United Technologies Corporation

Christina A Stenman

Shelton O Duelm

Christopher Treat

Conway Chuong

Alex J Simpson

Tuan David Vo

Alisha M Zimmermann

A liner assembly includes a plurality of flaps arranged about a central axis and operable to move relative to the central axis. Each of the plurality of flaps defines a forward end and an aft end, lateral sides, and an inner surface and an outer surface relative to the central axis. Each of the plurality of flaps has a thickness between the inner surface and the outer surface, and thickness varies in a lateral direction between the lateral sides.

Convergent-divergent gas turbine nozzle comprising movable flaps having a variable thickness in a lateral direction

A corrugated shield comprises a mounting base and a corrugated ring section. The mounting base is disposed at an aft end of the ring section for securing the shield ring section within a generally annular cavity. The generally annular cavity is defined at least in part by a hot fluid flow path boundary wall, and a radially adjacent and spaced apart cold fluid flow path boundary wall. The corrugated ring section is configured to substantially block a line of sight between the hot fluid flow path boundary wall and the cold fluid flow path boundary wall.

Corrugated mid-turbine frame thermal radiation shield

A shield system for a gas turbine engine extends between an inner case structure and a vane pack.

Shield system for gas turbine engine

A seal assembly for a nozzle in a gas turbine engine includes a connector having a first hinge portion for attaching to the nozzle, a flat portion for sealing against a wall of the engine; and a first hinge for attaching the connector to the flat portion wherein the connector is adapted to rotate relative to the nozzle and the flat portion is adapted to rotate relative to the connector.

Growing community of inventors

Wethersfield, CT, United States of America

Christina A Stenman