Let's say the airplane is cruising at altitude at lower speeds and 100% of the thrust is from the turbojet. Nothing from the inlet or nozzle. The thrust is 100,000 lbs total and is consuming 100 gal/hr. Now, let's speed up to the normal cruise where the turbojet is producing 8% of the total thrust. Let's say the thrust is 200,000 lbs for normal cruise. 8% is 16,000 lbs and the corresponding fuel flow would be 16 gal/hr for that thrust. So, does this mean that only 16 gal/hr are leaving the fuel tanks when the airplane is in cruise?!
We might as well get the numbers right. In one of the postings in the Concorde thread M2Dude gave some figures from RR. The cruise fuel flow was 9700 lb/hour/engine and the engine thrust was quoted as 8050 lb, but this may have included the secondary nozzle contribution as it was shown on the accompanying diagram and RR might well claim that thrust as part of the engine firms' contribution to powerplant thrust. At mid-cruise weight the required thrust per powerplant (intake+engine+nozzle) would have been about 10000 lb.