Turbine, particularly for an exhaust gas turbocharger, and exhaust gas turbocharger
The invention relates to a turbine ( 1 ), in particular of an exhaust gas turbocharger, having a turbine rotor ( 4 ), which is rotatably mounted in a housing ( 2 ), with which at least one radial inlet channel ( 9 ) for a guide apparatus ( 7 ) forming a medium which drives the turbine rotor ( 4 ) is associated, wherein said guide apparatus ( 7 ) has multiple guide vane bearing rings ( 10 ), which radially enclose said turbine rotor ( 4 ) and have guide vanes ( 8 ) which lie in said inlet channel ( 9 ), and a guide vane cover ring ( 12 ), and wherein said inlet channel ( 9 ) is axially delimited by said guide vane bearing ring ( 10 ) and said guide vane cover ring ( 12 ) and said guide apparatus ( 7 ) is mounted in the housing ( 2 ) so it is axially and/or radially movable for material relaxation. Furthermore, the invention relates to an exhaust gas turbocharger, in particular for a motor vehicle.
1. An exhaust gas turbocharger, comprising:
a turbine rotor rotatably mounted in a housing about a rotation axis, which is associated with guide apparatus defining a radial inlet channel, wherein the turbine rotor is driven by a medium in the inlet channel, wherein the guide apparatus comprises a guide vane bearing ring, a plurality of guide vanes radially surrounding the turbine rotor and located in the inlet channel, and a guide vane cover ring, wherein the inlet channel is axially delimited by the guide vane bearing ring and the guide vane cover ring, wherein the guide vane bearing ring and the guide vane cover ring are mounted axially and radially moveably relative to each other and to the housing for material relaxation; and
wherein the guide apparatus is subjected to an axial preload, and wherein a line of flux of the axial preload runs through the guide apparatus substantially parallel to the rotational axis of the turbine rotor.
2. The turbocharger according to claim 1 , wherein the guide vane bearing ring and the guide vane cover ring each lie in an axial depression of the housing.
3. The turbocharger according to claim 2 , wherein the axial depression for the guide vane bearing ring is formed in a bearing housing and the axial depression for the guide vane cover ring is formed in a turbine housing.
4. The turbocharger according to claim 3 , wherein the turbine housing includes an undercut opening axially adjacent to the guide vane cover ring and in fluidic communication with the inlet channel.
5. The turbocharger according to claim 1 , wherein the guide apparatus includes an axial play between at least one of the guide vane bearing ring and the housing, and the guide vane cover ring and the housing.
6. The turbocharger according to claim 1 , wherein the housing includes at least one of a first housing part defining a turbine housing and a second housing part defining a bearing housing.
7. The turbocharger according claim 1 , further comprising at least one axial spring element for providing the axial preload.
8. The turbocharger according to claim 7 , wherein the axial spring element is axially arranged between at least one of the guide vane bearing ring and the housing, and the guide vane cover ring and the housing.
9. The turbocharger according to claim 7 , wherein the axial spring element is at least one of a helical spring, a coil spring, a disc spring, an O-ring and a C-ring.
10. The turbocharger according to claim 1 , further comprising at least one radial spring element for providing a radial preload on the guide apparatus.
11. The turbocharger according to claim 1 , further comprising at least one radial-axial spring element for generating at least one of the axial preload and a radial preload.
12. The turbocharger according to claim 1 , wherein at least one axial spacer is provided between the guide vane bearing ring and the guide vane cover ring.
13. The turbocharger according to claim 12 , wherein the axial spacer is arranged on at least one of the guide vane bearing ring and the guide vane cover ring.
14. The turbocharger according to claim 12 , wherein the axial spacer is structured unitarily with at least one of the guide vane bearing ring and the guide vane cover ring.
15. The turbocharger according claim 12 , wherein at least one axial spring contact region of the guide apparatus substantially lies on the same radius as the axial spacer.
16. The turbocharger according to claim 15 , wherein the axial spring contact region is arranged aligned with the axial spacer.
17. The turbocharger according to claim 15 , wherein at least one axial contact region of the housing for the guide apparatus lies substantially on the same radius as at least one of the axial spacer and the at least one axial spring contact region of the guide apparatus.
18. The turbocharger according to claim 15 , wherein the line of flux of the axial preload deviates by 20% or less from the radius, on which the axial spacer lies, in both directions.
19. The turbocharger according to claim 1 , wherein at least one of the guide apparatus, the guide vane bearing ring and the guide vane cover ring comprise at least one pin connection for at least one of aligning and positioning on the housing.
20. The turbocharger according to claim 19 , wherein the pin connection comprises at least one pin, which is inserted in a pin reception of the guide apparatus and the housing.
21. The turbocharger according to claim 20 , wherein at least one the pin reception is structured as an elongated hole.
22. The turbocharger according to claim 21 , wherein the elongated hole in its longitudinal extension is orientated radially or axially.
23. The turbocharger according to claim 20 , wherein the at least one pin is orientated axially or radially.
24. The turbocharger according to claim 20 , wherein the at least one pin defines an axial spacer provided between the guide vane bearing ring and the guide vane cover ring.
25. An exhaust gas turbocharger, comprising:
at least one compressor operationally connected mechanically to a turbine rotor, wherein the turbine rotor is rotatably mounted in a housing about a rotation axis, which is associated with a guide apparatus forming a radial inlet channel, wherein the guide apparatus includes a guide vane bearing ring, a plurality of guide vanes radially surrounding the turbine rotor and located in the inlet channel and a guide vane cover ring, wherein the inlet channel is axially delimited by the guide vane bearing ring and the guide vane cover ring, and the guide vane bearing ring and the guide vane cover ring are moveably mounted at least one of axially and radially relative to each other and to the housing to facilitate material relaxation;
at least one axial spacer provided between the guide vane bearing ring and the guide vane cover ring; and
wherein the guide apparatus is subjected to an axial preload, and wherein a line of axial preload flux runs through the guide apparatus substantially parallel to the rotational axis of the turbine rotor.
26. A turbine for an exhaust gas turbocharger, comprising:
a housing;
a turbine rotor rotatably mounted in the housing about a rotation axis;
a guide apparatus mounted in the housing and defining a radial inlet channel for a medium to drive the turbine rotor, the guide apparatus including a guide vane bearing ring, a plurality of guide vanes radially surrounding the turbine rotor and disposed in the inlet channel, and a guide vane cover ring, wherein the inlet channel is axially delimited by the guide vane bearing ring and the guide vane cover ring;
wherein the guide vane bearing ring and the guide vane cover ring are mounted axially and radially moveably relative to each other and to the housing for material relaxation; and
wherein the guide apparatus is subjected to an axial preload, and wherein a line of flux of the axial preload runs through the guide apparatus substantially parallel to the rotational axis of the turbine rotor.