text: fig1 the invention will now be described with reference to the drawing figures , in which the reference numerals refer to like parts throughout . the embodiment of the invention consists of a rotating assembly of aerodynamic configured blades subject to the force of the wind that will convert the rotational motion of the assembly to a force to power the driveshaft which couples to a power generator . illustration on fig1 shows the lower disk 100 configured for counter clockwise rotation , however the geometry of the disks and blade of the design could be configured in a mirror image to enable clockwise rotation . the lower disk 100 provides recesses 101 to accept the blade pivot bearings 203 identified in fig2 and provides blade positioning channels 102 to accept the blade travel limiting follower pin 202 indentified in fig2 . provision for assembly of the disk 100 and the lower section of the drive shaft 401 indentified in fig3 and middle section of the drive shaft . 402 indentified in fig3 . is shown by cavities 103 . in the counter clockwise rotation mode the bottom of the upper disk 302 identified in fig3 is the mirror image of all the features indentified in fig1 . fig2 is a top down view of the lower disk 100 of the rotating assembly with eight blades 200 in place . the lower disk 100 and the bottom of the upper disk 300 identified in fig3 is the mirror image . the significance of the blade aerodynamic shape and the dimensional relationship of the blade pivot bearing projection 201 and blade travel limiting follower pin 202 determines the ability of each blade to assume its most effective position in the wind stream to generate a rotational force to drive the assembly , and therefore generate the greatest system power . fig3 ( new ) is a view of the individual parts of the rotating assembly , the upper shaft 403 is piloted through the upper disk 300 and fastened to the middle shaft 402 through holes 304 to the middle shaft at hole locations 407 by fasteners 405 . the middle shaft 402 is piloted through the lower disk 100 and fastened to the lower shaft 401 through holes 103 to the lower shaft at hole locations 409 by fasteners 405 . also identified is a representative blade assembly comprised of a blade 200 with the blade pivot bearing projections 201 and with the upper pivot bearing 203 and lower pivot bearing 203 and the blade travel limiting follower pins 202 which are retained and allowed to articulate between the upper disk 100 and lower disk 300 . fig4 new ) is a vertical cross section through the rotating assembly . fig5 ( new ) is a view of the complete assembly from the downwind side of the structure and the blades shown correspond to their location shown on fig2 . fig5 shows one method of mounting the assembly of fig2 by a vertical shaft turbine support structure . the rotating assembly is supported at the bottom by a base mounted bearing support 501 containing a bearing 502 . both of these parts are shown in the bottom section view . the design shown on this fig5 can have multiple support legs similar to a birdcage 503 . the rotating assembly is supported at the top by a bearing support 504 containing a bearing 505 . these parts are shown in the top section . fig6 ( new ) is a view looking down on the lower disk of the rotating assembly and a blade angle rotation limiter scheme which replaces the blade positioning channels 102 identified in fig1 with fixed protruding blade travel limiting stops 604 mounted on the disk . illustration on fig6 shows the lower disk 600 which provides recesses 601 to accept the blade pivot bearings 603 and is configured for counter clockwise rotation , however the geometry of the disks and blade of the design could be configured in a mirror image to enable clockwise rotation . in this embodiment the lower disk 600 provides fixed protruding stops 604 to provide blade travel limitation . in the counter clockwise rotation mode the bottom of the upper disk 700 identified in fig8 is the mirror image of all the features indentified in fig7 . fig7 ( new ) is a view looking down on the lower disk of the rotating assembly with the turbine blades in optimum positioning to yield maximum self regulated output of the turbine and a method using a blade angle rotation limiter scheme which replaces the blade positioning channels 102 in fig1 with fixed protruding blade travel limiting stops mounted on the disk . illustration on fig7 shows the lower disk 600 provides fixed protruding stops 604 to provide blade travel limitation . fig7 shows blades 800 optimum positioning to yield maximum self regulated output of the turbine . fig7 shows blade pivot bearing projection 801 . fig8 ( new ) is a view of the individual parts of the rotating assembly utilizing fixed protruding stops 604 , the upper shaft 403 is piloted through the upper disk 700 and fastened to the middle shaft 402 through holes 704 to the middle shaft at hole locations 407 by fasteners 405 . the middle shaft 402 is piloted through the lower disk 600 and fastened to the lower shaft 401 through holes 606 to the lower shaft at hole locations 409 by fasteners 405 . also identified is a representative blade assembly comprised of a blade 800 with the blade pivot bearing projections 801 and with the upper pivot bearing 603 and lower pivot bearing 603 which are retained and allowed to articulate between the upper disk 700 and lower disk 600 . fig9 ( new ) is a vertical cross section through the rotating assembly . fig1 ( new ) is a detail drawing of an individual blade 800 with one embodiment of blade travel limitation using fixed protruding stops 604 with one embodiment of a mechanical attachment of the stop 605 for blade travel limitation and a section view of the lower disk 600 that receives the blade . fig1 ( new ) is a view looking down on the lower disk 600 of the rotating assembly with the turbine blades 800 self regulating by aerodynamic and centrifugal forces into an over - speed prevention position .