United Technologies Corporation

Dana P Stewart

Jorge I Farah

Joey Wong

Jonathan P Burt

Michael A Mike

David N Waxman

Peter Chen

Conway Chuong

Edward R Szela

Theodore W Kapustka

Jonathan J Jakiel

John H Finn

A stator vane arrangement for a turbine engine includes a first vane platform, a second vane platform and a plurality of stator vanes extending radially between the first and the second vane platforms. The first and the second vane platforms extend circumferentially around an axis, and the first vane platform includes an aperture. The stator vanes are arranged circumferentially around the axis, and include a first stator vane that extends radially into the aperture and is fastened to the first vane platform.

Stator vane arrangement for a turbine engine

A turbine engine vane arrangement and a method for manufacturing a turbine engine vane arrangement are provided. The vane arrangement includes a plurality of vane arrangement segments arranged circumferentially around an axial centerline. Each of the vane arrangement segments includes an airfoil that extends radially between a first platform segment and a second platform segment. The first platform segment extends circumferentially between a first mate face and a second mate face. The first mate face of a first of the vane arrangement segments is bonded to the second mate face of a second of the vane arrangement segments.

Turbine engine vane arrangement having a plurality of interconnected vane arrangement segments

Gas turbine engine systems involving I-beam struts are provided. In this regard, a representative strut assembly for a gas turbine engine includes a first I-beam strut having first and second flanges spaced from each other and interconnected by a web, the first strut exhibiting a twist along a length of the web.

Gas turbine engine systems involving I-beam struts

A case assembly includes a plurality of segments, at least one braze joint, and one or more welds. The braze joint connects the plurality of segments together and the one or more welds extend across adjacent segments.

Case assembly and method

A static structure of a gas turbine engine includes a multiple of airfoil segments and at least one structural reinforcement ring mounted to the multiple of airfoil segments.

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Vernon, CT, United States of America

Dana P Stewart