Patent ID: 7780400
Filing Date: 2010-08-24
Classification: F01D,F02C,F05D

Abstract:
1. Gas turbine machine comprising at least two compressors, at least one combustion chamber, at least first and second turbines, and an arrangement for the detection of a shaft break on a rotor of the first turbine, wherein the second turbine is positioned downstream from the first turbine, characterized in that an actuating element ( 18 ) is positioned between the rotor of the first turbine and a stator of the second turbine ( 11 ) and lying radially inwardly adjacent to a rotor disc of the last rotor blade ring, as seen in the flow direction, of the first turbine, and is slidably guided in a radially inwardly lying seal structure ( 19 ) of the stator of the second turbine ( 11 ) to be slidable in the axial direction or in the flow direction, in that a transmission element ( 22 ) is slidably guided in the stator of the second turbine ( 11 ) to be slidable in the radial direction, in that the transmission element ( 22 ) cooperates at a radially inwardly lying end ( 25 ) with the actuating element ( 18 ) and cooperates at a radially outwardly lying end ( 26 ) with a switching element ( 23 ) that is positioned lying radially outwardly on a housing ( 14 ) of the gas turbine machine, and in that at least one elastically deformable spring element ( 21 , 27 ) is arranged for mechanical coupling between the actuating element ( 18 ) and the transmission element ( 22 ) and/or between the transmission element ( 22 ) and the switching element ( 23 ).