Changeable outlet flow section turbine jet nozzle ring

Abstract

The present invention belongs to the field of internal combustion engine turbocharging technology, in particular, it relates to a turbine nozzle ring used in turbocharger. Said invention provides the working principle of said turbine nozzle ring, and also provides the concrete structure of said turbine nozzle ring and its manufacture method.

Description

Technical field [0001] The invention relates to a turbine nozzle ring in a turbocharger in the technical field of turbocharging of an internal combustion engine. Background technique [0002] The use of variable nozzle turbo regulation technology for turbochargers is an effective measure developed in the past two decades to improve the torque reserve and transient response of internal combustion engines, and to reduce fuel consumption and harmful emissions. By changing the flow cross-sectional area of ​​the outlet of the turbine nozzle ring vane, a good match between the turbocharger and the internal combustion engine can be achieved in the full range of operating conditions. [0003] The existing technology of variable nozzle turbine adjustment, without exception, adopts the technical solution of adjustable nozzle. Adjustable nozzles use mechanical means to rotate the nozzle blades (change the installation angle of the nozzle blades in the turbine nozzle ring cascade) to change ...

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Problems solved by technology

Disadvantages are: complex structure, high manufacturing precision, high price, large volume; working at high temperature for a long time, it is difficult to ensure the reliability of the structure and operating system, so it is only used in turbochargers of diesel engines with relatively low gas temperature So far, it has not been widely used in turbochargers for gasoline engines with higher gas temperature; the high-temperature gas leakage in the gap between the nozzle blades and the inner wall of the turbine volute for the rotating blades makes the efficiency of the turbine stage Decrease; the adjustment of the nozzle blade angle change will cause the impeller inlet airflow angle of attack and the change of the turbine stage reaction degree. If the adjustment range is too large, the efficiency of the turbine stage will be greatly reduced.

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