General Electric Company

Craig Robert Jacobson

Robert Francis Manning

Elias Harry Lampes

Michael Hogan

Brian Ellis Clouse

Myron Daniel Toomey

A stator case for a gas turbine engine having a stator and a rotor. The rotor has a plurality of circumferential rows of blades. Each blade extends radially outward from a root to a tip. The case includes a tubular shell extending axially between a forward end and an aft end. The shell has an interior surface defining a hollow interior sized and shaped for receiving at least a portion of the rotor of the gas turbine engine. The case also includes a circular forward flange extending radially outward from the forward end of the shell and a circular aft flange extending radially outward from the aft end of the shell. In addition, the case includes a circular rib extending radially outward from the shell between adjacent rows of blades. The rib is sized and shaped for adjusting transient deflections of the shell to generally match transient deflections of the tips of the plurality of rotor blades to reduce a transient clearance between the interior surface of the tubular shell and the tips of the rotor blades.

Gas turbine engine stator case

A turbine blade includes an airfoil having opposing first and second sides and an internal passage extending longitudinally therebetween. A plurality of first turbulator ribs extend from the first side into the passage, and a plurality of second turbulator ribs extend from the second side into the passage. The first and second ribs are different in configuration from each other for obtaining different heat transfer enhancements on the first and second sides for reducing pressure losses and cooling air flow requirements.

Turbine blade having opposing wall turbulators

A turbine blade includes an airfoil having first and second opposite sides and an internal passage extending longitudinally therebetween for channeling air to cool the airfoil. A single restart turbulator rib is disposed in the passage adjacent to the inlet and has a first height e.sub.1 for obtaining a first convective heat transfer enhancement. A plurality of primary turbulator ribs are disposed downstream from the restart rib in the passage. The primary ribs include an initial primary rib having a second height e.sub.2 for obtaining a second convective heat transfer enhancement, with the initial primary rib being spaced longitudinally from the restart rib at a first spacing S.sub.1, and spaced longitudinally from a second primary rib at a second spacing S.sub.2. The first enhancement is less than the second enhancement to reduce overcooling of the airfoil between the restart and primary ribs.

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Peabody, MA, United States of America

Craig Robert Jacobson