METHOD OF IMMOBILIZING LOW PRESSURE SPOOL AND LOCKING TOOL THEREFORE

• US 20140255147A1
• Filed: 03/11/2013
• Published: 09/11/2014
• Est. Priority Date: 03/11/2013
• Status: Active Grant

• Current Assignee: Pratt & Whitney Canada Corporation (Raytheon Technologies Corporation d/b/a RTX)
• Original Assignee: Pratt & Whitney Canada Corporation (Raytheon Technologies Corporation d/b/a RTX)
• Inventors: ROOT, Richard, BINETTE, Hugo
• Granted Patent: US 9,234,441 B2
• Time in Patent Office: Days
• US Class Current: 415/1
• CPC Class Codes: F01D 25/002 Cleaning of turbomachines
• CPC Class Codes: F01D 25/285 Temporary support structures, e.g. for testing, assembling, installing, repairing; Assembly methods using such structures
• CPC Class Codes: F05D 2230/72 Maintenance

Abstract

A method of immobilizing a low pressure spool assembly including maintaining a body of the locking tool in the annular gas path, attaching a securing portion of the body across an aperture defined through an annular wall delimiting the gas path; positioning a stop connected to the body of the locking tool into a rotary path of a given one of the sets of blades of the low pressure spool assembly; and rotating the high pressure spool assembly thereby biasing a blade of the given set of blades of the low pressure spool assembly against the stop, thereby immobilizing the low pressure spool assembly. A locking tool and a method of performing engine maintenance are also provided.

Claims

1. A method of immobilizing a low pressure spool assembly of a gas turbine engine with a locking tool, the gas turbine engine also having a high pressure spool assembly, the high pressure spool assembly and the low pressure spool assembly being independently rotatable around a main axis and each having a plurality of rotors, each rotor having a set of blades extending across a corresponding portion of an annular gas path, the gas turbine engine further having an annular wall delimiting the annular gas path, the method comprising:

while maintaining a body of the locking tool in the annular gas path, attaching a securing portion of the body across an aperture defined through an annular wall delimiting the gas path;

positioning a stop connected to the body of the locking tool into a rotary path of a given one of the sets of blades of the low pressure spool assembly;

rotating the high pressure spool assembly to bias a blade of the given set of blades of the low pressure spool assembly against the stop, thereby immobilizing the low pressure spool assembly.

2. The method as defined in claim 1 further comprising:

removing a sensor from a sensor attachment associated to the aperture;

fastening an adapter portion of the locking tool to the sensor attachment;

wherein attaching the securing portion of the body across the aperture includes attaching the securing portion of the body to the adapter portion.

3. The method as defined in claim 1 wherein said given one of the sets of blades of the low pressure spool assembly is a set of blades of a fan of the gas turbine engine, and wherein the aperture is upstream of the fan.

4. The method as defined in claim 1 further comprising performing maintenance to the gas turbine engine while the high pressure spool assembly is rotated and the low pressure spool is immobilized.

5. The method as defined in claim 4 wherein said performing maintenance includes spraying a cleaning fluid into an engine core of the gas turbine engine associated with the high pressure spool assembly.

6. The method as defined in claim 4 wherein said performing maintenance includes performing at least one of a sound analysis and a vibration analysis on the high pressure spool assembly.

7. The method as defined in claim 1 further comprising, prior to said positioning, adjusting the distance between the stop and the body of the locking tool.

8. The method as defined in claim 1 wherein said attaching further comprises positioning a bushing between the body of the locking tool and the wall of the gas path.

9. The method as defined in claim 1 wherein positioning the stop into the rotary path of the given one of the sets of blades of the low pressure spool assembly includes positioning the stop into the rotary path of a fan of the low pressure spool assembly.

10. A locking tool for immobilizing a low pressure spool of a gas turbine engine, the low pressure spool being rotatable around a main axis of the gas turbine engine and having a plurality of rotors, each rotor having a set of blades extending across a corresponding portion of an annular gas path of the gas turbine engine, the gas turbine engine further having an annular wall delimiting a portion of the annular gas path with a sensor attachment provided for removably receiving a sensor, the sensor attachment having at least one fastener element external to the gas path and an aperture defined through the annular wall of the engine, the locking tool comprising:

an adapter portion complementary to the sensor attachment, and being removably fastenable to the sensor attachment, externally to the gas path, via the at least one fastener element, into an operative position;

a body portion having a body and a securing portion extending therefrom, the body portion being securable to the adapter portion across the aperture via the securing portion into a locking configuration where the body is secured in the gas path; and

a stop extending from the body portion, the stop extending into a rotary path of a given one of the sets of blades of the low pressure spool assembly when the body is secured in the gas path.

11. The locking tool as defined in claim 10, wherein the securing portion has a male member having a polygonal cross-section shape, and the adapter portion has a female member having a polygonal cross-section shape complementary to the polygonal cross-section shape of the male member and engaged therewith when in the locking configuration to prevent pivoting of the body portion relative the adapter portion.

12. The locking tool as defined in claim 11, wherein the securing portion has a post with a threaded tip protruding from the male member, and the adapter portion has a complementary bored neck, further comprising a nut securable against the threaded tip opposite the body when in the locking configuration.

13. The locking tool as defined in claim 10 further comprising a rod slidable inside the body and lockable in a plurality of lengthwise positions relative the body, the rod having the stop at an end thereof.

14. The locking tool as defined in claim 10 further comprising a bushing engageable around the securing portion, the bushing being compressed between the body and the wall of the gas path when in the locking configuration.

15. A method of performing engine maintenance on a gas turbine engine having a sensor attachment provided for receiving a sensor during operation, the sensor attachment having at least one fastener element and an aperture, the aperture being defined through a gas path wall of the engine, the sensor being removably fastenable to the sensor attachment externally to the gas path via the at least one fastener element into a fastened configuration in which a sensing element of the sensor is exposed to the gas path through the aperture, the method comprising:

unfastening and removing the sensor from the sensor attachment;

fastening an adapter to the sensor attachment, externally to the gas path;

introducing a locking tool into the gas path, and securing it to the adapter across the aperture in a locking configuration in which a stop of the locking tool extends into the rotary path of a rotary component of the gas turbine engine; and

performing said engine maintenance while the rotary component is prevented from rotation by abutment against the stop of the locking tool in the locking configuration.

16. The method as defined in claim 15 wherein performing the engine maintenance includes spraying water into an engine core of the gas turbine engine.

17. The method as defined in claim 15 wherein performing the engine maintenance includes performing at least one of a noise analysis and a vibration analysis.

18. The method as defined in claim 15 further comprising:

subsequently to said engine maintenance, unsecuring the locking tool from the adapter and removing it from the gas path;

unfastening and removing the adapter from the sensor attachment; and

fastening the sensor to the sensor attachment into the fastened configuration.

19. The method as defined in claim 15 wherein introducing the locking tool includes securing the locking tool so that the stop extends into the rotary path of a fan of the gas turbine engine.