A variable geometry turbocharger, comprising: a turbine rotor; and a variable nozzle mechanism for adjusting a flow of exhaust gas to the turbine rotor from a scroll flow passage formed on a radially outer side of the turbine rotor, wherein the variable nozzle mechanism includes: at least one nozzle vane (14, 14A) disposed in an exhaust gas flow passage for guiding the exhaust gas to the turbine rotor from the scroll flow passage; a support wall forming a flow passage wall on a first side of the exhaust gas flow passage with respect to an axial direction of the turbine rotor and supporting the nozzle vane (14, 14A) rotatably in a cantilever fashion; and a non-support wall forming a flow passage wall on a second side of the exhaust gas flow passage with respect to the axial direction, characterized in that of an end surface of the nozzle vane (14, 14A) on a side of the non-support wall, an edge portion on a side of a pressure surface includes a non-support-wall side linear portion formed to have a linear shape, wherein an end portion of the nozzle vane (14, 14A) on a side of the non-support wall includes a non-support-wall side rib shaped portion protruding toward a pressure surface of the nozzle vane (14, 14A), wherein the non-support-wall side linear portion is formed on a tip portion of the non-support-wall side rib shaped portion, and wherein, in a view taken in a direction of a rotational axis of the nozzle vane (14, 14A), the non-support-wall side rib shaped portion is disposed so as to protrude so that the non-support-wall side linear portion extends on the tangent of the nozzle vane (14, 14A) to the pressure surface. a turbine rotor; and a variable nozzle mechanism for adjusting a flow of exhaust gas to the turbine rotor from a scroll flow passage formed on a radially outer side of the turbine rotor, wherein the variable nozzle mechanism includes: at least one nozzle vane (14, 14A) disposed in an exhaust gas flow passage for guiding the exhaust gas to the turbine rotor from the scroll flow passage; a support wall forming a flow passage wall on a first side of the exhaust gas flow passage with respect to an axial direction of the turbine rotor and supporting the nozzle vane (14, 14A) rotatably in a cantilever fashion; and a non-support wall forming a flow passage wall on a second side of the exhaust gas flow passage with respect to the axial direction, at least one nozzle vane (14, 14A) disposed in an exhaust gas flow passage for guiding the exhaust gas to the turbine rotor from the scroll flow passage; a support wall forming a flow passage wall on a first side of the exhaust gas flow passage with respect to an axial direction of the turbine rotor and supporting the nozzle vane (14, 14A) rotatably in a cantilever fashion; and a non-support wall forming a flow passage wall on a second side of the exhaust gas flow passage with respect to the axial direction, characterized in that of an end surface of the nozzle vane (14, 14A) on a side of the non-support wall, an edge portion on a side of a pressure surface includes a non-support-wall side linear portion formed to have a linear shape, wherein an end portion of the nozzle vane (14, 14A) on a side of the non-support wall includes a non-support-wall side rib shaped portion protruding toward a pressure surface of the nozzle vane (14, 14A), wherein the non-support-wall side linear portion is formed on a tip portion of the non-support-wall side rib shaped portion, and wherein, in a view taken in a direction of a rotational axis of the nozzle vane (14, 14A), the non-support-wall side rib shaped portion is disposed so as to protrude so that the non-support-wall side linear portion extends on the tangent of the nozzle vane (14, 14A) to the pressure surface.