document: TECHNICAL FIELD  
           [0001]    The present invention relates to the field of thermal machines. It relates in particular to a cooled flow deflection apparatus for a fluid-flow machine which operates at high temperatures, as claimed in the precharacterizing clause of claim  1 .  
             [0002]    Such a flow deflection apparatus is generally known from the prior art, for example in the form of a cooled stator blade or rotor blade for a gas turbine.  
           PRIOR ART  
           [0003]    Present-day flow deflection apparatuses, especially stator blades or rotor blades in a gas turbine, are subjected to ambient temperatures which are above the maximum permissible material temperature. The use of special internal cooling channels allows the metal temperature to be reduced to a level which is required on the basis of the life of the apparatus.  
             [0004]    [0004]FIGS. 1 and 2 respectively show a cross section and longitudinal section of an example of a rotor blade of a gas turbine, as is currently used. The blade  10  essentially comprises a blade airfoil section  11  and a blade root  12 , by means of which it is attached to the rotor of the gas turbine. A number of cooling channels  17  run in the longitudinal direction of the blade  10  in the interior of the (hollow) blade airfoil section  11 , through which cooling channels  17  a cooling fluid, generally cooling air which enters through the blade root  12 , flows. The cooling fluid runs, with a cooling effect, in the cooling channels  17  along the insides of the hot-gas walls  14  and then (for film cooling) emerges to the outside through appropriate film-cooling openings which are arranged on the leading edge  18 , on the trailing edge  19  and at the blade tip (the emerging cooling fluid is indicated by the arrows in FIG. 2). The individual cooling channels  17  are separated from one another by separating walls  13  which at the same time have deflection devices  16  to ensure that the cooling fluid flows successively through adjacent cooling channels in alternately opposite directions.  
             [0005]    Until now, and in this case specifically in the case of rotating guide apparatuses such as rotor blades, the cooling channels  17  and their separating walls  13  have been cast.  
             [0006]    The known, cast separating walls  13  and deflection devices  16 , which are also referred to as ribs, have a number of disadvantages, however:  
             [0007]    The transitional region ( 15  in FIG. 1) from the hot-gas wall  14  to the separating wall (rib)  13  is an area which is difficult to cool owing to the large amount of material in that area. Increased heat transfer together with increased cooling-air consumption is required in order to ensure adequate strength there.  
             [0008]    The cold separating walls (ribs)  13 , around which the cooling air flows, lead to thermal stresses with the hot-gas wall  14 .  
             [0009]    Casting of the internal channels leads to a high blade weight, which can lead to high centrifugal-force stresses both for the blade root  12  and for the blade airfoil section  11 .  
             [0010]    The complex casting lengthens casting development and increases the amount of scrap.  
           DESCRIPTION OF THE INVENTION  
           [0011]    The object of the invention is thus to provide a cooled flow deflection apparatus which avoids the described disadvantages of the known apparatus and in particular is simple to produce, can be flexibly matched to the respective application, and is efficiently cooled.  
             [0012]    The object is achieved by the totality of features of claim  1 . The essence of the invention is no longer to produce, in particular to cast, the separating walls, which are used to bound the cooling channels, jointly with the apparatus, but to construct them as separate inserts which are subsequently inserted into the apparatus, and are secured there. The invention is thus considerably different to solutions such as those described in U.S. Pat. No. 5,145,315 or U.S. Pat. No. 5,516,260, in which specific inserts in cast cooling channels are used for specific guidance of the cooling fluid.  
             [0013]    The use of inserts (for example, in the case of blades, inserted through the blade root or through the blade tip) composed of metal or non-metal materials as a substitute for cast separating walls and, possibly, deflection devices, has a number of advantages:  
             [0014]    There is no large amount of material in the transitional region from the hot-gas wall to the insert (to the separating wall).  
             [0015]    There are no thermal stresses between the insert (separating wall) and the hot-gas wall.  
             [0016]    In the case of rotating blades, the blade weight and thus the centrifugal-force stresses are reduced both in the blade root and in the blade airfoil section.  
             [0017]    In the case of cast blades, the cast core is simpler, as a result of which both its capability to be produced and that of the blade are simpler.  
             [0018]    The cooling system can easily be adjusted by replacing the inserts, for example by varying the deflection radius of deflection devices or by introducing connecting cross sections between two cooling channels.  
             [0019]    A first preferred embodiment of the flow deflection apparatus according to the invention is characterized in that the flow deflection apparatus is in the form of a hollow casting, and in that holders, which are in the form of rails and into which the separating walls are inserted, are integrally formed in the interior of the flow deflection apparatus. This considerably simplifies assembly and attachment of the inserts, and ensures that the separating walls or inserts are sealed well at the edges. The separating walls are in this case preferably flat strips composed of a metallic or heat-resistant non-metallic (ceramic or composite) material.  
             [0020]    A secure seating for the inserts is achieved if, according to a second preferred embodiment of the invention, the inserted separating walls are, for security, connected by an integral material joint, preferably by soldering or welding, to the flow deflection apparatus.  
             [0021]    In the simplest form, the separating walls may be straight.  
             [0022]    It is particularly simple and advantageous if, according to another embodiment, the cooling fluid flows in mutually opposite directions in two adjacent cooling channels, if the cooling fluid is deflected from the outlet of the one cooling channel into the inlet of the other cooling channel by means of a deflection device, and if the deflection is produced by a separating wall which is bent into a U-shape.  
             [0023]    One particularly preferred embodiment of the flow deflection apparatus according to the invention is characterized in that the flow deflection apparatus is a blade in a gas turbine. Owing to the comparatively complex geometry of the blade, the invention in this case results in considerable simplifications.  
             [0024]    Another embodiment, which is particularly advantageous for rotor blades which rotate at high speed, is characterized in that the cooling channels and separating walls extend essentially in the radial direction with respect to the rotation axis of the gas turbine, in that the inserted separating walls are, for security, connected by an integral material joint, preferably by soldering or welding, to the blade, and in that the integral material joint is arranged at the end of the separating walls close to the axis. 
         
      
      
       BRIEF DESCRIPTION OF THE FIGURES  
         [0025]    The invention will be explained in more detail in the following text with reference to exemplary embodiments and in conjunction with the drawing, in which:  
           [0026]    [0026]FIG. 1 shows the cross section through a turbine blade having cast cooling channels according to the prior art;  
           [0027]    [0027]FIG. 2 shows a longitudinal section through the blade shown in FIG. 1;  
           [0028]    [0028]FIG. 3 shows a cross section, comparable to that in FIG. 1, through a blade according to one exemplary embodiment of the invention; and  
           [0029]    [0029]FIG. 4 shows a longitudinal section, comparable to that in FIG. 2, through the blade shown in FIG. 3.  
       
      
       APPROACHES TO IMPLEMENTATION OF THE INVENTION  
         [0030]    [0030]FIGS. 3 and 4 respectively show a cross section and longitudinal section of an exemplary embodiment of a cooled flow deflection apparatus according to the invention in the form of a rotor blade for a gas turbine. The geometry of the blade  20  is similar to that of the known blade  10  shown in FIGS. 1 and 2.  
           [0031]    Once again, the blade  20  essentially comprises a blade airfoil section  21  and a blade root  22 , by means of which it is attached to the rotor of the gas turbine. A number of cooling channels  27 , through which a cooling fluid which enters through the blade root  22  flows, run in the longitudinal direction of the blade  20 , in the interior of the (hollow) blade airfoil section  21 . The cooling fluid runs in cooling channels  27  along the insides of the hot-gas walls  24 , with a cooling effect, and in this case as well emerges to the outside through appropriate film cooling openings which are arranged on the leading edge  28 , on the trailing edge  29 , and at the blade tip. The individual cooling channels  27  are separated from one another by separating walls  23  which at the same time have deflection devices  26  to ensure that the cooling fluid flows successively through adjacent cooling channels in alternately opposite directions.  
           [0032]    In contrast to FIGS. 1 and 2, the separating walls  23  are in this case not cast, however, that is to say produced together with the blade  20  in one casting process, but are separate inserts, in the form of strips, which, once the blade  20  has been cast, are introduced through the blade root  22  or through the opposite blade tip. In order to allow the separating walls  23  to be inserted as required and to be secured after insertion, holders  30  which are in the form of rails and in which the longitudinal edges of the separating walls  23  are guided during insertion are integrally formed on the insides of the hot-gas walls.  
           [0033]    The separating walls (inserts)  23  may have any desired shape. For example, they may be straight. If a number of cooling channels are intended to be connected to one another by means of deflection devices  26 , it is advantageous for the separating walls  23  to be bent into a U-shape. The separating walls  23  can be secured on one or more sides, for example by soldering or welding. They may be fixed in the blade tip region or in the blade root region. The latter has the advantage that the centrifugal forces which occur load the insert or the separating wall in tension, thus preventing them from bulging out.  
           [0034]    In principle, the separating walls which can be inserted are provided at the same time that the blades are produced. However, it is also feasible within the scope of the invention for the cast separating walls subsequently to be removed from completely cast blades as shown in FIGS. 1 and 2 and for separate separating walls to be inserted and to be secured as a substitute for them.  
         LIST OF REFERENCE SYMBOLS  
         [0035]    [0035] 10 ,  20  Blade  
           [0036]    [0036] 11 ,  21  Blade airfoil section  
           [0037]    [0037] 12 ,  22  Blade root  
           [0038]    [0038] 13  Separating wall (rib)  
           [0039]    [0039] 14 ,  24  Hot-gas wall  
           [0040]    [0040] 15 ,  25  Transitional region  
           [0041]    [0041] 16 ,  26  Deflection device  
           [0042]    [0042] 17 ,  27  Cooling channel  
           [0043]    [0043] 18 ,  28  Leading edge  
           [0044]    [0044] 19 ,  29  Trailing edge  
           [0045]    [0045] 23  Insert  
           [0046]    [0046] 30  Holder (in the form of a rail)
summary: Apparatus is disclosed for providing cooling channels in the interior of a gas turbine rotor blade. The cooling channels are formed by metallic inserts which extend from adjacent the root of the blade toward the tip. The inserts are substantially flat and are secured in the interior of the airfoil section by means of rails which engage the longitudinal edges of the inserts and serve as a guide during insertion. The rails are preferable formed integrally with the blade casting.