WO2008077374A1

WO2008077374A1 - Method for the production of a blisk or a bling and component produced thereby

Info

Publication number: WO2008077374A1
Application number: PCT/DE2007/002245
Authority: WO
Inventors: Ulrich Knott; Albin Platz; Karl-Hermann Richter; Dieter Schneefeld
Original assignee: Mtu Aero Engines Gmbh
Priority date: 2006-12-23
Filing date: 2007-12-12
Publication date: 2008-07-03
Also published as: DE102006061448B4; DE102006061448A1

Abstract

The present invention relates to a method for the production of a blisk (“bladed disk”) or a bling (“bladed ring”) of a gas turbine or of a high pressure or low pressure compressor, wherein the method comprises the following steps: (a) production of an annular blade ring (12); and (b) connection of the annular blade ring (12) to a rotor disk (16) or a rotor ring in such a way that the blade ring (12) is arranged on the outer circumference (18) of the rotor disk (16) or the rotor ring. The invention relates further to a component of a gas turbine or of a high pressure or low pressure compressor, in particular a blisk (“bladed disk”) or a bling (“bladed ring”). According to the invention, the component (10) consists of a separately produced annular blade ring (12) and a rotor disk (16) connected thereto or a rotor ring connected thereto, wherein the blade ring (12) is arranged on the outer circumference (18) of the rotor disk (16) or the rotor ring.

Description

Method for producing a blisk or a bling and component produced therewith

description

The present invention relates to a method for producing a blisk ("bladed disk") or a bling ("bladed ring") of a gas turbine or a high or low pressure compressor. The invention further relates to a component produced by the method.

Bladed (Bladed Disk) and Bling (Bladed Ring) designate rotor designs where blades are made integral with a load bearing disk or bearing ring The advantage of these rotor designs is that the disks or ring shape are designed for low edge loads In general, compacting blisks made of titanium or nickel-based alloys are produced, in particular by milling, and occasionally by linear friction welding or electrochemical ablation On the other hand, in the turbine area, the disc and blade materials basically have to be different from each other, which means that turbine blisks can only be realized by means of joint technology, bearing in mind, however, that joining methods, such as linear friction welding, are necessary Compressive forces are not or are poorly suited to produce such turbine blisks. The same applies to bling. Due to the mentioned limitations, the known production methods can only be used to a limited extent if different structural designs of blisks or blings are required. In addition, the known methods are sometimes very complex and go hand in hand with a corresponding high cost. It is therefore an object of the present invention to provide a generic method for producing a blisk ("bladed disk") or a bling ("bladed ring"), which is used both in the production of a blisk or bling a gas turbine or a high or low pressure compressor can be and a variety of structural designs of these components allows.

It is a further object of the present invention to provide a generic component which is inexpensive to produce in a variety of different designs.

These objects are achieved by a method according to the features of claim 1 and a component according to the features of claim 11.

Advantageous embodiments of the invention are described in the respective subclaims.

A erfϊndungsgemäßes method for producing a blisk ("bladed disk") or a bling ("bladed ring") of a gas turbine or a high or low pressure compressor comprises the following steps: a) producing an annular blade ring and b) connecting the annular blade ring with a rotor disk or a rotor ring, such that the blade ring is arranged on the outer circumference of the rotor disk or the rotor ring. By initially producing the blade ring separately, it is advantageously possible to use a plurality of known methods for connecting the blade ring to the rotor disk or the rotor ring for producing the blisk or the bling. On the joining of individual blades on the corresponding rotor disk or the corresponding rotor ring - as is performed in known manufacturing processes for blisks or bling - can be omitted. In addition, the inventive method can be used both in the production of blisks or blings for a gas turbine o- but also for a high or low pressure compressor. The separate production of the blade ring and the subsequent connection of the blade ring with the rotor disk or the rotor ring also allows a variety of structural Ges- tions of these components. For example, cooling ducts that pass through both the blades and the disk in a turbine blisk to direct cooling air outwardly from the air system through the blades can be readily manufactured.

In an advantageous embodiment of the method according to the invention, the blade ring is produced by joining individual blades or blade segments produced by casting. It is possible that an annular element is equipped with the individual blades or individual blade segments are joined to form an annular blade ring. As a joining method, a high-temperature soldering or a diffusion soldering can be used. But it is also possible that the blade ring is made in one piece by means of a casting or milling process.

In a further advantageous embodiment of the method according to the invention, the connection of the annular blade ring with the rotor disk and the rotor ring takes place by means of a joining process. In this case, the joining process can be carried out by means of an electron beam welding method, a rotary friction welding method, a diffusion soldering method or a diffusion welding method. Other suitable joining processes are conceivable. It has been found in the use of the electron beam welding process that the quality of the connection can be significantly improved if, for example, metallic intermediate layers are used on the surface to be joined. The metallic interlayers are used because the blade material is generally not melt weldable. But it is also possible that the electron beam is deflected offset in the direction of a melt-weldable disc material. When using the diffusion soldering process, a suitable solder is applied to one of the surfaces to be joined (for example with solder foil or a physical vapor deposition method) and then introduced locally in a vacuum furnace or with a locally, for example, annular inductor, the required heat energy. When using a rotary friction welding process as a joining process for connecting the blade ring with the rotor disk or the rotor ring, the joining surface between turbine ring and disc can be made conical. In this case, the rotor disk or the rotor ring has an oversize in the axial direction and can subsequently ßend be finished. In particular, flywheel friction welding is used as the rotary friction welding method. Finally, when using the diffusion welding method, a corresponding joining device is to be selected which ensures that the joining components are pressed together at the corresponding diffusion welding temperature, so that an intimate connection is created between the blade ring and the rotor disk or the rotor ring.

In a further advantageous embodiment of the method according to the invention, the positioning of the blade ring on the rotor disk and the rotor ring by means of shrinking takes place. To ensure this, the blade ring, the rotor disk and the rotor ring have the necessary radii. The shrinkage ensures an intimate connection between the individual elements of the blisk or the bling.

In a further advantageous embodiment of the method according to the invention recesses are formed in the rotor disk and the rotor ring after connecting the annular blade ring with the rotor disk or the rotor ring, wherein the recesses between each two adjacent individual blades or blade segments of the blade ring on the outer circumference of the rotor disk or the rotor ring encircling are arranged. Such a configuration advantageously forms a shroud for shielding the rotor disk or the rotor ring. In this case, the shroud consists of the ring element or annular region of the blade ring. But it is also possible that after connecting the annular blade ring with the rotor disk or the rotor ring those portions of the blade ring, which lie between the individual blades are removed, such that only one foot section of the corresponding blade with the rotor disk and the Rotor ring is connected. This process step can be carried out with or without the formation of the abovementioned recesses in the rotor disk or the rotor ring. It can be seen that the method according to the invention provides a multitude of design options. The formation of said recesses or the removal of the intermediate regions of the blade ring is effected for example by means of an electrochemical mix removal method and / or by spark erosion. But other methods such as drilling or milling methods can be used.

An inventive component of a gas turbine or a high or low pressure compressor, in particular a blisk ("bladed disk") or a bling ("bladed ring") consists of a separately manufactured annular blade ring and a rotor disk or rotor ring connected thereto, wherein the Blade ring is arranged in the outer circumference of the rotor disk or the rotor ring. Due to the two-part design of the component according to the invention whose cost-effective production of a variety of different designs is guaranteed. In this case, the blade ring may consist of a multiplicity of individual blades or blade segments joined to one another in segments.

In an advantageous embodiment of the component according to the invention, this has a shroud for shielding the rotor disk or the rotor ring. The shroud serves in particular for shielding the hot gas in the gas turbine. The shroud can be formed, for example, by an annular region of the blade ring, wherein after connecting the annular blade ring with the rotor disk or the rotor ring recesses in the rotor disk or the rotor ring are formed, wherein the recesses between each two adjacent individual blades of the blade ring on the outer circumference the rotor disk or rotor ring are arranged circumferentially. This advantageously results in a particularly cost-effective production of a blisk or bling with shroud.

In particular, the components according to the invention are produced by one of the methods described above.

Further advantages, features and details of the invention will become apparent from the following description of several illustrative exemplary embodiments. Show Figure 1 is a schematic representation of a blade ring as part of a component according to the invention;

Figure 2 is a schematic representation of an inventive joined component according to a first embodiment;

Figure 3 is a schematic representation of an inventive joined component according to a second embodiment;

Figure 4 is a schematic representation of an inventive joined component according to a third embodiment;

5 shows a schematic representation of a joining process for connecting an annular blade ring with a rotor disk for producing a component according to the invention according to a first embodiment; and

Figure 6 is a schematic representation of a joining process for connecting an annular blade ring with a rotor disk for producing a component according to the invention according to a second embodiment.

FIG. 1 shows a schematic representation of a blade ring 12 as part of a blisk or a bling. The blade ring 12 consists of a plurality of individual blades 14, which are arranged annularly on the outer circumference of an annular element 26 of the blade ring 12. The annular element 26 is formed in the illustrated embodiment by a plurality of curved blade base elements 28 which are joined together, wherein first joining seams or points 30 arise. The blades 14 are arranged centrally on the outer surface of the respective blade base element 28. In the extension of the respective blade 14, a root section 22 of the blade 14 is formed in the blade base 28. The illustrated blade ring 12 is thereby produced by a segment-wise joining of the individual blades 14 or the blade base elements 28. In particular, this is a Hochtemperaturlötverfahren or Diffusion soldering used. But it is also possible that corresponding blade rings are produced in one piece by means of a casting or milling process.

FIG. 2 shows a schematic representation of a joined component 10, namely a blisk for a gas turbine. It can be seen that the blade ring 12 is connected to a rotor disk 16 such that the blade ring 12 comes to rest on the outer periphery 18 of the rotor disk 16. The rotor disk 16 and the blade ring 12 are connected by means of a joining process. The joining process may be an electron beam welding process, a spin welding process, a diffusion soldering process or a diffusion welding process. By joining the rotor disk 16 with the blade ring 12, a circumferential second joint seam 32 is formed.

FIG. 3 shows a schematic representation of a further embodiment of the component 10. It can be seen that the component 10 is again designed as a blisk. In the exemplary embodiment illustrated here, the blisk has a cover band 24 for shielding the rotor disk 16. In this case, the shroud 24 is formed by the annular region 26 of the blade ring 12. For this purpose, 16 recesses 20 are formed in the rotor disk 16 after connecting the annular blade ring 12 with the rotor disk, wherein the recesses 20 are arranged circumferentially between each two adjacent individual blades 14 of the blade ring 12 on the outer periphery 18 of the rotor disk 16. The formation of the recesses 20 takes place by means of a precise electrochemical removal process and / or by spark erosion. Other erosive methods are conceivable.

4 shows a schematic representation of a component 10 according to a third embodiment. Also in this embodiment, the component 10 is a blisk. It can be seen that this blisk has no shroud 24 in comparison to the blisk shown in FIG. In the illustrated component 10 after joining the annular blade ring 12 with the rotor disk 16 those portions of the blade ring 12, which lie between the individual blades 14 and blade segments removed, such that only each of the foot portion 22 of the corresponding blade 14 with the rotor disc 16 is connected. Such a blisk has only the second joining seams 32. The removal of the intermediate regions of the blade ring 12 can also take place by means of an electrochemical removal process and / or by spark erosion.

5 shows a schematic representation of a joining process for connecting the annular blade ring 12 to the rotor disk 16 for producing a component 10, namely a blisk. The illustrated joining process is a friction welding process, in particular a flywheel friction welding process. It can be seen that the joining surface between the blade ring 12 and the rotor disk 16 is conical. The same applies to the resulting second weld 32. A disk axis 34 is also shown schematically in this figure.

Also in the joining process shown in Fig. 6 is a friction welding, namely a Schwungradreibschweißverfahren. It can be seen that in this case too, a conical weld 32, in particular a friction weld seam 32, is formed when the blade ring 12 is connected to the rotor disk 16.

Claims

claims

A method of manufacturing a bladed disk or a bladed ring of a gas turbine or a high or low pressure compressor, characterized in that the method comprises the steps of: a) producing an annular blade ring (12) ; and b) connecting the annular blade ring (12) to a rotor disk (16) or rotor ring such that the blade ring (12) is located on the outer periphery (18) of the rotor disk (16) or rotor ring.

2. The method according to claim 1, characterized in that the blade ring (12) by a segment-wise joining produced by casting individual blades (14) or blade segments is made.

3. The method according to claim 2, characterized in that the joining method is a high temperature brazing method or a diffusion brazing method.

4. The method according to claim 1, characterized in that the blade ring (12) is produced in one piece by means of a casting or milling process.

5. The method according to any one of the preceding claims, characterized in that the connection of the annular blade ring (12) takes place with the rotor disk (16) or the rotor ring by means of a joining process.

6. The method according to claim 5, characterized in that the joining process is an electron beam welding method, a rotary friction welding method, a diffusion soldering method or a diffusion welding method.

7. The method according to any one of the preceding claims, characterized in that a positioning of the blade ring (12) on the rotor disk (16) or the rotor ring is effected by means of shrinking.

8. The method according to any one of the preceding claims, characterized in that after connecting the annular blade ring (12) with the rotor disc (16) or the rotor ring recesses (20) in the rotor disc (16) or the rotor ring are formed, wherein the recesses (20) between each two adjacent individual blades (14) of the blade ring (12) on the outer circumference (18) of the rotor disc (16) or the rotor ring are arranged circumferentially.

9. The method according to any one of the preceding claims, characterized in that after connecting the annular blade ring (12) with the rotor disc (16) or the rotor ring those areas of the blade ring (12) which lie between the individual blades (14), be removed, such that only one respective foot section (22) of the corresponding blade (14) with the rotor disk (16) or the rotor ring is connected.

10. The method according to claim 8 or 9, characterized in that the formation of the recesses (20) or the removal of the intermediate regions of the blade ring (12) by means of an electrochemical removal process and / or by spark erosion.

11. A component of a gas turbine or a high or low pressure compressor, in particular a blisk ("bladed disk") or a bling ("bladed ring"), characterized in that the component (10) of a separately manufactured annular blade ring (12) and an associated rotor disk (16) or a rotor ring connected thereto, wherein the blade ring (12) on the outer circumference (18) of the rotor disk (16) or the rotor ring is arranged.

12. Component according to claim 11, characterized in that the blade ring (12) consists of a plurality of segmentally joined individual blades (14) or blade segments.

13. Component according to claim 11 or 12, characterized in that the component (10) comprises a shroud (24) for shielding the rotor disk (16) or the rotor ring.

14. Component according to claim 13, characterized in that the shroud (24) by an annular portion (26) of the blade ring (12) is formed and after the connection of the annular blade ring (12) with the rotor disc (16) or the rotor ring recesses (20) in the rotor disk (16) or the rotor ring are formed, wherein the recesses (20) between each two adjacent individual blades (14) of the blade ring (12) on the outer circumference (18) of the rotor disk (16) or the rotor ring are arranged circumferentially ,

15. Component according to one of claims 11 to 14 prepared by a method according to any one of claims 1 to 10.