Multi-mode rocket-based combined cycle
AssigneeVenus Aerospace Corp.
InventorsBen Saletta, Andrew Thomas Duggleby
Life of this patent
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Abstract
An air breathing engine system has an engine inlet configured to receive a flow of air. A combustor is in fluid communication with the engine inlet. A rocket ejector is positioned between the engine inlet and combustor. The rocket ejector is connected to the combustor with a mixing tube. The rocket ejector adjustably outputs high-temperature gas into air in the mixing tube. The high-temperature gas changes a pressure and thermal energy of the air within the mixing tube, which can be used to optimize combustor operation, such as based on a trajectory, flight condition, or speed of an aircraft propelled by the air breathing engine system.
Claims20
A combined cycle propulsion system comprising:
- a jet engine and a rocket engine;
- an air inlet configured to receive a flow of air;
- a combustor in fluid communication with the air inlet;
- and
- a rocket ejector comprising the rocket engine positioned between the air inlet and combustor, the rocket ejector connected to the combustor with a mixing tube, wherein the rocket ejector is configured to adjustably output high-temperature gas into air in the mixing tube, wherein the high-temperature gas changes a pressure and thermal energy of the air within the mixing tube;
- and
- a rotating detonation rocket engine (RDRE) positioned exterior to an exhaust bell of the combustor and in fluid communication with the exhaust bell.
Dependencies are inferred from the claim text.