TASK 72-41-15-300-006 HPC Stage 8 Rotor Blade - Repair Damage By Material Removal, Repair-006 (VRS6014)

DMC:V2500-A0-72-41-1508-00A-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 72-41-15-300-006 HPC Stage 8 Rotor Blade - Repair Damage By Material Removal, Repair-006 (VRS6014)

Effectivity

FIG/ITEM

PART NO.

ASSEMBLY

02-370

6A3249

A

02-370

6A4908

B

02-370

6A5590

A

02-370

6A6464

B

02-370

6A6496

A

02-370

6A8747

B

02-385

6A3250

A

02-385

6A4909

B

02-385

6A5591

A

02-385

6A6465

B

02-385

6A6497

A

02-385

6A8748

B

02-400

6A3248C01

A

02-400

6A4910C01

B

02-400

6A5585C01

A

02-400

6A6470C01

B

02-400

6A6495C01

A

02-400

6A8745

B

02-415

6A3248C01

A

02-415

6A4910C01

B

02-415

6A5585C01

A

02-415

6A6470C01

B

02-415

6A6495C01

A

02-415

6A8745

B

02-416

6B1496

B

02-417

6A3248C02

A

02-417

6A4910C02

B

02-417

6A5585C02

A

02-417

6A6470C02

B

02-417

6A6495C02

A

02-417

6A8746

B

Material of component

DESCRIPTION

RR SYMBOL

MATERIAL

HP Compressor Stage 8 Rotor Blade

TDY

Titanium Alloy

General

This task gives the procedure to repair surface damage on the HP Compressor Stage 8 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 8 Rotor Blade, if the maximum limit for any 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 8 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 8 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 VRS6014.

TASKS identified by SPM TASK are in the Standard Practices Manual (SPM).

Related repairs

HP Compressor - Stage 3 to 12 - Rotor Blades - Repair 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 72-41-15-110-177 Chemically Clean (DELETED)

    1. This subtask has been deleted.

    2. SUBTASK 72-41-15-230-104 Do a Crack Test (DELETED)

    1. This subtask has been deleted.

    3. SUBTASK 72-41-15-220-288 Visually Examine (DELETED)

    1. This subtask has been deleted.

    4. SUBTASK 72-41-15-350-058-A00 Blend to Remove the Damaged Material

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

    3. Remove damage on the leading or trailing edge of the HP Compressor Stage 8 Rotor Blade by blending.

      4. Remove damage on the HP Compressor Stage 8 Rotor Blade airfoil surfaces 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 blended 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 72-41-15-350-058-B00 Remove Damage from the HP Compressor Rotor Blade(s), Stage 8, Assembly B (DELETED)

    1. This subtask has been deleted.

    6. SUBTASK 72-41-15-220-401 Visually and Dimensionally Inspect

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

      2. Do a visual inspection of the HP Compressor Stage 8 Rotor Blade.

      1. Make sure that all of the defects have been removed from the component.

      3. Do a dimensional inspection of the HP Compressor Stage 8 Rotor Blade.

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

    7. SUBTASK 72-41-15-220-166-B00 Examine the Repaired HP Compressor Rotor Blade(s), Stage 8, Assembly B (DELETED)

    1. This subtask has been deleted.

    8. SUBTASK 72-41-15-110-121 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 72-41-15-230-132 Do a Crack Test

      1. Do a penetrant crack test on the repair area(s) 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 72-41-15-380-058 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 8 Rotor Blade surface condition.

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

    11. SUBTASK 72-41-15-350-133 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 8 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 72-41-15-350-135 Identify the Repair

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

      NOTE

      If the HP Compressor Stage 8 Rotor Blade is already identified with the repair scheme identification symbol 27 from a previous repair application, further identification is not necessary.

      2. Vibro-peen 27 at one of the indicated locations on the HP Compressor Stage 8 Rotor Blade.

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

      2. Use vibration peen method.

    13. Figure: HP Compressor Stage 8 Rotor Blade - Leading And Trailing Edge Blending Details And Dimensions - Assembly A And Assembly B

    HP Compressor Stage 8 Rotor Blade - Leading And Trailing Edge Blending Details And Dimensions - Assembly A And Assembly B

    Figure: HP Compressor Stage 8 Rotor Blade - Leading And Trailing Edge Scalloping Details And Dimensions - Assembly A And Assembly B

    HP Compressor Stage 8 Rotor Blade - Leading And Trailing Edge Scalloping Details And Dimensions - Assembly A And Assembly B

    Figure: HP Compressor Stage 8 Rotor Blade - Repair Dimensions - Assembly A

    HP Compressor Stage 8 Rotor Blade - Repair Dimensions - Assembly A

    Figure: HP Compressor Stage 8 Rotor Blade - Repair Dimensions - Assembly B

    HP Compressor Stage 8 Rotor Blade - Repair Dimensions - Assembly B

    Figure: HP Compressor Stage 8 Rotor Blade - Repaired Leading And Trailing Edge Details Assembly A And Assembly B

    HP Compressor Stage 8 Rotor Blade - Repaired Leading And Trailing Edge Details Assembly A And Assembly B

    Figure: HP Compressor Stage 8 Rotor Blade - Airfoil Surface Dressing - Repair Details And Dimensions - Assembly A And Assembly B

    HP Compressor Stage 8 Rotor Blade - Airfoil Surface Dressing - Repair Details And Dimensions - Assembly A And Assembly B

    Figure: HP Compressor Stage 8 Rotor Blade- Leading And Trailing Edge Dressing Details - Assembly A And Assembly B

    HP Compressor Stage 8 Rotor Blade- Leading And Trailing Edge Dressing Details - Assembly A And Assembly B

    Figure: HP Compressor Stage 8 Rotor Blades - Marking Locations

    HP Compressor Stage 8 Rotor Blades - Marking Locations

Requirements After Job Completion

Follow-On Conditions

NONE
Change Type:

Revised the procedure in its entirety. (19VG363)