EP2692989A2 - Low modulus gas turbine compressor blade - Google Patents

Low modulus gas turbine compressor blade Download PDF

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Publication number
EP2692989A2
EP2692989A2 EP13003790.6A EP13003790A EP2692989A2 EP 2692989 A2 EP2692989 A2 EP 2692989A2 EP 13003790 A EP13003790 A EP 13003790A EP 2692989 A2 EP2692989 A2 EP 2692989A2
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EP
European Patent Office
Prior art keywords
blade
compressor
compressor blade
leading edge
modulus
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.)
Withdrawn
Application number
EP13003790.6A
Other languages
German (de)
French (fr)
Other versions
EP2692989A3 (en
Inventor
Karl Schreiber
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Rolls Royce Deutschland Ltd and Co KG
Rolls Royce PLC
Original Assignee
Rolls Royce Deutschland Ltd and Co KG
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Rolls Royce Deutschland Ltd and Co KG filed Critical Rolls Royce Deutschland Ltd and Co KG
Publication of EP2692989A2 publication Critical patent/EP2692989A2/en
Publication of EP2692989A3 publication Critical patent/EP2692989A3/en
Withdrawn legal-status Critical Current

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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
    • 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
    • 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
    • F01D5/288—Protective coatings for blades
    • 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
    • F05D2240/20—Rotors
    • F05D2240/30—Characteristics of rotor blades, i.e. of any element transforming dynamic fluid energy to or from rotational energy and being attached to a rotor
    • F05D2240/303—Characteristics of rotor blades, i.e. of any element transforming dynamic fluid energy to or from rotational energy and being attached to a rotor related to the leading edge of a rotor blade

Definitions

  • the invention relates to a gas turbine compressor blade, in particular an aircraft gas turbine or a stationary turbine, which has an airfoil, which is attached to a blade root.
  • the compressor blade has an inlet edge or leading edge, which is also referred to as the blade leading edge.
  • erosion-resistant materials known from the prior art are unsuitable as materials for compressor blades. Even erosion-resistant coatings prove to be in practice as not suitable because they are effective only at very small particle sizes.
  • the invention has for its object to provide a Fluggasturbinenverêtrschaufel, which has a high erosion resistance with a simple structure and simple, cost manufacturability.
  • At least the region of the leading edge of the compressor blade is made of a material which has a very low modulus of elasticity.
  • a suitable, low modulus of elasticity is on the order of 50 GPa.
  • the compressor blade according to the invention thus has in the region of the leading edge, due to the low modulus of elasticity, a relatively large elasticity, so that an impact of a foreign body, such as a sand particle or stone, by the elasticity of the material in the region of the leading edge does not cause damage , In particular, this results in no or only a very small erosion, compared with the known from the prior art compressor blades.
  • At least the region of the leading edge is made of a titanium alloy of the types Ti 28Nb 1 Fe 0.5Si, Ti-36Nb-2Ta-3Zr-0.30 or Ti-24Nb-4Zr-8Sn.
  • a titanium alloy of the types Ti 28Nb 1 Fe 0.5Si, Ti-36Nb-2Ta-3Zr-0.30 or Ti-24Nb-4Zr-8Sn.
  • the erosion wear can be reduced by about 50% compared to compressor blades, which are made of conventional alloys, such as Ti64.
  • the erosion wear can be reduced by 30%.
  • the entire compressor blade from the o.g. Titanium alloy to produce the low modulus or only produce parts of the compressor blade made of this material.
  • the leading edge is designed in the form of an entry edge element, which is connected to the airfoil of the compressor blade by means of a welding process.
  • a welding process is particularly advantageous.
  • the blade itself can be made according to the invention of one of the usual titanium alloys, for example Ti64, Ti6246 or Ti6242.
  • this preferably extends to just before the blade root, in the direct transition of the blade root, it is not necessary to apply or use the alloy according to the invention.
  • the compressor blade according to the invention which can be designed as a single compressor blade, as a blisk blade or as a fan blade, is thus highly resistant to erosion and damage by foreign bodies.
  • the invention thus also relates to a method for producing a compressor blade, in which an inlet edge element is manufactured separately and connected to the blade by means of a welding process, in particular a laser welding process, wherein the inlet edge element of a low-modulus (with respect to the modulus of elasticity) titanium alloy, for example is made of Ti 28Nb 1 Fe 0.5Si or of or Ti-36Nb-2Ta-3Zr-0.30 or of Ti-24Nb-4Zr-8Sn, and / or an alloy having an E-modulus of substantially 50 to 70 GPa, and wherein the airfoil is made of an alloy known in the art.
  • a low-modulus (with respect to the modulus of elasticity) titanium alloy for example is made of Ti 28Nb 1 Fe 0.5Si or of or Ti-36Nb-2Ta-3Zr-0.30 or of Ti-24Nb-4Zr-8Sn, and / or an alloy having an E-modulus of substantially 50 to 70 GPa, and wherein the airfo
  • the invention also relates to the use of a low-modulus (modulus of elasticity) titanium alloy, for example Ti 28Nb 1 Fe 0.5Si or Ti-36Nb-2Ta-3Zr-0.30 or Ti-24Nb-4Zr-8Sn, in particular for the leading edge region of a compressor blade ,
  • a low-modulus (modulus of elasticity) titanium alloy for example Ti 28Nb 1 Fe 0.5Si or Ti-36Nb-2Ta-3Zr-0.30 or Ti-24Nb-4Zr-8Sn
  • the gas turbine engine 10 is an example of a turbomachine to which the invention may find application. However, it will be understood from the following that the invention can be used with other turbomachinery as well.
  • the engine 10 is conventionally formed and includes in the flow direction one after another an air inlet 11, a fan 12 circulating in a housing, an intermediate pressure compressor 13, a high pressure compressor 14, combustion chambers 15, a high pressure turbine 16, an intermediate pressure turbine 17 and a low pressure turbine 18 and an exhaust nozzle 19, which are all arranged around a central engine axis 1.
  • the intermediate pressure compressor 13 and the high pressure compressor 14 each include a plurality of stages, each of which includes a circumferentially extending array of fixed stationary vanes 20, commonly referred to as stator vanes, that radially inwardly from the engine casing 21 in an annular flow passage through the compressors 13, 14 protrude.
  • the compressors further include an array of compressor blades 22 projecting radially outward from a rotatable drum or disc 26 coupled to hubs 27 of high pressure turbine 16 and intermediate pressure turbine 17, respectively.
  • the turbine sections 16, 17, 18 have similar stages, comprising an array of fixed vanes 23 projecting radially inward from the housing 21 into the annular flow passage through the turbines 16, 17, 18, and a downstream array of turbine blades 24 projecting outwardly from a rotatable hub 27.
  • the compressor drum or compressor disk 26 and the vanes 22 disposed thereon and the turbine rotor hub 27 and the turbine blades 24 disposed thereon rotate about the engine axis 1 during operation.
  • the Fig. 2 shows a schematic side view of a compressor blade according to the invention, which may be a conventional compressor blade, a fan blade or a blisk blade.
  • the blade has, for example, a blade root 31, with which a blade 29 designed in the usual way is connected.
  • an entry edge element 30 is connected by means of a laser weld seam 32.
  • the leading edge element 30 extends to just before the blade root 31, it does not need to be connected directly to the blade root 31.
  • the Fig. 3 shows a diagram of the course of the modulus of elasticity in a schematic manner. It can be seen that the modulus of elasticity of the leading edge element 30 is less than the modulus of elasticity of the blade 29, whereby a soft transition between the lower and the higher modulus of elasticity results in the region of the weld 32.

Abstract

The blade has an airfoil (29) provided with a leading edge (33), where an area of the leading edge is made from a low-modulus titanium alloy e.g. titanium-28 Niobium-1Iron-0.5silicon or titanium-36 Niobium -2Tantalum-3Zirconium-0.3 oxide or titanium-24 Niobium-4 Zirconium-8Tin. The leading edge is connected to the airfoil by a welding process. The area of the leading edge has a modulus of elasticity of substantially 50 to 70 GPa. The airfoil is made from titanium64 or titanium6246 or titanium6242 or Indium 718.

Description

Die Erfindung bezieht sich auf eine Gasturbinenverdichterschaufel, insbesondere auf eine Fluggasturbine oder eine stationäre Turbine, welche ein Schaufelblatt aufweist, welches an einem Schaufelfuß befestigt ist. Die Verdichterschaufel weist eine Eintrittskante oder Anströmkante auf, welche auch als Schaufelvorderkante bezeichnet wird.The invention relates to a gas turbine compressor blade, in particular an aircraft gas turbine or a stationary turbine, which has an airfoil, which is attached to a blade root. The compressor blade has an inlet edge or leading edge, which is also referred to as the blade leading edge.

Bei Fluggasturbinen besteht stets die Problematik, dass die Verdichterschaufeln starker Erosion durch angesaugte Partikel unterworfen sind. Hierbei handelt es sich beispielsweise um Sandkörnchen oder Ähnliches, welche mit hoher Geschwindigkeit auf die Verdichterschaufeln auftreffen.In aircraft gas turbines, there is always the problem that the compressor blades are subject to strong erosion by sucked particles. These are, for example, grains of sand or the like, which impinge on the compressor blades at high speed.

Als Folge der auftretenden Erosion ist es erforderlich, die Verdichterschaufeln auszutauschen oder zu reparieren. Letzteres ist insbesondere bei Blisks technisch sehr aufwändig und kostenintensiv.As a result of the erosion that occurs, it is necessary to replace or repair the compressor blades. The latter is technically very complicated and cost-intensive, especially in the case of blisks.

Die aus dem Stand der Technik bekannten erosionsfesten Werkstoffe sind als Werkstoffe für Verdichterschaufeln ungeeignet. Auch erosionsfeste Beschichtungen erweisen sich in der Praxis als nicht geeignet, da diese nur bei sehr kleinen Partikelgrößen wirksam sind.The erosion-resistant materials known from the prior art are unsuitable as materials for compressor blades. Even erosion-resistant coatings prove to be in practice as not suitable because they are effective only at very small particle sizes.

Der Erfindung liegt die Aufgabe zugrunde, eine Fluggasturbinenverdichterschaufel zu schaffen, welche bei einfachem Aufbau und einfacher, kostengünstiger Herstellbarkeit eine hohe Erosionsbeständigkeit aufweist.The invention has for its object to provide a Fluggasturbinenverdichterschaufel, which has a high erosion resistance with a simple structure and simple, cost manufacturability.

Erfindungsgemäß wird die Aufgabe durch die Merkmalskombination des Anspruchs 1 gelöst, die Unteransprüche zeigen weitere vorteilhafte Ausgestaltungen der Erfindung.According to the invention the object is achieved by the combination of features of claim 1, the dependent claims show further advantageous embodiments of the invention.

Erfindungsgemäß ist vorgesehen, dass zumindest der Bereich der Eintrittskante der Verdichterschaufel aus einem Werkstoff gefertigt ist, welcher einen sehr geringen E-Modul aufweist. Ein geeigneter, geringer E-Modul liegt in der Größenordnung von 50 GPa.According to the invention it is provided that at least the region of the leading edge of the compressor blade is made of a material which has a very low modulus of elasticity. A suitable, low modulus of elasticity is on the order of 50 GPa.

Die erfindungsgemäße Verdichterschaufel weist somit im Bereich der Eintrittskante, bedingt durch den geringen E-Modul, eine relativ große Elastizität auf, so dass ein Aufprall eines Fremdkörpers, beispielsweise eines Sandpartikels oder Steins, durch die Elastizität des Materials im Bereich der Eintrittskante nicht zu Beschädigungen führt. Insbesondere tritt damit keine oder nur eine sehr geringe Erosion auf, verglichen mit dem aus dem Stand der Technik bekannten Verdichterschaufeln.The compressor blade according to the invention thus has in the region of the leading edge, due to the low modulus of elasticity, a relatively large elasticity, so that an impact of a foreign body, such as a sand particle or stone, by the elasticity of the material in the region of the leading edge does not cause damage , In particular, this results in no or only a very small erosion, compared with the known from the prior art compressor blades.

Erfindungsgemäß ist es besonders vorteilhaft, wenn zumindest der Bereich der Eintrittskante aus einer Titanlegierung der Typen Ti 28Nb 1 Fe 0,5Si, Ti-36Nb-2Ta-3Zr-0.30 oder Ti-24Nb-4Zr-8Sn gefertigt sind. Mittels einer derartigen Legierung kann beispielsweise der Erosionsverschleiß um ca. 50 % verringert werden als bei Verdichterschaufeln, die aus gebräuchlichen Legierungen, beispielsweise Ti64 gefertigt sind. Gegenüber aus dem Stand der Technik bekannten Verdichterschaufeln aus Nickel-Basislegierungen, beispielsweise IN718, kann der Erosionsverschleiß um 30 % gesenkt werden.According to the invention, it is particularly advantageous if at least the region of the leading edge is made of a titanium alloy of the types Ti 28Nb 1 Fe 0.5Si, Ti-36Nb-2Ta-3Zr-0.30 or Ti-24Nb-4Zr-8Sn. By means of such an alloy, for example, the erosion wear can be reduced by about 50% compared to compressor blades, which are made of conventional alloys, such as Ti64. Compared to known from the prior art compressor blades made of nickel-based alloys, such as IN718, the erosion wear can be reduced by 30%.

Erfindungsgemäß ist es möglich, entweder die gesamte Verdichterschaufel aus der o.g. Titanlegierung mit dem geringen E-Modul zu fertigen oder lediglich Teile der Verdichterschaufel aus diesem Werkstoff herzustellen.According to the invention, it is possible either the entire compressor blade from the o.g. Titanium alloy to produce the low modulus or only produce parts of the compressor blade made of this material.

In einer besonders günstigen Ausgestaltung der Erfindung ist vorgesehen, dass die Eintrittskante in Form eines Eintrittskantenelements ausgebildet ist, welches mit dem Schaufelblatt der Verdichterschaufel mittels eines Schweißverfahrens verbunden ist. Besonders vorteilhaft ist die Verwendung eines Laserschweißverfahrens.In a particularly favorable embodiment of the invention, it is provided that the leading edge is designed in the form of an entry edge element, which is connected to the airfoil of the compressor blade by means of a welding process. Particularly advantageous is the use of a laser welding process.

Das Schaufelblatt selbst kann erfindungsgemäß aus einer der übliche Titanlegierungen hergestellt werden, beispielsweise Ti64, Ti6246 oder Ti6242.The blade itself can be made according to the invention of one of the usual titanium alloys, for example Ti64, Ti6246 or Ti6242.

Bei Ausbildung eines separaten Eintrittskantenelements erstreckt sich dieses bevorzugterweise bis kurz vor den Schaufelfuß, im direkten Übergang des Schaufelfußes ist es nicht erforderlich, die erfindungsgemäße Legierung aufzubringen oder einzusetzen.When forming a separate entrance edge element, this preferably extends to just before the blade root, in the direct transition of the blade root, it is not necessary to apply or use the alloy according to the invention.

Bei einer separaten Fertigung des erfindungsgemäßen Eintrittskantenelements und der Verbindung mittels eines Laserschweißverfahrens ergibt sich der Vorteil, dass sich durch die thermische Beeinflussung während des Laserschweißvorgangs ein weicher Übergang zwischen dem niedrigen E-Modul des Eintrittskantenelements und dem höheren E-Modul des Materials des restlichen Schaufelblattes ergibt. Es ergibt sich somit ein gradierter Übergang der elastischen Eigenschaften, welcher sich vorteilhaft auf das gesamte Bauteilverhalten der Verdichterschaufel auswirkt. Dieser Effekt beruht auf der Tatsache, dass bei Erwärmung der niedermoduligen Titanlegierung in Temperaturbereiche oberhalb ca. 500°C der E- Modul wieder auf Werte herkömmlicher Titanlegierungen ansteigt, und somit der unmittelbare Schweißnahtbereich homogen verläuft.In the case of a separate production of the entry edge element according to the invention and the connection by means of a laser welding process, there is the advantage that a soft transition between the low modulus of elasticity of the entry edge element and the higher modulus of elasticity of the material of the remaining airfoil results from the thermal influence during the laser welding process , This results in a graded transition of the elastic properties, which has an advantageous effect on the entire component behavior of the compressor blade. This effect is based on the fact that when heating the low-modulus titanium alloy in temperature ranges above about 500 ° C, the modulus of elasticity increases again to the values of conventional titanium alloys, and thus the immediate weld area is homogeneous.

Die erfindungsgemäße Verdichterschaufel, welche als einzelne Kompressorschaufel, als Blisk-Schaufel oder als Fan-Schaufel ausgebildet sein kann, ist somit in hohem Maße beständig gegen Erosion und Beschädigungen durch Fremdkörper.The compressor blade according to the invention, which can be designed as a single compressor blade, as a blisk blade or as a fan blade, is thus highly resistant to erosion and damage by foreign bodies.

Die Erfindung bezieht sich somit auch auf ein Verfahren zur Herstellung einer Verdichterschaufel, bei welchem ein Eintrittskantenelement separat gefertigt und mit dem Schaufelblatt mittels eines Schweißverfahrens, insbesondere eines Laserschweißverfahrens verbunden wird, wobei das Eintrittskantenelement aus einer niedermoduligen (bezüglich des E-Moduls) Titanlegierung, beispielsweise aus Ti 28Nb 1 Fe 0,5Si oder aus oder Ti-36Nb-2Ta-3Zr-0.30 oder aus Ti-24Nb-4Zr-8Sn, und/oder einer Legierung mit einem E-Modul von im Wesentlichen 50 bis 70 GPa gefertigt ist und wobei das Schaufelblatt aus einer nach dem Stand der Technik bekannten Legierung gefertigt ist.The invention thus also relates to a method for producing a compressor blade, in which an inlet edge element is manufactured separately and connected to the blade by means of a welding process, in particular a laser welding process, wherein the inlet edge element of a low-modulus (with respect to the modulus of elasticity) titanium alloy, for example is made of Ti 28Nb 1 Fe 0.5Si or of or Ti-36Nb-2Ta-3Zr-0.30 or of Ti-24Nb-4Zr-8Sn, and / or an alloy having an E-modulus of substantially 50 to 70 GPa, and wherein the airfoil is made of an alloy known in the art.

Die Erfindung bezieht sich auch auf die Verwendung einer niedermoduligen (E-Modul) Titanlegierung, beispielsweise Ti 28Nb 1 Fe 0,5Si oder Ti-36Nb-2Ta-3Zr-0.30 oder Ti-24Nb-4Zr-8Sn, insbesondere für den Eintrittskantenbereich einer Verdichterschaufel.The invention also relates to the use of a low-modulus (modulus of elasticity) titanium alloy, for example Ti 28Nb 1 Fe 0.5Si or Ti-36Nb-2Ta-3Zr-0.30 or Ti-24Nb-4Zr-8Sn, in particular for the leading edge region of a compressor blade ,

Im Folgenden wird die Erfindung anhand eines Ausführungsbeispiels in Verbindung mit der Zeichnung beschrieben. Dabei zeigt:

Fig. 1
eine schematische Darstellung eines Gasturbinentriebwerks gemäß der vorliegenden Erfindung,
Fig. 2
eine schematische Seitenansicht einer erfindungsgemäßen Verdichterschaufel, und
Fig. 3
eine Darstellung des Verlaufs des E-Moduls über die Schaufellänge.
In the following the invention will be described by means of an embodiment in conjunction with the drawing. Showing:
Fig. 1
a schematic representation of a gas turbine engine according to the present invention,
Fig. 2
a schematic side view of a compressor blade according to the invention, and
Fig. 3
a representation of the course of the modulus of elasticity over the blade length.

Das Gasturbinentriebwerk 10 gemäß Fig. 1 ist ein Beispiel einer Turbomaschine, bei der die Erfindung Anwendung finden kann. Aus dem Folgenden wird jedoch klar, dass die Erfindung auch bei anderen Turbomaschinen verwendet werden kann. Das Triebwerk 10 ist in herkömmlicher Weise ausgebildet und umfasst in Strömungsrichtung hintereinander einen Lufteinlass 11, einen in einem Gehäuse umlaufenden Fan 12, einen Zwischendruckkompressor 13, einen Hochdruckkompressor 14, Brennkammern 15, eine Hochdruckturbine 16, eine Zwischendruckturbine 17 und eine Niederdruckturbine 18 sowie eine Abgasdüse 19, die sämtlich um eine zentrale Triebwerksachse 1 angeordnet sind.The gas turbine engine 10 according to Fig. 1 is an example of a turbomachine to which the invention may find application. However, it will be understood from the following that the invention can be used with other turbomachinery as well. The engine 10 is conventionally formed and includes in the flow direction one after another an air inlet 11, a fan 12 circulating in a housing, an intermediate pressure compressor 13, a high pressure compressor 14, combustion chambers 15, a high pressure turbine 16, an intermediate pressure turbine 17 and a low pressure turbine 18 and an exhaust nozzle 19, which are all arranged around a central engine axis 1.

Der Zwischendruckkompressor 13 und der Hochdruckkompressor 14 umfassen jeweils mehrere Stufen, von denen jede eine in Umfangsrichtung verlaufende Anordnung fester stationärer Leitschaufeln 20 aufweist, die allgemein als Statorschaufeln bezeichnet werden und die radial nach innen vom Triebwerksgehäuse 21 in einem ringförmigen Strömungskanal durch die Kompressoren 13, 14 vorstehen. Die Kompressoren weisen weiter eine Anordnung von Kompressorlaufschaufeln 22 auf, die radial nach außen von einer drehbaren Trommel oder Scheibe 26 vorstehen, die mit Naben 27 der Hochdruckturbine 16 bzw. der Zwischendruckturbine 17 gekoppelt sind.The intermediate pressure compressor 13 and the high pressure compressor 14 each include a plurality of stages, each of which includes a circumferentially extending array of fixed stationary vanes 20, commonly referred to as stator vanes, that radially inwardly from the engine casing 21 in an annular flow passage through the compressors 13, 14 protrude. The compressors further include an array of compressor blades 22 projecting radially outward from a rotatable drum or disc 26 coupled to hubs 27 of high pressure turbine 16 and intermediate pressure turbine 17, respectively.

Die Turbinenabschnitte 16, 17, 18 weisen ähnliche Stufen auf, umfassend eine Anordnung von festen Leitschaufeln 23, die radial nach innen vom Gehäuse 21 in den ringförmigen Strömungskanal durch die Turbinen 16, 17, 18 vorstehen, und eine nachfolgende Anordnung von Turbinenschaufeln 24, die nach außen von einer drehbaren Nabe 27 vorstehen. Die Kompressortrommel oder Kompressorscheibe 26 und die darauf angeordneten Schaufeln 22 sowie die Turbinenrotornabe 27 und die darauf angeordneten Turbinenlaufschaufeln 24 drehen sich im Betrieb um die Triebwerksachse 1.The turbine sections 16, 17, 18 have similar stages, comprising an array of fixed vanes 23 projecting radially inward from the housing 21 into the annular flow passage through the turbines 16, 17, 18, and a downstream array of turbine blades 24 projecting outwardly from a rotatable hub 27. The compressor drum or compressor disk 26 and the vanes 22 disposed thereon and the turbine rotor hub 27 and the turbine blades 24 disposed thereon rotate about the engine axis 1 during operation.

Die Fig. 2 zeigt eine schematische Seitenansicht einer erfindungsgemäßen Verdichterschaufel, welche eine übliche Kompressorschaufel, eine Fan-Schaufel oder eine Blisk-Schaufel sein kann. Die Schaufel weist beispielsweise einen Schaufelfuß 31 auf, mit welchem ein in üblicher Weise ausgebildetes Schaufelblatt 29 verbunden ist. Im Bereich einer Eintrittskante oder Anströmkante ist ein Eintrittskantenelement 30 mittels einer Laser-Schweißnaht 32 verbunden. Das Eintrittskantenelement 30 erstreckt sich bis kurz vor den Schaufelfuß 31, es braucht nicht direkt mit dem Schaufelfuß 31 verbunden werden.The Fig. 2 shows a schematic side view of a compressor blade according to the invention, which may be a conventional compressor blade, a fan blade or a blisk blade. The blade has, for example, a blade root 31, with which a blade 29 designed in the usual way is connected. In the region of an entry edge or leading edge, an entry edge element 30 is connected by means of a laser weld seam 32. The leading edge element 30 extends to just before the blade root 31, it does not need to be connected directly to the blade root 31.

Die Fig. 3 zeigt eine Darstellung des Verlaufs des E-Moduls in schematischer Weise. Daraus ist ersichtlich, dass der E-Modul des Eintrittskantenelements 30 geringer ist als der E-Modul des Schaufelblatts 29, wobei sich im Bereich der Schweißnaht 32 ein weicher Übergang zwischen dem niedrigeren und dem höheren E-Modul ergibt.The Fig. 3 shows a diagram of the course of the modulus of elasticity in a schematic manner. It can be seen that the modulus of elasticity of the leading edge element 30 is less than the modulus of elasticity of the blade 29, whereby a soft transition between the lower and the higher modulus of elasticity results in the region of the weld 32.

Bezugszeichenliste:LIST OF REFERENCE NUMBERS

11
TriebwerksachseEngine axis
1010
Gasturbinentriebwerk / KerntriebwerkGas turbine engine / core engine
1111
Lufteinlassair intake
1212
Fanfan
1313
Mitteldruckkompressor (Verdichter)Medium pressure compressor (compressor)
1414
HochdruckkompressorHigh pressure compressor
1515
Brennkammerncombustors
1616
HochdruckturbineHigh-pressure turbine
1717
MitteldruckturbineIntermediate pressure turbine
1818
NiederdruckturbineLow-pressure turbine
1919
Abgasdüseexhaust nozzle
2020
Leitschaufelnvanes
2121
TriebwerksgehäuseEngine casing
2222
KompressorlaufschaufelnCompressor blades
2323
Leitschaufelnvanes
2424
Turbinenschaufelnturbine blades
2626
Kompressortrommel oder -scheibeCompressor drum or disc
2727
TurbinenrotornabeTurbinenrotornabe
2828
Auslasskonusoutlet cone
2929
Schaufelblattairfoil
3030
EintrittskantenelementLeading edge element
3131
Schaufelfußblade
3232
SchweißnahtWeld
3333
Eintrittskanteleading edge

Claims (9)

Gasturbinenverdichterschaufel mit einem Schaufelblatt (29) mit einer Eintrittskante (33), wobei zumindest der Bereich der Eintrittskante (33) aus einer niedermoduligen Titanlegierung gefertigt ist.A gas turbine compressor blade having an airfoil (29) with an entry edge (33), wherein at least the region of the entry edge (33) is made of a low modulus titanium alloy. Verdichterschaufel nach Anspruch 1, dadurch gekennzeichnet, dass zumindest der Bereich der Eintrittskante aus Ti 28Nb 1 Fe 0,5Si oder Ti-36Nb-2Ta-3Zr-0.30 oder Ti-24Nb-4Zr-8Sn gefertigt ist.Compressor blade according to claim 1, characterized in that at least the region of the leading edge of Ti 28Nb 1 Fe 0.5Si or Ti-36Nb-2Ta-3Zr-0.30 or Ti-24Nb-4Zr-8Sn is made. Verdichterschaufel nach Anspruch 1 oder 2, dadurch gekennzeichnet, dass die Eintrittskante in Form eines Eintrittskantenelements (30) ausgebildet ist, welches mittels eines Schweißverfahrens mit dem Schaufelblatt (29) verbunden ist.Compressor blade according to claim 1 or 2, characterized in that the inlet edge is formed in the form of an inlet edge element (30), which is connected by means of a welding process with the blade (29). Verdichterschaufel nach Anspruch 3, dadurch gekennzeichnet, dass das Eintrittskantenelement (30) mittels eines Laserschweißverfahrens mit dem Schaufelblatt verbunden ist.Compressor blade according to claim 3, characterized in that the inlet edge element (30) is connected to the blade by means of a laser welding process. Verdichterschaufel nach einem der Ansprüche 1 bis 4, dadurch gekennzeichnet, dass der Bereich der Eintrittskante (33) einen E-Modul von im Wesentlichen 50 bis 70 GPa aufweist.Compressor blade according to one of claims 1 to 4, characterized in that the region of the leading edge (33) has an E-modulus of substantially 50 to 70 GPa. Verdichterschaufel nach einem der Ansprüche 1 bis 5, dadurch gekennzeichnet, dass das Schaufelblatt aus Ti64 oder Ti6246 oder Ti6242 oder IN718 gefertigt ist.Compressor blade according to one of claims 1 to 5, characterized in that the blade is made of Ti64 or Ti6246 or Ti6242 or IN718. Verdichterschaufel nach einem der Ansprüche 1 bis 6, dadurch gekennzeichnet, dass die Verdichterschaufel in Form einer Kompressorschaufel ausgebildet ist.Compressor blade according to one of claims 1 to 6, characterized in that the compressor blade is formed in the form of a compressor blade. Verdichterschaufel nach einem der Ansprüche 1 bis 6, dadurch gekennzeichnet, dass die Verdichterschaufel in Form einer Fan-Schaufel ausgebildet ist.Compressor blade according to one of claims 1 to 6, characterized in that the compressor blade is designed in the form of a fan blade. Verdichterschaufel nach einem der Ansprüche 1 bis 6, dadurch gekennzeichnet, dass diese in Form einer Blisk-Schaufel ausgebildet ist.Compressor blade according to one of claims 1 to 6, characterized in that it is designed in the form of a blisk blade.
EP13003790.6A 2012-07-30 2013-07-30 Low modulus gas turbine compressor blade Withdrawn EP2692989A3 (en)

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Families Citing this family (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
AT516259B1 (en) 2014-11-03 2016-04-15 Zizala Lichtsysteme Gmbh Lighting system for a motor vehicle
DE102015002341A1 (en) * 2015-02-24 2016-08-25 GM Global Technology Operations LLC (n. d. Ges. d. Staates Delaware) Headlight for a motor vehicle
US10227032B2 (en) * 2016-07-01 2019-03-12 Ford Global Technologies, Llc Vehicle headlamp alignment system and method

Family Cites Families (16)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5509933A (en) * 1989-12-21 1996-04-23 Smith & Nephew Richards, Inc. Medical implants of hot worked, high strength, biocompatible, low modulus titanium alloys
US5320487A (en) * 1993-01-19 1994-06-14 General Electric Company Spring clip made of a directionally solidified material for use in a gas turbine engine
US5725354A (en) * 1996-11-22 1998-03-10 General Electric Company Forward swept fan blade
GB2322914B (en) * 1997-03-05 2000-05-24 Rolls Royce Plc Ducted fan gas turbine engine
US5954724A (en) * 1997-03-27 1999-09-21 Davidson; James A. Titanium molybdenum hafnium alloys for medical implants and devices
DE10307610A1 (en) * 2003-02-22 2004-09-02 Rolls-Royce Deutschland Ltd & Co Kg Compressor blade for an aircraft engine
WO2005064026A1 (en) * 2003-12-25 2005-07-14 Institute Of Metal Research Chinese Academy Of Sciences Super elasticity and low modulus ti alloy and its manufacture process
GB2418459B (en) * 2004-09-22 2009-04-29 Rolls Royce Plc A method of manufacturing an aerofoil
US7575418B2 (en) * 2004-09-30 2009-08-18 General Electric Company Erosion and wear resistant protective structures for turbine components
FR2906320B1 (en) * 2006-09-26 2008-12-26 Snecma Sa AUBE COMPOSITE TURBOMACHINE WITH METAL REINFORCEMENT
DE102006061916A1 (en) * 2006-12-21 2008-06-26 Rolls-Royce Deutschland Ltd & Co Kg Fan blade for a gas turbine engine
CN101760668B (en) * 2008-12-24 2011-04-20 北京有色金属研究总院 Biological medical titanium alloy with low elastic modulus
US9157327B2 (en) * 2010-02-26 2015-10-13 United Technologies Corporation Hybrid metal fan blade
DE102010032097A1 (en) * 2010-07-23 2012-01-26 Formtech Gmbh Compressor blade of a gas turbine engine with self-sharpening leading edge structure
JP5528986B2 (en) * 2010-11-09 2014-06-25 株式会社日立製作所 Precipitation hardening type martensitic stainless steel and steam turbine member using the same
CN102581550B (en) * 2011-01-05 2014-11-05 中国科学院金属研究所 Preparation method for strong-strength, low-modulus and high-damping beta titanium alloy

Non-Patent Citations (1)

* Cited by examiner, † Cited by third party
Title
None

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US20140030109A1 (en) 2014-01-30
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