General Electric Company

Bryan Keith Doloresco

Brent Franklin Beacher

Hsin-Tuan Liu

Gregory T Steinmetz

Kenneth William Krabacher

Robert Proctor

Michael J Epstein

Peter John Wood

Julius John Montgomery

Roger Owen Barbe

Robert Bruce Dickman

Andrew David Kemp

Hai Buu Sam

James Bernar Ogzewalla

A compressor airfoil includes opposite pressure and suction sides joined together at leading and trailing edges and extending in span between a root and tip. The airfoil includes stagger increasing above the root and decreasing above a midspan pitch section thereof.

Counterstagger compressor airfoil

A gas turbine engine includes a compressor including a casing and a stator assembly. The casing extends around the stator assembly, the stator assembly including a plurality of stator vanes, and a plurality of bleed scoops. Adjacent stator vanes define a static high-pressure region, the bleed scoops formed at least partially within the high pressure region.

Gas turbine engine bleed scoops

A compressor stator includes an outer casing supporting a row of stator vanes extending radially inwardly therefrom. Each vane includes pressure and suction sides extending axially between leading and trailing edges and radially between a root and a tip. The root and tip are twisted relative to a pitch section disposed therebetween. Each vane tip is radially convex adjacent a leading edge for defining an axially concave outer flowpath in the casing for reducing peak velocity of airflow for enhanced efficiency.

Twisted stator vane

A compressor airfoil includes pressure and suction sides extending from root to tip and between leading and trailing edges. Transverse sections have respective chords and camber lines. Centers of gravity of the sections are aligned along a double bowed stacking axis for improving performance.

Doubled bowed compressor airfoil

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Cincinnati, OH, United States of America

Bryan Keith Doloresco