Advanced booster system

A compression stage for a gas turbine engine comprising

• a rotor stage having a plurality of rotor blades spaced circumferentially around a rotor hub with a longitudinal centerline axis;
• a stator stage having a plurality of stator vanes spaced in a circumferential direction coaxial with the longitudinal centerline axis:
• each stator vane comprising a compressor airfoil having pressure and suction sides extending between leading and trailing edges, and longitudinally between a root and a tip, the trailing edge having an exit swirl angle distribution profile from the root to the tip such that the exit swirl angle has a maximum value at an intermediate radius location between the first radius location and the tip wherein the intermediate radius location is located at a span height of more than 50% from the root;
• and
• each rotor blade having a blade leading edge having a sweep angle profile such that the sweep angle increases from the blade root to the blade first height location at a first rate of change of sweep angle with respect to span height that is substantially constant wherein the sweep angle changes from a forward sweep to an aft sweep at a location that is between 10 percent and 30 percent of the span.

A booster for a gas turbine engine comprising:

• an inlet guide vane stage having a plurality of inlet guide vanes spaced in a circumferential direction around a longitudinal centerline axis;
• a plurality of stator stages, each stator stage having a plurality of stator vanes spaced in a circumferential direction around the longitudinal centerline axis and each stator vane having pressure and suction sides extending between leading and trailing edges, and longitudinally between a root and a tip, the leading edge for each vane in at least one stator stage having a forward sweep from the root to a first span location and at least one stator stage having vanes having leading edge aft sweep between the first span location and the tip, the leading edge aft sweep at the tip for each stator vane with leading edge aft sweep is less than the leading edge at sweep at the tip for any vane located axially forward from it;
• and
• a plurality of rotor stages, each rotor stage located in the upstream direction from a stator stage and coaxial with the stator stage and having a plurality of rotor blades spaced in a circumferential direction around a rotor hub located coaxially around the longitudinal centerline axis, each rotor blade having a blade leading edge having a sweep angle that increases from the blade root to a blade first height location on the blade leading edge at a first rate of change of sweep angle with respect to the span height that is substantially constant and increases from the blade first height location to the blade tip of the rotor blade at a second rate of change of sweep angle with respect to the span height that is substantially constant wherein the sweep angle changes from a forward sweep to an aft sweep at a location that is between 10 percent and 30 percent of the span.