Abstract: A process for producing olefins and diolefins. A flow of gas is compressed with a prime mover in a near adiabatic path. Resistance to the flow within the adiabatic path causes a temperature rise with respect to its pressure, where it enters a near adiabatic tunnel. At least one other gas is provided into the tunnel at a prescribed, independently controlled temperature and pressure. The compressed flow is comingled and mixed with at least one other gas. Hydrogen and oxygen are fed into the tunnel to produce steam. Steam is applied to at least one hydrocarbon for pyrolysis or thermal cracking to yield at least one of olefins and diolefins.

Abstract: An independent and conserved source of fuel and/or power comprises a top stage rocket engine firing up to 5000 F. at very high pressures, delivering jet flows up to transonic velocities into a near adiabatic tunnel for mixing in general and/or for transforming reactants introduced selectively. The related compression is supplied by an independent prime mover which compresses its exhaust and other recoverable fluids. Low grade flows, thereby upgraded in temperature and pressure, are adiabatically contained, are further upgraded in the tunnel to become part of the prescribed fuel for export at the tunnel ends; or fuel to be fired in a prime mover for electric or other power; or hydrogen for chemical use. Expansion turbines for this purpose are relieved of the load used to compress the excess air in standard gas turbines thus increasing export power. A portion of the expansion turbine's exhaust becomes part of recoverable fluids.

Abstract: Process of producing power comprising:providing a turbine adapted to generate shaft work, said turbine having a combustor; and a rocket engine having a nozzle and a compressor means;feeding fuel and oxidant to the rocket engine and the rocket engine compressor means;feeding carbonaceous matter and steam into the rocket engine nozzle;processing the output of the rocket engine nozzle into fuel for the turbine;introducing said fuel and oxidant for the turbine to the turbine combustor; andrecycling a substantial portion of the hot exhaust from the turbine to the rocket engine compressor means; andcontrolling the inlet temperature to the turbine.Apparatus for producing power comprising a rocket engine and a turbine adapted to generate shaft work is also disclosed.