An assembly is provided for an aircraft propulsion system. This assembly includes a nacelle inner structure and a deflection limiter. The nacelle inner structure includes an internal compartment and a cowl. The internal compartment is configured to house a core of a gas turbine engine. The cowl is configured to form an outer radial periphery of the internal compartment. The cowl is also configured to form an outer radial periphery of a compartment exhaust to the internal compartment at an aft end of the cowl. The deflection limiter is attached to the cowl. The deflection limiter is configured to limit radial outward movement of the cowl.

An engine exhaust nozzle for a jet engine offers a controllable variable mixing of engine exhaust and the surrounding airflow. The engine exhaust nozzle includes a nozzle, slots at the downstream end of the nozzle, curved vanes extending radially inward from the inner surface of the nozzle and adjacent to the slots, and a cover connected to the outside of the nozzle and movable with respect to the nozzle so as to open and close the slots. When the slots are opened, near-field mixing is enhanced between the jet exhaust and the surrounding air, thus reducing mixing further downstream and the noise associated therewith, thus reducing the overall noise transmitted to the ground. When the slots are closed, the nozzle propulsive efficiency improves at the expense of increased noise.

An engine exhaust nozzle for a jet engine offers a controllable variable mixing of engine exhaust and the surrounding airflow. The engine exhaust nozzle includes a nozzle, slots at the downstream end of the nozzle, curved vanes extending radially inward from the inner surface of the nozzle and adjacent to the slots, and a cover connected to the outside of the nozzle and movable with respect to the nozzle so as to open and close the slots. When the slots are opened, near-field mixing is enhanced between the jet exhaust and the surrounding air, thus reducing mixing further downstream and the noise associated therewith, thus reducing the overall noise transmitted to the ground. When the slots are closed, the nozzle propulsive efficiency improves at the expense of increased noise.

The invention relates to a concentric gas flow mixer in a multiple-flow turbomachine, comprising a nominally cylindrical upstream part and a downstream part having outer and inner lobes distributed peripherally around the tower of said mixer, characterised in that it comprises at least one modified lobe having a wall thickness, in at least one area, which is different from the other lobes, so as to modify the vibratory response of said mixer.

The invention relates to a concentric gas flow mixer in a multiple-flow turbomachine, comprising a nominally cylindrical upstream part and a downstream part having outer and inner lobes distributed peripherally around the tower of said mixer, characterised in that it comprises at least one modified lobe having a wall thickness, in at least one area, which is different from the other lobes, so as to modify the vibratory response of said mixer.

An ejector assembly for a cooling system of a gas turbine engine may comprise: a tail cone having a tail cone outlet in fluid communication with a cooling air flow of the cooling system; an ejector body defining a mixing section, a constant area section, and a diffuser section; and a nozzle section in fluid communication with an exhaust air flow of the gas turbine engine, the ejector assembly configured to entrain the cooling air flow via the exhaust air flow.

An ejector assembly for a cooling system of a gas turbine engine may comprise: a tail cone having a tail cone outlet in fluid communication with a cooling air flow of the cooling system; an ejector body defining a mixing section, a constant area section, and a diffuser section; and a nozzle section in fluid communication with an exhaust air flow of the gas turbine engine, the ejector assembly configured to entrain the cooling air flow via the exhaust air flow.

Presented are flush-mounted fluid inlets, methods for making/using such fluid inlets, and aircraft equipped with flush-mounted air inlets for engine intake/cooling, bleed air flow, etc. A fluid inlet device is presented for improving vehicle aerodynamic performance. The fluid inlet device includes an inlet base that rigidly mounts to the vehicle, laying substantially flush with a washed outer surface across which fluid flows. The inlet base has a mouth that fluidly couples with a vehicle duct. Two sidewalls are attached to the inlet base, extending between leading and trailing edges of the inlet mouth. An inlet ramp, which is interposed between and attached to the sidewalls, projects inward at an oblique angle from the mouth's leading edge. A highlight is attached to the inlet base, projecting forward from the trailing edge towards the leading edge of the mouth. The highlight has a waveform plan-view profile and undulating outer surface.

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 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.

A propulsion system coupled to a vehicle. The system includes a diffusing structure and a conduit portion configured to introduce to the diffusing structure through a passage a primary fluid produced by the vehicle. The passage is defined by a wall, and the diffusing structure comprises a terminal end configured to provide egress from the system for the introduced primary fluid. A constricting element is disposed adjacent the wall. An actuating apparatus is coupled to the constricting element and is configured to urge the constricting element toward the wall, thereby reducing the cross-sectional area of the passage.