Compressor wheel
A compressor wheel for an internal combustion engine may include a plurality of blades which in a circumferential direction of the wheel are spaced from one another. The plurality of blades may respectively include an inflow edge which during operation are subject to an inflow of a compressible fluid substantially axially to the wheel axis. The plurality of blades may include a surface layer of locally distinct materials to adapt to locally distinct loads during operation.
1. A compressor wheel for an internal combustion engine, comprising:
a body rotatable about a rotation axis and a plurality of blades disposed on the body and spaced from one another in a circumferential direction of the rotation axis, the plurality of blades respectively including an inflow edge which during operation are subjected to an inflow of a compressible fluid substantially axially to the rotation axis, wherein the plurality of blades respectively include a surface of locally distinct materials resistant to locally distinct loads during operation; and
wherein the surface of at least one blade of the plurality of blades includes an armour material disposed locally along the inflow edge and an anti-corrosive coating disposed in a region of the surface spaced away from the inflow edge.
2. The compressor wheel according to claim 1 , wherein the anti-corrosive coating includes an anodised layer.
3. The compressor wheel according to claim 1 , wherein the armour material and the anti-corrosive coating are disposed adjacently in an axial direction of the rotation axis.
4. A compressor wheel according to claim 3 , wherein the armour material in the axial direction of the compressor wheel extends over a length of approximately 10 to 40% of an axial blade length.
5. The compressor wheel according to claim 1 , wherein the armour material includes a plasma electrolytic oxidation (PEO) layer.
6. The compressor wheel according to claim 1 , wherein the plurality of blades includes a main blade and an auxiliary blade alternating in the circumferential direction, wherein the inflow edges of the main blades are arranged in a plane positioned upstream relative to a plane of the inflow edges of the auxiliary blades with respect to a flow direction of the fluid to be compressed.
7. The compressor wheel according to claim 1 , wherein the armour material is substantially provided only directly on the inflow edge.
8. The compressor wheel according to claim 1 , wherein the surface of the at least one blade has the armour material only on the inflow edge, and wherein the surface of the at least one blade outside of the inflow edge is without the armour material.
9. The compressor wheel according to claim 1 , wherein the plurality of blades includes main blades having inflow edges extending in a radial plane of the compressor wheel.
10. The compressor wheel according to claim 1 , wherein the body is a radial compressor wheel.
11. The compressor wheel according to claim 1 , wherein the body is composed of a material including at least one of aluminium, magnesium and titanium.
12. The compressor wheel according to claim 1 , wherein the at least one blade defines an axial blade length and the armour material extends over 10 to 40% of the axial blade length.
13. The compressor wheel according to claim 1 , wherein the anti-corrosive coating includes at least one of a thermally sprayed layer, a physical vapor deposition layer, and a chemical vapor deposition layer.
14. The compressor wheel according to claim 1 , wherein the armour material includes at least one of a steel alloy, a nickel-based alloy, a cobalt alloy and a titanium alloy.
15. An exhaust gas turbocharger for an internal combustion engine, comprising:
a compressor wheel including a central axial bore for receiving a rotor shaft;
a plurality of circumferentially spaced blades disposed on the compressor wheel each including an inflow edge, the plurality of blades further including a plurality of main blades alternating in a circumferential direction with a plurality of auxiliary blades, wherein the inflow edge of the main blades are arranged in a plane positioned upstream relative to a plane of the inflow edge of the auxiliary blades with respect to a flow direction; and
wherein at least one main blade has a surface of locally distinct materials, the surface of locally distinct materials including an armour material disposed on the inflow edge and an anti-corrosive coating disposed in a region spaced axially away from the inflow edge with respect to the central axial bore.
16. The exhaust gas turbocharger according to claim 15 , wherein the armour material includes a plasma electrolytic oxidation layer.
17. The exhaust gas turbocharger according to claim 15 , wherein the armour material and the anti-corrosive coating adjoin one another in an axial direction of the central axial bore.
18. The exhaust gas turbocharger according to claim 15 , wherein the anti-corrosive coating is disposed to butt-join the armour material on the inflow edge.
19. The exhaust gas turbocharger according to claim 18 , wherein the armour material is provided only on the inflow edge, and wherein the surface of the at least one main blade outside of the inflow edge is without the armour material.
20. The exhaust gas turbocharger according to claim 15 , wherein the anti-corrosive coating at least partially overlaps the armour material.