IPC분류정보
국가/구분 |
United States(US) Patent
등록
|
국제특허분류(IPC7판) |
|
출원번호 |
US-0187477
(2014-02-24)
|
등록번호 |
US-9664060
(2017-05-30)
|
우선권정보 |
JP-2013-040728 (2013-03-01); JP-2013-040744 (2013-03-01) |
발명자
/ 주소 |
- Inoue, Tomohiro
- Asakawa, Takao
- Segawa, Kenichi
|
출원인 / 주소 |
|
대리인 / 주소 |
Oblon, McClelland, Maier & Neustadt, L.L.P.
|
인용정보 |
피인용 횟수 :
0 인용 특허 :
7 |
초록
▼
A variable geometry system turbocharger includes a variable nozzle unit, which is disposed in a turbine housing by being sandwiched between the turbine housing and a bearing housing, and which adjusts a passage area for the exhaust gas to be supplied to a turbine impeller. The bearing housing includ
A variable geometry system turbocharger includes a variable nozzle unit, which is disposed in a turbine housing by being sandwiched between the turbine housing and a bearing housing, and which adjusts a passage area for the exhaust gas to be supplied to a turbine impeller. The bearing housing includes a container recessed portion which contains a link mechanism of the variable nozzle unit.
대표청구항
▼
1. A variable geometry system turbocharger configured to supercharge air to be supplied to an engine by using energy of an exhaust gas from the engine, comprising: a variable nozzle unit disposed in a turbine housing by being sandwiched between the turbine housing and a bearing housing, and configur
1. A variable geometry system turbocharger configured to supercharge air to be supplied to an engine by using energy of an exhaust gas from the engine, comprising: a variable nozzle unit disposed in a turbine housing by being sandwiched between the turbine housing and a bearing housing, and configured to adjust a passage area for the exhaust gas to be supplied to a turbine impeller, andan annular container recessed portion formed in the bearing housing to contain a link mechanism, whereinthe variable nozzle unit includes: a first base ring disposed between a turbine scroll passage and the turbine impeller in the turbine housing, and concentrically with the turbine impeller;a second base ring provided at a position away from and opposed to the first base ring in an axial direction of the turbine impeller, and integrally with the first base ring;a plurality of variable nozzles disposed between facing surfaces of the first base ring and the second base ring, each variable nozzle being rotatable in forward and reverse directions about a pivot parallel to a pivot of the turbine impeller;the link mechanism disposed on an opposite surface side of the first base ring from the facing surface thereof, the link mechanism including link members linking with the corresponding variable nozzles and a drive ring engaged with the link members to cause the plurality of variable nozzles to synchronously rotate in opening and closing directions via the link members;a support member provided integrally on the opposite surface of the first base ring from the facing surface thereof, the support member including an inner edge portion integrally joined to the opposite surface of the first base ring from the facing surface thereof, and an outer edge portion sandwiched by the turbine housing and the bearing housing; anda connecting passage formed on an inner side of the support member and configured to make the turbine scroll passage and the container recessed portion of the bearing housing communicate with each other. 2. The variable geometry system turbocharger according to claim 1, further comprising a plurality of joining pieces formed integrally on an inner peripheral surface of the support member in such a manner as to protrude radially inward at intervals in a circumferential direction of the support member, the joining pieces integrally joined to the opposite surface of the first base ring from the facing surface thereof. 3. The variable geometry system turbocharger according to claim 1, further comprising an annular protection wall formed radially outside the first base ring inside the turbine housing, and configured to protect the support member against heat from the exhaust gas in the turbine scroll passage. 4. The variable geometry system turbocharger according to claim 3, wherein the protection wall includes a side surface contacting to the support member, and the side surface of the protection wall includes an annular recessed step portion formed on an inner edge side thereof. 5. A variable nozzle unit configured to adjust a passage area for an exhaust gas to be supplied to a turbine impeller in a variable geometry system turbocharger, comprising: a first base ring disposed inside a turbine housing in the variable geometry system turbocharger and concentrically with the turbine impeller;a second base ring provided at a position away from and opposed to the first base ring in an axial direction of the turbine impeller, and integrated with the first base ring by using a plurality of connecting pins arranged in a circumferential direction of the base rings;a plurality of variable nozzles disposed between facing surfaces of the first base ring and the second base ring, each variable nozzle being rotatable in forward and reverse directions about a pivot parallel to a pivot of the turbine impeller;a link mechanism disposed in a link chamber formed on an opposite surface side of the first base ring from the facing surface thereof, and configured to cause the plurality of variable nozzles to rotate synchronously; anda support member having a diameter greater than an outside diameter of the first base ring and being provided integrally on the opposite surface of the first base ring from the facing surface thereof, the support member including an inner edge portion integrally joined to the opposite surface of the first base ring from the facing surface thereof with one end portions of the plurality of connecting pins connected thereto,a plurality of joining pieces formed integrally on an inner peripheral surface of the support member in such a manner as to protrude radially inward at intervals in a circumferential direction of the support member, the joining pieces integrally joined to the opposite surface of the first base ring from the facing surface thereof, andan outer edge portion attached to a bearing housing of the variable geometry system turbocharger. 6. The variable nozzle unit according to claim 5, further comprising a recessed step portion formed on an outer edge side of the opposite surface of the first base ring from the facing surface thereof. 7. The variable nozzle unit according to claim 5, further comprising a plurality of joining projecting portions formed on the opposite surface of the first base ring from the facing surface thereof at intervals in the circumferential direction of the base rings in such a manner as to protrude toward the one side in the axial direction of the turbine impeller, wherein a top surface of each joining projecting portion is joined to the corresponding joining piece of the support member. 8. The variable nozzle unit according to claim 5, further comprising a connecting passage formed on an inner side of the support member between the joining pieces adjacent in the circumferential direction of the support member, and configured to make a turbine scroll passage of the turbine housing and the link chamber communicate with each other. 9. A variable geometry system turbocharger configured to supercharge air to be supplied to an engine by using energy of an exhaust gas from the engine, comprising: a variable nozzle unit configured to adjust a passage area for an exhaust gas to be supplied to a turbine impeller, the variable nozzle unit including: a first base ring disposed inside a turbine housing in the variable geometry system turbocharger and concentrically with the turbine impeller;a second base ring provided at a position away from and opposed to the first base ring in an axial direction of the turbine impeller, and integrated with the first base ring by using a plurality of connecting pins arranged in a circumferential direction of the base rings;a plurality of variable nozzles disposed between facing surfaces of the first base ring and the second base ring, each variable nozzle being rotatable in forward and reverse directions about a pivot parallel to a pivot of the turbine impeller;a link mechanism disposed in a link chamber formed on an opposite surface side of the first base ring from the facing surface thereof, and configured to cause the plurality of variable nozzles to rotate synchronously; anda support member having a diameter greater than an outside diameter of the first base ring and being provided integrally on the opposite surface of the first base ring from the facing surface thereof, the support member including an inner edge portion integrally joined to the opposite surface of the first base ring from the facing surface thereof with one end portions of the plurality of connecting pins connected thereto,a plurality of joining pieces formed integrally on an inner peripheral surface of the support member in such a manner as to protrude radially inward at intervals in a circumferential direction of the support member, the joining pieces integrally joined to the opposite surface of the first base ring from the facing surface thereof, andan outer edge portion attached to a bearing housing.
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