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JTF-17A: Anybody Know Anything About This?  
User currently offlineBlackbird From , joined Dec 1969, posts, RR:
Posted (7 years 8 months 1 week 5 days 8 hours ago) and read 2454 times:

I know it was a low-bypass continuously-afterburning turbofan, designed primarily for the L-2000-7A SST.

I'm just wondering if there is any more information available on this engine?

Andrea K

8 replies: All unread, jump to last
 
User currently offline747400sp From United States of America, joined Aug 2003, 3649 posts, RR: 2
Reply 1, posted (7 years 8 months 1 week 5 days 6 hours ago) and read 2437 times:

I believe it had 50000+ lb of thrust dry and 63000 lb of thrust wet.

User currently offlineBlackbird From , joined Dec 1969, posts, RR:
Reply 2, posted (7 years 8 months 1 week 4 days 16 hours ago) and read 2376 times:

I actually already knew that part. I thought it was 61,000 or 62,000 lbs wet (53,000 lbs dry). But I was more wondering stuff like what it's bypass ratio was, it's diamater and length, fuel efficency, etc.

Andrea K


User currently offlineStarglider From Netherlands, joined Sep 2006, 678 posts, RR: 44
Reply 3, posted (7 years 8 months 1 week 4 days 11 hours ago) and read 2333 times:

Quoting Blackbird (Reply 2):
But I was more wondering stuff like what it's bypass ratio was, it's diamater and length, fuel efficency, etc

Try this link, it will lead you to a report about the JTF17A-20B for the Boeing Model 733-394:

http://handle.dtic.mil/100.2/AD378635



Regards,
Starglider


User currently offlineBlackbird From , joined Dec 1969, posts, RR:
Reply 4, posted (7 years 8 months 1 week 4 days 8 hours ago) and read 2307 times:

Thank you for your help.

The only thing left basically would be... Do you have any idea what the bypass-ratio was, or how many compressor/turbine stages there are?

Andrea K


User currently offlineN231YE From , joined Dec 1969, posts, RR:
Reply 5, posted (7 years 8 months 1 week 4 days 7 hours ago) and read 2302 times:

You might want to read this thread: GE GE4/J5P & PW JTF-17 Size (by 747400sp Feb 18 2006 in Tech Ops)

Quoting B2707SST (Reply 3):
The JTF17A-21L proposed for the Lockheed L-2000 was a low-bypass turbofan with afterburning capability in the bypass duct only (a "duct-burning turbofan"). It was to generate 60,760 lbs. of augmented or 38,130 lbs. of non-augmented thrust at takeoff. Bypass ratio was 1.3:1.


User currently offlineBlackbird From , joined Dec 1969, posts, RR:
Reply 6, posted (7 years 8 months 1 week 4 days 7 hours ago) and read 2296 times:

Acknowledged,

Andrea K


User currently offlineN231YE From , joined Dec 1969, posts, RR:
Reply 7, posted (7 years 8 months 1 week 4 days 7 hours ago) and read 2292 times:

I might be able to find some information on the JTF-17 compressor/turbine stages...but the key word is 'might.'

I have a book with the history of every aircraft engine manufacturer in the world that has ever existed throughout history. However, it is at my house on on side of the state, with my university's dorm (where I am currently at) on the other. I will try to drive home this weekend (weather permitting) and look this up.


User currently offline747400sp From United States of America, joined Aug 2003, 3649 posts, RR: 2
Reply 8, posted (7 years 8 months 1 week 4 days 4 hours ago) and read 2270 times:

I would say, think about a P&W 2000 size JT8.

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