TURBINE ROTOR LOCKING ASSEMBLY AND METHOD

• US 20200131909A1
• Filed: 10/29/2018
• Published: 04/30/2020
• Est. Priority Date: 10/29/2018
• Status: Active Grant

• Current Assignee: Rtx Corporation
• Original Assignee: United Technologies Corporation (Rtx Corporation)
• Inventors: Eastwood, Jonathan Jeffery, Juh, Christopher M.
• Granted Patent: US 11,143,032 B2
• Time in Patent Office: Days
• CPC Class Codes: B25B 23/0085 Counterholding devices
• CPC Class Codes: B25B 27/14 for assembling objects other than by press fit or detaching same
• CPC Class Codes: F01D 25/285 Temporary support structures, e.g. for testing, assembling, installing, repairing; Assembly methods using such structures
• CPC Class Codes: F01D 5/025 Fixing blade carrying members on shafts attachment of a member on a shaft in general F16D1/06; for non-positive displacement pumps F04D29/00
• 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: F05D 2220/329 in helicopters
• CPC Class Codes: F05D 2230/60 Assembly methods
• 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 2240/60 Shafts
• CPC Class Codes: F05D 2260/30 Retaining components in desired mutual position
• CPC Class Codes: F16B 31/02 for indicating the attainment of a particular tensile load or limiting tensile load apparatus for, or method of, determining value of torque or twisting moment for tightening a nut or other member similarly stressed G01L5/24
• CPC Class Codes: F16B 39/28 by special members on, or shape of, the nut or bolt F16B39/26 takes precedence; locknuts F16B39/12
• CPC Class Codes: F16D 1/0805 with radial clamping due to deformation of a resilient body or a body of fluid F16D1/091 takes precedence; elastic couplings F16D3/80; fluid pressure clutches F16D25/04

Abstract

A power turbine rotor locking assembly including a rotor shaft. The assembly also includes an aft rotor stage surrounding the rotor shaft. The assembly further includes a locknut torqued to the rotor shaft. The assembly yet further includes a plurality of torque resistance features located on an aft side of the aft rotor stage. The assembly also includes a tooling fixture having a plurality of corresponding torque resistance features, the corresponding torque resistance features selectively engageable with the torque resistance features of the aft rotor stage to resist circumferential movement during assembly and disassembly of the locknut with the rotor shaft.

Claims

1. A power turbine rotor locking assembly comprising:

a rotor shaft;

an aft rotor stage surrounding the rotor shaft;

a locknut torqued to the rotor shaft;

a plurality of torque resistance features located on an aft side of the aft rotor stage; and

a tooling fixture having a plurality of corresponding torque resistance features, the corresponding torque resistance features selectively engageable with the torque resistance features of the aft rotor stage to resist circumferential movement during assembly and disassembly of the locknut with the rotor shaft.

2. The power turbine rotor locking assembly of claim 1, wherein each of the plurality of torque resistance features of the aft rotor stage is a tab having a first circumferential side and a second circumferential side, wherein each of the corresponding torque resistance features is a slot.

3. The power turbine rotor locking assembly of claim 1, wherein the number of torque resistance features ranges from two (2) to eight (8).

4. The power turbine rotor locking assembly of claim 1, wherein the torque resistance features are circumferentially spaced from each other in an equidistant arrangement.

5. The power turbine rotor locking assembly of claim 1, wherein the torque resistance features are circumferentially spaced from each other in a non-equidistant arrangement.

6. The power turbine rotor locking assembly of claim 1, wherein the tooling fixture is an annular member having a radially outer surface and a radially inner surface, the radially inner surface defining a central aperture having a diameter greater than a diameter of the locknut and the rotor shaft.

7. The power turbine rotor locking assembly of claim 6, wherein the corresponding torque resistance features are located proximate the radially outer surface of the tooling fixture.

8. A gas turbine engine comprising:

a gas generator portion; and

a power turbine section arranged fluidly downstream from the gas generator portion, the power turbine mechanically disconnected from the gas generator portion, the power turbine comprising;

a rotor shaft;

an aft rotor stage surrounding the rotor shaft, the aft rotor stage defining a circumferential cutout on an aft side of the aft rotor stage, the circumferential cutout at least partially defined by a flange;

a locknut torqued to the rotor shaft;

a plurality of radial tabs extending inwardly from the flange; and

a tooling fixture having a plurality of slots selectively engageable with the radial tabs of the aft rotor stage to resist circumferential movement during assembly and disassembly of the locknut with the rotor shaft.

9. The gas turbine engine of claim 8, wherein the number of radial tabs ranges from two (2) to eight (8).

10. The gas turbine engine of claim 8, wherein the radial tabs are circumferentially spaced from each other in an equidistant arrangement.

11. The gas turbine engine of claim 8, wherein the radial tabs are circumferentially spaced from each other in a non-equidistant arrangement.

12. The gas turbine engine of claim 8, wherein the tooling fixture is an annular member having a radially outer surface and a radially inner surface, the radially inner surface defining a central aperture having a diameter greater than a diameter of the locknut and the rotor shaft.

13. The gas turbine engine of claim 12, wherein the slots are located proximate the radially outer surface of the tooling fixture.

14. The gas turbine engine of claim 8, wherein the gas turbine engine is located on a helicopter.

15. A method of circumferentially locking a turbine rotor of a power turbine comprising:

engaging a plurality of slots of a tooling fixture with a plurality of tabs of an aft side of an aft rotor stage; and

torqueing a locknut to assemble or disassemble the locknut from a rotor shaft of the power turbine.