Securing blade assortment

Abstract

A securing plate assortment including multiple different securing plates, the securing plates having different geometric codings. A turbine and method is also disclosed.

Claims

1. A securing plate assortment for a blade assembly of a gas turbine, comprising: a plurality of different securing plates, wherein the different securing plates have a first flange, a second flange, and a connecting web, and wherein the different securing plates have respective different geometric codings situated in respective coding areas; wherein, in each of the different securing plates, the first flange or the second flange has the respective coding area; and wherein each respective coding area is situated on a first surface of the first or second flange facing away from the blade assembly and/or on an edge joining the first surface with a surface facing the blade assembly; and wherein the different geometric codings include codings on or through the first surface, or codings on the edge.

2. The securing plate assortment as recited in claim 1 wherein the geometric codings differ in terms of number or shape or size of recesses or elevations.

3. The securing plate assortment as recited in claim 1 wherein different securing plates have the respective coding areas situated so as to correspond to each other, whose codings differ in terms of the number or shape or size of recesses or elevations.

4. A gas turbine comprising a securing plate assortment as recited in claim 1 and at least two turbine stages on which different securing plates are situated, each having different geometric codings.

5. The securing plate assortment as recited in claim 1 wherein each of the different securing plates include a functional area for supporting or securing the blade assembly and the respective coding area.

6. The securing plate assortment as recited in claim 5 wherein the respective coding area is situated differently from the functional area.

7. The securing plate assortment as recited in claim 6 wherein the respective coding area is spaced apart from the functional area.

8. The securing plate assortment as recited in claim 1 wherein at least one of the flanges or the connecting web of a first securing plate of the plurality of different securing plates having a functional area designed differently than the corresponding functional area of a second securing plate of the plurality of different securing plates.

9. The securing plate assortment as recited in claim 8 wherein the connecting webs of different securing plates have different longitudinal extensions or widths.

10. The securing plate assortment as recited in claim 8 wherein the connecting web of the first securing plates has a further coding area.

11. A method for assembling a blade assembly of a gas turbine, comprising selecting one of the securing plates from the securing plate assortment as recited in claim 1 based on the geometric coding and joining the selected securing plate to the blade assembly.

12. The method as recited in claim 11 further comprising assigning securing plates having different geometric coding to different mounting sites on the turbine; and joining the selected securing plate to the assigned mounting site on the turbine.

13. The method as recited in claim 11 wherein, prior to joining the blade assembly and securing plate with respect to each other, checking whether a securing plate assigned to the blade assembly was mounted.

14. The method as recited in claim 11 wherein the gas turbine includes at least two turbine stages assigned different securing plates.

Description

BRIEF DESCRIPTION OF THE DRAWING

(1) Further advantageous refinements of the present invention are derived from the subclaims and the following description of preferred embodiments, showing a partially schematic illustration.

(2) FIG. 1 shows a securing plate assortment designed according to one embodiment of the present invention, including three different securing plates; and

(3) FIG. 2 shows a schematic depiction of a turbine according to the present invention.

DETAILED DESCRIPTION

(4) FIG. 1 shows a securing plate assortment 1 designed according to one embodiment of the present invention including a plurality of different securing plates 10, 20 and 30.

(5) Securing plates 10, 20, 30 in each case have a first flange 11, 21, 31 and a second flange 12, 22, 32. On each securing plate 10, 20, 30, first flange 11, 21, 31 is joined to second flange 12, 22, 32 with the aid of a connecting web 13, 23, 33.

(6) These connecting webs 13, 23, 33 marginally differ in their longitudinal extension L.sub.13, L.sub.23, L.sub.33, whereby securing plates 10, 20, 30 also have different longitudinal extensions.

(7) The difference in longitudinal extension L.sub.13, L.sub.23, L.sub.33 of connecting webs 13, 23, 33 is function-related, i.e., due to the corresponding axial extension of the blade assembly to be secured by the securing plates.

(8) Moving blade roots may be in contact with the particular securing plate 10, 20, 30 in the area of longitudinal extension L.sub.13, L.sub.23, L.sub.33 of connecting webs 13, 23, 33; as a result, a functional area 14.1, 24.1, 34.1 of securing plates 10, 20, 30 is situated there in each case.

(9) Functional areas 14.2, 24.2, 34.2 are also situated on first flanges 11, 21, 31, here for axial securing, and are in contact with the moving blade roots.

(10) A coding area 15 is additionally provided on first flange 11 of securing plate 10 in functional area 14.2, a geometric coding of securing plate 10 being formed in this coding area with the aid of two recesses 16 and 17 designed as round holes. No recesses are provided in corresponding area 24.2, 34.2 of securing plates 20, 30, so that securing plate 10, despite its only minor difference in length, is distinguishable from securing plates 20, 30 haptically and in a wear-protected manner and assignable to the particular turbine stage or blade assembly.

(11) Adjoining functional areas 24.2 or 34.2, a coding area 25 or 35 is formed on first flange 21 of securing plate 20 and on first flange 31 of securing plate 30, the coding area being spaced apart from functional areas 24.2 or 34.2 in order to not impair their function, in particular to not weaken the surface.

(12) Coding areas 25 and 35 are situated in mutually corresponding positions of securing plate 20 and 30 in each case. Within the sense of this exemplary embodiment, it may also be provided, contrary to what is shown in FIG. 1, that the coding areas of all securing plates are situated in mutually corresponding positions of the particular securing plate, for example, that axial recesses differing in terms of number, shape and/or positioning are formed in areas 14.2, 24.2 and 34.2 and/or that radial elevations and/or recesses differing in number, shape and/or positioning are formed on the edges (left in FIG. 1).

(13) Coding area 25 of securing plate 20 has a radial elevation 26 (with regard to the assembled condition), which here essentially has the shape of a partial circle. Coding area 35 of securing plate 30 has a radial recess, which here has the shape of a partial circle.

(14) Due to the different positioning, number, shape and/or size of the recesses and elevations in coding area 15, 25, 35 in each case compared to the other coding areas, each securing plate 10, 20, 30 has a different geometric coding.

(15) A geometric coding, as it is shown in FIG. 1, in particular allows a haptic distinction between three securing plates 10, 20 and 30 without wear, which would prove difficult to do for an assembler without this geometric coding due to the only marginally different longitudinal extension L.sub.13, L.sub.23, L.sub.33 of the connecting webs 13, 23, 33.

(16) FIG. 2 shows schematically a gas turbine 2 with a first turbine stage 100 with securing plates 30 and a second turbine stage 102 with securing plates 20 having different geometric codings than securing plates 30. The securing plates 20 and 30 are shown schematically mounted to blade assemblies 105 and to mounting sites 103.

(17) While the description above explained exemplary embodiments, it shall be pointed out that a plurality of modifications is possible. Moreover, it shall be pointed out that the exemplary embodiments are only examples which are not intended to limit the scope of protection, the applications and the design. Rather, the description above gives those skilled in the art a guideline for implementing at least one exemplary embodiment, various modifications being possible, in particular with respect to the function and positioning of the described components, without departing from the scope of protection as it is derived from the claims and feature combinations equivalent to the claims.

LIST OF REFERENCE NUMERALS

(18) 1 securing plate assortment 10, 20, 30 securing 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 area 16, 17, 36 recess 26 elevation 100 turbine stage 102 turbine stage L.sub.13, L.sub.23, L.sub.33 longitudinal extension