EP2617945B1 - Rotor for a turbo machine and manufacturing process - Google Patents

Rotor for a turbo machine and manufacturing process Download PDF

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Publication number
EP2617945B1
EP2617945B1 EP12152073.8A EP12152073A EP2617945B1 EP 2617945 B1 EP2617945 B1 EP 2617945B1 EP 12152073 A EP12152073 A EP 12152073A EP 2617945 B1 EP2617945 B1 EP 2617945B1
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EP
European Patent Office
Prior art keywords
rotor blades
blade
rotor
group
blades
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.)
Not-in-force
Application number
EP12152073.8A
Other languages
German (de)
French (fr)
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EP2617945A1 (en
Inventor
Martin Pernleitner
Marcus Dr. Wöhler
Rudolf Stanka
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.)
MTU Aero Engines AG
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MTU Aero Engines AG
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by MTU Aero Engines AG filed Critical MTU Aero Engines AG
Priority to EP12152073.8A priority Critical patent/EP2617945B1/en
Priority to ES12152073.8T priority patent/ES2668268T3/en
Priority to US13/746,650 priority patent/US9657581B2/en
Publication of EP2617945A1 publication Critical patent/EP2617945A1/en
Application granted granted Critical
Publication of EP2617945B1 publication Critical patent/EP2617945B1/en
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Anticipated expiration legal-status Critical

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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
    • F01D5/30—Fixing blades to rotors; Blade roots ; Blade spacers
    • F01D5/3023—Fixing blades to rotors; Blade roots ; Blade spacers of radial insertion type, e.g. in individual recesses
    • F01D5/303—Fixing blades to rotors; Blade roots ; Blade spacers of radial insertion type, e.g. in individual recesses in a circumferential slot
    • F01D5/3038—Fixing blades to rotors; Blade roots ; Blade spacers of radial insertion type, e.g. in individual recesses in a circumferential slot the slot having inwardly directed abutment faces on both sides
    • 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
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/04—Antivibration arrangements
    • F01D25/06—Antivibration arrangements for preventing blade vibration
    • 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
    • F01D5/26—Antivibration means not restricted to blade form or construction or to blade-to-blade connections or to the use of particular materials
    • 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
    • F01D5/3007—Fixing blades to rotors; Blade roots ; Blade spacers of axial insertion type
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2240/00—Components
    • F05D2240/80—Platforms for stationary or moving blades
    • 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
    • F05D2260/30—Retaining components in desired mutual position
    • F05D2260/36—Retaining components in desired mutual position by a form fit connection, e.g. by interlocking
    • 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
    • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
    • Y10T29/00—Metal working
    • Y10T29/49—Method of mechanical manufacture
    • Y10T29/49316—Impeller making
    • Y10T29/4932—Turbomachine making

Definitions

  • the invention relates to a rotor for a turbomachine, in particular for an aircraft engine.
  • the invention further relates to a method for producing a blade ring of a rotor for a turbomachine and an aircraft engine.
  • Rotors for turbomachines are known in a variety of configurations.
  • a generic rotor comprises a blade ring which has a plurality of rotor blades with blade platforms resting flush against each other.
  • the blade platforms are each arranged in the radial direction between the blade and the blade root of the individual rotor blades and form an inner boundary of the flow path through the turbomachine when the rotor is mounted.
  • the tuning of the vibration behavior of bladed rotors is of central importance for the design of a turbomachine.
  • the frequency detuning is very difficult.
  • Known frequency detuning methods provide rotor blades with different natural frequencies. This is usually done by adding or removing masses.
  • the additional material is applied as a coating on the pressure side and / or the suction side of the rotor blade in the region of the blade tip of the blade, in order to obtain differently shaped rotor blades with correspondingly different natural oscillations.
  • the US 2 271 971 A discloses a rotor for a turbine in which a plurality of blades are attached to a rotor body.
  • the blades are provided with one-sided toothed blade roots, wherein the blade roots of adjacent blades are formed in pairs mirror images of each other.
  • the rotor base body has corresponding connection structures in which the blades are arranged side by side to form a blade ring.
  • the US 2 781 998 A discloses a bladed rotor for turbines or compressors.
  • a part of the rotor blades is formed integrally with the rotor base body, while the remaining rotor blades are manufactured separately and inserted into corresponding receptacles of the rotor body. It can be provided that in each case two separate rotor blades are provided with mirror-image blade roots and pushed together into a corresponding receptacle of the rotor body.
  • a rotor for a turbomachine which has a desired vibration behavior and is easier and more reliable to produce, is inventively provided in that the blade ring comprises at least two groups of differently shaped rotor blades, each group of rotor blades blade platforms are assigned, each with a complementary Vane platform of at least one other group of rotor blades and not flush with a blade platform of the same group of rotor blades are brought into abutment.
  • Each blade platform of a first group of rotor blades has at least one peripheral recess in which a complementary marginal elevation of an adjacent blade platform of an associated second group of rotor blades is arranged in a form-fitting manner.
  • the mechanical stability of the rotor under varying operating conditions for example, under varying operating temperatures and pressures, advantageously improved becomes.
  • the rotor blades that make up the blade ring of the rotor are formed such that two identical rotor blades, which accordingly belong to the same group or the same rotor blade type and have the same blade platforms, not flush mounted side by side, in the case of a faulty arrangement, the blade platforms would not lie flush against one another and thus always leave a gap between them identical trained blade platforms of the rotor blades of a single group would remain.
  • the blade ring could also not be closed.
  • the inventive design of the rotor blades only such rotor blades can instead be arranged flush side by side, which belong to different groups and their paddle platforms on the one hand geometrically different from each other and on the other hand are complementary to each other.
  • only two different groups of rotor blades are needed.
  • an integral exchange protection in the area of the hub platform of the rotor is provided by which it is reliably impossible to arrange two identically formed rotor blades with correspondingly equal vibration behavior next to one another and to add them to the blade ring. Additional components to ensure the security against confusion are not required for this, so that the weight of the rotor is advantageously not adversely affected.
  • the invention therefore makes it possible in a structurally simple and cost-effective manner to reliably manufacture a rotor with a desired frequency detuning (detuning), in which it is reliably ruled out that two identical rotor blades are inadvertently arranged next to one another.
  • each blade platform of the first group of rotor blades a marginal recess and an opposite marginal elevation and each blade platform of the second group of rotor blades to complement the blade platform of the first group complementary marginal elevation and a survey of the Bucket platform of the first group has complementary marginal depression.
  • adjacent blade platforms can be hooked to each other at their opposite edge regions, whereby a mechanically particularly stable connection of the individual rotor blades while ensuring the swap protection is achieved.
  • the recesses and the complementary elevations are formed in the region of lateral contact surfaces of the rotor blades, wherein the elevations are arranged in a form-fitting manner in the associated recesses.
  • a particularly effective frequency detuning of the rotor is achieved in a further embodiment of the invention in that the at least two groups of rotor blades have different blade blade geometries.
  • each group of rotor blades is provided with an associated and group-specific designed blade type, wherein the blade types of different groups of rotor blades differ from each other.
  • Rotor blades with different blade geometry are also understood to mean rotor blades whose blades themselves have the same geometry, but which differ with regard to their relative arrangement with respect to the blade platform. In this case, it may be provided, for example, that the blades of different groups also differ from one another with regard to their material, their coating or any combination of these features.
  • the at least two groups of rotor blades have blade platforms with mutually corresponding lateral contact surfaces. This is a structurally particularly simple way to create an integral swap protection and to bring adjacent rotor blades as large as possible in abutment with each other.
  • the contact surfaces being inclined and / or wavy and / or serrated and / or irregular.
  • the contact surfaces can form corresponding wedge surfaces with each other, which in addition to an integral swap protection and increased friction between the rotor blades and thus a mechanically particularly stable connection of adjacent rotor blades is achieved.
  • the design of the contact surfaces is basically not limited to certain geometries. In the geometric design of the corresponding contact surfaces, it is merely necessary to ensure that the contact surfaces of one group of rotor blades can not be brought flush into contact with the corresponding contact surfaces of a further group of rotor blades but not with contact surfaces of the same group of rotor blades.
  • a further aspect of the invention relates to a method for producing a blade ring of a rotor for a turbomachine, in particular for an aircraft engine, comprising at least the steps a) providing at least two groups of differently shaped rotor blades, wherein each group of rotor blades are associated with blade platforms, each with and b) arranging the rotor blades in the form of the blade ring, wherein each complementary blade platforms of the at least two groups of rotor blades flush with each other in abutment with one another to be brought.
  • each blade platform of a first group of rotor blades has at least one marginal depression, in which a complementary marginal elevation of an adjacent blade platform of an associated second group of rotor blades is arranged positively.
  • step b) blade platforms of a first group of rotor blades and blade platforms of a second group of rotor blades are brought into contact alternately.
  • step b) blade platforms of a first group of rotor blades and blade platforms of a second group of rotor blades are brought into contact alternately.
  • a mechanically particularly stable connection of the blade ring to the rotor is made possible in a further embodiment in that blade roots of the rotor blades are arranged and fixed in step b) in a complementary groove of a rotor base body.
  • the blade roots of the individual rotor blades can in principle be identical, that is to say group-independent. Alternatively, however, it can also be provided that the rotor blades have group-specific blade roots.
  • rotor blades are used which have group-specific designed blade types, wherein the blade blade types of different groups of rotor blades differ from each other. It can be provided, for example, that the blades of different groups additionally differ from each other in terms of their material, their coating or any combination of these features. This allows a particularly effective frequency detuning of the rotor, since in this way in combination with the group-specific trained blade platforms never two identically designed blades can be installed flush side by side. Vice versa However, it is advantageously not necessary to design each individual blade of the rotor individually in order to achieve a sufficient frequency detuning.
  • Another aspect of the invention relates to an aircraft engine, wherein it is provided according to the invention that it comprises a rotor according to one of the preceding embodiments and / or a blade ring, which is produced by means of a method according to one of the preceding embodiments.
  • Fig. 1 shows a schematic plan view of two flush-mounted rotor blades 10a, 10b during the manufacture of a blade ring (not shown) of a rotor for an aircraft engine. From the rotor blades 10a, 10b, the cut blades 12a, 12b are shown, which are connected to blade platforms 14a, 14b of the rotor blades 10a, 10b and extending in a conventional manner from the blade platforms 14a, 14b from radially upwards. Radially below the blade platforms 14a, 14b, the rotor blades 10a, 10b comprise respective blade roots 16a, 16b (see FIG. Fig.
  • the two rotor blades 10a, 10b comprise differently designed blade platforms 14a, 14b and belong to two different groups.
  • the blade platforms 14a, 14b of the two groups of rotor blades 10a, 10b lie flush against each other and form in the finished mounted blade ring or in the finished rotor a continuous, radially inner shroud, which limits the flow path in the associated aircraft engine.
  • the blades 12a, 12b are formed group-specific, wherein blades blades 12a and 12b of the same group have an identical blade geometry and blades 12a, 12b of different groups have different blade geometry.
  • the blade platform 14a belonging to the first group of rotor blades 10a is designed such that it is flush with the blade platform 14b belonging to the second group of rotor blades 10b and designed to be complementary to the blade platform 14a.
  • the blade platform 14a of the first group in the region I has a recess which is peripheral with respect to the dot-dashed dividing plane A and, in the opposite region II, a marginal elevation with respect to the dash-dotted dividing plane A.
  • Corresponding blade platform 14b of the second group accordingly has a marginal elevation complementary to the depression of the blade platform 14a in region I and a marginal depression complementary to the elevation of blade platform 14a in region II.
  • the graduation plane A hereby identifies the theoretical graduation plane between two conventional rotor blades whose blade platforms have consistently planar contact surfaces and thus can not be arranged so that they are not interchangeable.
  • first rotor blades provided with identical blade platforms and the wells and elevations then by a corresponding milling treatment of the blade platforms 14a, 14b are generated.
  • the blade platform 14a of the first group of rotor blades 10a can not be placed flush with another blade platform 14a of the first group, but only on the blade platform 14b belonging to the second group of rotor blades 10b.
  • the blade platform 14b belonging to the second group of rotor blades 10b can also be placed flush with the paddle platform 14a belonging to the first group, but not flush with another paddle platform 14b of the second group.
  • two identical rotor blades 10a-10a or 10b-10b of the same group with identical blade platforms 14a-14a or 14b-14b can never be installed flush next to each other.
  • blade platforms 14a of rotor blades 10a of the first group and blade platforms 14b of rotor blades 10b of the second are alternately formed to form a blade ring Group attached to each other.
  • a particularly effective frequency detuning of the finished blade ring and thus of the assembled rotor is reliably achieved.
  • one or more further groups of differently shaped rotor blades are used with group-specific blade platforms, wherein the blade platforms are always to be designed such that they are not flush with blade platforms of rotor blades of the same group, but flush with blade platforms of rotor blades at least can be applied to another group.
  • the depressions and elevations are formed in lateral contact or contact surfaces of the blade platforms 14a, 14b of the rotor blades 10a, 10b and form a tongue and groove connection.
  • a structurally particularly simple swap protection can be achieved, for example, in that the first group of rotor blades 10a has bilateral elevations (springs) and the second group of rotor blades 10b has recesses (grooves) on both sides.
  • Fig. 2 shows a schematic frontal view of two alternately formed rotor blades 10a, 10b during the manufacture of a blade ring (not shown) of an aircraft engine rotor.
  • Rotor blades 10a, 10b show partially cut airfoils 12a, 12b, which are connected to blade platforms 14a, 14b of rotor blades 10a, 10b and extend radially upward from blade platforms 14a, 14b.
  • Radially below the blade platforms 14a, 14b, the rotor blades 10a, 10b comprise respective blade roots 16a, 16b, via which the connection of the rotor blades 10a, 10b to one Rotor body of the rotor takes place.
  • the blade platforms 14a, 14b have mutually corresponding lateral contact surfaces III.
  • the contact surfaces III are formed obliquely or wedge-shaped with respect to the axis of rotation of the rotor extending division plane A, so that the blade platform 14a of the first group only with the blade platform 14b of the second group, but not with a further blade platform 14a of the first Group can be brought flush into contact.
  • the blade platforms 14a, 14b of the two groups of rotor blades 10a, 10b form a continuous, radially inner shroud, which limits the flow path in the assigned aircraft engine, analogous to the previous exemplary embodiment in the completely assembled blade ring or in the finished rotor.
  • the wedge-shaped design of the contact surfaces causes depending on the angle of the wedge increased friction between the contact surfaces III.
  • the contact surfaces III have a fundamentally arbitrary contour profile and, for example, can be corrugated and / or serrated or have other suitable elevations / depressions. It is only important that the contact surfaces III of the first group of rotor blades 10a can be brought into contact flush only with corresponding contact surfaces III of the second (or another) group of rotor blades 10b, but not with contact surfaces III of the first group of rotor blades 10a.

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

Description

Die Erfindung betrifft einen Rotor für eine Strömungsmaschine, insbesondere für ein Flugzeugtriebwerk. Die Erfindung betrifft weiterhin ein Verfahren zum Herstellen eines Schaufelkranzes eines Rotors für eine Strömungsmaschine sowie ein Flugzeugtriebwerk.The invention relates to a rotor for a turbomachine, in particular for an aircraft engine. The invention further relates to a method for producing a blade ring of a rotor for a turbomachine and an aircraft engine.

Rotoren für Strömungsmaschinen sind in vielfältigen Ausgestaltungen bekannt. Ein gattungsgemäßer Rotor umfasst einen Schaufelkranz, welcher mehrere Rotorschaufeln mit bündig aneinander anliegenden Schaufelplattformen aufweist. Die Schaufelplattformen sind dabei jeweils in radialer Richtung zwischen dem Schaufelblatt und dem Schaufelfuß der einzelnen Rotorschaufeln angeordnet und bilden bei montiertem Rotor eine innere Begrenzung des Strömungspfads durch die Strömungsmaschine. Die Abstimmung des Schwingverhaltens von beschaufelten Rotoren ist dabei von zentraler Bedeutung für die Auslegung einer Strömungsmaschine. Insbesondere bei thermischen Gasturbinen wie Flugzeugtriebwerken, die in unterschiedlichen Drehzahlbereichen betrieben werden, ist die Frequenzverstimmung sehr schwierig. Bekannte Verfahren zur Frequenzverstimmung sehen vor, Rotorschaufeln mit unterschiedlichen Eigenfrequenzen zu versehen. Dies erfolgt üblicherweise über das Hinzufügen oder die Entnahme von Massen. Hierzu werden, wie beispielsweise in der DE 10 2007 014 886 A1 beschrieben, in die Schaufelblätter der Rotorschaufeln Bohrungen oder Taschen eingebracht, welche anschließend mit einem andersartigen Zusatzmaterial aufgefüllt werden. Alternativ ist es aus der WO 03/062606 A1 bekannt, dass das Zusatzmaterial als eine Beschichtung auf der Druckseite und/oder der Saugseite der Rotorschaufel im Bereich der Schaufelspitze des Schaufelblatts aufgetragen wird, um unterschiedlich ausgebildete Rotorschaufeln mit dementsprechend unterschiedlichen Eigenschwingungen zu erhalten.Rotors for turbomachines are known in a variety of configurations. A generic rotor comprises a blade ring which has a plurality of rotor blades with blade platforms resting flush against each other. The blade platforms are each arranged in the radial direction between the blade and the blade root of the individual rotor blades and form an inner boundary of the flow path through the turbomachine when the rotor is mounted. The tuning of the vibration behavior of bladed rotors is of central importance for the design of a turbomachine. In particular, in thermal gas turbines such as aircraft engines, which are operated in different speed ranges, the frequency detuning is very difficult. Known frequency detuning methods provide rotor blades with different natural frequencies. This is usually done by adding or removing masses. For this purpose, as in the DE 10 2007 014 886 A1 described, introduced into the blades of the rotor blades bores or pockets, which are then filled with a different type of additional material. Alternatively it is from the WO 03/062606 A1 It is known that the additional material is applied as a coating on the pressure side and / or the suction side of the rotor blade in the region of the blade tip of the blade, in order to obtain differently shaped rotor blades with correspondingly different natural oscillations.

Die US 2 271 971 A offenbart einen Rotor für eine Turbine, bei welchem eine Mehrzahl an Schaufeln an einem Rotorgrundkörper befestigt werden. Die Schaufeln sind mit einseitig gezahnten Schaufelfüßen versehen, wobei die Schaufelfüße von benachbarten Schaufeln paarweise spiegelbildlich zueinander ausgebildet sind. Der Rotorgrundkörper weist korrespondierende Anschlussstrukturen auf, in welchen die Schaufeln nebeneinander angeordnet werden, um einen Schaufelkranz zu bilden.The US 2 271 971 A discloses a rotor for a turbine in which a plurality of blades are attached to a rotor body. The blades are provided with one-sided toothed blade roots, wherein the blade roots of adjacent blades are formed in pairs mirror images of each other. The rotor base body has corresponding connection structures in which the blades are arranged side by side to form a blade ring.

Die US 2 781 998 A offenbart einen beschaufelten Rotor für Turbinen oder Kompressoren. Ein Teil der Rotorschaufeln ist dabei integral mit dem Rotorgrundkörper ausgebildet, während die verbleibenden Rotorschaufeln separat hergestellt und in entsprechende Aufnahmen des Rotorgrundkörpers eingeschoben werden. Dabei kann vorgesehen sein, dass jeweils zwei separater Rotorschaufeln mit spiegelbildlichen Schaufelfüßen versehen und gemeinsam in eine entsprechende Aufnahme des Rotorgrundkörpers geschoben werden.The US 2 781 998 A discloses a bladed rotor for turbines or compressors. A part of the rotor blades is formed integrally with the rotor base body, while the remaining rotor blades are manufactured separately and inserted into corresponding receptacles of the rotor body. It can be provided that in each case two separate rotor blades are provided with mirror-image blade roots and pushed together into a corresponding receptacle of the rotor body.

Diese bekannten Arten der Frequenzverstimmung sind jedoch fertigungstechnisch aufwendig und vergleichsweise teuer. Darüber hinaus kann nicht zuverlässig ausgeschlossen werden, dass zwei identisch ausgebildete Rotorschaufeln mit identischem Schwingungsverhalten nebeneinander angeordnet werden.However, these known types of frequency detuning are technically complex and relatively expensive. In addition, it can not be ruled out reliably that two identically designed rotor blades with identical vibration behavior are arranged next to one another.

Aufgabe der vorliegenden Erfindung ist es, einen gattungsgemäßen Rotor zu schaffen, welcher ein gewünschtes Schwingungsverhalten aufweist und dabei einfacher und prozesssicherer herstellbar ist. Eine weitere Aufgabe der Erfindung ist es, ein Verfahren zum Herstellen eines Schaufelkranzes eines Rotors für eine Strömungsmaschine zu schaffen, welches eine einfachere und prozesssicherere Herstellung eines Rotors mit einem gewünschten Schwingungsverhalten ermöglicht. Schließlich ist es Aufgabe der Erfindung, ein Flugzeugtriebwerk mit einem derartigen Rotor zu schaffen.Object of the present invention is to provide a generic rotor, which has a desired vibration behavior and thereby easier and process reliable to produce is. Another object of the invention is to provide a method for producing a blade ring of a rotor for a turbomachine, which enables a simpler and more reliable production of a rotor with a desired vibration behavior. Finally, it is an object of the invention to provide an aircraft engine with such a rotor.

Die Aufgaben werden erfindungsgemäß durch einen Rotor mit den Merkmalen des Patentanspruchs 1, durch ein Verfahren gemäß Patentanspruch 8 sowie durch ein Flugzeugtriebwerk mit den Merkmalen des Patentanspruchs 12 gelöst. Vorteilhafte Ausgestaltungen mit zweckmäßigen Weiterbildungen der Erfindung sind in den jeweiligen Unteransprüchen angegeben, wobei vorteilhafte Ausgestaltungen des Rotors als vorteilhafte Ausgestaltungen des Verfahrens und umgekehrt anzusehen sind.The objects are achieved by a rotor with the features of claim 1, by a method according to claim 8 and by an aircraft engine with the features of claim 12. Advantageous embodiments with expedient developments of the invention are specified in the respective subclaims, wherein advantageous embodiments of the rotor are to be regarded as advantageous embodiments of the method and vice versa.

Ein Rotor für eine Strömungsmaschine, welcher ein gewünschtes Schwingungsverhalten aufweist und dabei einfacher und prozesssicherer herstellbar ist, ist erfindungsgemäß dadurch geschaffen, dass der Schaufelkranz wenigstens zwei Gruppen von unterschiedlich ausgebildeten Rotorschaufeln umfasst, wobei jeder Gruppe von Rotorschaufeln Schaufelplattformen zugeordnet sind, welche jeweils mit einer komplementären Schaufelplattform wenigstens einer anderen Gruppe von Rotorschaufeln und nicht mit einer Schaufelplattform derselben Gruppe von Rotorschaufeln bündig in Anlage bringbar sind. Jede Schaufelplattform einer ersten Gruppe von Rotorschaufeln weist wenigstens eine randständige Vertiefung auf, in welcher eine komplementäre randständige Erhebung einer benachbarten Schaufelplattform einer zugeordneten zweiten Gruppe von Rotorschaufeln formschlüssig angeordnet ist. Hierdurch ist ein konstruktiv besonders einfacher Vertauschschutz gegeben. Darüber hinaus ist es bei entsprechender Ausgestaltung der Vertiefung und der zugeordneten Erhebung besonders einfach möglich, benachbarte Rotorschaufeln miteinander zu "verhaken", wodurch neben dem Vertauschschutz zusätzlich auch die mechanische Stabilität des Rotors unter wechselnden Betriebsbedingungen, beispielsweise unter wechselnden Betriebstemperaturen und -drücken, vorteilhaft verbessert wird. Mit anderen Worten ist es erfindungsgemäß vorgesehen, dass die Rotorschaufeln, aus denen der Schaufelkranz des Rotors besteht, derart ausgebildet sind, dass zwei gleiche Rotorschaufeln, die dementsprechend zu derselben Gruppe bzw. demselben Rotorschaufeltyp gehören und gleiche Schaufelplattformen aufweisen, nicht bündig nebeneinander einbaubar sind, da die Schaufelplattformen im Fall einer Fehlanordnung nicht bündig aneinander anlegbar wären und somit stets eine Lücke zwischen den identisch ausgebildeten Schaufelplattformen der Rotorschaufeln einer einzelnen Gruppe bestehen bliebe. Aufgrund des daraus resultierenden Bauraummehrbedarfs könnte der Schaufelkranz zudem nicht mehr geschlossen werden. Mit Hilfe der erfindungsgemäßen Ausgestaltung der Rotorschaufeln können statt dessen nur solche Rotorschaufeln bündig nebeneinander angeordnet werden, die zu unterschiedlichen Gruppen gehören und deren Schaufelplattformen sich einerseits geometrisch voneinander unterscheiden und andererseits komplementär zueinander ausgebildet sind. In einfachster Ausgestaltung der Erfindung werden somit lediglich zwei unterschiedliche Gruppen von Rotorschaufeln benötigt. Grundsätzlich können aber natürlich auch drei oder mehr Gruppen unterschiedliche ausgebildeter Rotorschaufeln verwendet werden, wobei grundsätzlich gilt, dass zumindest Schaufelplattformen derselben Gruppe von Rotorschaufeln aufgrund ihrer gruppenspezifischen Ausgestaltung nicht bündig miteinander in Anlage bringbar sind. Hierdurch ist erfindungsgemäß ein integraler Vertauschschutz im Bereich der Nabenplattform des Rotors geschaffen, durch welchen es zuverlässig verunmöglicht ist, zwei gleich ausgebildete Rotorschaufeln mit entsprechend gleichem Schwingungsverhalten bündig nebeneinander anzuordnen und zum Schaufelkranz zu fügen. Zusätzliche Bauteile zur Sicherstellung der Verwechslungssicherheit sind hierzu nicht erforderlich, so dass das Gewicht des Rotors vorteilhafter Weise nicht nachteilig beeinflusst wird. Die Erfindung ermöglicht daher auf konstruktiv einfache und kostengünstige Weise die prozesssichere Herstellung eines Rotors mit einer gewünschten Frequenzverstimmung (Detuning), bei welchem zuverlässig ausgeschlossen ist, dass versehentlich zwei gleiche Rotorschaufeln nebeneinander angeordnet ist.A rotor for a turbomachine, which has a desired vibration behavior and is easier and more reliable to produce, is inventively provided in that the blade ring comprises at least two groups of differently shaped rotor blades, each group of rotor blades blade platforms are assigned, each with a complementary Vane platform of at least one other group of rotor blades and not flush with a blade platform of the same group of rotor blades are brought into abutment. Each blade platform of a first group of rotor blades has at least one peripheral recess in which a complementary marginal elevation of an adjacent blade platform of an associated second group of rotor blades is arranged in a form-fitting manner. As a result, a structurally particularly simple exchange protection is given. In addition, it is particularly easy with appropriate design of the depression and the associated survey "hooked" adjacent rotor blades with each other, which in addition to the exchange protection in addition, the mechanical stability of the rotor under varying operating conditions, for example, under varying operating temperatures and pressures, advantageously improved becomes. In other words, it is inventively provided that the rotor blades that make up the blade ring of the rotor, are formed such that two identical rotor blades, which accordingly belong to the same group or the same rotor blade type and have the same blade platforms, not flush mounted side by side, in the case of a faulty arrangement, the blade platforms would not lie flush against one another and thus always leave a gap between them identical trained blade platforms of the rotor blades of a single group would remain. Due to the resulting increase in space requirements, the blade ring could also not be closed. With the help of the inventive design of the rotor blades, only such rotor blades can instead be arranged flush side by side, which belong to different groups and their paddle platforms on the one hand geometrically different from each other and on the other hand are complementary to each other. In the simplest embodiment of the invention thus only two different groups of rotor blades are needed. In principle, however, it is also possible to use three or more groups of differently designed rotor blades, with the general rule that at least blade platforms of the same group of rotor blades can not be brought into abutment with each other due to their group-specific configuration. As a result, according to the invention, an integral exchange protection in the area of the hub platform of the rotor is provided by which it is reliably impossible to arrange two identically formed rotor blades with correspondingly equal vibration behavior next to one another and to add them to the blade ring. Additional components to ensure the security against confusion are not required for this, so that the weight of the rotor is advantageously not adversely affected. The invention therefore makes it possible in a structurally simple and cost-effective manner to reliably manufacture a rotor with a desired frequency detuning (detuning), in which it is reliably ruled out that two identical rotor blades are inadvertently arranged next to one another.

Weitere Vorteile ergeben sich, indem die Vertiefung und/oder die Erhebung der betreffenden Schaufelplattform mit Hilfe eines Trennverfahrens, insbesondere durch Fräsen und/oder Schleifen, in die betreffende Schaufelplattform eingebracht ist. Dies ermöglicht weitere Kostensenkungen, da zunächst Rotorschaufeln mit identisch ausgebildeten Schaufelplattformen hergestellt werden können. Die entsprechenden Vertiefungen und Erhebungen können dann anschließend durch das Trennverfahren in die Schaufelplattformen eingebracht werden. Dies erlaubt es auch, zunächst herkömmliche Rotorschaufeln mit einheitlich ausgebildeten Schaufelplattformen bereitzustellen und anschließend im Sinne der vorliegenden Erfindung nachzubearbeiten, wodurch weitere Kostensenkungen sowohl bei der Herstellung als auch bei der Reparatur und Überholung entsprechender Rotoren realisiert werden. Zudem kann die Erfindung hierdurch auch auf bereits bestehende Rotoren bzw. Rotorschaufeln angewendet werden. Alternativ oder zusätzlich kann aber natürlich auch vorgesehen sein, dass die wenigstens zwei unterschiedlichen Gruppen von Rotorschaufeln durch abweichende Herstellungsverfahren, beispielsweise durch Urformen und/oder Fügen, hergestellt werden.Further advantages result from the depression and / or the elevation of the relevant blade platform being introduced into the relevant blade platform by means of a separation process, in particular by milling and / or grinding. This allows further cost reductions, since first rotor blades can be manufactured with identically designed blade platforms. The corresponding depressions and elevations can then subsequently be introduced into the blade platforms by the separation process. This also makes it possible to first provide conventional rotor blades with uniformly designed blade platforms and then post-process them in the sense of the present invention, whereby further cost reductions are realized both in the manufacture and in the repair and overhaul of corresponding rotors. In addition, the invention can also be applied to existing rotors or rotor blades. Alternatively or additionally, but of course It can also be provided that the at least two different groups of rotor blades are produced by deviating production methods, for example by primary forming and / or joining.

In einer weiteren vorteilhaften Ausgestaltung der Erfindung ist vorgesehen, dass jede Schaufelplattform der ersten Gruppe von Rotorschaufeln eine randständige Vertiefung sowie eine gegenüberliegende randständige Erhebung und jede Schaufelplattform der zweiten Gruppe von Rotorschaufeln eine zur Vertiefung der Schaufelplattform der ersten Gruppe komplementäre randständige Erhebung und eine zur Erhebung der Schaufelplattform der ersten Gruppe komplementäre randständige Vertiefung aufweist. Auf diese Weise können einander benachbarte Schaufelplattformen an ihren gegenüberliegenden Randbereichen miteinander verhakt werden, wodurch eine mechanisch besonders stabile Anbindung der einzelnen Rotorschaufeln unter gleichzeitiger Sicherstellung des Vertauschschutzes erzielt wird.In a further advantageous embodiment of the invention, it is provided that each blade platform of the first group of rotor blades a marginal recess and an opposite marginal elevation and each blade platform of the second group of rotor blades to complement the blade platform of the first group complementary marginal elevation and a survey of the Bucket platform of the first group has complementary marginal depression. In this way, adjacent blade platforms can be hooked to each other at their opposite edge regions, whereby a mechanically particularly stable connection of the individual rotor blades while ensuring the swap protection is achieved.

In einer weiteren vorteilhaften Ausgestaltung der Erfindung ist vorgesehen, dass die Vertiefungen und die komplementären Erhebungen im Bereich seitlicher Kontaktflächen der Rotorschaufeln ausgebildet sind, wobei die Erhebungen formschlüssig in den zugeordneten Vertiefungen angeordnet sind. Dies stellt eine konstruktiv einfache Möglichkeit dar, um benachbarte Rotorschaufeln über eine Art Nut-Feder-Verbindung mechanisch stabil miteinander zu verbinden.In a further advantageous embodiment of the invention it is provided that the recesses and the complementary elevations are formed in the region of lateral contact surfaces of the rotor blades, wherein the elevations are arranged in a form-fitting manner in the associated recesses. This represents a structurally simple way to connect adjacent rotor blades via a kind of tongue and groove connection mechanically stable.

Eine besonders wirksame Frequenzverstimmung des Rotors wird in weiterer Ausgestaltung der Erfindung dadurch erzielt, dass die wenigstens zwei Gruppen von Rotorschaufeln unterschiedliche Schaufelblattgeometrien aufweisen. Mit anderen Worten ist es erfindungsgemäß vorgesehen, dass jede Gruppe von Rotorschaufeln mit einem zugeordneten und gruppenspezifisch ausgebildeten Schaufelblatttyp versehen ist, wobei sich die Schaufelblatttypen unterschiedlicher Gruppen von Rotorschaufeln voneinander unterscheiden. Unter Rotorschaufeln mit unterschiedlichen Schaufelblattgeometrien sind dabei auch Rotorschaufeln zu verstehen, deren Schaufelblätter für sich genommen dieselbe Geometrie besitzen, sich aber im Hinblick auf ihre relative Anordnung bezüglich der Schaufelplattform unterschieden. Dabei kann beispielsweise vorgesehen sein, dass sich die Schaufelblätter unterschiedlicher Gruppen auch im Hinblick auf ihr Material, ihre Beschichtung oder eine beliebige Kombination dieser Merkmale voneinander unterschieden. Dies ermöglicht eine besonders wirksame Frequenzverstimmung des Rotors, da auf diese Weise in Verbindung mit den gruppenspezifisch ausgebildeten Schaufelplattformen niemals zwei Rotorschaufeln mit identischen Schaufelblättern bündig nebeneinander eingebaut werden können. Umgekehrt ist es jedoch vorteilhafter Weise nicht erforderlich, jedes einzelne Schaufelblatt des Rotors individuell auszugestalten, um eine ausreichende Frequenzverstimmung zu erzielen.A particularly effective frequency detuning of the rotor is achieved in a further embodiment of the invention in that the at least two groups of rotor blades have different blade blade geometries. In other words, it is provided according to the invention that each group of rotor blades is provided with an associated and group-specific designed blade type, wherein the blade types of different groups of rotor blades differ from each other. Rotor blades with different blade geometry are also understood to mean rotor blades whose blades themselves have the same geometry, but which differ with regard to their relative arrangement with respect to the blade platform. In this case, it may be provided, for example, that the blades of different groups also differ from one another with regard to their material, their coating or any combination of these features. This allows a particularly effective frequency detuning of the rotor, since in this way in combination with the group-specific trained blade platforms never two rotor blades with identical Blades can be installed flush side by side. Conversely, however, it is advantageously not necessary to design each individual airfoil of the rotor individually in order to achieve a sufficient frequency detuning.

Weitere Vorteile ergeben sich, indem die wenigstens zwei Gruppen von Rotorschaufeln Schaufelplattformen mit miteinander korrespondierenden seitlichen Anlageflächen aufweisen. Dies stellt eine konstruktiv besonders einfache Möglichkeit dar, um einen integralen Vertauschschutz zu schaffen und benachbarte Rotorschaufeln möglichst großflächig miteinander in Anlage zu bringen.Further advantages result from the fact that the at least two groups of rotor blades have blade platforms with mutually corresponding lateral contact surfaces. This is a structurally particularly simple way to create an integral swap protection and to bring adjacent rotor blades as large as possible in abutment with each other.

Weitere Vorteile ergeben sich, indem die Anlageflächen schräg und/oder gewellt und/oder gezackt und/oder unregelmäßig ausgebildet sind. Beispielsweise können die Anlageflächen miteinander korrespondierende Keilflächen bilden, wodurch neben einem integralen Vertauschschutz auch eine erhöhte Reibung zwischen den Rotorschaufeln und damit eine mechanisch besonders stabile Anbindung von benachbarten Rotorschaufeln erzielt wird. Die Ausgestaltung der Anlageflächen ist aber grundsätzlich nicht auf bestimmte Geometrien beschränkt. Es ist bei der geometrischen Auslegung der korrespondierenden Anlageflächen lediglich darauf zu achten, dass die Anlageflächen einer Gruppe von Rotorschaufeln nur mit den korrespondierenden Anlageflächen einer weiteren Gruppe von Rotorschaufeln aber nicht mit Anlageflächen derselben Gruppe von Rotorschaufeln bündig in Anlage bringbar sind.Further advantages result from the contact surfaces being inclined and / or wavy and / or serrated and / or irregular. For example, the contact surfaces can form corresponding wedge surfaces with each other, which in addition to an integral swap protection and increased friction between the rotor blades and thus a mechanically particularly stable connection of adjacent rotor blades is achieved. The design of the contact surfaces is basically not limited to certain geometries. In the geometric design of the corresponding contact surfaces, it is merely necessary to ensure that the contact surfaces of one group of rotor blades can not be brought flush into contact with the corresponding contact surfaces of a further group of rotor blades but not with contact surfaces of the same group of rotor blades.

Ein weiterer Aspekt der Erfindung betrifft ein Verfahren zum Herstellen eines Schaufelkranzes eines Rotors für eine Strömungsmaschine, insbesondere für ein Flugzeugtriebwerk, umfassend zumindest die Schritte a) Bereitstellen von wenigstens zwei Gruppen unterschiedlich ausgebildeter Rotorschaufeln, wobei jeder Gruppe von Rotorschaufeln Schaufelplattformen zugeordnet sind, welche jeweils mit einer komplementären Schaufelplattform wenigstens einer anderen Gruppe von Rotorschaufeln und nicht mit einer Schaufelplattform derselben Gruppe von Rotorschaufeln bündig in Anlage bringbar sind, und b) Anordnen der Rotorschaufeln in Form des Schaufelkranzes, wobei jeweils zueinander komplementäre Schaufelplattformen der wenigstens zwei Gruppen von Rotorschaufeln bündig miteinander in Anlage gebracht werden. Erfindungsgemäß ist vorgesehen, dass jede Schaufelplattform einer ersten Gruppe von Rotorschaufeln wenigstens eine randständige Vertiefung aufweist, in welcher eine komplementäre randständige Erhebung einer benachbarten Schaufelplattform einer zugeordneten zweiten Gruppe von Rotorschaufeln formschlüssig angeordnet wird. Hierdurch ist ein konstruktiv besonders einfacher Vertauschschutz gegeben. Darüber hinaus ist es bei entsprechender Ausgestaltung der Vertiefung und der zugeordneten Erhebung besonders einfach möglich, benachbarte Rotorschaufeln miteinander zu "verhaken", wodurch neben dem Vertauschschutz zusätzlich auch die mechanische Stabilität des Rotors unter wechselnden Betriebsbedingungen, beispielsweise unter wechselnden Betriebstemperaturen und -drücken, vorteilhaft verbessert wird. Auf diese Weise ist eine einfachere und proxesssicherere Herstellung eines Rotors mit einem gewünschten Schwingungsverhalten ermöglicht, da auf konstruktiv einfache Weise sichergestellt ist, dass niemals zwei identisch ausgebildete Rotorschaufeln mit dementsprechend gleichem Schwingungsverhalten bündig nebeneinander angeordnet werden können. Hierdurch ist erfindungsgemäß ein integraler Vertauschschutz an der Nabenplattform des Rotors geschaffen. Zusätzliche Bauteile zur Sicherstellung der Verwechslungssicherheit sind vorteilhafter Weise nicht erforderlich, so dass das Gewicht des Rotors nicht nachteilig beeinflusst wird. Das erfindungsgemäße Verfahren ermöglicht daher auf konstruktiv einfache und kostengünstig Weise die besonders prozesssichere Herstellung eines Schaufelkranzes bzw. eines mit einem derartigen Schaufelkranz versehenen Rotors mit einer gewünschten Frequenzverstimmung (Detuning). Weitere Merkmale und deren Vorteile sind den vorhergehenden Beschreibungen zu entnehmen.A further aspect of the invention relates to a method for producing a blade ring of a rotor for a turbomachine, in particular for an aircraft engine, comprising at least the steps a) providing at least two groups of differently shaped rotor blades, wherein each group of rotor blades are associated with blade platforms, each with and b) arranging the rotor blades in the form of the blade ring, wherein each complementary blade platforms of the at least two groups of rotor blades flush with each other in abutment with one another to be brought. According to the invention, it is provided that each blade platform of a first group of rotor blades has at least one marginal depression, in which a complementary marginal elevation of an adjacent blade platform of an associated second group of rotor blades is arranged positively. As a result, a structurally particularly simple exchange protection is given. In addition, it is particularly easy with appropriate design of the depression and the associated survey "hooked" adjacent rotor blades with each other, which in addition to the exchange protection in addition, the mechanical stability of the rotor under varying operating conditions, for example, under varying operating temperatures and pressures, advantageously improved becomes. In this way, a simpler and more secure proximal manufacturing a rotor with a desired vibration behavior is possible, since it is ensured in a structurally simple way that never two identically shaped rotor blades with correspondingly equal vibration behavior can be arranged flush side by side. As a result, according to the invention, an integral exchange protection is provided on the hub platform of the rotor. Additional components to ensure the security against confusion are advantageously not required, so that the weight of the rotor is not adversely affected. The inventive method therefore allows in a structurally simple and cost-effective manner, the particularly reliable production of a blade ring or a rotor provided with such a blade ring with a desired frequency detuning (detuning). Further features and their advantages can be found in the previous descriptions.

In einer vorteilhaften Ausgestaltung der Erfindung ist vorgesehen, dass in Schritt b) abwechselnd Schaufelplattformen einer ersten Gruppe von Rotorschaufeln und Schaufelplattformen einer zweiten Gruppe von Rotorschaufeln miteinander in Anlage gebracht werden. Auf diese Weise werden lediglich zwei unterschiedliche Typen von Rotorschaufeln mit komplementär zueinander ausgebildeten Gruppen von Schaufelplattformen benötigt, so dass der Schaufelkranz besonders schnell und prozesssicher mit einer gewünschten Frequenzverstimmung hergestellt werden kann.In an advantageous embodiment of the invention, it is provided that in step b) blade platforms of a first group of rotor blades and blade platforms of a second group of rotor blades are brought into contact alternately. In this way, only two different types of rotor blades are required with complementary trained groups of blade platforms, so that the blade ring can be made particularly fast and reliable with a desired frequency detuning.

Eine mechanisch besonders stabile Anbindung des Schaufelkranzes an den Rotor ist in weiterer Ausgestaltung dadurch ermöglicht, dass Schaufelfüße der Rotorschaufeln in Schritt b) in einer komplementären Nut eines Rotorgrundkörpers angeordnet und festgelegt werden. Die Schaufelfüße der einzelnen Rotorschaufeln können dabei grundsätzlich identisch, das heißt gruppenunabhängig, ausgebildet sein. Alternativ kann jedoch auch vorgesehen sein, dass die Rotorschaufein gruppenspezifisch ausgebildete Schaufelfüße aufweisen.A mechanically particularly stable connection of the blade ring to the rotor is made possible in a further embodiment in that blade roots of the rotor blades are arranged and fixed in step b) in a complementary groove of a rotor base body. The blade roots of the individual rotor blades can in principle be identical, that is to say group-independent. Alternatively, however, it can also be provided that the rotor blades have group-specific blade roots.

Weitere Vorteile ergeben sich, indem in Schritt a) wenigstens zwei Gruppen von Rotorschaufeln mit unterschiedlichen Schaufelblattgeometrien bereitgestellt werden. Mit anderen Worten ist es erfindungsgemäß vorgesehen, dass Rotorschaufeln verwendet werden, welche gruppenspezifisch ausgebildete Schaufelblatttypen aufweisen, wobei sich die Schaufelblatttypen unterschiedlicher Gruppen von Rotorschaufeln voneinander unterscheiden. Dabei kann beispielsweise vorgesehen sein, dass sich die Schaufelblätter unterschiedlicher Gruppen zusätzlich im Hinblick auf ihr Material, ihre Beschichtung oder eine beliebige Kombination dieser Merkmale voneinander unterschieden. Dies ermöglicht eine besonders wirksame Frequenzverstimmung des Rotors, da auf diese Weise in Verbindung mit den gruppenspezifisch ausgebildeten Schaufelplattformen niemals zwei identisch ausgebildete Schaufelblätter bündig nebeneinander eingebaut werden können. Umgekehrt ist es jedoch vorteilhafter Weise nicht erforderlich, jedes einzelne Schaufelblatt des Rotors individuell auszugestalten, um eine ausreichende Frequenzverstimmung zu erzielen.Further advantages are obtained by providing at least two groups of rotor blades with different blade geometry in step a). In other words, it is provided according to the invention that rotor blades are used which have group-specific designed blade types, wherein the blade blade types of different groups of rotor blades differ from each other. It can be provided, for example, that the blades of different groups additionally differ from each other in terms of their material, their coating or any combination of these features. This allows a particularly effective frequency detuning of the rotor, since in this way in combination with the group-specific trained blade platforms never two identically designed blades can be installed flush side by side. Vice versa However, it is advantageously not necessary to design each individual blade of the rotor individually in order to achieve a sufficient frequency detuning.

Ein weiterer Aspekt der Erfindung betrifft ein Flugzeugtriebwerk, wobei erfindungsgemäß vorgesehen ist, dass dieses einen Rotor nach einem der vorhergehenden Ausführungsbeispiele und/oder einen Schaufelkranz, welcher mittels eines Verfahrens nach einem der vorhergehenden Ausführungsbeispiele hergestellt ist, umfasst. Die sich hieraus ergebenden Merkmale und deren Vorteile sind den vorstehenden Beschreibungen zu entnehmen.Another aspect of the invention relates to an aircraft engine, wherein it is provided according to the invention that it comprises a rotor according to one of the preceding embodiments and / or a blade ring, which is produced by means of a method according to one of the preceding embodiments. The resulting features and their advantages can be found in the above descriptions.

Weitere Merkmale der Erfindung ergeben sich aus den Ansprüchen, dem Ausführungsbeispiel sowie anhand der Zeichnung. Die vorstehend in der Beschreibung genannten Merkmale und Merkmalskombinationen sowie die nachfolgend im Ausführungsbeispiel genannten Merkmale und Merkmalskombinationen sind nicht nur in der jeweils angegebenen Kombination, sondern auch in anderen Kombinationen verwendbar, ohne den Rahmen der Erfindung zu verlassen. Dabei zeigt:

  • Fig. 1 eine schematische Aufsicht von zwei bündig aneinander anliegenden Rotorschaufeln; und
  • Fig. 2 eine schematische Frontalansicht von zwei alternativ ausgebildeten Rotorschaufeln.
Further features of the invention will become apparent from the claims, the embodiment and the drawings. The features and combinations of features mentioned above in the description as well as the features and feature combinations mentioned below in the exemplary embodiment can be used not only in the respectively indicated combination but also in other combinations, without departing from the scope of the invention. Showing:
  • Fig. 1 a schematic plan view of two flush juxtaposed rotor blades; and
  • Fig. 2 a schematic frontal view of two alternately formed rotor blades.

Fig. 1 zeigt eine schematische Aufsicht von zwei bündig aneinander angelegten Rotorschaufeln 10a, 10b während der Herstellung eines Schaufelkranzes (nicht abgebildet) eines Rotors für ein Flugzeugtriebwerk. Von den Rotorschaufeln 10a, 10b sind die geschnitten dargestellten Schaufelblätter 12a, 12b erkennbar, welche mit Schaufelplattformen 14a, 14b der Rotorschaufeln 10a, 10b verbunden sind und sich in an sich bekannter Weise von den Schaufelplattformen 14a, 14b aus radial nach oben erstrecken. Radial unterhalb der Schaufelplattformen 14a, 14b umfassen die Rotorschaufeln 10a, 10b jeweilige Schaufelfüße 16a, 16b (s. Fig. 2), über welche in ebenfalls an sich bekannter Weise die Anbindung der Rotorschaufeln 10a, 10b an einen Rotorgrundkörper des Rotors erfolgt. Man erkennt, dass die beiden Rotorschaufeln 10a, 10b unterschiedlich ausgebildete Schaufelplattformen 14a, 14b umfassen und zu zwei unterschiedlichen Gruppen gehören. Die Schaufelplattformen 14a, 14b der beiden Gruppen von Rotorschaufeln 10a, 10b liegen bündig aneinander an und bilden im fertig montierten Schaufelkranz bzw. im fertigen Rotor ein durchgehendes, radial inneres Deckband, welches im zugeordneten Flugzeugtriebwerk den Strömungspfad begrenzt. Fig. 1 shows a schematic plan view of two flush-mounted rotor blades 10a, 10b during the manufacture of a blade ring (not shown) of a rotor for an aircraft engine. From the rotor blades 10a, 10b, the cut blades 12a, 12b are shown, which are connected to blade platforms 14a, 14b of the rotor blades 10a, 10b and extending in a conventional manner from the blade platforms 14a, 14b from radially upwards. Radially below the blade platforms 14a, 14b, the rotor blades 10a, 10b comprise respective blade roots 16a, 16b (see FIG. Fig. 2 ), via which the connection of the rotor blades 10a, 10b to a rotor main body of the rotor takes place in a manner also known per se. It can be seen that the two rotor blades 10a, 10b comprise differently designed blade platforms 14a, 14b and belong to two different groups. The blade platforms 14a, 14b of the two groups of rotor blades 10a, 10b lie flush against each other and form in the finished mounted blade ring or in the finished rotor a continuous, radially inner shroud, which limits the flow path in the associated aircraft engine.

Weiterhin sind auch die Schaufelblätter 12a, 12b gruppenspezifisch ausgebildet, wobei Schaufelblätter 12a bzw. 12b derselben Gruppe eine identische Schaufelblattgeometrie und Schaufelblätter 12a, 12b unterschiedlicher Gruppen unterschiedliche Schaufelblattgeometrien aufweisen. Die zur ersten Gruppe von Rotorschaufeln 10a gehörende Schaufelplattform 14a ist dabei derart ausgebildet, dass sie mit der zur zweiten Gruppe von Rotorschaufeln 10b gehörenden und komplementär zur Schaufelplattform 14a ausgebildeten Schaufelplattform 14b bündig in Anlage gebracht ist. Zu diesem Zweck weist die Schaufelplattform 14a der ersten Gruppe im Bereich I eine bezüglich der strichpunktierten Teilungsebene A randständige Vertiefung und im gegenüberliegenden Bereich II eine bezüglich der strichpunktierten Teilungsebene A randständige Erhebung auf. Die korrespondierende Schaufelplattform 14b der zweiten Gruppe weist dementsprechend im Bereich I eine zur Vertiefung der Schaufelplattform 14a komplementäre randständige Erhebung und im Bereich II eine zur Erhebung der Schaufelplattform 14a komplementäre randständige Vertiefung auf.Furthermore, the blades 12a, 12b are formed group-specific, wherein blades blades 12a and 12b of the same group have an identical blade geometry and blades 12a, 12b of different groups have different blade geometry. The blade platform 14a belonging to the first group of rotor blades 10a is designed such that it is flush with the blade platform 14b belonging to the second group of rotor blades 10b and designed to be complementary to the blade platform 14a. For this purpose, the blade platform 14a of the first group in the region I has a recess which is peripheral with respect to the dot-dashed dividing plane A and, in the opposite region II, a marginal elevation with respect to the dash-dotted dividing plane A. Corresponding blade platform 14b of the second group accordingly has a marginal elevation complementary to the depression of the blade platform 14a in region I and a marginal depression complementary to the elevation of blade platform 14a in region II.

Man erkennt, dass die Teilungsebene A dabei die theoretische Teilungsebene zwischen zwei herkömmlichen ausgebildeten Rotorschaufeln kennzeichnet, deren Schaufelplattformen durchgängig ebene Anlageflächen aufweisen und somit nicht vertauschsicher anordenbar sind. Zur Herstellung der unterschiedlichen Rotorschaufeln 10a, 10b, das heißt der Rotorschaufeln 10a der ersten Gruppe und der Rotorschaufeln 10b der zweiten Gruppe, kann es vorgesehen sein, dass zunächst Rotorschaufeln mit identisch ausgebildeten Schaufelplattformen bereitgestellt und die Vertiefungen und Erhebungen anschließend durch eine entsprechende Fräsbehandlung der Schaufelplattformen 14a, 14b erzeugt werden.It can be seen that the graduation plane A hereby identifies the theoretical graduation plane between two conventional rotor blades whose blade platforms have consistently planar contact surfaces and thus can not be arranged so that they are not interchangeable. To produce the different rotor blades 10a, 10b, that is, the rotor blades 10a of the first group and the rotor blades 10b of the second group, it may be provided that first rotor blades provided with identical blade platforms and the wells and elevations then by a corresponding milling treatment of the blade platforms 14a, 14b are generated.

Aus Fig. 1 wird weiterhin deutlich, dass die Schaufelplattform 14a der ersten Gruppe von Rotorschaufeln 10a nicht bündig an eine weitere Schaufelplattform 14a der ersten Gruppe, sondern nur an die zur zweiten Gruppe von Rotorschaufeln 10b gehörende Schaufelplattform 14b anlegbar ist. Entsprechend kann auch die zur zweiten Gruppe von Rotorschaufeln 10b gehörende Schaufelplattform 14b nur bündig an die zur ersten Gruppe gehörende Schaufelplattform 14a, aber nicht bündig an eine weitere Schaufelplattform 14b der zweiten Gruppe angelegt werden. Somit können nie zwei gleiche Rotorschaufeln 10a-10a bzw. 10b-10b derselben Gruppe mit identischen Schaufelplattformen 14a-14a bzw. 14b-14b bündig nebeneinander verbaut werden. Zur Ausbildung eines Schaufelkranzes werden statt dessen abwechselnd Schaufelplattformen 14a von Rotorschaufeln 10a der ersten Gruppe und Schaufelplattformen 14b von Rotorschaufeln 10b der zweiten Gruppe aneinander angelegt. Gleichzeitig ist es aufgrund der gruppenspezifischen Ausgestaltungen der Schaufelplattformen 14a, 14b stets sichergestellt, dass niemals zwei identische Schaufelblätter 12a-12a bzw. 12b-12b bündig nebeneinander angeordnet werden können. Hierdurch wird prozesssicher eine besonders wirksame Frequenzverstimmung des fertigen Schaufelkranzes und damit des fertig montierten Rotors erzielt.Out Fig. 1 It is also clear that the blade platform 14a of the first group of rotor blades 10a can not be placed flush with another blade platform 14a of the first group, but only on the blade platform 14b belonging to the second group of rotor blades 10b. Correspondingly, the blade platform 14b belonging to the second group of rotor blades 10b can also be placed flush with the paddle platform 14a belonging to the first group, but not flush with another paddle platform 14b of the second group. Thus, two identical rotor blades 10a-10a or 10b-10b of the same group with identical blade platforms 14a-14a or 14b-14b can never be installed flush next to each other. Instead, blade platforms 14a of rotor blades 10a of the first group and blade platforms 14b of rotor blades 10b of the second are alternately formed to form a blade ring Group attached to each other. At the same time it is always ensured due to the group-specific configurations of the blade platforms 14a, 14b that never two identical blades 12a-12a and 12b-12b can be arranged flush side by side. As a result, a particularly effective frequency detuning of the finished blade ring and thus of the assembled rotor is reliably achieved.

Aufgrund des integralen Verwechslungsschutzes der gruppenspezifisch ausgebildeten Rotorschaufeln 10a, 10b, welcher umgangssprachlich auch als "foolproof design" bezeichnet wird, ist es dabei ohne die Notwendigkeit zusätzlicher Bauteile zuverlässig ausgeschlossen, dass zwei identisch ausgebildete Rotorschaufeln 10a-10a bzw. 10b-10b, das heißt Rotorschaufeln derselben Gruppe, aneinander angelegt werden, da in diesem Fall stets eine offensichtliche Lücke zwischen benachbarten Schaufelplattformen 14a-14a bzw. 14b-14b verbleiben würde. Der Schaufelkranz könnte dann aufgrund des daraus resultierenden Bauraummehrbedarfs nicht mehr geschlossen werden. Grundsätzlich kann es auch vorgesehen sein, dass ein oder mehrere weitere Gruppen von unterschiedlich ausgebildeten Rotorschaufeln mit gruppenspezifisch ausgebildeten Schaufelplattformen verwendet werden, wobei die Schaufelplattformen stets derart auszubilden sind, dass sie nicht bündig an Schaufelplattformen von Rotorschaufeln derselben Gruppe, aber bündig an Schaufelplattformen von Rotorschaufeln wenigstens einer anderen Gruppe anlegbar sind.Due to the integral confusion protection of the group-specific trained rotor blades 10a, 10b, which colloquially is also referred to as "foolproof design", it is reliably excluded without the need for additional components that two identically designed rotor blades 10a-10a and 10b-10b, that is Rotor blades of the same group, be applied to each other, since in this case would always remain an obvious gap between adjacent blade platforms 14a-14a and 14b-14b. The blade ring could then no longer be closed because of the resulting increase in space requirements. In principle, it can also be provided that one or more further groups of differently shaped rotor blades are used with group-specific blade platforms, wherein the blade platforms are always to be designed such that they are not flush with blade platforms of rotor blades of the same group, but flush with blade platforms of rotor blades at least can be applied to another group.

Alternativ oder zusätzlich zu den gezeigten Vertiefungen und Erhebungen kann vorgesehen sein, dass die Vertiefungen und Erhebungen in seitlichen Kontakt- bzw. Anlageflächen der Schaufelplattformen 14a, 14b der Rotorschaufeln 10a, 10b ausgebildet sind und eine Art Nut-Feder-Verbindung bilden. Ein konstruktiv besonders einfacher Vertauschschutz kann beispielsweise dadurch erzielt werden, dass die erste Gruppe von Rotorschaufeln 10a beidseitige Erhebungen (Federn) und die zweite Gruppe von Rotorschaufeln 10b beidseitige Vertiefungen (Nuten) aufweist.Alternatively or in addition to the depressions and elevations shown, it can be provided that the depressions and elevations are formed in lateral contact or contact surfaces of the blade platforms 14a, 14b of the rotor blades 10a, 10b and form a tongue and groove connection. A structurally particularly simple swap protection can be achieved, for example, in that the first group of rotor blades 10a has bilateral elevations (springs) and the second group of rotor blades 10b has recesses (grooves) on both sides.

Fig. 2 zeigt eine schematische Frontalansicht von zwei alternativ ausgebildeten Rotorschaufeln 10a, 10b während der Herstellung eines Schaufelkranzes (nicht abgebildet) eines Rotors für ein Flugzeugtriebwerk. Von den Rotorschaufeln 10a, 10b sind die teilgeschnitten dargestellten Schaufelblätter 12a, 12b erkennbar, welche mit Schaufelplattformen 14a, 14b der Rotorschaufeln 10a, 10b verbunden sind und sich von den Schaufelplattformen 14a, 14b aus radial nach oben erstrecken. Radial unterhalb der Schaufelplattformen 14a, 14b umfassen die Rotorschaufeln 10a, 10b jeweilige Schaufelfüße 16a, 16b, über welche die Anbindung der Rotorschaufeln 10a, 10b an einen Rotorgrundkörper des Rotors erfolgt. Die Schaufelplattformen 14a, 14b weisen miteinander korrespondierende seitliche Anlageflächen III auf. Man erkennt, dass die Anlageflächen III schräg bzw. keilförmig bezüglich der entlang der Rotationsachse des Rotors verlaufenden Teilungsebene A ausgebildet sind, so dass die Schaufelplattform 14a der ersten Gruppe nur mit der Schaufelplattform 14b der zweiten Gruppe, nicht jedoch mit einer weiteren Schaufelplattform 14a der ersten Gruppe bündig in Anlage bringbar ist. Die Schaufelplattformen 14a, 14b der beiden Gruppen von Rotorschaufeln 10a, 10b bilden analog zum vorhergehenden Ausführungsbeispiel im fertig montierten Schaufelkranz bzw. im fertigen Rotor ein durchgehendes, radial inneres Deckband, welches im zugeordneten Flugzeugtriebwerk den Strömungspfad begrenzt. Die keilförmige Ausgestaltung der Anlageflächen bewirkt je nach Winkel des Keiles eine erhöhte Reibung zwischen den Anlageflächen III. Es ist jedoch zu betonen, dass die Anlageflächen III einen grundsätzlich beliebigen Konturverlauf aufweisen und beispielsweise gewellt und/oder gezackt ausgebildet sein können oder sonstige geeigneten Erhebungen/Vertiefungen aufweisen können. Wichtig ist lediglich, dass die Anlageflächen III der ersten Gruppe von Rotorschaufeln 10a nur mit korrespondierenden Anlageflächen III der zweiten (oder einer weiteren) Gruppe von Rotorschaufeln 10b, aber nicht mit Anlageflächen III der ersten Gruppe von Rotorschaufeln 10a bündig in Anlage bringbar sind. Fig. 2 shows a schematic frontal view of two alternately formed rotor blades 10a, 10b during the manufacture of a blade ring (not shown) of an aircraft engine rotor. Rotor blades 10a, 10b show partially cut airfoils 12a, 12b, which are connected to blade platforms 14a, 14b of rotor blades 10a, 10b and extend radially upward from blade platforms 14a, 14b. Radially below the blade platforms 14a, 14b, the rotor blades 10a, 10b comprise respective blade roots 16a, 16b, via which the connection of the rotor blades 10a, 10b to one Rotor body of the rotor takes place. The blade platforms 14a, 14b have mutually corresponding lateral contact surfaces III. It can be seen that the contact surfaces III are formed obliquely or wedge-shaped with respect to the axis of rotation of the rotor extending division plane A, so that the blade platform 14a of the first group only with the blade platform 14b of the second group, but not with a further blade platform 14a of the first Group can be brought flush into contact. The blade platforms 14a, 14b of the two groups of rotor blades 10a, 10b form a continuous, radially inner shroud, which limits the flow path in the assigned aircraft engine, analogous to the previous exemplary embodiment in the completely assembled blade ring or in the finished rotor. The wedge-shaped design of the contact surfaces causes depending on the angle of the wedge increased friction between the contact surfaces III. It should be emphasized, however, that the contact surfaces III have a fundamentally arbitrary contour profile and, for example, can be corrugated and / or serrated or have other suitable elevations / depressions. It is only important that the contact surfaces III of the first group of rotor blades 10a can be brought into contact flush only with corresponding contact surfaces III of the second (or another) group of rotor blades 10b, but not with contact surfaces III of the first group of rotor blades 10a.

Claims (12)

  1. A rotor for a turbomachine, particularly for an aircraft engine, with a blade ring comprising a plurality of differently configured rotor blades (10a, 10b) with blade platforms (14a, 14b) being in flush contact with each other, wherein the blade ring comprises at least two groups of differently designed rotor blades (10a, 10b), wherein each group of rotor blades (10a, 10b) are assigned to the blade platforms (14a, 14b), each of which can be brought into flush contact with a complementary blade platform (14a, 14b) of at least one other group of rotor blades (10a, 10b) and not with a blade platform (14a, 14b) of the same group of rotor blades (10a, 10b) characterized in that each blade platform (14a) of a first group of rotor blades (10a) comprises at least a marginal depression, in which a complementary marginal elevation of an adjacent blade platform (14b) of an assigned second group of rotor blades (10b) is positively arranged.
  2. A rotor according to claim 1, characterized in that the depression and /or elevation of the associated blade platform (14a, 14b) is inserted with the aid of a separating process, particularly by milling and/or grinding, into the associated blade platform (14a, 14b).
  3. A rotor according to claim 2, characterized in that each blade platform (14a) of the first group of rotor blades (10a) comprises a marginal depression and oppositely a marginal elevation and each blade platform (14b) of the second group of rotor blades (10b) comprises a marginal elevation complementary to the depression on the blade platform (14a) of the first group and a marginal depression complementary to the elevation of the blade platform (14a) of the first group.
  4. A rotor according to one of claims 1 to 3, characterized in that the depressions and the complementary elevations are configured in the area of the lateral contact surfaces of the rotor blades (10a, 10b), wherein the elevations are positively arranged in the assigned depressions.
  5. A rotor according to one of claims 1 to 4, characterized in that at least two of the groups of rotor blades (10a, 10b) comprise different blade geometries.
  6. A rotor according to one of claims 1 to 5, characterized in that at least two groups of rotor blades (10a, 10b) comprise blade platforms (14a, 14b) having mutually corresponding lateral contact surfaces (III).
  7. A rotor according to claim 6, characterized in that the contact surfaces (III) are configured at an angle and/or corrugated and/or jagged and/or in an irregular form.
  8. A method for manufacturing a blade ring of a rotor for a turbomachine, particularly for an aircraft engine, comprising the following steps:
    a) providing at least two groups of differently configured rotor blades (10a, 10b), wherein each group of rotor blades (10a, 10b) are assigned to blade platforms (14a, 14b), with at least one group of rotor blades (10a, 10b) which can be brought into flush contact with at least one other group of rotor blades (10a, 10b) and not with a blade platform (14a, 14b) from the same group of rotor blades (10a, 10b); and
    b) arranging the rotor blades (10a, 10b) in the form of the blade ring, wherein in each case mutually complementary blade platforms (14a, 14b) of the at least two groups of rotor blades (10a, 10b) are brought into flush contact with each other
    is characterized in that
    each blade platform (14a) of a first group of rotor blades (10a) comprises at least one marginal depression, in which a complementary marginal elevation of an adjacent blade platform (14b) is positively engaged with an assigned second group of rotor blades (10b).
  9. A method according to claim 8, characterized in that in step b) blade platforms (14a) of a first group of rotor blades (10a) and blade platforms (14b) of a second group of rotor blades (10b) are alternately brought into contact with each other.
  10. A method according to claims 8 or 9, characterized in that the blade roots of the rotor blades (10a, 10b) in step b) are arranged and fixed in a complementary groove of a rotor base body.
  11. A method according to one of claims 8 to 10, characterized in that in step a) at least two groups of rotor blades (10a, 10b) are made available with different rotor blade geometries.
  12. Aircraft engine, comprising a rotor according to one of the claims 1 to 7 and/or a blade ring, which is manufactured according to one of the claims 8 to 11.
EP12152073.8A 2012-01-23 2012-01-23 Rotor for a turbo machine and manufacturing process Not-in-force EP2617945B1 (en)

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EP12152073.8A EP2617945B1 (en) 2012-01-23 2012-01-23 Rotor for a turbo machine and manufacturing process
ES12152073.8T ES2668268T3 (en) 2012-01-23 2012-01-23 Rotor for a turbomachine and manufacturing process
US13/746,650 US9657581B2 (en) 2012-01-23 2013-01-22 Rotor for a turbomachine

Applications Claiming Priority (1)

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EP12152073.8A EP2617945B1 (en) 2012-01-23 2012-01-23 Rotor for a turbo machine and manufacturing process

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US9657581B2 (en) 2017-05-23
EP2617945A1 (en) 2013-07-24
ES2668268T3 (en) 2018-05-17
US20130189111A1 (en) 2013-07-25

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