Abstract: The present technology relates generally to a device for the detection of a shaft fracture in a rotor of a turbine, for example a medium pressure turbine such as a gas turbine, in particular an aircraft engine, whereby at least one stator-side sensor element is positioned downstream from the turbine in the area of a stator-side guide vane ring of another turbine in particular, a low pressure turbine; and whereby a radially inner section of the last rotor-side moving blade ring (as seen in the direction of flow) of the turbine cooperates with at least one sensor element directly and/or proximally in the event of a shaft fracture in the rotor of the turbine to generate an electric signal corresponding to the shaft fracture.

Abstract: A device for detecting a shaft rupture in a rotor of a turbine, in particular a medium-pressure turbine, of a gas turbine, in particular of an aircraft engine, at least one stator-side sensor element being positioned downstream from the turbine, in particular in the area of a stator-side blade ring of another turbine, in particular a low-pressure turbine, and, in case of a shaft rupture of the rotor of the turbine, a radially externally situated segment of a last (seen in the direction of flow) rotor-side blade ring of the turbine working together with the, or with each, sensor element to generate an electrical signal corresponding to the shaft rupture.

Abstract: An arrangement is provided for detecting a shaft break on a rotor of a first turbine, especially a medium pressure turbine, of a gas turbine machine, especially an aircraft engine. A second turbine (11), especially a low pressure turbine, is positioned downstream from the first turbine. An actuating element (18) is positioned lying radially inwardly relative to a flow channel, between the rotor of the first turbine and a stator of the second turbine. A transmission element (22) is guided in the stator of the second turbine (11), in order to transmit a shaft break detected by the radially inwardly positioned actuating element (18) to a switching element (23) positioned radially outwardly relative to the flow channel on a housing (14) of the gas turbine.

Abstract: A gas turbine machine includes a second turbine (11), e.g. a low pressure turbine, positioned downstream from a first turbine (10), e.g. a medium pressure turbine. An arrangement for detecting a shaft break of a rotor shaft includes an operator element (16) positioned between the rotor of the first turbine (10) and a stator of the second turbine (11) radially inwardly relative to a flow channel, and a sensor element (21) guided in the stator of the second turbine (11), to convert a shaft break, detected by the radially inwardly positioned operator element (16), into an electrical signal and to transmit this electrical signal to a switching element which is positioned radially outwardly relative to the flow channel on a housing of the gas turbine machine.

Abstract: A device for detecting a shaft rupture in a rotor of a turbine, in particular a medium-pressure turbine, of a gas turbine, in particular of an aircraft engine, at least one stator-side sensor element being positioned downstream from the turbine, in particular in the area of a stator-side blade ring of another turbine, in particular a low-pressure turbine, and, in case of a shaft rupture of the rotor of the turbine, a radially externally situated segment of a last (seen in the direction of flow) rotor-side blade ring of the turbine working together with the, or with each, sensor element to generate an electrical signal corresponding to the shaft rupture.

Abstract: The present technology relates generally to a device for the detection of a shaft fracture in a rotor of a turbine, for example a medium pressure turbine such as a gas turbine, in particular an aircraft engine, whereby at least one stator-side sensor element is positioned downstream from the turbine in the area of a stator-side guide vane ring of another turbine in particular, a low pressure turbine; and whereby a radially inner section of the last rotor-side moving blade ring (as seen in the direction of flow) of the turbine cooperates with at least one sensor element directly and/or proximally in the event of a shaft fracture in the rotor of the turbine to generate an electric signal corresponding to the shaft fracture.

Abstract: 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.

Abstract: The invention relates to an arrangement for detecting a shaft break in a rotor of a first turbine (10), particularly a medium pressure turbine, of a gas turbine, particularly of an aircraft engine, whereby a second turbine (11), particularly a low pressure turbine, is positioned downstream of the first turbine (10), with an operator element (16) positioned between the rotor of the first turbine (10) and a stator of the second turbine (11) radially inwardly relative to a flow channel, and with a sensor element (21) guided in the stator of the second turbine (11), in order to convert a shaft break, detected by the radially inwardly positioned operator element (16), into an electrical signal and to transmit this electrical signal to a switching element which is positioned radially outwardly relative to the flow channel on a housing of the gas turbine.