Cast turbocharger turbine housing having guide vanes
원문보기
IPC분류정보
국가/구분
United States(US) Patent
등록
국제특허분류(IPC7판)
F01D-009/04
F01D-009/02
F02B-037/24
출원번호
US-0122652
(2015-03-02)
등록번호
US-10240469
(2019-03-26)
국제출원번호
PCT/US2015/018234
(2015-03-02)
국제공개번호
WO2015/134351
(2015-09-11)
발명자
/ 주소
Rylance, Sean
McArdle, Nathan
출원인 / 주소
BorgWarner Inc.
대리인 / 주소
Perkins Coie LLP
인용정보
피인용 횟수 :
0인용 특허 :
1
초록▼
A turbocharger (1) includes a compressor section and a cast turbine section. The turbine section includes a turbine wheel (4), and a turbine housing (11) that defines a gas inlet (13), a gas outlet (10), a volute (9) disposed between the gas inlet (13) and the gas outlet (10). The turbine housing (1
A turbocharger (1) includes a compressor section and a cast turbine section. The turbine section includes a turbine wheel (4), and a turbine housing (11) that defines a gas inlet (13), a gas outlet (10), a volute (9) disposed between the gas inlet (13) and the gas outlet (10). The turbine housing (11) also includes vanes (20) that protrude integrally from, and have a fixed orientation relative to, an inner surface of the turbine housing (11). The turbine wheel (4) is disposed in the turbine housing (11) between the volute (9) and the gas outlet (10), and the vanes (20) are disposed in the turbine housing (11) between the turbine wheel (4) and the volute (9). A method of casting the turbine housing (11) and the vanes (20) together as a single piece is described.
대표청구항▼
1. A turbocharger (1) including a compressor section (3) and a cast turbine section (2), the turbine section (2) comprising a turbine wheel (4), and a turbine housing (11) that defines a gas inlet (13), a gas outlet (10), a volute (9) disposed between the gas inlet (13) and the gas outlet (10), and
1. A turbocharger (1) including a compressor section (3) and a cast turbine section (2), the turbine section (2) comprising a turbine wheel (4), and a turbine housing (11) that defines a gas inlet (13), a gas outlet (10), a volute (9) disposed between the gas inlet (13) and the gas outlet (10), and vanes (20) arranged in a plane that protrude integrally from, and have a fixed orientation relative to, two opposed inner surfaces of the turbine housing (11),wherein the turbine wheel (4) is disposed in the turbine housing (11) between the volute (9) and the gas outlet (10), and the vanes (20) are disposed in the turbine housing (11) between the turbine wheel (4) and the volute (9), and at least one vane of the vanes (20) has a cross-sectional shape that is different than the cross-sectional shape of at least a different one of the vanes (20). 2. The turbocharger (1) according to claim 1, wherein the vanes (20) are configured to redirect a flow of exhaust gas within the turbine housing (11) from a first flow direction to a second flow direction that is at an angle (θ) relative to the first flow direction. 3. The turbocharger (1) according to claim 2, wherein the angle (θ) is the same for each of the vanes (20). 4. The turbocharger (1) according to claim 2, wherein the angle (θ) for at least one vane (20b) of the vanes is different than the angle (θ) for at least a different one of the vanes (20a). 5. The turbocharger (1) according to claim 2, wherein the angle (θ) between the first flow direction and the second flow direction is in a range of 100 degrees and 170 degrees. 6. The turbocharger (1) according to claim 1, wherein each of the remaining vanes (20) has the same cross-sectional shape. 7. The turbocharger (1) according to claim 1, wherein each vane (20) is oriented so as to provide gas flow redirection from a first flow direction that is circumferential relative to the turbine wheel (4) to a second flow direction that is more radially oriented than the first flow direction. 8. The turbocharger (1) according to claim 1, wherein at least one vane (20a) of the vanes provides more exhaust gas redirection than at least a different one of the vanes (20b). 9. The turbocharger (1) according to claim 1, further comprising a bypass passage (19) that extends between the gas inlet (13) and the gas outlet (10) and bypasses the turbine wheel (4), and a wastegate valve (17) disposed in the bypass passage (19). 10. A method of forming a cast, single-piece turbine housing including integral, fixed vanes (20), wherein the method comprises the following steps: making a pattern of the turbine housing (11);dipping the pattern into a slurry of fine refractory material containing a binder;coating the dipped pattern with coarse ceramic particles;allowing the dipped, coated pattern to harden, forming a hardened mold; pouring molten metal into the hardened mold to form the turbine housing (11) including integral, fixed vanes (20); andremoving the turbine housing (11) including integral, fixed vanes (20) from the hardened mold. 11. The method of claim 10, wherein the pattern is formed of foam. 12. The method of claim 10, wherein the pattern provides the turbine housing (11) with a gas inlet (13), a gas outlet (10), and a volute (9) disposed between the gas inlet (13) and the gas outlet (10), and the vanes (20) protrude integrally from an inner surface of the turbine housing (11) at a location that is adjacent to the volute (9).
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이 특허에 인용된 특허 (1)
Nancarrow James H. (Torrance CA), Turbocharger control.
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