Turbocharger

Abstract

The invention relates to a turbocharger ( 1 ) with variable turbine geometry (VTG), comprising a multiplicity of guide blades ( 7 ). Each guide blade ( 7 ) has a blade lever ( 19, 19 ′), wherein the center plane (Em 2 ) of an intermediate region ( 24; 24 ′) of the blade lever ( 19, 19 ′) is arranged so as to be offset axially along a blade shaft longitudinal axis (L) at a distance (a) from the center plane (Em 1 ) of a first end region ( 20; 20 ′) of the blade lever ( 19, 19 ′) and of a second end region ( 23; 23 ′) of the blade lever ( 19, 19 ′), and wherein a recess ( 26; 26 ′) is arranged adjacent to the intermediate region ( 24; 24 ′) between the first end region ( 20; 20 ′) and the second end region ( 23; 23 ′).

1 . A turbocharger ( 1 ) with variable turbine geometry (VTG)
 having a turbine housing ( 2 ) with a feed channel ( 9 ) for exhaust gases;   having a turbine rotor ( 4 ) which is mounted rotatably in the turbine housing ( 2 );   having a guide cascade ( 18 ) with variable turbine geometry   which surrounds the turbine rotor ( 4 ) radially to the outside,   which has a blade bearing ring ( 6 ),   which has a plurality of guide blades ( 7 ) which have in each case one blade shaft ( 8 ) which is mounted in the blade bearing ring ( 6 ) and has a blade shaft longitudinal axis (L),   which has an adjusting ring ( 5 ;  5 ′) which is operatively connected to the guide blades ( 7 ); and   which has one blade lever ( 19 ;  19 ′) per guide blade ( 7 ),
 having a receiving recess ( 21 ;  21 ′) which is arranged in a first end region ( 20 ) for one shaft end of the blade shaft ( 8 ) which has a longitudinal axis (L), 
 having a lever head ( 22 ,  22 ′) at a second end region ( 23 ;  23 ′) which has the same center plane (E M1 ) as the first end region ( 20 ;  20 ′), and 
 having an intermediate region ( 24 ;  24 ′), on which a supporting face ( 25 ) is arranged for radial mounting of the adjusting ring ( 5 ;  5 ′), 
 wherein the center plane (E M2 ) of the intermediate region ( 24 ;  24 ′) is arranged axially offset along the blade shaft longitudinal axis (L) by a spacing (a) with respect to the center plane (E M1 ) of the first end region ( 20 ;  20 ′) and the second end region ( 23 ;  23 ′), and 
 wherein in that a recess ( 26 ;  26 ′) is arranged adjacent to the intermediate region ( 24 ;  24 ′) between the first end region ( 20 ;  20 ′) and the second end region ( 23 ;  23 ′). 
   
     
     
         2 . The turbocharger ( 1 ) with variable turbine geometry (VTG) as claimed in  claim 1 , wherein the intermediate region ( 24 ;  24 ′) is of arcuate configuration. 
     
     
         3 . The turbocharger ( 1 ) with variable turbine geometry (VTG) as claimed in  claim 1 , wherein a bearing part ( 30 ) having a bearing face ( 31 ) which interacts with the supporting face ( 25 ) is arranged below a receiving recess ( 27 ;  27 ′) of the adjusting ring ( 5 ;  5 ′). 
     
     
         4 . The turbocharger ( 1 ) with variable turbine geometry (VTG) as claimed in  claim 3 , wherein the supporting face ( 25 ) is arranged within the receiving recess ( 27 ;  27 ′). 
     
     
         5 . The turbocharger ( 1 ) with variable turbine geometry (VTG) as claimed in  claim 3 , wherein the receiving recess ( 27 ;  27 ′) has side wall faces ( 36 ;  36 ′ and  37 ;  37 ′) as a delimitation for the rolling movement of the intermediate region ( 24 ;  24 ′) in the circumferential direction (U) of the adjusting ring ( 5 ;  5 ′). 
     
     
         6 . The turbocharger ( 1 ) with variable turbine geometry (VTG) as claimed in  claim 3 , wherein exclusively an adjusting ring inner face ( 35 ) is provided as radial support of the intermediate region ( 24 ;  24 ′). 
     
     
         7 . The turbocharger ( 1 ) with variable turbine geometry (VTG) as claimed in  claim 6 , wherein the adjusting ring ( 5 ;  5 ′) has elevations ( 34 ), the radial width (B E ) of which is smaller than the radial width (B V ) of the adjusting ring ( 5 ). 
     
     
         8 . A blade lever ( 19 ) for a turbocharger ( 1 ) with variable turbine geometry (VTG)
 having a receiving recess ( 21 ;  21 ′) which is arranged in a first end region ( 20 ;  20 ′) for one shaft end of the blade shaft ( 8 ) which has a longitudinal axis (L),   having a lever head ( 22 ;  22 ′) at a second end region ( 23 ;  23 ′) which has the same center plane (E M1 ) as the first end region ( 20 ;  20 ′), and   having an intermediate region ( 24 ;  24 ′), on which a supporting face ( 25 ) is arranged for radial mounting of the adjusting ring ( 5 ;  5 ′),   wherein the center plane (E M2 ) of the intermediate region ( 24 ;  24 ′) is arranged axially offset along the blade shaft longitudinal axis (L) by a spacing (a) with respect to the center plane (E M1 ) of the first end region ( 20 ;  20 ′) and the second end region ( 23 ;  23 ′), and   in that a recess ( 26 ;  26 ′) is arranged adjacent to the intermediate region ( 24 ;  24 ′) between the first end region ( 20 ;  20 ′) and the second end region ( 23 ;  23 ′).   
     
     
         9 . A blade lever ( 19 ;  19 ′) for a turbocharger ( 1 ) with variable turbine geometry (VTG), which blade lever ( 19 ;  19 ′) is attached to a guide blade ( 7 ) and includes:
 a receiving recess ( 21 ;  21 ′) which is arranged in a first end region ( 20 ) for one shaft end of the blade shaft ( 8 ) which has a longitudinal axis (L), 
 a lever head ( 22 ,  22 ′) at a second end region ( 23 ;  23 ′) which has the same center plane (E M1 ) as the first end region ( 20 ;  20 ′), and 
 an intermediate region ( 24 ;  24 ′), on which a supporting face ( 25 ) is arranged for radial mounting of the adjusting ring ( 5 ;  5 ′), 
 wherein the center plane (E M2 ) of the intermediate region ( 24 ;  24 ′) is arranged axially offset along the blade shaft longitudinal axis (L) by a spacing (a) with respect to the center plane (E M1 ) of the first end region ( 20 ;  20 ′) and the second end region ( 23 ;  23 ′), 
 wherein recess ( 26 ;  26 ′) is arranged adjacent to the intermediate region ( 24 ;  24 ′) between the first end region ( 20 ;  20 ′) and the second end region ( 23 ;  23 ′) and 
 wherein the intermediate region ( 24 ;  24 ′) is of arcuate configuration. 
 
     
     
         10 . An adjusting ring for a turbocharger ( 1 ) with variable turbine geometry (VTG) according to  claim 3 .