EP2789800A1 - Lock plates assortment, corresponding gas turbine and method of assembly - Google Patents

Abstract

The present invention relates to a safety plate assortment with a plurality of different locking plates, wherein the locking plates have different geometric coding. A gas turbine with such a bellows assortment and an associated method for mounting a blade assembly in a gas turbine are also presented.

Description

The present invention relates to a safety plate assortment for a blade assembly of a gas turbine with a plurality of different locking plates, a gas turbine with such a safety plate assortment and a method for assembling such a blade assembly.

Known gas turbines often have different turbine stages, in each of which rotor blades are fixed by means of locking plates on a turbine disk. A corresponding device for blade safety is among others in the EP 0 610 668 A1 shown.

In gas turbines with multiple turbine stages, it may happen that due to the different axial widths of individual turbine stages and / or due to the different design of the blades safety plates are installed, which differ slightly in their functionally related dimensions. Such a trained range of only slightly different safety plates, which are difficult to distinguish with the naked eye, can lead to an increased susceptibility to error during assembly.

An object of an embodiment of the present invention is to improve the assembly of blade assemblies with safety plates.

This object is solved by the features of claim 1. Claim 10 is directed to a gas turbine with such a safety plate assortment, claim 11 to a method for assembling blade assemblies. Advantageous embodiments of the invention are the subject of the dependent claims.

According to one aspect of the invention, a securing plate assortment has a plurality of different securing plates, with different securing plates having different geometric codings.

This can advantageously be achieved in one embodiment, that during mounting of the gas turbine different locking plates with a lower error rate or error-free the associated blade assembly can be assigned. As a result, in particular an advantageous increase in safety can be achieved.

According to a preferred embodiment of the invention, the geometric codes differ in number and / or shape and / or size of, in particular based on the mounting state axial and / or radial, recesses and / or elevations.

As a result, in one embodiment advantageously a haptic and / or low-wear differentiation of the different locking plates is made possible. In addition, in one embodiment advantageously an optical differentiation of the different locking plates can be made possible. Additionally or alternatively, an assembly process can be at least partially automated by such a geometric coding.

An encoding may have one, two or more recesses and / or elevations. The recesses may differ in their shape; In particular, different codes may alternatively have round holes, grooves, indentations and / or similar recesses. The surveys may differ in their form; it can be provided webs, pins and / or similar surveys. Additionally or alternatively, elevations and / or recesses may have maximum dimensions, for example diameters, which differ by at least 5 mm, in particular at least 10 mm. Additionally or alternatively, elevations and / or recesses of different locking plates may be arranged at different points of the locking plates, for example (relative to the mounting position) offset in the circumferential direction.

According to a preferred development, the locking plates have a functional area for supporting or securing the blade arrangement and a coding area on, wherein the geometric coding of the locking plates is arranged in the coding area.

As a result, it can advantageously be ensured in one embodiment that the coding of the securing plates does not or only slightly influences the function of the securing plate and / or the function of the turbine component to be secured.

In the present case, a functional area is to be understood in particular to mean a region of the securing plate which, in particular by means of positive and / or frictional contact with the blade arrangement to be secured, limits, in particular prevents, undesired, in particular axial, movement of the blade arrangement.

In the present case, a coding region is to be understood as meaning, in particular, a region of the securing plate in which different recesses and / or elevations are arranged, which in their combination represent the geometric coding of the securing plate.

In the context of the invention, it is also possible that the geometric coding of the securing plate is formed by the combination of recesses and / or elevations of at least two coding region.

According to a preferred embodiment, the locking plates on a first flange, a second flange and a connecting web. In this case, at least one of the flanges and / or the connecting web on a functional area, which is designed differently than a functional area of the other locking plates.

It can be provided in particular that the connecting webs of different locking plates have different longitudinal extents and / or widths.

In the sense of this development, the longitudinal extension of a securing plate is in particular that which is axial in relation to the gas turbine State to understand. In one embodiment, the longitudinal extent of various locking plates of the securing plate assortment differ by at most 10 mm, in particular by at most 1 mm, which is difficult to distinguish with the naked eye in the mounting situation.

According to a preferred embodiment, the first flange and / or the second flange of the locking plates, in particular in each case, at least one coding region. This can be arranged in an embodiment on a surface of the flange facing the blade arrangement, on a surface of the flange facing away from the blade arrangement and / or an edge of the flange connecting these two surfaces.

As a result, in one embodiment, advantageously, a geometric coding in a near-end, even in the assembled state accessible or visible area of the locking plate can be arranged, which in particular a better haptic distinction of different or differently coded locking plates can be done.

According to a preferred development additionally or alternatively, the connecting web of the locking plates on a coding area. As a result, in particular advantageously an improved optical differentiation of the different locking plates before or during assembly is made possible and a larger space can be used for coding.

According to a preferred embodiment, different locking plates have mutually correspondingly arranged coding regions whose coding differs in number and / or shape and / or size of recesses.

As a result, it can advantageously be achieved in one embodiment that a simpler differentiation of different locking plates can take place during assembly, since the installer always checks the same coding region. Also, a simpler automated checking assembled locking plates can be achieved in one embodiment advantageously.

According to a preferred development, the coding region is different from the functional region, in particular disposed of.

This can advantageously be achieved in one embodiment, that the coding of the locking plates can still be checked in the assembled state.

According to a further aspect of the invention, a gas turbine has at least two, in particular a plurality of, turbine stages, wherein different locking plates are arranged at the different turbine stages, which are designed so as to be distinguishable by means of their coding region.

As a result, it can be advantageously achieved, in particular, that the appropriate securing plates can be arranged simply and / or with little risk of error during assembly of each turbine stage.

• unterschiedlichen Schaufelanordnungen wird jeweils ein Sicherungsblech aus einem Sicherungsblechsortiment mit unterschiedlichen Sicherungsblechen unterschiedlicher geometrischer Kodierung zugeordnet,
• diese Schaufelanordnungen werden mit der Turbine verbunden, und
• Sicherungsbleche werden anhand ihrer geometrischen Kodierung ausgewählt und mit der zugeordneten Schaufelanordnung verbunden.

According to a further aspect of the invention, a method for assembling blade arrangements of a gas turbine comprises the following steps:

• different blade arrangements are each assigned a locking plate from a safety plate assortment with different locking plates of different geometric coding,
• these blade assemblies are connected to the turbine, and
• Locking plates are selected on the basis of their geometric coding and connected to the associated blade arrangement.

As a result, it can be advantageously achieved, in particular, that during the installation of the gas turbine different locking plates can be associated with a lower error rate or error-free the associated blade arrangements. As a result, in particular an advantageous reduction of the error rate during assembly can be achieved.

• unterschiedlichen Montagestellen werden an der Turbine Sicherungsbleche mit unterschiedlicher geometrischer Kodierung zugeordnet, und
• Sicherungsbleche werden anhand ihrer geometrischen Kodierung ausgewählt und mit der zugeordneten Montagestelle an der Turbine verbunden.

According to a preferred embodiment of the method, the following steps are provided:

• different mounting locations are assigned to the turbine locking plates with different geometric coding, and
• Locking plates are selected based on their geometric coding and connected to the associated mounting point on the turbine.

As a result, in particular an advantageous reduction of the error rate during assembly can be achieved.

According to a preferred embodiment of the method is checked before a geometrical definition of blade assembly and locking plate to each other, whether one of these blade assemblies associated locking plate was mounted.

In one embodiment, first locking plate first and blade assemblies are mounted on a turbine stage, the blade assemblies and the locking plate are not yet fixed to each other. This determination can be made in particular by deforming, in particular bending a flange, the locking plate.

As long as the determination has not yet been made, it is checked whether one of the built-in blade assemblies associated safety plate was mounted.

As a result, in particular advantageously the error rate during assembly can be further reduced.

According to a preferred embodiment of the method, in which the gas turbine has at least two, in particular a plurality, of turbine stages, each turbine stage is assigned a securing plate of the securing plate assortment.

As a result, it can be advantageously achieved, in particular, that during mounting, each turbine stage can be arranged in a simple and / or less error-prone manner the appropriate securing plates.

Fig. 1

ein nach einer Ausführung der vorliegenden Erfindung ausgebildetes Sicherungsblechsortiment mit drei unterschiedlichen Sicherungsblechen.

Further advantageous developments of the present invention will become apparent from the dependent claims and the following description of preferred embodiments. This shows, partially schematized:

Fig. 1

a trained according to an embodiment of the present invention safety plate assortment with three different locking plates.

Fig. 1 shows a trained according to an embodiment of the present invention safety plate assortment 1 a number of different locking plates 10, 20 and 30th

The locking plates 10, 20, 30 each have a first flange 11, 21, 31 and a second flange 12, 22, 32. In each locking plate 10, 20, 30, the first flange 11, 21, 31 is connected to the second flange 12, 22, 32 by means of a connecting web 13, 23, 33.

This connecting webs 13, 23, 33 differ slightly in their longitudinal extent L ₁₃ , L ₂₃ , L ₃₃ , whereby the locking plates 10, 20, 30 have a different longitudinal extent.

The difference in the longitudinal extent L ₁₃ , L ₂₃ , L _{33 of} the connecting webs 13, 23, 33 is due to the function, ie by the corresponding axial extension of the to be secured by the locking plates (not shown here) blade assembly.

In the region of the longitudinal extension L ₁₃ , L ₂₃ , L _{33 of} the connecting webs 13, 23, 33 can be blade feet with the respective locking plate 10, 20, 30 are in contact; Therefore, there is in each case a functional area 14.1, 24.1, 34.1 of the locking plates 10, 20, 30 are arranged.

Also on the first flanges 11, 21, 31 are arranged here for axial securing functional areas 14.2, 24.2, 34.2, which are in contact with the blade feet.

On the first flange 11 of the securing plate 10, a coding region 15 is additionally arranged in the functional region 14.2, in which a geometric coding of the securing plate 10 is formed by means of two recesses 16 and 17 formed as round holes. In the corresponding area 24.2, 34.2 of the locking plates 20, 30, no recesses are provided, so that the locking plate 10, despite its only slight difference in length haptically and wear-resistant from the locking plates 20, 30 to differentiate and assign the respective turbine stage or blade assembly.

On the first flange 21 of the locking plate 20 and the first flange 31 of the locking plate 30, adjacent to the functional areas 24.2 and 34.2, a coding region 25 or 35 is formed, which is spaced from the functional areas 24.2 and 34.2, so as not to function in particular, not to weaken the surface.

The coding regions 25 and 35 are arranged at mutually corresponding positions of the respective securing plate 20 and 30, respectively. For the purposes of this embodiment may also be provided that, unlike in FIG. 1 shown, the coding areas of all locking plates are arranged at mutually corresponding positions of the respective locking plate, for example, in the areas 14.2, 24.2 and 34.2 axial recesses in a different number, shape and / or arrangement are formed and / or on the edges (left in Fig. 1 ) Radial elevations and / or recesses in a different number, shape and / or arrangement are formed.

The coding region 25 of the securing plate 20 has a, here in part substantially part-circular, radial (relative to the mounting state) elevation 26. The coding region 35 of the securing plate 30 has a, here part-circular, radial recess.

Due to the different positioning, number, shape and / or size of the recesses and elevations in the respective coding region 15, 25, 35, compared With the other coding areas, each locking plate 10, 20, 30 has a different geometric coding.

A geometric encoding, as in FIG. 1 is shown in particular allows wear-free a haptic distinction of the three locking plates 10, 20 and 30, which is difficult for an assembly worker due to the only slightly different longitudinal extent L ₁₃ , L ₂₃ , L _{33 of} the connecting webs 13, 23, 33 without this geometric coding would prove.

Although exemplary embodiments have been explained in the foregoing description, it should be understood that a variety of modifications are possible. It should also be noted that the exemplary embodiments are merely examples that are not intended to limit the scope, applications and construction in any way. Rather, the expert is given by the preceding description, a guide for the implementation of at least one exemplary embodiment, with various changes, in particular with regard to the function and arrangement of the components described, can be made without departing from the scope, as it turns out according to the claims and these equivalent combinations of features. LIST OF REFERENCE NUMBERS 1 Locking plate range 10, 20, 30 Locking plate 11, 21, 31 first flange 12, 22, 32 second flange 13, 23, 33 connecting web 14, 24, 34 functional area 15, 25, 35 coding region 16, 17, 36 recess 26 survey L ₁₃ , L ₂₃ , L ₃₃ longitudinal extension

Claims (14)

Locking plate assortment (1) for a blade arrangement of a gas turbine, with a plurality of different locking plates (10, 20, 30), wherein different locking plates have different geometric coding. Locking plate assortment according to claim 1, wherein the geometric coding in number and / or shape and / or size of recesses (16, 17, 36) and / or elevations (26) differ. Locking plate assortment according to one of the preceding claims, wherein the locking plates have a functional region (14, 24, 34) for supporting or securing the blade arrangement, and a coding region (15, 25, 35), and wherein the geometric coding of the locking plates in the coding region arranged is. A locking plate assortment according to one of the preceding claims, wherein the locking plates have a first flange (11, 21, 31), a second flange (12, 22, 32) and a connecting web (13, 23, 33), and wherein at least one of the flanges and / or the connecting web of a locking plate has a functional area which is designed differently than the corresponding functional area of another securing plate. Locking plate assortment according to the preceding claim, wherein the connecting webs (13, 23, 33) of different locking plates (10, 20, 30) have different longitudinal extents (L ₁₃ , L ₂₃ , L ₃₃ ) and / or widths. Safety washer assortment according to one of the preceding claims, wherein the first flange (11, 21, 31) and / or the second flange (12, 22, 32) of the locking plates (10, 20, 30) has a coding region (15, 25, 35) , Locking plate assortment according to one of the preceding claims, wherein the connecting web (13, 23, 33) of the locking plates has a coding region. Locking plate assortment according to the preceding claim, wherein different locking plates have mutually correspondingly arranged coding regions whose coding differs in number and / or shape and / or size of recesses and / or elevations. Locking plate assortment according to one of the preceding claims, wherein the coding region of the functional area different, in particular thereof objected to, or is arranged in this. Gas turbine with a safety plate assortment according to one of the preceding claims with at least two turbine stages on which different locking plates (10, 20, 30) are arranged, which have different geometric coding. Method for mounting a blade arrangement of a gas turbine, wherein a locking plate (10, 20, 30) is selected from a safety plate assortment according to one of the preceding claims on the basis of its geometric coding and connected to the blade assembly. A method according to the preceding claim, wherein - Assigned to different mounting sites on the turbine locking plates (10, 20, 30) with different geometric coding, and - Locking plates (10, 20, 30) selected on the basis of their geometric coding and connected to the associated mounting point on the turbine. Method according to one of the preceding claims, wherein is checked prior to a determination of blade assembly and locking plate (10, 20, 30) to each other, whether a said blade assembly associated locking plate (10, 20, 30) has been mounted. Method according to one of the preceding claims, wherein the gas turbine has at least two turbine stages to which different locking plates (10, 20, 30) are assigned.

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