A20N Engine Start
The A320NEO seems to take an age between pushback and engine startup to request for taxi. Would a more learned subscriber venture the reason(s) why? After push and start the other day, we waited for the 'request taxi' call and an inbound to the ramp had to hold short waiting for the outbound. The flight deck commented on R/T "yes, we're in the NEO; it takes forever..." - what's different about the NEO that makes for a longer startup time? Thanks for enlightening me!
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The engine cranks for a few seconds longer to stabilise the internal temperatures within the engine but it is on a par with an IAE. It does seem an age in comparison to a CFM.
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Bowed rotor protection.
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The CFM Leap-1A (the other engine option on the NEO) takes an age as well for the same reason, nice and quick if it is cold after sitting overnight but cranks for ages once it is hot.
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From experience, it’ll take about a minute longer than the IAE, so about 2 minutes per engine.
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Same story with the PW1500 on an A220 (CSeries) and GENx on the 747-8
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Originally Posted by Sirijus
(Post 10885381)
Same story with the PW1500 on an A220 (CSeries) and GENx on the 747-8
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Originally Posted by Fursty Ferret
(Post 10885351)
Bowed rotor protection.
GEnx does much the same thing. Bowed rotor is caused by the differential cooling after shutdown (hot air rises, so the bottom cools quicker than the top...) which will literally result in a small 'bow' in the rotor. Starting the engine with a bowed rotor will cause high vibes and can rub compressor seals resulting in a permanent loss of performance. Worse case it can even cause compressor blades to crack or fracture. |
Out of interest, why wasn’t this an issue on the previous CFM/IAE generation? Bigger NEO engine squeezed in a tighter space?
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For fuel efficiency everything about an engine is being made to operate to the limit e. g. Fan diameter to process more air mass, compression increasing core pressure, N1 and higher EGT. So the tolerances are reduced. Older engines had more margins. Some of them also had to motor to bring residual EGT down for start. In PW the separated fan through gearing so it could operate at it's own efficient speed. It allowed them bigger fan and less stages of compression reducing weight.
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Originally Posted by Bus Driver Man
(Post 10885631)
Out of interest, why wasn’t this an issue on the previous CFM/IAE generation? Bigger NEO engine squeezed in a tighter space?
GE9X on the 777X takes bowed rotor mitigation one step further - there is a small electric motor on the gearbox that uses aircraft power to slowly rotate the core after shutdown at roughly one rotation per minute - that will even out the cooling of the core and prevent the rotor from bowing. It's commonly referred to as the 'rotisserie' for what should be obvious reasons. |
Originally Posted by tdracer
(Post 10886195)
GE9X on the 777X takes bowed rotor mitigation one step further - there is a small electric motor on the gearbox that uses aircraft power to slowly rotate the core after shutdown at roughly one rotation per minute - that will even out the cooling of the core and prevent the rotor from bowing. It's commonly referred to as the 'rotisserie' for what should be obvious reasons.
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Originally Posted by Bus Driver Man
(Post 10885631)
Out of interest, why wasn’t this an issue on the previous CFM/IAE generation? Bigger NEO engine squeezed in a tighter space?
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If I recall correctly, Concorde also had a de-bow procedure for warm engines.
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There’s been a EGT maximum before introducing fuel on big Engines for a long time on the wide bodies I’ve flown. Generally 100c but 150c for some.....Only an issue for turnarounds, especially when there is no wind blowing the Engine around on transit.
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Originally Posted by AerocatS2A
(Post 10886243)
The IAE engines already had a significant motoring cycle prior to fuel input (about 30 seconds), I don't know if the CFMs had something similar. At least the NEO can cool both engines at the same time, something I gather the B737 MAX does not do.
Interesting info from everyone. Thanks. |
At least the NEO can cool both engines at the same time, something I gather the B737 MAX does not do. |
IAE V2500 used to have a 50sec dry crank for shortly after it came into service, reduced to 30sec a few years later.
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Originally Posted by Fursty Ferret
(Post 10886457)
Simultaneous engine starts?
(On the A380, 2 engines are started simultaneously. But the APU is more powerful to be able to do that. No idea about the A340 and B747.) |
Grateful for everyone's most learn-ed replies... truly fascinating all this tech stuff to me in the air traffic world. Thank you for taking the time to respond.
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