A turbofan assembly that includes a primary turbine section and an aft fan section positioned downstream from the primary turbine section. The primary turbine section includes a bypass duct configured to channel a stream of bypass air therethrough, and a main flow duct configured to discharge a stream of exhaust gas therefrom. The bypass duct and the main flow duct each include a discharge end positioned such that a mixed stream of bypass air and exhaust gas is discharged from the primary turbine section. The aft fan section includes at least one turbine and fan stage including a turbine portion and a fan portion coupled to the turbine portion. The turbine portion is positioned to receive the mixed stream of bypass air and exhaust gas, and the fan portion is positioned radially outward from the turbine portion.

Systems and methods for an exhaust system for a gas turbine engine are provided. The exhaust system includes an eductor system adapted to receive a primary exhaust fluid. The eductor system includes a body that extends along a first axis, with a plurality of ducts spaced apart about a circumference of the body. Each of the plurality of ducts extend from the body along a second axis transverse to the first axis to define a plurality of eductor primary flow paths that terminate in a mixing chamber. The mixing chamber is adapted to receive a secondary cooling fluid and to mix the primary exhaust fluid with the secondary cooling fluid to create a mixed fluid flow.

A gas turbine engine includes a combustion section that generates combustive gases that form a primary exhaust flow and an exhaust system downstream from the combustion section. The exhaust system includes an eductor system that includes a body that extends along a first axis, and a plurality of ducts spaced apart about a circumference of the body. Each of the plurality of ducts define a plurality of eductor primary flow paths that terminate in a mixing chamber. The exhaust system includes a muffler system downstream from the mixing chamber that includes a plurality of baffles that cooperate to define a tortuous path and attenuate sound generated by the gas turbine engine. The exhaust system includes a housing that surrounds the eductor system and the muffler system such that the eductor system and the muffler system are contained within the housing.

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 T.sub.1P.sub.1, a second exhaust conduit to receive a second exhaust air flow at a second temperature-pressure product T.sub.2P.sub.2, 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.

An ejector/mixer for a gas turbine engine includes an annular wall having upstream end adapted to be fastened to an engine case and a downstream end forming a plurality of lobes. A support member interconnects the lobes, and includes an annular blade located radially inwardly of the bight of the lobes. The lobes extend radially inwardly downstream relative to the annular wall and the support member includes an annular blade and has spaced apart joint surfaces spaced apart to coincide with the joint surfaces of a respective lobes. The spaced-apart joint surfaces of the support member being profiled to mate with the corresponding joint surface of the lobes.

An engine assembly for an aircraft, including an internal combustion engine having a liquid coolant system in fluid communication with a heat exchanger, an exhaust duct in fluid communication with air passages of the heat exchanger, a fan in fluid communication with the exhaust duct for driving a cooling air flow through the air passages of the heat exchanger and into the exhaust duct, and an intermediate duct in fluid communication with an exhaust of the engine and having an outlet positioned within the exhaust duct downstream of the fan and upstream of the outlet of the exhaust duct. The outlet of the intermediate duct is spaced inwardly from a peripheral wall of the exhaust duct. The engine assembly may be configured as an auxiliary power unit. A method of discharging air and exhaust gases in an auxiliary power unit having an internal combustion engine is also discussed.

Provided is a gas turbine system including: a compressor that compresses external air to generate compressed air; a combustor that burns the compressed air generated by the compressor together with fuel to generate a combustion gas; a turbine driven by the combustion gas generated by the combustor; an exhaust unit that guides a combustion gas that has passed through the turbine to outside; a nacelle formed in a cylindrical shape and extending along an axis line about which the turbine rotates and arranged so as to cover the compressor, the combustor, the turbine, and the exhaust unit; and an exit unit that guides the combustion gas, which passed through the turbine, to a discharge port provided in the surface of the nacelle.

The invention relates to a mixing device and a turbofan engine having such a mixing device 30 for mixing a first gas flow 40 with a second gas flow 50 in a turbofan engine 20, having an actuating device 95 and walls 60, which bound a channel 65 for the first gas flow 40 and a channel 70 lying radially outside for the second gas flow 50, the actuating device 95 comprising a coupling element 110 that is coupled to the walls (60), the actuating device 95 being designed to pivot the walls 60 between a first position and a second position disposed radially outside relative to the first position, the actuating device 95 comprising an adjusting ring 105 that can be rotated between a first rotating position and a second rotating position in the peripheral direction and that is joined to the coupling element 110.

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 turbine exhaust case (TEC) of a turbofan aeroengine includes a mixer in an annular wavy configuration having alternate crests and valleys, and a plurality of radial deswirling struts interconnecting an annular hub positioned within the mixer and selected valleys of the mixer. A plurality of secondary trailing edge struts smaller than the deswirling struts in average chord dimensions interconnect the annular hub and other selected valleys free of connection with the deswirling struts.