US Patent 10392961 Nozzle blade design for a variable nozzle turbine

Systems are provided for a nozzle blade for a variable nozzle turbine of a turbocharged engine. In one example, a nozzle blade for a turbine nozzle of a variable geometry turbine may include: a cambered outer surface that curves from an inlet end to an outlet end of the nozzle blade, relative to a chord of the nozzle blade, the chord having a chord length defined from the inlet end to the outlet end, the nozzle blade having an aspect ratio in a range of 1.54 to 2.95, a thickness that is greatest in a range of 47 to 61% of the chord length, and a camber line angle change ratio in a range of 0.94 to 1.16 from the inlet end to the outlet end of the nozzle blade.