Controlled convergence compressor flowpath for a gas turbine engine

A gas turbine engine comprising:

• a compressor formed from a rotor assembly and a stator assembly;
• wherein the compressor comprises an inner compressor surface and an outer compressor surface;
• wherein the rotor assembly is formed from a plurality of radially outward extending compressor blades from the inner compressor surface 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 from the outer compressor surface 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 the inner and outer compressor surfaces form a compressor flowpath;
• wherein the compressor flowpath converges moving downstream;
• wherein a rate of the convergence of the compressor flowpath increases at the inner and outer surfaces adjacent to roots of the blades and vanes;
• and
• wherein the rate of the convergence of the compressor flowpath reduces at the inner and outer surfaces adjacent to tips of the blades and vanes.