Disassembly Method for a Gas Turbine
First Claim
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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, anda high-pressure system,wherein the low-pressure system comprises;
a low-pressure compressor,a low-pressure turbine,a connecting shaft,a stub shaft, andan 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.
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Accused Products
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.
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Citations
20 Claims
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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:
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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. - View Dependent Claims (2, 3, 4, 5, 6, 7, 8, 9, 10, 11, 12, 13, 14)
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15. A fixing device, comprising:
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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.
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16. A guide device, comprising:
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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. - View Dependent Claims (17)
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18. A calibration device, comprising:
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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. - View Dependent Claims (19, 20)
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Specification