Devices, systems, and methods of a casing for a heat suppression system of a gas turbine engine exhaust include a floating heat shield.

An exhaust system has an engine exhaust plane associated with an entrance to the exhaust system, an exhaust exit plane associated with an exit of the exhaust system, a forward cap movable relative to the engine exhaust plane and configured to selectively intersect the engine exhaust plane, and an aft cap movable relative to the exhaust exit plane and configured to selectively intersect the exhaust exit plane.

Exhaust systems having adjustable nozzles and related methods are disclosed. An example exhaust system includes a nozzle. A portion of the nozzle is moveable from a first position to a second position to change an angle of convergence of the nozzle. The example exhaust system includes an exit area. The portion of the nozzle is at least partially disposed in the exit area. An opening is defined between the exit area and the portion of the nozzle disposed in the exit area. A size of the opening is to change in response to movement of the portion of the nozzle.

A system includes a matrix material to remove heat from an object. The matrix material includes a plurality of vascular structures. Each of the vascular structures are filled with a fluid. At least one transducer generates field-induced forces into the fluid within the vascular structures of the matrix material. At least one controller pulses the transducer to generate the field-induced forces into the fluid within the vascular structures. The field-induced forces generate fluid flow within the vascular structures to remove the heat from the object.

A vertical take-off and landing (VTOL) aircraft is provided and includes a fuselage, wings extending outwardly from opposite sides of the fuselage, nacelles supportively disposed on the wings and reversely oriented, axial flow engines disposed in each of the nacelles to generate mechanical energy for driving lift and thrust generating prop-rotor rotations.

Systems and methods for power generation for an aircraft are provided. In one example embodiment, a power generation system for an aircraft includes a thermionic generator arranged to receive heat from at least one heat source. The thermionic generator is configured to generate electrical power for one or more aircraft systems based at least in part on the heat received from the at least one heat source. The power generation system further includes a thermoelectric generator arranged to receive waste heat from the thermionic generator. The thermoelectric generator is configured to generate electrical power for one or more aircraft systems based at least in part on the waste heat received from the thermionic generator.

An exhaust system for reducing infrared emissions of a rotary wing aircraft includes a manifold; an opening in the manifold, the opening configured to face upwards and away from the rotary wing aircraft; and a chimney including a wall positioned about the opening, the chimney configured to eject an emission of intermixed secondary air and engine exhaust upwards and away from the rotary wing aircraft.

Devices, systems, and methods of a casing for a heat suppression system of a gas turbine engine exhaust include a floating heat shield.

Methods and systems for restricting movement in a flow mixer of an exhaust duct, the flow mixer having a first row of flutes and a second row of flutes generally opposite to the first row of flutes, each flute being elongated and defining an elongated axis. At least two flute ties connect, or couple, together at least two flutes from the first row of flutes and at least two flutes from the second row of flutes. A retainer is coupled to the flute ties and extends generally perpendicularly to the elongated axis of each of the flutes from the first and second rows of flutes. The combination of the retainer and flute ties is configured to generally restrain relative movement between the flutes from the first row and the flutes from the second row.

A device for altering infrared signature of an exhaust duct includes a housing configured to attach to an exhaust duct of a vehicle and at least one body attached to the housing at opposing ends of the at least one body, an opening in at least one of the opposing ends being in fluidic communication with a cavity within the at least one body such that fluid can flow into the cavity through the opening.