Ramjet engine with axial air supply fan

RAMJET ENGINE WITH AXIAL AIR SUPPLY FAN

0002This patent application claims priority from U.S. Provisional Patent Application No. 60/096,831, filed August 17, 1998, and entitled RAMJET ENGINE WITH AXIAL- AIR SUPPLY FAN, the disclosure of which is incorporated herein by this reference.

0003A portion of the disclosure of this patent document contains material which is subject to copyright protection. The owner has no objection to the facsimile reproduction by anyone of the patent document or the patent disclosure, as it appears in the Patent and Trademark Office patent file or records, but otherwise reserves all copyright rights whatsoever.

TECHNICAL FIELD

0005My invention relates to a high efficiency axial fan for the supply of air, and to the novel combination of such fan to a transversely disposed ramjet engine. More particularly, my invention relates to a power plant driven by a ramjet engine, and to a unique combination of inlet air supply components and ramjet power train components .

BACKGROUND

0007A continuing demand exists for a simple, highly efficient and inexpensive thermal power plant which can reliably provide low cost electrical and mechanical power. This is because many electrical and/or mechanical power plants could substantially benefit economically from a prime mover that offers significantly improved cycle efficiencies. This is_ particularly true in medium size power plants generally in the 10 to 100 megawatt range - which are used in many industrial applications, including stationary electric power generating units, rail locomotives, and marine power systems.

0008Medium sized power plants are also well suited for industrial and utility cogeneration facilities. Such facilities are increasingly employed to service thermal power needs while simultaneously generating electrical power in a cost effective manner. Power plant designs which are now commonly utilized in co-generation applications include (a) gas turbines, driven by the combustion of natural gas, fuel oil, or other fuels, which capture the thermal and kinetic energy from the combustion gases, (b) steam turbines, driven by the steam which is generated in boilers from the combustion of coal, fuel oil, natural gas, solid waste, or other fuels, and (c) large scale reciprocating engines, usually diesel cycle and typically fired with fuel oils. Of the currently available power plant technologies, diesel fueled reciprocating and advanced aeroderivative gas turbine engines have the highest efficiency levels. Unfortunately, with respect to the reciprocating engines, at higher power output levels, the size of the individual engine components required become almost unmanageably large, and as a result, commercial use of single unit reciprocating engine- systems in larger sizes has been minimal.

0009Gas turbines perform more reliably than reciprocating engines, and thus are in widespread use. However, because gas turbines are only moderately efficient in converting fuel to electrical energy, gas turbine powered plants are most effectively employed in co-generation systems where both electrical and thermal energy can be utilized. In that manner, the gas turbine efficiency can be counterbalanced by using the thermal energy to increase the overall cycle efficiency.

0010In any event, and particularly in view of reduced governmental regulation in the sale of electrical power, it can be appreciated that significant cost reduction in electrical power generation would be desirable. This objective can be most effectively accomplished by generating electrical power at higher overall cycle efficiency than is achieved with technology currently utilized for power generation.

0011One of the technical challenges in providing a high efficiency ramjet based engine is the ability to provide a uniform fuel air mixture, at near ambient pressure, at the ramjet inlet ramp compression structure. Incoming air must be received through an inlet structure, and thoroughly mixed with fuel, and then fed to the ramjet inlet, all in a manner which promotes good fuel/air mixing and efficient uptake at the ramjet inlet. Also, the fuel/airmix must be fed to the ramjet inlet in a- stable, reliable smooth flow pattern, without short circuiting or unnecessary turbulence.

0012In gas turbine technology, it is well known that an axial bypass fan and an axial combustion air compressor are effective in an axially oriented combustion chamber arrangement, to drive post combustion turbine blades. However, my ramjet engine compresses essentially ambient pressure fuel/air mixtures against a stationary peripheral wall, and is thus oriented transversely to the output shaft . Since the necessary inlet air compression to support combustion in the ramjet occurs only along the inlet ramp of the ramjet, in my ramjet engine, it is unnecessary to additional energy for the compression of gaseous fuels, or of combustion air. However, it is necessary to provide a uniform, low pressure flow of combustion air along a converging annulus, in order to position a fuel/air mixture where it is readily captured and burned by a rotating ramjet engine. Therefore, it would be desirable to provide an axial fan arrangement in combination with a transversely oriented ramjet engine, so as to be able to take maximum advantage of the highly efficient ramjet engine operating cycle, while reliably and uniformly mixing low pressure fuel and the supplied inlet air to provide a uniform, consistent composition lean fuel -air mixture to the engine . SUMMARY OF THE INVENTION

0013I have now invented a novel, improved power plant which uses as one important component the novel combination of an axial fan supply for combustion air at relatively low velocity to a supersonic ramjet prime mover which rotates a driven power shaft. By use of such an arrangement, efficient fuel air pre-mix can be achieved. Also, by use of a metered fuel feed apparatus, the power output of the ramjet power plant can be turned down as necessary to maintain the desired rotating velocity. In this manner, a constant rotating velocity can be achieved, as is necessary in synchronous power generation apparatus.

0014To achieve the desired power plant operational parameters, I have now developed a novel fuel -air mixing housing which uses an axial supply fan design and which introduces a lean, uniformly mixed fuel -air mixture to a transverse mounted ramjet engine configuration. This apparatus overcomes some specific problems inherent in the heretofore known apparatus and methods that are known to me and which have heretofore been proposed for the application of ramjet technology to stationary power generation equipment. Of primary importance, I have now developed a simple, low speed, essentially ambient pressure air supply axial fan apparatus which can deliver a stabilized, smoothly flowing oxidant carrier gas to a housing for thorough mixing with a gaseous fuel which is supplied at low pressure. _

0015More specifically, my novel axial fan enables fuel- air pre-mix between an inlet carrier gas such as air which carries an oxidant such as oxygen, and thoroughly mixes the carrier gas with a selected fuel such as natural gas. The housing, and the process employed therein, thoroughly mixes the fuel and the oxidant to produce a fuel -oxidant of uniform mixture. Overall, the housing provides a convergent, preferably annularly shaped gas flow path, that is, of lower cross-sectional area toward the outlet as compared to the inlet of a section examined. Preferably, an annular housing is sized to match the output of the axial fan, and the fuel/air pre-mix feed requirements at the inlet of the transversely mounted ramjet engine. In my axial fan design, the inlet gas flow path in the fuel-air pre-mix housing has a longitudinal axis. The gas flow path is defined by (i) an upstream housing end, (ii) a downstream housing end, (iii) an outer surface of an inner wall, and (iv) an inner surface of an outer wall. A plurality of fuel supply structures are disposed in fluid communication with the gas flow discharged from the axial fan. Most preferably, the fuel supply structures are mounted radially in spokelike fashion spanning all or a portion of the gap between the outer surface of the inner wall and the inner surface of the outer wall . For effective air flow stabilization, the number of fuel supply structures-. (stators) must be commensurate with the geometry involved in view of the fuel/oxidant mixing criteria desired. However, for one configuration depicted herein, where the annular inlet duct has diameter at the inner surface of the outer wall of about 72 inches, and a diameter at the outer surface of the inner wall of about 48 inches, the number of fuel supply structures (stators) is preferably up to about 30 or so. Also, each stator preferably spans a substantial portion of the gap, ^or more preferably extend fully between the gap between the outer surface of the inner wall and the inner surface of the outer wall, so that the output of the axial fan is flow stabilized.

0016A thoroughly mixed lean fuel-air mixture is supplied to the inlet of two or more transversely mounted ramjets. The ramjets are preferably provided in an unshrouded construction. Each ramjet is situated so as to engage and to compress the mixed inlet gas stream which is impinged by the ramjet inlet upon its rotation about the aforementioned axis of rotation. Combustion of well mixed fuel occurs in the rotary ramjet combustor. The hot combustion gases formed by oxidation of the fuel escape rearwardly from the ramjet nozzle, thrusting the ramjet tangentially about the axis of rotation, i.e., it rotates the rotor and associated output shaft . The power generated by the turning output shaft portions may be used directly in mechanical form,- or may be used to drive an electrical generator and thus generate electricity. By use of my novel axial fan in combination with a transversely mounted ramjet which compresses a fuel/air mixture against a stationary peripheral wall, desired low emission levels of oxides of nitrogen can be achieved, and overall efficiency of the engine is enhanced.

0017The design of my axial fan overcomes some of the significant and serious problems which have plagued earlier attempts at the use of supersonic ramjets for efficient electrical power production.

0018First, careful attention to the aerodynamic design of axial fan blades and stators minimizes aerodynamic drag. Thus, the design minimizes parasitic losses to the power plant due to the drag resulting from power required to supply combustion air. Although a relatively small savings due to this element is achieved in the overall plant energy balance, it is nevertheless important commercially because it enables a power plant to reduce parasitic losses that undesirably consume fuel and reduce overall efficiency.

0019Second, the selection of materials and the mechanical design of rotating fan components avoids use of excessive quantities or weights of materials, and provides the necessary strength, particularly tensile strength where needed in the fan rotor. Third, the axial fan with annular air flow outlet _ is a key element in my system configuration which provides for effective mechanical separation of the cool entering fuel and oxidizer gases from the exiting hot combustion gases, while allowing supersonic ramjet operation along a transverse circumferential pathway.

0020To help achieve the desired power plant operational efficiency, I have now developed a novel axial fan design and overall engine configuration which overcomes some specific problems inherent in the heretofore known apparatus and methods that are known to me and which have been proposed for the application of ramjet technology to stationary power generation equipment. Of primary importance, I have now developed a simple, low speed axial fan apparatus which can deliver a stabilized, smoothly flowing air supply.

0021An airtight casing having an interior stationary housing with a first wall surface and an exterior stationary housing with a second wall surface are disposed substantially concentrically along an longitudinal axis, to define between the first wall surface and the second wall surface an annular inlet air plenum. Extending substantially radially between the first wall surface of the interior stationary plenum, and the second wall surface of the exterior stationary plenum, is a number Z of smooth, airfoil shaped stators S, where Z is a positive integer. A short distance therefrom, in an upstream direction, a centrally- disposed fan rotor is provided to rotate about said longitudinal axis. The fan rotor is provided with a relatively smooth, bulbous stationary inlet nacelle, or alternately, a rotating inlet spinner. Just downstream of the inlet nacelle, the fan rotor has a generally cylindrical hub surface which provides a blade attachment portion. Extending substantially radially outward from the blade attachment portion are a number of fan blades. The fan blades are disposed to move air from upstream of the fan toward the airfoil shaped stators, and then on through the gap between the interior stationary plenum and the exterior stationary plenum.

0022A ramjet engine rotor operating cavity is provided, at least part of which has a lowered atmospheric pressure, in order to eliminate aerodynamic drag on the rotor. Attached at the radial end of the rotor are one or more of the at least one ramjets. Each of the ramjet engines is provided in an unshrouded thrust module configuration, where compression is accomplished against a peripheral radial wall. The ramjet engines are situated so as to engage and to compress that portion of the airstream which is impinged by the ramjet upon its rotation about the aforementioned axis of rotation.

0023Fuel is added to the inlet air before compression in the ramjet inlet. The fuel may be conveniently provided through use of fuel supply passageways located- in airfoil shaped stators of the axial inlet air fan, which are located radially in an annular ring, with fuel injection passageways communicating between the fuel supply passageways and the inlet air passageway. Fuel injected into the inlet air stream is thus well mixed with the inlet air before arriving at the ramjet engine combustion chamber.

0024Many variations in the air flow configuration and in provision of the fuel supply, secondary fuel supply, may be made by those skilled in the art without departing from the teachings hereof. Finally, in addition to the foregoing, my novel combination of an axial fan and a ramjet power plant is simple, durable, and relatively inexpensive to manufacture.

OBJECTS, ADVANTAGES, AND FEATURES OF THE INVENTION

0026From the foregoing, it will be apparent to the reader that one important and primary object of the present invention resides in the provision of a novel combination of an axial air supply fan and a transversely mounted ramjet powered engine.

0027Other important but more specific objects of the invention reside in the provision of ramjet based power generation plant as described in the preceding paragraph which: allow the supply of combustion air to be done in a simple, direct manner; cooperate with the fuel supply structures to optimize fuel/air mixing; have a minimum of mechanical parts; are easy to construct, to start, to operate, and to service; cleanly burns fossil fuels; in conjunction with the just mentioned object, results in fewer negative environmental impacts than most power generation facilities presently in use.

0028Again, the important and unique feature of my ramjet engine is the combination of an axial flow inlet air fan with a rotating ramjet wherein the actual ramjet inlet is transverse to the axis of inlet air flow.

0029Other important objects, features, and additional advantages of my invention will become apparent to those skilled in the art from the foregoing and from the detailed description which follows and the appended claims, in conjunction with the accompanying drawing. BRIEF DESCRIPTION OF THE DRAWING

0030FIG. 1 provides a partial perspective view of my novel power plant apparatus, showing the inlet nacelle, the axial inlet air fan, the fuel header and inlet fuel feed lines which feed fuel at low pressure to stators- for injection at fuel outlets, and showing the converging annular inlet gas flow path to accelerate the mixed inlet gas to the transversely oriented rotary ramjet, which rotates within a low aerodynamic drag housing and which compresses the mixed inlet gas against a peripheral wall, to oxidize the fuel and to create hot combustion gases, thereby driving the rotary ramjet and output shaft which is coupled with a gear box for useful mechanical output work. FIG. 2 is a partial perspective view of my novel power plant apparatus, similar to the view just shown in FIG. 1 above, but now showing the axial inlet air fan and accompanying fan motor in more detail, and now showing the fuel -air pre-mix housing having a series of radially disposed airfoil shaped stators and accompanying vortex generators for adding transverse momentum to the entering air to assure adequate mixing of fuel and air to produce a uniformly mixed inlet gas for supply to the transversely oriented rotary ramjet. FIG. 3 is a split, partially exposed perspective view of the combustion air inlet, showing the inlet nacelle, the axial inlet air fan, struts used for the connection of a portion of the electrical power, water, oil, compressed air, and vacuum lines to the engine.

0031FIG. 4 is a partially, split, partially exposed perspective view of my ramjet power plant apparatus, showing in a first part the annular air supply plenum- and accompanying axial inlet air fan, and in a second part the fuel -air premix housing with airfoil shaped stators which are fixed between inner and outer stationary housing walls, and the vortex generators for adding transverse momentum to the entering air to assure adequate mixing of fuel and air to produce a uniformly mixed inlet gas for supply to the rotary ramjet.

0032FIG. 5 is a cross-sectional view of the inlet to my ramjet power plant, showing the inlet nacelle, the axial inlet fan and accompanying fan motor, the air supply plenum, the fuel -air premix housing with airfoil shaped stators which are fixed between inner and outer stationary housing walls, and the transition section with a converging annular passageway having an outer peripheral wall, for feed of the mixed inlet gas to the ramjets at the periphery of the rotor; cooling air, cooling water, and the air lines helpful to evacuate boundary layer air from the rotor to help assist in reduction of aerodynamic drag near the rotor are also illustrated. DETAILED DESCRIPTION

0033Referring now to the drawing, FIG. 1 depicts a partial cut-away perspective view of my novel rotary ramjet driven power plant 100. Major components shown in this FIG. 1 include the rotary ramjet engine assembly- 102 and gear set 104. The ramjet engine assembly 102 has a driven output shaft 108, which is operationally coupled with gear set 104 for power transfer therethrough. Gear set 104 has power output shaft 110, which is coupled with and rotates at a desired rate of rotation to drive an electrical generator (not shown) , or other shaft power consumer.

0034The structure of the rotary ramjet engine assembly 102 has several key components. A high strength rotor ¹²⁰s has output shaft portions 124 and 108. The output shaft portions 108 and 124 turn in inlet 126 and outlet (barely visible) 128 bearing assemblies, respectively. In FIG. 1, one embodiment of my high strength rotor 120 design and components thereof is shown, illustrating rotor construction using central disc 134 (of ultra-high strength steel, or high strength fiber composite, or metal matrix composite) .

0035A plurality of rim segments 138 in a series of rim segments from 138_ through 138_X are interlockingly and detachably secured to the central disc 134. One or more, and preferably two or more ramjets 140 are provided using detachably affixable ramjet thrust segments 142 in a series of thrust segments 1421_ through 142_x affixed to central disc 134. Each of the required ramjet thrust segments are provided in functional order, shaped as required in a then relevant portion of the applicable ramjet structure, the basics of which are- taught in my earlier and now issued United States Patent No. 5,372,005, and particularly, No. 5,709,076, as well as U.S. Patent Application Serial No. 08/213,217 (filed March 3, 1994); for details see the full disclosures of each, which are incorporated herein in their entirety by this reference.

0036Importantly, there are also a number of peripherially extending and preferably helical strakes Sι_ through S^. Each of strakes S_]_ through Sj has a number of strake segments SS of radial height SJJ, each strake segment SS being integrally provided with a rim segment 138, or with a ramjet thrust segment portion 142, as appropriate. The strakes Sη_ through S^ partition the well mixed fuel-air inlet gas 170 (which preferably is thoroughly and uniformly mixed as further explained herein below to provide both fuel and oxidizer) , so that the mixed inlet gas 170 flows to the ramjet inlet throat 174. This process occurs at a first of one or more ramjets 140 and then at a second (not shown) of one or more ramjets 140 and so on to an Xth of the one or more ramjets 140 that are mounted on rotor 120. Preferably, the number X of ramjets 140 and the number N of strakes S are the same -positive integer number, and N and X are at least equal to two.

0037The strakes Sι_ through S_j allow the feed of a well mixed fuel-air inlet gas 170 to each ramjet 140 without appreciable bypass of the entering mixed inlet gas 170- to the exhaust combustion gases 176. Also, the exhaust combustion gases 176 exiting from each of the one or more ramjets 140 is effectively prevented by the arrangement of strakes S from interfering with the inflow of fuel air premix, thus effectively preventing the return of spent combustion gases 176 from the exhaust side Sgx of strakes S to the inlet side S N of strakes S.

0038The construction and operation of my ramjet 140 is quite unique. The ramjet thrust segments 142, as seen in FIG. 1, are provided in an unshrouded configuration, that is, the ramjet structure affixed as part of rotor 120 provides the necessary elements for compression of incoming mixed inlet gas 170, except for a containment structure against which compression of the mixed inlet gas 170 and expansion of escaping hot combustion gas 176 occurs. In this unique engine, the necessary containment structure for compression of the incoming fuel -air mixture is provided by the inner peripheral wall 203 of engine housing 204. The above discussed strakes S have a radial height S_jj (see FIG. 5) which extends to a tip end S> that is designed for rotation very near to the interior peripheral wall surface 203, in order to minimize gas leakage in either direction.

0039Turning now to FIGS. 4 and 5, the detailed structure of the overall fuel-air pre-mixing housing 210 and related components of my novel rotary ramjet power- plant 100 are illustrated. Major components include an inlet plenum 212, a support casing 214 with utility struts 216 that support fan housing 218, and the mixing section 220. The preferably smooth outer surface 222 of the fan housing 218, and the inner surface 224 of the support casing 214 provide an initial length Xp for receiving the inlet airflow.

0040As noted in FIG. 2, a fuel FF such as natural gas is supplied, through a main fuel header 226 and a pressure regulator 228, thence to fuel supply line 230 and then on to one or more fuel supply headers or manifolds 232. Fuel distribution lines 234 (in a series of distribution lines 234_]_ through 234_x, where "x" associated with distribution lines "234" corresponds to the number of fuel supply structures 240 (stators) , to provide fuel from headers 232 to the fuel supply structures 240, via fuel inlet fittings 242 (see FIG. 7) .

0041Fuel inlet fittings 242 are preferably provided in size and shape to extend through outer wall 250 of mixing section 220, to secure (with fasteners such as nuts 251) the radially distal fuel inlet 252 of fuel

0042-li supply structures 240. The fuel inlet - fittings 242 can also be utilized to secure the radially distal or outer end 240_Q of fuel supply structures 240 to the inner surface 255 of outer wall 250. In this configuration, a radially proximal inlet 256 with proximal inlet threads- 257 is plugged with gas tight fastener 258, which also serves to secure the radially proximal or inner end 240 of fuel supply structures 240 to the outer surface 260 of inner wall 262 of the convergent, preferably annular inlet air plenum 264. As further seen in FIG. 3, spacers 266 with smooth airfoil leading edges 268 are provided at a narrow cross-section of inlet air plenum 264 to securely space apart the inner wall 262 and outer wall 250 via a gap distance G. Fuel supply structure 240 preferably has a low drag aerodynamic body shape with a leading edge 240j_,, a trailing edge 240^, a chord C and a thickness T. A fuel passageway 270 defined by interior wall 272 extends between distal inlet 252 and the proximal inlet 256 of fuel supply structure 240. For ease of fabrication, I prefer to provide fuel injection outlets 274 defined by an injector edge wall in opposition to fastener receiving threads which are used to secure one or more vortex generators 278 to stator 240 via fasteners 280. As noted above, ramjets 140 are suitable for oxidizing a fuel FF continuously supplied thereto, preferably in a thoroughly mixed inlet gas stream 170. Referring now to FIG. 4, and to FIG. 1, it can be seen that in order to accomplish the required thorough mixing, the entering airstream 288 is preferably provided through inlet plenum 212, where the preferably stationary inlet nacelle 292 before axial fan 300- partitions the inlet carrier gas stream 288 (normally air, although mixed gas containing preselected additives could be provided) into an annular air supply stream 294. The aerodynamically efficient blades 301 of axial fan 300 are attached to fan hub 302 which is driven by fan motor 304. Fan motor 304 is supported by preferably spoked 305 type mounting bracket 306 detachably mounted from a recessed fan mounting flange 308 at the upstream end 310 of support casing 214. The fan is preferably supplied by electrical power via cable 320, through utility strut 216.

0043The annular flow of the inlet air stream 294 is straightened and smoothed by the leading edge portion 240L of the fuel supply structures 240. Fuel is injected at fuel injection outlets 274. Transverse momentum is imparted to some of the inlet air stream 294 as well as to the relatively low velocity injected fuel by vortex generators 278. The vortex generators are located sufficiently upstream of the ramjets U so as to allow thorough and reliable fuel-air mixing through a mixing length Xjj, as indicated in FIG. 9. A resultant thoroughly mixed inlet gas stream 170 is fed to ramjets 140, which utilize oxygen (preferably from the incoming airstream 288, or otherwise supplied or supplemented) as the oxidant source. Ramjets 140 are provided at the outer, distal reaches of rotor 120 so that the propulsive effect of the ramjets 140 is utilized to turn- rotor 120 and the output shaft 108.

0044The rotor 120 is rotatably secured in an operating position by a fixed support structure base 320 at pivot pin 322 in a manner suitable for extremely high speed operation, such as rotation rates in the range from as low as about 4,500 rpm, or more preferably from about 6000 to 7000 rpm, or up to about 8,900 rpm, or even 10,000 to 20,000 rpm, or higher. In this regard, inlet side bearing assembly 126 and outlet side bearing assembly 128, or suitable variations thereof, must provide adequate bearing support for high speed rotation and thrust, with minimum friction. The detailed bearing and lubrication systems may be provided by any convenient means, and although oil supply and return lines are shown in FIG. 5 of the drawing, need not be further discussed herein.

0045As earlier indicated, a key feature of my power plant is the rotor 120. Rotor 120 spins about its axis of rotation due to thrust from ramjets 140. Two design parameters of the rotor 120 are extremely important. First, the rotor must be constructed of materials which enable it to survive the extremely high centrifugal loads encountered while the rotor is moving so that the ramjet can operate at supersonic speeds, preferably in the Mach 3.5 range, i.e., the rotor must be capable of withstanding extremely high tensile stress. Second, at such speeds, minimizing the rotor's overall aerodynamic - drag is critical .

0046For ease of construction, I prefer to use an interlocking dove tail type attachment arrangement for interlocking the ventilatable rim segments 138 to rotor hub 134. As provided, any of the rim sigments 138 or the ramjet thrust modules such as module 142 are releasably affixed as a part of rotor 120, and thus rim segments 138 and the ramjet thrust modules may be easily replaced. I prefer use of a boundary layer control technique to reduce aerodynamic drag on the rotor 120. One suitable method is to provide a tight fitting housing 400 with rotor side surface 402 in close proximity to surface 120_s of rotor 120. More preferably, providing and sealing an operating cavity 404, behind the tight fitting housing 400, so as to enable the rotor to function as a vacuum pump, which allows most gas on the surface 120_s of the rotor to be suctioned off via vacuum line 410 from hoop shaped vacuum header 412. Also, cooling air for the rim segments 138 and thrust segments 142 is provided via hoop shaped compressed air header 420 and air line 422. Finally, even though high combustion temperatures are experienced, my advanced fuel -air mixing apparatus provides extremely low NOX output. This is because of the lean and extremely well mixed fuel -air inlet gas stream, and because of the short residence times at the_ high combustion temperatures.

0047One important advantage which is afforded by my axial air flow fan and accompanying fuel -air mixing apparatus and method is that low pressure fuel can be utilized, particularly fuels of less than 60 psig, and more preferably less than about 30 psig, and even more preferably, of about 15 psig or less. A related advantage is that low pressure gas gathered from hydrocarbon production can be utilized. For example, gas now normally flared in offshore oil platforms, or from gas gathering fields, or gas transmission facilities, or from refinery operations, can be advantageously utilized, without the necessity to compress such gas

0048(which operation cannot be conducted safely, with respect to some types of fuels which may be alternately and advantageously consumed in my equipment) .

0049Thus, it can be seen that the method and apparatus for producing mechanical, electrical, and thermal power as described above provides a- revolutionary, compact, easily constructed, cost effective power plant. The output from this power plant can be used in conjunction with existing power delivery systems, and represents a significant option for reducing air emissions by combustion of clean burning fuels. Further, given the efficiencies, dramatically less fuel will be consumed per unit of electrical, mechanical, or thermal energy generated. -

0050Consequently, it will be seen that the objects set forth above, including those made apparent from the proceeding description, are efficiently attained, and, since certain changes may be made in carrying out the construction of a power generation apparatus and in the execution of the method of power generation described herein, while nevertheless achieving desirable results in accord with the principles generally set forth herein, it is to be understood that the invention may be embodied in other specific forms without departing from the spirit or essential characteristics thereof. For example, while I have set forth exemplary designs for a fuel feed arrangement, many other embodiments are also feasible to attain the result of the principles of the apparatus and via use of the methods disclosed herein.

0051All the features disclosed in this specification (including any accompanying claims, the drawing, and the abstract) and/or any steps in the method or process so disclosed, may be combined in any combination, except combinations where at least some of the features and/or steps are mutually exclusive. Each feature disclosed in this specification (including in the accompanying claims, the drawing, and the abstract) , may be replaced by alternative features serving the same or similar purpose, unless expressly stated otherwise. Thus, unless expressly stated- otherwise, each feature disclosed is one example only of a generic series of equivalent or similar features.

0052Therefore, it will be understood that the foregoing description of representative embodiments of the invention have been presented only for purposes of illustration and for providing an understanding of the invention, and it is not intended to be exhaustive or restrictive, or to limit the invention to the precise forms disclosed. On the contrary, the intention is to cover all modifications, equivalents, and alternatives falling within the spirit and scope of the invention as expressed herein. As such, it is intended to cover the structures and methods described therein, and not only the equivalents or structural equivalents thereof, but also equivalent structures or methods. Thus, the scope of the invention is intended to include variations from the embodiments provided which are nevertheless described by the broad meaning and range properly afforded to the language used herein, or to the equivalents thereof.