General Electric Company

Frederick W Tegarden

Thomas G Wakeman

Dean Thomas Lenahan

Jeffrey Glover

Martin C Hemsworth

Thomas P Joseph

Michael Harvey Schneider

James Edward Cencula

Gregg Hunt Wilson

Donald L Bellia

Charles H Gay, Jr

Kenneth J Lenhart

Hahn M Spofford

Albert P Sterman

Joseph Henry Schleue

Brett R Chouinard

Julie A Ritchie

Clearance control is provided by a shaped, integral environmental shield and circumferentially segmented cooling manifold. Each manifold has impingement rails located radially outside selected components of the stator casing. Cooling air is directed onto stator components and returns immediately through circuitous paths to improve uniformity of cooling. The structure incorporates the environmental shield into a two piece bonded structure to facilitate construction and assembly.

Integral clearance control impingement manifold and environmental shield

An aircraft engine thrust mount includes a pair of spaced apart thrust links pivotally joined at one end to an engine first frame and at opposite ends to a lever. A platform is fixedly joined to an aircraft pylon and includes first and second spaced apart clevises and a center clevis therebetween. The center clevis is pivotally joined to a center of the lever for carrying thrust force from the first frame through both thrust links and to the platform and pylon during normal operation. A pair of pins pivotally join the thrust links to the lever and extend through apertures in the platform first and second clevises to define predetermined gaps therebetween for allowing the lever to rotate relative to the platform center clevis up to a predetermined angular rotation. In a failure mode of operation the pins contact the platform first and second clevises for transmitting thereto either tension or compression thrust loads for providing an alternate failsafe loadpath. In a preferred embodiment, the platform further includes an aft mount joined to an engine second frame spaced aft of the engine first frame.

Aircraft engine thrust mount

A shroud panel is removably joinable inwardly of a fan casing and outwardly of a fan blade in a turbofan gas turbine engine. The panel includes an arcuate backing plate having a plurality of screws disposed therethrough for mounting the panel to the casing. Each of the screws includes a locking ring joined to the shank thereof and spaced from the screw head for allowing limited translation of the screw through the panel while preventing its liberation therefrom.

Removable fan shroud panel

A turbine shroud includes a ceramic sealing layer secured to a metal substrate. In one form, the metal substrate includes a plurality of pegs extending therefrom. Intermediate bonding layers are disposed on the peg-metal substrate structure. A ceramic sealing layer of zirconium oxide with about 20 weight percentage magnesium oxide is disposed, e.g., plasma sprayed, on the intermediate bonding layers. The ceramic sealing layer includes an ordered pattern of very fine cracks therein which reduce the thermal stress in the ceramic sealing layer. A method of constructing a turbine shroud structure is also disclosed.

Metal-ceramic turbine shroud and method of making the same

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Glendale, OH, United States of America

Frederick W Tegarden