Go Back  PPRuNe Forums > Flight Deck Forums > Tech Log
Reload this Page >

Temps in compressor stage gas turbine?

Wikiposts
Search
Tech Log The very best in practical technical discussion on the web

Temps in compressor stage gas turbine?

Thread Tools
 
Search this Thread
 
Old 11th Nov 2014, 17:38
  #1 (permalink)  
Thread Starter
 
Join Date: Sep 2006
Location: Los Angeles, USA
Age: 52
Posts: 1,631
Likes: 0
Received 0 Likes on 0 Posts
Temps in compressor stage gas turbine?

I was wondering if anyone knows what the temps are roughly in the compressor stage of let's say a RR 250-C20 type engine? That engine has an axial flow turbine before a centrifugal flow turbine and I'm most curious how the temps are in the initial or axial part of that design? Reason I'm asking is, if the temps are not that high, could you get away with carbon fibre blades and stators in this part?
AdamFrisch is offline  
Old 11th Nov 2014, 18:54
  #2 (permalink)  
 
Join Date: Mar 2002
Location: Florida
Posts: 4,569
Likes: 0
Received 1 Like on 1 Post
Stable temperatures are one thing, short time stagnation stall temperatures are quite another. Then there is the erosion at high velocities and the workaround costs.

I would have concerns about the ruggedness to withstand abnormalities without having to scrap the parts.
lomapaseo is offline  
Old 11th Nov 2014, 18:55
  #3 (permalink)  
 
Join Date: Jan 2014
Location: Norfolk
Posts: 428
Likes: 0
Received 0 Likes on 0 Posts
I don't have any experience on that engine type but I would think you are looking at around 250 degrees C. The latter stages of an axial flow compressor are usually made with nickel alloys or titanium because of the heat.
Vendee is offline  
Old 11th Nov 2014, 19:03
  #4 (permalink)  
 
Join Date: Jan 2012
Posts: 38
Likes: 0
Received 0 Likes on 0 Posts
Vendee, he's asking about typical temperatures in the axial stages i.e. stages 1 to 6 in a RR 250-C20B. You're correct though, a typical compressor outlet temperature is slightly above 250 degrees C.
pilot9248 is offline  
Old 11th Nov 2014, 21:11
  #5 (permalink)  
 
Join Date: Jan 2014
Location: Norfolk
Posts: 428
Likes: 0
Received 0 Likes on 0 Posts
TTF, yes I know what he was asking
Vendee is offline  
Old 11th Nov 2014, 22:18
  #6 (permalink)  
 
Join Date: Jun 2001
Location: Australia
Posts: 889
Likes: 0
Received 0 Likes on 0 Posts
I thought a key property of carbon fibre structures was flexibility - the ability to distort elastically under stress. In other words, a low Young's Modulus.

For reasons of compressor case clearance and precise aerodynamic control, I would have thought compressor rotor blades must have a very high resistance to tensile stress; a high Young's Modulus.

Stators, perhaps. You could use them in the early stages, even if the temps were too high in later stages.
Oktas8 is offline  
Old 11th Nov 2014, 22:50
  #7 (permalink)  
 
Join Date: Feb 2002
Location: UK
Age: 58
Posts: 3,504
Received 173 Likes on 94 Posts
Sounds Familiar

Is this what you are looking for?

TURIN is offline  

Posting Rules
You may not post new threads
You may not post replies
You may not post attachments
You may not edit your posts

BB code is On
Smilies are On
[IMG] code is On
HTML code is Off
Trackbacks are Off
Pingbacks are Off
Refbacks are Off



Contact Us - Archive - Advertising - Cookie Policy - Privacy Statement - Terms of Service

Copyright © 2024 MH Sub I, LLC dba Internet Brands. All rights reserved. Use of this site indicates your consent to the Terms of Use.