The invention provides a method for computational fluid dynamics and apparatuses making enable an efficient implementation and use of an enhanced jet-effect, either the Coanda-jet-effect, the hydrophobic jet-effect, or the waving-jet-effect, triggered by specifically shaped corpuses and tunnels. The method is based on the approaches of the kinetic theory of matter providing generalized equations of fluid motion and is generalized and translated into terms of electromagnetism. The method is applicable for slow-flowing as well as fast-flowing real compressible-extendable generalized fluids and enables optimal design of convergent-divergent nozzles, providing for the most efficient jet-thrust. The method can be applied to airfoil shape optimization for bodies flying separately and in a multi-stage cascaded sequence. The method enables apparatuses for electricity harvesting from the fluid heat-energy, providing a positive net-efficiency. The method enables generators for practical-expedient power harvesting using constructive interference of waves due to the waving jet-effect.

The invention provides a method for computational fluid dynamics and apparatuses making enable an efficient implementation and use of an enhanced jet-effect, either the Coanda-jet-effect, the hydrophobic jet-effect, or the waving-jet-effect, triggered by specifically shaped corpuses and tunnels. The method is based on the approaches of the kinetic theory of matter providing generalized equations of fluid motion and is generalized and translated into terms of electromagnetism. The method is applicable for slow-flowing as well as fast-flowing real compressible-extendable generalized fluids and enables optimal design of convergent-divergent nozzles, providing for the most efficient jet-thrust. The method can be applied to airfoil shape optimization for bodies flying separately and in a multi-stage cascaded sequence. The method enables apparatuses for electricity harvesting from the fluid heat-energy, providing a positive net-efficiency. The method enables generators for practical-expedient power harvesting using constructive interference of waves due to the waving jet-effect.

The invention provides a method for computational fluid dynamics and apparatuses making enable an efficient implementation and use of an enhanced jet-effect, either the Coanda-jet-effect, the hydrophobic jet-effect, or the waving-jet-effect, triggered by specifically shaped corpuses and tunnels. The method is based on the approaches of the kinetic theory of matter providing generalized equations of fluid motion and is generalized and translated into terms of electromagnetism. The method is applicable for slow-flowing as well as fast-flowing real compressible-extendable generalized fluids and enables optimal design of convergent-divergent nozzles, providing for the most efficient jet-thrust. The method can be applied to airfoil shape optimization for bodies flying separately and in a multi-stage cascaded sequence. The method enables apparatuses for electricity harvesting from the fluid heat-energy, providing a positive net-efficiency. The method enables generators for practical-expedient power harvesting using constructive interference of waves due to the waving jet-effect.

An aerial vehicle engine is proposed which may be powered an adjustable, vortex-based virtual aerospike engine. The vehicle may also include a combustion chamber which may be coupled to the exit nozzle. The combustion chamber may include one or more gas inlets, one or more blanket inlets and one or more main inlets. The gas inlet may be configured to let in a column of gases into the combustion chamber in a direction parallel to the direction of the rocket with minimal angular velocity to prevent the column of gases from mixing with a vortex of propellants or gases. The one or more main inlets may be configured to spray fuel or oxidizer at a specific angle, where the angle may be adjustable for forming the vortex of propellants or gases. The one or more blanket inlets may be configured to spray fuel/oxidizer/(inert) coolant at a specific angle, where the angle may be adjustable and may or may form a vortex, a stagnant pocket of gases (acting as a blanket) or a stream of gases that exits through the exit nozzle. Further, the column of gases inside the combustion chamber leading up to the exit nozzle may form a virtual aerospike nozzle, the virtual aerospike nozzle may exit the gases to propel the vehicle, wherein the virtual aerospike nozzle may not require cooling.

An aerial vehicle engine is proposed which may be powered an adjustable, vortex-based virtual aerospike engine. The vehicle may also include a combustion chamber which may be coupled to the exit nozzle. The combustion chamber may include one or more gas inlets, one or more blanket inlets and one or more main inlets. The gas inlet may be configured to let in a column of gases into the combustion chamber in a direction parallel to the direction of the rocket with minimal angular velocity to prevent the column of gases from mixing with a vortex of propellants or gases. The one or more main inlets may be configured to spray fuel or oxidizer at a specific angle, where the angle may be adjustable for forming the vortex of propellants or gases. The one or more blanket inlets may be configured to spray fuel/oxidizer/(inert) coolant at a specific angle, where the angle may be adjustable and may or may form a vortex, a stagnant pocket of gases (acting as a blanket) or a stream of gases that exits through the exit nozzle. Further, the column of gases inside the combustion chamber leading up to the exit nozzle may form a virtual aerospike nozzle, the virtual aerospike nozzle may exit the gases to propel the vehicle, wherein the virtual aerospike nozzle may not require cooling.

An aerial vehicle engine is proposed which may be powered an adjustable, vortex-based virtual aerospike engine. The vehicle may also include a combustion chamber which may be coupled to the exit nozzle. The combustion chamber may include one or more gas inlets, one or more blanket inlets and one or more main inlets. The gas inlet may be configured to let in a column of gases into the combustion chamber in a direction parallel to the direction of the rocket with minimal angular velocity to prevent the column of gases from mixing with a vortex of propellants or gases. The one or more main inlets may be configured to spray fuel or oxidizer at a specific angle, where the angle may be adjustable for forming the vortex of propellants or gases. The one or more blanket inlets may be configured to spray fuel/oxidizer/(inert) coolant at a specific angle, where the angle may be adjustable and may or may form a vortex, a stagnant pocket of gases (acting as a blanket) or a stream of gases that exits through the exit nozzle. Further, the column of gases inside the combustion chamber leading up to the exit nozzle may form a virtual aerospike nozzle, the virtual aerospike nozzle may exit the gases to propel the vehicle, wherein the virtual aerospike nozzle may not require cooling.

A heat exchanger positioned within an annular duct of a gas turbine engine is provided. The heat exchanger extends substantially continuously along the circumferential direction and defining a heat exchanger height equal to at least 10% of a duct height. An effective transmission loss (ETL) for the heat exchanger positioned within the annular duct is between 5 decibels and 1 decibels for an operating condition of the gas turbine engine. The heat exchanger includes a heat transfer section defining an acoustic length (L.sub.i), and wherein an Operational Acoustic Reduction Ratio (OARR) is greater than or equal to 0.75 to achieve the ETL at the operating condition.

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.

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.

A rocket-based combined cycle propulsion system comprising an air inlet and a centerbody extending along a center axis. The centerbody at least partially defines the air inlet. The system further includes a first propulsion system (e.g., a rotating detonation rocket engine, RDRE) and a second propulsion system (e.g., a scramjet) coupled with the first propulsion system. The system further includes an air bleed assembly including an inlet aperture formed in the centerbody, an outlet aperture positioned in the first propulsion system, and a duct fluidly connecting the inlet aperture and the outlet aperture.