Method for producing a rotor of a charging apparatus
원문보기
IPC분류정보
국가/구분
United States(US) Patent
등록
국제특허분류(IPC7판)
F01D-011/02
B23P-013/02
B23P-015/00
F01D-005/02
F01D-025/16
F01D-025/28
F02B-037/00
F01D-005/06
출원번호
US-0817898
(2015-08-04)
등록번호
US-9970309
(2018-05-15)
우선권정보
DE-10 2014 215 441 (2014-08-05)
발명자
/ 주소
Klusácek, Michal
출원인 / 주소
Bosch Mahle Turbo Systems GmbH & Co. KG
대리인 / 주소
Fishman Stewart PLLC
인용정보
피인용 횟수 :
0인용 특허 :
11
초록▼
A method of producing a rotor of a charging apparatus may include the steps of providing at least one compressor wheel and a turbine wheel. The compressor wheel and the turbine wheel may each include a bearing section having a radial bearing surface at a longitudinal end for mounting a bearing housi
A method of producing a rotor of a charging apparatus may include the steps of providing at least one compressor wheel and a turbine wheel. The compressor wheel and the turbine wheel may each include a bearing section having a radial bearing surface at a longitudinal end for mounting a bearing housing. At least one of the radial bearing surfaces may include a radial oversizing corresponding to a rotationally asymmetric geometry between at least the bearing section of the compressor wheel and the bearing section of the turbine wheel. The method may include the step of assembling the compressor wheel, the turbine wheel and each bearing section together to form a unitary structure, and machining the at least one of the radial bearing surfaces to reduce the respective radial oversizing until each of the radial bearing surfaces are rotationally symmetrical with respect to each other.
대표청구항▼
1. A method for producing a rotor of a charging apparatus, comprising the steps of: providing at least one compressor wheel and a turbine wheel, wherein the compressor wheel and the turbine wheel each include a bearing section having a radial bearing surface at a longitudinal end for mounting a bear
1. A method for producing a rotor of a charging apparatus, comprising the steps of: providing at least one compressor wheel and a turbine wheel, wherein the compressor wheel and the turbine wheel each include a bearing section having a radial bearing surface at a longitudinal end for mounting a bearing housing wherein at least one of the radial bearing surfaces includes a radial oversizing corresponding to a rotationally asymmetric geometry between at least the bearing section of the compressor wheel and the bearing section of the turbine wheel,assembling the compressor wheel, the turbine wheel and each bearing sections together to form a unitary structure, andmachining the at least one of the radial bearing surfaces to reduce the respective radial oversizing until each of the radial bearing surfaces are rotationally symmetrical with respect to each other. 2. The method according to claim 1, wherein the step of assembling the compressor wheel, the turbine wheel and each bearing section together further includes connecting the turbine wheel to the compressor wheel via a labyrinth seal, and machining each of the bearing sections, the turbine wheel, the labyrinth seal and the compressor wheel until the unitary structure is rotationally symmetrical. 3. The method according to claim 1, wherein the step of assembling the compressor wheel, the turbine wheel and each bearing section together further includes connecting a labyrinth seal to at least one of the compressor wheel and the turbine wheel via at least one of welding, soldering, adhesively bonding or and screwing to one another. 4. The method according to claim 1, wherein each of the bearing sections have an axial end face, and at least one axial end face includes a radial oversizing, and the step of machining the at least one of the radial bearing surfaces further includes machining the at least one axial end face to reduce the respective radial oversizing until each of the radial bearing surfaces are rotationally symmetrical and each of the axial end faces are perpendicular to the respective radial bearing surfaces. 5. The method according to claim 4, further comprising the step of forming an axial air bearing into at least one of the axial end faces via at least one of etching, eroding and machining. 6. The method according to claim 5, wherein the step of forming an axial air bearing into at least one of the axial end faces balances the unitary structure. 7. The method according to claim 1, wherein each radial bearing surface includes an axial end face, and the step of machining at least one of the radial bearing surfaces includes machining each of the radial bearing surfaces and each axial end face in at least one of a lathe and a centreless manner until each of the radial bearing surfaces are rotationally symmetrical and each of the axial end faces are perpendicular to the respective radial bearing surfaces. 8. The method according to claim 1, wherein the step of machining the at least one of the radial bearing surfaces includes turning and grinding until each of the radial bearing surfaces are rotationally symmetrical with respect to each other. 9. The method according to claim 1, wherein the compressor wheel, the turbine wheel and each bearing section have a radial oversizing corresponding to a rotationally asymmetric geometry with respect to each other, and the step of machining further includes at least one of turning and grinding each of the compressor wheel, the turbine wheel and each bearing section to reduce the respective radial oversizing until the unitary structure is rotationally symmetrical. 10. A method for producing a rotor of an exhaust gas turbocharger, comprising the steps of: providing a compressor wheel and a turbine wheel, the compressor wheel having a first bearing section at a first longitudinal end and the turbine wheel having a second bearing section at a second longitudinal end, wherein at least one of the first bearing section and the second bearing section defines a radial oversizing relative to a predefined radial extent less than the radial oversizing;connecting the compressor wheel to the turbine wheel via a labyrinth seal to form a unitary structure having a rotation axis; andmachining the at least one of the first bearing section and the second bearing section to reduce the respective radial oversizing to the respective predefined radial extent and define a first bearing surface associated with the first bearing section that is rotationally symmetrical to a second bearing surface associated with the second bearing section. 11. The method according to claim 10, wherein the step of connecting the compressor wheel to the turbine wheel via a labyrinth seal further includes at least one of welding, soldering, adhering and screwing the labyrinth seal to at least one of the compressor wheel and the turbine wheel. 12. The method according to claim 10, wherein the turbine wheel, the compressor wheel and the labyrinth seal each define a respective radial oversizing relative to a respective predefined radial extent less than the respective radial oversizing; and wherein the step of machining the at least one of the first bearing section and the second bearing section further includes machining each of the turbine wheel, the compressor wheel and the labyrinth seal to reduce the respective radial oversizing to the respective predefined radial extent. 13. The method according to claim 10, wherein the first bearing section has a first axial end face and the second bearing section has a second axial end face, wherein at least one of the first axial end face and the second axial end face includes a radial oversizing; and wherein the step of machining the at least one of the first bearing section and the second bearing section further includes machining the at least one of the first axial end face and the second axial end face to reduce the respective radial oversizing until each of the first radial bearing surface and the second radial bearing surface are rotationally symmetrical to one another and each of the first axial end face and the second axial end face extend perpendicular to the associated first bearing surface and the second bearing surface. 14. The method according to claim 13, further comprising forming an axial air bearing into at least one of the first axial end face and the second axial end face via at least one of etching, eroding and machining. 15. The method according to claim 14, wherein the respective axial air bearing balances the first bearing section with respect to the second bearing section. 16. The method according to claim 10, further comprising forming an axial air bearing into at least one of the first longitudinal end of the first bearing section and the second longitudinal end of the second bearing section, wherein the respective axial air bearing is formed via at least one of etching, eroding and machining. 17. The method according to claim 10, wherein the step of machining the at last one of the first bearing section and the second bearing section includes machining each of the first bearing section and the second bearing section in at least one of a lathe and a centreless manner to reduce the respective radial oversizing to the respective predefined radial extent and define a first bearing surface associated with the first bearing section that is rotationally symmetrical to a second bearing surface associated with the second bearing section.
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