Abstract:
A blading member for a fluid flow machine, for example, for use in gas turbine engines. The blading member includes a platform member and an airfoil member. The platform member and airfoil member are designed to allow for easy assembly/disassembly and replacement of members independent of other members.

Description:
CROSS-REFERENCE TO RELATED APPLICATIONS 
       [0001]    This application claims priority to EP Application No. 14199453.3 filed Dec. 19, 2014 and EP Application No. 15171782.4 filed Jun. 12, 2015, both of which are hereby incorporated in their entirety. 
       TECHNICAL FIELD 
       [0002]    The present disclosure relates to the field of blading members for fluid flow machines as described in the preamble of claim  1 . It further relates to an airfoil member and a platform member of blading members as mentioned above. Such blading members may for instance be applied in gas turbine engines. 
       BACKGROUND 
       [0003]    It is known in the art to manufacture airfoils and platforms of blading members of fluid flow machines separately and to assemble a blading member from at least one airfoil member and at least one platform member. This offers various benefits, e.g. different materials may be used for the airfoil and the platform, complexity of the individual pieces is reduced, thus allowing for more complex cooling schemes, and in providing individual geometries more suitable for casting or machining. However, airfoils and platforms need to be joined properly and reliably. 
         [0004]    It may generally be stated that it may be found beneficial if the joint between the two members may easily be disassembled, preferably without damaging any of the members, and particularly not damaging the platform member. This facilitates for instance replacement of worn airfoils, while the platform member may be further used. 
         [0005]    EP 1 176 284 proposes joining airfoils and platforms by brazing. 
         [0006]    U.S. Pat. No. 5,797,725 discloses blading members wherein each of the airfoil and the platform comprise a corresponding flute which are filled by a common retainer. In a preferred embodiment the retainer is manufactured inside the flutes by casting, and in particular by a process referred to a bi-casting. 
         [0007]    U.S. Pat. No. 7,686,571 and U.S. Pat. No. 7,704,044 propose coupling airfoils and platforms applying a mechanical interlock element, wherein said mechanical interlock element is slidably received inside flutes provided in the platform and along the pressure or suction side of the airfoil. 
         [0008]    According to the teaching of US 2012/0009071 airfoil and platform members are joined and locked to each other in inserting a flexible wire into corresponding recesses of the members to be locked. 
         [0009]    US 2009/0196761 describes joining airfoil and platform members by a so-called injection molding process. 
         [0010]    Moreover, European patent application 14 199 453.3, to which priority is claimed and the entire content of which is furthermore incorporated herein by reference, discloses blading member and a method for assembling and joining the blading member, wherein mechanical interlock members are provided in order to virtually generate an undercut by which the airfoil member and the platform member are interlocked. 
         [0011]    Independent from the actual process or device applied for interlocking said members, there is a need to properly position the members before interlocking them. In US 2009/0196761 for instance a built blading member is disclosed wherein the airfoil member features a shoulder which abuts a corresponding counterpart shoulder formed on the platform member. The counterpart shoulder may be provided within a receiver opening of the platform member, or may likewise be provided as a section of a face of the platform member, adjacent the receiver opening. 
       SUMMARY 
       [0012]    It is an object of the present disclosure to provide a blading member for a fluid flow machine which comprises, and is assembled from, at least one airfoil member and a platform member. It is a further object of the present disclosure to address the issues related to the assembly of a blading member of the kind initially mentioned. In one aspect, it is an object of the present disclosure to provide a blading member which overcomes drawbacks of the art cited above. It is a further object of the present disclosure to provide an airfoil member which overcomes drawbacks of the art cited above. It is still a further object of the present disclosure to provide a platform member which overcomes drawbacks of the art cited above. In another aspect it is an object of the present disclosure to provide a blading member in which at least one airfoil member and platform member may be easily assembled and be reliably and precisely positioned to each other before joining them by any appropriate means or method, including, but not limited to, the methods disclosed in the art cited above. Further, in this respect, airfoil members and platform members suitable to build the blading member are an additional object of the present disclosure. In still another aspect, a method for assembling a blading member as referred to above. 
         [0013]    This is achieved in providing a blading member according to claim  1 . It is further achieved in providing an airfoil member or a platform member according to any of the further independent claims. 
         [0014]    Further effects and advantages of the disclosed subject matter, whether explicitly mentioned or not, will become apparent in view of the disclosure provided below. 
         [0015]    In the context of this disclosure a blading member may be a part of a running blade row as well as a part of a stationary guide vane row, and a blading member may comprise one or more airfoils. A platform or shroud may be arranged at the foot as well as at the tip of an airfoil or of multiple airfoils. 
         [0016]    A blading member for a fluid flow machine according to the present disclosure comprises a platform member and at least one airfoil member. The platform member comprises a platform member receiver section, said platform member receiver section comprising a first face and a second face, and a platform member receiver opening being disposed in the receiver section, the receiver opening extending from the first face. The airfoil member extends from an airfoil base to an airfoil tip and comprises an airfoil member foot section and an airfoil member aerodynamic section, wherein the airfoil member foot section extends from the airfoil base to the airfoil member aerodynamic section and the airfoil member aerodynamic section extends from the airfoil member foot section to the airfoil tip. The airfoil member foot section comprises an airfoil member male mating section received within the platform member receiver opening. The airfoil member aerodynamic section projects from the first face of the platform member receiver section. It is understood that this does not require the airfoil member aerodynamic section to project from a surface which is flush with the first face of the platform member receiver section, but it is well within the scope of this statement, for instance, that the airfoil member foot section might protrude from the platform member receiver section first face, and the airfoil member aerodynamic section starts from there. It is further understood that this means that the first face of the platform member receiving section points towards the airfoil tip. At least one support shoulder is disposed on the airfoil foot section, and a counterpart support shoulder is disposed on the platform member, wherein the support shoulder and the counterpart support shoulder abut each other. At least one support shoulder and a corresponding counterpart support shoulder are beveled, wherein the bevel angles of said support shoulder and said corresponding counterpart support shoulder are identical at least at corresponding mating points. It will be appreciated that in practice the bevel angles will be slightly different due to manufacturing tolerances. Slight deviations which will be considered acceptable without compromising the function of shoulders by the person skilled in the art are also well within the scope of this disclosure and are covered by the above statement. The allowable difference may depend on the actual bevel angle, but an acceptable deviation between the bevel angle of a support shoulder and the mating counterpart support shoulder at corresponding mating contact points may be as large as ±2° or even ±5°. 
         [0017]    Each of the support shoulder and counterpart support shoulder may comprise a flat surface, but may also comprise a convexly rounded surface. In certain embodiments, one of the support shoulder and counterpart support shoulder may comprise or be provided as a convexly rounded surface, while the other one of the support shoulder and counterpart support shoulder may comprise or be provided as a flat surface. 
         [0018]    Due to the beveling of the corresponding shoulders, the airfoil member comprises a male tapered section, while the platform member receiver opening comprises a mating female tapered section. By virtue of these interacting tapering sections the airfoil member becomes properly centered in the platform member receiver opening when the members are assembled, and a self-centering assembly interface is provided. 
         [0019]    The bevel angle, as measured against a line perpendicular to an airfoil member longitudinal axis, wherein longitudinal is to be understood as extending along the airfoil spanwidth, may generally be anywhere between 0° and 90°, but may more specifically be larger than or equal to 30° and smaller than or equal to 60°. Larger than or equal to 40° and smaller than or equal to 50° may be found a particularly appropriate range. Generally, the larger the angle is, that is, the more acute the resulting tapering sections are, the better the airfoil member is centered, while the smaller the angle is, that is the more obtuse the resulting tapering section are, the more precise the airfoil is positioned in its longitudinal direction. 
         [0020]    The blading member may comprise a multitude of airfoil members. All airfoil members comprised in one blading member may be connected to a platform in a similar manner and in particular in applying the teaching of the present disclosure. Further, a second platform member or a shroud member may be arranged at and connected to the airfoil tip. The connection between the second platform member and the airfoil or the airfoils may be affected in the manner described in the present document, or in any other suitable manner. 
         [0021]    In particular, the platform member receiver opening may be a platform member receiver through opening extending from the first face to the second face. This might provide improved access for interlocking the members, compared to a blind receiver opening. Further in particular, the counterpart support shoulder may be provided within the platform member receiver opening. 
         [0022]    In another aspect, an airfoil member for a blading member according to the present disclosure is disclosed, the airfoil member comprising an airfoil aerodynamic section and an airfoil member foot section, wherein a support shoulder is provided on the airfoil member foot section, and wherein the support shoulder is beveled. In still another aspect, a platform member for a blading member according to the present disclosure is disclosed, the platform member comprising a receiver section, said receiver section comprising a first face and a second face, and a receiver opening being disposed in the receiver section and extending from the first face, wherein a beveled counterpart support shoulder is provided on the platform member, wherein in particular the beveled counterpart support shoulder is provided within the receiver opening, and wherein in particular the platform receiver opening is a platform receiver through opening. 
         [0023]    In some embodiments, the support shoulder of the airfoil member points towards the airfoil member base, while the counterpart support shoulder of the platform member points towards the airfoil tip. In other words, at the support shoulder the airfoil member tapers along a direction from the airfoil tip to the airfoil base, while the platform member comprises a section of the platform member receiver opening at the counterpart support shoulder where the platform member receiver opening tapers in a direction from the first face to the second face. Accordingly, an airfoil member and a platform member exhibiting said features are disclosed. These embodiments are suited for assembling the blading member in inserting the airfoil member into the platform receiver opening with the airfoil base first, or, from the first face of the platform member receiver opening. 
         [0024]    In other embodiments the support shoulder of the airfoil member points towards the airfoil member tip, while the counterpart support shoulder of the platform member points towards the airfoil base. In other words, at the support shoulder the airfoil member tapers along a direction from the airfoil base to the airfoil tip, while the platform member comprises a section of the platform member receiver opening at the counterpart support shoulder where the platform member receiver opening tapers in a direction from the second face to the first face. Accordingly, an airfoil member and a platform member exhibiting said features are disclosed. These embodiments are suited for assembling the blading member in inserting the airfoil member into the platform receiver opening with the airfoil tip first, or, from the second face of the platform member receiver opening. It is moreover understood that these embodiments may be well suited for rotating blading members, as the support shoulder and the counterpart support shoulder would then bear centrifugal forces acting on the airfoil member. 
         [0025]    The bevel angle of the shoulders may be constant along the extent of a shoulder, which facilitates manufacturing, as for instance only one tool applied at one specific angle may be required to manufacture the beveled shoulders. 
         [0026]    A shoulder may at least be provided on a side of the airfoil member foot section disposed on a suction side of the airfoil member aerodynamic section and on a side of the airfoil member foot section disposed on a pressure side of the airfoil member aerodynamic section. These may be two distinct support shoulders. In further embodiments a support shoulder extends on the periphery of a cross section of the airfoil member foot section from a side disposed on a pressure side of the airfoil aerodynamic section to a side disposed on a suction side of the airfoil member aerodynamic section such that the support shoulders being present on said two sides of the airfoil member may be part of one support shoulder. In still more specific embodiments, a support shoulder extends around the entire periphery of a cross section of the airfoil member foot section. 
         [0027]    Likewise, a counterpart support shoulder may at least be provided on a side of the platform member receiver opening which is disposed on a suction side of the airfoil member aerodynamic section and on a side of the platform member receiver opening which is disposed on a pressure side of the airfoil member aerodynamic section. As to the platform member as such this means that a counterpart support shoulder may at least be provided on a side of the platform member receiver opening which is intended, or configured and arranged, respectively, to be arranged on a suction side of the airfoil member aerodynamic section and on a side of the platform member receiver opening which is intended, or configured and arranged, respectively, to be arranged on a pressure side of the airfoil member aerodynamic section. These may be two distinct counterpart support shoulders. In other embodiments, a counterpart support shoulder extends on the periphery of a cross section of the platform member receiver opening from a side which is arranged on a pressure side of the airfoil aerodynamic section to a side which is arranged on a suction side of the airfoil member aerodynamic section. As to the platform member as such this means that a counterpart support shoulder may extend on the periphery of a cross section of the platform member receiver opening from a side of the platform member receiver opening which is intended, or configured and arranged, respectively, to be arranged on a suction side of a airfoil member aerodynamic section to a side of a platform member receiver opening which is intended, or configured and arranged, respectively, to be arranged on a pressure side of the airfoil member aerodynamic section. In an even more specific embodiment a counterpart support shoulder extends around the entire periphery of a cross section of the platform member receiver opening. 
         [0028]    The skilled person will readily understand how the different configurations of support shoulders and counterpart support shoulders lined out above may be best combined. 
         [0029]    As mentioned above, the blading member as disclosed herein is well suited for providing blading members comprising multiple airfoils. To that extent, the platform member may comprise a multitude of platform receiver openings. The blading member may further comprise a corresponding multitude of airfoil members, wherein at least the airfoil member male mating section of the airfoil member foot section of each airfoil member is received in a platform receiver opening. 
         [0030]    In still another aspect of the blading member according to the present disclosure, a platform or shroud may be provided on both longitudinal ends of the airfoil member, that is, at the airfoil base and at the airfoil tip. Accordingly, an airfoil member head section may be provided at the airfoil tip of an airfoil member. The blading member, in respective embodiments, further comprises a second platform member or shroud with at least one platform receiver opening being provided therein, wherein at least a male mating section of the airfoil head section is received in a platform receiver opening of the second platform or shroud member. 
         [0031]    The airfoil member and the platform member may be joined or interlocked by any appropriate method and/or locking device, including, but not limited to, the methods and/or locking devices mentioned above. For instance, the assembly may be interlocked or joined by bi-cast, injection molding, locking pins, any other mechanical interlock, and so forth. To provide a further example, they may be locked to each other in that mechanical interlock members are provided in order to virtually generate an undercut by which the airfoil member and the platform member are locked to each other, as is described in European patent application 14 199 453.3, which is furthermore incorporated herein by reference in its entirety, and more specifically the respectively pertinent disclosure of which is incorporated herein by reference. Accordingly, disclosed is a blading member comprising interlock means, and in particular interlock means as disclosed in any of the above cited references. Further disclosed is a blading member wherein the airfoil member and the platform member are joined or interlocked by any method as disclosed in any of the above cited references. 
         [0032]    Disclosed to this extent are furthermore a blading member, an airfoil member, and a platform member, wherein at least one flute or other depression is provided on at least one of the airfoil member and the platform member, wherein further such depression is suitable to receive a locking means for interlocking the airfoil member and the platform member. In particular, said depression may be provided inside the receiver opening and/or on the mating section of the airfoil member foot. In more particular embodiments, depressions are provided on the airfoil member as well as in the platform member receiver opening, and arranged such that, when the airfoil member and the platform member are assembled, they are arranged adjacent each other, in essence forming a combined cavity. Such combined cavity may for instance be filled by a method such as above-referenced bi-cast or injection molding, in order to form an interlock feature inside the combined cavity. 
         [0033]    A method for assembling the airfoil member and the platform member to form a blading member according to the present disclosure comprises inserting the airfoil member foot section into the platform member receiver opening from the first face, and mating a support shoulder provided on the foot section of the airfoil member and a counterpart support shoulder provided on the platform, and in particular within the platform member receiver opening, thereby centering the airfoil member foot section, or the airfoil member male mating section, respectively, within the platform member opening. 
         [0034]    A further method for assembling the airfoil member and the platform member to form a blading member according to the present disclosure comprises inserting the aerodynamic section of the airfoil member into a platform member receiver through opening from the second face, forwarding the aerodynamic section through the receiver through opening, and further advancing the airfoil member in said direction through the receiver through opening until a support shoulder provided on the foot section of the airfoil member and a counterpart support shoulder provided on the platform member, and in particular within the platform member receiver opening, mate, thereby centering the airfoil member foot section, or the airfoil member male mating section, respectively, within the platform member opening. 
         [0035]    It is understood that subsequently the assembly may be locked by any of the methods or in applying any of the locking devices referred to above. 
         [0036]    It is understood that the features and embodiments disclosed above may be readily combined with each other. It will further be appreciated that further embodiments are conceivable within the scope of the present disclosure and the claimed subject matter which are obvious and apparent to the skilled person. 
     
    
     
       BRIEF DESCRIPTION OF THE DRAWINGS 
         [0037]    The subject matter of the present disclosure is now to be explained in more detail by means of selected exemplary embodiments shown in the accompanying drawings. The figures show 
           [0038]      FIG. 1  a general overview of an airfoil member and a platform member according to the present disclosure; 
           [0039]      FIG. 2  details of a first embodiment of the airfoil member and the platform member; 
           [0040]      FIG. 3  details of a second embodiment of the airfoil member and the platform member; 
           [0041]      FIG. 4  details of an exemplary embodiment of the interface between the airfoil member and the platform member of a blading member according to the present disclosure; 
           [0042]      FIG. 5  details of a further exemplary embodiment of the interface between the airfoil member and the platform member of a blading member according to the present disclosure; 
           [0043]      FIG. 6  details of still a further exemplary embodiment of the interface between the airfoil member and the platform member of a blading member according to the present disclosure; 
           [0044]      FIG. 7  an exemplary embodiment of a blading member with a platform member being provided on both longitudinal ends of an airfoil member. 
       
    
    
       [0045]    It is understood that the drawings are highly schematic, and details not required for instruction purposes may have been omitted for the ease of understanding and depiction. It is further understood that the drawings show only selected, illustrative embodiments, and embodiments not shown may still be well within the scope of the herein disclosed and/or claimed subject matter. 
       DETAILED DESCRIPTION 
       [0046]      FIG. 1  depicts a first exemplary embodiment of the blading member according to the present disclosure. Shown are an airfoil member  1  and a platform member  2 . The airfoil member  1  comprises an airfoil member aerodynamic section  3  and an airfoil member foot section  4  extending from an airfoil base  16  to the airfoil aerodynamic section  3 . The platform member  2  comprises a receiver opening  5  provided in a receiver section  6  and extending from a first face  7  of the receiver section to a second face  8  of the receiver section. The platform member receiver opening  5  is shaped and dimensioned such as to receive airfoil member foot section  4 , or a mating section thereof. Furthermore, the airfoil member aerodynamic section  3  comprises a concavely curved pressure side  10  and a convexly curved suction side  11 . The airfoil further comprises a leading edge and a trailing edge (without reference numerals) as is apparent to the skilled person. The leading edge and the trailing edge separate the pressure side and the suction side from each other. It may be found beneficial if the cross sections of the airfoil foot section and the airfoil aerodynamic section are by and large similar to each other. Thus, also the airfoil foot section may comprise a convexly shaped surface and a concavely shaped surface, as well as the platform receiver opening may comprise a convexly shaped area and a concavely shaped area. The platform member may in other embodiments also comprise multiple receiver sections and receiver openings and may thus be adapted to receive a multitude of airfoil members, such that a blading member may comprise a multitude of airfoils. A support shoulder  12  is provided on the airfoil member, while a counterpart support shoulder  13  is provided on the platform member. Support shoulder  12  and counterpart support shoulder  13 , in this specific embodiment, run as ledges around the foot section  4  and the receiver opening  5  as a closed loop from a suction side area to a pressure side area. However, other embodiments in which for instance a multitude of support shoulders and/or counterpart support shoulders, respectively, are arranged on areas adjacent the pressure and the suction side of the airfoil aerodynamic section, or, in other words, a shoulder may not be a continuous ledge, but an interrupted ledge, thus resulting in said multitude of support shoulders or counterpart support shoulders, respectively. 
         [0047]      FIG. 2  depicts in more detail the assembly of an airfoil member  1  and a platform member  2 . The drawing depicts two possible embodiments of an interlock member which might be applied for locking the assembly, and which is lined out in more detail in European patent application 14 199 453.3. As is seen, the airfoil member  1  is inserted into the receiver opening  5  from top to bottom, or, more precisely said, from the first face  7  towards the second face  8  of the platform receiver section  6 . Receiver opening  5 , in this embodiment, is provided as a receiver through opening, extending from the first face  7  to the second face  8 . The aerodynamic section of the airfoil member  1  is in this embodiment partially received within the platform receiver opening  5  and projects from the first face  7 . A support shoulder  12  is provided on the airfoil member and abuts a counterpart support shoulder  13  formed within the receiver through opening  5 . A male mating section  14  of the airfoil member foot section  4  is received within the platform member receiver opening  5  and may in particular fit snugly within the receiver opening. The airfoil member foot section  4  in part projects from the platform member receiver section second face  8 . An airfoil base  16  thus is located outside the receiver opening. Support shoulder  12  which is provided on airfoil member  1  matingly abuts counterpart support shoulder  13  which provided on the platform, and in this embodiment within the receiver opening. Support shoulder  12  and counterpart support shoulder  13  are beveled at at least approximately and essentially identical bevel angles a. While the surface of support shoulder  12  points to the airfoil base, the surface of counterpart support shoulder  13  points to the airfoil tip, or, to the first face  7 . In other words, the beveled shoulders  12 ,  13  provide for a tapered section of the airfoil member and for a tapered section of the receiver opening, both tapering in a direction from the airfoil tip to the airfoil base, or from the receiver section  6  first face  7  to the receiver section  6  second face  8 , respectively. Due to the thereby provided mating tapers, the airfoil is centered in the receiver opening, and at the same time a well-defined position in the airfoil longitudinal direction, that is, a direction extending between the airfoil base and the airfoil tip, is provided for. On the left-hand part of  FIG. 2 , a first exemplary configuration of an interlock member, a retainer member and an interlock receiver recess is shown. An interlock receiver recess  9  is provided in the airfoil foot section  4 . An interlock member  15  is provided in the interlock receiver recess and comprises a section protruding therefrom. An interlock counterpart seating surface  17  is provided on the platform member receiver section second face  8  and bears the seating surface of the interlock member  15 . A retainer member  18  is provided which is on the one hand interlocked with the platform and on the other hand mates with the interlock member  15 . Retainer member  18  is weld-connected to interlock member  15  by a weld connection  19 . To assemble the blading member, firstly the airfoil foot  4  is inserted through the receiver through opening  5  and forwarded from the first face  7  towards the second face  8  until support shoulder  12  abuts and mates with counterpart support shoulder  13 , thereby, due to the interaction of the tapering sections provided by the shoulders  12  and  13 , centering the airfoil member within the receiver opening. Then interlock member  15  is inserted into interlock receiver recess  9 . Retainer member  18  is introduced into an undercut provided on platform member  2  and brought into abutting contact with interlock member  15 . Thereafter, weld connection  19  is produced. The location of weld connection  19  is easily accessible if the blading member is not mounted to a rotor or a stator, and may thus be easily produced and also disjoined for inspection, servicing and reconditioning purposes. As is seen, a part of the platform receiver section is form locked between support shoulder  12  and interlock member  15 , and thus the platform member and the airfoil member are locked to each other. With reference to the right-hand side of  FIG. 2 , a second configuration of an interlock recess  9 , an interlock member  20  and a spring type retainer member  21  is shown. Spring-type retainer member  21  applies a force directed towards the ground of the interlock receiver recess  9  on the interlock member  20 . Due to the wedge shape of interlock member  20  in the shown cross-section, a force directed from the platform member receiver section first face  7  towards the second face  8  becomes effective on the airfoil member  1 , and the bearing surface of the support shoulder  12  is firmly pressed onto the corresponding counter support shoulder  13  provided in the platform receiver through opening. 
         [0048]    With reference to  FIG. 3 , a reverse configuration is shown. The airfoil member  1  is inserted into the platform receiver through opening  5  in a direction from the second face  8  towards the first face  7 . The airfoil member foot section extends only through a part of the platform member receiver through opening  5 . Airfoil base  16  is thus located inside the receiver through opening  5 . Support shoulder  12  which is provided on airfoil member  1  matingly abuts counterpart support shoulder  13  provided on platform  2 , and in this embodiment within receiver opening  5 . Support shoulder  12  and counterpart support shoulder  13  are beveled at an at least approximately and essentially identical bevel angle a. While the surface of support shoulder  12  points to the airfoil tip, the surface of counterpart support shoulder  13  points to the airfoil base, or, to the second face  8 . In other words, the beveled shoulders  12 ,  13  provide for a tapered section of the airfoil member and for a tapered section of the receiver opening, both tapering in a direction from the airfoil base to the airfoil tip, or, from the receiver section  6  second face  8  to the receiver section  6  first face  7 , respectively. Due to the thereby provided mating tapers, the airfoil is centered in the receiver opening, and at the same time a well-defined position in the airfoil longitudinal direction, that is, a direction extending between the airfoil base and the airfoil tip, is provided for. As is seen, the bevel angle in this embodiment is smaller than in the embodiment of  FIG. 2 . This difference in the angle is not tied to the different configuration, but the angle may be chosen dependent on various parameters. 
         [0049]    For instance, the smaller bevel angle provides for a more precise positioning in the longitudinal direction, while larger bevel angles support centering or the airfoil member in the receiver opening. However, it will be appreciated that the smaller bevel angle may support bearing centrifugal forces if a rotating blade member is provided by an arrangement as shown in  FIG. 3 . Interlock receiver recess  22  is provided on a platform member receiver through opening  5  inner wall. Interlock members  15 ,  20  are provided in the interlock receiver recess or recesses provided on opposite sides of the platform member receiver through opening.  FIGS. 4 through 6  depict in more detail the arrangement of support shoulders and counterpart support shoulders of various exemplary embodiments of blading members according to the present disclosure. 
         [0050]      FIG. 4  depicts a longitudinal cut through one embodiment. Airfoil member  1  is joined with platform member  2  to form a blading member. In this longitudinal cut, internal cooling channels  101  are schematically indicated inside airfoil member  1  in a manner known per se in order to indicate the possibility of internal cooling structures being present. However, it should be noted that these cooling structures are not relevant to the subject matter of the present disclosure, and are only schematically hinted at in  FIG. 4  as well as in the subsequent figures, while omitting any details. It is understood that within the frame of this disclosure for instance airfoil members exhibiting significantly more complex cooling structures as well as airfoil members without any cooling structures are possible. Airfoil member  1  and platform member  2  comprise beveled support shoulder  12  and beveled counterpart support shoulder  13 , which mate in order to properly place airfoil member  1  relative to platform member  2 . Counterpart support shoulder  13  is arranged within the receiver opening and at a distance d from the first face  7 , or hot gas side, of the platform receiver section  6 . Distance d might for instance be in a range from 0 to 20 mm, or in other embodiments from 0 to 10 mm, wherein the boundary values are included in the said range. Along distance d a lateral gap with gap width c is provided. Gap width c may for instance be larger than or equal to 0.01 mm and smaller than or equal to 2.0 mm. Also, between the mating shoulders and the second face  8  of platform receiver section  6 , or airfoil base  16 , respectively, a lateral gap is provided. Said lateral gaps facilitate insertion of airfoil member  1  into the receiver opening provided in platform member receiver section  6 . Airfoil base  16  is shown flush with the second surface  8  of the platform receiver section. This feature, however, is not mandatory. Flutes  24  and  25 , of which the cross section is visible in the present depiction, are provided on an inner wall of platform receiver section  6  and on airfoil member foot section  4 . The flutes  24  and  25  are arranged on the platform member and the airfoil member, respectively, such that, when the airfoil member and the platform member are assembled, they are located adjacent each other, and at least exhibit an overlap with each other, such as to form a combined cavity. A retainer or interlock member may be inserted or manufactured filling the combined cavity and thus interlocking airfoil member  1  and platform member  2 . The interlock member may for instance be manufactured in place inside the common cavity in applying, to name some, a method like bi-casting or injection molding which have been referred to above. Instead of flutes, any other pair or pairs of overlapping depressions may be provided to receive an interlock member. 
         [0051]    With reference to  FIG. 5 , a further embodiment is shown. The mating shoulders  12 ,  13  are arranged immediately adjacent the first face  7  of platform receiver section  6 . The first face of platform receiver section  6  as well as the surface of airfoil member  1  is shaped such as to provide a smooth transition surface between airfoil member  1  and platform member  2 . Said radius may in certain embodiments provide, for instance, aerodynamic benefits for a hot gas flow flowing over the first face  7  and around the airfoil aerodynamic section when the blading member operates in a turbo engine. In the manner described above, flutes  24  and  25  are provided, forming a combined cavity suited to receive any appropriate kind of interlock or retainer feature for interlocking airfoil member  1  and platform member  2 . 
         [0052]    While in the above mentioned figures the flutes, or interlocking feature, respectively, has been shown to be disposed towards the cold gas side, or, towards the airfoil base, respectively, as seen from the mating beveled shoulders,  FIG. 6  depicts an embodiment wherein the interlocking feature is disposed towards the hot gas side, or the airfoil tip, respectively. Disposing the interlocking feature towards the cold gas side from the mating shoulders may exhibit the advantage of better isolating the interlocking feature from hot gases, in particular hot combustion gases. However, also an arrangement as provided in the embodiment of  FIG. 6  may be found beneficial. Besides,  FIG. 6  depicts various exemplary geometries for the transition between the first face  7  of the platform receiver section  6  and the outer surface of the airfoil member  1 . These transition geometries are not beforehand relevant to the subject matter of the present disclosure, and may be chosen by the skilled person dependent on, for example, aerodynamic properties or other criteria. 
         [0053]      FIG. 7  depicts a disassembled embodiment of the blading member according to the present disclosure wherein a second platform or shroud  200  is arranged at the tip of the airfoil member  1 . On one longitudinal end of the airfoil member  1  an airfoil member foot section  4  is provided, which is in accordance with the subject matter of the present disclosure, that is, amongst other features, a beveled support shoulder is provided. The platform receiver opening is provided in platform member  2  and is suited to receive airfoil member foot section  4 , or a part thereof, while also a beveled counterpart support shoulder is provided on platform member  2 . At the tip of the airfoil, head section  400  is provided, while the second platform member  200  comprises a platform receiver opening suited to receive the airfoil head section  400 . At the interface between the airfoil head section  400  and second platform  200 , beveled shoulders, and other features described above at the interface between foot section  4  and platform member  2 , may or may not be provided. Generally, second platform member  200  may also be attached to the airfoil member in any other suitable manner. 
         [0054]    In the exemplary embodiments lined out above, the airfoil foot section and the platform receiver through opening have been shown with the cross section essentially resembling the cross section of an airfoil aerodynamic section. While this is a suitable embodiment, and may in particular be useful to avoid overly abrupt or stepwise changes of the airfoil member cross-section, this is not a mandatory feature. 
         [0055]    Embodiments comprising multiple airfoils will in the light of the explanations above be apparent to the skilled person without exemplary embodiments being explicitly shown. 
         [0056]    While the subject matter of the disclosure has been explained by means of exemplary embodiments, it is understood that these are in no way intended to limit the scope of the claimed invention. It will be appreciated that the claims cover embodiments not explicitly shown or disclosed herein, and embodiments deviating from those disclosed in the exemplary modes of carrying out the teaching of the present disclosure will still be covered by the claims.