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.

Abstract: A gas turbine engine (20) comprises a diffuser (24) and a nozzle (26) affixed to a cylindrical housing member (22), a bearing assembly (34) including a support tube (36) affixed at one end (36a) in cantilever fashion to a radially inner portion (26c) of the nozzle, a compressor (28) and a turbine (30) affixed to axially spaced apart ends of a shaft (32) rotatably mounted therebetween in the support tube by antifriction bearings, and an annular combustion chamber (40) disposed between the compressor and turbine and concentric to the shaft. A fuel slinger (38), affixed to the shaft, receives fuel from an air/fuel annulus (96) defined by the support tube and shaft. An air/fuel mixture in the annulus also lubricates the bearings and cools a hub portion (30a) of the turbine. Movement of the mixture through the air/fuel annulus is enhanced by pumps (38c, 102, 104 and 312).