Unsteady two-dimensional compressible inviscid flow in stationary and moving from a transonic turbine stage is analysed numerically using finite volume method. Discretisation of the computational domain is carried out using multi-block grids with hybrid cells. The fluxes across the cell edges, including those at the stator-rotor interface, are estimated by a flux vector splitting method and stored in a novel edge-based data structure. The unsteady pressure fluctuations on the suction and pressure surfaces of the stator and rotor, and the shock function contours in the stage, are presented. The effects of inlet Mach number and axial gap between stator and rotor blade rows are discussed. The values of time-averaged isentropic Mach number and time-lagged periodicity are reported.