| 摘要 |
<p>In an exhaust gas turbocharger with a radial or axial turbine and an at least partially radial flow turbine nozzle ring (8), a movable slide ring (2) makes possible an infinite adjustment of the turbine inlet cross-section. The movement of the slide ring (2), which slides between nozzle ring (8) and rotor blading (1), occurs by means of an axial displacement. The front edge around which the gas flows is shaped to conform with the flow in order to avoid downstream separations. With radial turbines, the inlet flow angle to the turbine rotor blading remains approximately constant over the whole control range. In consequence, the shock loss at the turbine rotor blading substantially disappears. The infinite adjustment of the turbine inlet cross-section results in an improved part load behavior of the supercharged engine because the air quantity supplied to the engine is matched to the combustion conditions and smokeless operation is obtained over the whole rotational speed range.</p> |
