Turbo jet engine for aircraft, has static support tube concentrically supported within low pressure shaft, where front end of tube is guided into front area of engine and motor-generator-unit is arranged at front end of tube

摘要

The engine has a low pressure shaft (3) concentrically arranged within a high pressure shaft (2). A motor-generator-unit (16) is formed from a stator (17) and a rotor (18). A static support tube (13) is concentrically supported within the low pressure shaft. A rearward end (14) of the tube is firmly connected with outer and inner frame structures (4, 5) and an exhaust housing (10). A front end (15) of the tube is guided into a front area of the engine. The motor-generator-unit is arranged at the tube front end. The stator is supported on the low pressure shaft over a bearing assembly (19).