Turbocharger turbine assembly
First Claim
1. A turbocharger comprising:
- a turbine housing including a gas inlet passage;
a turbine wheel that has a plurality of blades and is arranged in the turbine housing;
a bearing housing connected to the turbine housing;
a shaft rotatably supported in the bearing housing and connected to the turbine wheel;
a heat shield;
a nozzle ring disposed around the turbine wheel and including a plurality of vanes with flow channels being defined between the vanes that are in fluid communication with the gas inlet passage and with the turbine wheel; and
a shroud arranged in surrounding relation to at least a portion of the turbine wheel, the shroud being connected to the nozzle ring, the nozzle ring and shroud are connected to the heat shield;
wherein the heat shield is secured to the bearing housing by a plurality of cross key pins, each cross key pin being inserted in a radially extending first passage in the heat shield and a complementary radially extending second passage in the bearing housing, the first passage and second passage being oriented normal to a rotational axis of the turbine wheel and symmetrically arranged in a circular pattern about the rotational axis of the turbine wheel such that the cross key pins force symmetrical thermal expansion of the heat shield, nozzle ring and shroud during operation of the turbocharger; and
wherein the flow channels defined by the vanes are configured to direct gas tangentially and radially inward toward an inner diameter of the turbine wheel and the shroud is configured to define a flow path in communication with the gas inlet passage and the flow channels, the flow path extending in a direction parallel to a rotational axis of the turbine wheel, wherein the shroud includes a first leg that extends in a radial direction of the turbine wheel and a second leg that extends in the direction parallel to the rotational axis of the turbine wheel, and wherein the shroud further includes a first gas seal arranged between the second leg of the shroud and an inside wall of the turbine housing and a second gas seal arranged between the heat shield and the bearing housing.
1 Assignment
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Accused Products
Abstract
A turbocharger including a turbine housing including a gas inlet passage and a turbine wheel arranged in the turbine housing. A bearing housing is connected to the turbine housing. A nozzle ring is disposed around the turbine wheel and a shroud is arranged in surrounding relation to at least a portion of the turbine wheel. The shroud is connected to the nozzle ring and the nozzle ring and shroud are connected to a heat shield. The heat shield is secured to the bearing housing by a plurality of cross key pins, each cross key pin being inserted in a radially extending first passage in the heat shield and a complementary radially extending second passage in the bearing housing. The first passages and second passages are symmetrically arranged in a circular pattern about a rotational axis of the turbine.
197 Citations
7 Claims
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1. A turbocharger comprising:
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a turbine housing including a gas inlet passage; a turbine wheel that has a plurality of blades and is arranged in the turbine housing; a bearing housing connected to the turbine housing; a shaft rotatably supported in the bearing housing and connected to the turbine wheel; a heat shield; a nozzle ring disposed around the turbine wheel and including a plurality of vanes with flow channels being defined between the vanes that are in fluid communication with the gas inlet passage and with the turbine wheel; and a shroud arranged in surrounding relation to at least a portion of the turbine wheel, the shroud being connected to the nozzle ring, the nozzle ring and shroud are connected to the heat shield; wherein the heat shield is secured to the bearing housing by a plurality of cross key pins, each cross key pin being inserted in a radially extending first passage in the heat shield and a complementary radially extending second passage in the bearing housing, the first passage and second passage being oriented normal to a rotational axis of the turbine wheel and symmetrically arranged in a circular pattern about the rotational axis of the turbine wheel such that the cross key pins force symmetrical thermal expansion of the heat shield, nozzle ring and shroud during operation of the turbocharger; and wherein the flow channels defined by the vanes are configured to direct gas tangentially and radially inward toward an inner diameter of the turbine wheel and the shroud is configured to define a flow path in communication with the gas inlet passage and the flow channels, the flow path extending in a direction parallel to a rotational axis of the turbine wheel, wherein the shroud includes a first leg that extends in a radial direction of the turbine wheel and a second leg that extends in the direction parallel to the rotational axis of the turbine wheel, and wherein the shroud further includes a first gas seal arranged between the second leg of the shroud and an inside wall of the turbine housing and a second gas seal arranged between the heat shield and the bearing housing. - View Dependent Claims (2, 3, 4, 5)
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6. A method of providing symmetrical thermal expansion of components of a turbocharger including a turbine housing and a turbine wheel arranged in the turbine housing and connected to a shaft that is rotatably supported in a bearing housing, the method comprising:
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providing a nozzle ring disposed around the turbine wheel and including a plurality of vanes with flow channels being defined between the vanes that are in fluid communication the gas inlet passage and with the turbine wheel; connecting a shroud arranged in surrounding relation to at least a portion of the turbine wheel to the nozzle ring; connecting the shroud and the nozzle ring to a heat shield; connecting the heat shield to the bearing housing with a plurality of cross key pins, each cross key pin being inserted in a radially extending first passage in the heat shield and a complementary radially extending second passage in the bearing housing, the first passage and first passage being oriented normal to a rotational axis of the turbine wheel and symmetrically arranged in a circular pattern about the rotational axis of the turbine wheel such that the cross key pins force symmetrical thermal expansion of the heat shield, nozzle ring and shroud during operation of the turbocharger; and wherein the connecting a shroud arranged in surrounding relation includes connecting a shroud that is integrally formed with the nozzle ring such that the plurality of vanes extend away from the shroud, wherein the providing a nozzle ring includes providing a nozzle ring where the flow channels defined by the vanes are configured to direct gas tangentially and radially inward toward an inner diameter of the turbine wheel, and the shroud is configured to define a flow path in communication with the gas inlet passage and the flow channels, the flow path extending in a direction parallel to a rotational axis of the turbine wheel, and wherein the connecting a shroud arranged in surrounding relation includes connecting a shroud where the shroud includes a first leg that extends in a radial direction of the turbine wheel and a second leg that extends in the direction parallel to the rotational axis of the turbine wheel and further including providing a first gas seal arranged between the second leg of the shroud and an inside wall of the turbine housing and providing a second gas seal arranged between the heat shield and the bearing housing. - View Dependent Claims (7)
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Specification