United Technologies Corporation

Raytheon Technologies Corporation

David C Pimenta

Glenn Levasseur

Robert Russell Mayer

Steven D Roberts

Richard W Monahan

Paul R Senofonte

Timothy Dale

Andrew S Miller

Fernando K Grant

Joseph J Czapski, Jr

Chung-Han Liou

Jocelyn Charis Damgaard

Stephanie Ernst

Igor S Garcia

Tracks (), fastened to static structure of an aircraft engine nozzle, guide sliders () journaled in struts () fastened to a flap () of the nozzle. Each slider and attached journal axle or bolt () is formed of cobalt, and each track slider surface () and journal bushings () are formed of a nickel alloy to reduce wear from rubbing. Track slides () are mounted to the static structure of the nozzle by blind bolts () having a tool recess () at its threaded tip to prevent the bolt () from turning as a nut is secured. Each slider has limited rotation due to a pin (), thereon engaging a slot in a tab () of the bushing () to assist in inserting the slider () into the beveled ends of the tracks (), when mounting or replacing a flap.

Sliding nozzle flap assembly

A gas turbine engine system includes an airframe support, a gas turbine engine mounted to the airframe support, a nozzle exhaust mounted to the airframe support, and a flexible annular seal having a first end that is attached to the gas turbine engine and a second end that is attached to an exhaust nozzle. The flexible annular seal may include a flexible annular wall that permits relative deflection between the gas turbine engine and the exhaust nozzle to facilitate the reduction of undesirable load transfer.

Flexible seal for gas turbine engine system

A system includes a gas turbine engine, a nozzle structure located adjacent to the gas turbine engine, a flexible annular seal linking the gas turbine engine and the nozzle structure, the flexible annular seal having a plurality of corrugate sections, and a reinforcement member positioned between two of the plurality of corrugate sections.

A system includes a gas turbine engine, a nozzle structure located adjacent to the gas turbine engine, a flexible annular seal linking the gas turbine engine and the nozzle structure, the flexible annular seal having a plurality of corrugate sections arranged about a centerline, and a connection device secured to the gas turbine engine and to the nozzle structure. The connection device is adjustable to select a length of the flexible annular seal measured along the centerline.

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Rocky Hill, CT, United States of America

David C Pimenta