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A compression stage having a plurality of stator vanes and rotor blades coaxial with a longitudinal centerline axis, each stator vane having an exit swirl angle distribution such that the exit swirl angle has a maximum value at an intermediate radius location and each rotor blade having a blade lead

A compression stage having a plurality of stator vanes and rotor blades coaxial with a longitudinal centerline axis, each stator vane having an exit swirl angle distribution such that the exit swirl angle has a maximum value at an intermediate radius location and each rotor blade having a blade leading edge adapted to receive the flow from the stator vanes with the exit swirl angle distribution profile.

대표청구항 ▼

1. 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 circumferenti

1. 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 a 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 aft sweep at the tip for any vane located axially forward from it;a plurality of rotor stages, each rotor stage 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 shape adapted to receive the flow from a stator stage or an inlet guide vane stage located axially forward from it. 2. A booster according to claim 1 wherein at least one stator stage has stator vanes having leading edge forward sweep at the root and leading edge aft sweep at the tip. 3. A booster according to claim 1 wherein the leading edge aft sweep for the vanes in at least one stator stage increases between the first radius and the tip. 4. A booster according to claim 1 wherein all of the vanes have a leading edge forward sweep between the root and an outer radius location on the vane. 5. 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 aft sweep at the tip for any vane located axially forward from it; anda 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. 6. A booster according to claim 5 wherein the first rate of change of sweep angle with respect to span height is less than the second rate of change of sweep angle with respect to span height. 7. A compression stage according to claim 5 wherein the first rate of change of sweep angle with respect to span height is substantially equal to the second rate of change of sweep angle with respect to span height.