The engine has a core-flow channel (5), and a bypass duct (3) surrounding the core-flow channel and comprising an inner sidewall (2). The sidewall is retained against an engine lining (1). The sidewall has a straight, conically widening form that is smooth...

A generator assembly for a gas turbine engine (10). The assembly includes an electrical generator (32) connected via a first sprag clutch (34) to an accessory gearbox (22) driven by the engine (10). The generator (32) is also connected by a second sprag cl...

A mechanical drive system for an accessory gearbox (24) of a gas turbine engine is provided. The gas turbine engine includes a high-pressure drive shaft (12) and a low-pressure drive shaft (14). The mechanical drive system includes a tower shaft (32) and a...

A mechanical drive system for an accessory gearbox (24) of a gas turbine engine (10) is provided. The engine has a high-pressure drive shaft (12) and a low-pressure drive shaft (14). The mechanical drive system includes a first tower shaft (36), a second t...

A mechanical drive system for an accessory gearbox (24) of a gas turbine engine is provided. The engine has a high-pressure drive shaft (12) and a low-pressure drive shaft (14). The mechanical drive system includes a first tower shaft (36), a second tower ...

The turbine has electrical generators driven through a differential gear (30) having two planet wheels (31`, 32`) driven by high and low pressure rotor shafts (1, 2) of high and low pressure bodies. The wheels drive a planet gear (33) mounted in a casing (...

An aircraft gas turbine propulsion engine includes a compressor (10) and ancillary systems (cabin pressurising pumps and other services) in a box 16. A fuel cell 18 powers electric motors (12) and (14) via a switch (20) for the purpose of either simultaneo...