Abstract: A gas turbine engine (10) comprises a diffuser (14) and a nozzle (16) affixed to an annular housing (12), a bearing assembly including first and second bearings (24,26) mounted on a support tube (28) affixed at one end (28a) in cantilever fashion to a radially inner portion (16c) of the nozzle, a compressor (18) and a turbine (20) affixed to axially spaced apart ends of a shaft (22) rotatably mounted in the bearings, and an annular combustor (32) disposed between the compressor and turbine and concentric to the shaft. The diffuser is adjustably attached to the housing external threads (14e) on an outer annular surface of the diffuser and received in internal threads (12e) in an internal annular surface of the housing. An electric generator (42) is disposed radially inward of the annular combustor axially between the diffuser and nozzle. A fuel slinger (30), affixed to the shaft, receives fuel from an air/fuel annulus (88) defined by a stator (44) and a rotor (46) of the generator.