Blackbird From , joined Dec 1969, posts, RR:
Reply 2, posted (7 years 11 months 1 week 1 day 7 hours ago) and read 2506 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.
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.
N231YE From , joined Dec 1969, posts, RR:
Reply 7, posted (7 years 11 months 1 week 21 hours ago) and read 2422 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.