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Turbocharger turbine assembly

  • US 9,732,633 B2
  • Filed: 03/09/2015
  • Issued: 08/15/2017
  • Est. Priority Date: 03/09/2015
  • Status: Active Grant
First Claim
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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.

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