United Technologies Corporation

Raytheon Technologies Corporation

Christopher M Quinn

Charles W Brown

Shelton O Duelm

Sreenivasa R Voleti

Matthew A Turner

Thomas J Robertson, Jr

Darin S Lussier

Andrew G Alarcon

Colin J Kling

James Glaspey

Peter V Tomeo

Shari L Bugaj

David J Hyland

Corey L Hubbert

Keith T Salamon

Alan J Walker

Jr Thomas J Robertson

A case for a gas turbine engine includes a plurality of distinct case sections in axial series. The case sections include, in axial order, a flange section, a forward shell section, a containment section, and an aft shell section. The forward shell section, the containment section, and the aft shell section are formed of a plurality of unidirectional roving fiber layers and a plurality of non-crimp fabric layers. The flange section is formed of a second plurality of non-crimp fabric layers. The plurality of unidirectional roving fiber layers do not have stitching or weaves. A ballistic liner is attached with the containment section, and a fiberglass layer encapsulates the plurality of unidirectional roving fiber layers, the plurality of non-crimp fabric layers, and the second plurality of non-crimp fabric layers.

Case with ballistic liner

A platform for a fan of a gas turbine engine includes a body portion, a forward flange at a front of the body portion that includes an engagement feature that interacts with a forward flange of a lug of a hub of a fan of a gas turbine engine, and a pin integral with a rear portion of the body portion. The pin is receivable in an aperture in a rear flange of the lug.

Low profile fan platform attachment

A turbine engine component () comprises a fiber structure () forming at least a portion of an airfoil (). A matrix () embeds the fiber structure. A carbon nanotube filler () is in the matrix.

Vibration-damped composite airfoils and manufacture methods

A fan hub assembly for a gas turbine engine includes a fan hub that is configured to rotate about an axis. The fan hub has an axially extending aperture and a platform. A fastener is received in the aperture in a slip fit relationship to secure the platform to the fan hub.

Gas turbine engine fan spacer platform attachments

A composite article includes a laminate structure of at least first and second fiber layers. Each of the layers includes a network of primary reinforcement fibers disposed in a matrix. The layers are bonded to each other along an interface of the matrices. The matrices include a concentration of secondary reinforcement particles locally at the interface to strengthen the interface.

Secondary reinforcement at interface of laminate structure

Anti-rotation tabs for the platforms in the fan section of a gas turbine engine are provided. The anti-rotation tabs interface with the trailing edge of the spinner, thereby preventing the platform from rotating and twisting.

T-shaped platform leading edge anti-rotation tabs

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 case for a gas turbine engine includes a containment section with a plurality of unidirectional roving fiber layers and a plurality of non-crimp fabric layers. A method of manufacturing the case includes winding the plurality of unidirectional roving fiber layers around the plurality of non-crimp fabric layers.

A fairing assembly includes an outer wall, a first side wall, a second side wall, and a saddle. The first side wall and the second side wall extend from opposing sides of the outer wall. Together the first side wall, the second side wall, and the outer wall form a cavity within the fairing assembly. The saddle is positioned within the cavity and extends between the first side wall and the second side wall. The saddle has a first rib adapted to connect to the first side wall and a second rib adapted to connect to the second side wall. The first rib and the second rib connect together at a central hub.

Fairing assembly

A fan assembly includes a first fan blade with a rib extending therealong and a first fairing platform mounted on and supported from the first fan blade. The first fairing platform has a flange with a groove that mates with the rib.

Growing community of inventors

Middletown, CT, United States of America

Christopher M Quinn