WO2011054342A1 - Blisk, gas turbine and method for producing a blisk of said type - Google Patents
Blisk, gas turbine and method for producing a blisk of said type Download PDFInfo
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- WO2011054342A1 WO2011054342A1 PCT/DE2010/001280 DE2010001280W WO2011054342A1 WO 2011054342 A1 WO2011054342 A1 WO 2011054342A1 DE 2010001280 W DE2010001280 W DE 2010001280W WO 2011054342 A1 WO2011054342 A1 WO 2011054342A1
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- Prior art keywords
- blade segments
- blisk
- gas turbine
- rotor disk
- rotor
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Classifications
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/34—Rotor-blade aggregates of unitary construction, e.g. formed of sheet laminae
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
- B23P—METAL-WORKING NOT OTHERWISE PROVIDED FOR; COMBINED OPERATIONS; UNIVERSAL MACHINE TOOLS
- B23P15/00—Making specific metal objects by operations not covered by a single other subclass or a group in this subclass
- B23P15/006—Making specific metal objects by operations not covered by a single other subclass or a group in this subclass turbine wheels
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/12—Blades
- F01D5/22—Blade-to-blade connections, e.g. for damping vibrations
- F01D5/225—Blade-to-blade connections, e.g. for damping vibrations by shrouding
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2270/00—Control
- F05D2270/01—Purpose of the control system
- F05D2270/11—Purpose of the control system to prolong engine life
- F05D2270/114—Purpose of the control system to prolong engine life by limiting mechanical stresses
Definitions
- the invention relates to a blisk for a gas turbine according to the preamble of patent claim 1, a method for producing such a blisk and a gas turbine according to the preamble of patent claim 12.
- blisk stands for "bladed disk” and is generally used for an integrally bladed rotor disk
- vanes or vanes joined together to form vane segments are not positively and non-positively connected to the rotor but also attached integrally to the rotor disk as shown, for example, in U.S. Patent US 7,431,564 B2
- the blades may also be integrally formed with the rotor disk, however, the rotor disk and the blade segments shown separately in the U.S. Patent the advantage that they consist of a different material and may have different structural states than the rotor disk, so that the material properties of the blades or blade segments can be adjusted specifically to the respective requirements.
- the object of the present invention is to provide a blisk for a gas turbine, which eliminates the aforementioned disadvantages and is easy to produce in terms of production, to provide a method for producing such a blisk as well as a gas turbine with an improved rotor.
- a blisk according to the invention for a gas turbine in particular for an aircraft gas turbine, has a multiplicity of blades, which are combined to form vane segments arranged in a row.
- the blade segments each have a foot, via which they are materially connected to a rotor disk.
- at least one respective cavity or chamber is formed between the feet of adjacent blade segments.
- the vane segments are joined to sockets of the rotor disc. This has the advantage that the respective position of the blade segments is predetermined, so that complex adjustments can be omitted in the connection of the blade segments on the rotor disk.
- damping elements for influencing the vibration behavior of the blade segments are arranged in the cavities in one embodiment.
- the shrouds may also define a gap between them and thus be laterally spaced from each other.
- the blade segments are preferably made hollow, so that the blade segments are also cooled from the inside.
- An exemplary vane segment includes at least two individual vanes.
- cast blade segments it is advantageous if at least three individual blades to a Blade segment are joined together, since then a high pouring rate can be achieved by casting.
- more than three individual blades can be connected to a blade segment.
- the manufacturing costs are reduced exponentially with the number of integrated individual blades.
- the rotor disk and the blade segments are produced separately from one another. Subsequently, the blade segments in the region of their feet on the outer circumference of the rotor disc cohesively or otherwise integrally added, wherein between the feet of adjacent blade segments at least one cavity is formed in each case.
- the method according to the invention has the particular advantage that the production costs are significantly reduced compared to the known production methods. For example, blade root and shroud loops and the number of joints required are reduced. In addition, the production is facilitated by the fact that the available space per blade foot is increased. Furthermore, a higher rigidity of the blade segments is achieved than with individual blades.
- the joining of the blade segments to the rotor disk preferably takes place by friction welding, inductive high-frequency pressure welding or hot isostatic pressing.
- the blade segments can be grouted to bases of the rotor disks, which are executed directly in the formation of the rotor disk with or subsequently formed in a preparation of a rotor disk-side joining surface.
- the geometry of the joining surface depends, among other things, on the joining method to be used.
- the joining surface is preferably flat, for example, during friction welding. However, it can also be curved or have a different course.
- the base cuboid, cylindrical and drgl. Are executed.
- the blade segments are preferably cast. However, they can also be forged or generatively produced, for example. The type of production depends, among other things, on the position in the turbine. Thus, blade segments for the turbine side are preferred as castings and blade segments for the
- a gas turbine according to the invention in particular an aircraft gas turbine, has a rotor which is composed of a multiplicity of rotor disks.
- Each rotor disk has a multiplicity of blades, which are combined to form blade segments arranged in a row and connected in a material-locking manner to the rotor disk.
- the blades are spaced apart from one another on the foot side, so that a multiplicity of cavities extending in the axial direction is formed.
- the cavities are connected to a cooling system so that the rotor disk can be cooled on the outer peripheral side and the blade segments on the foot side.
- the temperature gradients are specifically adjustable, in particular in the foot region of the blade segments, which has a direct effect on the radial length of the joint zone.
- the present invention also relates to and comprises integrally bladed rotor rings, so-called bling or “bladed rings.”
- bling integrally bladed rotor rings
- the terms “blisk” and “bling” are treated synonymously and as synonymous in the context of the present invention not limited to the turbine side of a gas turbine, but also extends to the compressor side.
- FIGURE shows a section of a blisk according to the invention.
- a turbine blisk 2 according to the invention for a gas turbine has a rotor disk 4 and a multiplicity of blade segments 6, which are fastened on the outer circumference of the rotor disk 4 and arranged in a row of blades.
- the rotor disk 4 is for example a forged part or produced by powder metallurgy and has on the outer circumference a plurality of integral and cuboidal bases 8.
- the base 8 are spaced apart in the circumferential direction and each have a flat joining surface 10 on the circumference. However, the joining surface 10 may also be curved.
- the blade segments 6 are castings, on the compressor side also forged parts, and each have two blades 12, which are arranged between an inner shroud 14 and an outer shroud 16. They are each hollow with two oppositely oriented side core exits 18.
- the blade segments 6 each have an approximately cuboid base 20 with a plane facing away from the blades 12 flat connecting surface 22, with which they cohesively on the respective joining surface 10 of the base 8, in particular by means a friction welding process, are connected.
- the cross section of the connecting surface 22 preferably corresponds to the cross section of the joining surface 10, wherein the feet 20 are tapered in the direction of their respective connecting surface 22.
- a cavity or a chamber 24 is formed, which is delimited in the radial direction by a circumferential surface section 26 of the rotor disk 4 and by shroud surface sections 28, 30 of the inner cover strips 14.
- the feet 20 with the sockets 8 each have two opposite side surfaces 32, 34.
- the side surfaces 32, 34 are planar and extend radially to the rotor disk 4, so that they are employed accordingly and the cavities 24 of the peripheral surface portion 26 in the direction of Shroud surface portions 28, 30 are extended. They open the rotor disk side via a rounded transition region 36 in the peripheral surface portion 26 which is concave.
- Inside cover band side open the side surfaces 32, 34 in the shroud surface portions 28, 30.
- the shroud surface portions 28, 30 are also concave, but they have a stronger curvature than that
- the cavities 24 are connected on the foot side with a cooling system for cooling the blade segments 6 and on the outer peripheral side for cooling the rotor disk 4.
- Damping elements or inserts arranged, for example, as material thickening in Foot area or in the cavity-side transition region may be formed by the feet 20 to the inner shroud 14.
- the inner cover strips 14 are slightly spaced apart in the region of their lateral wedge surfaces 38, so that a fluidically favorable closed or virtually closed inner side inner band surface 40 is provided.
- the outer shrouds 16 are based at least during operation due to the thermal expansion of the blade segments 6 with their contact surfaces 42 against each other, wherein to achieve a positive connection and thus improve the support effect their contact surfaces 42, for example, Z-shaped formed. However, they can also be double-Z-shaped and similar.
- the rotor disk 4 and the blade segments 6 are produced separately from one another.
- the rotor disk 4 is a forged part, but it can also be produced by a generative manufacturing method.
- the pedestals 8 can be formed on the outer circumference of the rotor disk 4 via a generative manufacturing process.
- the blade segments 6 are preferably castings and have at least two blades 12 at a time. After the separate production of the rotor disk 4 and the blade segments 6, these are added via their foot-side connecting surfaces 22 to the socket-side joining surfaces 10 of the rotor disk 4 by a friction welding process. In this case, a cavity 24 is formed between adjacent legs 20 due to the spacing between the base 8 and the same cross-sections of the base 8 and the feet 20.
- the blade segments 6 can also be connected to the rotor disk 4 by high-frequency induction-pressure welding (IHFP) or hot isostatic pressing (HIP) and the like.
- IHFP high-frequency induction-pressure welding
- HIP hot isostatic pressing
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Ceramic Engineering (AREA)
- Pressure Welding/Diffusion-Bonding (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
Abstract
Description
Beschreibung description
Blisk, Gasturbine und Verfahren zur Herstellung einer derartigen Blisk Blisk, gas turbine and method for producing such a blisk
Die Erfindung betrifft eine Blisk für eine Gasturbine nach dem Oberbegriff des Patentanspruchs 1, ein Verfahren zur Herstellung einer derartigen Blisk sowie eine Gasturbine nach dem Oberbegriff des Patentanspruchs 12. The invention relates to a blisk for a gas turbine according to the preamble of patent claim 1, a method for producing such a blisk and a gas turbine according to the preamble of patent claim 12.
Der Begriff Blisk steht für„Bladed Disk" und wird im Allgemeinen für eine integral beschaufelte Rotorscheibe verwendet. Im Gegensatz zu dem in der US 2007/0059181 AI gezeigten Rotor werden Schaufeln bzw. zu Schaufelsegmenten zusammengefügte Einzelschaufeln nicht form- und kraftschlüssig mit dem Rotor verbunden, sondern wie zum Beispiel in dem US-Patent US 7,431,564 B2 gezeigt stoffschlüssig an einer Rotorscheibe angefügt. Die Schaufeln können auch integral mit der Rotorscheibe ausgebildet werden, jedoch hat die in dem US-Patent gezeigte getrennte Herstellung der Rotorscheibe und der Schaufeln bzw. Schaufelsegmente den Vorteil, dass diese aus einem anderen Material bestehen und andere Gefügezustände aufweisen können als die Rotorscheibe, so dass die Materialeigenschaften der Schaufeln bzw. Schaufelsegmente gezielt auf die jeweiligen Anforderungen eingestellt werden können. The term blisk stands for "bladed disk" and is generally used for an integrally bladed rotor disk In contrast to the rotor shown in US 2007/0059181 AI, vanes or vanes joined together to form vane segments are not positively and non-positively connected to the rotor but also attached integrally to the rotor disk as shown, for example, in U.S. Patent US 7,431,564 B2 The blades may also be integrally formed with the rotor disk, however, the rotor disk and the blade segments shown separately in the U.S. Patent the advantage that they consist of a different material and may have different structural states than the rotor disk, so that the material properties of the blades or blade segments can be adjusted specifically to the respective requirements.
Nachteilig an der in dem US-Patent gezeigten Blisk ist jedoch, dass die Schaufeln bzw. Schaufelsegmente, bevor sie mit der Rotorscheibe verbunden werden, zu einem Kranz gefügt werden. Dabei werden die Schaufeln bzw. Schaufelsegmente im Bereich ihrer Füße miteinander verbunden, die entsprechend radial verlängert und keilförmig ausgebildet sind. Die exakte Herstellung sowie die genaue Verbindung der Füße sind jedoch verhältnismäßig aufwendig. However, it is a disadvantage of the blisk shown in the US patent that the blades or blade segments are joined into a ring before they are connected to the rotor disk. In this case, the blades or blade segments in the region of their feet are connected to each other, which are correspondingly radially extended and wedge-shaped. However, the exact production and the exact connection of the feet are relatively expensive.
' Aufgabe der vorliegenden Erfindung ist es, eine Blisk für eine Gasturbine, die die vorgenannten Nachteile beseitigt und fertigungstechnisch einfach herzustellen ist, ein Verfahren zur Herstellung einer derartigen Blisk sowie eine Gasturbine mit einem verbesserten Rotor zu schaffen. The object of the present invention is to provide a blisk for a gas turbine, which eliminates the aforementioned disadvantages and is easy to produce in terms of production, to provide a method for producing such a blisk as well as a gas turbine with an improved rotor.
Diese Aufgabe wird gelöst durch eine Blisk mit den Merkmalen des Patentanspruchs 1, durch ein Verfahren mit den Schritten des Patentanspruchs 9 sowie durch eine Gasturbine mit den Merkmalen des Patentanspruchs 12. Eine erfindungsgemäße Blisk für eine Gasturbine, insbesondere für eine Fluggasturbine, hat eine Vielzahl von Schaufeln, die zu in einer Reihe angeordneten Schaufelsegmenten zusammengefasst sind. Die Schaufelsegmente haben jeweils einen Fuß, über den sie stoffschlüssig mit einer Rotorscheibe verbunden sind. Erfindungsgemäß ist zwischen den Füßen benachbarter Schaufelsegmente zumindest jeweils ein Hohlraum bzw. eine Kammer gebildet. This object is achieved by a blisk having the features of patent claim 1, by a method having the steps of patent claim 9, and by a gas turbine having the features of patent claim 12. A blisk according to the invention for a gas turbine, in particular for an aircraft gas turbine, has a multiplicity of blades, which are combined to form vane segments arranged in a row. The blade segments each have a foot, via which they are materially connected to a rotor disk. According to the invention, at least one respective cavity or chamber is formed between the feet of adjacent blade segments.
Diese Lösung hat den Vorteil, dass die Füße nicht in seitlicher Anlage miteinander sind, wodurch eine verbesserte Kühlung der Schaufelsegmente und der Rotorscheibe erzielbar ist. Des Weiteren ist die Fertigung des erfindungsgemäßen Blisk gegenüber dem bekannten Stand der Technik nach dem US-Patent aufgrund der seitlichen Beabstandung der Schaufelfüße vereinfacht, wodurch die Herstellkosten signifikant reduziert werden. Insbesondere werden Scheibenlasten im Fußbereich sowie Randlasten vollständig bzw. nahezu vollständig beseitigt. This solution has the advantage that the feet are not in lateral contact with each other, whereby an improved cooling of the blade segments and the rotor disk can be achieved. Furthermore, the manufacture of the blisk according to the invention over the known prior art according to the US patent is simplified due to the lateral spacing of the blade roots, whereby the production costs are significantly reduced. In particular, disk loads in the foot area as well as edge loads are completely or almost completely eliminated.
Bei einem Ausführungsbeispiel werden die Schaufelsegmente an Sockeln der Rotorscheibe gefügt. Dies hat den Vorteil, dass die jeweilige Position der Schaufelsegmente vorbestimmt ist, so dass aufwendige Justierarbeiten bei der Anbindung der Schaufelsegmente an der Rotorscheibe entfallen können. In one embodiment, the vane segments are joined to sockets of the rotor disc. This has the advantage that the respective position of the blade segments is predetermined, so that complex adjustments can be omitted in the connection of the blade segments on the rotor disk.
Neben der bereits erwähnten fußseitigen Kühlung sind bei einem Ausführungsbeispiel in den Hohlräumen Dämpfungselemente zur Beeinflussung des Schwingungsverhaltens der Schaufelsegmente angeordnet. Darüber hinaus ist es zur Einstellung des Schwingungs- bzw. Dämpfungsverhaltens sowie zur Redzierung der Strömungsverluste vorteilhaft, wenn die Schaufelsegmente mit jeweils einem Innendeckband und/oder einem Außendeckband versehen sind, die sich zumindest in Betrieb in Anlage, beispielsweise unter Vorspannung, mit benachbarten Deckbändera befinden. Die Deckbänder können jedoch auch einen Spalt zwischen sich definieren und somit seitlich voneinander beabstandet sein. In addition to the foot-side cooling already mentioned, damping elements for influencing the vibration behavior of the blade segments are arranged in the cavities in one embodiment. In addition, it is advantageous for adjusting the vibration or damping behavior and for reducing the flow losses when the blade segments are each provided with an inner shroud and / or an outer shroud, which are at least in operation in conditioning, for example under bias, with adjacent shrouds , However, the shrouds may also define a gap between them and thus be laterally spaced from each other.
Die Schaufelsegmente sind vorzugsweise hohl ausgeführt, so dass die Schaufelsegmente ebenfalls von innen kühlbar sind. The blade segments are preferably made hollow, so that the blade segments are also cooled from the inside.
Ein beispielhaftes Schaufelsegment umfasst mindestens zwei Einzelschaufeln. Bei gegossenen Schaufelsegmenten ist es vorteilhaft, wenn zumindest drei Einzelschaufeln zu einem Schaufelsegment zusammengefügt sind, da dann eine gießtechnisch hohe Ausbringrate zu erzielen ist. Selbstverständlich sind jedoch auch mehr als drei Einzelschaufeln zu einem Schaufelsegment verbindbar. Insbesondere reduzieren sich die Herstellungskosten exponential mit der Anzahl der eingebundenen Einzelschaufeln. An exemplary vane segment includes at least two individual vanes. In cast blade segments, it is advantageous if at least three individual blades to a Blade segment are joined together, since then a high pouring rate can be achieved by casting. Of course, however, more than three individual blades can be connected to a blade segment. In particular, the manufacturing costs are reduced exponentially with the number of integrated individual blades.
Bei einem erfindungsgemäßen Verfahren zur Herstellung einer derartigen Blisk werden die Rotorscheibe und die Schaufelsegmente getrennt voneinander hergestellt. Anschließend werden die Schaufelsegmente im Bereich ihrer Füße am Außenumfang der Rotorscheibe stoffschlüssig oder andersartig integral angefügt, wobei zwischen den Füßen benachbarter Schaufelsegmente zumindest jeweils ein Hohlraum gebildet wird. In a method according to the invention for producing such a blisk, the rotor disk and the blade segments are produced separately from one another. Subsequently, the blade segments in the region of their feet on the outer circumference of the rotor disc cohesively or otherwise integrally added, wherein between the feet of adjacent blade segments at least one cavity is formed in each case.
Das erfindungsgemäße Verfahren hat insbesondere den Vorteil, dass die Herstellungskosten signifikant gegenüber den bekannten Herstellungsverfahren reduziert werden. So werden zum Beispiel Schaufelfuß- und Deckbandschleifen, sowie die Anzahl der notwendigen Fügungen reduziert. Darüber hinaus wird die Herstellung dadurch erleichtert, dass der zur Verfügung stehende Platz pro Schaufelfuß vergrößert wird. Ferner wird eine höhere Steifigkeit der Schaufelsegmente als bei Einzelschaufeln erzielt. The method according to the invention has the particular advantage that the production costs are significantly reduced compared to the known production methods. For example, blade root and shroud loops and the number of joints required are reduced. In addition, the production is facilitated by the fact that the available space per blade foot is increased. Furthermore, a higher rigidity of the blade segments is achieved than with individual blades.
Das Fügen der Schaufelsegmente an der Rotorscheibe erfolgt bevorzugterweise durch Reibschweißen, induktives Hochfrequenzpressschweißen oder durch heißisostatisches Pressen. Dabei können die Schaufelsegmente an Sockeln der Rotorscheiben gefugt werden, die direkt bei der Ausbildung der Rotorscheibe mit ausgeführt oder nachträglich bei einer Vorbereitung einer rotorscheibenseitigen Fügefläche ausgebildet werden. Die Geometrie der Fügefläche richtet sich unter anderem nach dem anzuwendenden Fügeverfahren. So ist die Fügefläche zum Beispiel beim Reibschweißen bevorzugterweise eben ausgebildet. Sie kann jedoch auch gekrümmt sein oder einen andersartigen Verlauf aufweisen. Ebenso können die Sockel quaderförmig, zylindrisch und drgl. ausgeführt werden. The joining of the blade segments to the rotor disk preferably takes place by friction welding, inductive high-frequency pressure welding or hot isostatic pressing. In this case, the blade segments can be grouted to bases of the rotor disks, which are executed directly in the formation of the rotor disk with or subsequently formed in a preparation of a rotor disk-side joining surface. The geometry of the joining surface depends, among other things, on the joining method to be used. Thus, the joining surface is preferably flat, for example, during friction welding. However, it can also be curved or have a different course. Likewise, the base cuboid, cylindrical and drgl. Are executed.
Bei einem Ausführungsbeispiel werden die Schaufelsegmente vorzugsweise gegossen. Sie können aber auch beispielsweise geschmiedet oder generativ hergestellt werden. Die Art der Herstellung richtet sich unter anderem nach der Position in der Turbine. So werden Schaufelsegmente für die Turbinenseite bevorzugterweise als Gussteile und Schaufelsegmente für dieIn one embodiment, the blade segments are preferably cast. However, they can also be forged or generatively produced, for example. The type of production depends, among other things, on the position in the turbine. Thus, blade segments for the turbine side are preferred as castings and blade segments for the
Verdichterseite auch als Schmiedeteile ausgeführt. Eine erfindungsgemäße Gasturbine, insbesondere eine Fluggasturbine, hat einen Rotor, der aus einer Vielzahl von Rotorscheiben zusammengesetzt ist. Jede Rotorscheibe weist eine Vielzahl von Schaufeln auf, die zu in einer Reihe angeordneten Schaufelsegmenten zusammen- gefasst und stoffschlüssig mit der Rotorscheibe verbunden sind. Erfindungsgemäß sind die Schaufeln fußseitig voneinander beabstandet, so dass eine Vielzahl von sich in axialer Richtung erstreckende Hohlräume gebildet ist. Vorteilhafterweise sind die Hohlräume mit einem Kühlungssystem verbunden, so dass die Rotorscheibe außenumfangseitig und die Schaufelsegmente fußseitig gekühlt werden können. Hierdurch sind die Temperaturgradienten insbesondere im Fußbereich der Schaufelsegmente gezielt einstellbar, was sich unmittelbar auf die radiale Länge der Fügezone auswirkt. Compressor side also designed as forgings. A gas turbine according to the invention, in particular an aircraft gas turbine, has a rotor which is composed of a multiplicity of rotor disks. Each rotor disk has a multiplicity of blades, which are combined to form blade segments arranged in a row and connected in a material-locking manner to the rotor disk. According to the invention, the blades are spaced apart from one another on the foot side, so that a multiplicity of cavities extending in the axial direction is formed. Advantageously, the cavities are connected to a cooling system so that the rotor disk can be cooled on the outer peripheral side and the blade segments on the foot side. As a result, the temperature gradients are specifically adjustable, in particular in the foot region of the blade segments, which has a direct effect on the radial length of the joint zone.
Sonstige vorteilhafte Ausführungsbeispiele der Erfindung sind Gegenstand weiterer Unteransprüche. Other advantageous embodiments of the invention are the subject of further subclaims.
Die vorliegende Erfindung bezieht sich selbstverständlich auch auf integral beschaufelte Rotorringe, sogenannte Bling bzw.„Bladed Rings" und umfasst diese. Die Begriffe„Blisk" und „Bling" werden im Rahmen der vorliegenden Erfindung synonym und als gleichbedeutend behandelt. Ebenso ist die erfindungsgemäße Lösung nicht auf die Turbinenseite einer Gasturbine beschränkt, sondern erstreckt sich ebenfalls auf die Verdichterseite. Of course, the present invention also relates to and comprises integrally bladed rotor rings, so-called bling or "bladed rings." The terms "blisk" and "bling" are treated synonymously and as synonymous in the context of the present invention not limited to the turbine side of a gas turbine, but also extends to the compressor side.
Im Folgenden wird ein bevorzugtes Ausführungsbeispiel der Erfindung anhand einer schematischen Figur näher erläutert. Die einzige Figur zeigt einen Ausschnitt einer erfindungsgemäßen Blisk. In the following, a preferred embodiment of the invention will be explained in more detail with reference to a schematic figure. The single FIGURE shows a section of a blisk according to the invention.
In den Figuren tragen gleiche konstruktive Elemente die gleichen Bezugsziffern, wobei bei mehreren gleichen konstruktiven Elementen in einer Figur aus Gründen der Übersichtlichkeit nur einige dieser konstruktiven Elemente mit einem Bezugszeichen versehen sind. In the figures, the same structural elements bear the same reference numerals, with several identical structural elements in a figure for reasons of clarity, only some of these constructive elements are provided with a reference numeral.
Eine erfindungsgemäße Turbinen-Blisk 2 für eine Gasturbine weist eine Rotorscheibe 4 und eine Vielzahl von Schaufelsegmenten 6 auf, die am Außenumfang der Rotorscheibe 4 befestigt und in einer Schaufelreihe angeordnet sind. Die Rotorscheibe 4 ist beispielsweise ein Schmiedeteil oder pulvermetallurgisch hergestellt und weist außenumfangseitig eine Vielzahl von integralen und quaderartigen Sockeln 8 auf. Die Sockel 8 sind in Umfangsrichtung voneinander beabstandet und weisen umfangsseitig jeweils eine ebene Fügefläche 10 auf. Die Fügefläche 10 kann jedoch auch gekrümmt ausgeführt sein. A turbine blisk 2 according to the invention for a gas turbine has a rotor disk 4 and a multiplicity of blade segments 6, which are fastened on the outer circumference of the rotor disk 4 and arranged in a row of blades. The rotor disk 4 is for example a forged part or produced by powder metallurgy and has on the outer circumference a plurality of integral and cuboidal bases 8. The base 8 are spaced apart in the circumferential direction and each have a flat joining surface 10 on the circumference. However, the joining surface 10 may also be curved.
Die Schaufelsegmente 6 sind Gussteile, auf der Verdichterseite auch Schmiedeteile, und weisen jeweils zwei Schaufelblätter 12 auf, die zwischen einem Innendeckband 14 und einem Außendeckband 16 angeordnet sind. Sie sind jeweils hohl ausgeführt mit zwei entgegengesetzt zueinander orientierten seitlichen Kernaustritten 18. Die Schaufelsegmente 6 haben jeweils einen etwa quaderartigen Fuß 20 mit einer von den Schaufelblättern 12 abgewandten ebenen Verbindungsfläche 22, mit der sie an der jeweiligen Fügefläche 10 der Sockel 8 stoffschlüssig, insbesondere mittels eines Reibschweißverfahrens, angebunden sind. Der Querschnitt der Verbindungsfläche 22 entspricht vorzugsweise dem Querschnitt der Fügefläche 10, wobei die Füße 20 in Richtung ihrer jeweiligen Verbindungsfläche 22 verjüngend ausgebildet sind. The blade segments 6 are castings, on the compressor side also forged parts, and each have two blades 12, which are arranged between an inner shroud 14 and an outer shroud 16. They are each hollow with two oppositely oriented side core exits 18. The blade segments 6 each have an approximately cuboid base 20 with a plane facing away from the blades 12 flat connecting surface 22, with which they cohesively on the respective joining surface 10 of the base 8, in particular by means a friction welding process, are connected. The cross section of the connecting surface 22 preferably corresponds to the cross section of the joining surface 10, wherein the feet 20 are tapered in the direction of their respective connecting surface 22.
Zwischen benachbarten Füßen 20 der Schaufelsegmente 6 ist erfindungsgemäß jeweils ein Hohlraum bzw. eine Kammer 24 gebildet, der in radialer Richtung von einem Umfangsflä- chenabschnitt 26 der Rotorscheibe 4 und von Deckbandflächenabschnitten 28, 30 der Innendeckbänder 14 begrenzt ist. Dabei bilden die Füße 20 mit den Sockeln 8 jeweils zwei gegenüberliegende Seitenflächen 32, 34. Die Seitenflächen 32, 34 sind eben ausgebildet und verlaufen radial zur Rotorscheibe 4, so dass sie zueinander entsprechend angestellt sind und die Hohlräume 24 von dem Umfangsflächenabschnitt 26 in Richtung der Deckbandflächenabschnitte 28, 30 erweitert sind. Sie münden rotorscheibenseitig über einen abgerundeten Übergangsbereich 36 in den Umfangsflächenabschnitt 26, der konkav ausgebildet ist. Innendeckbandseitig münden die Seitenflächen 32, 34 in die Deckbandflächenabschnitte 28, 30. Die Deckbandflächenabschnitte 28, 30 sind ebenfalls konkav ausgebildet, jedoch weisen sie eine stärke Wölbung als der Between adjacent feet 20 of the blade segments 6, according to the invention, in each case a cavity or a chamber 24 is formed, which is delimited in the radial direction by a circumferential surface section 26 of the rotor disk 4 and by shroud surface sections 28, 30 of the inner cover strips 14. The feet 20 with the sockets 8 each have two opposite side surfaces 32, 34. The side surfaces 32, 34 are planar and extend radially to the rotor disk 4, so that they are employed accordingly and the cavities 24 of the peripheral surface portion 26 in the direction of Shroud surface portions 28, 30 are extended. They open the rotor disk side via a rounded transition region 36 in the peripheral surface portion 26 which is concave. Inside cover band side open the side surfaces 32, 34 in the shroud surface portions 28, 30. The shroud surface portions 28, 30 are also concave, but they have a stronger curvature than that
Umfangsflächenabschnitt 26 auf. Peripheral surface portion 26 on.
Die Hohlräume 24 sind mit einem Kühlsystem zur Kühlung der Schaufelsegmente 6 fuß- seitig und zur Kühlung der Rotorscheibe 4 außenumfangsseitig verbunden. Zur Einstellung desThe cavities 24 are connected on the foot side with a cooling system for cooling the blade segments 6 and on the outer peripheral side for cooling the rotor disk 4. To set the
Schwingungsverhaltens der Schaufelsegmente 6 sind in den Hohlräumen 24 nicht gezeigteVibration behavior of the blade segments 6 are not shown in the cavities 24
Dämpfungselemente bzw. Inserts angeordnet, die zum Beispiel als Materialverdickungen im Fußbereich oder im hohlraumseitigen Übergangsbereich von den Füßen 20 zum Innendeckband 14 ausgebildet sein können. Damping elements or inserts arranged, for example, as material thickening in Foot area or in the cavity-side transition region may be formed by the feet 20 to the inner shroud 14.
Die Innendeckbänder 14 sind im Bereich Ihrer seitlichen Keilflächen 38 gering voneinander beabstandet, so dass eine strömungstechnisch günstige geschlossene bzw. nahezu geschlossene ringraumseitige Innendeckbandfläche 40 geschaffen ist. Die Außendeckbänder 16 stützen sich zumindest im Betrieb aufgrund der Wärmeausdehnung der Schaufelsegmente 6 mit ihren Kontaktflächen 42 gegeneinander ab, wobei zur Erzielung eines Formschlusses und somit zur Verbesserung der Stützwirkung ihre Kontakflächen 42 beispielsweise Z-fÖrmig ausgebildet sind. Sie können jedoch auch Doppel-Z-formig und ähnlich ausgeführt sein. The inner cover strips 14 are slightly spaced apart in the region of their lateral wedge surfaces 38, so that a fluidically favorable closed or virtually closed inner side inner band surface 40 is provided. The outer shrouds 16 are based at least during operation due to the thermal expansion of the blade segments 6 with their contact surfaces 42 against each other, wherein to achieve a positive connection and thus improve the support effect their contact surfaces 42, for example, Z-shaped formed. However, they can also be double-Z-shaped and similar.
Bei einem erfindungsgemäßen Verfahren zur Herstellung einer derartigen Blisk 2 werden die Rotorscheibe 4 und die Schaufelsegmente 6 getrennt voneinander hergestellt. Wie bereits erwähnt ist die Rotorscheibe 4 ein Schmiedeteil, jedoch kann sie auch nach einem generativen Fertigungsverfahren hergestellt werden. Insbesondere können die Sockel 8 über ein generatives Fertigungsverfahren am Außenumfang der Rotorscheibe 4 ausgebildet werden. Die Schaufelsegmente 6 sind vorzugsweise Gussteile und weisen zumindest jeweils zwei Schaufelblätter 12 auf. Nach der getrennten Herstellung der Rotorscheibe 4 und der Schaufelsegmente 6 werden diese über ihre fußseitigen Verbindungsflächen 22 an den sockelseitigen Fügeflächen 10 der Rotorscheibe 4 nach einem Reibschweißverfahren angefügt. Dabei wird aufgrund der Beabstan- dung der Sockel 8 zueinander und den gleichen Querschnitten der Sockel 8 und der Füße 20 jeweils ein Hohlraum 24 zwischen benachbarten Füßen 20 ausgebildet. In a method according to the invention for producing such a blisk 2, the rotor disk 4 and the blade segments 6 are produced separately from one another. As already mentioned, the rotor disk 4 is a forged part, but it can also be produced by a generative manufacturing method. In particular, the pedestals 8 can be formed on the outer circumference of the rotor disk 4 via a generative manufacturing process. The blade segments 6 are preferably castings and have at least two blades 12 at a time. After the separate production of the rotor disk 4 and the blade segments 6, these are added via their foot-side connecting surfaces 22 to the socket-side joining surfaces 10 of the rotor disk 4 by a friction welding process. In this case, a cavity 24 is formed between adjacent legs 20 due to the spacing between the base 8 and the same cross-sections of the base 8 and the feet 20.
Alternativ zum Reibschweißen können die Schaufelsegmente 6 auch durch induktives Hochfrequenzpressschweißen (IHFP) oder heißisostatisches Pressen (HIP) und dergleichen mit der Rotorscheibe 4 verbunden werden. As an alternative to friction welding, the blade segments 6 can also be connected to the rotor disk 4 by high-frequency induction-pressure welding (IHFP) or hot isostatic pressing (HIP) and the like.
Offenbart ist eine Blisk 2 für eine Gasturbine mit einer Vielzahl von Schaufelsegmenten 6, die eine Vielzahl von Schaufelblättern 12 und jeweils einen Fuß 20 zur Befestigung an der Rotorscheibe 4 aufweist, wobei zwischen den Füßen 20 zumindest jeweils ein Hohlraum bzw. eine Kammer 24 gebildet ist, ein Verfahren zur Herstellung einer derartigen Blisk 2, sowie eine Gasturbine mit einem Rotor, der aus mehreren derartiger Blisk 2 zusammengesetzt ist. Disclosed is a blisk 2 for a gas turbine with a plurality of blade segments 6, which has a plurality of blades 12 and one foot 20 for attachment to the rotor disk 4, wherein between the feet 20 at least one cavity or a chamber 24 is formed , a method for producing such a blisk 2, and a gas turbine with a rotor, which is composed of a plurality of such blisk 2.
Claims
Applications Claiming Priority (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| DE102009052305A DE102009052305A1 (en) | 2009-11-07 | 2009-11-07 | Blisk, gas turbine and method for producing such a blisk |
| DE102009052305.7 | 2009-11-07 |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| WO2011054342A1 true WO2011054342A1 (en) | 2011-05-12 |
Family
ID=43430833
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| PCT/DE2010/001280 Ceased WO2011054342A1 (en) | 2009-11-07 | 2010-10-30 | Blisk, gas turbine and method for producing a blisk of said type |
Country Status (2)
| Country | Link |
|---|---|
| DE (1) | DE102009052305A1 (en) |
| WO (1) | WO2011054342A1 (en) |
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20150098802A1 (en) * | 2013-10-08 | 2015-04-09 | General Electric Company | Shrouded turbine blisk and method of manufacturing same |
| US10247015B2 (en) | 2017-01-13 | 2019-04-02 | Rolls-Royce Corporation | Cooled blisk with dual wall blades for gas turbine engine |
| US10415403B2 (en) | 2017-01-13 | 2019-09-17 | Rolls-Royce North American Technologies Inc. | Cooled blisk for gas turbine engine |
| US10718218B2 (en) | 2018-03-05 | 2020-07-21 | Rolls-Royce North American Technologies Inc. | Turbine blisk with airfoil and rim cooling |
| US10934865B2 (en) | 2017-01-13 | 2021-03-02 | Rolls-Royce Corporation | Cooled single walled blisk for gas turbine engine |
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|---|---|---|---|---|
| GB201206269D0 (en) * | 2012-04-05 | 2012-05-23 | Napier Turbochargers Ltd | Axial Flow Turbine Blisc |
| ES2532582T3 (en) * | 2012-08-09 | 2015-03-30 | Mtu Aero Engines Gmbh | Method for manufacturing a TiAl blade crown segment for a gas turbine, as well as a corresponding blade crown segment |
| US20150354374A1 (en) * | 2014-06-09 | 2015-12-10 | General Electric Company | Turbine blisk and method of manufacturing thereof |
| US9551230B2 (en) * | 2015-02-13 | 2017-01-24 | United Technologies Corporation | Friction welding rotor blades to a rotor disk |
| DE102018217597A1 (en) * | 2018-10-15 | 2020-04-16 | Siemens Aktiengesellschaft | Control wheel arrangement for a steam turbine and method for producing a control wheel arrangement |
| WO2020099184A1 (en) * | 2018-11-15 | 2020-05-22 | Rolls-Royce Deutschland Ltd & Co Kg | Method for producing a component for a turbomachine |
| CN116237567B (en) * | 2023-04-20 | 2025-09-16 | 中国航发航空科技股份有限公司 | Machining method applied to blisk blade |
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| US7431564B2 (en) | 2004-04-16 | 2008-10-07 | Rolls Royce Plc | Turbine blisk |
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| DE102007037208B4 (en) * | 2007-08-07 | 2013-06-20 | Mtu Aero Engines Gmbh | Turbine blade with at least one insert sleeve for cooling the turbine blade |
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- 2009-11-07 DE DE102009052305A patent/DE102009052305A1/en not_active Withdrawn
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| DE2423036A1 (en) * | 1973-05-14 | 1974-12-05 | British Leyland Uk Ltd | TURBINE DISC CAST IN ONE PIECE |
| US20060099078A1 (en) * | 2004-02-03 | 2006-05-11 | Honeywell International Inc., | Hoop stress relief mechanism for gas turbine engines |
| US7431564B2 (en) | 2004-04-16 | 2008-10-07 | Rolls Royce Plc | Turbine blisk |
| US20070059181A1 (en) | 2005-01-26 | 2007-03-15 | Mtu Aero Engines Gmbh | Apparatus and method for securing a rotor blade in a rotor of a turbine-type machine |
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| US20150098802A1 (en) * | 2013-10-08 | 2015-04-09 | General Electric Company | Shrouded turbine blisk and method of manufacturing same |
| US10247015B2 (en) | 2017-01-13 | 2019-04-02 | Rolls-Royce Corporation | Cooled blisk with dual wall blades for gas turbine engine |
| US10415403B2 (en) | 2017-01-13 | 2019-09-17 | Rolls-Royce North American Technologies Inc. | Cooled blisk for gas turbine engine |
| US10934865B2 (en) | 2017-01-13 | 2021-03-02 | Rolls-Royce Corporation | Cooled single walled blisk for gas turbine engine |
| US10718218B2 (en) | 2018-03-05 | 2020-07-21 | Rolls-Royce North American Technologies Inc. | Turbine blisk with airfoil and rim cooling |
Also Published As
| Publication number | Publication date |
|---|---|
| DE102009052305A1 (en) | 2011-05-12 |
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