Abstract: A stator vane for a compressor is described. The stator vane has an airfoil root, an airfoil tip, a leading edge, a trailing edge, an inner span region, a midspan region and an outer span region, wherein the stator vane has a normalized camber profile that increases in the outer span region in a spanwise direction towards the tip and is more than 1.4 in the outer span region.

Abstract: A rotor blade having an airfoil for a compressor is described. The airfoil has an airfoil root, an airfoil tip located at a spanwise distance from the airfoil root, a leading edge extending from the airfoil root to the airfoil tip, an inner span region (“S1”) between the airfoil root and a first height location on the airfoil leading edge, a midspan region (“S2”) between the first height location and a second height location on the airfoil leading edge located radially outward from the first height location; an outer span region (“S3”) between the second height location and the airfoil tip, wherein the airfoil has a normalized camber profile such that the normalized camber increases in the outer span region in a spanwise direction towards the tip and is more than 2.2 in the outer span region.

Abstract: An airfoil for a compressor is described. The airfoil has a root, an airfoil tip, a leading edge, a trailing edge, airfoil pressure and suction sides extending between the leading edge and the trailing edge. The airfoil has an inner span region and an outer span region and the trailing edge has a dihedral profile such that the trailing edge dihedral angle decreases in at least a portion of the inner span region and the outer span region.

Abstract: A method of operating a compressor having a row of blades for preventing a compressor stall is disclosed, the method comprising the steps of mounting a plasma generator in a casing or a shroud radially outwardly and apart from the blade tips wherein the plasma generator comprises a radially inner electrode and a radially outer electrode separated by a dielectric material; and supplying an AC potential to the radially inner electrode and the radially outer electrode.

Abstract: An airfoil for a compressor is described. The airfoil has a root, an airfoil tip, a leading edge, a trailing edge, airfoil pressure and suction sides extending between the leading edge and the trailing edge. The airfoil has an inner span region and an outer span region and the trailing edge has a dihedral profile such that the trailing edge dihedral angle decreases in at least a portion of the inner span region and the outer span region.

Abstract: A rotor blade having an airfoil for a compressor is described. The airfoil has an airfoil root, an airfoil tip located at a spanwise distance from the airfoil root, a leading edge extending from the airfoil root to the airfoil tip, an inner span region (“S1”) between the airfoil root and a first height location on the airfoil leading edge, a midspan region (“S2”) between the first height location and a second height location on the airfoil leading edge located radially outward from the first height location; an outer span region (“S3”) between the second height location and the airfoil tip, wherein the airfoil has a normalized camber profile such that the normalized camber increases in the outer span region in a spanwise direction towards the tip and is more than 2.2 in the outer span region.

Abstract: A stator vane for a compressor is described. The stator vane has an airfoil root, an airfoil tip, a leading edge, a trailing edge, an inner span region, a midspan region and an outer span region, wherein the stator vane has a normalized camber profile that increases in the outer span region in a spanwise direction towards the tip and is more than 1.4 in the outer span region.

Abstract: A variable stator vane airfoil is mounted on a button centered about a rotational axis and includes circular leading and trailing edges circumscribed about the rotational axis at a button radius. Contoured pressure and suction sides extend from the circular leading edge to the circular trailing edge and are recessed inwardly from a perimeter circumscribed about the rotational axis at the button radius. One of upstream and downstream pressure side portions of the contoured pressure side is straight and another of the upstream and downstream pressure side portions is convexly curved. One of the upstream and downstream suction side portions is straight and another of the upstream and downstream suction side portions is convexly curved. One of the upstream pressure side portion and upstream suction side portion is straight and another of the upstream pressure side portion and upstream suction side portion is convexly curved.

Abstract: A plasma leakage flow control system for a compressor is disclosed, comprising a circumferential row of compressor blades, an annular casing surrounding the tips of the blades, located radially apart from the tips of the blades and at least one annular plasma generator located on the annular casing. The annular plasma generator comprises an inner electrode and an outer electrode separated by a dielectric material. A gas turbine engine having a plasma leakage flow control system further comprises an engine control system which controls the operation of the annular plasma generator such that the blade tip leakage flow can be changed.

Abstract: A method of operating a compressor having a row of blades for preventing a compressor stall is disclosed, the method comprising the steps of mounting a plasma generator in a casing or a shroud radially outwardly and apart from the blade tips wherein the plasma generator comprises a radially inner electrode and a radially outer electrode separated by a dielectric material; and supplying an AC potential to the radially inner electrode and the radially outer electrode.

Abstract: A variable stator vane airfoil is mounted on a button centered about a rotational axis and includes circular leading and trailing edges circumscribed about the rotational axis at a button radius. Contoured pressure and suction sides extend from the circular leading edge to the circular trailing edge and are recessed inwardly from a perimeter circumscribed about the rotational axis at the button radius. One of upstream and downstream pressure side portions of the contoured pressure side is straight and another of the upstream and downstream pressure side portions is curved. One of the upstream and downstream suction side portions is straight and another of the upstream and downstream suction side portions is curved. One of the upstream pressure side portion and upstream suction side portion is straight and another of the upstream pressure side portion and upstream suction side portion is curved.

Abstract: A compression system is disclosed, comprising a first compressor having a first flowpath, a second compressor having a second flowpath located axially aft from the first compressor, and a transition duct capable of flowing an airfow from the first compressor to the second compressor, the transition duct having at least one plasma actuator mounted in the transition duct.

Abstract: A booster system is disclosed, comprising a first rotor stage having a plurality of first rotor blades spaced circumferentially around a rotor hub with a longitudinal axis and having a first pitch-line radius extending from the longitudinal axis, a last rotor stage located axially aft from the first rotor stage, the last rotor stage comprising a plurality of last rotor blades spaced circumferentially around the longitudinal axis and having a second pitch-line radius extending from the longitudinal axis, and a gooseneck duct located axially aft from the last rotor stage and capable of receiving an airflow, the gooseneck duct comprising an inlet end and an exit end located at a distance axially aft from the inlet end and having at least one plasma actuator mounted in the gooseneck duct.

Abstract: A gas turbine engine is disclosed, comprising a compressor having a circumferential row of blades, a casing surrounding the tips of the blades, located radially apart from the tips of the blades and at least one plasma generator located on the casing. The plasma generator comprises a first electrode and a second electrode separated by a dielectric material. The gas turbine engine further comprises an engine control system which controls the operation of the plasma generator such that the stable operating range of the compressor is increased.