An aircraft system (20) includes a first propulsor (36A), a second propulsor (36B), a drivetrain and an intermittent combustion engine (66). The first propulsor (36A) includes a first propulsor rotor (42A) and a first vane array (44A). The second propulsor...

A heat exchanger system for a propulsion system inlet duct (36) includes a heat exchanger assembly that is disposed within an inlet duct assembly (34). The heat exchanger assembly includes a heat exchanger with a front facing area that is greater than an a...

A propulsion system and methods are presented. A substantially tubular structure (102) comprises a central axis (104) through a longitudinal geometric center, and a first fan (108) rotates around the central axis, and comprises a first fan hub (110) and fi...

A gas turbine engine (10) having an axial flow direction (X) therethrough in use. The gas turbine engine (10) comprises one or more rotor stages each comprising at least one rotor blade (120) having a root portion (122). The gas turbine engine (10) compris...

This invention relates to a propulsive unit (10) for an aircraft, comprising: a nacelle (12) which defines a duct (20) for channelling an airflow when in use and which provides an outwardly facing surface (14) of the propulsive unit (10), the outwardly fac...