A turbine vane including at least one inner cavity including a plurality of deflectors which are carried by an inner face of the lower surface wall and by an inner face of the upper surface wall, wherein each deflector extends mainly in a transverse direction from the inner face of the lower surface wall or from the inner face of the upper surface wall, in the direction of the other one of the lower surface wall or the upper surface wall, and wherein the length of each deflector in the transverse direction is greater than half the transverse distance between the inner face of the lower surface wall and the inner face of the upper surface wall, on either side of the deflector.

A compressor device of a supercharging device for an internal combustion engine (1), having an inlet channel (21) with a side wall (23), an exhaust-gas inlet (25) in the side wall (23), at which exhaust-gas inlet an exhaust-gas recirculation channel (27) opens into the inlet channel (21), and a flow barrier (29) in the inlet channel (21), which flow barrier at least partially spans the exhaust-gas inlet (25), is spaced apart from the exhaust-gas inlet (25) and is suitable for diverting exhaust gas which flows from the exhaust-gas inlet (25) into the inlet channel (21) at an angle with respect to an axial direction of the inlet channel (21) or with respect to the axis of a compressor (3).

A guide vane for a turbomachine, having a blade airfoil and at least one platform, to which the blade airfoil is connected. A cooling channel system is provided for cooling the platform and the blade airfoil. The platform has, on the side thereof facing the airfoil, at least one sealing lip for sealing to a rotating system of the turbomachine. At least one cooling channel extends through the sealing lip, which cooling channel forms part of the cooling channel system.

A diffuser and deswirl flow structure includes a plurality of tube structures with an outer wall that is hollow and elongate and that extends between a first portion and a second portion. The plurality of tube structures is disposed in an annular arrangement about the longitudinal axis. The flow structure also includes a plurality of flow passages extending through the tube structures. The plurality of flow passages extend from the first portion to the second portion, respectively. The plurality of flow passages respectfully include a diffuser portion, which is proximate the first portion and configured to diffuse a fluid flow from a compressor wheel. The plurality of flow passages respectfully include a deswirl portion, which is proximate the second portion and configured to deswirl the fluid flow from the diffuser portion. The outer wall defines the diffuser portion and the deswirl portion. The outer wall is self-supporting.

Baffle inserts for airfoils of gas turbine engines are described. The baffle inserts include a baffle insert body having a first side portion and a second side portion, wherein each side portion has a respective end, a first set of vortex generation elements is arranged at the end of the first side portion, and a second set of vortex generation elements is arranged at the end of the second side portion. The first set of vortex generation elements and the second set of vortex generation elements are arranged at an aft end of the baffle insert body.

Methods and apparatuses for reducing engine noise provided. In one embodiment, an apparatus is provided that includes a plurality of seals and flaps that are interconnected and circumferentially arranged. Also included are a plurality of micro-vortex generator pairs respectively disposed in a circumferential manner on an interior surface of the seals. Each micro-vortex generator pair includes a first and second micro-vortex generator. In another embodiment, a method of generating a plurality of vortices in a nozzle section of a jet engine is provided. A plurality of micro-vortex generator pairs are provided on a plurality of seal surfaces of the nozzle section, respectively. The micro-vortex generator pairs are constructed to generate two vortices adjacent to an interior surface of the nozzle section and extending in a direction towards a nozzle exit. The interaction between the nozzle flow and the micro-vortex generator pairs greatly modify the shock cell structure within the nozzle section and the turbulence structure in the jet plume.

An assembly for a turbomachine through which an air flow passes, includes a stator including guide vanes extending radially in relation to a longitudinal axis, at least one inter-vane platform extending between the radially outer ends of two circumferentially consecutive guide vanes, each inter-vane platform including an outer surface that faces the axis, a heat exchanger located downstream of the stator in relation to a direction of circulation of the air flow in the turbomachine during operation, this stator including a heat exchange surface extending in the extension of an inter-vane platform. At least one inter-vane platform located in the upstream extension of the heat exchange surface is provided with at least one turbulence generator on its outer surface.

Exhaust frequency mitigation apparatus, exhaust diffusers, and turbomachines are provided. An exhaust frequency mitigation apparatus includes a main body extending along an axial centerline from a base to a tip. the base defines a first diameter and the tip defining a second diameter. the main body converges from the first diameter to the second diameter with respect to the axial centerline. The base is configured to extend from an inner shell of a turbomachine exhaust diffuser. The exhaust frequency mitigation apparatus further includes at least one rib extending from a root coupled to the main body to a free end.

A turbine includes: a rotatable impeller with a hub provided with a plurality of rotor blades; and a tubular member in which a diffuser located downstream of the impeller is formed. On an inner surface of the tubular member, a plurality of projections projecting radially inward of the tubular member are formed at positions closer to an inlet end of the tubular member than an outlet end of the tubular member. The plurality of projections are arranged in a circumferential direction of the inner surface so as to leave a space between adjacent projections.

A tip shroud, comprising a plurality of tip shoes encircling a rotor assembly, in a turbine may deform due to thermal gradients experienced during operation of the turbine. Accordingly, a tip shoe is disclosed that utilizes an internal cooling cavity to supply coolant throughout the interior of the tip shoe, as well as to the slash faces of the tip shoe. In addition, features are described that increase the surface area exposed to the coolant, while remaining suitable for additive manufacturing.