Most of the ab air,80%, went through the whole engine. A small amount, 20% which was required to make the compressor function properly at high inlet temps, was bled from the 4th compressor stage and then to the ab.
I'd be interested where you get those figures from
peter.
Also the popular colored airflow diagrams in a previous post which don't show any engine bypass air going to the ab
The bleed bypass can be identified on the engine by six very large pipes running from the forth stage to the afterburner.
The bleed air from the forth stage was scheduled by the main fuel control as a function of compressor inlet temperature and engine speed. The transition normally occurred in a compressor inlet temperature range of 85° to 115° C, corresponding to a Mach range of 1.8 to 2.0.
If the AB is reduced to minimum AB, the engine would actually be dragging on the engine mounts at high Mach numbers. Further reduction of engine thrust below military power will result in no propulsive thrust on the aircraft.
At sea level static conditions military thrust constitutes 70% of maximum thrust, whereas at high altitude it is approx 28% of the maximum available.
The engine will always be producing thrust irrespective of throttle position - assuming it hasn't been shut down that is.
engineers described the powerplant as a turbo-ramje
While I don't have any evidence that Kelly Johnson or Ben Rich ever referred to the engine as a "turbo ramjet", the term was used by Lockheed and NASA people, the principle behind the term, and what it meant, being well understood.