The high maneuverability combined with stealth requirements imposes very high inlet pressure distortion at the engine inlet. The fan being the first component in a gas turbine engine is subjected to this high inlet distortion which causes severe surge margin loss. Hence there is a need for a fan development with high distortion tolerance and surge margin. The increased surge margin with higher distortion tolerance would make this standard of fan more versatile for integration with higher thrust class engines. This fan also has anti-icing system.