Circular propulsion jet compressor-engine, through a circular combustion chambers propellants spheroidal geometry set, generates a tangential push the turning radius and therefore resulting angular momentum about the shaft of the circle in rotation. This impulse is the consequence of the principle of action-reaction, the violent expansion that occurs inside the combustion chamber, when burning mixtures of fuel and oxidizer at high pressure, or by merging a small mass of H.sub.2, encapsulated and simultaneously subjected to very high pressure, constant electromagnetic fields and high-frequency electric fields and high peak intensity. The high pressure on the oxidant or H.sub.2, is achieved using the force resulting from the centripetal acceleration shaft rotating about a significant mass of a piston, solid or liquid and alternatively or cyclically. The gases and vapors produced are cooled inside the engine. In the combustion reaction, water vapor is condensed and water obtained by, pollution is retained inside the engine.

A gas turbine engine has a compressor section with a low pressure compressor and a high pressure compressor having a downstream end. A cooling air system includes a tap from a location upstream of the downstream most location. The tap passes air to a boost compressor, and the boost compressor passes the air back to a location to be cooled. The boost compressor is driven by a shaft in the engine through an epicyclic gear system. A speed control changes the relative speed between an input and an output to the epicyclic gear system.