A mixer assembly group for a turbofan engine, having a primary flow channel extending along a central axis of the turbofan engine and a secondary flow channel. The mixer assembly group includes a mixer for guiding a first fluid flow from the primary flow channel and a second fluid flow from the secondary flow channel in the direction of an exhaust of the turbofan engine, as well as for intermixing the first and second fluid flows, and a connection appliance, which has at least one connection component that is fixated at the mixer and by means of which the mixer assembly group is to be fixated at two different first and second engine components of the turbofan engine, with are subject to operating temperatures of different heights during operation of the turbofan engine.

An assembly for a rear of a dual-flow turbomachine having a longitudinal axis includes a secondary nozzle and a heating system. The secondary nozzle is defined about the longitudinal axis and ejects a mixture of the flows coming from a secondary vein and a primary vein of the turbomachine. The secondary nozzle is of a convergent-divergent form with a neck corresponding to a minimal cross-cross-section of the secondary nozzle. The heating system is located on a portion of the internal circumference of the secondary nozzle longitudinally in the region of the neck or upstream from the neck.

An assembly for a rear of a dual-flow turbomachine having a longitudinal axis includes a secondary nozzle and a heating system. The secondary nozzle is defined about the longitudinal axis and ejects a mixture of the flows coming from a secondary vein and a primary vein of the turbomachine. The secondary nozzle is of a convergent-divergent form with a neck corresponding to a minimal cross-cross-section of the secondary nozzle. The heating system is located on a portion of the internal circumference of the secondary nozzle longitudinally in the region of the neck or upstream from the neck.

An ejector including a mixing section; an inlet to the mixing section, the inlet comprising a first wall; a nozzle disposed in the inlet; the nozzle comprising the second wall defining a first channel through the nozzle, wherein the first wall and the second wall define a second channel through the inlet, the second wall has a trailing edge and a curved surface including a varying radius of curvature defining depressions extending to the trailing edge, a first flow of a first fluid into the second channel creates a pressure in the mixing section that draws a second flow of a second fluid through the first channel and into the mixing section, and the first flow and the second flow interact along the curved surface including the depressions and the trailing edge, forming a mixture comprising the first fluid and the second fluid. An outlet from the mixing section outputs the mixture, wherein the flow is well mixed and contains significant amounts of each fluid.

A method of controlling plume exhaust heat and/or noise radiation from a turbofan engine assembly having a short nacelle. A mixer duct shell is supported such that a downstream edge of the short nacelle overlays an upstream portion of the mixer duct shell. A first portion of fan exhaust may be routed through the mixer duct shell between its inner surface and an outer surface of a core engine shroud. A second portion of fan exhaust may be routed over an outer surface of the mixer duct shell. At least one of the inner surface and an outer surface of the mixer duct shell may have an acoustic lining including a honeycomb core structure.

A method of controlling plume exhaust heat and/or noise radiation from a turbofan engine assembly having a short nacelle. A mixer duct shell is supported such that a downstream edge of the short nacelle overlays an upstream portion of the mixer duct shell. A first portion of fan exhaust may be routed through the mixer duct shell between its inner surface and an outer surface of a core engine shroud. A second portion of fan exhaust may be routed over an outer surface of the mixer duct shell. At least one of the inner surface and an outer surface of the mixer duct shell may have an acoustic lining including a honeycomb core structure.

A compression inner core cowl for a jet engine can have a concave annular section of the core cowl. The concave section can begin within the expanse of an outer fan cowl and extend aft of the fan cowl toward the tail cone, defining an annular bypass section between the fan cowling and the core cowling. The concave geometry of the core cowling reduces the strength of supersonic shock waves generated at the corners of the cowlings adjacent a supersonic airflow stream to increase overall efficiency of the engine.

It is provided a mixer for an engine, that for the mixing of fluid flows from a primary flow channel and a secondary flow channel of the engine, respectively has multiple first and second guide elements that alternate along a circumferential direction and extend along a central axis, wherein the first guide elements are formed in a diffusor-like manner with at least one radially outwardly extending section, and the second guide elements are formed in a nozzle-like manner with at least one radially inwardly extending section, and the mixer is made of a composite material with at least two separate material layers. The at least two material layers are arranged with their edges along the central axis in an overlapping manner and/or edge to edge, and namely in an area of the mixer in which the first and second guide elements are provided.

It is provided a mixer for an engine, that for the mixing of fluid flows from a primary flow channel and a secondary flow channel of the engine, respectively has multiple first and second guide elements that alternate along a circumferential direction and extend along a central axis, wherein the first guide elements are formed in a diffusor-like manner with at least one radially outwardly extending section, and the second guide elements are formed in a nozzle-like manner with at least one radially inwardly extending section, and the mixer is made of a composite material with at least two separate material layers. The at least two material layers are arranged with their edges along the central axis in an overlapping manner and/or edge to edge, and namely in an area of the mixer in which the first and second guide elements are provided.

An ultrashort nacelle configuration employs a fan cowl having an exit plane and a serrated trailing edge. A variable pitch fan is housed within the fan cowl. The variable pitch fan has a reverse thrust position inducing a reverse flow through the exit plane and into the fan cowl. The serrated trailing edge forms a plurality of vortex generators configured to induce vortices in the reverse flow.