Vad orsakar så mycket motorskador?

2

EASA och FAA har placerat en 300-timmars inspektions AD på utvalda Dreamliner Trent 1000-motorer efter flera misslyckanden. Här är ett foto av en AirNZ-motor.

länk

Uppdatera från kommentar till referensartikel:

AD hänvisar specifikt till: Intermediate Pressure Compressor (IPC) Stage (Rotor) 1 blad IPC Rotor 2 blad IPC Shaft Stage 1-8 Rotoraggregat Tidigare berättelser hade RR "avlastning 35% av utvecklingsrisken för Trent 1000 till sina partners. IPC-modulen är gjord av Kawasaki. Detta verkar vara annorlunda än det andra kända problemet på Trent 1000 av trötthetssprickor i Intermediate TURBINE

Vad orsakar så mycket skada?

    
uppsättning Pilothead 15.04.2018 00:58

1 svar

6

Rapportera här säger att det är misstänkt för att orsakas av utländska eller inhemska föremålskador (FOD / DOD).

Provided with the photos taken of the NZ99 engine after it landed back in Auckland, a spokeswoman said: "The cause of these incidents is yet to be determined and this is the role of the Transport Accident Investigation Commission. But the damage sustained on Tuesday suggests an engine part has travelled through the engine."

An aviation source told Newsroom: "The damaged blades are in the aft section of the turbine blade sections. It is likely the damage has resulted from a failure of a turbine blade or blades in an earlier section that has been spat out the back with a domino effect.”

Jag skulle tro att en övertemperatur och / eller överdriven vibration kan ha inträffat. Det verkar likt skadorna i dessa två händelser, som innehöll dessa händelser:

Boeing 777-200, GE90, Dec 2010.

The damage pattern leads to the suspicion that one or more fuel injectors in the combustion chamber behaved abnormally leading to an excessive temperature build up in the turbine area, which probably caused the LPT guide vanes material to fail. The engine manufacturer has registed six similiar failures which are all suspected to be the result of fuel injector malfunctions.

Boeing 737-400, CFM56, nov 2009.

The in-flight malfunction of the aircraft’s right engine was a result of a cascading rupture of the stage-1 LPT blades, [which] was probably precipitated by thermal degradation of the blade alloy, resulting in excessive creep extension, tip shroud/seal interference and blade rupture. Material characteristics of some of the LPT blades installed in the engine were consistent with a raw material manufacturing cast that had previously been identified as being susceptible to creep rupture.

    
svaret ges 15.04.2018 14:26