General Electric Company

United States of America As Represented by the Secretary of the Air Force

Robert W Harris

Ching-Pang Lee

George A Durgin

John Frederick Ackerman

William Randolph Stowell

Phillip D Napoli

Richard L Horvath

Thomas A Brisken

Kenneth Morand Lieland

A turbine blade squealer tip includes an airfoil shaped tip cap having a squealer tip wall extending radially outwardly from and around the perimeter of the airfoil shaped tip cap to define a radially outwardly open tip cavity. The tip wall has an inboard side facing the interior of the cavity and an outboard side facing away from the cavity and the tip cap has an outer tip side on a bottom of the cavity. Thermal barrier coatings are disposed on the inboard and outboard sides of the squealer tip wall and on the outer tip side of the tip cap. One embodiment provides the tip cap with cooling holes disposed therethrough to flow cooling air into the cavity.

Thermal barrier coated squealer tip cavity

A coated article comprises a substrate, an inner environmental resistant coating portion including Al on the substrate, and an outer heat energy reflecting and oxygen diffusion inhibiting coating portion outward of the inner portion. The outer coating portion is multi-layer, comprising 6-48 discrete stacked layers and a total outer coating portion thickness in the range of about 2.5-25 microns.

Article with tailorable high temperature coating

A turbine airfoil includes a plurality of internal ribs joined to laterally opposite first and second sidewalls to define a serpentine cooling circuit therein. A span rib extends longitudinally between a root and tip of the airfoil. And, a slant rib extends obliquely to the span rib to define respective portions of the serpentine circuit longitudinally above and below the slant rib.

Slant-tier turbine airfoil

An improved high pressure turbine rotor blade and tip cap structure therefor is provided, which comprises, a plurality of metallic layers bonded to the tip end of the blade, each layer having a peipheral shape conforming to the camber of the blade, the layers defining a plurality of radially outwardly opening, serpentine-shaped passageways for passage of coolant fluid through the periphery of the tip end of the blade.

Cooled turbine blade tip closure

A cavity is defined between the rotating and stationary parts of a gas turbine engine through which cavity air is circulated. Upstream and downstream seals are disposed at opposite ends of the cavity for regulating the circulation of air flowing into and out of the cavity. A cooling air circuit for the engine rotor is provided which channels air from the stationary portion of the engine to the rotor through the cavity therebetween. The rotor air cooling circuit includes an inducer chamber where the cooling air is accelerated and transferred to the engine rotor. The inducer chamber is defined by two additional seals which, in conjunction with the other cavity seals define chambers upstream and downstream of the central inducer chamber. A bypass circuit directs the air circulated within the upstream chamber directly to the downstream chamber (bypassing the inducer chamber) so that the coolant air flowing through the inducer chamber is not contaminated with the air circulated between the engine rotor and stator.

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Cincinnati, OH, United States of America

Robert W Harris