196 results about "Axial turbine" patented technology

A hydraulic turbine power generator mounted on a single shaft wherein the hydraulic turbine means includes a plurality of reaction type turbine stages arranged to be in combination, rotatably responsive to the hydraulic fluid coupled to the turbines. One of the turbine stages having axial turbine runner means mounted to the single shaft and having a plurality of adjustable blades for permitting the pitch of the blades to be adjusted for controlling the effective operative fluid head to cause the shaft to rotate at a preselected speed and including means for adjusting the pitch of the adjustable blades. The turbine stages can be a Francis type turbine and a Kaplan type turbine. The hydraulic turbine power generator can be oriented in an upward direction to cause the fluid flow to travel upwardly through the turbine stages and function as a two phase turbine expander resulting in the separation of the liquid phase from the gas / vapor stage.

An interturbine duct for channelling combustion gases between two axial turbine stages. The interturbine duct is made of sheet material to provide a relatively lightweight construction.

In the axial turbine according to the present invention, a nozzle blade 1 and / or a movable blade 5 has a profile in which a throat-pitch ratio “s / t” is maximized at a blade-central portion in height, wherein “s” being a shortest distance between a rear edge of a nozzle blade (movable blade) and a back side of another nozzle blade that is adjacent to the nozzle blade, and “t” being a pitch of the nozzle blades disposed in the row, minimized in a position between the blade-central portion in height and a blade-root portion and increased from a minimized value to the blade-root portion. This structure enables to provide the axial turbine, which permits to control flow distribution of the working fluid in the height direction of the blade in the passage between the blades of a turbine nozzle unit and a turbine movable nozzle and reduce the blade profile loss and the secondary flow loss at the blade-root portion, thus making a further improvement in the turbine stage efficiency.

A turbocharger, having an axial compressor wheel and an axial turbine wheel mounted on a first shaft supported by a housing, and a radial compressor wheel and a radial turbine wheel mounted on a second shaft, the second shaft concentrically extending around the first shaft and being supported by the housing. The housing defines a first duct extending axially from the exducer of the axial compressor to the inducer of the radial compressor, and a second duct extending axially from the exducer of the radial turbine to the inducer of the axial turbine. A plurality of controllable compressor guide vanes extend through the first duct, and a plurality of controllable turbine stator vanes extend through the second duct. The housing is provided with variable diffuser vanes at the exducer of the radial compressor, and with variable turbine vanes at the inducer of the radial turbine. The variable turbine vanes and the turbine stator vanes are controlled to accurately control the rotation rate of the radial and axial turbines. The compressor guide vanes are controlled to minimize surge and maximize choke flow rate.

This invention relates to an abradable coating system for use in axial turbine engines. When coated onto a turbine ring seal segment the coating system may allow formation of an individualized seal between turbine blade disks and the surrounding ring seal without causing excessive wear to the blade tips. The abradable coating system includes columns of an abradable material. Thus, interference between the blades and the abradable coating system causes the individual columns to break off at the base. This abrasion mechanism may reduce blade wear and spalling of the coating system when compared to conventional coatings.

A damping arrangement for a blade (20) of an axial turbine, in particular a gas turbine, includes a damping element (17) which is arranged in a recess (16) in the blade aerofoil (10) of the blade (20) and frictionally dampens the vibrations of the blade (20). In such a damping arrangement, simplified manufacture and assembly and a reliable and effective function are achieved by the recess being configured as a cavity (16) extending in the radial direction through the inside of the blade aerofoil (10), the damping element (17) being inserted in the radial direction into said cavity (16).

A heat engine having a rotary vane compressor and a rotary vane turbine operates in a highly efficient thermodynamic cycle which includes a power expansion phase up to ambient pressure and a limited temperature constant volume combustion followed by a constant pressure combustion and / or a constant temperature combustion. A compound propulsion engine utilizing the thermodynamic cycle has a primary stage having an axial compressor and a rotary vane turbine, and a secondary stage having an axial turbine and a rotary vane compressor, the two stages being aero-thermodynamically coupled to each other without provision of an interconnecting drive shaft.

A tandem axial turbine that comprises a front confusor, a funnel-shaped runner having inner blades and capable of accelerating and directing an oncoming flow toward a co-axial rear runner which rotates in an opposite direction. A tangential turbine has a hub, blades capable of rotating in relation to the hub between positions across and along the flow, and propulsion springs for controlling the movement of the blades in relation to the hub and the transfer of the energy. A second tangential turbine comprises a runner having a hub and blades and a shroud capturing the runner from above and around and permitting the blades to dip into water flowing immediately below the hub and an opening of the shroud. A surface vessel comprises a stabilized frame rotatably affixed on a vessel hull about a center of wave induced rocking motions of the vessel and therefore isolated from a rocking motion of the vessel.