung in the vanes. The blades and vanes each have an airfoil and a blade root. To be able to fasten the blades on the rotor or in the stator, grooves are inserted in the stator and on the rotor shaft. In these grooves, the feet of the guide vanes and blades are inserted and locked there.
  • the fixed guide vanes have the task of directing the flow of the compressed or the gaseous medium to be relaxed on the rotating rotor blading so that the energy conversion takes place with the best possible efficiency.
  • blades in one piece from a single material for. B. stainless steel for gas turbine compressor or a nickel-based superalloy for gas turbines to produce and to equip with these similar blades a row of blades.
  • Such blades are hereinafter referred to as conventional blades.
  • the average mass of a row of blades is limited by the carrying capacity of the rotor.
  • a rotor with integral blading in particular for an engine, are circumferentially arranged on the rotor blades, wherein the rotor blade to reduce vibrations, a metallic blade root, a metallic blade leaf portion, at least part of the Blade leading edge and the adjoining portion of the blade surface, and having a blade made of fiber reinforced plastic.
  • the attachment of the blade made of plastic to the metallic blade section by gluing / riveting or by clamping takes place.
  • Out DE 14 26 816 A1 is an axial turbomachine with a compressor blade ring in which Verguss sapll GmbHe of casting resin or aluminum or Al alloys are arranged between adjacent blades known. By casting the spaces between the blade roots, the circumferential distance should be kept exactly as well as materials and production times saved.
  • the aim of the invention is to avoid the mentioned disadvantages of the prior art.
  • the invention is based on the object to develop a thermal turbomachine, in which due to a reduced weight, the life of the rotor is increased.
  • this object is achieved in a thermal turbomachine according to the preamble of claim 1, characterized in that the intermediate pieces between the blades of a blade row consist of intermetallic compounds.
  • the advantages of the invention are that on the one hand, the weight of the rotor is reduced, and on the other hand, the brittleness of the intermetallic spacers no increased risk for the operation of the machine means.
  • the intermediate pieces consist of an intermetallic ⁇ -TiAl compound or an intermetallic orthorhombic TiAl compound, because this inventive use of material leads to a considerable weight reduction of the rotor.
  • the specific gravity of titanium-aluminide intermetallic compounds is only about 50% of that of stainless Cr-Ni-W steel.
  • FIGURE shows a cross section through the rotor according to the invention of a high-pressure compressor for a gas turbine.
  • Fig. 1 shows a cross section through a blade row of a rotor 1 for a high-pressure compressor of a gas turbine.
  • the rotor 1 is surrounded by a stator 2.
  • blades 3, 3 ' are mounted, while in the stator 2 vanes 5 are mounted.
  • the blades 3, 3 ', 5 are exposed to a temperature of approximately 600 ° C. for several thousand hours at a pressure of approximately 32 bar.
  • the shaft of the rotor 1 is also made of steel.
  • the density of steel is about 7.9 g / cm 3 .
  • intermediate pieces 4 are respectively mounted in the circumferential groove of the rotor 1 in a blade row of the rotor 1.
  • these intermediate pieces 4 are made of an intermetallic compound, here of a ⁇ -titanium-aluminide compound.
  • This intermetallic compound used for the production of the intermediate pieces 4 has the following chemical composition (in% by weight): Ti (30.5-31.5) Al- (8.9-9.5) W- (0.3-0.4) Si.
  • Titanium-metal intermetallic compounds with aluminum have some interesting properties that make them attractive as engineering materials in the medium and higher temperature range. These include their lower compared to superalloys and lower than stainless steels. However, their technical usability often stands in the way of their brittleness.
  • the ⁇ -titanium-aluminide intermetallic compound described above is characterized by about 50% lower density than the steel used in this embodiment for the rotor and the blades. Furthermore, it has an E-modulus at room temperature of 171 GPa and a thermal conductivity ⁇ of 24 W / mK.
  • Table 1 compares further physical properties of the two alloys. Table 1: Physical properties of the different materials Density in g / cm 3 Thermal expansion coefficient in K -1 ⁇ -Ti-Al 4 10x10 -6 Stainless steel 7.9 18.6 x 10 -6
  • the weight reduction of the inventive rotor has an advantageous effect on increasing the life of the machine.
  • intermetallic spacers is carried out in a known manner by casting, hot-isostatic pressing and heat treatment with a minimum of mechanical post-processing.
  • the intermediate piece 4 of the high-pressure compressor may, for example, also be made of a known intermetallic orthorhombic titanium-aluminide alloy with a density of 4.55 g / cm 3 .
  • Orthorhombic titanium aluminide alloys are based on the ordered compound Ti 2 AlNb and have the following chemical composition: Ti (22-27) Al- (21-27) Nb.
  • Ti (22-27) Al- (21-27) Nb The inventive use of a titanium high-temperature alloy, which has, for example, the following chemical composition (in% by weight): 0.06 C, 0.4 Si, 5.8 Al, 4 Sn, 4 Zr, 0.5 Mo, ⁇ 0.05 Fe, 0.11 O, ⁇ 0.03 N, ⁇ 0.006 H, remainder Ti, is conceivable.
  • the invention not only for high-pressure compressor rotors, but also for turbine rotors with turbine blades made of a superalloy, for example a nickel-based superalloy, in which the intermediate pieces between the blades, for example of a ⁇ -titanium-aluminide intermetallic alloy or an intermetallic orthorhombic titanium-aluminide alloy.
  • a superalloy for example a nickel-based superalloy
  • the intermediate pieces between the blades for example of a ⁇ -titanium-aluminide intermetallic alloy or an intermetallic orthorhombic titanium-aluminide alloy.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Materials Engineering (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)

Description

Technisches GebietTechnical area

Die Erfindung bezieht sich auf das Gebiet der Kraftwerkstechnik. Sie betrifft eine axial durchströmte thermische Turbomaschine gemäss dem Oberbegriff des Patentanspruches 1, welche gegenüber dem bekannten Stand der Technik ein reduziertes Rotorgewicht aufweist.The invention relates to the field of power plant technology. It relates to an axial flow thermal turbomachine according to the preamble of claim 1, which has a reduced rotor weight compared to the known prior art.

Stand der TechnikState of the art

Thermische Turbomaschinen, z. B. Hochdruckverdichter für Gasturbinen oder Turbinen, bestehen im wesentlichen aus einem mit Laufschaufeln bestückten Rotor und einem Stator, in den Leitschaufeln eingehängt sind. Die Laufschaufeln und die Leitschaufeln weisen jeweils ein Schaufelblatt und einen Schaufelfuss auf. Um die Schaufeln auf dem Rotor bzw. im Stator befestigen zu können, sind im Stator und auf der Rotorwelle Nuten eingestochen. In diese Nuten werden die Füsse der Leit- und Laufschaufeln eingeschoben und dort arretiert.Thermal turbomachinery, z. As high-pressure compressor for gas turbines or turbines consist essentially of a rotor equipped with blades and a stator, are hung in the vanes. The blades and vanes each have an airfoil and a blade root. To be able to fasten the blades on the rotor or in the stator, grooves are inserted in the stator and on the rotor shaft. In these grooves, the feet of the guide vanes and blades are inserted and locked there.

Die feststehenden Leitschaufeln haben die Aufgabe, den Strom des zu verdichtenden bzw. des zu entspannenden gasförmigen Mediums so auf die rotierende Laufbeschaufelung zu lenken, dass die Energieumwandlung mit bestmöglichem Wirkungsgrad erfolgt.The fixed guide vanes have the task of directing the flow of the compressed or the gaseous medium to be relaxed on the rotating rotor blading so that the energy conversion takes place with the best possible efficiency.

Es ist bekannt, Schaufeln einstückig aus einem einzigen Material, z. B. aus rostfreiem Stahl für Gasturbinenverdichter oder aus einer Nickel-Basis-Superlegierung für Gasturbinen, herzustellen und mit diesen gleichartigen Schaufeln eine Schaufelreihe zu bestücken. Derartige Schaufeln werden nachfolgend als konventionelle Schaufeln bezeichnet.It is known, blades in one piece from a single material, for. B. stainless steel for gas turbine compressor or a nickel-based superalloy for gas turbines to produce and to equip with these similar blades a row of blades. Such blades are hereinafter referred to as conventional blades.

Für bestimmte Anwendungen ist die durchschnittliche Masse einer Schaufelreihe von der Tragkapazität des Läufers begrenzt.For certain applications, the average mass of a row of blades is limited by the carrying capacity of the rotor.

Daher sind Lösungen bekannt geworden, Schaufeln in Hybrid-Bauweise herzustellen. Bei der Hybrid-Bauweise werden zur Herstellung einer Schaufel verschiedene Werkstoffe mit unterschiedlichen physikalischen Eigenschaften miteinander kombiniert, um eine optimale Auslegung einer Schaufel zu erhalten. So ist z. B. eine Hybrid-Rotorschaufel für ein Triebwerk aus DE 101 10 102 A1 bekannt, bei welcher die Hinterkante des Schaufelblattes, die nur eine aerodynamische Funktion hat, aus einem Leichtbauwerkstoff, vorzugsweise einem Faserverbundstoff, z. B. Kohlenfaser-Verbundwerkstoff, hergestellt ist. Durch eine solche (leichte) Hinterkante lässt sich vorteilhaft das Gewicht der Schaufel reduzieren. Die Verbindung der beiden Schaufelblattteile (schwere metallische Vorderkante und leichte Hinterkante aus Faserverbundwerkstoff) erfolgt durch Kleben oder Vernieten.Therefore, solutions have become known to produce blades in hybrid construction. In the hybrid construction method, different materials with different physical properties are combined with one another to produce a blade, in order to obtain an optimum design of a blade. So z. B. a hybrid rotor blade for an engine DE 101 10 102 A1 known, in which the trailing edge of the airfoil, which has only an aerodynamic function, made of a lightweight material, preferably a fiber composite material, for. As carbon fiber composite material is produced. By such a (slight) trailing edge can be advantageous to reduce the weight of the blade. The connection of the two airfoil parts (heavy metal leading edge and light trailing edge made of fiber composite material) is done by gluing or riveting.

Eine ähnliche Lösung ist in WO 99/27234 beschrieben. Dort wird ein Rotor mit integraler Beschaufelung, insbesondere für ein Triebwerk, offenbart, an dem umfänglich Rotorschaufeln angeordnet sind, wobei die Rotorschaufel zur Verringerung von Schwingungen einen metallischen Schaufelfuss, einen metallischen Schaufelblattabschnitt, der wenigstens einen Teil der Schaufelvorderkante und des daran angrenzenden Bereichs der Schaufelfläche bildet, und ein Schaufelblatt aus faserverstärktem Kunststoff aufweisen. Auch hier erfolgt die Befestigung des Schaufelblattes aus Kunststoff an dem metallischen Schaufelblattabschnitt durch Kleben/Nieten oder durch Klemmen.A similar solution is in WO 99/27234 described. There is disclosed a rotor with integral blading, in particular for an engine, are circumferentially arranged on the rotor blades, wherein the rotor blade to reduce vibrations, a metallic blade root, a metallic blade leaf portion, at least part of the Blade leading edge and the adjoining portion of the blade surface, and having a blade made of fiber reinforced plastic. Again, the attachment of the blade made of plastic to the metallic blade section by gluing / riveting or by clamping takes place.

Dieser bekannte Stand der Technik hat die nachfolgend aufgeführten Nachteile. Einerseits halten die genannten Befestigungsarten über einen langen Zeitraum keinen grossen Belastungen Stand, anderseits sind die faserverstärkten Kunststoffe nur in bestimmten Temperaturbereichen einsetzbar, so dass diese bekannten technischen Lösungen insbesondere nur für die Triebwerkstechnik geeignet sind. Ausserdem wird die Charakteristik des Schaufelblattes (mechanische Eigenschaften, Oxidationsbeständigkeit, Reibungseigenschaften) gegenüber den aus einem einzigen Material bestehenden Schaufelblättern verändert, was sich nachteilig auf das Betriebsverhalten der Maschine auswirken kann.This known prior art has the following disadvantages. On the one hand, the mentioned types of fastening do not withstand great loads over a long period of time; on the other hand, the fiber-reinforced plastics can only be used in certain temperature ranges, so that these known technical solutions are suitable in particular only for engine technology. In addition, the characteristic of the airfoil (mechanical properties, oxidation resistance, friction properties) is changed compared to the blades made of a single material, which can adversely affect the performance of the machine.

Weiterhin ist aus EP 0 513 407 B1 eine Turbinenschaufel aus einer Legierung auf der Basis eines dotierstoffhaltigen Gamma-Titan-Aluminides bekannt, welche aus Schaufelblatt, Schaufelfuss und gegebenenfalls Schaufeldeckband besteht. Bei der Herstellung dieser Schaufel wird der Gusskörper derart partiell wärmebehandelt und warmverformt, dass das Schaufelblatt anschliessend eine grobkörnige Struktur aufweist, die zu hoher Zug- und Zeitstandfestigkeit führt, und dass der Schaufelfuss und/oder das Schaufeldeckband eine feinkörnige Struktur aufweist, die zu einer gegenüber dem Schaufelblatt erhöhten Duktilität führt. Zwar wird mit dem Einsatz dieser Schaufeln im Vergleich zu konventionellen Schaufeln vorteilhaft die Masse des Rotors abgesenkt, nachteilig an diesem Stand der Technik ist aber, dass die Schaufelspitzen aufgrund ihrer Sprödigkeit wegplatzen, wenn sie während des Betriebes mit dem Stator in Berührung kommen. Dies ist aber normalerweise nicht zu verhindern.Furthermore, it is off EP 0 513 407 B1 a turbine blade made of an alloy based on a dopant-containing gamma titanium aluminide known which consists of the blade, blade root and possibly blade shroud. In the production of this blade, the cast body is partially heat-treated and hot-formed so that the blade then has a coarse-grained structure which leads to high tensile and creep strength, and that the blade root and / or the blade cover strip has a fine-grained structure facing one Increased ductility leads to the airfoil. While the mass of the rotor is advantageously lowered with the use of these blades in comparison to conventional blades, it is disadvantageous in this prior art that the blade tips break away due to their brittleness when they come into contact with the stator during operation. This is usually not preventable.

Aus DE 14 26 816 A1 ist eine axiale Turbomaschine mit einem Verdichter-Laufschaufelkranz, bei dem zwischen benachbarten Schaufeln Vergussfüllstücke aus Giessharz oder Aluminium bzw. Al-Legierungen angeordnet sind, bekannt. Durch das Vergiessen der Räume zwischen den Schaufelfüssen sollen der Umfangsabstand genau eingehalten sowie Werkstoffe und Fertigungszeiten eingespart werden.Out DE 14 26 816 A1 is an axial turbomachine with a compressor blade ring in which Vergussfüllstücke of casting resin or aluminum or Al alloys are arranged between adjacent blades known. By casting the spaces between the blade roots, the circumferential distance should be kept exactly as well as materials and production times saved.

Im Dokument US-A-2 936 155 wird eine axial durchströmte thermische Turbomaschine, insbesondere Kompressor, beschrieben, bei der in einer Umfangsnut abwechselnd Laufschaufeln und Zwischenstücke, welche vorzugsweise aus Gummi bestehen, montiert sind. Damit sollen Schaufelvibrationen der Schaufeln gedämpft werden. Hohen Temperaturen halten aber diese Gummizwischenstücke nicht stand.In the document US-A-2,936,155 is an axial flow thermal turbomachine, in particular compressor, described in which in a circumferential groove alternately blades and spacers, which are preferably made of rubber, are mounted. This should dampen blade vibrations of the blades. However, high temperatures do not withstand these rubber spacers.

Ähnliches gilt für die in US-A-4 743 166 beschriebenen Turbomaschinen, bei denen zur Verhinderung von Leckageluft unter der Schaufelplattform und zwischen den Schaufelfüssen Dichtelemente aus Kunststoff angeordnet sind.The same applies to the in US-A-4,743,166 described turbomachinery in which are arranged to prevent leakage of air under the blade platform and between the blade roots sealing elements made of plastic.

Schliesslich sind aus US-A-2 327 839 Dampf- und Gasturbinen bekannt, bei denen der Rotor aus einem niedriglegiertem Baustahl besteht, die Schaufeln aus hochlegierten austenistischen Stählen und die Zwischenstücke aus hochlegierten Cr- oder Ni-Stählen, um unterschiedliche Längenausdehnungen und damit permanente Deformationen und ein Lockern der Schaufeln zu verhindern.Finally are off US-A-2 327 839 Steam and gas turbines are known in which the rotor consists of a low-alloyed structural steel, the blades of high-alloy austenitic steels and the intermediate pieces of high-alloy Cr or Ni steels to prevent different linear expansion and thus permanent deformation and loosening of the blades.

Darstellung der ErfindungPresentation of the invention

Ziel der Erfindung ist es, die genannten Nachteile des Standes der Technik zu vermeiden. Der Erfindung liegt die Aufgabe zu Grunde, eine thermische Turbomaschine zu entwickeln, bei welcher aufgrund eines reduzierten Gewichtes die Lebensdauer des Rotors erhöht wird.The aim of the invention is to avoid the mentioned disadvantages of the prior art. The invention is based on the object to develop a thermal turbomachine, in which due to a reduced weight, the life of the rotor is increased.

Erfindungsgemäss wird diese Aufgabe bei einer thermische Turbomaschine gemäss Oberbegriff des Patentanspruches 1 dadurch gelöst, dass die Zwischenstücke zwischen den Laufschaufeln einer Schaufelreihe aus intermetallischen Verbindungen bestehen.According to the invention this object is achieved in a thermal turbomachine according to the preamble of claim 1, characterized in that the intermediate pieces between the blades of a blade row consist of intermetallic compounds.

Die Vorteile der Erfindung bestehen darin, dass dadurch einerseits das Gewicht des Rotors reduziert wird, und andererseits die Sprödigkeit der intermetallischen Zwischenstücke kein erhöhtes Risiko für den Betrieb der Maschine bedeutet.The advantages of the invention are that on the one hand, the weight of the rotor is reduced, and on the other hand, the brittleness of the intermetallic spacers no increased risk for the operation of the machine means.

Es ist vorteilhaft, wenn die Zwischenstücke aus einer intermetallischen γ-TiAl-Verbindung oder einer intermetallischen orthorhombischen TiAl-Verbindung bestehen, weil dieser erfindungsgemässe Werkstoffeinsatz zu einer beachtlichen Gewichtsreduktion des Rotors führt. Die spezifische Dichte der intermetallischen Titan-Aluminid-Verbindungen beträgt nur ca. 50 % der Dichte von rostfreiem Cr-Ni-W-Stahl.It is advantageous if the intermediate pieces consist of an intermetallic γ-TiAl compound or an intermetallic orthorhombic TiAl compound, because this inventive use of material leads to a considerable weight reduction of the rotor. The specific gravity of titanium-aluminide intermetallic compounds is only about 50% of that of stainless Cr-Ni-W steel.

Kurze Beschreibung der ZeichnungenBrief description of the drawings

In der Zeichnung ist ein Ausführungsbeispiel der Erfindung dargestellt. Die einzige Figur zeigt einen Querschnitt durch den erfindungsgemässen Rotor eines Hochdruckverdichters für eine Gasturbine.In the drawing, an embodiment of the invention is shown. The single FIGURE shows a cross section through the rotor according to the invention of a high-pressure compressor for a gas turbine.

Wege zur Ausführung der ErfindungWays to carry out the invention

Nachfolgend wird die Erfindung anhand eines Ausführungsbeispieles und der Figur 1 näher erläutert.Hereinafter, the invention with reference to an embodiment and the FIG. 1 explained in more detail.

Fig. 1 zeigt einen Querschnitt durch eine Laufschaufelreihe eines Rotors 1 für einen Hochdruckverdichter einer Gasturbine. Der Rotor 1 ist von einem Stator 2 umgeben. In den Rotor 1 sind in einer sich darin befindenden Umfangsnut Laufschaufeln 3, 3' montiert, während im Stator 2 Leitschaufeln 5 eingehängt sind. Die Schaufeln 3, 3', 5 werden beispielsweise bei einem Druck von ca. 32 bar mehreren Tausend Stunden lang einer Temperatur von ca. 600 °C ausgesetzt. Sie bestehen aus einem rostfreien Cr-Ni-W-Stahl mit folgender chemischer Zusammensetzung (in Gew.- %): 0.12 C, < 0.8 Si, < 1.0 Mn, 17 Cr, 14.5 Ni, < 0.5 Mo, 3.3 W, < 1 Ti, < 0.045 P, <0.03 S, Rest Fe. Die Welle des Rotors 1 besteht ebenfalls aus Stahl. Die Dichte von Stahl beträgt ca. 7,9 g/cm3. Fig. 1 shows a cross section through a blade row of a rotor 1 for a high-pressure compressor of a gas turbine. The rotor 1 is surrounded by a stator 2. In the rotor 1 in a circumferential groove located therein blades 3, 3 'are mounted, while in the stator 2 vanes 5 are mounted. For example, the blades 3, 3 ', 5 are exposed to a temperature of approximately 600 ° C. for several thousand hours at a pressure of approximately 32 bar. They consist of a stainless Cr-Ni-W steel with the following chemical composition (in% by weight): 0.12 C, <0.8 Si, <1.0 Mn, 17 Cr, 14.5 Ni, <0.5 Mo, 3.3 W, <1 Ti, <0.045 P, <0.03 S, balance Fe. The shaft of the rotor 1 is also made of steel. The density of steel is about 7.9 g / cm 3 .

Zwischen zwei benachbarten Laufschaufeln 3 und 3' sind in einer Schaufelreihe des Rotors 1 jeweils Zwischenstücke 4 in die Umfangsnut des Rotors 1 montiert. Erfindungsgemäss sind diese Zwischenstücke 4 aus einer intermetallischen Verbindung, hier aus einer γ-Titan-Aluminid-Verbindung hergestellt.Between two adjacent blades 3 and 3 ', intermediate pieces 4 are respectively mounted in the circumferential groove of the rotor 1 in a blade row of the rotor 1. According to the invention, these intermediate pieces 4 are made of an intermetallic compound, here of a γ-titanium-aluminide compound.

Diese für die Herstellung der Zwischenstücke 4 verwendete intermetallische Verbindung hat folgende chemische Zusammensetzung (in Gew.- %): Ti-(30.5-31.5)Al-(8.9-9.5)W-(0.3-0.4)Si.This intermetallic compound used for the production of the intermediate pieces 4 has the following chemical composition (in% by weight): Ti (30.5-31.5) Al- (8.9-9.5) W- (0.3-0.4) Si.

Intermetallische Verbindungen des Titans mit dem Aluminium haben einige interessante Eigenschaften, welche sie als Konstruktionswerkstoffe im mittleren und höheren Temperaturbereich als attraktiv erscheinen lassen. Dazu gehört ihre gegenüber Superlegierungen und gegenüber rostfreien Stählen niedrigere Dichte. Ihrer technischen Verwertbarkeit steht aber in der vorliegenden Form oft ihre Sprödigkeit entgegen.Titanium-metal intermetallic compounds with aluminum have some interesting properties that make them attractive as engineering materials in the medium and higher temperature range. These include their lower compared to superalloys and lower than stainless steels. However, their technical usability often stands in the way of their brittleness.

Die oben beschriebene intermetallische γ-Titan-Aluminid-Verbindung zeichnet sich durch eine etwa um 50 % geringere Dichte aus als der bei diesem Ausführungsbeispiel für den Rotor und die Schaufeln benutzte Stahl. Weiterhin weist sie einen E-Modul bei Raumtemperatur von 171 GPa und eine Wärmeleitfähigkeit λ von 24 W/mK.The γ-titanium-aluminide intermetallic compound described above is characterized by about 50% lower density than the steel used in this embodiment for the rotor and the blades. Furthermore, it has an E-modulus at room temperature of 171 GPa and a thermal conductivity λ of 24 W / mK.

In Tabelle 1 sind weitere physikalischen Eigenschaften der beiden Legierungen gegenübergestellt. Tabelle 1: Physikalische Eigenschaften der verschiedenen Werkstoffe Dichte in g/cm3 Wärmeausdehnungskoeffizient in K-1 γ-Ti-Al 4 10 x 10-6 Rostfreier Stahl 7.9 18.6 x 10-6 Table 1 compares further physical properties of the two alloys. Table 1: Physical properties of the different materials Density in g / cm 3 Thermal expansion coefficient in K -1 γ-Ti-Al 4 10x10 -6 Stainless steel 7.9 18.6 x 10 -6

Da die rotierenden Bauteile des Hochdruckverdichters einer Gasturbinenanlage bei Temperaturen bis zu ca. 600 °C stark beansprucht werden, wirkt sich die Gewichtsreduktion des erfindungsgemässen Rotors vorteilhaft auf eine Erhöhung der Lebensdauer der Maschine aus.Since the rotating components of the high pressure compressor of a gas turbine plant are stressed at temperatures up to about 600 ° C, the weight reduction of the inventive rotor has an advantageous effect on increasing the life of the machine.

Die Herstellung der intermetallischen Zwischenstücke erfolgt in bekannter Weise durch Giessen, heiss-isostatisches Pressen und Wärmebehandlung mit einer minimalen maschinellen Nachbearbeitung.The production of intermetallic spacers is carried out in a known manner by casting, hot-isostatic pressing and heat treatment with a minimum of mechanical post-processing.

Selbstverständlich ist die Erfindung nicht auf das beschriebene Ausführungsbeispiel beschränkt.Of course, the invention is not limited to the embodiment described.

Das Zwischenstück 4 des Hochdruckverdichters kann beispielsweise auch aus einer bekannten intermetallischen orthorhombischen Titan-Aluminid-Legierung mit einer Dichte von 4.55 g/cm3 hergestellt sein. Orthorhombische Titan-Aluminid-Legierungen basieren auf der geordneten Verbindung Ti2AlNb und haben folgende chemische Zusammensetzung: Ti-(22-27)Al-(21-27)Nb. Auch die erfindungsgemässe Verwendung einer Titan-Hochtemperaturlegierung, welche beispielsweise folgende chemische Zusammensetzung hat (Angaben in Gew.- %): 0.06 C, 0.4 Si, 5.8 Al, 4 Sn, 4 Zr, 0.5 Mo, < 0.05 Fe, 0.11 O, < 0.03 N, < 0.006 H, Rest Ti, ist denkbar.The intermediate piece 4 of the high-pressure compressor may, for example, also be made of a known intermetallic orthorhombic titanium-aluminide alloy with a density of 4.55 g / cm 3 . Orthorhombic titanium aluminide alloys are based on the ordered compound Ti 2 AlNb and have the following chemical composition: Ti (22-27) Al- (21-27) Nb. The inventive use of a titanium high-temperature alloy, which has, for example, the following chemical composition (in% by weight): 0.06 C, 0.4 Si, 5.8 Al, 4 Sn, 4 Zr, 0.5 Mo, <0.05 Fe, 0.11 O, < 0.03 N, <0.006 H, remainder Ti, is conceivable.

Weiterhin ist es möglich, die Erfindung nicht nur für Hochdruckverdichterrotoren einzusetzen, sondern auch für Turbinenrotoren mit Turbinenschaufeln aus einer Superlegierung, beispielsweise einer Nickel-Basis-Superlegierung, bei denen die Zwischenstücke zwischen den Laufschaufeln beispielsweise aus einer intermetallischen γ -Titan-Aluminid-Legierung oder einer intermetallischen orthorhombischen Titan-Aluminid-Legierung bestehen. Auch damit lassen sich vorteilhaft Gewichtsreduktionen und eine Erhöhung die Lebensdauer der Maschine erreichen.Furthermore, it is possible to use the invention not only for high-pressure compressor rotors, but also for turbine rotors with turbine blades made of a superalloy, for example a nickel-based superalloy, in which the intermediate pieces between the blades, for example of a γ-titanium-aluminide intermetallic alloy or an intermetallic orthorhombic titanium-aluminide alloy. This can also be advantageous to achieve weight reductions and increase the life of the machine.

Für den beschriebenen erfindungsgemässen Einsatz der intermetallischen Ti-AI-Legierungen spielt ihre Sprödigkeit keine nachteilige Rolle, da sie als Zwischenstücke keinem Schleifkontakt bzw. keinem Reibverschleiss ausgesetzt sind.Their brittleness does not play a disadvantageous role for the described use according to the invention of the Ti-Al intermetallic alloys, since they are not exposed to any sliding contact or frictional wear as intermediate pieces.

BezugszeichenlisteLIST OF REFERENCE NUMBERS

11
Rotorrotor
22
Statorstator
3, 3'3, 3 '
Laufschaufelblade
44
Zwischenstückconnecting piece
55
Leitschaufelvane
D1 D 1
Dichte des RotormaterialsDensity of the rotor material
D2 D 2
Dichte des ZwischenstückesDensity of the intermediate piece

Claims (4)

  1. Axial-flow thermal turbomachine, having a rotor (1) made of a metallic material with a first density (D1), in which rotor blades (3, 3') and intermediate pieces (4) are mounted alternately in a circumferential groove, wherein said intermediate pieces (4) consist of a material with a second density (D2), which is lower than the first density (D1) characterized in that the material having the second density (D2) is an intermetallic compound.
  2. Turbomachine according to Claim 1, characterized in that the intermetallic compound is a γ-titanium aluminide alloy or an orthorhombic titanium aluminide alloy.
  3. Turbomachine according to Claim 2, characterized in that the γ-titanium aluminide alloy has the following chemical composition (details in % by weight): Ti-(30.5-31.5)Al-(8.9-9.5)W-(0.3-0.4)Si.
  4. Turbomachine according to one of Claims 1 to 3, characterized in that the turbomachine is a high-pressure compressor of a gas turbine having a rotor (1) which substantially comprises a stainless Cr-Ni steel.
EP04101054.7A 2003-03-26 2004-03-15 Axial-flow thermal turbomachine Expired - Lifetime EP1462614B1 (en)

Applications Claiming Priority (2)

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DE10313490A DE10313490A1 (en) 2003-03-26 2003-03-26 Thermal turbomachine with axial flow
DE10313490 2003-03-26

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EP1902160B1 (en) * 2005-07-12 2009-03-18 Alstom Technology Ltd Ceramic heat insulating layer
DE102009030398A1 (en) * 2009-06-25 2010-12-30 Mtu Aero Engines Gmbh Method for producing and / or repairing a blade for a turbomachine
SG11201503276PA (en) 2012-12-14 2015-06-29 United Technologies Corp Hybrid turbine blade for improved engine performance or architecture
EP2931458B1 (en) 2012-12-14 2019-02-06 United Technologies Corporation Multi-shot casting

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DE513407C (en) 1926-11-02 1930-11-27 Conservenfabrik Und Trocknungs Method for drying fruit juices
US2327839A (en) * 1940-03-26 1943-08-24 Bbc Brown Boveri & Cie Turbine construction
GB750397A (en) * 1951-12-10 1956-06-13 Power Jets Res & Dev Ltd Damped turbine and dynamic compressor blades
US2857134A (en) * 1954-03-17 1958-10-21 Parsons C A & Co Ltd Assembly of blades for turbines and the like
DE1426816A1 (en) * 1963-07-02 1969-03-13 Licentia Gmbh Method for producing a blade ring of an axial flow machine, in particular an axial compressor
JPS57168005A (en) * 1981-04-10 1982-10-16 Hitachi Ltd Rotor structue for axial machines
US4743166A (en) * 1984-12-20 1988-05-10 General Electric Company Blade root seal
DE3789776T2 (en) * 1986-02-05 1994-08-18 Hitachi Ltd Heat-resistant steel and gas turbine parts made from it.
EP0513407B1 (en) * 1991-05-13 1995-07-19 Asea Brown Boveri Ag Method of manufacture of a turbine blade
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GB9606963D0 (en) * 1996-04-02 1996-06-05 Rolls Royce Plc A root attachment for a turbomachine blade
DE19751129C1 (en) 1997-11-19 1999-06-17 Mtu Muenchen Gmbh FAN rotor blade for an engine
DE10110102C2 (en) 2000-12-18 2002-12-05 Deutsch Zentr Luft & Raumfahrt rotor blade

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US7037079B2 (en) 2006-05-02
EP1462614A2 (en) 2004-09-29
US20060062674A1 (en) 2006-03-23
DE10313490A1 (en) 2004-10-14
EP1462614A3 (en) 2006-11-15
JP2004293549A (en) 2004-10-21

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