TASK 72-41-15-300-005 HPC Stage 7 Rotor Blade - Repair Damage By Material Removal, Repair-005 (VRS6013)

DMC:V2500-A0-72-41-1507-00A-655A-C|Issue No:003.00|Issue Date:2021-08-01

Export Control

EAR Export Classification: Not subject to the EAR per 15 C.F.R. Chapter 1, Part 734.3(b)(3), except for the following Service Bulletins which are currently published as EAR Export Classification 9E991: SBE70-0992, SBE72-0483, SBE72-0580, SBE72-0588, SBE72-0640, SBE73-0209, SBE80-0024 and SBE80-0025.

Copyright

© IAE International Aero Engines AG (2001, 2014 - 2021) The information contained in this document is the property of © IAE International Aero Engines AG and may not be copied or used for any purpose other than that for which it is supplied without the express written authority of © IAE International Aero Engines AG. (This does not preclude use by engine and aircraft operators for normal instructional, maintenance or overhaul purposes.).

Applicability

All

Common Information

TASK 72-41-15-300-005 HPC Stage 7 Rotor Blade - Repair Damage By Material Removal, Repair-005 (VRS6013)

Effectivity

FIG/ITEM

PART NO.

ASSEMBLY

02-270

6A3246

A

02-270

6A4905

B

02-270

6A5588

A

02-270

6A6462

B

02-270

6A6493

A

02-270

6A8314

B

02-270

6A8743

B

02-285

6A3247

A

02-285

6A4906

B

02-285

6A5589

A

02-285

6A6463

B

02-285

6A6494

A

02-285

6A8315

B

02-285

6A8744

B

02-300

6A3245C01

A

02-300

6A4907C01

B

02-300

6A5584C01

A

02-300

6A6469C01

B

02-300

6A6492C01

A

02-300

6A8312

B

02-300

6A8741

B

02-315

6A3245C01

A

02-315

6A4907C01

B

02-315

6A5584C01

A

02-315

6A6469C01

B

02-315

6A6492C01

A

02-315

6A8312

B

02-315

6A8741

B

02-316

6B1495

B

02-317

6A3245C02

A

02-317

6A4907C02

B

02-317

6A5584C02

A

02-317

6A6469C02

B

02-317

6A6492C02

A

02-317

6A8313

B

02-317

6A8742

B

Material of component

PART IDENT

RR SYMBOL

MATERIAL

HP Compressor Stage 7 Rotor Blade

TDY or TTX

Titanium alloy

General

This TASK gives the procedure to repair surface damage on the HP Compressor Stage 7 Rotor Blade by material removal.

This repair must only be done when the instruction to do so is given in the relevant inspection procedures (identified by the applicable part number) located in section 72-41-15.

You can mix a scallop and edge dressing to a given HP Compressor Stage 7 Rotor Blade, if the maximum limit for any one of these is not exceeded.

Rotor blades must be repaired as soon as damage or wear is monitored, to get back HP compressor efficiency and extend the rotor blade life.

Material removal from the HP Compressor Stage 7 Rotor Blade airfoil fillet radius is not permitted.

When the depth of the dressed material is more than 0.002 in. (0.05 mm) it is necessary to glass bead peen the HP Compressor Stage 7 Rotor Blade to restore the airfoil surface condition, refer to Repair, VRS6150 TASK 72-41-15-300-040 (REPAIR-040).

Where reference is made to a SUBTASK within a TASK in the form "TASK, SUBTASK" the operator must read and apply the complete TASK. The SUBTASK is listed only when the TASK gives options for the processing of the component. The specified SUBTASK instructs what option must be used during application of the TASK for the successful completion of the repair scheme VRS6013.

The practices and processes referred to in the procedure by the TASK/SUBTASK number are in the SPM.

Related Repairs

HP Compressor - Stage 3 to 12 - Rotor Blades - Restore Airfoil Surface condition, refer to Repair, VRS6150 TASK 72-41-15-300-040 (REPAIR-040).

NOTE

Equipment and materials necessary to do this repair are in the SPM TASKS given below:
SPM TASK 70-11-08-300-503
SPM TASK 70-23-04-230-501
SPM TASK 70-23-05-230-501
SPM TASK 70-35-03-300-501
SPM TASK 70-09-00-400-501

NOTE

It is possible that some materials in the consumable materials chart cannot be used for some or all of the necessary applications. Before you use the materials, make sure the types, quantities and applications of the materials necessary are legally permitted in your location. All persons must obey all applicable federal, state, local and provincial laws and regulations when it is necessary to work with these materials.

NOTE

To identify the consumable materials refer to the Process Consumable Materials Index (PCI).

NOTE

Other necessary consumable materials are referred to in the SPM TASKS in this TASK.

Preliminary Requirements

Pre-Conditions

Action/ConditionData Module/Technical Publication
Make sure all the necessary cleaning and inspection procedures are done before this repair.

Support Equipment

NONE

Consumables, Materials and Expendables

NONE

Spares

NONE

Safety Requirements

NONE

Procedure

    1. SUBTASK 72-41-15-110-185 Chemically Clean (DELETED)

    1. This subtask has been deleted.

    2. SUBTASK 72-41-15-230-131 Do a Crack Test (DELETED)

    1. This subtask has been deleted.

    3. SUBTASK 72-41-15-220-587 Visually Examine (DELETED)

    1. This subtask has been deleted.

    4. SUBTASK 72-41-15-350-063 Blend to Remove the Damaged Material

    1. For Assembly A, refer to Figure, Figure, Figure, Figure, Figure, Figure, and Figure. For Assembly B, refer to Figure, Figure, Figure, Figure, Figure, Figure, and Figure.

    2. Refer to SPM TASK 70-35-03-300-501.

    3. Remove damage on the leading or trailing edge of the HP Compressor Stage 7 Rotor Blade by blending.

      4. Remove damage on the HP Compressor Stage 7 Rotor Blade airfoil surface by blending.

      1. The maximum depth of blending on the airfoil surface must not be more than 0.005 in. (0.13 mm).

      2. The diameter of the blend area (blend ratio) must be between 25 and 50 times the depth of the blended area. Larger blend ratios are acceptable but must only be used for very small defects.

      3. Impact damage, such as nicks, must be blended to twice the depth of the defect.

    5. SUBTASK 72-41-15-350-057-B00 Remove Damage from the HP Compressor Rotor Blade(s), Stage 7, Assembly B (DELETED)

    1. This subtask has been deleted.

    6. SUBTASK 72-41-15-220-165 Visually and Dimensionally Inspect

    1. For Assembly A, refer to Figure, Figure, Figure, Figure, Figure, Figure, and Figure. For Assembly B, refer to Figure, Figure, Figure, Figure, Figure, Figure, and Figure.

      2. Do a visual inspection of the HP Compressor Stage 7 Rotor Blade.

      1. Make sure that all of the defect(s) have been removed from the component.

      3. Do a dimensional inspection of the HP Compressor Stage 7 Rotor Blade.

      1. Discard the blades, if more than the limits specified.

    7. SUBTASK 72-41-15-220-165-B00 Examine the Repaired HP Compressor Rotor Blade(s), Stage 7, Assembly B (DELETED)

    1. This subtask has been deleted.

    8. SUBTASK 72-41-15-110-120 Do a Swab Etch

      1. Clean and swab etch the repaired area(s).

      1. Refer to SPM TASK 70-11-08-300-503.

    9. SUBTASK 72-41-15-230-065 Do a Crack Test

      1. Do a penetrant crack test on the repair areas by one of the procedures that follow:

      1. Refer to SPM TASK 70-23-05-230-501, ultra high sensitivity. Cracks are not permitted.

    2. Refer to SPM TASK 70-23-04-230-501.

    10. SUBTASK 72-41-15-380-057 Restore the Airfoil Surface Condition

      1. NOTE

        This SUBTASK, to restore the surface condition, is only necessary if the depth of material removal is greater than 0.002 in. (0.05 mm).

        Restore the HP Compressor Stage 7 Rotor Blade surface condition.

      1. Refer to Repair, VRS6150 TASK 72-41-15-300-040 (REPAIR-040).

    11. SUBTASK 72-41-15-350-005 Polish the Repair Area

      CAUTION

      TITANIUM COMPONENT - ONLY USE SILICON CARBIDE ABRASIVE STONES, WHEELS AND PAPERS TO DRESS, BLEND AND POLISH THE COMPONENT.

      CAUTION

      TITANIUM COMPONENT- THE MAXIMUM SPEED FOR MECHANICAL TOOLS MUST NOT EXCEED 1000 REVOLUTIONS PER MINUTE.

      CAUTION

      TITANIUM COMPONENT - MAKE SURE THAT DURING MATERIAL REMOVAL, BLENDING TO MAKE SMOOTH AND POLISHING THAT NO SPARKS ARE PRODUCED.

      CAUTION

      TITANIUM COMPONENT - IF THE MATERIAL SHOWS A CHANGE IN COLOUR TO DARKER THAN A LIGHT STRAW COLOUR THE COMPONENT MUST BE REJECTED.

      CAUTION

      TITANIUM COMPONENT - AVOID BUILD UP OF HEAT BY APPLYING ONLY GENTLE PRESSURE AND KEEPING THE TOOL SPEED AS LOW AS POSSIBLE. USE TECHNIQUES WHICH ALLOW FOR PROGRESSIVE WEAR OF THE DRESSING MEDIA TO PRESENT A CONTINUALLY FRESH CUTTING SURFACE TO THE WORK PIECE.

      CAUTION

      TITANIUM COMPONENT - DO NOT DWELL ON ONE AREA OF THE COMPONENT.

      CAUTION

      TITANIUM COMPONENT - DRESS WHERE POSSIBLE IN A CIRCULAR MOTION.

      NOTE

      This SUBTASK only needs to be applied if Step has not been applied.

      1. Polish the repair area on the HP Compressor Stage 7 Rotor Blade.

      1. Polish the repair area to remove scratches and to achieve a surface finish of 10 microinches (0.25 micrometers).

      2. Use suitable silicon carbide abrasive papers to achieve the given surface finish.

    12. SUBTASK 72-41-15-350-006 Identify the Repair

    1. For Assembly A and Assembly B, refer to Figure.

      NOTE

      If the HP Compressor Stage 7 Rotor Blade is already identified with the repair scheme identification symbol 26 from a previous repair application, further identification is not necessary.

      2. Vibro-peen 26 at one of the indicated locations on the HP Compressor Stage 7 Rotor Blade.

      1. Refer to SPM TASK 70-09-00-400-501.

      2. Use vibration peen method.

    13. Figure: HP Compressor Stage 7 Rotor Blade - Leading And Trailing Edge Blending Details And Dimensions - Assembly A And Assembly B

    HP Compressor Stage 7 Rotor Blade - Leading And Trailing Edge Blending Details And Dimensions - Assembly A And Assembly B

    Figure: HP Compressor Stage 7 Rotor Blade - Leading And Trailing Edge Dressing Details - Assembly A And Assembly B

    HP Compressor Stage 7 Rotor Blade - Leading And Trailing Edge Dressing Details - Assembly A And Assembly B

    Figure: HP Compressor Stage 7 Rotor Blade - Leading And Trailing Edge Scalloping Details And Dimensions - Assembly A And Assembly B

    HP Compressor Stage 7 Rotor Blade - Leading And Trailing Edge Scalloping Details And Dimensions - Assembly A And Assembly B

    Figure: HP Compressor Stage 7 Rotor Blade - Repair Dimensions - Assembly A

    HP Compressor Stage 7 Rotor Blade - Repair Dimensions - Assembly A

    Figure: HP Compressor Stage 7 Rotor Blade - Repair Dimensions - Assembly B

    HP Compressor Stage 7 Rotor Blade - Repair Dimensions - Assembly B

    Figure: HP Compressor Stage 7 Rotor Blade - Repaired Leading And Trailing Edge Details - Assembly A And Assembly B

    HP Compressor Stage 7 Rotor Blade - Repaired Leading And Trailing Edge Details - Assembly A And Assembly B

    Figure: HP Compressor Stage 7 Rotor Blade - Airfoil Surface Dressing - Repair Details And Dimensions - Assembly A And Assembly B

    HP Compressor Stage 7 Rotor Blade - Airfoil Surface Dressing - Repair Details And Dimensions - Assembly A And Assembly B

    Figure: HP Compressor Stage 7 Rotor Blades - Marking Locations

    HP Compressor Stage 7 Rotor Blades - Marking Locations

Requirements After Job Completion

Follow-On Conditions

NONE
Change Type:

Revised the procedure in its entirety. (19VG363)