CONNECTION OF REDUCED RADIAL CLEARANCE BETWEEN TURBINE SHAFT AND SHAFT NECK OF COMPRESSOR OF INTERNAL COMBUSTION ENGINE, AND GAS TURBINE ENGINE CONTAINING DESCRIBED CONNECTION Russian patent published in 2011 - IPC F02C7/36 

FIELD: engines and pumps.

SUBSTANCE: connection between turbine shaft and shaft neck of compressor of gas turbine engine includes torque transmission devices between turbine shaft and shaft neck of compressor and locking devices of the end of turbine shaft on shaft neck of compressor. Compressor shaft neck includes multiple teeth made in radial direction from its inner surface. Turbine shaft includes many axial slots on its end, and teeth of neck interact with slots of turbine shaft. Locking devices includes nut tightened on the thread made on turbine shaft end. Nut includes multiple axial slots each of which is made between two adjacent teeth and interacts with teeth of compressor shaft neck. In addition, locking devices includes nut locking ring having many cutouts interacting with teeth of locking nut, thus locking its rotation. The other invention of the group refers to gas turbine engine including the above connected between low pressure turbine shaft and low pressure compressor shaft neck.

EFFECT: invention allows decreasing radial clearances of connection of turbine shaft and compressor shaft neck, simplifying erection and removal of low pressure turbine.

5 cl, 4 dwg