A mixing system for a power generation system. The power generation system includes a rotary machine, an exhaust processing system, and a duct system. The rotary machine is configured to produce an exhaust stream. The exhaust processing system is positioned to receive and process the exhaust stream. The duct system is oriented to channel an air stream to the exhaust processing system and to channel the exhaust stream from the rotary machine to the exhaust processing system. The mixing system is within the duct system. The mixing system includes a plurality of supports, a plurality of links extending between at least two of the supports, and at least one wrap circumscribing at least two of the links. The at least one wrap is oriented to change an effective direction of momentum of the exhaust stream and the air stream.

An ejector comprises a primary nozzle having an annular wall forming part of an outer boundary of an exhaust portion of a primary flow path of a gas turbine engine. The annular wall has a downstream end defining a plurality of circumferentially distributed lobes. The ejector further comprises a secondary nozzle having an annular wall disposed about the primary nozzle, the primary nozzle and the secondary nozzle defining a secondary flow passage therebetween for channeling a secondary flow. The secondary nozzle defines a mixing zone downstream of an exit of the primary nozzle. A flow guide ring is mounted to the primary nozzle lobes. The ring has an aerodynamic surface extending from a leading edge to a trailing edge respectively disposed upstream and downstream of the exit of the primary nozzle. The aerodynamic surface of the ring is oriented to guide the high velocity primary flow into the mixing zone.

The invention relates to a turbine engine separate flow mixer centered on a longitudinal axis, comprising an exhaust housing, a shroud directly connected to the exhaust housing and intended to mix the flows originating in the turbine engine, said shroud comprising a metal sheet formed by a succession of first and second longitudinal strips distributed circumferentially around the longitudinal axis of the mixer by circumferentially placing the second strips on either side of the first strips, the first and second strips being configured to form the shroud when at rest and grooves in the shroud when operating, the grooves being defined by an alternation of internal lobes and of external lobes.

In a cowl for a nozzle, an internal wall has a cross-section with a determined abscissa on the axis defining a neck line on the internal wall. The cowl has, downstream of the determined abscissa, indentations in the trailing edge which delimit chevrons distributed in the circumferential direction. The internal wall of the cowl diverges radially towards the interior, in a second axial half-plane passing through the tip of a chevron, from the upstream tangent on the point of the neck line in the second axial half-plane, and the lines defining the internal wall of the cowl in any axial half-plane do not have a turning point downstream of the determined abscissa of the neck line.

An exhaust casing for a gas turbine engine comprises a shroud configured to surround an exhaust cone, and a heat shield attached to the shroud. The heat shield has a first end and a second end axially spaced apart from each other. A gap is defined radially between the shroud and the heat shield. The gap is configured to enclose at least a portion of an interface defined between at least one strut and the shroud. The exhaust casing is configured to surround the exhaust cone and configured to be connected to the exhaust cone via the at least one strut.

An exhaust duct of a gas turbine engine comprises a hub defining a radially-inner surface of a substantially annular exhaust gas path, and a strut extending into the exhaust gas path. The strut is attached to the hub via a first fastener at a forward fastening location closer to a leading edge of the strut than to a trailing edge of the strut, and via a second fastener at an aft fastening location closer to the trailing edge than to the leading edge. The second fastener is engaged with an appendage of the strut. The appendage is received into a receptacle formed in the hub open to the radially-inner surface.

A propulsion unit includes a gas turbine engine arranged along an axis and an exhaust system coupled to the gas turbine engine. The gas turbine engine includes an engine core configured to discharge a core flow and a fan configured to be driven by the engine core to discharge a bypass flow. The exhaust system receives the mixed bypass and core flows from the gas turbine engine.

An exhaust duct of a gas turbine engine comprises a hub defining a radially-inner surface of a substantially annular exhaust gas path, and a strut extending into the exhaust gas path. The strut is attached to the hub via a first fastener at a forward fastening location closer to a leading edge of the strut than to a trailing edge of the strut, and via a second fastener at an aft fastening location closer to the trailing edge than to the leading edge. The second fastener is engaged with an appendage of the strut. The appendage is received into a receptacle formed in the hub open to the radially-inner surface.

A turbine exhaust assembly for a gas turbine engine according to an example of the present disclosure includes, among other things, a turbine exhaust case comprised of CMC material and attachable to a turbine case, a tail cone comprised of CMC material that has a leading edge and a trailing edge, and an exhaust mixer comprised of CMC material and coupled to the turbine exhaust case. The exhaust mixer has a plurality of lobes arranged about the tail cone to define an exhaust flow path. A plurality of struts extend from the tail cone to support the exhaust mixer at a location aft of the leading edge of the tail cone. A method of assembling a propulsion system is also disclosed.

An exhaust mixer for a gas turbine engine where each outer lobe has at the downstream end a circumferential offset in a direction corresponding to that of the swirl component of the flow entering the mixer. The mixer has a crest line having at least a downstream portion curved with respect with respect to a circumferential direction of the mixer and/or a center line at the downstream end tilted with respect to a radial line extending to the tip of the outer lobe to define the circumferential offset. A method of mixing a core flow and a bypass flow surrounding the core flow with an annular mixer is also provided.