United Technologies Corporation

Raytheon Technologies Corporation

Barry William Spaulding

Gregory E Reinhardt

Daniel W Major

Paul Thomas Rembish

Donald Summers

Kelton Gallant

A gas turbine engine includes a fan that includes a plurality of fan blades rotatable about an axis. An on-wing portion includes a compressor section and a combustor that is in fluid communication with the compressor section. A turbine section is in fluid communication with the combustor. A core flow path is arranged within a core nacelle. The fan is arranged upstream from the core flow path. A fan drive gear system module is coupled to the turbine section for rotating the fan about the axis. A connector assembly including first and second members respectively is secured to the on-wing portion and the fan drive gear system module. The first and second members are removably secured to one another by radially extending fasteners. The first members are connected to an on-wing portion of the gas turbine engine and the second members are connected to the fan drive gear system module. The fasteners are accessible through the bypass flow path.

Fan drive gear system module and inlet guide vane coupling mechanism

A connection assembly for securing a fan drive gear system module within a gas turbine engine includes first and second members removably secured to one another by radially extending fasteners.

The present disclosure relates generally to a fastener lock for engaging a threaded fastener. The fastener lock defines a discontinuous circular opening therethrough with at least one extending tab extending into the discontinuous circular opening. When a threaded fastener is disposed in the discontinuous circular opening, the at least one extending tab engages the threads of the threaded fastener.

Growing community of inventors

Middletown, CT, United States of America

Barry William Spaulding