Pratt & Whitney Canada Corp.

Eric S Durocher

Eugene Gekht

Ghislain Plante

Robert Peluso

Michel Abdelnour

Michel Labrecque

Herve Turcotte

Keith Morgan

Jean Dubreuil

A seal assembly of a shaft bearing system includes an inner seal element fixed to a shaft and rotatable therewith about a shaft axis, and an outer seal located radially outboard of the inner seal element and rotationally fixed relative to the shaft axis. The outer seal includes a first circumferential seal segment, and a second circumferential seal segment abutting the first circumferential seal segment at a seal joint. The first circumferential seal segment includes one or more circumferentially extending first segment fingers installed into one or more complimentary second segment pockets at least partially defining a tortuous pathway in an axial direction between the first seal segment and the second seal segment.

Serviceable propeller shaft zero air gap seal

An assembly for a propulsion system of an aircraft includes a gearbox, at least one accessory load assembly, a propulsor, and an electric motor. The gearbox module includes a gear assembly and an output shaft. The gear assembly is connected to the output shaft. The at least one accessory load assembly includes at least one accessory load coupled to the output shaft. The propulsor is coupled to the output shaft. The electric motor includes a rotor. The rotor is coupled to the gear assembly to drive rotation of the output shaft about a rotational axis. The rotation of the output shaft drives rotation of the propulsor and the at least one accessory load for each accessory load assembly of the at least one accessory load assembly.

Electric motor propulsion system for an aircraft

The method can include operating the hybrid aircraft power plant in a first mode of operation in which a plurality of controllable parameters including a fuel flow to the thermal engine and an electric power to the electric motor has a first set of values corresponding to a first power output; receiving a requested power output; determining a second set of values of the one or more of the controllable parameters to bring first power output to the requested power output; determining whether said second set of values poses a risk of undesired clutch behavior; and when the second set of values poses the risk, modulating the second set of values to avoid the risk and setting the plurality of controllable parameters to the modulated second set of values.

Method and system for operating a hybrid aircraft engine

Growing community of inventors

Boucherville, Canada

Eric S Durocher