Method and device for reducing the speed in the event of breakage of a gas turbine engine turbine shaft
View Patent ↗A device for detecting breakage of a gas turbine engine shaft and for reducing the rotational speed of the turbine includes a rotor of a turbine or of a first stage turbine driving the shaft. The rotor has a turbine disk with a rim. A stator that the rotor rotates inside or a nozzle guide vanes assembly of the first turbine stage is provided. A temperature sensor is positioned on the stator or on the nozzle guide vanes assembly, immediately downstream of the rim. The sensor is located to sense temperature on a portion of the stator that contacts the rotor, or on a portion of the nozzle guide vanes assembly that contacts the first stage rotor, in the event of shaft breakage. An engine fuel control member connects to the sensor and can interrupt fuel supply to the engine, when the sensor emits a signal above a predetermined threshold.
1. A device for detecting breakage of a shaft of a turbine in a gas turbine engine and for reducing the rotational speed of the turbine, comprising:
a stator,
a turbine rotor driving the shaft and rotating inside the stator, the turbine rotor including a turbine disk provided with a rim,
a temperature sensor sensing a temperature on the stator, the temperature sensor positioned on the stator immediately downstream of the rim, the temperature sensor located to sense the temperature on a portion of the stator that contacts the rotor in the event of shaft breakage, and
an engine fuel control member connected to the temperature sensor, the engine fuel control member interrupting fuel supply to the engine when the temperature sensor emits a signal that is above a predetermined threshold.
2. The device as claimed in claim 1 , in which the temperature sensor is a thermocouple.
3. The device as claimed in claim 1 , further comprising:
a plurality of temperature sensors that are thermocouples.
4. The device as claimed in claim 2 , further comprising:
a thermocouple probe fixed to the stator by means of a coating.
5. The device as claimed in claim 3 , further comprising a plurality of thermocouple probes fixed to the stator by means of a coating.
6. The device as claimed in claim 4 , further comprising:
thermocouple wires connecting the thermocouple probe to the engine fuel control member, the thermocouple wires guided through a cavity of a radial arm of an exhaust casing.
7. The device as claimed in claim 4 , in which the coating is a mass, and the mass is a material selected from the group consisting of a ceramic based on zirconia, a ceramic based on alumina, an alloy based on NiCoAl, and an alloy based on NiAl.
8. The device as claimed in claim 7 , in which the mass has a thickness of 2 to 4 mm.
9. The device as claimed in claim 1 , in which the engine fuel control member is a full authority digital electronic control (FADEC).
10. The device as claimed in claim 1 , in which the predetermined threshold is an exhaust gas temperature margin, defined as the difference between a temperature at which the engine has to be run in order to obtain a desired thrust and a certified temperature.
11. A device for detecting breakage of a shaft of a turbine in a gas turbine engine and for reducing the rotational speed of the turbine, comprising:
a first turbine stage,
a nozzle guide vanes assembly of the first turbine stage,
a first stage turbine rotor driving the shaft, the first stage turbine rotor including a turbine disk provided with a rim,
a temperature sensor sensing a temperature on the nozzle guide vanes assembly, the temperature sensor positioned on the nozzle guide vanes assembly immediately downstream of the rim, the temperature sensor located to sense the temperature on a portion of the nozzle guide vanes assembly that contacts the first stage turbine rotor in the event of shaft breakage, and
an engine fuel control member connected to the temperature sensor, the engine fuel control member interrupting fuel supply to the engine when the temperature sensor emits a signal that is above a predetermined threshold.
12. The device as claimed in claim 11 , in which the temperature sensor is a thermocouple.
13. The device as claimed in claim 11 , further comprising:
a plurality of temperature sensors that are thermocouples.
14. The device as claimed in claim 12 , further comprising:
a thermocouple probe fixed to the nozzle guide vanes assembly by means of a coating.
15. The device as claimed in claim 13 , further comprising:
a plurality of thermocouple probes fixed to the nozzle guide vanes assembly by means of a coating.
16. The device as claimed in claim 14 , further comprising:
thermocouple wires connecting the thermocouple probe to the engine fuel control member, the thermocouple wires guided through a cavity of a radial arm.
17. The device as claimed in claim 14 , in which the coating is a material selected from the group consisting of a ceramic based on zirconia, a ceramic based on alumina, an alloy based on NiCoAl, and an alloy based on NiAl.
18. The device as claimed in claim 17 , in which the material has a thickness of 2 to 4 mm.
19. The device as claimed in claim 11 , in which the engine fuel control member is a full authority digital electronic control (FADEC).
20. The device as claimed in claim 11 , in which the predetermined threshold is a gas temperature margin, defined as the difference between a temperature at which the engine has to be run in order to obtain a desired thrust and a certified temperature.