Patent ID: 8205827

Claim:
An engine for use in operating an aircraft, the engine comprising: a decomposition chamber configured to decompose into at least one combustible constituent element a first chemically unstable substance in the presence of a catalyst, wherein the decomposition of the first chemically unstable substance releases a first amount of heat and the first combustible constituent element expands as a result of the first amount of heat; a first turbine fluidly connected to the decomposition chamber, wherein the first turbine is configured to receive only the expanded at least one constituent combustible element and the first amount of heat from the decomposition chamber, wherein the first turbine is further configured to rotate after receiving the expanded at least one constituent combustible element; a compressor rotationally connected to the first turbine, and configured to rotate as a result of the rotation of the first turbine, and wherein the compressor is further configured to receive air, and is further configured to compress the air as a result of the rotation of the compressor; and a combustion chamber fluidly connected to an outlet of the first turbine and to the compressor, and wherein the combustion chamber is configured to receive and combine (i) the compressed air and (ii) the at least one combustible constituent element, and wherein the combustion chamber is further configured to combust the combined compressed air and at least one combustible constituent element, thereby generating a combustion product.