An apparatus for a gas turbine engine comprises a spool lock for locking a compressor spool and a lift for removing a rotor from the compressor spool. The spool lock comprises an outer ring configured for attachment to a compressor case of the gas turbine engine, an inner ring configured to support
An apparatus for a gas turbine engine comprises a spool lock for locking a compressor spool and a lift for removing a rotor from the compressor spool. The spool lock comprises an outer ring configured for attachment to a compressor case of the gas turbine engine, an inner ring configured to support a compressor spool within the compressor case, and a web extending between the outer ring and the inner ring. The lift comprises a beam configured for attachment to a flange of the gas turbine engine, a support strut configured to support the beam above the compressor spool, and a hoist configured to support the rotor for removal from the compressor spool.
대표청구항▼
1. An apparatus for a gas turbine engine, the apparatus comprising: a spool lock for locking a compressor spool of the gas turbine engine, the spool lock comprising an outer ring configured for attachment to a compressor case of the gas turbine engine, an inner ring configured to support the compres
1. An apparatus for a gas turbine engine, the apparatus comprising: a spool lock for locking a compressor spool of the gas turbine engine, the spool lock comprising an outer ring configured for attachment to a compressor case of the gas turbine engine, an inner ring configured to support the compressor spool within the compressor case, and a web extending between the outer ring and the inner ring; anda lift for removing a rotor from the compressor spool, the lift comprising: a beam configured for attachment to a flange of the gas turbine engine;a support strut configured to attach to the flange to support the beam above the compressor spool; anda hoist configured to support the rotor for removal from the compressor spool. 2. The apparatus of claim 1, wherein the hoist comprises a lift jig configured to support the rotor from the beam by inserting the lift jig into a blade retention slot in the rotor. 3. The apparatus of claim 2, wherein the lift jig comprises a dovetail and a stop configured to axially position the lift jig with respect to the fan rotor when the dovetail is inserted into the blade retention slot. 4. The apparatus of claim 1, wherein the beam is suspended from a flush attachment member attached to the flange. 5. The apparatus of claim 4, wherein the support strut is pivotally attached to the beam. 6. The apparatus of claim 4, wherein the support strut is pivotally attached to a strut coupler configured for flush attachment to the flange. 7. The apparatus of claim 1, wherein the outer ring of the spool lock comprises bolt holes spaced to attach the spool lock to the compressor case using existing bolt holes in the compressor case. 8. The apparatus of claim 7, wherein the inner ring of the spool lock comprises bolt holes spaced to lock the compressor spool against rotation using existing bolt holes in the compressor spool. 9. A system comprising: a gas turbine engine, the gas turbine engine including: a spool assembly positioned within a compressor casing;a fan disk rotationally coupled to the spool assembly; anda casing coaxially disposed about the fan disk, the casing having a flange;a spool lock for locking the spool assembly to the compressor casing, the spool lock comprising an outer ring attached to the compressor casing, an inner ring attached to the spool assembly and a web connecting the outer ring to the inner ring; anda lift for supporting the fan disk, the lift comprising a beam and two support struts attached to the flange to support the beam above the spool assembly, the beam comprising a hoist configured to support the fan disk. 10. The system of claim 9, wherein the support struts are pivotally attached to the beam. 11. The system of claim 10, wherein the support struts support the beam substantially parallel to a rotational axis of the spool assembly. 12. The system of claim 9, wherein the spool assembly comprises a booster spool, the booster spool comprising a fan shaft and a compressor stage. 13. The system of claim 12, wherein the web comprises holes for reducing weight and for providing access to the compressor stage. 14. The system of claim 13, wherein the spool lock comprises bolt holes for bolting the outer ring to the compressor casing and for bolting the inner ring to the spool assembly. 15. The system of claim 9, wherein the hoist comprises a lift jig configured to support the fan disk by insertion into a blade retention slot. 16. A maintenance method for a gas turbine engine, the method comprising: attaching a lift to a flange of a gas turbine engine, the lift comprising a beam and a support strut pivotally attached to the beam;aligning the beam above the compressor spool by attaching the support strut to the flange;attaching a spool lock to the gas turbine engine, the spool lock comprising an outer ring, an inner ring and a web connecting the inner ring to the outer ring;locking a compressor spool of the gas turbine engine by connecting the inner ring to the compressor spool and the outer ring to a stationary casing; andsupporting a fan disk from the beam. 17. The method of claim 16, further comprising removing the fan disk from the compressor spool. 18. The method of claim 17, further comprising translating the fan disk axially along the beam. 19. The method of claim 18, further comprising installing the fan disk onto the compressor spool. 20. The method of claim 16, wherein aligning the beam above the compressor spool comprises pivotally attaching the support strut to the flange.
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이 특허에 인용된 특허 (7)
Monsarrat William G. (Willimantic CT) Brodell Robert F. (Marlborough CT), Engine modularity.
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