Method for manufacturing a stator or rotor component

Abstract

Method for manufacturing a stator or rotor component which is intended during operation to conduct a gas flow. A first wall part ( 14, 15 ) is placed with its one edge bearing against the flat side of a second wall part ( 9, 10 ), extending in the radial direction of the component, in such a way that the first wall part extends in the circumferential direction of the component. The edge of the first wall part is then laser-welded to the second wall part from an, in the circumferential direction, opposite side of the second wall part in relation to the first wall part in such a way that the joined-together portions of the wall parts form a T-shaped joint.

1 . A method for manufacturing a stator or rotor component ( 21 ) which is intended during operation to conduct a gas flow, said method comprising: 
 placing a first wall part ( 1 ,  14 ,  15 ,  114 ) with one edge ( 3 ) thereof bearing against the flat side ( 4 ) of a second wall part ( 4 ,  9 ,  109 ) and thereby extending in the intended radial direction of the component in such a way that the first wall part extends in the intended circumferential direction of the component; and    laser-welding the edge of the first wall part to said second wall part from, in the circumferential direction, an opposite side of the second wall part in relation to the first wall part in such a way that the joined-together portions of the wall parts form a T-shaped joint ( 5 ).    
   
   
       2 . The method as recited in  claim 1 , wherein the first wall part ( 1 ,  14 ,  15 ,  114 ) is placed essentially perpendicular to the flat side of the second wall part ( 4 ,  9 ,  109 ).  
   
   
       3 . The method as recited in  claim 1 , wherein the second wall part ( 4 ,  9 ,  109 ) is arranged to extend in the axial direction of the component.  
   
   
       4 . The method as recited in  claim 1 , wherein the first wall part ( 1 ,  14 ,  15 ,  114 ) is arranged to extend in the axial direction of the component.  
   
   
       5 . The method as recited in  claim 1 , wherein the second wall part ( 4 ,  9 ,  109 ), extending in the radial direction, is arranged to limit a gas duct ( 20 ) in the circumferential direction of the component.  
   
   
       6 . The method as recited in  claim 1 , wherein the second wall part ( 4 ,  9 ,  109 ) is arranged such that it has said essentially radial widening for guidance of said gas flow during operation of the component.  
   
   
       7 . The method as recited in  claim 1 , wherein the second wall part ( 4 ,  9 ,  109 ) is arranged such that it has said essentially radial widening for transmitting load during operation of the component.  
   
   
       8 . The method as recited in  claim 1 , wherein the first wall part ( 1 ,  14 ,  15 ,  114 ), extending in the circumferential direction, is arranged to limit a gas duct ( 20 ) in the radial direction.  
   
   
       9 . The method as recited in  claim 1 , wherein the first wall part ( 1 ,  14 ,  15 ,  114 ) has a shape which curves essentially in said circumferential direction.  
   
   
       10 . The method as recited in  claim 1 , wherein the first wall part ( 14 ,  15 ) is placed with a second edge, which is opposite to the first-named edge, bearing against the flat side of a further second wall part ( 10 ,  110 ), which is arranged at a distance in the circumferential direction from the first-named second wall part ( 9 ), and is connected thereto.  
   
   
       11 . The method as recited in  claim 10 , wherein the edge of the first wall part ( 14 ,  15 ,  114 ) is laser-welded to the second wall part ( 10 ,  110 ) from an, in the circumferential direction, opposite side of the second wall part in relation to the first wall part in such a way that the joined-together portions of the wall parts form a T-shaped joint ( 5 ).  
   
   
       12 . The method as recited in  claim 10 , wherein the two wall parts ( 9 ,  10 ,  109 ,  110 ) which are spaced apart in the circumferential direction constitute at least part of two different blades for guidance of a gas flow.  
   
   
       13 . The method as recited in  claim 10 , wherein the two wall parts ( 9 ,  10 ,  109 ,  110 ) which are spaced apart in the circumferential direction constitute at least part of two different stays for transmission of load.  
   
   
       14 . The method as recited in  claim 11 , wherein the two second wall parts ( 9 ,  10 ) are formed by a single, substantially U-shaped element ( 6 ).  
   
   
       15 . The method as recited in  claim 1 , wherein said first and second wall part ( 9 ,  10 ,  14 ,  15 ) are arranged between an inner and outer ring element ( 7 ,  8 ) in the radial direction.  
   
   
       16 . The method as recited in  claim 15 , wherein said second wall part ( 9 ,  10 ) is connected to at least one of the ring elements ( 7 ,  8 ) by laser-welding from an, in the radial direction, opposite side of the ring element in relation to the second wall part in such a way that the joined-together portions form a T-shaped joint ( 5 ).  
   
   
       17 . The method as recited in  claim 14 , wherein said U-shaped element ( 6 ), prior to said laser-welding of the wall parts, is arranged between the inner ring element ( 7 ) and the outer ring element ( 8 ).  
   
   
       18 . The method as recited in  claim 1 , wherein said stator component ( 21 ) has an essentially circular cross-sectional shape and in that a plurality of ducts ( 20 ) for conduction of the gas flow extend in the axial direction between an inner and an outer ring.  
   
   
       19 . The method as recited in  claim 1 , wherein said rotor component ( 23 ) has an essentially circular cross-sectional shape and in that a plurality of ducts ( 20 ) for conduction of the gas flow extend in the axial direction between an inner and an outer ring.  
   
   
       20 . The method as recited in  claim 1 , wherein said stator component ( 21 ) is configured for a gas turbine.  
   
   
       21 . The method as recited in  claim 1 , wherein said rotor component ( 23 ) is configured for a gas turbine.  
   
   
       22 . The method as recited in  claim 1 , wherein said stator component ( 21 ) is intended for a jet engine.  
   
   
       23 . The method as recited in  claim 1 , wherein said rotor component ( 23 ) is intended for a jet engine.