Rohr, Inc.

Goodrich Corporation

Joseph Christopher Zecca

Galdemir Cezar Botura

Michael Sean Pretty

Claude Marc Hubert

Timothy Olson

John Moule

Brian Burkett

Michael John Layland

Aleksandar Ratajac

David B Sweet

James Michael Roman

Russell Brian Hayes

David Bert Sweet

Timothy Robert Olson

Brian Bobby Burkett

A seal retainer for a fire seal of a gas turbine engine is provided. The seal retainer includes a core formed from a thermoplastic material and having a shape of a seal retainer with a top surface and a bottom surface, a first layer applied to the top surface of the core, and a second layer applied to the bottom surface of the core. The first layer and the second layer are formed from a high-temperature resistant material.

Coated thermoplastic seal retainer for fire seal test

A nacelle may include a pylon and a thrust reverser having an inner fixed structure. A locking mechanism may automatically engage and prevent relative movement between thrust reverser halves. A bumper may be coupled to the inner fixed structure. The locking mechanism may limit deflections between the thrust reverser and the pylon in response to a burst duct. A locking mechanism in the inner fixed structure may include a pressure relief door and an arrestor which hooks onto a retaining bar in a pylon bracket. The locking mechanism may allow the thrust reverser halves to be opened for access to the engine.

Automatic deflection limiting latches for a thrust reverser

Methods and fire sealing systems for a panel of a gas turbine engine are provided. The fire sealing systems include a thermal blanket mounted on the panel, the thermal blanket having a close-out and defining a seal landing at a periphery edge of the panel, a seal retainer mounted to the panel along the seal landing, and a fire seal securely retained within the seal retainer, wherein at least one of the seal retainer or the fire seal comprises an extension portion and a blanket engaging portion such that a close-out volume formed between the thermal blanket and the fire seal above the close-out of the thermal blanket is enclosed.

Close-out enclosure for panel of a gas turbine engine

An electric heater () for integration into an acoustic panel () having sound-penetrating pores () communicating with a sound-canceling medium. The heater () includes an electrically conductive layer () with resistance-setting apertures () filled with sealant (). Openings (), which contribute to the sound-penetrating pores (), extend through the sealant-filled apertures (). The acoustic panel () can be assimilated into an aircraft component, such as a nacelle inlet lip, which requires both noise-reducing and ice-protecting features.

Electric heater for integration into an aircraft acoustic panel

An aircraft component includes a first segment having a first leading edge surface that extends to a first end of the first segment. The aircraft component also includes a second segment having a second leading edge surface that extends to a second end of the second segment. The second end is substantially adjacent to the first end of the first segment, and is connected to the first end. The first leading edge surface includes electrical resistance heating that extends to the first end of the first segment. In addition, the second leading edge surface includes electrical resistance heating that extends to the second end of the second segment. The electrical resistance heating is capable of providing ice protection heating immediately on either side of a juncture between the connected first and second ends.

Ice protection system for a multi-segment aircraft component

Growing community of inventors

San Diego, CA, United States of America

Joseph Christopher Zecca