A gas turbine engine, comprising: a compressor formed from a rotor assembly and a stator assembly; wherein the rotor assembly is formed from a plurality of radially outward extending compressor blades aligned into a plurality of circumferentially extending rows and wherein the rotor assembly is rotatable; wherein the stator assembly is formed from a plurality of radially inward extending compressor vanes aligned into a plurality of circumferentially extending rows, wherein the stator assembly is fixed relative to the rotatable rotor assembly and wherein the rows of compressor vanes alternate with the rows of compressor blades moving in a downstream direction; wherein an inner compressor surface defines a circumferential inner boundary surface of the compressor and an outer compressor surface defines a circumferential outer boundary surface of the compressor whereby the inner and outer compressor surfaces (22, 20) form a compressor flowpath; the compressor flowpath converging in the downstream direction; wherein between a leading edge and a trailing edge of a first compressor blade the compressor flowpath rate of convergence increases moving downstream to the trailing edge of the first compressor blade due to an increasing convergence rate of the inner compressor surface proximate a root of the first compressor blade; and characterised in that the compressor flowpath between the trailing edge of the first compressor blade and a leading edge of a first compressor vane immediately downstream from the first compressor blade converges at a reduced rate with respect to a rate of convergence between the leading and trailing edges (44, 46) of the first compressor blade. a compressor formed from a rotor assembly and a stator assembly; wherein the rotor assembly is formed from a plurality of radially outward extending compressor blades aligned into a plurality of circumferentially extending rows and wherein the rotor assembly is rotatable; wherein the stator assembly is formed from a plurality of radially inward extending compressor vanes aligned into a plurality of circumferentially extending rows, wherein the stator assembly is fixed relative to the rotatable rotor assembly and wherein the rows of compressor vanes alternate with the rows of compressor blades moving in a downstream direction; wherein an inner compressor surface defines a circumferential inner boundary surface of the compressor and an outer compressor surface defines a circumferential outer boundary surface of the compressor whereby the inner and outer compressor surfaces (22, 20) form a compressor flowpath; the compressor flowpath converging in the downstream direction; wherein between a leading edge and a trailing edge of a first compressor blade the compressor flowpath rate of convergence increases moving downstream to the trailing edge of the first compressor blade due to an increasing convergence rate of the inner compressor surface proximate a root of the first compressor blade; and characterised in that the compressor flowpath between the trailing edge of the first compressor blade and a leading edge of a first compressor vane immediately downstream from the first compressor blade converges at a reduced rate with respect to a rate of convergence between the leading and trailing edges (44, 46) of the first compressor blade.