Abstract: One embodiment includes a multistage infrared suppression exhaust system for an aircraft, including: a stage one including a first exhaust conduit to receive a first exhaust air flow at a first temperature-pressure product T1P1, a second exhaust conduit to receive a second exhaust air flow at a second temperature-pressure product T2P2, and a flow integrator mechanically configured to mix the first exhaust air flow with the second exhaust air flow in an integration chamber while preventing back flow into the second exhaust conduit; and a stage two including a stage two cooling airflow to cool the mixed first and second exhaust air flows.

Abstract: One embodiment includes a multistage infrared suppression exhaust system for an aircraft, including: a stage one including a first exhaust conduit to receive a first exhaust air flow at a first temperature-pressure product T1P1, a second exhaust conduit to receive a second exhaust air flow at a second temperature-pressure product T2P2, and a flow integrator mechanically configured to mix the first exhaust air flow with the second exhaust air flow in an integration chamber while preventing back pressure into the second exhaust conduit; and a stage two including a stage two cooling airflow to cool the mixed first and second exhaust air flows.

Abstract: A method for suppressing infrared radiation from an engine of an aircraft operating in an environment includes directing hot exhaust from the aircraft engine into a lobed mixer of a single baffle infrared suppressor having a collapsible, translatable baffle to generate alternating flows of hot exhaust gas and cold air. The method further includes directing the alternating flows of hot exhaust gas and cold air towards the single baffle assembly to mix the hot exhaust gas with the cold air.

Abstract: A method for suppressing infrared radiation from an aircraft engine includes directing hot exhaust from the aircraft engine into a lobed mixer of a single baffle infrared suppressor having a single baffle assembly to generate alternating flows of hot exhaust gas and cold air. The method further includes directing the alternating flows of hot exhaust gas and cold air towards the single baffle assembly to mix the hot exhaust gas with the cold air.

Abstract: A method for suppressing infrared radiation from an aircraft engine includes directing hot exhaust from the aircraft engine into a lobed mixer of a single baffle infrared suppressor having a single baffle assembly to generate alternating flows of hot exhaust gas and cold air. The method further includes directing the alternating flows of hot exhaust gas and cold air towards the single baffle assembly to mix the hot exhaust gas with the cold air.

Abstract: A method for suppressing infrared radiation from an engine of an aircraft operating in an environment includes directing hot exhaust from the aircraft engine into a lobed mixer of a single baffle infrared suppressor having a collapsible, translatable baffle to generate alternating flows of hot exhaust gas and cold air. The method further includes directing the alternating flows of hot exhaust gas and cold air towards the single baffle assembly to mix the hot exhaust gas with the cold air.

Abstract: An infrared signature suppression system for reducing infrared radiation emitted by a vehicle. The system includes an elongate duct mounted on the vehicle having a hollow interior extending along an axial centerline between an upstream end and a downstream end for transporting exhaust gas emitted by the vehicle, and a baffle positioned in the hollow interior of the duct between the upstream end and the downstream end. At least a portion of at least one of the duct and the baffle includes an emissivity coating for reducing infrared radiation emitted by the vehicle.

Abstract: An infrared signature suppression system for reducing infrared radiation emitted by a vehicle. The system includes an elongate duct mounted on the vehicle having a hollow interior extending along an axial centerline between an upstream end and a downstream end for transporting exhaust gas emitted by the vehicle, and a baffle positioned in the hollow interior of the duct between the upstream end and the downstream end. At least a portion of at least one of the duct and the baffle includes an emissivity coating for reducing infrared radiation emitted by the vehicle.

Abstract: An infrared suppressor system for a gas turbine engine is provided for suppressing infrared radiation associated with the hot metal parts of the engine and with the hot exhaust gases exhausted from the engine. The system features a unique arrangement of multiple baffles that are connected together as a single baffle module. The baffle arrangement permits mixing of hot and cool gas flows while eliminating line-of-sight infrared radiation in an axially compact suppressor. The baffles are additionally linked together into a single insertable baffle module that permits removal of the baffle module when infrared suppression is unnecessary.

Abstract: An infrared suppressor system for a gas turbine engine is provided for suppressing infrared radiation associated with the hot metal parts of the engine and with the hot exhaust gases exhausted from the engine. The system features a unique arrangement of multiple baffles that are connected together as a single baffle module. The baffle arrangement permits mixing of hot and cool gas flows while eliminating line-of-sight infrared radiation in an axially compact suppressor. The baffles are additionally linked together into a single insertable baffle module that permits removal of the baffle module when infrared suppression is unnecessary.

Abstract: An ejecting exhaust nozzle in a gas turbine engine includes a convergent section, a divergent section, extending downstream from the convergent section, and an ejector for ejecting an airflow into the core airflow is fed by a boost pump. The boost pump includes a flow mixer with a boost plane wherein a fan airflow is injected into a ram airflow and then mixed in a mixing section extending downstream from the boost plane. Varying the fan airflow to boost the ram airflow to control a boosted ram airflow pressure allows ejector operation throughout the flight envelope of the gas turbine engine.

Abstract: An exhaust system having a protective arrangement includes a plurality of spaced overlapping inclined armor plate blockers providing a ballistic shield over the entire exhaust area. A louvered grate is provided extending between the tops of the blockers to permit egress of gases from the engine but to block destructive elements from being thrown into the interior of an engine. Cooling air is supplied to the blockers and is caused to move along a path which carries it across the surfaces of the blockers so as to materially reduce the temperature of these surfaces. Further, this cooling air is directed not only over surfaces of the blockers which are directly visible externally of the vehicle, but also over a surface which, while not directly visible from the exterior of the vehicle, is a potential source of reflected heat which could be sensed exteriorly of the vehicle.

Abstract: An infrared suppressor system for gas turbine engine is provided for suppressing infrared radiation associated with the hot metal parts of the engine and with the hot exhaust gases exhausted from the engine.

Abstract: A system of separating or removing foreign particles from the gaseous fluid flowing in the primary flow path of a gas turbine engine is provided wherein the particles are removed from the stream near the engine inlet and flow through a conduit to ejector means operative to effect a flow of a second stream of fluid in the conduit. Mixing means are provided for mixing the second stream of fluid with the gaseous fluid flowing in the primary flow path.

Abstract: An infrared suppression system is provided for an aircraft gas turbine engine for reducing the level of emitted infrared radiation from the engine exhaust. The hot exhaust stream emitted from the engine is mixed with the cooling airflows received from a plurality of sources in order to more effectively reduce the level of emitted infrared radiation. In addition, the infrared suppression system prohibits a direct line of sight back into the core engine.