Embodiments are directed to systems and methods for reducing the infrared signature of a vehicle, specifically to the use of mixed flow or centrifugal blowers to reduce the amount of infrared radiation being emitted from the engine exhaust. A blower and mixer are used to cool the exhaust gas from an aircraft engine. The blower and mixer use a tertiary exhaust duct to swirl cool air from an engine particle separator (EPS) and/or oil cooler, for example, with the hot engine exhaust gas. Existing blowers in the EPS or oil cooler may be used to motivate air flow so that a unique or dedicated blower is not required. In addition to reducing exposure to hostile forces, other benefits of cooling the exhaust gas include greatly reduced ground-impingement temperatures and safer personnel working zones because the hot plume is mostly eliminated.

A turbine impeller includes: a hub portion coupled to an end of a rotational shaft; a plurality of main blades disposed at intervals on a peripheral surface of the hub portion; and a short blade disposed between two adjacent main blades among the plurality of main blades. An inter-blade flow channel is formed between the two adjacent main blades so that a fluid flows through the inter-blade flow channel from an outer side toward an inner side of the turbine impeller in a radial direction. In a meridional plane, a hub-side end of a leading edge of the short blade is disposed on an inner side, in the radial direction, of a hub-side end of a leading edge of the main blade.

A turbine of an organic Ranking cycle (ORC) is described. The turbine includes a shaft supported by at least two bearings and a plurality of axial stages of expansion, defined by arrays of stator blades alternated with arrays or rotor blades. The rotor blades are sustained by corresponding supporting disks. A main supporting disk is directly coupled to the shaft in an outer position with respect to the bearings, and the remaining supporting disks are constrained to the main supporting disk, and one to the other in succession, but not directly to the shaft. Some of the remaining supporting disks are constrained to the main supporting disk and cantileverly extend from the same side of the bearings that support the shaft, so that the center of gravity of the rotor part of the turbine is shifted more towards the bearings.

A centrifugal compressor includes: a rotational shaft; a main casing surrounding at least a part of the rotational shaft, the main casing having an inlet and an outlet separated from each other in an axial direction of the rotational shaft and an annular space surrounding a section of the rotational shaft at a side of the inlet and communicating with the inlet; at least one impeller disposed in a fixed state to the rotational shaft inside the main casing; a flow guide member disposed inside the annular space and extending along the axial direction of the rotational shaft; a plurality of injection holes disposed along the flow guide member and separated from one another along the axial direction of the rotational shaft; and a flow path which extends inside the annular space and through which a cleaning fluid to be supplied to the plurality of injection holes is capable of flowing.

A radial inflow turbine includes a turbine wheel having a blade, in which a hub-side end of a leading edge of the blade is located radially inward relative to a shroud-side end of the leading edge, and a housing having a scroll part and a bend part deflecting a flow of a working fluid flowing radially inward from the scroll part, along an axial direction. The turbine wheel has at least one through hole bypassing the blade.

The present invention describes an axial pump for pumping liquid metal, the axial pump comprising an inlet for receiving liquid, at least one rotor, the rotor comprising a rotor hub and a plurality of rotor blades positioned thereon, a stator, comprising a stator hub and a plurality of stator vanes, and an outlet for discharging the liquid metal, the pump being adapted for providing efficient pumping while reducing or avoiding erosion of the pump by the liquid metal.

A combustion chamber arrangement comprises an annular combustion chamber, a plurality of circumferentially arranged vanes and a radially inner sealing ring. The vanes are arranged at the axially downstream end of the annular combustion chamber. Each of the vanes comprises an aerofoil extending radially between a radially inner platform and a radially outer platform. The radially inner sealing ring forms a seal between a downstream end of a radially inner annular wall structure of the combustion chamber and the radially inner platforms of the vanes. A portion of the axial length of the radially inner sealing ring comprises a radially inner wall and a radially outer wall spaced radially from the radially inner wall to define a chamber. The radially inner wall has apertures to supply coolant into the chamber and the radially outer wall has effusion cooling apertures to supply coolant onto the surface of the radially outer wall.

An aircraft engine, comprising a thermal engine, an axial turbine having a turbine inlet, and an exhaust assembly fluidly connecting the thermal engine to the axial turbine. The exhaust assembly includes a housing and a deflector removably mounted within the housing. The deflector has circumferentially distributed vanes. The deflector is a first deflector, having a first set of geometric characteristics, that is removable from the housing and replaceable by a second deflector having a second set of geometric characteristics different from the first set of geometric characteristics. The first deflector is one of a first class of deflectors and the second deflector is one of a second class of deflectors, the first and second class of deflectors respectively defining first and second exhaust flow profiles that differ from each other.

A turbine wheel for a turbine of an exhaust gas turbocharger. The turbine wheel has a base body comprising a back wall and a plurality of turbine blades, connected to the base body, which each comprise a leading edge. The leading edges are designed to be wave shaped.

A fume exhaust assembly and a fume exhaust device are provided. The fume exhaust assembly includes a fan, a vortex generating portion, a fume intake pipe, and a fume exhaust pipe. The vortex generating portion includes a vortex pipe and an air intake channel. The air intake channel is in communication with the vortex pipe, an inlet of the air intake channel is connected to the fan, and an outlet of the air intake channel is configured to generate a vortex updraft in the vortex pipe. The fume intake pipe and the fume exhaust pipe are in communication with the vortex pipe. An outlet of the fume intake pipe is arranged above the outlet of the air intake channel. The outlet of the fume intake pipe is configured to be in communication with a low-pressure zone of the vortex updraft. The fume exhaust pipe is connected to an outlet of the vortex pipe.