Auxiliary Combustion Chambers (Rochen)

The auxiliary combustion chambers are a thrust-augmentation feature the source dossier attributes to the Focke Rochen. The source states that "the exhaust nozzle forked in two at the end of the turbojet engine and ended in two auxiliary combustion chambers located on the trailing edges of the circular wing."

Claimed operation

• The projected Focke-Wulf turbojet's exhaust nozzle forks into two branches.
• Each branch terminates in an auxiliary combustion chamber on the trailing edge of the Circular-Wing Annular-Duct Configuration.
• "When fuel was added, the auxiliary combustion chambers acted as primitive afterburners, providing horizontal flight."
• "Control at low speed was achieved by varying the power to each auxiliary chamber through two small nozzles" — that is, asymmetric thrust from the two chambers is claimed to provide low-speed control.

Evidence status

The source describes the arrangement in the conditional mood and gives no thrust figures, chamber dimensions, fuel-flow data or test results. The aircraft was never built. The feature is recorded here as a design proposal, distinct from the Downwash Vectoring Louvers mechanism that the same source describes for the same aircraft.