| 摘要 |
Disclosed is a turbocharger with a dual-blade nozzle system, comprising a turbine housing, a fixed nozzle ring (1), a linearly moving nozzle disk (2), a mid-housing (5), a rack (4), rocker arm rods (3), and a gear (6), wherein airfoil-shaped fixed blades (8) are provided on the front end face of the fixed nozzle ring (1), with blade-type holes (9) provided between the fixed blades (8), and the fixed nozzle ring (1) is sheathed around the outside of the mid-housing (5) and fixed to the mid-housing (5) via screws; the linearly moving nozzle disk (2) is provided on the rear end of the fixed nozzle ring (1), a group of moving blades (7) is provided on the front end face of the linearly moving nozzle disk (2), the moving blades (7) are movably inserted into the blade-type holes (9), the rear end face of the linearly moving nozzle disk (2) is fixedly connected to two rocker arm rods (3), with the rocker arm rods (3) inserted into the mid-housing (5) and engaged with the rack (4) via the gear (6). The provision of an additional blade along a nozzle flow passage in the turbocharger with the dual-blade nozzle system can not only reduce the cross-sectional area of the passage, but also separate the original nozzle into two gas passages to reduce the loss of gas flow due to transverse flow; in addition, the gas flow can flow at an optimum gas flow angle according to the original design, so that the turbine can keep working in the high efficiency region. |
