Patent Document

FIELD OF INVENTION 
       [0001]    The present invention relates to the field of gas turbines. It refers to a gas turbine rotor with a cooling air slot according to the preamble of claim  1 , and also refers to a method for producing such a gas turbine rotor. 
       BACKGROUND 
       [0002]    A gas turbine rotor, as is used for example in the case of types GT11 and GT13 gas turbines of the assignee of the present application, is known from publication EP-A2-1 705 339 (see FIG. 1 there). Such a gas turbine rotor is also shown in  FIGS. 1 and 2  of the present application. The gas turbine rotor  10  which is shown in  FIG. 1  is constructed from rotor disks which are welded together in a known manner in the direction of the axis  18  and has a compressor section  11  and a turbine section  12 , between which the combustion chamber is arranged in the assembled state of the gas turbine.  FIG. 3  corresponds to FIG. 5 from EP-A1-1 862 638 and shows an enlarged detail of the turbine section  11  which adjoins the combustion chamber. 
         [0003]    In the two sections  11  and  12 , a plurality of rows of rotor blades, which are not shown in  FIG. 1 , are fastened one behind the other in the axial direction. The rotor blades are inserted by correspondingly designed blade roots into encompassing rotor blade slots ( 37  in  FIG. 3 ). A heat accumulation segment carrier  35  is formed upstream of the first rotor blade slot  37  of the turbine section  11  in the flow direction and has a multiplicity of axial heat accumulation segment slots  15  which are distributed over the circumference. Beneath the heat accumulation segment carrier  35  an encompassing cooling air slot  13  is arranged, which by means of axial cooling air holes  14  ( FIG. 2 ) which are distributed over the circumference is exposed to admission of compressed cooling air from the compressor section of the gas turbine. The cooling air slot  13  is partially covered by bridges  36  which are spaced apart by means of gaps  38  and limit access to the cooling air slot  13  to the gaps  38 . 
         [0004]    In such gas turbine rotors, encompassing incipient cracks, or cracks  17  ( FIG. 2 ), can occur in the slot base  16  of the cooling air slot  13  depending upon the operating mode and operating time. The incipient cracks grow further with each start-up and after reaching a specific crack depth lead to unstable crack propagation as a result of rotating bending stress and fundamentally impair the component operational safety. Therefore, incipient cracks, especially in the slot base  16  of turbine shafts, must be reliably avoided. 
         [0005]    Corresponding strength calculations, which are conducted according to the findings with crack development, prove that the intense operationally induced heat yield during start-up of the plant, in conjunction with the high notch effect of the slot geometry according to the previous design according to  FIG. 2 , leads to significant alternating plastifications which cause the crack formation. 
         [0006]    A slot geometry for newly manufactured rotors therefore takes into consideration the two criteria (heat yield as load shock and notch effect of the old slot geometry) with a wider slot for reducing the air velocity and less sharp transition radii of the slot base to the slot flanks. The previous repair methods are based on constructing the new slot geometry by means of machining out the slot, i.e. by increasing the old slot geometry. In this case, the bridges  36  of the heat accumulation segment carriers  35  are removed over the slot width, which reduces the supporting stability of the remaining bridge sections as a guide for the slot-covering cover segments, or requires the subsequent arrangement of the bridges  36  by means of welded connections and post-heat treatment of the latter. 
       SUMMARY 
       [0007]    The disclosure is directed to a method for machining a gas turbine rotor having a cooling air slot, which concentrically extends around an axis of the gas turbine rotor and is supplied with compressed cooling air via axial cooling air holes, which at the side lead into the slot base of the cooling air slot, and the opening of which is covered by bridges which are arranged in a distributed manner over the circumference and spaced apart from each other by gaps. The method includes lowering a material-removing tool in the gaps between the bridges one after the other into the cooling air slot. The method also includes machining the slot base of the cooling air slot over the entire circumference, and widening, in width the slot base of the cooling air slot as a result of the material removal in such a way that it has a tear-shaped cross-sectional contour with a constriction which lies at the level of the bridges. 
     
    
     
       BRIEF DESCRIPTION OF THE DRAWINGS 
         [0008]    The invention is to be subsequently explained in more detail based on exemplary embodiments in conjunction with the drawings. In the drawings: 
           [0009]      FIG. 1  shows in a perspective, partially sectioned view an as known per se gas turbine rotor with a cooling air slot in the turbine section; 
           [0010]      FIG. 2  shows an enlarged detail from  FIG. 1  with the cooling air slot and an associated cooling air hole; 
           [0011]      FIG. 3  shows a perspective view of the heat accumulation segment slot of the gas turbine rotor from  FIG. 1  with the cooling air slot lying beneath it; 
           [0012]      FIG. 4  shows the principle of machining the cooling air slot according to the invention, and 
           [0013]      FIG. 5  shows a flow diagram according to an exemplary embodiment of the invention. 
       
    
    
     DETAILED DESCRIPTION OF THE PREFERRED EMBODIMENTS 
       [0014]    Introduction to the Embodiments 
         [0015]    It is therefore an object of the invention to provide a method for machining a gas turbine rotor, with which in the case of crack-prone cooling air slots with partially overlapped bridges the slot base and the slot flanks of the cooling air slots are made free of cracks by forming a new slot contour without welds with subsequent heat treatment in conjunction with the bridge renewal being necessary. 
         [0016]    A further object of the invention is based on using a slot shape with which operationally induced component reaction cracks are avoided. 
         [0017]    The object is achieved by the entirety of the features of claim  1 . It is an essential feature for the solution that a material-removing tool, particularly a milling tool, is lowered in the gaps between the bridges one after the other into the cooling air slot, and in this way the slot base of the cooling air slot is machined over the entire circumference, and that the slot base of the cooling air slot is widened in width as a result of the material removal in such a way that it has a tear-shaped cross-sectional contour with a constriction which lies at the level of the bridges. 
         [0018]    According to one development of the invention a specific section of the cooling air slot is machined through each of the gaps, wherein the machining sections which are associated with adjacent gaps overlap. 
         [0019]    A further development of the method is that the material-removing tool is moved in a programmed controllable manner in the cooling air slot in a plurality of planes, in that the gas turbine rotor is rotatably supported around its axis, and that once the associated section of the cooling air slot is machined through a gap the material-removing tool is withdrawn from the cooling air slot, the gas turbine rotor is rotated around its axis by a predetermined angle, and the material-removing tool is lowered in a new gap into the cooling air slot for machining. 
         [0020]    Another development is that the machining of the slot base is conducted in such a way that the cooling air slot in the slot base has a crack-resistant slot shape with a notch factor of &lt;1.5. 
         [0021]    The material-removing tool for machining the slot base is preferably controlled according to a numerical control program (NC-program). In particular, a component-specific cross-sectional final profile of the slot base is determined in this case from the individual operating data of the gas turbine rotor, wherein the cross-sectional final profile can be produced from one or more cross-sectional master profiles by the use of distortion parameters which are determined, a corresponding NC-program for controlling the material-removing tool is associated with each cross-sectional master profile, and the determined distortion parameters are used for adapting the NC-program for the creation of the cross-sectional final profile. The adapting of the NC-program is preferably undertaken by the distortion parameters offline with a postprocessor, or online in the machine control system. 
         [0022]    If the gas turbine rotor, before the machining in the cooling air slot, has cracks of a specific crack depth, the cross-sectional final profile which is to be achieved as a result of the machining is preferably influenced by the type and state of the cracks. 
         [0023]    Detailed Description 
         [0024]    In  FIG. 4 , a cooling air slot  13 , as it is also shown in  FIG. 2  and as it is before the machining, is drawn in with broken lines. The cooling air slot  13  has a very narrow slot base  16  which leads to the compressed air which flows in through the cooling air holes  14  locally heating the opposing slot flanks in specific operating states and causing thermal stresses in the cooling air slot. It is the aim of the machining method, without intervention into the structure of the bridges  36  ( FIG. 3 ), to widen the cooling air slot which lies beneath them, starting from the cross-sectional contour of the cooling air slot  13  in  FIG. 4 , so that the harmful effects of the cooling air which flows into the slot can be substantially alleviated. 
         [0025]    For this purpose, according to  FIG. 4  a material-removing tool, especially with a longish milling body  22 , which rotates around an axis  23 , is lowered in the gaps  38  between the bridges  36  one after the other into the cooling air slot, and the slot base  16  of the cooling air slot is widened over the entire circumference so that a cross-sectional profile according to the slots which are shown in  FIG. 4  as a cooling air slot  19  or cooling air slot  19 ′ results. The milling tool  22  in this case must not only be rotated the axial direction but also in the circumferential direction. As a result of this type of machining, the slot base of the cooling air slot is widened in width (b 1 , b 2 ) by material removal in such a way that it has the tear-shaped cross-sectional contour which is shown in  FIG. 4  with a constriction  20  which lies at the level of the bridges  36 . Furthermore, as a result of the rotation in the circumferential direction, a specific circumferential section of the cooling air slot is machined through each of the gaps  38 , wherein the machining sections which are associated with adjacent gaps overlap. A uniformly widened slot base cross section over the circumference, as is to be seen in  FIG. 4 , altogether results in this way despite the geometric limitation during the individual machining steps. The rounded transition between slot flanks and slot base in this case preferably has the shape of an elliptical section (ellipse  24 ). 
         [0026]    The slot shape in this case is determined by a slot width (b 1 , b 2 ) as a flow path length which alleviates the effect of the air from the compressor, which flows in through the cooling air holes, in such a way that this does not bring about impermissible heat yield into the slot flanks. For this purpose the slot base has a tear-shaped formation with a constriction  20  and a transition  21  between a widened section and a section of constant width with the aim of a notch factor of &lt;1.5 as a design feature of the crack-resistant slot shape. From the individual operating data of each gas turbine rotor the component-specific shape of the slot base is determined by known mathematical methods. 
         [0027]    The new slot shape is defined according to  FIG. 5  by a flow diagram  40  by the current damage state first being determined. Taking into consideration the manner of use of the generator (from operating data  26 ), a new final profile  29 ,  31  is generated. For describing the final profile  29 ,  31 , a master profile  28 ,  30  is used which is distorted with specific distortion parameters  27 . A plurality of master profiles  28 ,  30  can be given from which a profile which is specific for this rotor is selected. An NC-program, which was previously manually generated, is associated with each master profile. The determined distortion parameters  27  are used in order to also adapt the NC-program in an NC-control system  32 . Re-programming is therefore dispensed with. The necessary coordinate transformations are converted either offline in a postprocessor or online directly in the machine control system. The NC-control system  32  then controls a milling machine  25  with the milling body  22  which is introduced through the gaps  38  into the cooling air slot  13  of the gas turbine rotor  10  which is to be machined. A rotary drive  33 , which can measure the rotational angle at the same time, is connected to the NC-control system  32 . 
         [0028]    The tool  22  is guided through the gaps  38  between the bridges/support elements  36  which cover the slot opening so that these are not affected by the cutting process. The tool  22 , as described above, by a suitable drive unit which is fastened outside the slot, is moved in a programmed controllable manner in the slot in a plurality of planes. By variable equipping of the tool with different cutting bodies or different tool shapes the surface roughness of the machining zones and the surface milled profile can be varied. The drive unit can be an externally seated (above the slot) speed-controllable motor. 
         [0029]    The component surface, which is milled in a defined manner in contour and depth, is the aim of the milling process, wherein the surface depth which is to be milled is predetermined by the crack depth which is determined before or during the milling process, or by a new slot shape configuration. The tool in this case machines a slot surface which is delimited as a result of the movement space of the window between the bridges over the slot. In order to free the entire slot circumference of cracks by milling by metal cutting, a stepwise repositioning of the construction of rotor and tool is carried out until the slot surfaces which are freed of cracks or are to be newly contoured are covered. 
       LIST OF DESIGNATIONS 
       [0000]    
       
           10  Gas turbine rotor 
           11  Compressor section 
           12  Turbine section 
           13  Cooling air slot 
           14  Cooling air hole 
           15  Heat accumulation segment slot 
           16  Slot base 
           17  Crack 
           18  Axis (gas turbine rotor) 
           19 ,  19 ′Cooling air slot (machined) 
           20  Constriction 
           21  Transition 
           22  Milling body 
           23  Axis (milling spindle) 
           24  Ellipse 
           25  Milling machine 
           26  Operating data 
           27  Distortion parameter 
           28 ,  30  Master profile 
           29 ,  31  Final profile 
           32  NC-control system 
           33  Rotary drive (with rotational angle measurement) 
           35  Heat accumulation segment carrier 
           36  Bridge 
           37  Rotor blade slot 
           38  Gap 
           40  Flow diagram 
         b 1 , b 2  Width

Technology Category: 4