Abstract: The disclosure relates to a cylinder head having at least one cylinder. The cylinder head comprises a radial turbine including a rotor arranged in a turbine casing and rotatably mounted on a shaft, an overall exhaust line which opens into an inlet zone of the radial turbine, said zone merging into a flow duct which carries exhaust gas, and at least one coolant duct integrated into the turbine casing to form a cooling system, the at least one coolant duct extending in a spiral around the shaft in the casing, wherein the at least one coolant duct extends circumferentially around and at a distance from the flow duct over an angle ?, where ??45°.

Abstract: A blower for a furnace is provided where the blower has an impeller that is configured to create a primary air flow of combustion air into the blower housing and a secondary air flow of cooling air through the blower motor. The primary air flow of combustion air into the furnace generates hot exhaust gases for a heat exchanger in the furnace. The secondary air flow cools the blower motor. The secondary air flow is mixed with the hot exhaust gases in the blower housing and cools the exhaust gases before being discharged from the blower housing.

Abstract: A blade assembly, which may have blisk for a gas turbine engine, includes an annular rim disposed about a rotor axis and a blade assembly disposed around the rim. The blade assembly has circumferentially disposed and radially extending inner and outer rows of inner and outer airfoils, respectively and each airfoil has axially spaced apart leading and trailing airfoil edges. An annular shroud is disposed between and connecting the inner and outer rows of inner and outer airfoils and has axially spaced apart annular leading and trailing shroud edges corresponding to the leading and trailing airfoil edges, respectively. An axially extending cavity is provided in each of the leading and trailing shroud edges for reducing stresses in leading and trailing airfoil edges, respectively and the corresponding airfoil edges are located near the cavities. The cavities preferably extend axially under the corresponding airfoil edges.

Abstract: An axial-flow reversible turbine comprises a nozzle assembly and a wheel rotor mounted consecutively in the direction of the flow of the working medium and provided with two-section blades. One section of said blades forms the flow duct of the direct-rotating turbine and the other section, the flow duct of the counter-rotating turbine. The flow duct of the direct-rotating turbine incorporates a valve in the form of variable-incidence airfoil vanes intended to deny the access of the working medium into said duct. The inside diameter of the flow duct of the counter-rotating turbine is larger than the outside diameter of the flow duct of the direct-rotating turbine. The gas flow ducts of the direct- and counter-rotating turbines communicate with each other through a cylindrical bushing with ports.

Abstract: An auxiliary fan is disposed upon the periphery of at least a portion of the fan of a conventional gas turbofan engine. Flow modulating components such as variable vanes and nozzles are utilized in conjunction therewith to produce a wide range of operating bypass ratios. Such an engine is one of the variable cycle variety and has the capability of operating efficiently at both subsonic and supersonic speeds.