Radial turbine blade system

Abstract

A radial turbine blade system comprised of airfoils forming a circular array on a disk or series of disks around a central opening which serves as the exhaust outlet. Single or multiple sections comprised of a circular array of airfoils on a disk are arranged along the central axis. Nozzles direct high velocity mass flow fluids between the disks and onto the leading edges the airfoils. Three forces are used to convert the high velocity mass flow to mechanical output. First, is the shock effect of high velocity particles striking the leading surface of the airfoils. Second, is the lift force vector produced by the fluid flow over the airfoils. Third, is the fluid motive force of the high velocity mass flow contacting the inner walls of the disks. The invention can utilize various types of fluid forces such as gasses produced from the combustion of fuel or steam.

I claim:  
     
         1 . A rotational radial turbine blade system for translating motive energy comprised of airfoils which form a circular array on a disk or series of disks around a central opening which serves as the exhaust outlet. The longest airfoils on each disk extend from the outer edge of the disk to the outer edge of the exhaust opening. Smaller airfoils are interspersed in the remaining gaps between the longer airfoils. The number of longer airfoils and length of the longer airfoils varies depending on the size of the disk(s). The number of smaller airfoils and the number of arrays of distinct lengths of smaller airfoils varies depending on the size of the disk and the application. Multiple sections may be arranged side-by-side along the central axis (e.g. stacked) in order to increase the power output of a single system. The radial turbine blade system rotates about the central axis of the disks. Nozzles are used to direct the high velocity mass flow of fluids between the disks and onto the leading edges the airfoils which extend radially from the central exhaust opening. The airfoil array and disk system combined with at least one nozzle between each disk spacing, with the nozzle outlet positioned in line with each airfoil array, comprise this claim.