Gas turbine engine configured for modular assembly/disassembly and method for same
A method for assembling and disassembling a module of gas turbine engine is provided, along with a gas turbine engine configured for modular assembly/disassembly. The engine includes a first shaft and a second shaft. The first shaft connects a compressor section and a first turbine section. The second shaft is connected to the second turbine section. The first and second shafts are rotatable about the engine rotational axis. The second shaft and the second turbine section together form a module that can be assembled, or disassembled, or both from the engine.
1. A method of disassembling a gas turbine engine, comprising the steps in sequence of:
providing a gas turbine engine having a rotational axis, a compressor section, a first turbine section, a second turbine section, a first shaft connecting the compressor section and the first turbine section, which first shaft is rotatable about the rotational axis, a second shaft connected to the second turbine section, which second shaft is rotatable about the rotational axis, a shaft spacer, and a first shaft nut;
removing the shaft spacer;
moving the second shaft and the second turbine section axially forward as a module to a disassembly position;
uncoupling the first shaft nut; and
removing the second shaft and the second turbine section as a module axially rearward from the gas turbine engine.
2. The method of claim 1 , wherein the engine further comprises a frame spacer, and the method further comprising the step of removing the frame spacer prior to moving the second shaft and the second turbine section module axially forward.
3. The method of claim 2 , wherein the first shaft nut includes a castellated end surface, and the second shaft includes a flange having a castellated distal end surface that mates with the castellated end surface of the first shaft nut, and the method further includes engaging the castellated end surfaces of the first shaft nut and the second shaft, and rotating the second shaft to rotate the first shaft nut.
4. The method of claim 1 , wherein the engine further comprises a third shaft connecting a second compressor stage connected to a third turbine section, which third turbine section includes a rotor stage; and
wherein the step of removing the second shaft and the second turbine section as a module from the gas turbine engine, includes removing the third turbine rotor stage as part of the module.
5. The method of claim 1 , wherein the engine further comprises a first frame having an attachment flange, a second frame having an attachment flange, and a frame spacer, which frame spacer is configured to be disposed between the attachment flanges; and
wherein the method further comprises the step of removing the flange spacer prior to moving the second turbine section and the second shaft axially forward within the engine to the disassembly position.
6. The method of claim 5 , wherein the engine further comprises an outer radial seal and an inner radial seal, and wherein the outer radial seal and the inner radial seal are respectively positioned so that each assumes a non-interfering configuration when the second shaft and the second turbine section are moved axially forward as a module to the disassembly position.
7. The method of claim 1 , wherein the engine further comprises a gearbox shaft connected to the second shaft.