Abstract: A method and device for retrofitting a gas turbine engine for improved hot day performance are disclosed. The method can include removing a first selected stator bladerow from the plurality of compressor stages, the first selected stator bladerow having a first inlet swirl angle and including a first plurality of fixed stator vanes. Each stator vane of the first plurality of fixed stator vanes can have a first stator vane angle. The method can also include providing a first improved stator bladerow to replace the first selected stator bladerow. The first improved stator bladerow can have a second plurality of fixed stator vanes, each having a second stator vane angle smaller than the first stator vane angle. The method can also include replacing the first selected stator bladerow with the first improved stator bladerow to produce an increased pressure ratio and flow rate compared to the first selected stator bladerow.

Abstract: A method and device for retrofitting a gas turbine engine for improved hot day performance are disclosed. The method can include removing a first selected stator bladerow from the plurality of compressor stages, the first selected stator bladerow having a first inlet swirl angle and including a first plurality of fixed stator vanes. Each stator vane of the first plurality of fixed stator vanes can have a first stator vane angle. The method can also include providing a first improved stator bladerow to replace the first selected stator bladerow. The first improved stator bladerow can have a second plurality of fixed stator vanes, each having a second stator vane angle smaller than the first stator vane angle. The method can also include replacing the first selected stator bladerow with the first improved stator bladerow to produce an increased pressure ratio and flow rate compared to the first selected stator bladerow.

Abstract: A stator assembly for a turbine engine is disclosed. The stator assembly has a stator support ring, a plurality of stator vanes protruding radially inwardly from the stator support ring, and at least one bleed port disposed on the stator support ring between at least two adjacent stator vanes of the plurality of stator vanes. The at least one bleed port defines an oblong profile having a first end terminating near a leading edge of a first stator vane of the at least two adjacent stator vanes, and a second end, substantially opposed from the first end, terminating near a trailing edge of a second stator vane of the at least two adjacent stator vanes. The profile may be concave toward a suction sidewall of the second stator vane of the at least two adjacent stator vanes.

Abstract: A stator assembly for a turbine engine is disclosed. The stator assembly has a stator support ring, a plurality of stator vanes protruding radially inwardly from the stator support ring, and at least one bleed port disposed on the stator support ring between at least two adjacent stator vanes of the plurality of stator vanes. The at least one bleed port defines an oblong profile having a first end terminating near a leading edge of a first stator vane of the at least two adjacent stator vanes, and a second end, substantially opposed from the first end, terminating near a trailing edge of a second stator vane of the at least two adjacent stator vanes. The profile may be concave toward a suction sidewall of the second stator vane of the at least two adjacent stator vanes.