A heat exchanger for an aircraft engine includes: a body including a plate-like first member and a plate-like second member that are stacked in a thickness direction of the first and second members and joined together, and a channel which is defined in the body and in which the cooling target fluid flows; and a corrugated fin plate disposed in the channel in the body. The body is bent along a curved surface to which the heat exchanger is attached. A plurality of heat dissipation fins stand on an outer surface of at least one of the first member or the second member.

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.

A seal assembly includes a seal arc segment that defines first and second seal supports and radially inner and outer sides with the radially outer side including radially-extending sidewalls and a radially inner surface that joins the radially-extending sidewalls. The radially-extending sidewalls and the radially inner surface define a pocket. The seal assembly includes a carriage that defines first and second support members with the first support member supporting the seal arc segment in a first ramped interface and the second support member supporting the seal arc segment in a second ramped interface. The radially inner surface has a higher surface roughness than the radially extending sidewalls.

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.

A simple-cycle gas turbine system includes an injection system including a plurality of injection tubes that may inject a fluid into a duct of an exhaust processing system that may process exhaust gas generated by a gas turbine engine. The exhaust processing system includes a selective catalytic reduction (SCR) system that may reduce a level of nitrogen oxides (NO.sub.x) within the exhaust gas; and a mixing system positioned adjacent to the plurality of injection tubes and within the exhaust processing system. The mixing system includes a mixing module having a plurality of turbulators that may swirl the fluid, or the exhaust gas, or both, in a first swirl direction to encourage turbulent flow along an axis of the exhaust processing system and thereby facilitate mixing between the fluid and the exhaust gas.

The invention relates to a profiled structure, elongated in a direction in which the structure has a length exposed to an airflow, and transversely to which the structure has a leading edge (164) and/or a trailing edge, at least one of which is profiled and has, in said direction of elongation, serrations (28a) defined by successive teeth (30) and depressions (32).

Along the profiled leading edge and/or profiled trailing edge, the successive teeth (30) and depressions (32) extend only over a part of said length exposed to the flow over which the amplitude and/or spacing of the teeth varies monotonically except for the few teeth nearest each end of said part, a remaining part (280) of said length being smooth.

An acoustic panel is provided that includes a perforated first skin, a second skin and a core. The core is between and connected to the perforated first skin and the second skin. The core includes a plurality of chambers, a first corrugated structure and a second corrugated structure. The chambers includes a first chamber. The first chamber extends from the perforated first skin, through the first corrugated structure and the second corrugated structure, to the second skin.

A gear baffle, a gearbox of a gas turbine engine including a gear baffle, and a method of installing a gear baffle adjacent to a gear in a gearbox of a gas turbine engine are disclosed. The gearbox includes a housing, having disposed therein a gear, and a baffle adjacent to the gear to interact with lubricant fluid around the gear. The baffle includes a first interface for attaching the baffle to a structure to a first side of the gear, and a second interface for attaching the baffle to a structure to a second, axially opposite, side of the gear. The second interface may be axially spaced apart from the first interface by an axial distance. The baffle may include a main wall interconnecting the first interface with the second interface. The main wall may include a compliant corrugation that accommodates a variation in the axial distance between the first interface and the second interface.

A turbomachine blade including a body that extends mainly in a plane defined by a main axis B and a longitudinal direction, which is defined by a lower surface wall, an upper surface wall, a leading edge located at a first longitudinal end of the body and a trailing edge located at a second longitudinal end of the body, wherein the body of the blade includes a plurality of first pipes that extend mainly along the direction of the main axis B, for circulation of a gas flow, and a plurality of second pipes that extend mainly along the longitudinal direction, for circulation of a second gas flow.

A turbomachine includes a rotor and a stator, the stator having a plurality of profiled structures, each profiled structure being elongated in a direction of elongation in which the profiled structure has a length exposed to an airflow, and having a leading edge and/or a trailing edge, at least one of which is profiled and has, in said direction of elongation, serrations defined by a succession of peaks and troughs and having a geometric pattern transformed, over at least a part of said length exposed to the airflow, by successive scaling, via multiplicative factors, in the direction of elongation and/or transverse to the direction of elongation. The geometric pattern, as defined with reference to a radial distribution of the integral scale of the turbulence, evolves in a non-periodic manner.