Abstract:
A turbine blade, including: an airfoil and a platform, which has an upper face on which the airfoil is arranged; and at least one lateral face, the lateral face including a slot for insertion of a sealing strip. The transition between the upper face of the platform and the at least one lateral face includes a stepped portion and a beveled portion is provided.

Description:
CROSS-REFERENCE TO RELATED APPLICATIONS 
       [0001]    This application claims priority to PCT Application No. PCT/EP2014/061996, having a filing date of Jun. 10, 2014, based off of European Application No. 13173717.3 having a filing date of Jun. 26, 2013, the entire contents of which are hereby incorporated by reference. 
     
    
     FIELD OF TECHNOLOGY 
       [0002]    The following relates to a turbine blade or vane, for example a guide vane or a rotor blade of a gas turbine or of a steam turbine. Embodiments of the invention furthermore relate to a method for producing such a turbine blade or vane and a turbine. 
       BACKGROUND 
       [0003]    Turbine blades or vanes of gas turbines or steam turbines are typically exposed to severe mechanical, chemical and thermal loading. For this reason, the surfaces of the respective main blade or vane parts and the surfaces of the blade or vane platforms, which are likewise exposed to said loading, are provided with suitable coatings. A coating system of this type comprises, for example, what is termed a bond coat and a thermal barrier coating (TBC). 
         [0004]    The main blade or vane part of a turbine blade or vane is generally arranged on what is termed a platform. The platform and the blade or vane root arranged therebeneath serve to arrange and to fasten the turbine blade or vane on a mount component, for example a rotor disk or a ring or blade or vane ring. In this context, it is undesirable for coating material resulting from the coating of the main blade or vane part and the surface of the platform to protrude beyond the edge of the platform and to be located in particular on the lateral face of the platform. Corresponding contamination of the lateral faces of the platform would make it more difficult to precisely arrange the turbine blade or vane on the mount component, for example on the rotor disk or on a ring, and could moreover lead to undesirable mechanical effects or leakage flows. 
         [0005]    The main blade or vane part and the surface of the platform are preferably coated by spraying on the coating material. Possible overspraying of the platform edges of turbine blades or vanes, for example guide vanes or rotor blades, is not acceptable, and therefore, for the aforementioned reasons, coating material which has passed beyond the platform edge has to be removed manually, for example has to be abraded. This results in increased costs, an additional loss of time during the production process and, under certain circumstances, undesirable deviations in the dimensioning of the respective turbine blade or vane. 
         [0006]    In order to avoid the above-described post-machining of the platforms, the marginal edges of the top surface of the platform are partly set back by recesses, such that the transition between the top platform surface and the lateral face of the platform has a stepped configuration. A step or recess of this type usually has a height of 4 mm. 
         [0007]    A slot for a sealing strip is generally arranged on the lateral face of the platform. The slot comprises a top and a bottom edge. Since the platform of rotor blades or guide vanes becomes thinner in the direction of the generator connected to the turbine, or in the main direction of flow, this being due to the contour of the hot gas flow duct, there is the risk that the top edge becomes continuously thinner, and under certain circumstances will disappear, owing to the above-described step or recess. The top edge of the sealing slot is required, however, in order to prevent coating material from being sprayed into the slot itself. 
       SUMMARY 
       [0008]    Against this background, the aspect relates to providing an advantageous turbine blade or vane. The aspect relates to an advantageous turbine. A further aspect provides an advantageous method for producing a turbine blade or vane. 
         [0009]    The turbine blade or vane according to embodiments of the invention comprise a main blade or vane part and a platform. The platform comprises a top surface, on which the main blade or vane part is arranged. The platform furthermore comprises at least one lateral face. The lateral face comprises a slot for insertion or reception of a sealing strip. The transition between the top surface of the platform and the lateral face comprises a stepped region and a beveled region. 
         [0010]    During the production of the turbine blade or vane, the edge which is initially present in the blank for the platform between the top surface of the platform and the lateral face has thus been configured, in a first region, in the form of a step or notch or in the form of a setback or a recess. In a second region, the original edge has been configured in the form of a bevel or fold or chamfer. 
         [0011]    The stepped region and the beveled region are preferably arranged in succession in a longitudinal direction of the turbine blade or vane. The turbine blade or vane can comprise a front side and a rear side. In this case, the front side is the side on which the leading edge of the main blade or vane part is arranged on the platform, and the rear side is the side on which the trailing edge of the main blade or vane part is arranged. Considered in the direction from the front side to the rear side of the turbine blade or vane, the stepped region is preferably arranged upstream of the beveled region. 
         [0012]    The turbine blade or vane according to embodiments of the invention has the advantage that the disadvantages arising in conjunction with a continuously stepped configuration of the edge of the platform are avoided. In particular, the upper edge of the sealing slot is retained and, in particular, does not lose its stability. 
         [0013]    The turbine blade or vane according to embodiments of the invention are advantageously a rotor blade or a guide vane, for example a rotor blade or a guide vane of a gas turbine or of a steam turbine. 
         [0014]    The platform can comprise, for example, two lateral faces, a front side and a rear side. In this case, the stepped region is arranged between the front side and the beveled region, and the beveled region is arranged between the stepped region and the rear side. In this respect, “between” means in a direction parallel to the respective side edge or parallel to the longitudinal direction of the respective lateral face. It is preferable for both lateral faces of the platform, as described, to be configured with a stepped region and a beveled region. 
         [0015]    In addition, the platform can comprise a transition region, which is arranged between the stepped region and the beveled region and in which the stepped region merges into the beveled region. It is preferable that the stepped region merges continuously into the beveled region in the transition region. Continuous merging of the stepped region into the bevelled region has the advantage that the turbine blade or vane is easy to mount and undesirable tilting in the mount, for example in the rotor disk, is avoided. 
         [0016]    The stepped region preferably has a step having a height of between 2 mm and 6 mm, for example between 3.5 mm and 4.5 mm, preferably 4 mm. The step can moreover have a depth of between 0.4 mm and 8 mm, for example between 0.5 mm and 7 mm, preferably 6 mm. 
         [0017]    The beveled region is advantageously arranged between the rear side of the platform and the main blade or vane part in a longitudinal direction running parallel to the lateral face. That is to say that, in a projection of the position of the main blade or vane part on an axis running along the lateral face, the beveled region is arranged on this axis between the rear side of the platform and the main blade or vane part, in particular the trailing edge of the main blade or vane part. This has the advantage that the region of the platform in which the thickness of the platform is at its smallest is designed with a beveled edge. As a result, the function and stability of the slot for the sealing strip are retained. 
         [0018]    It is advantageous that the height or thickness of the platform decreases from the trailing edge of the main blade or vane part toward the rear side of the platform. It is preferable that the thickness or height of the platform at the beveled region decreases toward the rear side of the platform. The decrease is advantageously continuous. 
         [0019]    The turbine blade or vane according to embodiments of the invention have the advantage that reworking required under certain circumstances following the coating is reduced or is avoided. At the same time, the deviations in the geometry or dimensioning of the platform which are caused as a result of the additional machining of the platform arising from overspraying of coating material are reduced or avoided completely. In addition, the turbine blade or vane according to embodiments of the invention is easy to service. It causes fewer difficulties in relation to erosion and corrosion during refurbishment. In principle, the combination of a beveled region with a stepped region can be used both for guide vanes and for rotor blades. 
         [0020]    The turbine according to embodiments of the invention comprise an above-described turbine blade or vane. It fundamentally has the same advantages as the above-described turbine blade or vane. The turbine according to embodiments of the invention can be a gas turbine or a steam turbine, for example. 
         [0021]    The method according to embodiments of the invention for producing an above-described turbine blade or vane according to embodiments of the invention is distinguished by the fact that the stepped region and/or the beveled region and/or the transition region between the stepped region and the beveled region is removed from the platform by electrical discharge machining (EDM). The method according to embodiments of the invention has the advantage that the geometry of the platform which is characteristic of the turbine blade or vane according to embodiments of the invention can be generated in a simple manner. 
         [0022]    The geometry of the stepped region and/or of the beveled region which is characteristic of the turbine blade or vane according to embodiments of the invention can preferably be implemented in an electrode, for example graphite electrode, used during the production of the turbine blade or vane. In principle, it is possible, for example, for the stepped region and/or the beveled region and/or the transition region to likewise be worked out of the platform blank in conjunction with the working out of the slot for the sealing strip. This is the case in particular for guide vanes. 
         [0023]    Furthermore, the electrode used can be produced by milling, for example. Particularly in the case of rotor blades, it is expedient to produce the electrode to be used by 5 axis milling. 
     
    
     
       BRIEF DESCRIPTION OF THE DRAWINGS 
         [0024]    Some of the embodiments will be described in detail, with reference to the following figures, wherein like designations denote like members, wherein: 
           [0025]      FIG. 1  schematically shows a section through part of a turbine blade or vane. 
           [0026]      FIG. 2  schematically shows a partial region of a guide vane in a perspective view; 
           [0027]      FIG. 3  schematically shows a partial region of a guide vane in a perspective view and 
           [0028]      FIG. 4  schematically shows a gas turbine. 
       
    
    
     DETAILED DESCRIPTION 
       [0029]      FIG. 1  schematically shows a section through part of a turbine blade or vane  1 . The turbine blade or vane  1  shown in  FIG. 1  can be, for example, a guide vane  117  or a rotor blade  115 .  FIG. 1  schematically shows part of the platform  2  and part of the main blade or vane part  3 . The platform  2  comprises a top surface  4 , a bottom surface  5 , a front side  6 , a rear side  7  and two lateral faces  8 . The main blade or vane part  3  is arranged on the top side  4  or on the top surface of the platform  2 . A blade or vane root  9  adjoins the bottom surface  5  or bottom side of the platform  2 . 
         [0030]    The lateral face  8  comprises a slot  10  for insertion of a sealing strip. The sealing strip serves to seal off the intermediate space between two adjacent turbine blades or vanes  1 . 
         [0031]    Both the main blade or vane part  3  and the top surface  4  of the platform  2  are coated with a bond coat and a thermal barrier layer. This is typically done by spraying on the coating material. In order to prevent overspraying of the coating material from the top surface onto the lateral face, the transition from the top surface  4  to the lateral face  8  is configured in the form of a step  11 . This has the effect that overspraying of the stepped region  11  is harmless and in particular does not make post-machining of the platform  2  necessary. Moreover, the region of the lateral face  8  beneath the step  11  or recess or notch is effectively protected against undesirable spraying with coating material. 
         [0032]    The step  11  has a height h of 4.0±0.5 mm and a depth t of 0.6±0.1 mm. 
         [0033]      FIGS. 2 and 3  schematically show a partial region of a guide vane  117  in a perspective view. The guide vane  117  comprises a main vane part  3 , a platform  2  and a vane root  9 . The main vane part  3  is arranged on the platform  2 . It comprises a leading edge  16  and a trailing edge  17 . The platform  2  comprises two lateral faces  8 . A slot  10  for insertion of a sealing ring is arranged on each lateral face  8 . 
         [0034]    In the main direction of flow  20  of the hot gas, or in a longitudinal direction  21  running parallel to one of the lateral faces  8 , the thickness or height d of the platform  2  decreases, preferably continuously, at least from the trailing edge  17  of the main vane part  3  toward the rear side  7  of the platform  2 . In  FIG. 2 , for example, the thickness or height d 1  of the platform  2  downstream of the trailing edge  17  is greater than the thickness or height d 2  of the platform  2  on the rear side  7 . 
         [0035]    A stepped region  13  and, adjoining the latter, a beveled region  14  are arranged between the front side  6  of the platform  2  and the rear side  7  of the platform  2 , along the lateral face  8  above the slot  10  for the sealing ring. The stepped region  13  starts at the front side  6  of the platform  2 , and extends as far as downstream of the trailing edge  17  of the main vane part  3 , in relation to the longitudinal direction  21 . The beveled region  14  extends from the stepped region  13  as far as the rear side  7  of the platform  2 . 
         [0036]    There is a transition region  15  between the stepped region  13  and the beveled region  14 . In the transition region  15 , the geometry of the stepped region  13  merges continuously into the geometry of the beveled region  14 . 
         [0037]    The stepped region  13  preferably has a step  11  having a height of between 2 mm and 6 mm, for example 3.5 mm to 4.5 mm, preferably 4 mm. The step  11  preferably has a depth t of between 0.4 mm and 0.8 mm, for example between 0.5 mm and 0.7 mm, preferably 0.6 mm. 
         [0038]      FIG. 4  schematically shows a gas turbine. In the interior, a gas turbine has a rotor with a shaft  107  which is mounted such that it can rotate about an axis of rotation and is also referred to as the turbine rotor. An intake housing  109 , a compressor  101 , a burner arrangement  15 , a turbine  105  and the exhaust gas housing  190  follow one another along the rotor. 
         [0039]    The burner arrangement  15  is in communication with a for example annular hot gas duct. There, multiple series-connected turbine stages form the turbine  105 . Each turbine stage is formed from blade or vane rings. As seen in the direction of flow of a working medium, in the hot gas duct a row of guide vanes  117  is followed by a row formed from rotor blades  115 . 
         [0040]    In that context, the guide vanes  117  are secured to an inner housing of a stator, whereas the rotor blades  115  of a row are fitted to the rotor for example by means of a turbine disk. A generator is coupled to the rotor. 
         [0041]    While the gas turbine is in operation, the compressor  101  sucks in air through the intake housing  109  and compresses it. The compressed air provided at the turbine-side end of the compressor  101  is passed to the burner arrangements  15 , where it is mixed with a fuel. The mix is then burnt in the combustion chamber, forming the working medium. From there, the working medium flows along the hot gas duct past the guide vanes  117  and the rotor blades  115 . The working medium is expanded at the rotor blades  115 , transferring its momentum, so that the rotor blades  115  drive the rotor and the latter in turn drives the generator coupled to it. 
         [0042]    Although the present invention has been disclosed in the form of preferred embodiments and variations thereon, it will be understood that numerous additional modifications and variations could be made thereto without departing from the scope of the invention. 
         [0043]    For the sake of clarity, it is to be understood that the use of “a” or “an” throughout this application does not exclude a plurality, and “comprising” does not exclude other steps or elements.