| 摘要 |
The invention relates to an arrangement for the detection of a shaft break on a rotor of a first turbine, especially a medium pressure turbine, of a gas turbine, especially an aircraft engine, whereby a second turbine ( 11 ), especially a low pressure turbine, is positioned downstream from the first turbine, with an actuating element ( 18 ) positioned lying radially inwardly relative to a flow channel, between the rotor of the first turbine and a stator of the second turbine ( 11 ), and with a transmission element ( 22 ) guided in the stator of the second turbine ( 11 ), in order to transmit a shaft break detected by the actuating element ( 18 ) positioned lying radially inwardly to a switching element ( 23 ), which is positioned lying radially outwardly relative to the flow channel on a housing ( 14 ) of the gas turbine.
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