GAS TURBINE ENGINE CONFIGURED FOR MODULAR ASSEMBLY/DISASSEMBLY AND METHOD FOR SAME

• US 20150369123A1
• Filed: 06/19/2015
• Published: 12/24/2015
• Est. Priority Date: 06/20/2014
• Status: Active Grant

• Current Assignee: Rtx Corporation
• Original Assignee: United Technologies Corporation (Raytheon Technologies Corporation d/b/a RTX)
• Inventors: Hanrahan, Paul R.
• Granted Patent: US 10,094,277 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 5/026 Shaft to shaft connections
• CPC Class Codes: F01D 5/066 Connecting means for joining rotor-discs or rotor-elements together, e.g. by a central bolt, by clamps
• CPC Class Codes: F02C 3/10 with another turbine driving an output shaft but not driving the compressor
• CPC Class Codes: F02C 3/107 with two or more rotors connected by power transmission
• CPC Class Codes: F05B 2230/70 Disassembly methods
• CPC Class Codes: F05B 2230/80 Repairing, retrofitting or upgrading methods
• CPC Class Codes: F05D 2220/32 in gas turbines
• CPC Class Codes: F05D 2230/51 in a modular way, e.g. using several identical or complementary parts or features
• CPC Class Codes: F05D 2230/70 Disassembly methods
• CPC Class Codes: F05D 2230/80 Repairing, retrofitting or upgrading methods
• CPC Class Codes: F05D 2250/182 crenellated, notched
• CPC Class Codes: F05D 2260/30 Retaining components in desired mutual position
• CPC Class Codes: F05D 2260/31 Retaining bolts or nuts
• CPC Class Codes: Y10T 29/4924 Scroll or peristaltic type

Abstract

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 faun a module that can be assembled, or disassembled, or both from the engine.

Claims

1. A gas turbine engine having a rotational axis, comprising:

a first shaft connecting a compressor section and a first turbine section, which first shaft is rotatable about the engine rotational axis; and

a second shaft connected to a second turbine section, which second shaft is rotatable about the engine rotational axis;

wherein the second shaft and the second turbine section together form a module that can be assembled, or disassembled, or both from the engine; and

wherein the engine is adapted to permit the second shaft and the second turbine section to selectively move axially forward within the engine to a disassembly position.

2. The engine of claim 1, wherein the engine includes a shaft spacer, which shaft spacer is removable to permit the second shaft and the second turbine section module to selectively move axially forward within the engine to the disassembly position.

3. The engine of claim 1, wherein the engine includes a frame spacer that is removable to permit the second shaft and the second turbine section module to selectively move axially forward within the engine to the disassembly position.

4. The engine of claim 1, further comprising an inner radial seal configured to assume a non-interfering configuration in the disassembly position.

5. The engine of claim 1, further comprising an outer seal member configured to assume a non-interfering configuration in the disassembly position.

6. The engine of claim 1, further comprising;

a first shaft nut having a castellated end surface; and

a flange attached to the second shaft having a castellated distal end surface that mates with the castellated end surface of the first shaft nut;

wherein in the disassembly position, the castellated end surface of the first shaft nut is engaged with the castellated distal end surface of the flange.

7. The engine of claim 1 further comprising 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 second shaft, the second turbine section, and the third turbine rotor stage are included in the module that can be assembled, or disassembled, or both from the engine.

8. The engine of claim 7, further comprising 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 which flange spacer is removable to permit the second turbine section and the second shaft to selectively move axially forward within the engine to the disassembly position.

9. The engine of claim 7, further comprising a gearbox shaft connected to the second shaft.

10. The engine of claim 7, further comprising;

a first shaft nut having a castellated end surface; and

a flange attached to the second shaft having a castellated distal end surface that mates with the castellated end surface of the first shaft nut;

wherein in the disassembly position, the castellated end surface of the first shaft nut is engaged with the castellated distal end surface of the flange.

11. The engine of claim 10, wherein the flange attached to the second shaft is L-shaped, with a first leg and a second leg, wherein the second leg includes the castellated distal end surface.

12. The engine of claim 11, wherein the first leg extends radially outwardly from an outer diameter surface of the second shaft, and the second leg extends axially outwardly from the first leg, and a relief channel is disposed between the second leg and the outer diameter surface of the second shaft.

13. The engine of claim 12, wherein the second leg includes an inner radial surface, and a ramp surface extending between the distal end surface and the inner radial surface.

14. A method of disassembling a gas turbine engine, comprising the steps 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 engine rotational axis, a second shaft connected to the second turbine section, which second shaft is rotatable about the engine 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 from the gas turbine engine.

15. The method of claim 14, 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.

16. The method of claim 15, 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.

17. The method of claim 14, 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.

18. The method of claim 14, 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.

19. The method of claim 18, 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.

20. The method of claim 14, wherein the engine further comprises a gearbox shaft connected to the second shaft.