United Technologies Corporation

Keith T Salamon

Barry M Ford

Matthew A Turner

Christopher M Quinn

John P Tirone

A gas turbine engine includes a core engine, a fan coupled to be driven by the core engine, a first case structure around the core engine and a second case structure around the fan. The first case structure and the second case structure define a bypass passage there between. A vane structure includes an airfoil extending radially between the first case structure and the second case structure. A seal is configured to control leakage between the bypass passage and a core engine.

Gas turbine engine including vane structure and seal to control fluid leakage

A wall assembly includes a wall that extends axially along a centerline, and circumferentially at least partially around the centerline. The wall assembly also includes a plurality of mounting brackets arranged circumferentially around the centerline, and a plurality of wall brackets. Each of the mounting brackets includes a groove that extends axially into the respective mounting bracket. Each of the wall brackets includes a tongue and a base. The tongue extends axially from the base into the groove of a respective one of the mounting brackets. The base is connected to the wall.

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Middletown, CT, United States of America

Keith T Salamon