The invention relates to a
turbine nozzle ring in a
turbocharger. Pressurized air flowing out from an outlet manifold bypass of an
air compressor of the
turbocharger per se and / or
compressed air of an external air source (or exhaust
fuel gas flowing out from an outlet manifold bypass of an
exhaust pipe of an internal-
combustion engine) passes through the hollow cavity of a
nozzle blade or a hollow interlayer nearby the inner wall of a bladeless
volute inlet
pipe, and jets and blows a
nozzle blade ring or the interior of a bladeless
volute runner and / or a main
fuel gas flow in a downstream way from a blade profile back (or ventral face) and / or a through-flow slit
cut at the
tail edge part (a jet deflection arc guide plate is connected to the back of the
tail edge slit) or an annular arc through-flow gap at a hollow interlayer outlet nearby the zero-degree section of a bladeless
volute tongue tip and the jet deflection arc guide plate connected thereafter, so that the air flow formed by mixing the gap
jet flow and the main flow generates flow direction deflection at the outlet of the nozzle ring to cause the change of an outlet
airflow angle (namely outlet flowing section area). The
turbine nozzle ring has the advantages of high control strength, simple structure, low cost, safety, reliability, high efficiency, convenience for control and applicability for the
gasoline engine
turbocharger, and the additional air has the functions of additional pressurization and auxiliary energy application.