Gas turbine engine configured for modular assembly/disassembly and method for same

• US 10,094,277 B2
• Filed: 06/19/2015
• Issued: 10/09/2018
• 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.
• Primary Examiner(s): Rivera, Carlos A
• Assistant Examiner(s): THOMAS, KYLE ROBERT
• Application Number:
  US14/745,158
• Publication Number:
  US 20150369123A1
• Time in Patent Office: 1,208 Days
• 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 form 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 the first shaft is rotatable about the rotational axis;

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

a shaft nut, having a castellated end surface, is threaded to the first shaft by a threaded surface of the shaft nut to secure the first turbine section; and

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

wherein the second shaft, and the second turbine section together form a module that is adapted to be assembled with the gas turbine engine and disassembled from the gas turbine engine;

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

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

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.

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

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

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

a third shaft connecting a second compressor section to a third turbine section, which the third turbine section includes a rotor stage;

a shaft nut, having a castellated end surface, is threaded to the first shaft by a threaded surface of the shaft nut to secure the first turbine section; and

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

wherein the second shaft, the second turbine section, and the rotor stage of the third turbine section together form a module that is adapted to be assembled with the gas turbine engine and disassembled from the as turbine engine;

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

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

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.

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

4. The gas turbine engine of claim 2, wherein the gas turbine engine includes a frame spacer that is removable to permit the module to selectively move axially forward within the gas turbine engine to the disassembly position.

5. The gas turbine engine of claim 2, further comprising an inner radial seal configured to assume a non-interfering configuration in the disassembly position.

6. The gas turbine engine of claim 2, further comprising an outer seal member configured to assume a non-interfering configuration in the disassembly position.

7. The gas turbine engine of claim 2, further comprising a first frame having an attachment flange, a second frame having an attachment flange, and a frame spacer, which the frame spacer is configured to be disposed between the attachment flanges, and which the flange spacer is removable to permit the second turbine section and the second shaft to selectively move axially forward within the gas turbine engine to the disassembly position.

8. The gas turbine engine of claim 2, further comprising a gearbox shaft connected to the second shaft.

9. The gas turbine engine of claim 2, wherein the first leg extends radially outward from an outer diameter surface of the second shaft, and the second leg extends axially outward from the first leg, and a relief channel is disposed between the second leg and the outer diameter surface of the second shaft.

10. The gas turbine engine of claim 9, wherein the second leg includes an inner radial surface, and a ramp surface extending between the castellated distal end surface and the inner radial surface.

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

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

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

a third shaft connecting a second compressor section to a third turbine section, which the third turbine section includes a rotor stage;

a shaft nut, having a castellated end surface, is threaded to the first shaft by a threaded surface of the shaft nut to secure the first turbine section; and

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

wherein the second shaft, the second turbine section, and the third turbine rotor stage together form a module that is adapted to be assembled with the gas turbine engine and disassembled from the gas turbine engine; and

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.