General Electric Company

Mark Anthony Holleran

Darrell Glenn Senile

Matthew Mark Weaver

Nicholas John Bloom

Alexander Martin Sener

Douglas Glenn Decesare

Brian Gregg Feie

A shroud assembly is provided for a gas turbine engine defining an axial direction, a radial direction, and a circumferential direction. The shroud assembly includes: a shroud segment extending substantially along the circumferential direction and including a shroud wall, the shroud wall defining a shroud attachment opening; a hanger assembly including a hanger wall defining a hanger attachment opening; and an attachment pin assembly including a first member defining an interference fit with the hanger wall through the hanger attachment opening and including a shoulder contacting the hanger wall, the first member further extending through the shroud attachment opening and defining a hollow core; and a second member extending through the hollow core of the first member, the second member extending between a first end and a second end, the second member including a rim at the first end and a secondary attachment member at the second end.

Shroud pin for gas turbine engine shroud

Fairing assemblies and methods for assembling gas turbine engine fairing assemblies are provided. For example, a fairing assembly comprises a plurality of fairings, an annular inner band defining a plurality of inner pockets, and an annular outer band defining a plurality of outer pockets. Each fairing has an inner end radially spaced apart from an outer end. Each inner pocket is shaped complementary to each fairing inner end and has forward and aft ends. Each outer pocket is shaped complementary to each fairing outer end and has forward and aft ends. The inner and outer bands are each a single piece structure. Each fairing inner end is received within one of the plurality of inner pockets, and each fairing outer end is received within one of the plurality of outer pockets. Some embodiments also comprise an inner ring positioned against the inner band to close the inner pockets.

Fairing assembly

Nozzle segment assemblies for gas turbine engines include an outer band, inner band, and at least one airfoil body between the outer band and inner band. The airfoil body includes an outer end extending through the outer band and having an outer end reinforced wall portion engaging with the outer band and an inner end extending through the inner band and having an inner end reinforced wall portion engaging with the inner band. A thickness of the outer end and inner end reinforced wall portions are each greater than a thickness of a central wall portion of the airfoil body to reduce stresses in the airfoil body. The outer band, the inner band, and the airfoil bodies are ceramic matrix composite (CMC) materials. Direct mounting of the airfoil bodies to the inner and outer hangers of the nozzle further reduce stress.

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Cincinnati, OH, United States of America

Mark Anthony Holleran