Disassembly Method for a Gas Turbine

• US 20150343573A1
• Filed: 06/01/2015
• Published: 12/03/2015
• Est. Priority Date: 05/30/2014
• Status: Active Grant

• Current Assignee: Lufthansa Technik AG (Deutsche Lufthansa AG)
• Original Assignee: Lufthansa Technik AG (Deutsche Lufthansa AG)
• Inventors: ALBERT, RAINER, PINKOWSKY, TANJA, HOEHN, ANDINA, BOBSIEN, DENNIS
• Granted Patent: US 9,776,287 B2
• Time in Patent Office: Days
• US Class Current: 1/1
• CPC Class Codes: B23P 6/002 Repairing turbine components, e.g. moving or stationary blades, rotors, B23P6/045 takes precedence
• CPC Class Codes: F01D 17/06 responsive to speed
• CPC Class Codes: F01D 25/285 Temporary support structures, e.g. for testing, assembling, installing, repairing; Assembly methods using such structures
• CPC Class Codes: F05D 2230/68 using auxiliary equipment for lifting or holding
• CPC Class Codes: F05D 2230/70 Disassembly methods
• CPC Class Codes: F05D 2230/72 Maintenance
• CPC Class Codes: F05D 2230/80 Repairing, retrofitting or upgrading methods
• CPC Class Codes: F16C 43/00 Assembling bearings
• CPC Class Codes: G01P 21/02 of speedometers
• CPC Class Codes: Y10T 29/497 Pre-usage process, e.g., preloading, aligning
• CPC Class Codes: Y10T 29/49723 including reconditioning of part
• CPC Class Codes: Y10T 29/49732 by attaching repair preform, e.g., remaking, restoring, or patching
• CPC Class Codes: Y10T 29/53 Means to assemble or disassemble

Abstract

Disassembly method for gas turbines (11) for replacing and/or inspecting and/or repairing components arranged in a front bearing region (5) of the gas turbine (11),

• • the gas turbine (11) comprising at least one fan module (1), a gas turbine housing, a low-pressure system and a high-pressure system,
  • the low-pressure system comprising a low-pressure compressor (4), a low-pressure turbine (9), a connecting shaft (13), a stub shaft (8) and an N1 shaft (10),
  • the N1 shaft (10) being connected to the low-pressure compressor (4) via the stub shaft (8) and the connecting shaft (1),
  • the connecting shaft (13) being supported in the gas turbine housing via a first bearing unit (6), and
  • the stub shaft (8) being supported in the gas turbine housing via a second bearing unit (7), wherein
  • the disassembly method comprises at least the steps of:
• a) dismounting the fan module (1), and
• b) fixing the N1 shaft (10) in an axial direction relative to the gas turbine housing using a fixing device (14), and
• c) dismounting the stub shaft (8) using a guide device (15), the orientation of which relative to the gas turbine (11) in at least one spatial direction is determined by a component of the remaining gas turbine (11), this taking place after the N1 shaft (10) has been fixed and after the fan module (1) has been dismounted.

Claims

1. A method for disassembling a gas turbine for replacing and/or inspecting and/or repairing components arranged in a front bearing region of the gas turbine, comprising:

providing a fixing device;

providing a guide device;

providing a gas turbine, wherein the gas turbine comprises;

at least one fan module,

a gas turbine housing,

a low-pressure system, and

a high-pressure system,

wherein the low-pressure system comprises;

a low-pressure compressor,

a low-pressure turbine,

a connecting shaft,

a stub shaft, and

an N1 shaft,

wherein the N1 shaft is connected to the low-pressure compressor via the stub shaft and the connecting shaft,

wherein the connecting shaft is supported in the gas turbine housing via a first bearing unit,

wherein the stub shaft is supported in the gas turbine housing via a second bearing unit; and

dismounting the fan module;

fixing the N1 shaft in an axial direction relative to the gas turbine housing using the fixing device;

dismounting the stub shaft using the guide device,

wherein an orientation of the guide device relative to the gas turbine in at least one spatial direction is determined by a component of a portion of the gas turbine not yet dismounted,

wherein dismounting the stub shaft comprises dismounting the stub shaft after fixing the N1 shaft in an axial direction relative to the gas turbine housing using the fixing device and after dismounting the fan module.

2. The method according to claim 1,

wherein fixing the N1 shaft in the axial direction relative to the gas turbine housing using the fixing device comprises:

dismounting an exhaust gas cone; and

then

mounting the fixing device in the location of the exhaust gas cone; and

then

connecting the N1 shaft to the fixing device.

3. The method according to claim 1, further comprising:

providing a press device,

wherein dismounting the stub shaft using the guide device comprises;

releasing all connections between the stub shaft and the N1 shaft; and

then

releasing all connections between the stub shaft and the connecting shaft;

fitting the press device, wherein fitting the press device comprises connecting the press device to the N1 shaft and connecting the press device to the stub shaft; and

then

applying a first force to the stub shaft via the press device and applying a second force opposite to the first force to the N1 shaft via the press device,

wherein the first force and second force are oriented such that the stub shaft and the N1 shaft are moved apart in the axial direction.

4. The method according to claim 3, further comprising:

supporting the stub shaft in the radial direction via the guide device while applying the force to the stub shaft and to the N1 shaft via the press device.

5. The method according to claim 4,

wherein supporting the stub shaft in the radial direction via the guide device while applying the first force to the stub shaft via the press device and applying the second force to the N1 shaft via the press device comprises attaching the guide device to a gas turbine housing of the low-pressure compressor while applying the first force to the stub shaft via the press device and applying the second force to the N1 shaft via the press device.

6. The method according to claim 1, wherein dismounting the stub shaft using the guide device comprises dismounting the stub shaft and the low-pressure compressor.

7. The method according to claim 5, wherein dismounting the stub shaft using the guide device comprises dismounting the stub shaft and the low-pressure compressor.

8. The method according to claim 6,

wherein dismounting the stub shaft using the guide device comprises dismounting the first bearing unit and the connecting shaft,

wherein dismounting the first bearing unit and the connecting shaft comprises dismounting the first bearing unit and the connecting shaft after the low-pressure compressor has been dismounted.

9. The method according to claim 8, wherein following:

dismounting the fan module;

fixing the N1 shaft in an axial direction relative to the gas turbine housing using the fixing device; and

dismounting the stub shaft using the guide device, further comprising;

replacing at least one sub-system of a sensor system.

10. The method according to claim 9, further comprising:

providing a calibration device,

wherein replacing the at least one sub-system of the sensor system comprises;

calibrating the sensor system,

wherein the sensor system comprises a sensor and a clock generator,

wherein calibrating the sensor system comprises measuring a distance between the clock generator and a sensor head of the sensor via the calibration device.

11. The method according to claim 10,

wherein measuring the distance between the clock generator and a sensor head of the sensor via the calibration device comprises arranging the calibration device on the second bearing unit while measuring the distance between the clock generator and the sensor head of the sensor via the calibration device.

12. The method according to claim 1,

wherein dismounting the stub shaft using the guide device comprises dismounting the second bearing unit.

13. The method according to claim 11, wherein dismounting the stub shaft using the guide device comprises dismounting the second bearing unit.

14. The method according the claim 1,

wherein the fixing device comprises:

a fixing rod; and

a centering plate

wherein the fixing rod is configured to connect the N1 shaft to the fixing device,

wherein the centering plate is configured to fix the fixing rod, such that the centering plate is held in a defined position by a part of the gas turbine,

wherein the centering plate comprises at least one connector,

wherein the at least one connector is configured to attach the centering plate to the gas turbine in place of the exhaust gas cone,

wherein the guide device comprises;

a retraining device; and

a guide pipe,

wherein the retaining device is configured to be connected to a front part of the gas turbine,

wherein when mounted, the guide pipe is supported by a central hole in the retaining device,

wherein the guide pipe comprises a thread at one end,

wherein the guide pipe is configured to connect to the N1 shaft via the thread.

15. A fixing device, comprising:

a fixing rod; and

a centering plate,

wherein the fixing device is configured to be utilized in a method of disassembling a gas turbine for replacing and/or inspecting and/or repairing components arranged in a front bearing region of the gas turbine, wherein the method comprises;

providing a gas turbine, wherein the gas turbine comprises;

at least one fan module,

a gas turbine housing,

a low-pressure system, and

a high-pressure system,

wherein the low-pressure system comprises;

a low-pressure compressor,

a low-pressure turbine,

a connecting shaft,

a stub shaft, and

an N1 shaft,

wherein the N1 shaft is connected to the low-pressure compressor via the stub shaft and the connecting shaft,

wherein the connecting shaft is supported in the gas turbine housing via a first bearing unit, and

wherein the stub shaft is supported in the gas turbine housing via a second bearing unit;

dismounting the fan module;

fixing the N1 shaft in an axial direction relative to the gas turbine housing using the fixing device; and

dismounting the stub shaft using a guide device,

wherein an orientation of the guide device relative to the gas turbine in at least one spatial direction is determined by a component of a portion of the remaining gas turbine not yet dismounted,

wherein dismounting the stub shaft comprises dismounting the stub shaft after fixing the N1 shaft in an axial direction relative to the gas turbine housing using a fixing device and after dismounting the fan module,

wherein the fixing rod is configured to connect the N1 shaft to the fixing device,

wherein the centering plate is configured to fix the fixing rod, such that the centering plate is held in a defined position by a part of the gas turbine,

wherein the centering plate comprises at least one connector,

wherein the at least one connector is configured to attach the centering plate to the gas turbine in place of the exhaust gas cone.

16. A guide device, comprising:

a retaining device; and

a guide pipe,

wherein the guide device is configured to be utilized in a method of disassembling a gas turbine,

wherein the method comprises;

providing a gas turbine, wherein the gas turbine comprises;

at least one fan module,

a gas turbine housing,

a low-pressure system, and

a high-pressure system,

wherein the low-pressure system comprises;

a low-pressure compressor,

a low-pressure turbine,

a connecting shaft,

a stub shaft, and

an N1 shaft,

wherein the N1 shaft is connected to the low-pressure compressor via the stub shaft and the connecting shaft,

wherein the connecting shaft is supported in the gas turbine housing via a first bearing unit, and

wherein the stub shaft is supported in the gas turbine housing via a second bearing unit;

dismounting the fan module;

fixing the N1 shaft in an axial direction relative to the gas turbine housing using the fixing device;

dismounting the stub shaft using a guide device,

wherein an orientation of the guide device relative to the gas turbine in at least one spatial direction is determined by a component of a portion of the remaining gas turbine not yet dismounted,

wherein dismounting the stub shaft comprises dismounting the stub shaft after fixing the N1 shaft in an axial direction relative to the gas turbine housing using a fixing device and after dismounting the fan module; and

supporting the stub shaft in the radial direction via the guide device while applying the force to the stub shaft and to the N1 shaft via the press device,

wherein the retaining device is configured to be connected to a front part of the gas turbine,

wherein when mounted, the guide pipe is supported by a central hole in the retaining device,

wherein the guide pipe comprises a thread at one end,

wherein the guide pipe is configured to connect to the N1 shaft via the thread.

17. The guide device according to claim 16,

wherein supporting the stub shaft in the radial direction via the guide device while applying the first force to the stub shaft via the press device and applying the second force to the N1 shaft via the press device comprises attaching the guide device to a gas turbine housing of the low-pressure compressor while applying the first force to the stub shaft via the press device and applying the second force to the N1 shaft via the press device.

18. A calibration device, comprising:

a first outer face; and

a second outer face,

wherein the calibration device is configured to be utilized in a method of disassembling a gas turbine for replacing and/or inspecting and/or repairing components arranged in a front bearing region of the gas turbine,

wherein the method comprises;

providing a gas turbine, wherein the gas turbine comprises;

at least one fan module,

a gas turbine housing,

a low-pressure system, and

a high-pressure system,

wherein the low-pressure system comprises;

a low-pressure compressor,

a low-pressure turbine,

a connecting shaft,

a stub shaft, and

an N1 shaft,

wherein the N1 shaft is connected to the low-pressure compressor via the stub shaft and the connecting shaft,

wherein the connecting shaft is supported in the gas turbine housing via a first bearing unit, and

wherein the stub shaft is supported in the gas turbine housing via a second bearing unit;

dismounting the fan module;

fixing the N1 shaft in an axial direction relative to the gas turbine housing using a fixing device;

dismounting the stub shaft using a guide device,

wherein an orientation of the guide device relative to the gas turbine in at least one spatial direction is determined by a component of a portion of the remaining gas turbine not yet dismounted,

wherein dismounting the stub shaft comprises dismounting the stub shaft after fixing the N1 shaft in an axial direction relative to the gas turbine housing using a fixing device and after dismounting the fan module,

wherein replacing the at least one sub-system of the sensor system comprises;

calibrating the sensor system,

wherein the sensor system comprises a sensor and a clock generator,

wherein calibrating the sensor system comprises measuring a distance between the clock generator and a sensor head of the sensor is via the calibration device,

wherein a radius of the first outer face corresponds to a radius of a clock generator of a first sensor system,

wherein the second outer face corresponds in shape to an inner face of the second bearing unit.

19. The calibration device according to claim 18,

wherein measuring the distance between the clock generator and the sensor head of the sensor via the calibration device comprises arranging the calibration device on the second bearing unit while measuring the distance between the clock generator and the sensor head of the sensor via the calibration device.

20. The calibration device according to claim 18,

wherein the calibration device comprises an annular projection,

wherein at least one gap is provided in the annular projection, to allow the calibration device to move past obstacles while moving the calibration device into and/or out of a calibration position.