CFM Fan Platform

航空发表于 2011-4-13 08:47:20

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航空发表于 2011-4-13 08:47:37

February 2002 WTT face to face CFMI / Boeing Proprietary Information - Unauthorized Disclosure, Use, or Export are Prohibited 1 Fan Platform February 2002 WTT face to face CFMI / Boeing Proprietary Information - Unauthorized Disclosure, Use, or Export are Prohibited 2 Fan Platform AFT Pin Loss • A piece of a fan platform was liberated into the fan flow on an engine having accumulated 3495 TSN, and 2069 CSN • After engine shutdown, the platform piece, and the AFT pin nut have been recovered inside the engine  The AFT pin not recovered • The platform piece and nut were expertised  Bushing was lost at shock with fan case  Rupture of the platform was statis, no LCF  The self locking fixture of the nut was per specification • The booster spool has been shipped to CFM for expertise February 2002 WTT face to face CFMI / Boeing Proprietary Information - Unauthorized Disclosure, Use, or Export are Prohibited 3 AFT Pin Loss Non conformity Design concern Pin Assembly error Engine life Pin Nut Platform Bushing Booster lug - Rupture - Stretching Pin-nut assembly - Wrong assembly torque - Loosening by vibrations Platfo- rm microrotation Assembly procedure Nut rupture Booster - Crushed area - Thermal effect - Interference with pin Platform - Platformrupture - Bushing rupture - Swaged design effect / non swaged Wrong parts - Pin - Nut - Non swaged bushing Process - Wrong tooling used : air driven screw driver - Wrong wrench used - Bad lubrication - Torque level - Bad working conditions Particular events - Ingestion - Vibrations Particular actions Very low probability Low probability High probability Investigation on going Investigation completed Fan Platform February 2002 WTT face to face CFMI / Boeing Proprietary Information - Unauthorized Disclosure, Use, or Export are Prohibited 4 Root Cause status • Nut looseness  Torque value is 21 N-m  AFT pin and booster hole geometry tolerances (340-000-814-0/-815-0) allow potential interference which would explain the looseness  Process to torque the nut of the AFT pin is not easy  Potential platform micro-rotation could be a contributor in the nut liberation AFT Pin Loss Root cause not fully understood. Waiting for Booster Spool Investigation. Fan Platform February 2002 WTT face to face CFMI / Boeing Proprietary Information - Unauthorized Disclosure, Use, or Export are Prohibited 5 Current Definitions Status • Booster spool upgraded with counter-weights in Nov 2000  Torque value increased to 27 N-m  Better durability (lower de-torque stresses, less lug bending)  Torque value applied on the pin • Production improvement (340-000-816-0) introduced in Jul 2001  New booster design with thicker lug  AFT pin diameter increased and geometry optimized  Torque value increased to 45 N-m AFT Pin Loss No Platform liberation concern with above configurations Fan Platform February 2002 WTT face to face CFMI / Boeing Proprietary Information - Unauthorized Disclosure, Use, or Export are Prohibited 6 Field Containment Plan • Implementation of booster spool counter-weights is effective at solving the AFT pin nut looseness • Inspection of platform AFT pin torque to be recommended at first opportunity (fan blade relubrication)  SB in review, expected to be released in Feb 2002 – One-time operation – Torque at 21 N-m AFT Pin Loss Fan Platform February 2002 WTT face to face CFMI / Boeing Proprietary Information - Unauthorized Disclosure, Use, or Export are Prohibited 7 Content • Background • Technical Status • Design Improvement • In-service Plan Fan Platform February 2002 WTT face to face CFMI / Boeing Proprietary Information - Unauthorized Disclosure, Use, or Export are Prohibited 8 Background • Initial configuration (340-001-805/806-0) since EIS :  Concern with bushing migration • Swaged bushing (340-001-809/810-0), since Oct 2000 :  Implemented on all platform lugs  Rework since Nov 2000 – 805 --> 810, and 806 --> 809 – SB 72-271 : Recommend to implement swaged bushing at next shop visit when engine > 10,000CSN • Basic material : anodized 7075 aluminum • Minor interferences with disk and blades • Cases of seal disbond Fan Platform February 2002 WTT face to face CFMI / Boeing Proprietary Information - Unauthorized Disclosure, Use, or Export are Prohibited 9 Technical Status • Rig tests experience :  4 middle lug ruptures encountered during rig tests : – Parts representative of type designs : with and w/o swaged bushing – Test representative of operating conditions (500 - 5,405 rpm)  Cracks found during same tests on 3 sets (24 platform/set) after around 40,000 cycles on: – Middle lug hole : 16 platforms cracked – Forward lug hole : 1 platform cracked – Aft lug hole : 1 platform cracked – Ribs : 2 platforms cracked Platform P/N Bushing Cycles at rupture Liberation Event # 1 340-001-809-0 Swaged 42,657 Yes Event # 2 340-001-806-0 Non-swaged 37,017 Yes Event # 3 340-001-809-0 Swaged 40,108 Yes Event # 4 340-001-809-0 Swaged 40,108 No Fan Platform February 2002 WTT face to face CFMI / Boeing Proprietary Information - Unauthorized Disclosure, Use, or Export are Prohibited 10 Technical Status • Mechanical Analysis  Part modelization : – Finite Element Model are established – Critical locations are well predicted  Rig tests vs lab results on current middle lug (809) life :  Predicted - 3S life for non-swaged platform (805/806) : Lab analysis Predicted average Predicted -3S Initiation 19000 19300 12700 Propagation 23000 19000 9500 Total life 42000 38000 26500 Initiation site Predicted -3S Initiation 10000 Propagation 8500 Total life 21400 Middle Lug Fan Platform February 2002 WTT face to face CFMI / Boeing Proprietary Information - Unauthorized Disclosure, Use, or Export are Prohibited 11 New Platform Design (340-001-814-0) • New platform design implemented to achieve durability goal  More than 36,000 cycles at crack initiation • New geometry with swaged bushings  Middle lug bushing outer diameter increased (same pin diameter)  Resolves also minor interferences • New material Aluminum 7449 instead of Aluminum 7075 under evaluation  Go-ahead in Feb 2002 • Shot-peening implemented • Weight decreased • Bowl seal implemented on both sides (lip seal removed) • No need to have elastomer strip for weight balancing Fan Platform February 2002 WTT face to face CFMI / Boeing Proprietary Information - Unauthorized Disclosure, Use, or Export are Prohibited 12 Thickening New hole for mass and static balancing optimization Draft removal New transition radius Constant thickness New extrados edge for seal Thick bushing New intrados edge to prevent interference with blade New 340-001-814-0 Platform Fan Platform February 2002 WTT face to face CFMI / Boeing Proprietary Information - Unauthorized Disclosure, Use, or Export are Prohibited 13 New Design Schedule • New design definition frozen • Detailed drawings Feb 2002 • Engineering tests 2Q 2002 • Authorities submital 3Q 2002 • Authorities approval 4Q 2002 • Production introduction 1Q 2003 Fan Platform February 2002 WTT face to face CFMI / Boeing Proprietary Information - Unauthorized Disclosure, Use, or Export are Prohibited 14 Field Plan Objective : Replace all platforms by new design Proposed Plan • Retrofit no later than: • Sep 30 2007 for -805/-806 • Sep 30 2008 for -809/-810 • Service Bulletin Category 2 • Recommend replacement at shop visit • New platform production capability set up to support ~100 sets/month Fan Platform February 2002 WTT face to face CFMI / Boeing Proprietary Information - Unauthorized Disclosure, Use, or Export are Prohibited 15 Repairs Full repair (SB 72-0271):  Process includes: remove seals, weight, bushings and coating; resize the bushing holes, anodize, install swaged bushings, replace seals and balance weight  SB72-0271 recommends swaged bushing implementation at shop visit for engine having accumulated more than 10,000 cycles  RD issued and available (TR 72-0038 to be ESM 72-21-20 repair 1) – Addresses all platform damages together – Seal bonding is a proprietary process (Le Joint Français) – Seals can be purchased separately through CFM – Bonding specification issued, validation through standard pull test Fan Platform February 2002 WTT face to face CFMI / Boeing Proprietary Information - Unauthorized Disclosure, Use, or Export are Prohibited 16 Repairs Local repair - to install swaged bushings  Repair procedure validated (Snecma No. 15-93702)  Requires Electrolytic Anodization – Repair sites limited due to environmental issues  New local repair not detrimental to environment in progress – Application of Alodine 1200, and Blindexite paste in the hole – Wet aging tests successfully completed on coupons – Validation expected 2nd Qtr 2002 Fan Platform

979199501 发表于 2011-4-13 12:24:40

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plication of Alodine 1200, and Blindexite paste in the hole
– Wet aging tests successfully completed on coupons
– Validation expected 2nd Qtr 2002
Fan Platform

kinran 发表于 2011-6-4 23:28:30

:victory: :victory:

bocome 发表于 2011-7-31 04:34:19

CFM Fan Platform

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CFM Fan Platform

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