A hybrid control system (26) for controlling an electric machine (20) coupled to a gas turbine engine (10) is provided. The control system comprises: a primary analog control loop (28) including an analog controller (32) for controlling the electric machin...

A hybrid combustor combines two distinct fuel injection sources (20,22) to spray fuel in the combustor (16). The combustor (16) combines a rotary fuel slinger (20) for spraying fuel in a first combustion zone (38) during high power level and cruise conditi...

A gas turbine engine recuperator (30) including a plurality of independent arcuate segments (32), each segment having an inlet connection member (58) designed to sealingly engage a plenum (28) in fluid flow communication with the compressor discharge, and ...

A gas turbine engine recuperator (30) includes exhaust passages (42) providing fluid flow communication between an exhaust inlet (50) and an exhaust outlet (52). The exhaust inlet (50) is oriented to receive exhaust flow from a turbine (18) of the engine (...

A gas turbine engine recuperator (30) includes exhaust passages (42) providing fluid flow communication between an exhaust inlet (50) and an exhaust outlet (52). The exhaust inlet (50) is oriented to receive exhaust flow from a turbine (18) of the engine (...

A method of controlling a speed of a gas turbine engine (10,110) including a gas generator or high pressure spool (24,124) and a power turbine or low pressure spool (20,120) rotating independently from one another, including controlling a rotational speed ...

A power generating apparatus for use with an aircraft gas turbine engine (10) has a low pressure spool assembly (12) which includes an electrical generator (34). The electrical generator (34) includes a generator stator (48) supported on a stationary struc...

Methods for controlling an aircraft turbofan engine during icing of a temperature probe and devices for carrying out such methods are described. The methods may comprise: using (46) one or more signals representative of temperature received from a heated t...

A gas turbine engine exhaust mixer has a plurality of circumferentially distributed alternating inner and outer lobes (42, 44). The outer lobes (44) protrude into the annular bypass passage (24) of the engine, whereas the inner lobes (42) protrude into the...