Patent Application
20180266259
The invention relates to a rotor comprising at least one turbine blade and a securing device for axially and radially securing the turbine blade, wherein the rotor comprises a blade groove and the turbine blade comprises a turbine blade root, wherein the blade groove and the turbine blade root is adapted to the blade groove, wherein the securing device has a retaining piece which is arranged between the blade groove and the turbine blade root.
Blade fastening mechanisms are normally used for fastening rotor blades on a rotor of a continuous-flow machine, in particular a steam turbine. As a result of the relatively high rotation of the rotor, the rotor blades arranged on the rotor are subjected to large centrifugal forces. The turbine blade root of the turbine blades must therefore withstand large forces and is forced radially outward in the blade groove. In addition to the centrifugal forces, high vibrational loads present a further problem and can lead to mechanical damage and material fatigue. Corrosion and traveling movement of the blade root due to steam impingement or vibrations inside the blade groove present further problems. In order to fix the turbine blade root inside the blade groove, various solutions, such as for example metal wedges, spring rings or sealing pieces, are known. Although metal wedges establish locking of the associated blade root inside a blade groove both axially and radially, in the case of large rotor blades it is difficult to generate sufficient retaining forces in the radial direction with such metal wedges during rotation. Furthermore, metal wedges exhibit corrosive behavior during extensive operation in the steam medium, and this makes dismantling difficult.
Axially threaded rotor blades are known which, in turbomachines, such as for example steam turbines, on account of the operating stress, require a construction which absorbs the axial operating forces of the turbine blade and keeps the blade in its axial position. Such securing mechanisms are also referred to as axial securing mechanisms. In the case of such axial securing mechanisms, there are normally arranged two notches which are formed in a superposed manner with respect to one another. However, superpositions of notches frequently have increased stress and therefore signify limited use in turbomachine construction.
It is an object of the invention to provide a blade fastening mechanism in a continuous-flow machine in which a precise and firm retention of blades and the associated blade holders is ensured over a long period of operation.
This object is achieved by way of a rotor comprising at least one turbine blade and a securing device for axially and radially securing the turbine blade, wherein the rotor comprises a blade groove and the turbine blade comprises a turbine blade root, wherein the blade groove and the turbine blade root is adapted to the blade groove, wherein the securing device has a retaining piece which is arranged between the blade groove and the turbine blade root, wherein the retaining piece has a projection which is arranged into a recess in the turbine blade root, wherein the projection engages into the recess in such a way that displacement of the retaining piece in the axial direction is prevented, wherein the securing device has a force spring which exerts a force, acting in the radial direction from the rotor, on the turbine blade.
The invention therefore proposes arranging a securing device into a space between the rotor and the turbine blade root. Said space is advantageously arranged in the rotor. The notch formed by the space is thus displaced in a radially inward direction towards the axis of rotation. Consequently, the forces applied to the rotor are distributed better.
Advantageous refinements are given in the subclaims.
In one refinement, the retaining piece is integrated directly into the blade root. In this case, this is distinctly formed, in the radially inward direction, either at the front edge of the blade root or advantageously at the rear edge of the blade root, as seen in the axial direction. A distinct formation at the front edge and rear edge is possible here of an axial recess, which further allows the axial insertion of the modified blade.
In a first advantageous refinement, the securing device has a plate which is arranged in a second recess in the retaining piece and in a rotor recess, wherein the plate engages into the second recess and into the rotor recess in such a way that displacement of the plate in the axial direction is prevented.
Active displacement in the axial direction of the retaining piece is thus prevented in an effective manner. The plate is in this case arranged into a rotor recess and into a second recess in the retaining piece and therefore forms a barrier for the retaining piece to be displaceable in the axial direction.
In an advantageous refinement, a force spring is arranged between the blade groove and the retaining piece.
Said force spring exerts a force from the rotor on the turbine blade root. During transportation and during operation, it is important, especially in the case of low rotational speeds, to exert a force on the turbine blade root which acts in a radial direction. Consequently, displacement of the turbine blade in the axial direction as a result of friction effects is further avoided. Above a certain rotational speed, centrifugal forces acting in the radial direction on the turbine blade are so large that the influence of the spring force due to the force spring can be neglected.
Advantageously, the force spring is arranged next to the retaining piece, between the blade groove and the blade root.
This is a particularly simple and constructive solution which is producible by simple means.
In a further advantageous refinement, the blade root has an arranged front edge, as seen in the axial direction, and a rear edge arranged opposite the front edge, as seen in the axial direction, wherein the retaining piece extends from the front edge to the rear edge.
Here, the invention now advantageously proposes refining the retaining piece in such a way that the dimensions in the axial direction are such that the retaining piece extends from the front edge to the rear edge.
In a further advantageous refinement, a first securing plate is arranged at the front edge and a second securing plate is arranged at the rear edge.
This prevents, in an effective manner, axial displacement of the retaining piece, both in one axial direction and in the oppositely-facing axial direction.
In a further advantageous refinement, a first force spring is arranged at the front edge and a second force spring is arranged at the rear edge.
As a result, symmetrical distributions of forces and vibrations, which arise in particular during start-up or during transportation, can be further minimized.
In a further advantageous refinement, the projection is of elongate design in the circumferential direction (with respect to the axis of rotation).
An elongate design is normally a relatively simple production process, which here will lead to a cost saving.
The projection is advantageously of rectangular cross section.
In a further advantageous refinement, the projection is formed as a cylinder and engages into a recess formed as a blind bore. This presents an alternative to the elongate design form of the projection. A locally-engaging force acts on the blind bore advantageously proposed here in which the cylinder formed as the projection engages.
The rotor recess and the second recess are advantageously arranged one above the other in the radial direction.
As a result of the orientation with a one-above-the-other arrangement in the radial direction, tilting of the plate is prevented in an effective manner. The above-described properties, features and advantages of this invention and the manner in which they are achieved become clearer and more easily understandable in conjunction with the following description of the exemplary embodiments, which are explained in more detail in conjunction with the drawings.
Exemplary embodiments of the invention are described below with reference to the drawings. Said drawings are not intended to illustrate the exemplary embodiments in a representative manner, but rather the drawing, where expedient for elucidations, is shown in schematic and/or slightly distorted form. With respect to additions to the teaching directly identifiable in the drawing, reference is made to the relevant prior art.
In the drawings:
The axis of rotation 5 and the axial direction 7 are arranged parallel to one another. The rotor 2 rotates about the axis of rotation 5 at a rotational speed. The turbine blade is adapted in the blade groove 4 such that there is as little play as possible between the turbine blade root 3 and the blade groove 4. Without the securing device 8, it would be possible for the turbine blade to be displaced freely in the axial direction 7.
The rotor 2 and the turbine blade may be part of a turbomachine, for example a steam turbine. During the start-up of a continuous-flow machine, the centrifugal forces are still relatively small, and during transportation, there are no centrifugal forces present at all. Consequently, it is possible that the turbine blade is displaceable in the axial direction 7. This is prevented by way of a securing device 8. Above a certain rotational frequency, the centrifugal forces are so large that the turbine blade presses, in the blade groove 4, against so-called bearing flanks 9 and thereby acquires a stable position. Above this certain rotational frequency, axial displacement is difficult. With the securing device 8, displacement of the turbine blade in the axial direction 7 and in the radial direction is prevented in an effective manner. The securing device 8 comprises a retaining piece 10.
The retaining piece has, on the top side 13, a projection 15 which, according to a first variant of the invention, is of elongate design in a circumferential direction 16. The projection 15 is of rectangular cross section. The projection 15 is formed over the entire top side 13 and extends into a recess 17 in the turbine blade root 3. The recess 17 is in this case of complementary design with respect to the projection 15. This means that the recess 17 is also of elongate design and rectangular cross section.
If the projection is arranged in the recess 17, the retaining piece can no longer be displaced in the axial direction 7, and so displacement of the retaining piece 10 in the axial direction 7 is prevented.
As shown in
The difference of the securing device 8 according to the second variant with respect to the securing device 8 of the first variant is that the projection 15 is not of elongate design but is formed as a cylinder 24 and extends into a blind bore in the turbine blade root 3. In this case, the cylinder 24 has a similar mode of action to the projection 15 according to
The plate 19 is arranged in an encircling manner in the circumferential direction 16 and is in this case formed in a segmented manner. This means that the plate 19 is composed of individual segments. The plate 19 is arranged in a form-fitting manner in the rotor recess 20 and in the second recess. The plates 19 are inserted to a circumferential position via a milled opening of the encircling groove and pushed to their final position, and following insertion of the last segment, the segments are joined to one another at the divisions by spot welding. The force spring 18 serves for ensuring that the turbine blade bears against the rotor 2 in a standstill state, e.g. during transportation. The force spring 18 is designed for example as a disk spring. The force spring 18 can also be designed as a clamping piece, however.
Although the invention has been more specifically illustrated and described in detail by the preferred exemplary embodiment, the invention is not limited by the examples disclosed and other variations can be derived herefrom by a person skilled in the art, without departing from the protective scope of the invention.
| Number | Date | Country | Kind |
|---|---|---|---|
| 15151806.5 | Jan 2015 | EP | regional |
This application is the US National Stage of International Application No. PCT/EP2016/050066 filed Jan. 5, 2016, and claims the benefit thereof. The International Application claims the benefit of European Application No. EP15151806 filed Jan. 20, 2015. All of the applications are incorporated by reference herein in their entirety.
| Filing Document | Filing Date | Country | Kind |
|---|---|---|---|
| PCT/EP2016/050066 | 1/5/2016 | WO | 00 |
