Construction and arrangement of compressor drive shafts in gas turbine propulsion units

Claim 1

A COMPRESSOR DRIVE SHAFT IN GAS TURBINE PROPULSION UNITS, COMPRISING AT LEAST THREE BEARINGS, TWO SHAFT PARTS, AND MEANS DETACHABLY CONNECTING SAID TWO SHAFT PARTS WITH ONE ANOTHER SO AS TO BE COUPLED WITH EACH OTHER IN THE DIRECTION OF ROTATION AND CENTERED WITH RESPECT TO EACH OTHER, A TURBINE ROTOR AND A COMPRESSOR ROTOR, ONE OF SAID SHAFT PARTS BEING COORDINATED TO THE TURBINE ROTOR AND THE OTHER SHAFT PART BEING COORDINATED TO THE COMPRESSOR ROTOR, SAID TWO SHAFT PARTS BEING DETACHABLY CONNECTED WITH ONE ANOTHER IN THE AXIAL DIRECTION DURING ASSEMBLY OF SAID COMPRESSOR DRIVE SHAFT, SAID DETACHABLE AXIAL CONNECTION MEANS BETWEEN SAID TWO SHAFT PARTS BEING SO ARRANGED AND CONSTRUCTED AS TO BE ACCESSIBLE FROM THE OUTSIDE FROM THE SIDE OF THE COMPRESSOR, SAID OTHER SHAFT PART COORDINATED TO THE COMPRESSOR ROTOR BEING CONSTRUCTED AS HOLLOW SHAFT AND SAID ONE SHAFT PART COORDINATED TO THE TURBINE ROTOR BEING CONSTRUCTED IN PART AS A PLUG-IN-TYPE SHAFT HAVING AN EXTENSION EXTENDING AT LEAST PARTLY THROUGH SAID OTHER SHAFT PART, THE OUTER END OF SAID EXTENSION PROJECTING BEYOND THE OUTER END OF THE COMPRESSOR SHAFT PART AND BEING PROVIDED WITH THREADED MEANS, AND MEANS CLAMPINGLY CONNECTING THE OUTER END OF SAID ONE SHAFT PART IN AXIAL ABUTTING ENGAGEMENT INCLUDING BUSHING MEANS HAVING A COLLAR PORTION IN ENGAGEMENT WITH SAID OTHER SHAFT PART, AND A NUT THREADABLY ENGAGING SAID THREADED MEANS TO CLAMPINGLY TIGHTENING SAID COLLAR PORTION AGAINST A SHOULDER PROVIDED IN SAID EXTENSION WHEREBY SAID COLLAR PORTION FORMS AN ABUTMENT IN THE AXIAL DIRECTION FOR SAID ONE SHAFT PART.