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Engines and things and Butterfly Wings

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Old 11th Oct 1999, 04:13
  #1 (permalink)  
SOC
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Cool Engines and things and Butterfly Wings

If you want a decent answer to a tech question then ask an Engineer. So here I go.
Why is the RB211 G4/H4 more efficient than earlier RB 211 especially on QANTAS aircraft. Is GE CFC 80C2 a better engine than the PW JT9 7R4 or in particular is a PW better than a GE and is the RR RB211 better on a 767 -300 series thaqn the GE series.
PS I have looked at the Rolls Royce and QANTAS web page but the info is not specific enough. Thanks for any info on the above.
 
Old 15th Oct 1999, 19:10
  #2 (permalink)  
Genghis the Engineer
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(1) I haven't got the foggiest.

(2) But Rolls Royce publishes a very well written book called "The Jet Engine", if you can find an up to date copy, it may well contain all the wisdom you require.

G
 
Old 16th Oct 1999, 16:25
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Le Pen
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Cool

Hiya
Sorry but I dont know/care why its more efficient! But I would imagine higher turbine operating temp, better fuel burn and airflow through the combustion chambers and overall better airflow through the compressors and turbines has something to do with it.

As for which is better, it depends upon your point of view and experience.
Personally I love the RB211/Trent 'cause it has easy access to most of the major parts under the fan cowls, fan blades are easy to change and general fault finding/trouble shooting is straight forward. I hate the older JT9-D,7Q 'cause its dirty, reversers are a bugger and the cowls are a nightmare to close. JT9-7R4E is a bit better 'cause of the new cowling. CF6-80C2 rarely go wrong reversers are easy to lock out, good oil consumption....I could go on....

As I said before it is all personal experience. But I hope this helps.

Love

Le Pen



------------------
Nil Fault Found.....My A**e
 
Old 18th Oct 1999, 03:42
  #4 (permalink)  
teaspoon155
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Unhappy

G-T mod uses a HP system developed for the RR Trent 700 engine.The module has a weight decrease of 200lb per engine, 2 to 3% improvement in SFC and approx 25 degrees C reduction in TGT at T/O thrust.
HPC- Stage 1 root redesign to reduce windage and eliminate leakage path.
Combustor- Low emissions combustor, reduced total volume, double sided dilution system.
HPT- Improved efficiency,tip clearance control.
Also more fuel spray nozzles with new design.Oil return tubes increased diameter,redesigned bearing vents for better flow.
Hope the info helps.


 

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