# US 11,306,620 B2 · Method of reassembling a gas turbine engine

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- Number: US 11,306,620 B2
- Document ID: US11306620B2
- Status: Granted
- Kind: B2
- Application number: 16/941,754
- Filed: 2020-07-29
- Published: 2020-12-03
- Granted: 2022-04-19
- Earliest claimed: 2013-11-19
- Assignees: ROLLS-ROYCE plc
- Applicants: ROLLS-ROYCE plc
- Inventors: Christopher Richard Hallam; Jonathan Paul Taylor
- Web page: https://patentgrep.com/patent/US11306620B2

## CPC

- F01D 25/285: {Temporary support structures, e.g. for testing, assembling, installing, repairing; Assembly methods using such structures}
- B23P 15/00: Making specific metal objects by operations not covered by a single other subclass or a group in this subclass
- B23P 19/04: for assembling or disassembling parts
- B64F 5/50: Handling or transporting aircraft components
- F02C 7/20: Mounting or supporting of plant; Accommodating heat expansion or creep
- F16M 11/42: with arrangement for propelling the support {stands on wheels}
- B23P 6/002: {Repairing turbine components, e.g. moving or stationary blades, rotors, (B23P6/045 takes precedence)}
- Y10T 29/49318: Repairing or disassembling
- Y10T 29/49721: with disassembling
- Y10T 29/49895: Associating parts by use of aligning means [e.g., use of a drift pin or a "fixture"]
- F01D: NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES (machines or engines for liquids F03; non-positive displacement pumps F04D)
- B23P: METAL-WORKING NOT OTHERWISE PROVIDED FOR; COMBINED OPERATIONS; UNIVERSAL MACHINE TOOLS (arrangements for copying or controlling B23Q)
- B64F: GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLY ADAPTED FOR USE IN CONNECTION WITH AIRCRAFT; DESIGNING, MANUFACTURING, ASSEMBLING, CLEANING, MAINTAINING OR REPAIRING AIRCRAFT, NOT OTHERWISE PROVIDED FOR; HANDLING, TRANSPORTING, TESTING OR INSPECTING AIRCRAFT COMPONENTS, NOT OTHERWISE PROVIDED FOR
- F02C: GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS (construction of turbines F01D; jet-propulsion plants F02K; construction of compressors or fans F04; generating combustion products of high pressure or high velocity F23R; using gas turbines in compression refrigeration plants F25B11/00)
- F16M: FRAMES, CASINGS OR BEDS OF ENGINES, MACHINES OR APPARATUS, NOT SPECIFIC TO ENGINES, MACHINES OR APPARATUS PROVIDED FOR ELSEWHERE; STANDS; SUPPORTS
- Y10T: TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION

## Abstract

A method of reassembling a gas turbine engine including steps to support a core engine on a core stand and support a fan case on a fan stand that includes a base frame coupled a fan case frame by a hinge. The fan case frame is arranged to (i) rotate about an axis of the hinge between abutting the base frame and being perpendicular to the base frame, and (ii) tilt about a yaw axis perpendicular to the hinge, which is located in a plane of the fan case frame. The method includes rotating and tilting the fan case frame to align the fan case and core engine, translating at least one of the core engine and the fan case into axial abutment, coupling the fan case and the core engine to reassemble the gas turbine engine, and decoupling the fan case from the fan stand.

## Claims

### Claim 1

A method of reassembling a gas turbine engine, the gas turbine engine including a core engine and a fan case, the method comprising steps to:
support a core engine on a core stand;
support a fan case on a fan stand, the fan stand including:
a base frame; and
a fan case frame coupled to the base frame at one edge by a hinge, the fan case frame being arranged to: i) rotate about an axis of the hinge between abutting the base frame and being perpendicular to the base frame, and ii) tilt about a yaw axis perpendicular to the hinge, the yaw axis being located in a plane of the fan case frame, the fan case frame including a coupling arrangement configured to couple, in use, a fan case of a gas turbine engine to the fan case frame, the coupling arrangement being arranged to rotate about a roll axis perpendicular to the axis of the hinge, the roll axis being disposed through the plane of the fan case frame and being centrally located through the coupling arrangement;
rotate and tilt the fan case frame to align the fan case and core engine;
translate at least one of the core engine and the fan case into axial abutment;
couple the fan case and the core engine to reassemble the gas turbine engine; and
decouple the fan case from the fan stand.

### Claim 2 (depends on 1)

The method of reassembling as claimed in claim 1, further comprising a step to translate the gas turbine engine axially away from the fan stand.

### Claim 3 (depends on 1)

The method of reassembling as claimed in claim 1, further comprising a step to reassemble fan blades and a spinner to the gas turbine engine.