EP1143108A1 - Method for manufacturing a bladed stator segment and bladed stator segment - Google Patents

Abstract

A method of fabricating a guide vane assembly (16,20) for a turbine, during which for forming a guide vane crown (16), recesses (4), especially openings or cutouts, one for each guide vane (6), are made in a first ring. A guide vane (6) is then inserted into each opening or cutout (4) and the respective guide vane (6) is fixed with its first end (14) in the respective opening or cutout (4) and with its second end (12) to a second ring (10). The openings or cutouts (4) are formed with a profile matched to the guide vane profile and the positions of the individual guide vanes (6) are established together.

Description

The invention relates to a method for producing a Guide vane component and a guide vane component for one Turbine, especially for a high pressure or medium pressure stage a turbine.

In the field of technical energy generation, thermal Turbomachinery used, for example gas and steam turbines. In these the thermal working ability of the appropriate working medium (gas, steam) in mechanical work implemented. The blading has an effect Wing-like profiles that are in annular guide and Blade grilles are arranged as a transmission element. A guide vane and rotor vane grate each form a work stage. Since the ability to implement a stage is limited, in As a rule, turbines have several stages, depending on the thermal gradient of the working medium.

For the highest possible efficiency, an exact and Precise flow control of the drive medium is essential. This requires a precise geometric design of the individual Blades and vanes and their precise Location arrangement necessary.

The guide vanes of a turbine are arranged in a ring and form a vane ring. Usually this is formed from individual guide vane parts, in which the actual Airfoil usually made of profile material, in the blade root area by means of spacers and Bucket head area is fixed using a shroud. The spacers have the particular task of doing the necessary Distance between the guide vanes and the rotational position to ensure the guide vanes. The twist position is set using the so-called opening angle and is essential for the flow control. The mutual The distance between the individual blades is also called Called division.

Because of the large number of individual blade parts, for example the intermediate pieces, is the manufacture and the Assembly of a guide vane ring is very time and cost intensive.

The invention has for its object a method for Production of a guide vane component and a guide vane component specify where easy manufacture is possible is.

• in einem ersten Ring Ausnehmungen, insbesondere Durchbrüche, für jeweils eine Leitschaufel eingebracht werden,
• in die Ausnehmungen jeweils eine Leitschaufel eingeführt wird, und
• die jeweilige Leitschaufel mit ihrem ersten Ende in der jeweiligen Ausnehmung und mit ihrem zweiten Ende an einem zweiten Ring befestigt wird.

The object is achieved according to the invention by a method for producing a guide vane component for a turbine, in particular a guide vane component for a high-pressure or medium-pressure stage of a turbine, in which a guide vane ring is formed

• recesses, in particular openings, for each guide vane are made in a first ring,
• a guide vane is inserted into each of the recesses, and
• the respective guide vane is fastened with its first end in the respective recess and with its second end to a second ring.

The first ring is in particular an outer ring and the second ring an inner ring arranged concentrically to the outer ring. The main difference from the conventional one Process can be seen in the fact that the guide vane ring, in particular its outer ring, not from the multitude described above Guide vane parts, in particular intermediate pieces, is built up. Rather, the outer ring is in the making initially in one piece. This makes it much faster and also enables easier assembly. Due to the The individual guide vanes are simple and with recesses mountable with high accuracy.

In a preferred embodiment, in the first ring, the outer ring, recesses with a to the guide vane profile customized profiles incorporated so that the guide vanes held in the exact position in the outer ring. In order to lets are the position of each in an advantageous manner Set guide vanes to each other with high accuracy.

The recesses in the outer ring are preferably profiled in such a way that that is, with one adapted to the guide vane profile Profile formed that the rotational position of the guide vane is fixed with respect to the axial axis of the outer ring. By the profiled configuration of the recesses is therefore particularly both the pitch and the so-called opening angle determined with high accuracy and precision. There are no separate spacers required, as in the conventional manufacturing process are necessary. Thereby becomes the variety of parts for the manufacturing process significantly reduced, and in particular the manufacturing costs kept low by a short assembly time.

Not least because of the advantage of high positioning accuracy combined with the small number of parts is suitable this manufacturing method in particular for manufacturing a Guide vane component for a high pressure or medium pressure stage a turbine. These usually point in comparison very small guide vanes at a low pressure level on.

To make the recesses highly precise these are preferably by means of laser cutting or introduced by means of water jet processes.

For a secure and fast attachment the guide vanes in the recesses in particular by means of laser welding or electron beam welding welded.

Depending on the performance of the cutting or welding tool, for example the laser for cutting the recesses or the laser for welding is the material thickness to choose differently of the outer ring. To the use of Enabling lasers of conventional power is in a preferred embodiment on the outer ring around it Support ring attached. This is particularly true after completion of the guide vane ring attached to the outer ring and gives the guide vane ring a sufficiently high mechanical Strength.

With sufficient performance of the cutting or welding tool can the recesses in the form of openings also by an outer ring with sufficient material thickness introduced and the guide vanes are welded therein. Electron beam methods are particularly suitable for this.

After completion of the guide vane ring, this is in a preferred embodiment in individual guide vane segments divided. This means that when using the guide vane ring in a turbine between the individual vane segments thermal expansion allowed. The number of vane segments, into which the guide vane ring is divided depends decisive from the expected thermal stress and thermal expansion from.

Another advantage in the manufacture of the guide vane component arises if according to a particularly preferred variant the guide vane component, i.e. the guide vane ring or the vane segment, automatically and in particular is manufactured fully automatically. The fully automatic production is made possible by the simple manufacturing process, where the individual guide vanes with the two rings are welded, being in recesses of the outer ring be introduced.

The object is further achieved by the invention a guide vane component for a turbine, in particular for a high pressure or medium pressure stage of a turbine in which a vane between a first ring segment and a Another ring segment is arranged and in particular formed as an opening of the first ring segment with its first end and on the second ring segment is attached to its second end. The first ring segment is preferably an outer ring segment, and the second Ring segment an inner ring segment.

The advantages and advantages mentioned with regard to the method Refinements are analogous to the guide vane component transferred to. Preferred embodiments of the Guide vane component are laid down in the subclaims.

Fig. 1

eine Turbine mit einem Hochdruckteil und mit einem Niederdruckteil, und

Fig. 2

die einzelnen Verfahrensschritte zur Herstellung eines Leitschaufelbauteils.

The individual method steps for producing a guide vane component are explained in more detail using an exemplary embodiment of the invention. They show in highly schematic representations:

Fig. 1

a turbine with a high pressure part and with a low pressure part, and

Fig. 2

the individual process steps for the manufacture of a guide vane component.

According to FIG. 1, a turbine 1, in particular one Power plant turbine for a power plant for the generation of energy is designed for an output of up to more than one gigawatt, a high pressure part 1A and a low pressure part 1B. This is in the direction of flow of a drive medium which Flows through turbine 1, downstream of the high pressure part 1A. For Illustration are the high pressure and low pressure parts 1A, 1B shown as separate units, which are connected via a shaft 3 are interconnected. They are usually in one common turbine housing integrated.

The drive medium, namely steam in the case of a steam turbine and gas in the case of a gas turbine, the pipe 5 High pressure and low pressure part 1A, 1B supplied and discharged. The Drive medium drives the shaft 3 by means of it Blades on. The drive medium is through the turbine 1 passed over fixed guide vanes. The blades and guide vanes of the high pressure and low pressure part 1A, 1B are not shown in FIG. 1. The Guide blades and the blades of a turbine stage are usually arranged side by side in the circumferential direction and each form a blade ring. This changes in the axial direction 8 of the turbine 1 guide vane rings and moving vane rings from.

For the most efficient flow guidance through the turbine 1 is the formation of the blades as well as their mutual Arrangement crucial. In the preparation of must therefore have a high dimensional accuracy and positioning accuracy be respected.

A production method is described with reference to FIG. 2, that ensures high dimensional accuracy and positioning accuracy. In a process step A of the manufacturing process becomes a first ring, namely an outer ring 2 manufactured. For example, a flat steel becomes one Ring curved. This ring will then be more appropriate Machined to form the outer ring 2. In particular the two ends of the flat steel become together The ring is welded and the ring is annealed. The surfaces of the ring are treated as needed, for example Grooves screwed in.

According to a method step B, the outer ring 2 several recesses 4 mainly in the form of openings incorporated. The recesses 4 are circumferential around the entire Outer ring 2 introduced. Are in the embodiment only four recesses 4 are shown.

The recesses 4 designed as openings serve for Pickup and for precise positioning of the guide vanes 6. For this purpose, the recesses 4 have a guide vane 6 customized profile. The recesses 4 are in particular by means of laser welding or water jet processes incorporated into the outer ring 2 precisely and in accordance with the profile.

In a method step C, the guide vanes 6 are successively inserted into the recesses 4 assigned to them and arranged between the outer ring 2 and an inner ring 10. The guide vanes 6 are preferably from the outside pushed through the recesses 4 in the direction of the inner ring 10. Because of the profiled design of the recesses 4, the individual guide blades 6 in the recesses 4 positioned in a fixed position and secure against rotation. So that is both Distance, the so-called division, of adjacent guide vanes 6 fixed to each other as well as their so-called opening angle in relation to the axial axis 8 of the outer ring 2. The opening angle gives the position or rotational position of the cross-sectional profile of the guide vanes 6 with respect to the axial axis 8.

In a subsequent process step, which in the figure the guide vanes are not shown separately their first ends, namely their outer ends 14, in the recesses 4 attached and with their second ends, namely their inner ends 12, on the inner ring 10. They are preferred by means of laser welding or electron beam welding welded.

At the end of this process step is a vane ring 16 formed of an outer ring 2, an inner ring 10 and guide vanes evenly spaced apart therebetween 6 has. The guide vanes 6 extend around the entire, between the inner ring 10 and the outer ring 2 formed ring surface.

In a method step D, the outer ring is applied directly 2 a support ring 18 is applied, which around the outer ring 2 preferably runs around completely as a closed ring.

This support ring 18 serves to increase the mechanical strength of the vane ring 16. When using a suitable strong cutting and welding tool for incorporation of the recesses 4 and for welding the guide vanes 6 in and on the rings 2, 10 can also be on this support ring 18 to be dispensed with. In this case the outer ring 2 is clear stronger than in the variant with support ring 18.

In a last step E, the guide vane ring 16 divided into several guide vane segments 20, wherein only one guide vane segment 20 is shown in FIG. 2, which has four guide vanes 6. The division of the Guide vane ring 16 takes place in guide vane segments 20 through suitable separation processes. The guide vane segments 20 each have a first ring segment, namely an outer ring segment 24, and a second ring segment, namely a Inner ring segment 22, with the individual guide blades 6 from the inner ring segment 22 to the recesses 4 of the outer ring segment 24 are enough.

In FIG. 2, the method step E is shown the support ring 18 omitted for clarity. The division of the guide vane ring 16 into several guide vane segments 20 is preferably done after attachment the support ring 18.

The size of the individual guide vane segments 20 depends after their thermal stress during the operation of the turbine. It is essential that due to the thermal Load between the individual guide vane segments 20 sufficient expansion gaps are provided.

The individual process steps, in particular the process steps B and C and then attaching the Guide vanes 6 are preferably automatic, in particular fully automatic. The manufacturing process described it is very well suited for automatic production. With automatic production, a significantly higher one Accuracy and productivity achieved when doing this manually conventional type is possible. This will change the flow conditions in the turbine compared to the conventional manufacturing process improved. Because of compared to the guide vanes of a low-pressure part comparatively small guide vanes of a high pressure or medium pressure part points out the new procedure especially for one High-pressure or medium-pressure stage assembly advantages on.

Claims (11)

Method for producing a guide vane component (16, 20) for a turbine, in particular a guide vane component (16, 20) for a high-pressure or medium-pressure stage of a turbine, in which a guide vane ring (16) recesses (4), in particular openings, for each guide vane (6) are made in a first ring (2), a guide vane (6) is inserted into each of the recesses (4), and the respective guide vane (6) is fastened with its first end (14) in the respective recess (4) and with its second end (12) to a second ring (10). Method according to Claim 1, in which the recesses (4) formed with a profile adapted to the guide vane profile and the position of the individual guide vanes (6) fix each other. The method of claim 1 or 2, wherein the recesses (4) with a profile adapted to the guide vane profile are trained and the rotational position of the guide vanes (6) to the axial axis (8) of the ring (2). Method according to one of the preceding claims, in which the recesses (4) by means of laser cutting or by means of water jet processes be introduced. Method according to one of the preceding claims, in which the guide blades (6) in the recesses (4) in particular welded by means of laser welding or electron beam welding become. Method according to one of the preceding claims, in which after inserting the guide vanes (6) on the first ring (2) a support ring (18) is attached. Method according to one of the preceding claims, in which the guide vane ring (18) into individual guide vane segments (20) is shared. Method according to one of the preceding claims, in which the guide vane component (16, 20) is manufactured automatically. Guide vane component (16, 20) for a turbine, in particular for a high pressure or medium pressure stage of a turbine, at a guide vane (6) between a first ring segment (24) and a second ring segment (22) is arranged and in a recess designed in particular as an opening (4) of the first ring segment (24) with its first End (14) and on the second ring segment (22) with its second End (12) is attached. Guide vane component (16,20) according to claim 9, wherein the Guide blade (6) welded to the first ring segment (24) is. Guide vane component (16, 20) according to claim 9 or 10, a support ring segment (18) is arranged on the first ring segment (24) is.

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