Devices, systems, and methods of a casing for a heat suppression system of a gas turbine engine exhaust include a heat shield and an insulation layer for arrangement between the heat shield and an outer skin.

An aircraft and method of operating an aircraft. The aircraft includes a temperature sensor and a processor. The temperature sensor that obtains an optical signal indicative of a temperature at a selected location of an outer surface of the aircraft. The processor is configured to determine the temperature at the selected location from the optical signal, and operate the aircraft based on the temperature at the selected location.

Embodiments are directed to boosting aircraft engine performance for takeoff and critical mission segments by reducing airflow used for cooling exhaust gases. The airflow is reduced by stopping an accessory blower or by closing an external air vent. Eliminating the cooling airflow to the exhaust has the effect of lowering the backpressure on the engine, which thereby increases maximum engine power.

A hybrid propulsion engine for a rotorcraft includes a core turboshaft engine having a gas path and an output shaft that provides torque to a main rotor. A fan module is disposed relative to the core turboshaft engine and is coupled to the output shaft. The fan module has a bypass air path that is independent of the gas path. A thrust nozzle is configured to mix exhaust gases from the core turboshaft engine with bypass air from the fan module and to discharge the mixture to provide propulsive thrust. In a turboshaft configuration, the fan module is closed to prevent the flow of bypass air therethrough such that the thrust nozzle does not provide propulsive thrust. In a turboshaft and turbofan configuration, the fan module is open allowing the flow of bypass air therethrough such that the thrust nozzle provides propulsive thrust, thereby supplying propulsion compounding for the rotorcraft.

Devices and systems of the inventive concept provide a durable, all-weather manned or unmanned aircraft that is capable of vertical flight and provides improved stability upon payload launch or delivery. The payload bay is positioned along the central axis of the aircraft and proximal to the aircraft's center of gravity. Control and fuel systems are positioned fore and aft of the payload bay, respectively. The payload bay is configured to store and deliver a wide variety of payload types. The aircraft also includes features that reduce vibration, prolong the interval between necessary maintenance, and permit all-weather operation.

Devices, systems, and methods of a casing for a heat suppression system of a gas turbine engine exhaust include a heat shield and an insulation layer for arrangement between the heat shield and an outer skin.

Embodiments are directed to systems and methods for reducing the infrared signature of a vehicle, specifically to the use of mixed flow or centrifugal blowers to reduce the amount of infrared radiation being emitted from the engine exhaust. A blower and mixer are used to cool the exhaust gas from an aircraft engine. The blower and mixer use a tertiary exhaust duct to swirl cool air from an engine particle separator (EPS) and/or oil cooler, for example, with the hot engine exhaust gas. Existing blowers in the EPS or oil cooler may be used to motivate air flow so that a unique or dedicated blower is not required. In addition to reducing exposure to hostile forces, other benefits of cooling the exhaust gas include greatly reduced ground-impingement temperatures and safer personnel working zones because the hot plume is mostly eliminated.

An exhaust system for reducing infrared emissions of a rotary wing aircraft includes a duct assembly having an inlet portion and an outlet portion; the inlet portion configured to receive exhaust from an engine of the aircraft; and the outlet portion coupled to the inlet portion, the outlet portion having an outlet duct with an outlet opening, the outlet duct configured expel an emission containing engine exhaust proximate to a tail fairing of the rotary wing aircraft.

According to one aspect, an infrared suppression system that utilizes a primary airflow and a secondary air flow for a gas turbine engine is provided. The infrared suppression system includes an exit flap configured to control a flow of exhaust air out of the gas turbine engine and a secondary flow door that is configured to selectively control the secondary air flow into the gas turbine engine. The mixture of the secondary air flow and the primary air flow from the gas turbine engine suppresses an infrared signature produced by the gas turbine engine.

An airplane including an airframe and a turboprop propulsion system is disclosed in this paper. The turboprop propulsion system includes a propeller mounted for rotation about a propeller axis and a gas turbine coupled to the propeller to drive rotation of the propeller.