An assembly (860, 1460, 1800, 1900) comprising: an exhaust gas turbine housing that comprises an inner wall (864, 1464) and an outer wall (862, 1462) that define a first exhaust gas channel (867, 1467) and a second exhaust gas channel (869, 1469) to a turbine wheel space wherein the inner wall (864, 1464) comprises an inner wall end (865, 1465) at the turbine wheel space and the outer wall comprises an outer wall end (863, 1463, 1863) at the turbine wheel space; a first adjustable divider vane (882-2, 1482-2, 1882-1,1920) disposed adjacent to the inner wall end (865, 1465); a second adjustable divider vane (882-1, 1482-1, 1882-1, 1920) disposed adjacent to the outer wall end (863, 1463, 1863); a first structure (833-2, 1483-2, 1883-2, 1930) and a second structure (833-1, 1483-1, 1883-1, 1930) each having a vane-like shape that comprises opposing ends (1932, 1934) and opposing side surfaces (1933, 1935), wherein each of said first adjustable divider vane (882-2, 1482-2, 1882-1, 1920) and said second adjustable divider vane (882-1, 1482-1, 1882-1, 1920) is pivotable with respect to the corresponding first structure (833-2, 1483-2, 1883-2, 1930) and second structure (833-1, 1483-1, 1883-1, 1930) respectively, to form a relatively continuous surface with at least one of the opposing side surfaces (1933, 1935) of the corresponding one of said first structure (833-2, 1483-2, 1883-2, 1930) and said second structure (833-1, 1483-1, 1883-1, 1930); and at least one set of adjustable variable geometry nozzle vanes (884, 1484, 1884, 1990) that define nozzle throats that direct flow of exhaust gas from one of the exhaust gas channels (867, 869, 1467, 1469) to the turbine wheel space. an exhaust gas turbine housing that comprises an inner wall (864, 1464) and an outer wall (862, 1462) that define a first exhaust gas channel (867, 1467) and a second exhaust gas channel (869, 1469) to a turbine wheel space wherein the inner wall (864, 1464) comprises an inner wall end (865, 1465) at the turbine wheel space and the outer wall comprises an outer wall end (863, 1463, 1863) at the turbine wheel space; a first adjustable divider vane (882-2, 1482-2, 1882-1,1920) disposed adjacent to the inner wall end (865, 1465); a second adjustable divider vane (882-1, 1482-1, 1882-1, 1920) disposed adjacent to the outer wall end (863, 1463, 1863); a first structure (833-2, 1483-2, 1883-2, 1930) and a second structure (833-1, 1483-1, 1883-1, 1930) each having a vane-like shape that comprises opposing ends (1932, 1934) and opposing side surfaces (1933, 1935), wherein each of said first adjustable divider vane (882-2, 1482-2, 1882-1, 1920) and said second adjustable divider vane (882-1, 1482-1, 1882-1, 1920) is pivotable with respect to the corresponding first structure (833-2, 1483-2, 1883-2, 1930) and second structure (833-1, 1483-1, 1883-1, 1930) respectively, to form a relatively continuous surface with at least one of the opposing side surfaces (1933, 1935) of the corresponding one of said first structure (833-2, 1483-2, 1883-2, 1930) and said second structure (833-1, 1483-1, 1883-1, 1930); and at least one set of adjustable variable geometry nozzle vanes (884, 1484, 1884, 1990) that define nozzle throats that direct flow of exhaust gas from one of the exhaust gas channels (867, 869, 1467, 1469) to the turbine wheel space.