AU668178B2 - Hyperbolic sheath turbine - Google Patents

Description

P100/011l 2815MIg ABIL Regulation 3.2 mrz AUSTRALIA Patents Act 1990

ORIGINAL

COMPLETE SPECIFICATION STANDARD PATENT Invention T4~ Hyperjolic 5 urbine 151W- PPA1 RM jj#-r and acceleration.

The following statement is a full description of this invention, including the best method of performning it known to me:- I. 1 1 0 I I 'his invention relates to a turbine (combustion or self-propelled and also transmission rotated or rotated by external means) with hyperbolic constrictxng flow along inside surface of sheath of turbine. Turbine is designed for motion through low density gas medium. Large reductions in area are designed for with this type of Turbine meaning exit area is proportionally much smaller than entry area with reductions being basically greater than fifteen times that of exit area but reductions can be grecter than fifteen times or even less but as with the hyperbolic constricting nature of the sheath the area reductions of the first two sets being greater than a times 3 factor with further successive reduction ratios being less and diminishing with spacing for blades being equal or near equal or preferably increasing through turbine.

15 Backflush from front of the turbine exists hence surface flow exists along inside of hyperbolic sheath by a high pressure central region at front forcing the hyperbolic path sheath flow. Blades can be bent centrally near shaft for enhancing back-flush or simply straight. Th end of turbine 20 has opening capability for flow relief or side relief portes can be introduced for further intermittent or constant flow 'o orelief. Spring loading of end or relief portes for constant and set flow relief or applied increased pressure (higher backflush) and flow through-put or reuced pressure flow relief is utilized. Increased through-put means higher turbine output and energy output in terms of central shaft rotational energy or gas exhaust thrust.

The shaft of the turbine can be threaded at spaced points along shaft at equally spaced distances or near equally I 2 spaced distances and the blade assembly fastened between nuts or threaded collars that hold blade assembly to shaft. This way blades can be changed if needed for repair or replacement. The shaft can be tensioned between bearing housing or bushes by bearing housings being supported outside turbine by external structure strong enough to stand significant tensioning and loading on bearing. Lubrication of bearings is not a significant problem due to temperature of exhaust gases in this way.

The blade assembly can be two or more blades with the frontal blade assemblies being bent centrally so as central frontal high pressure flow impeded region at front of turbine gives or assists backflush. Sheath can be made of conical sections weided together in series approximating hyperbolic curve with 15 each adjoining section along turbine direction having more accutely angled or lower divergent angled sections joined along length of turbine towards exit. The rear sections are held to main sheath assembly by spring which sets the pressure limit S inside central region of turbine and allows flow relief into another hyperbolic sheath but this being reversed to allow rapid expansion of gases from turbine without flow restriction.

In this case the hyperbolic curve is reversed about central axis. The bridging assembly for bearings can be attached to reversed hyperbolic sheath active for flow relief for sheath assembly support if exit side bearing is in line of exhaust gas flow cooling cai be applied to exit side bearing assembly.

Branching of exhaust gas exit allows exit of gas around bearing housing with end conical segment being able to move inside reverse hyperbolic flow relief sheath and shaft support t 1 3 bearing on exit side being insulated and cooled is fixed but moveable rear sheath components move over shaft and cover fixed exit side bearing housing. This central cover moves with rear sheath components over shaft towards exit side bearing housing.

Entrapment of incoming gas by motion of turbine is physical by shape and also magnetically enhaned. The magnetic coil is hyperbolically wound around outside of sheath and windings are tapered and diminishing towards rear of turbine for magnetic entrapment of magnetically susceptable material and magnetic acceleration of magnetically susceptable material associated to hot gas flow through turbine. Magnetic field affect on hot gas serves to activate hot gas and increase pressure inside turbine pushing gas down turbine. The sheath can be current 15 activated meaning current is flowing along sheath which forms a circular field inside sheath means magnetically susceptable material i.e. gases enter sheath by magnetic entrapment by either the moving wound hyperbolic tapered coil or the electrically conducting sheath or isolated conducting layer 20 and by activating gases, pressure increases inside turbine and also speed of exhaust gases. The conductive layer is isolated by fibre glass and is supported on polymer material or ceramic material or electrically insulating material.

oe. The fuel is introduced through side of sheath and sprayed down into turbine through jets or nozzles and can have ion forming material like salts suspended or dissolved and on combustion ions activate further ionizations and increase pressure in turbine and ions pull gases down turbine and assist flow through the turbine, Sparking points are about half way "4 down sheath past nozzles and can be spark plugs with continuous spark.

The basic trial model is 120mm. entry diameter and is spun at greater than 4000 and is 300mm. long with 5 conical sections and a exit diameter of 34.5mm. with a overall reduction ratio of 12 times ontry area. The basic coil strength 2.

of I Tesla is applied with grIaer than 20 amps/mm. in windings and windings are air cooled. A thin isolated conductive layer is inserted between windings and welded segments of sheath with 5 segments each 60mm. long with reducing divergent angles of 35 ,25 015050 and 00 in consecutive order. Blade assemblies are a single metal circular plate cut and bent or pressed into shape of blades.

The following one figure represents the invention as described. The figure is the turbine assembly complete with support bracket 1 for tensioning shaft 14 with 3 as the dual opposed taper roller bearing at. each end of shaft and 2 being the conical sections welded together to form hyperbolic sheath.

The blade plate or assembly 12 is folded 900 at 13 near front of 20 turbine for enhancing backflush of central region and is held between two threaded collars 16 on thread 15 on shaft 14. Fuel ""is injected through nozzle 7 and ignited by sparking point 8 with flow down sheath 9 and through outlet where cover 10 for "end bearing 3 is supported from sheath 2. The bearings at each end are loaded and held by threaded collars 11 which are on the threaded shaft areas. The sheath is isolated electrically from conducting layer 5 by insulating layer 4 and condu(., ag layer 5 is supported on non-electrically conducting support 6. The reversed hyperbolic sheath 19 for flow relief I T is isolated electrically from conducting layer 20 which is supported on non-electrically conducting support 21. The flow through to reverse hyperbolic sheath is pressure activated by high pressure in turbine pushing flange at 23 open which is spring loaded by spring 22 held between nut 18a and reverse hyperbolic sheath 19 and end 18 of rod through spring holds end conical component to main conical sections of turbine sheath. The tensioning of shaft 14 is obtained with support bracket 1 which is in two sections and overlapped at 24 and mounts 25 on bracket sections serve to hold bracket sections together by threaded rods 26 which are tensioned by nuts 27.

The tapered wound coil is shown by 28.

S S. o 955 5 5 5" S S .S a S. 5 5 5 S 5 5 S S S 1 5

Claims (9)

1. A gas turbine having a sheath converging substaintially hyperbolically towards its outlet comprising.a central shaft on which a plurality of blade assemblies are mounted along the length of the shaft with each blade assembly comprising a set of radial blades mounted on a hub or blades pressed on a single plate being bent or twisted near centre of plate with at least the first two sets of blades close to large diameter entry into turbine twisted 900 about radial axis near centre of plate and the ratio of area reduction between locations of the first two sets of blades nearest to the inlet preferably being more than three, with further area ratios between locations of successive sets of blades decreasing along turbine axis, such that shaft is rotated or self-propelled by combustion of fuel after being introduced through nozzles and :15 ignited by sparking -lae located halfway down the sheath S exposed to the turbines interior with the sheath having a high reduction ratio of inlet to outlet areas ranging from five to twenty-five, sets of angular bearings are oppositely faced in angle to give two way thrust load resistance and preloaded being prefer- ::20 ably angular thrust bearings and each set of bearings are held externally to turbine by supporting bracket at each end of turbine with the bracket made adjustable in length by threaded rods or bolts through mounts for adjusting load and spacing of bearings at both ends of shaft and tension in shaft, a cover supported by end of hyperbolic sheath is over end bearings to protect against hot gas, the sheath has a hyperbolically wound coil exterior to sheath to produce a magnetic field for acceleration and entrapment into turbine of magnetically susceptable material being gas with hot .i smbusted gases being magnetically activated in turbine to increase 7 pressure in turbine and assist flow through turbine.

2. The turbine with hyperbolically converging sheath as claimed in claim 1 consist of conical sections welded together with less angularly divergnet conical sections towards exit of turbine such that conical sections approximate the hyperbolic taper of sheath or passage through turbine.

3. The turbine with hyperbolically converging sheath as claimed in claim 1 )as a isolated electrically conducting layer serving to accelerate magnetically susceptable material through turbine and entrap magnetically susceptable material into turbine has a high current density current flow along length and is supported on polymer, ceramic or electrically ron-conducting cover externally over hyperbolic sheath and is isolated from metal hyperbolic turbine sheath by fibre glass cloth or thermally stable elect- rically non-conducting material.

4. The turbine with hyperbolically converging sheath as claimed S* in claim 1 has electrical windings around hyperbolic turbine sheath such that the plane of the windings being perpendicular to length of sheath or turbine flow and comprise a hyperbolically :"20 wound coil which is tapered with fewer windings towards base or exit of turbine diminishing iv thickness and number of windings around hyperbolic turbine sheath for entrapment into turbine and activation of gas in turbine to increase pressure and assist flow through turbine.

5. The turbine with hyperbolically converging sheath as claimed in claim 1 is characterized by having both a isolated supported electrically conducting layer external to turbine sheath and also external to the electrically conductive layer supported on electr- e ically.insulating .material is a hyperbolically wound tapered coil 8 being tapered in number of windings toward turbine exit for magnet- ic entrapment of gas into turbine and activation of gas in turbine to increase pressure in turbine and increase flow through turbine.

6. The turbine with hyperbolically converging sheath as claimed in claim 1 has a reversed hyperbolic sheath welded to end of second last sheath section being joined to last sheath secyion by bolts through flange on last or rear hyperbolic section of sheath being held shut and sealed from reversed hyperbolic sheath by a spring which allows release at high enough pressures in turbine of gases into reversed hyperbolic sheath or opened as desiredsby compressing springs to give pressure lelief of gas expanding into reverse hyperbolic sheath, with isolating non-electrically conductive material isolating electrically conductive layer over reversed hyperbolic sheath for magnetic field activation of gases in turbine in terms of increased pressure and flow.

7. The turbine with hyperbolically converging sheath as claim.- in claim 1 has fuel with ionic material dissolved or suspended 0 which in turn is sprayed into turbine through t' e nozzles for fuel entry into turbine for combustion to leave free ions to initita :"20 ionic forming collisions and increase number of ions thus increas- ing magnetic affect on pressure increase and flow through turbine.

8. The turbine with hyperbolically converging sheath as claimed in claim 1 has a moveable last sheath section of turbine's sheath that is branched or is a multiple channel exit opening which serves to shield end bearings f-r. hot turbine exit gas.

9. The turbine with hyperbolically converging sheath substain- tially as herein described with reference to accompanying drawing. GEORGE CONTOLEON 13TH. OF FEBRUARY,1996. APPLICANT DATE ABSTRACT Backflush from the front of the turbine exists hence surface flow exists along inside of hyperbolic she by a high pressure central region at front forcing the hyperbolic path sheath flow. Blades can be bent centrally near shaft for enhancing back-flush or simply straight. The end of turbine has opening capability for flow relief or side relief portes can be introduced for further interi,ittent or constant flow relief. Spring loading of end cr relief portes for constant and set flow relief or applied increased pressure (higher backflush) and flow through-put or reduced pressure flow relief is utilized. Increased through-put means higher turbine output and energy output in teris of central shaft rotational energy or gas exhaust thrust. 8. Tonic material is dissolved or suspended in fuel and *0 Ssprayed into turbine for combustion leaving free ions to initiate ionic forming collisions and increase number of ions thus increasing magnetic affect on flow through turbine by magnetic fields applied in turbine. *o ooo