General Electric Company

Gregory T Steinmetz

John Jared Decker

Peter Nicholas Szucs

Peter John Wood

Mark Joseph Mielke

Brent Franklin Beacher

Hsin-Tuan Liu

Bryan Keith Doloresco

Kenneth William Krabacher

Thomas Ory Moniz

Andrew Breeze-Stringfellow

James Edward Johnson

Kenneth Edward Seitzer

John Christopher Brauer

Jorge Francisco Seda

Lawrence Wayne Dunbar

Philip Roger Gliebe

Robert Bruce Dickman

An aircraft gas turbine engine assembly includes an inter-turbine frame axially located between high and low pressure turbines. Low pressure turbine has counter rotating low pressure inner and outer rotors with low pressure inner and outer shafts which are at least in part rotatably disposed co-axially within a high pressure rotor. Inter-turbine frame includes radially spaced apart radially outer first and inner second structural rings disposed co-axially about a centerline and connected by a plurality of circumferentially spaced apart struts. Forward and aft sump members having forward and aft central bores are fixedly joined to axially spaced apart forward and aft portions of the inter-turbine frame. Low pressure inner and outer rotors are rotatably supported by a second turbine frame bearing mounted in aft central bore of aft sump member. A mount for connecting the engine to an aircraft is located on first structural ring.

Aircraft engine with inter-turbine engine frame supported counter rotating low pressure turbine rotors

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

An airfoil includes a leading edge chord barrel between a root and a tip, and forward aerodynamic sweep at the tip.

Swept barrel airfoil

A compressor stator vane includes pressure and suction sides extending chordally between leading and trailing edges, and longitudinally between a root and a tip. The vane narrows in chord to a waist between the root and tip. The vane may also be bowed at its trailing edge in cooperation with the narrow waist.

Narrow waist 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 bowed stacking axis either tangentially, axially, or both, for improving performance.

Bowed compressor airfoil

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Cincinnati, OH, United States of America

Gregory T Steinmetz