GB2490563A - Pre-rotating or de-rotating fluid flow with a volute - Google Patents

Abstract

A volute comprises an axial opening and a tangential or radial opening. The volute is located upstream of a fluid compressor or marine propeller, or downstream of a fluid turbine. When used with a fluid compressor or marine propeller the volute pre-rotates the fluid before it enters the compressor or marine propeller. When used with a turbine the volute de-rotates the fluid after it leaves the turbine. When used with a turbine, the volute includes an inlet 5 which accepts spirally rotating fluid 1, a bell mouth portion 3, a volute portion 2, and a tangential or radial outlet 4 which emits a linear fluid flow 6. Annular turning devices may be used to pre-rotate or de-rotate the fluid flow. The volute may be double-width with an axial opening on each side. Up to eight volutes may be used together such that they share a common tangential opening, but have multiple axial openings. The volute may be used in a turbo-charger.

Description

SPIRAL ENERGV RECOVERV and FLOW PRE-ROTATION for TURBOCHARGERS, TURBO-EXPANSION VALVES, TURBOJETS and MARINE PROPELLERS, etc. This invention concerns means for usefully regaining spiral en- ergy otherwise lost from rotary power generating engines (ex- panders) and rotary power absorbing engines (compressors) dis-charging rotating flow And, by similar such means as this is -provided for, but in reverse, pre-rotating flow to axial, or axial inlet rotary engines in the same direction as their di-rection of rotation. And, since liquids are, strictly speaking, physically compressible and expandable, it concerns both liquid and vapour flowing such engines.

It thereby also concerns the fundamentals *of the fluid dynamics of Archimedes' spiral screw and subsequent derivatives, such as screw compressors and airscrews. And, as such, it also introduces the concept of spiral energy.

Commonly, i.c. (internal combustion) engine turbochargers com- prise an exhaust radial flow adiabatic expansion cooling tur-bine powering an air supply centrifugal adiabatic compression heating compressor (refrigeration turbo-expansion valves being similarly so configured when operating in conjunction with an in-series secondary compressor -which can be centrifugal). Jet engines and gas turbines commonly have multi-stage axial flow fan compressors and axial flow expansion turbines. Common to all such cases is that the gas discharge from their turbines is spirally rotating which, in certain cases, can often be in ex-cess of 100,000 r.p.m.. It is obvious that energy has to have been expended to cause such rotation and, as such, hitherto, is then uselessly dissipated or exhausted downstream of the tur-bine, which is why it has not been possible to achieve turbine efficiencies much in excess of 70%, and why, hitherto, there has been no convincingly plausible explanation why this was not higher. According to the Laws of Physics, it is logical that it should be possible to usefully regain such spiral energy (less a %age efficiency loss applicable to the regain means), but not obvious how such regain might be obtained -simply.

In this invention, spirally rotating fluid discharged from ro- tary turbines or compressors is de-rotated by a.downstream spi-ral, -or semi-spiral volute having an axial bell-mouthed flow inlet on one (1) side and a tangential radial flow outlet, such that the spiral energy of the entering rotating flow is conver- ted to a static pressure potential energy increase at it's out-let. Where such a volute has equal size inlets and outlets, the velocity pressure kinetic energy of the entering fluid would be the same as at it's outlet. However, the entering fluid also has spiral potential energy, but the de-rotated fluid at it's outlet has no such potential energy element, yet the entering total energy must equal the leaving total energy (less surface friction static pressure loss -manifested as heat energyL Therefore, logically, to make the entering and leaving total energies balance there has to have been static pressure regain such that the leaving static pressure is higher than the enter-ing static pressure (as measured at the centre of the rotating flow). This static pressure regain effectbeing generated by the increased centrifuging effect on the fluid as it unwinds and increases in diameter as it flows through the de-rotating volut e.

It should be noted that if a de-rotating' volute had an abrupt inlet that non-rotating fluid flow into it would become turbu-lent flow within it, that would be substantially reversionary and rolling such that radial discharge flow from it's tangen- tial peripheral outlet duct would also be turbulent, and roll-ing. Such effect could be averted if, at such abrupt juncture, there were annular turning vanes. If the entering flow was, however, spirally rotating, such turning means would likewise ensure that discharge flow was non-rotating.

Spirally rotating fluid discharging from the open end of hori- ontal conduit would not, by definition, have any static press-ure penultimate to such end, yet fluid would discharge at right angles from a pin-prick hole in the wall of the conduit penul-timate to such end, thereby demonstrating the centrifugal force and potential spiral energy (mass flow X force) of the rotating flow in the said conduit. By deduction, an open-ended de-rota- ting volute's inlet static pressure would, therefore, be nega-tive, and if the open end were larger than the volute's inlet then such negative pressure would be even lower. Reducing pressure at the discharge outlet of an upstream turbine by such means increases static pressure difference across it such that it would output more power -in the case of a turbocharger, to it's compressor, such that boost pressure would increase with-out any increase in exhaust back-pressure, and such that the downstream exhaust gas temperature would be lower due to in-creased pressure differential expansion cooling, attesting to an increase in thermal efficiency. Similarly, de-rotating vo- lutes would increase the efficiency of refrigeration turbo-ex-pansion valves, gas turbines, power-station steam turbines and turboets. And it is estimated that the typical, 70 to 80%, efficiency of such turbines would, thereby, be increased by in the order of 20 to 30%.

It is known that inlet guide vanes, variable and fixed, are used to pre-rotate flow to centrifugal refrigeration and turbo-charger compressors to increase their efficiency. However, in doingso, they uselessly transmit torque into their conduit's containing sidewalls and such loss, plus the frictional heat generation across them, accounts for their efficiency losses.

In any case, variable (pitch) guide vanes do not also have var-iable airfoils, or spiral twist, such that the? then stall at low pitch angles (causing high drag) and are less efficient at high pitch angles -and their interlinking hinging mechanism hubs cause pressure drop. Whereas, the useless sidewall torque generated by a de-rotating volute is only that that surface friction exerts upon the sidewalls of the volute, generating an unwinding force on the volute -and pre-rotation rate inherent-ly passively varies as flow rate varies, which would only vary if the centrifugal compressor r.p.m. correspondingly varied.

Not only are pre-rotating volutes more efficient than guide vanes alone (without a volute), but are also much simpler. It t should be noted that the pressure generated by a centrifugal compressor is a function of it's rotor's tip speed such that, pre-rotating the fluid entering it in the same direction as the rotor's direction of rotation would tend to increase it's speed of rotation and it'.s tip speed such that, for a given compression pressure increase (U), the nominal speed of the compressor's drive motor can be reduced such that it would con-same less energy. (U) Ps qualified in the next paragraph. N.B.

Qariable inlet guide vanes, in conjunction with variable speed motors, are sometimes used to stabilise the capacity control of centrifugal refrigeration compressors and, as such, could be similarly so used with pre-rotating volutes (as could adjust-able/fixed inlet guide vanes be used to increase, or decrease, the inherent rate of pre-rotation of a volute).

(0) In the case of pre-rotating volutes, it should be noted that the spiral energy imparted to such rotation results in their outlet static pressure being less than the inlet's such that the static pressure at the inlet of a subsequent rotary compressor would be less than it otherwise would be. Therefore, for a given discharge pressure, the compressor pressure increa-se would have to be that much higher. Thus the benefit derived from having pre-rotated flow to axial/axial inlet compressors must be balanced against such static pressure loss -as would also apply to axia]Iaxial inlet rotary expanders.

Pre-rotated flow to rotary compressors and expanders notionally affects their performance maps/pressure-volume rating curves.

However, pre-rotating volutes should only be used in conjunc- tion with rotors, propellers, impellers, etc. specifically de- signed for pre-rotated flow. Such design, and that of the volu- tes, can be undertaken by advanced CFD (computational fluid dy-namics), particularly with regard to vane, or blade leading edge pitch relative to spiral flow pitch and radiusing. fin- creasing leading edge radiusing maximises the non-surging/non-stalling performance envelope where flow varies, but would have a minor adverse effect on peak efficiency -even vanes can be slightly thickened at their leading edges for such purpose -hut trailing edges should always be knife-edge sharp.) Pre-rotating volutes, with rectangular or circular inlets, can also be applied to 516W (single-inlet, single-width) and direct drive D1DW (double-inlet, double-width) centrifugal fans. [With 516W centrifugal fans, they would also provide an efficient and convenient means or turning duct flow into the intake eye of the fan. In the case of DIDW centrifugal fans, two (2) volutes, one (1) each side of the fan, siamesed together with appro-priate duct change-of-section transitions, would also usefully use, otherwise lost, velocity pressure kinetic energy in the SC) upstream duct/AHU (air handling unit).) N.B. The bell-mouthed inlets of 616W and D1DW centrifugal fans should be reversed to facilitate efficient connection to pre-rotating valutes and, where such volutes are not duct connected their peripheral in- lets should be bell-mouthed. [Pre--rotating and de-rotating vo-lutes can also be used with axial single, or multi-stage fans.] increasing the efficiency of turbochargers, by pre-rotating in- take air to the centrifugal compressor and de-rotating the ex-haust gases from the turbine, would mean that 25 to 30% more energy could be extracted from the exhaust gases. And the ac-tual adiabatic charge air temperature rise per unit of boost S pressure would be less -requiring less intercooling. Such ex- tra energy extraction from the exhaust gases can be used to in-crease engine power and/or economy -parttcularly in the case of fuel economy-increasing systems using throttle-controlled, hybrid-power generating, variable speed supercharqers.

Volutes applied to radial flow turbines and centrifugal compre- ssors can simp]y comprise their empty' volutes (with blanked-off bearing holes). Or, they could contain a rotor (mounted on a shaft common to the turbine or the centrifugal compressor), so configured and rotated that it is a further, close-coupled, turbine or compressor stage, such that both such stages would be connected to the same motor, or generator, or motor-gener- ator where it's speed is varied or volume flow varies suffic-sently. [It should be noted that the function of compressors and expanders can reverse where their nominal mass flow, or their speed is variable and varies sufficiently such that their motor or generator (as applicable) thereby becomed, strictly speaking, a motor-generator.) It should be noted that a pre-ro-tator volute containing a rotor so configured and rotated that the entity acts as a compressor would, by definition, discharge flow with a higher rate of (pre-)rotation than an empty' vol-ute handling the same volume flow would.

It would not be aerodynamically feasible to add volutes to air-plane longitudinal turbojet and fan-jet engines. However, in certain cases, it might be feasible to contain lateral, smaller diameter, turbojet engines within wing halves such that there would be pre-rotating volutes at the wing roots or in the fuse-lage with extended, acoustically insulated, intakes run outside the fuselage to just short of the cockpit, and with similar such extensions run within the wing to tip volutes (faired-in to act as wing end-plates); the volutes also providing end-re-flection Sound attenuation. As such, the lateral parts in each wing-half, including the engine, could be bolted together via plates and high tensile CF (carbon fibre) rods (a la Rover K' series engines) to form a rigid entity that doubles-up as wing wing main spars, supported with leading and trailing edge D' box structural engine fairings (**) containing acoustic/thermal insulation (the combustion chamber onwards, and the volute, re-quiring to be thermally insulated). Tip volutes, or their outer perimeters, could be rotatable to provide for VTOL/VSTOL (ver- tical take-off & landing/very short TOL) and reverse thrust ca- pability, and afford the high speed flight capabi]ity of turbo-jet engines (e.g. higher than Boeing's V 22 Osprey tilt-rotor SO affords). It should be noted that such VIOL propulsion would be in the order of 60% more efficient than a helicopter's since it obviates the spiral energy losses of the powering jet engine and the main rotor, and obviates power lost to the, non-lifting and non-forward thrusting, tail rotor (equal to main rotor tor-rque) -and such efficiency and sound attenuation possibility would make it stealth' quiet, eliminating main rotor chopper noise. Such rotatable volutes should have means for vectoring thrust for hover lateral stability control (by splaying their thrusts) and, in forward flight, providing for increased man-ouevrability and for compensating for single engine operation.

Plternatively, non-rotating tip volutes with separate, variable volume, hrizontal and vertical radial outlets could be used, as also could votutes that are tiltable, or tilted (as they would be when at right angles to a dihedralled wing), such that in hover mode tip discharges would be, or can be, outwardly splayed. Pitch control in hover could be provided for via gyro-scopic computerised control of the rotable movement of the tip volutes (a Ia Segway control), or control of the volute vector-ed thrust from a small 3rd jet engine (for powering auxiliary sevices). (U) Wings with rotatable tip votutes not necessarily requiring ailerons, flaps or leading edge slats.

A similar possible, non-'JTOL/VSTOL, airplane configuration for voluted-axial turbojet engines would be one with twin-booms joined at the tailplane as per a WW II P-38 Lockheed Lightning.

With discharges from the turbine de-rotating volutes being down such booms (thermally/acoustically insulated -gaving high sound attenuation), affording the possibility for the outer wing panels to be thin and of high aspect ratio, amd possibly swept back -and there could even be secondary rotatable de-ro-tating volutes at the wing tips and, or, multiple, successively smaller, intermediate volutes along the wingspan.

Frank Whittle's original concept centrifugal compressor-radial flow turbine jet engine would also be enhanced with the addi-tion of volutes, and would provide a more compact arrangement than a voluted axial jet engine for applications where packa- ging' is of importance. Alternatively, a radial in-flowing com-pressor-radial discharging turbine turbojet engine could be used (wherein the compressor pre-rotates flow to the turbine, which de-rotates such flow, and their rotors are so configured and rotated for such functions) for an even smaller package', such that two (2) vertical, or lateral, such engines might be accommodated mid-fuselage, with their inlet and discharge ducts run externally fore and aft to, respectively, just short of the nose (to obtain a ram effect from it) and to just short of it's tail such that with the fuselage and it flattened drag would be reduced) -in this way, with inboard landing gear and with no outboard pylon mounted engines to support, wings could be thin and have efficient continuous length flaps/ailerons.

With ships, their outboard propellers could be substituted with inboard multi-bladed impellers (similar to fan-jet first stage compressor impellers) mounted within annular casings, connected via a pre-rotating volute and conduit to an oval bow intake, and, via a de-rotating volute and conduit, to fiat oval dis-charge outlets at the stern. In this way, the bow wave's static pressure resistance would be reduced (and velocity pressure ram effect availed) and the drag-inducing low pressure zone at the stern infilled by the aforesaid flat oval discharge outlets such that hull hydrodynamic efficiency would be significantly improved. Such pre-rotation, shrouding and use of multi-scythe- -bladed impellers would reduce cavitation loss to significantly less than the cavitation losses of conventional outboard prop- -6 - ellers, which, together with the availed ram effect, would sig- nificantly improve propulsion efficiency, which with the sig-nificantly improved hull hydrodynamic efficiency would result in engine power and fuel consumption being much lower than that S of conventional propulsion system. (Where there might conven- tionally be a bow sub-surface proboscis, it could now be open-ended to generate an intake flow ram effect to the one (1), or more, midship impellers. Such a system could also be applied to ç'stealth' submarines such that not only would the higher pro-pulsion and hull hydrodynasic efficiency be thereby inherently quieter than with an external propulsion system, but also there would be end reflection' acoustic sound reduction by the vol-utes -and the inherently long inlet and discharge tracts can double-up as very effective annular sound attenuators. Such is-proved propulsion and hull efficiencies can be used to increase top/cruising speeds for given power input such that such tech-nology would also be applicable to hunter/killer submarines.

fllternatively, a reverse system would be possible wherein there would be two (2) intakes either side of the bow (a La torpedo tubes) and a single flat oval clisharge at the stern (dihedrall- ed where the stern is still chined), and which should be knife-edge seamlessly merged into the trailing edge of the hull.

In larger vessels there would likely require to be more than one (I) such system and, as such, can most conveniently be pro-vided for via the use of single siamesed together, single, or siamesed together, double-width volutes (having axial openings each side) connecting to corresponding separate impellers conn- ected to likewise configured de-rotating volutes. Such siam-esing being facilitated by means of the volutes having square, or rectangular peripheral tangential ducts connecting to a lar- ger rectangular or square inlet opening connection. Or, circu- tar ducts could be siamesed together, in the fashion of Russ-ian Soyuz' multiple rockets, for high pressure applications.

This invention will now be described solely by way of example and with reference to the accompanying drawings in which: Figure 1 shows a volute de-rotating spiraLly rotating fluid Figure 2 shows a marine propulsion application using a double-width' double outlet pre-rotating volute with two (2) "single-width' single outlet tie-rotating volutes.

Figure 3a shows Figure 8 of Siemens AG's SB 2 440 343 A patent application for a Gas turbine exhaust arrangement', designed to be of short axial length.

Figures 3b & 3c each show modifications of the aforesaid patent application that provide for partial de-rotation of the exhaust gases.

]n Figure 1: spirally rotating fluid I, discharged from a conn-ected rotary turbine or axial compressor, enters volute 2 via reverse bell-mouth inlet 3, whose sidesare SPR Foil curved (see Patent no: GB 2 381 835) such that flow turns into volute 2 by means of Coanda surface effect, and discharges from volute -7 - 2, de-rotated via.it's peripheral tangential outlet 4. Inlet 5 and outlet 4 are the same size such that their flows have equal velocity pressure (and kinetic energy).. However, fluid flow I has spiral energy and de-rotáted fluid flow 6 has none, yet their total energies must be equal such that, therefore, the static pressure (and potential energy) of fluid flow 6 must be higher than that of fluid flow I (less the surface frictional pressure losses of volute 2). Or, to put it another way, the static pressure of fluid flow I is now lower than it otherwise would be, as would also be the static pressure at the discharge outlet of a connected upstream rotary turbine such that the static pressure difference across it would be so increased, in- creasing it's power output. Where the axial length of the volu- te may be desired to be minimised, inlet 3 could have a radius-eci lip with with a cone inside it, preferably concave radiused at it's base or with concave curved sides, and preferably with at least one (1) annular turning splitter inbetween -or inlet 3, with or without a curved lip (and no cone), could have a set of annular turning vanes (not necessarily at 45 degrees) inside it. Similarly, a volute with multiple peripheral radial open- ings could be shallower -and in the case of an expansion cool- ing turbine with such multiple outlets, their conduit dischar-ges could be spirally wrapped-around the turbine's generator to usefully cool it, and then be re-combined via a de-rotating vo-lute similarly having multiple peripheral radial inlets.

For maximum effect and efficiency the outer perimeter of such volutes should be spiral. However, where, for instance, a high pressure generating centrifugal compressor has a large diameter -to-width ratio rotor such that it's volute is substantially circular, a similarly so configured pre-rotating volute would be fit-for-purpose. Similarly, semi-spiral volutes can be used, i.e. part circular and part spiral.

In Figure 2: water flow 7 enters, via conduit 8 from a bell-mouthed circular, or flat oval, inlet proboscis forward of the bow of the ship containing it, to double-width volute 9. Volute 9 pre-rotates the water flow to multi-scythe-bladed propellers and 11, whose spirally rotating discharges are de-rotated by single-width volutes 12 and 13 such that non-rotating water is conveyed via conduits 14 and 15 to be discharged at the stern of the vessel via wide, flat oval, outlets. Axial, single or multi-stage, propellers 10 and 11 are mounted on stiff, hollow, shafts 16 and 17, supported at their ends by ball bearings mounted in bearing plate 18. Shafts 16 and 17 transmit the out- put power from motors 19 and 20 to propellers IC) and 11. An up-side-down parallel version of this system could be mounted on top of this system such that there would be four (4) propellers and motors (conduits 8, 14 and 15 and the radial openings of volutes 9, 12 and 13, could be square or rectangular so that such siamesing would afford a common intake and commoned-up discharges. Alternatively, the propellers could could be sub- stituted with centrifugal compressors' Ci.e. rotors within vo- lutes 12 and 13) and the pre-rotating volutes' curved neck ax-ial openings could be substituted with openings having a curved lip and annular turning vanes for a more compact arrangement (although not affording any discharge system end-reflection sound attenuation), or the volutes to the propellers could alt be ones having curved-lip-annular-turning-vane axial openings In Figure 3a the art of minimiseci length gas turbine exhausts S is exemplified by the copy of figure 8 of Siemens AG's GB 1,04 5,689 A patent application, to which turbine blades' 3's di-rection of rotation A' has been added. From this, it can be seen that exhaust gas B's flow would be significantly more than C's because of the reversionary flow 0' that occurs on the leeuward side plate 19. General Electric Co.'s patent app-lication GB 1,045,589 and Hitachi Ltd.'s JP 52 -153005 contain similar such turbine exhaust' art.

The gas turbine exhaust volutes' of the above mentioned patent applications, downstream from the rotating flow discharged from their turbine's rotor blades/vanes, far from de-rotating such flow, add another rotation dimension to such flow such that the flow in the outer annular voluted chamber would be rolling and rotating. It should particularly be noted that their represent-ations of flow direction in the outer annular chamber shown on their drawings is not correct. They show rolling flow rotating in one half of the annular chamber in a clockwise direction and anti-clockwise in the other half. However, due to the rotation of the rotor (which could be in excess of 100,000 rpm), rota- tion would be in one direction only -such that at the (non-tangential) juncture between the outlet and the annular chamber there would actually be some reversionary (entrained) flow (**) in the exhaust conduit at such juncture -and such reversionary flow evidences no possibility that that there might be any de-rotating' static pressure regain, of which there would be some had the exhaust outlet been tangential to the chamber.

(If fluid flow was reversed through their exhaust chambers the entering fluid flow would diverge in opposing rotational di-rections -in particular see splitter plate 19 in figure 3a Siemens AG1s figure 8). However, flow would (pre-)rotate in one direction only if splitter plate 19 was curved and the sides of neck 11 were both curved in the same direction such that neck 11 becomes a semi-tangential opening; flow turning efficiency being improved with via the use of more than one (1) curved splitter 19. Alternatively, plate 19 could be tangential to rim (see figure 3c) and form one side of opening 11, with it's other side then being tangential to case 7, and the other side of case 7 was converged to the base of plate 19 such that case 7 becomes semi-volute shaped (i.e. as per this invention) -in which such configuration the exhaust gases would be usefully de-rotated, though not de-rolled, which would require use of a further de-rotating volute in a different plane.] With such annular discharge turbines, a de-rotating volute should have an annular opening in it's intake neck, whose inner disc is the end of a column, preferably with a radiused base and with a set of intervening annular turning vanes (not necessarily at 45 de- grees), or the end of a truncated cone, preferably with a ra-diused base or concave curved sides and with one (1), or more, vanes or splitters being supported via radial bicycle' spokes) -such turning devices giving the shortest possible axial leng-th volute.

Claims (13)

1. CLAIMS: 1 1. A fluid flowing device for de-rotating flow from rotary com-pressors or expanders discharging spirally rotating flow, or for pre-rotating flow to axial, or axial inlet, rotary com- pressors and expanders in the same direction as their direc-S tion of rotation, comprising of a substantially snail-like voluted or circular chamber, or combination thereof, with an axial flow opening on one (1) side of it, so shaped that flow from one to the other is turned by means of coanda stir-face effect and or by annular turning devices, and with a radial, tangential or semi-tangential flowing, opening.
2. 2. fl fluid flowing device according to claim 1, in which it's axtal opening is annular, the inner disc of which is the end of a column, or truncated cone whose sides are substantially concave curved, such that each accords with an applicable claim I said turning means.
3. 3. A fluid flowing device according to any preceding claim, in which there are one (1) of any of the such aforesaid axial openings each side of it, and in which the flow through each is in opposite directions.
4. 4. A fluid flowing device according to any preceding claim, ex- cepting claim 3, in which another such device's axial open-ing is connected to it's axial opening, and in which fluid flow through the axial openings of any intermediate ones is in the same direction.
5. 5. A fluid flowing device according to claim 1, in which there are no turning vanes or splitters, but in which there is a rotor which, in the case of the device being a de-rotator is so configured and rotated that the entity acts as a corn- *, * pressor, or in the case of the device being being a pre-ro-tator is so configured and rotated that the entity acts as an expander. * *
6. 6. A fluid flowing device according to any preceding claim, in which one (1) is siamesed to another one (I), or more, of * any of the precedingly claimed fluid flowing devices.
7. 7. A fluid flowing device according to any preceding claim, cx-cepting claim 6, in which it has more than one (1) of it's either such said radial openings.
8. S. S * S

   * 45 8. A fluid flowing device according to claim 7, in which any such radial opening incorporates means for varying volume flow through it.
9. 9. 4 fluid flowing device according to any preceding claim, en-SC) cepting claim 3, in which a dc-rotator one is rotatable, or it's perimeter is rotatable, about it's axial axis relative to the engine it is connected to.
10. 10. A fluid flowing device according to any claim 7 to 9, in 1 -ic' - 1 which there are means for directionally changing flow from at least one Cl) of the so claimed radial openings.
11. IL A fluid flowing device according to claims S to 10, in S which it is tijtable1 or tilted1 relative to another such one.
12. 12. A fluid flowing device according to any preceding claim, in in which any one that is a pre-rotator has, or operates in conjunction with, pre-rotating guide vanes.
13. 13. A fluid flowing device according to any preceding claim, in which where one (1) has one (1), or more, semi-tangential flowing radial openings any such opening incorporates one (1), or more, turning splitter plates. * I S * 55 e *Iaee * 5 a, I. * I I * * 5*51 * S *IS SII I * S I * IS Amendment to the claims have been filed as follows CLAIMS.=-flfls 1. A fluid flowing device for dc-rotating the flow from rotary * compressors or expanders discharging spirally rotating flow, or for pie-rotating the flow to axial, or axial inlet, ro- tary compressors or expanders in the direction of their di-rection of rotation, comprising of a snail-like voluted, or circular, or combination thereof chamber having a side opew-ing and a peripheral tangential, or semi-tangential opening and turning means between the side opening and the chamber periphery comprising either a curved funnell, so shaped that a Coanda surface effect is engendered with, or without, the use of one (1), or sore, annular turning splitters, or com-prises of an annular set of turning vanes preferably used with, or without, a correspondingly radiused lip to the sldr opening.2; A fluid flowing device according to claim 1, in whièh it's side opening is annular, the inner disc of which is a col-umn end, or a truncated cone end whose sides are concave * curved, such that each accords with an applicable claim I said turning means. S. * * S.* 3. A fluid flowing device according to any preceding claim, in which there is.another one (1) of any of the such aforesaid side openings on it's other side, and in which flow through * ,25 them is in opposite directions. S. * * **4. A fluid flowing device according to any preceding claim, ex-cepting claim 3, in which another such device's side opening is connected to it's side opening, and in which fluid flow : ."?O through the side openings of any intermediate ones is in the same direction.S *S*sS * I5. A fluid flowing device according to claim I, in which there are no turning vanes or splitters, but in which there is a rotor which, in the case of the device being a dc-rotator is so configured and rotated that the entity acts as a com- pressor, or in the case of the device be*ng being a pre-ro-tator is so configured and rotated that the entity acts as an expander.-£. A fluid flowing device according to any preceding claim, in which one (1) is siamesed to another one (1), or more, of them.7. A fluid flowing device according to any preceding claim, ex-cepting claim 6, Sn which it has more than one U). of the such said peripheral openings.a. A fluid flowing device according to claim 7, in which any of the said peripheral openings incárporates meeüts for varying sass flow through it S. A flui$ flowing device according to any preceding claim, ex-cepting claim 3, in whsch a dc-rotator one is rotatable, or I it1s perimeter is rotatable1 about it1s. side apenin9 ak5 relative to the engine it is connected to.to. A fluid flowing device according to clams 7, 8 or 9, in S which there are teans for directionally changing flow from at least one of the so claied periheraL openings.it. A fluid flowing device according to claims 8, 3 or 10, in which it is tiltabie, or tilted1 relative to another such one.12. A fluid flowing device according to any preceding claim, in in which any one that is a pre-rotator intorporatesff or operates in conjunction with, guide vanes. £513. 4 fluid flowing device according to any preceding claim, in which there are turning means at a peripheral opening June-t ur e. t0 * * S S * **S* *5*SS * S * *, * * * * * * doS * 4* * I 5*5*I.* 4* P * S