A method for assembling a shear web assembly of a wind turbine includes providing at least one spar cap. The method also includes forming a spar connecting member of a thermoplastic material via additive manufacturing. Further, the method includes securing the spar connecting member to the spar cap. Moreover, the method includes providing a shear web, forming a web connecting member of a thermoplastic material via additive manufacturing, and securing the web connecting member at a first end of the shear web. In addition, the method includes interconnecting the web connecting member and the spar connecting member at a joint. Thus, the method further includes heating the joint to secure the web connecting member and the spar connecting member together.

A cooling device uses siphon circulation whose heat source is an object-to-be-cooled installed in a vehicle to circulate refrigerant to the object-to-be-cooled, the cooling device including: a tank that is disposed above the object-to-be-cooled and stores the refrigerant; an outflow path that opens to the inside of the tank and through which the refrigerant flows out; a passage member that extends from the inside to the outside of the tank, with an open end of an inside section of the passage member positioned inside the tank being positioned above an opening of the outflow path; and identifying means that is provided at an outside section of the passage member positioned outside the tank and by which the position of the open end inside the tank can be identified.

A cooling device uses siphon circulation whose heat source is an object-to-be-cooled installed in a vehicle to circulate refrigerant to the object-to-be-cooled, the cooling device including: a tank that is disposed above the object-to-be-cooled and stores the refrigerant; an outflow path that opens to the inside of the tank and through which the refrigerant flows out; a passage member that extends from the inside to the outside of the tank, with an open end of an inside section of the passage member positioned inside the tank being positioned above an opening of the outflow path; and identifying means that is provided at an outside section of the passage member positioned outside the tank and by which the position of the open end inside the tank can be identified.

A cooling device uses siphon circulation whose heat source is an object-to-be-cooled installed in a vehicle to circulate refrigerant to the object-to-be-cooled, the cooling device including: a tank that is disposed above the object-to-be-cooled and stores the refrigerant; an outflow path that opens to the inside of the tank and through which the refrigerant flows out; a passage member that extends from the inside to the outside of the tank, with an open end of an inside section of the passage member positioned inside the tank being positioned above an opening of the outflow path; and identifying means that is provided at an outside section of the passage member positioned outside the tank and by which the position of the open end inside the tank can be identified.

A radial turbomachine with axial thrust compensation includes a rotor disc with main bladed rings. The main bladed rings together with auxiliary bladed rings delimit a plurality of concentric front main chambers at different pressures. A plurality of concentric rear annular main chambers, each in fluid communication with a respective front main chamber and at the same pressure as the respective front main chamber, is delimited between a rear face of the rotor disc and a fixed casing. The concentric front main chambers are delimited by front areas of the rotor disc and concentric rear annular main chambers are delimited by rear annular areas of the rotor disc. All the rear annular areas are identical to the respective front areas except for one, which is a compensation area configured to compensate, at least in part, for the thrust of external pressure acting on the shaft.

A radial turbomachine with axial thrust compensation includes a rotor disc with main bladed rings. The main bladed rings together with auxiliary bladed rings delimit a plurality of concentric front main chambers at different pressures. A plurality of concentric rear annular main chambers, each in fluid communication with a respective front main chamber and at the same pressure as the respective front main chamber, is delimited between a rear face of the rotor disc and a fixed casing. The concentric front main chambers are delimited by front areas of the rotor disc and concentric rear annular main chambers are delimited by rear annular areas of the rotor disc. All the rear annular areas are identical to the respective front areas except for one, which is a compensation area configured to compensate, at least in part, for the thrust of external pressure acting on the shaft.

A method for manufacturing a rotor blade panel of a wind turbine includes placing a mold of the rotor blade panel relative to a computer numeric control (CNC) device. The method also includes forming one or more fiber-reinforced outer skins in the mold. The method also includes printing and depositing, via the CNC device, printing and depositing, via the CNC device, a plurality of rib members that intersect to form at least one three-dimensional (3-D) reinforcement grid structure onto an inner surface of the one or more fiber-reinforced outer skins before the one or more fiber-reinforced outer skins have cooled from forming. Further, the grid structure bonds to the fiber-reinforced outer skin(s) as the structure is deposited. In addition, the plurality of rib members include, at least, a first rib member extending in a first direction and a second rib member extending in a different, second direction. Moreover, the first rib member has a varying height along a length thereof.

A turbine impeller includes: a base material which contains aluminum as a main element; and an anti-erosion coating which covers a surface of the base material. Accordingly, since liquid droplets hit the anti-erosion coating before the base material even when the liquid droplets flow into the rotating turbine impeller, the damage to the base material due to erosion is suppressed.

A turbine inlet supplies compressed air to drive a turbine impeller. There is a compressor impeller and a compressor inlet connected to supply air to be compressed to the compressor impeller. The compressor impeller delivers air to a compressor outlet. The compressor outlet is connected to the turbine inlet. A turbine outlet is connected to a first connection connected to an aircraft. The turbine impeller is connected to the compressor impeller by a drive shaft including a radially outwardly extending thrust disk, and thrust bearings provided on each side of the thrust disk. A cooling air inlet is connected to pass air along the thrust bearings, then radially inwardly and then axially along the shaft. The cooling air is directed to a cooling air outlet. The cooling air outlet is connected to a second connection maintained separate from the first connection. An environmental control system is also disclosed.

Provided is an improved architecture for rotary kinetic fluid motors and pumps, in which working fluid gains or loses pressure by flowing through an alternating sequence of radial-flow impellers and radial-flow fluid vortices, the impellers and fluid vortices all rotating around a single axis and in a common direction at staggered speeds, each vortex being the product of rotating fluid that is flowing radially through a bladeless annular volume.