HK1024730A - Ramjet engine for power generation - Google Patents

Description

Ramjet engine for power generation

In the disclosure of this patent document, portions are subject to copyright protection. These matters are described in the patent and trademark office patent documents or records, and the copyright owner has no objection to the facsimile reproduction by anyone of the personal records of the patent document or the patent disclosure. But the copyright owner will legally reserve all rights if used in other situations.

The invention uses the technology of a stamping sprayer to generate power. The basic principles of this technology are discussed in detail in my previously applied patents. Those patents are filed on 9/14/1992 as application number 07/945,228, and are now U.S. patent number 5,372,005, published on 12/13/1994. In addition, some details of this technique are provided in U.S. patent application No. 08/480,663, filed 6/7/1995. Details of the specific implementation of this technique are also evident from earlier filed U.S. provisional patent application. Provisional patent application No. 60/028,311, filed on a date of 1996, 12/16. This document combines these patent applications with approved patents.

Field of the invention

The present invention relates to an efficient, novel ramjet technology driven rotary engine and a method of using the engine to generate electrical and mechanical energy. The method minimizes nitrogen oxide emission rates. More particularly, the present invention relates to a power-generating apparatus propelled by a ramjet technology engine, and some configurations thereof. These structures are capable of withstanding the extremely high tensile stresses generated at supersonic speeds by rotating components mounted at the end of the ramjet. This feature of the power plant is particularly useful for generating electrical and mechanical energy.

Background

There is a continuing need in society for simple, efficient, and inexpensive thermoelectric devices that reliably provide low-cost electrical and mechanical energy. This is because many power generation plants that produce electrical and/or mechanical energy can actually benefit from prime movers. The prime mover has recently been a significant improvement in the actual cycle thermal efficiency in the generation of power. Particularly in medium-sized power plants in the range of about 10 to 100 megawatts (1 megawatt equals 1000 kilowatts). Medium-sized power generation equipment is used primarily in industrial applications such as stationary generator sets, rail vehicles, ship propulsion systems, and aircraft engines.

Medium size power generation plants are also suitable for use in industrial and consumer cogeneration plants. Such equipment is increasing in the thermal energy demand service industry because it is used to generate electricity while reducing the overall cost. Current power plant designs for cogeneration applications include: a) the gas turbine is driven by heat energy and kinetic energy obtained by co-combustion of natural gas, fuel oil or other fuels; b) a steam turbine driven by steam obtained by combustion of coal, natural gas, combustible waste or other fuels in a boiler; c) large-scale reciprocating (piston) engines, which are typically implemented using diesel engines burning heavy oil.

Of the power plant technologies currently in use, the reciprocating piston diesel and aero-engine derived turbines are the most efficient. Unfortunately, in the case of a reciprocating piston diesel engine, if the required output power is above 1 megawatt, the parts of the engine are too bulky to handle. Therefore, the reciprocating piston type diesel engine is widely used in commercial use, and a large-volume series has not been developed yet. Gas turbines have better reliability than reciprocating piston diesel engines, and are often used in high output power class applications. However, due to its general efficiency in converting fuel to electricity, the majority of gas turbine power generation plants are used in combined power generation systems that utilize both electricity and heat. In such applications, only moderately power efficient gas turbines improve overall efficiency by utilizing heat energy.

Fossil fuel fired steam turbines produce power systems that are also quite inefficient in generating power, with the ratio of total output power to the heating value of the fuel typically ranging from 30% to 40%. But due to its high reliability, it is commonly used in utility and industrial base load power generation systems.

In any case, any technique that significantly reduces the cost of the generated power is desirable, especially from the standpoint of the administrative legislation that simplifies electricity sales. Fundamentally, the most efficient use of power generation technologies will be seen in the long term fuel costs and overall greater efficiency.

Summary of The Invention

I have now invented an improved power generation apparatus that utilizes a supersonic ramjet thrust unit as a prime mover to drive a power shaft. In this way to generate power, the supersonic ramjet thrust unit is coupled directly or indirectly to an electric generator. By using an auxiliary fuel feed system, the power output of the ram injection thrust unit can be adjusted to the value required to maintain a constant rotational speed, as is required at minimum output load of a synchronous power plant. The efficiency of a supersonic ramjet power plant is greatly improved over the entire operating range compared to power plants heretofore known to me.

Four difficulties are solved in the power generation device of my invention. It is these challenges that have hindered earlier efforts to apply ramjet technology to power generation:

first, at moderate mach numbers (ratio of rotating circumferential edge velocity to sonic velocity), the aerodynamic drag of the design is minimal. Here, the operation speed is preferably from about mach 2.5 to mach 4.0. This is achieved by reducing the effective atmospheric density of the rotor operating space and using boundary layer control and cooling techniques. Thus, the design minimizes parasitic losses of the power-generating equipment. Parasitic losses come from drag created as the rotor rotates. This is quite important in terms of scale efficiency. Since it allows the power plant to be produced without significant parasitic losses that result in unnecessary fuel consumption and overall efficiency degradation.

Secondly, the material selection and mechanical design of the rotating parts avoids the use of excessive or heavy materials, but requires a certain strength, in particular tensile strength. The rotor is made of a material with strong tensile force, so that internal fracture caused by centrifugal force during high-speed rotation of the rotor can be avoided.

Third, the design mechanically splits the cool inlet fuel and oxidant gases from the hot outlet combustion gases while allowing the ramjet to operate along an annular channel.

Fourth, the design provides film cooling for the edge components of the rotor. The edge member includes an edge lobe, an edge side plate, and a punch jet thrust unit. This novel design allows the use of lightweight materials for the material surrounding the ramjet combustion chamber and hot combustion exhaust port, even including the lightweight material titanium, which is combustible.

To address the above-mentioned problems, i developed a new rotor design and method. This design overcomes the problems inherent in all devices heretofore. The method enables the use of the ramjet technology in stationary power generation equipment. Most importantly, I designed and developed a low drag rotor with one or more unshrouded ramjet thrust units mounted to the rotor tip. The number N of side plates S divide the gas at the inlet into a first inlet, a second inlet, and up to the nth inlet, which flow into the ramjet in sequence. The side plates are distributed along the periphery to spirally extend. Each side plate S has an upstream edge (or inlet edge) and a downstream edge (or outlet edge). I prefer that the number of ramjets X and the number of side plates N be the same and positive integers for rotor balancing and power output purposes. The values of X and N are at least equal to 2. The tail gas discharged from the stamping and spraying machine is returned to the inlet side of the next stamping and spraying machine which is arranged in sequence, so that the so-called tail gas short circuit is effectively protected. In each ramjet combustion chamber, this problem can be effectively accomplished by the side plates S under high pressure. The downstream edge extends from the exhaust port of the ramjet to before the inlet of the next ramjet. Bypass protection between hot exhaust gas and cool inlet fuel-air mixture is accomplished by my design ramjet thrust unit. The exhaust gases from each ramjet expand to near atmospheric pressure so that the side plates S act only as a large fan or pump which propels the exhaust gases as the rotor rotates.

I provide several specific solutions to achieve a high strength rotor. In a more desirable embodiment, the cross-section of the rotor consists of carbon fiber discs. In another solution, the rotor consists of a steel hub and high strength spokes. In either case, the rim assembly and ram jet propulsion unit are attached to the rotor and may be removed or replaced.

The air pressure in the working gap of the rotor is less than atmospheric pressure, preferably about 1 psi. The purpose is to eliminate the aerodynamic drag of the rotor. The rotor working gap can be evacuated by a vacuum pump and properly sealed to ensure vacuum. The places that need to be sealed are: (a) a rotor output shaft passing through a shaft wall of the working gap; (b) a marginal lobe; (c) a ram ejector thrust unit.

The edge flap and the ram injector thrust unit each contain a cooling air receiving cavity. Each cavity has radially extending parallel sidewalls, a cavity sidewall, and a trailing sidewall. Cooling air outlet passages pass through the two side walls. The cooling air receiving chamber functions as a centrifugal compressor which delivers cooling air to its outlet passage. The exit of the cooling air channel is at the edge flap and the face of the ramjet thrust unit. The radial dimension from the side wall of a single air receiving chamber determines the working distance of the air receiving chamber compressed air and thus the air pressure delivered to the exit of a particular boundary layer cooling channel.

Attached to the radial end of the rotor are one or more ram jets. Each ram injector has a shroudless thrust unit configuration. These ramjet engines rotate about the aforementioned output shaft and act to compress the air stream impinged upon by it. The fuel and air mix before entering the ram injector inlet passage. The device makes the fuel and the air enter the annular channel for mixing and oxidation through the mutual switching between the fuel supply channel and the air inlet channel, and then enter the combustion chamber of the ramjet engine. The fuel exits the ram injector aft nozzle and rapidly propels the output shaft and rotor for rotation. The power thus generated can be used directly to generate electricity by using its mechanical energy, or it can be used to drive a generator. The ramjet engine allows it to run synchronously, i.e. the power output of the ramjet can be varied to maintain the speed of the rotating shaft constant.

When the ramjet power plant is used in a waste heat utilization system, the fuel gas discharged by the ramjet is fed into a heat exchanger. Where the gas is cooled and the liquid for heat exchange is heated (e.g. water, we can get hot water or water vapour). The heat exchange fluid can be conveniently used for thermal or mechanical purposes. Such as driving a steam turbine. And the cooled gas is finally discharged to the atmosphere.

Finally, it is noted that variations may be made in the airflow path layout, fuel supply and supplemental fuel supply equipment, starting ignition, etc., without departing from the principles herein. In addition, this new power generation device is simple, durable and relatively inexpensive to manufacture. Objects, advantages and features of the invention

From the foregoing, it is an important and primary object of the present invention to provide a new ramjet power engine that can be used to generate both mechanical and electrical energy at a cost effective rate.

More specifically, it is an important object of the present invention to provide a ramjet driven power generation device. The device can bear the stress and deformation generated during high-speed rotation, thereby providing a method for generating power with high efficiency.

Other important objects of the invention have been mentioned in the foregoing description of the power plant:

the device has high efficiency. I.e. it is capable of delivering high heat and high work relative to the calorific value of the fuel input to the power plant;

in connection with the above object, the inventive device provides the power producer and ultimately the power purchaser with lower cost than currently available;

the inventive device enables the generation of power to be carried out in a simple and direct manner;

the inventive device has a minimum of mechanical parts;

the device avoids complex subsystems;

compared with numerous existing power generation devices, the device saves physical space;

the device is easy to manufacture, start, operate and maintain;

the device can fully burn fossil fuel;

in relation to the above object, the inventive device has less negative impact on the environment than most of the power generating facilities currently in use;

the device of the invention has a rotating part composed of the structure of the minimum substance arranged at the tail end, which is used for counteracting the stress and deformation effect generated when the device rotates at a high speed;

the inventive device operates with minimal aerodynamic drag.

One of the important features of the present invention is the novel high strength rotor structure. In one embodiment, the rotor consists of a high-strength steel hub and spokes. The tail end of the rotary side wheel is provided with a thrust unit of the punching and jetting machine without a protective cover. The unique structure makes it possible to rotate at speed higher than the ultimate stress failure speed of the material and provide sufficient cooling condition for the side wheel and the punching and jetting machine to ensure the integrity of the material in high temperature condition. In another design, the rotor is comprised of carbon fiber resin disks, which simplifies the overall structure and provides ample strength while also providing a ventilated cooling system design to ensure the integrity of the rotor, edge wheel and ramjet structural materials.

Another important feature of the present invention is the design of the use of a shroudless ramjet. In this design, a stationary circumferential wall plate surrounding the die-jet is part of the die-jet thrust unit. This particular design minimises the material used in the rotating part, and thus allows the rotor to be made of a lower strength material and (possibly) a higher safety margin for the overall strength requirements at a given operating mach number.

A further important feature of the present invention is the use of a slotted plate to separate the inlet channel flow (in which the fuel and air have been previously mixed) from the exhaust gas flow of the ramjet. This tailored design feature ensures that exhaust gas is removed directly from the engine and only the inlet flow required for combustion is provided to the ramjet.

Other objects, features and other advantages of the present invention will become apparent from the following detailed description, when considered in conjunction with the appended claims and drawings.

Brief description of the drawings

FIG. 1 provides a partial perspective view of my design power-generation device. The figure shows a rotor mounted for rotation within a power generating apparatus, the rotor carrying an output shaft for rotation about an axis, the output shaft being coupled to a gearbox and connected to a generator via the gearbox.

FIG. 2 is a partial longitudinal cross-sectional view of my design ramjet power-producing apparatus. The figure shows the output shaft secured to the rotor and something related to it, as well as the shroudless ramjet thrust unit integral with the rotor. In addition, an inlet air passage, an annular passage, an exhaust gas discharge passage and an exhaust gas discharge outlet are shown. The figure also shows cooling air, cooling water and vacuum space profiles;

FIG. 3 is a carbon fiber rotor with an edge wheel, unshielded ramjet and side plates integral therewith, particularly illustrating the edge wheel portion with the side plates.

FIG. 4 is an expanded view of the rotor circumference, with the cut-away at line 4-4 indicated in FIG. 3. The relationship between the thrust unit of the unshrouded stamping sprayer and the side wheel part and the side plate part is shown in the figure;

FIG. 5 is a perspective view of an edge lobe including a shroudless ramjet thrust unit and associated side plate portions;

FIG. 6 is a cross-sectional view of a carbon fiber rotor, a shroudless ramjet thrust unit and associated circumferential side walls;

fig. 7 is a cross-sectional view of a second embodiment of a rotor. The figures show a steel rotor, a shroudless ramjet thrust unit and associated circumferential side walls;

figure 8 is a side wheel view with side plates. The cooling air passages and their outlets, as well as the film cooling outlets, are also clearly indicated in the figure;

figure 9 sets forth a partial cross-sectional view at the angle of line 9-9 indicated in figure 8. The close-fitting relationship of the rotor side plates to the inner surface of the circumferential wall is shown;

FIG. 10 is a partial cross-sectional view of a thrust unit and side plate embodiment;

FIG. 11 is a perspective view of the thrust unit and side plate embodiment of FIG. 10;

FIG. 12 is a partial perspective view of a rotor and side plate embodiment. The figures show details of film cooling holes and airflow at the associated radial edge layer and side plates;

fig. 13 shows a cross-sectional view of the circumferential wall of the power generating apparatus. This view is taken along line 13-13 of fig. 2 at the location of the connecting side plates, showing the ring valve in the closed position;

fig. 14 shows a cross-sectional view of the circumferential wall of the power generating apparatus. Similar to fig. 13, except with the annular valve in the open position. The annular valve in the open position is used to bleed air through the circumferential side wall when the device is activated;

FIG. 15 is a longitudinal elevational view of an outer frame of the power-generating apparatus. As viewed from the line 15-15 in fig. 2. The outer frame, the exhaust gas discharge passage, the circumferential wall, the cooling water and the passage of the cooling air are shown in the figure;

FIG. 16 is a schematic of a cyclic power generation system layout consisting of a power generation plant, a generator and a steam turbine. Steam turbines can also be used to generate electricity. The power generation equipment uses a rotor and a thrust unit driven by a novel supersonic stamping injection machine designed by I as a prime motor;

FIG. 17 is a side elevational view of FIG. 16;

fig. 18 is a partial cross-sectional view of a modified version of the novel power-generating apparatus. The figure shows the cooling system, the ring valve and the side plates which change position due to the rotation of the rotor.

Detailed Description

Reference is now made to the description. FIG. 1 depicts a partially cut-away perspective view of my supersonic ramjet driven power-generating apparatus 100. The main components in the figure are a supersonic ramjet engine complete machine assembly 102 and a gear set 104 fixed on its mounting bottom slot 106. The ramjet engine assembly 102 has a drive output shaft 108. The shaft is coupled to a gear set 104 for power transmission. The gear set has a power take-off 110 coupled to the generator and driving a generator 112 at a desired rotational speed. Power is output by the generator 112 through cables in the protective casings 116A, 116B, 116C.

The supersonic ramjet engine is mounted in a ramjet engine complete machine assembly 102, the structure of which is clearly illustrated in the associated fig. 2, 4, 7, 8, 10, 11 and 18. I developed a high strength rotor 120 having output shaft portions 108 and 124. The output shaft sections 108 and 124 are in bearings 126 and 128 of the inlet and outlet passages, respectively. And two sets of bearings are mounted in the frames 130 and 132, respectively. In fig. 2, 7, 8, 10 and 11, one embodiment of a high strength rotor 120 design is shown. The rotor structure employs a unitary (high strength steel) hub 134 with radially extending solid spokes 136 outward of a solid ventable side wheel portion 138 or ventable shroudless ramjet 142. The latter two are described with reference to fig. 11 and 18.

For ease of construction, i prefer to make (a) the interlocking hinges 144 between the hub 134 and the spokes 136, or (b) the interlocking hinges 146 between the connecting spokes 136 and each ramjet, with a piano hinge type connecting structure arrangement, as shown in fig. 2 and 8. As shown in FIG. 8, interlocking hinge 148 between spoke 136 and side wheel portion 138 is formed by hinge portion 150 on spoke 136 and a complementary hinge portion 152 on side wheel portion 138. The latch 154 is inserted into a receptacle 156 in an inner sidewall 158 of the side wheel and then through a mating receptacle 160 in an outer sidewall 162 of the spoke 136. The pin 154 is in a close-fitting relationship with the receptacles 156 and 160. Similar components are also used in the construction of the hinge joints 146 between the spokes 136 and the ramjet 142. As previously described, any of the edge wheel sections 138 or the ramjet thrust units U, such as unit 142, may be removably secured to the rotor as part of the rotor 120. In this way, the edge wheel portion 138 and the ram jet thrust unit are easily replaced.

Fig. 3, 5, 6 and 12 depict a similar functional design for making the rotor 120' from carbon fiber material. The rotor is cut with a series of T-shaped mounting teeth which fit into Y-shaped tooth slots on each side wheel section 138 or ram jet thrust unit U.

As can be seen in FIG. 4, the circumferential edge of the rotor 120 is formed by a plurality of edge lobes 138 and one or more ramjets U (e.g., 142). Importantly, there are a number of circumferentially extending side panels S1 to SN circumferentially above the circumferential edge. Each side panel has a number of side panel lobes. It is proposed that each side plate lobe be formed integrally with the side wheel lobe or the ram injector. As shown in fig. 4, each side flap may be defined by a pair of their edges. The side panel S1 begins at S1(IN-I) of the inlet IN of the mixed gas 170, then to S1(I-H), then to S1(H-G), and so on until S1(A-EX), and ends at the exhaust end EX of the side panel of the combustion gas 172. Similarly, the side panel S2 begins at S2(IN-R) of the inlet IN, then goes to S2(R-Q), and so on, similar to the previous. The side plates S1 to SN separate the incoming gas 170 (fuel and oxidant mixed gas prepared in advance) so that the mixed gas 170 flows into the inlet throat 174 of the ramjet. This process is followed by the 1 st, 2 nd, and up to the X th unshielded ramjet mounted on the outer end of the rotor 120. For rotor balancing purposes, the number X of unshielded ramjets U and the number of side plates S should be equal and at least 2.

The side panels S1 through SN allow the mixed gas 170 to be fed into each ramjet without appreciable flooding of the inlet gas 170 into the combustion exhaust 176. Most importantly, the ram injector exhaust combustion gases 176 avoid the so-called "short circuit" phenomenon due to the presence of the skirt. This prevents the exhaust combustion gases 176 from one ramjet exhaust edge SEX from returning to the next ramjet inlet edge SI. This feature of the side plates is more attractive in view of the rotor or rotating device 120 (different parts can be seen in different figures). The rotor rotates against (a) a stationary annular inner mount with an inwardly curved plate surface 200; (B) and more preferably an annular circumferential wall plate 202 having an inner circumferential wall plate 204. The side panel S has a height HH from the top ST which is intended to be rotated very close to the circumferential panel inner side wall 204. As can be seen in fig. 9 and 18, a wear resistant smooth sealing metal ring 206 is embedded in the fixed circumferential plate inner side wall 204 with the top end ST of the side plate S in tight contact therewith.

I have designed a ramjet configuration and its operation that is also unique. The ramjet thrust unit U in fig. 5 and 11 shows a unshrouded structure. That is, the configurations depicted in fig. 5 and 11 provide only the components necessary for intake compression, and no volumetric configuration, with which compression and expansion occur. In this particular engine, the containment structure is formed by the inside circumferential wall 204 of the plate 202.

The actual compression zone and the die-jet structure can be seen in fig. 5 and 11. The incoming mixed gas stream 170 is compressed by the ram jet inlet structure 210. The inlet structure 210 is between the ram eductor side RJ of the S2(IN-R) inlet section and the eductor side of the S1(a-EX) inlet section. The transition portion 212 then serves to stabilize the normal impact process. After passing through the straight-down flame holder 214, to the combustion chamber 216. Combustion then occurs in combustion chamber 216. Due to the obstruction of the gas geometric throat 218 to the choke point 220, the pressure rises to 180 pounds per square inch (the pressure in this region may be selected to be an otherwise appropriate value depending on design requirements) due to combustion. After exiting choke point 220, the combustion gases expand to near atmospheric pressure in the area of outer flow nozzle 222 and cool to approximately 1100 ° F or so. The helically arranged side plates S1 and S2 are thin plates having a thickness (axial) of about 0.15 "at the root and about 0.1" at the tip. From the design shown, it is believed that gas leakage will be minimized and substantially define the area of the combustion chamber 216.

Turning now to fig. 2 and 18. These views further illustrate the general structure of my designed prime mover for a power generation plant. Ramjets U1 and U2 are adapted to oxidize fuel FF. Fuel FF is continuously supplied from a fuel tank (not shown) through fuel supply pressure regulator 230 (FIG. 1), through fuel supply manifold 232, and into air stream 234 through fill port 236 to form mixed air stream 170. The incoming air flow 234 is generated from an inlet air plenum IAP by a fan F driven by a fan motor FM or by other means, and is provided via an annular supply SH consisting of an inner plate IH and an outer plate OH. The fuel injection ports 236 are positioned as far as possible upstream of the ramjet so that the fuel can be adequately mixed. The mixed gas stream 170 is fed into the ramjet U. It uses oxygen from air stream 234 (ambient air surrounding the power plant) as the oxidant feed. The ramjet U is mounted outside the circumference of the rotor 120 (or carbon fiber rotor 120 '), and its propulsion serves to rotate the rotor 120 or 120', including the output shaft 108 (directly connected to the rotor).

The rotor 120 is protected by fixed support structures or frames 130 and 132 and can safely operate at very high speeds, such as 10,000 to 20,000 rpm, and even higher. From this point of view, the inlet and outlet side bearings 126, 128 and related components must provide adequate support during high speed rotation and propulsion. When the working gap 250 is sealed around, the rotation has minimal resistance and results in a working pressure of about 1 psi within the vacuum environment. Details of the bearings and lubrication system are readily available in the knowledge of high speed rotating machines and are not discussed further herein.

The working gap 250 is defined by the circumferential inner wall 204, an inner wall 254 of the frame 130, and an inner wall 256 of the frame 132. During normal operation, the gap is evacuated to a vacuum pressure of about 1 psi. As shown in fig. 18, the inlet side of the ram jet propulsion unit U provides an outer seal 260 and the outlet side provides an outer seal 262. Such a seal prevents "blow-by" into the vacuum working gap 250.

To cool the edge wheel portion 136 and the ramjet thrust units U1 and U2, compressed air is provided through air passages 270A and 270B. I prefer to provide 250 psi and 80 deg.F air to the chambers 272A and 272B, and allow it to expand through the porous metal orifices 274A and 274B to 13.5 psi and-150 deg.F before entering the distribution chambers 276A and 276B. Cold air from distribution chambers 276A and 276B is injected into the vent chambers of edge wheel section 136 or ram jet thrust unit U (e.g., 142), respectively. The cool air in distribution chambers 276A and 276B is protected from leaking into working gap 250 by seals 280 and 282.

The vacuum in void 250 is maintained by a pump (not shown) through vacuum line ports 290 and 292 through 294 and 296.

The rotor design of the second embodiment is shown in figures 3, 5, 6 and 12. Here, a high strength carbon fiber rotor 120' is presented. The rotor 120 'has an inner mass with high strength and an output shaft 108'.

As shown in fig. 4, 5, 8, 11 and 12, i prefer to use a ventable film cooling surface, including the combustion chamber 216 of the ramjet U. Cooling air (preferably compressed air) is supplied to a plenum chamber, such as the chamber VC, of each section of the ram injector U. The plenum VC functions as a centrifugal compressor and compressed cool air is fed into the outlet 300 of the cooling passage holes 302. The cooling air passage holes 302 are desirably patterned with a high density, and the actual parameters depend on the characteristics of a given design, including velocity (Mach number), capacity, and other factors. In this manner, the ventable edge wheel section 138 and the ventable shroudless punch sprayer 142 have cooling air flow passages through their coolable plates 304. It is located between the plenum chambers VC and includes a cold inner surface CS and a hot outer surface HS at the radial ends of the edge wheel section 138 and the punch spray 142. Due to the swirl action of the side plates, the cooling air emerging from the outlets 300 of the holes 302 blows over the hot surfaces HSS of the side plates, performing the same cooling action. Note that cooling air arrows CA in fig. 8 indicate that the cooling air flow direction is out through the outlet 300. In actual operation, the cooling air CA encounters the high velocity gas stream 176, creating a very thin effective cooling film. Of course, one side of each side panel is in contact with the cool mixture inlet air 170. This film cooling method is important because it allows the use of materials such as titanium around the periphery of the combustion chamber. In this way, damage to the combustion chamber by the high temperatures generated during combustion and damage to other components by the hot exhaust gases can be avoided.

Cooling water CW flows through the outer cooling chamber CCO for cooling the circumferential plate 202 and its inner wall 204 and through the inner cooling chamber CCI for cooling the plate 198 and its wall 200.

A key feature of the present power generation apparatus is the rotor 120. The rotor rotates about the axis of rotation due to the propelling action of the ramjet U. Two design parameters of the rotor 120 are important. First, the rotor must be made of a material that can support the extremely high centrifugal loading effects to ensure that the ramjet can operate in the mach 3.5 range. I.e. the material is required to withstand extremely high tensile stresses. Secondly, at such speeds, it is important to minimize the overall aerodynamic drag of the rotor.

See also figures 16 and 17. The figure shows my power generation equipment and the necessary power generation equipment connected. The shaft portion 108 transfers mechanical energy to the primary gearbox 104 in the usual manner. The gearbox 104 reduces the speed of the shaft 108 to a lower speed of the shaft 110 to meet the needs of the application. In fig. 1, 16 and 17, the primary gearbox 104 is connected by a shaft 110 to a primary generator 112. The generator generates electrical energy that is delivered to a power grid or other electrical load. The shaft 110 may also be directly applied to do mechanical work.

To activate the power-generating device, a starter motor 400 is shown connected to the gear set 104. The motor 400 is used to rotate the rotor and bring the ram jet propulsion unit U to a suitable tangential speed in order to start the ram jet machine U. Once the ramjet U is started, the motor 400 is cut off.

Starting and adjusting the ramjet U can be accomplished by providing auxiliary fuel 500 through line 502 to an injection port 504. The fuel is ignited by a plasma igniter or other corresponding igniter to feed the ram injector U with a wing-like inlet flow. Once the pilot fuel supply activates the ramjet flame holder 214, fuel FF is introduced through the injection ports 236.

In fig. 13, 14 and 18, there are a series of ring gate valves in different positions around the edge of the circumferential wall 200. To start, the ring gate valve 600 is opened in the direction of arrow 602 in FIG. 14, creating an air gap 603. Thus, a portion of the incoming compressed air on the 200 surfaces will escape to the outside in the direction of arrows 604 and 606. This unique partial shroud ram ejector 162 allows bypass air 604 and 606 to escape. Because the ring punch jet U has a "swallowed" flow blocking configuration, the gate valve 600 may be closed by an actuator 610, as shown in fig. 13. I show a hydraulic actuator 610 having a shaft 612 that is mounted to a bracket 614 a. Any convenient mechanical, electrical or hydraulic actuator may be conveniently used for this purpose.

In the combined cycle system of fig. 16 and 17, the reuse of the combustion exhaust gas discharged from the ramjet U is given. As shown, the hot exhaust gas is easily collected by the exhaust gas conduit EXD. Exhaust gas line EXD is connected to a heat recovery steam generator HSRG. The steam generator HSRG heats the condensate coming out of the steam condenser SC via the condensate pump CP and generates steam to drive the steam turbine ST. In a common design, the working fluid is water. Water is not only most easily heated to produce high pressure steam for driving the steam engine, but also can be used for the supply of thermal energy in cogeneration applications. As shown, steam engine ST may also generate shaft power for rotating generator 112, or for coupling to another generator through gearbox 104'. In addition, steam engine ST may also generate shaft power for other purposes.

Since the thrust of the ramjet determines the overall output of the power generation plant, the thrust of the ramjet is an important indicator of the overall output of the power generation plant. The propulsion of the ramjet increases in proportion to the mass (fuel) obtained and carried out by the ramjet, as does the overall output of the power plant. Thus doubling the inlet area and the mass available doubles the thrust and thus doubles the power output of the system.

Finally, my design outputs very little NOx, even with very high combustion temperatures. This is because the residence time at high temperature of combustion is short and the fuel is well mixed. This choked boundary layer is unique in that it matches premixing technology to achieve near perfect premixing conditions and low NOx emissions. In this way, the nitrogen oxide emissions are limited by limiting the size of the unbalanced free base region in the combustion chamber. NOx emissions are estimated to be less than 5ppm, or EI less than 0.5 grams of nitrogen dioxide per kilogram of fuel.

As described above, the method and structure for generating mechanical, electrical or thermal energy provides a novel power generation plant. The device has the characteristics of improvement, compactness, easy manufacture and cost-effective. The output of the power-generating device can be used in conjunction with existing power transmission systems and represents a meaningful choice. This option reduces the emission of nitrogen oxide gases by completely burning the fuel. Furthermore, when the efficiency is constant, the fuel required to generate each unit of electrical, mechanical or thermal energy is greatly reduced.

It should be understood that the objects set forth above are apparent from the discussion, but that certain variations are permissible when the structures and methods of power generation as set forth herein are utilized in a particular manner. It will thus be appreciated that the present invention may be embodied in other specific forms without departing from the spirit or essential principles described herein. For example, I propose an exemplary design of a fuel feed process, and include other designs that achieve the device principles and use the methods herein.

All of the features disclosed herein (including any accompanying claims, drawings, and abstract), methods, or steps in a process may be combined in any combination, except combinations where mutually exclusive.

Each feature disclosed herein (including any accompanying claims, drawings, and abstract) can be replaced by alternative features serving the same or similar purpose, unless expressly stated otherwise. Thus, each feature disclosed herein is one example only of a generic series of equivalent or similar features unless expressly stated otherwise.

Therefore, it is to be understood that the foregoing description is only illustrative of the invention and is not to be construed as limiting the invention to the precise form 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 in the appended claims. For that reason, the claims are intended to cover all structures and methods described herein. Not only are equivalent or structural equivalents, but also equivalent structures or methods are encompassed. To this end, as set forth in the following claims, the invention extends to all alternative forms and modifications of the broad concepts expressed by the claims, or equivalents thereof.

Claims (68)

1. A power generation device, the device comprising:

(a) a mounting box including an air inlet and an exhaust outlet for intake of combustion air;

(b) a fuel inlet for supplying fuel to said device;

(c) a rotor, said rotor being rotatably secured to said mounting box, said rotor having an axis of rotation, said rotor extending outwardly from said axis of rotation to an outer surface portion;

(d) a circumferential wall, said circumferential wall

(1) Disposed along the axis of rotation between the combustion air inlet and the exhaust gas outlet,

(2) is disposed radially outwardly from the axis of rotation,

(3) is disposed radially outwardly from the outer layer surface portion of the rotor, and

(4) includes an inner circumferential wall surface portion;

(e) one or more ram jets, one said ram jet or said ram jets

(1) Each consisting of a shroudless compression section located at said outer surface portion of said rotor,

(2) said unshielded compression section co-compressing said inlet combustion air with at least one of said inner circumferential wall surface portions between one or more of said ramjets and said at least a portion of said inner circumferential wall surface portion,

(3) an operable velocity with respect to said inlet air of at least mach 1.5;

(f) one or more side plates, one for each ram jet, wherein each side plate extends generally radially outward from at least a portion of the outer peripheral wall surface portion of the rotor to a point adjacent the inner peripheral wall surface portion; one or more side plates operatively separating said exhaust gases from said inlet combustion air, wherein one or more of said ramjets receives inlet air and fuel thereto and oxidizes said fuel to create hot combustion gases; hot combustion gases are propellably exhausted from the one or more ramjets, creating a thrust force that causes the rotor to rotate.

2. The apparatus of claim 1 wherein each of said one or more side plates includes a helical formation extending substantially from said outer surface portion of said rotor.

3. The apparatus of claim 2 wherein the number N of one or more helical skirt is equal to the number N of one or more die sprayers.

4. The apparatus of claim 1, wherein said circumferential wall surface portion of said circumferential wall further comprises a wear-resistant seal for effectively sealing an interface between one or more of said side plates and said inner circumferential wall surface portion.

5. The apparatus of claim 1, wherein said outer surface portion of said rotor comprises a plurality of side lobes, said side lobes.

6. The apparatus of claim 5 wherein at least one of said side lobes is replaceably removable from said rotor.

7. The apparatus of claim 1, wherein one of said one or more ramjets further comprises a partially unshielded outlet nozzle, and wherein one of said one or more ramjets utilizes a portion of said inside circumferential wall surface portion for pressure reduction of the effluent gases.

8. The apparatus of claim 1 wherein said outer surface portion of said rotor further comprises at least one coolable wall having

(a) An inside stave surface, and

(b) an outer hot wall surface, and

(c) a plurality of cooling holes having outlets at the hot wall surface of the outer layer. The cooling holes provide a passageway between the inner cold wall surface and the outer hot wall surface,

(d) the cooling holes are adapted to provide a film of cooling air on the outer surface portion of the rotor by passing cooling air supplied to the inner stave surface therethrough such that the cooling air exits from the outlet.

9. The apparatus of claim 5 wherein each of said side lobes further comprises a cooling air receiving cavity, said mounting box further comprising a rotor face portion, said cooling air cavity effectively containing cooling air supplied thereto for metering outflow therefrom.

10. The apparatus of claim 1, further comprising an air dampening channel in communication with the inlet air plenum and an outlet air dampening arrangement, the air dampening channel configured to activate the one or more ram injectors, the air dampening channel defined by

(a) A through wall portion of the circumferential wall, and

(b) an indexing valve within said circumferential wall

(c) In which the air damping channel can be arranged between

(1) A closed sealing position where substantially no inlet air escapes from said air damping channel, an

(2) An open position where the plug valve is displaced from the through wall portion of the circumferential wall, a gap being formed between the through wall portion and the indexing valve allowing at least a portion of the inlet air to spill through the air damping passage,

(d) thereby allowing combustion to begin at the one or more ramjets.

11. The apparatus of claim 10 wherein said indexing valve comprises a ring gate valve operatively mounted along at least a portion of the periphery of said mounting box where said ring gate valve is mounted immediately radially outward of said one or more ramjets, said ring gate valve being movable when said one or more ramjets are rotated thereby from (a) an open position where a portion of the air flow ahead of said one or more ramjets can escape through said valve without being compressed by said one or more ramjets when said one or more ramjets are rotated immediately therebeneath to (b) a closed position where substantially no air flow escapes therethrough.

12. An apparatus for generating power comprising

(a) A support structure, said support structure comprising

(1) An oxidant supply conduit, and

(2) a first mounting box portion with a rotor edge surface, and

(3) a second mounting box portion with a rotor rim surface;

(b) a first output shaft, said first output shaft being safely rotatable in view of said support structure;

(c) a rotor, said rotor comprising an outer surface portion;

(d) one or more ram jet propulsion units, one or more ram jet propulsion units

(1) Each provided integrally by said outer surface portion of said rotor for rotation,

(2) each further comprising a shroudless outer portion comprising a substantially constant cross-sectional size, as viewed sequentially from a front cross-section to a rear cross-section with a cross-section perpendicular to the inlet airflow, whereby when the one or more ram jet propulsion units are operated at an inlet airflow velocity M of at least Mach 1.5₀When the pressure is reduced, the minimum pressure resistance is obtained, and

(3) each cooperating with at least a portion of said rotor rim surface of said second mounting box portion for compressing said inlet combustion air between one or more said ramjets and at least a portion of said rotor rim surface;

(e) one or more side plates, each side plate corresponding to a ramjet propulsion unit, wherein each of said one or more side plates extends generally radially outward from at least a portion of said outer surface portion of said rotor to a point proximate said rotor edge surface, one of said one or more side plates being effective to separate said inlet combustion air from said exhaust gas, wherein one of said one or more ramjets receives inlet air and fuel thereto and oxidizes said fuel to create hot combustion gases which are propulsively exhausted from one of said one or more ramjets to create a thrust force that causes said rotor to rotate.

13. The apparatus for generating electrical power of claim 12, further comprising a heat recovery section arranged to receive hot combustion gases from one or more ram jet propulsion units; the heat recovery section further comprises an inlet, an outlet and an auxiliary working fluid which circulates in and out of the heat recovery section, whereby the hot combustion gases are cooled by heat exchange and the recovered heat is transferred to the auxiliary working fluid.

13. The power-generation apparatus of claim 13, wherein the auxiliary working fluid is used to provide thermal energy.

14. The apparatus of claim 13, wherein the secondary working fluid is comprised of water, and wherein the heating of the secondary working fluid produces steam.

15. The apparatus of claim 14, further comprising a steam turbine, said steam obtained from the heating of said water being pressurized and fed to said steam turbine to produce useful work on an output shaft of the steam turbine.

16. The apparatus of claim 12 wherein said first output shaft is operatively connected to a first electrical generator, said first output shaft providing said mechanical work thereon, which shaft rotates said first electrical generator to generate electricity.

17. The apparatus of claim 15 wherein said steam turbine output shaft is operatively connected to a first electrical generator, said mechanical work being provided on said steam turbine output shaft which rotates said first electrical generator to generate electricity.

18. The apparatus of claim 16 further comprising a second electrical generator, said steam turbine output shaft producing said shaft work which rotates said second electrical generator to produce electricity.

19. The apparatus of claim 12, wherein the apparatus produces shaft power at an inlet speed of at least mach 3 with a simple cycle efficiency of at least thirty-seven percent based on the ratio of mechanical energy output to fuel energy input.

20. The apparatus of claim 12, wherein the apparatus produces shaft power at an inlet speed of at least mach 3.5 with a simple cycle efficiency of at least about forty-five percent based on a ratio of mechanical energy output to fuel energy input.

21. The apparatus of claim 12, wherein the apparatus produces shaft power at an inlet speed of at least mach 4 with a simple cycle efficiency of at least about fifty-two percent based on a ratio of mechanical energy output to fuel energy input.

22. The apparatus of claim 1 or claim 12 wherein at least one of the materials comprising said rotor has a specific strength in excess of 683,220 inches.

23. The apparatus of claim 1 or claim 12 wherein at least one of the materials comprising said rotor has a specific strength of between 683,220 inches and 1,300,250 inches.

24. The apparatus of claim 1 or claim 12, wherein at least a portion of the material comprising the rotor has a specific strength of about 1,300,250 inches.

25. The apparatus of claim 1 or claim 12 wherein at least a portion of the material comprising the rotor has a specific strength in excess of 1,300,250 inches.

26. The apparatus of claim 1 or claim 12, wherein at least a portion of material comprising the rotor has a specific strength in a range of about 1,300,250 inches and about 3,752,600 inches.

27. The apparatus of claim 1 or claim 12, wherein at least a portion of the material comprising the rotor has a specific strength of about 3,752,600 inches.

28. The apparatus of claim 1 or claim 12 wherein at least a portion of the material comprising the rotor has a specific strength in excess of 3,752,600 inches.

29. The apparatus of claim 1 or claim 12, wherein at least one of the materials comprising the rotor has a specific strength between 3,752,600 inches and 15,000,000 inches.

30. The apparatus of claim 1 or claim 12, wherein at least a portion of the material comprising the rotor has a specific strength of about 15,000,000 inches.

31. Apparatus according to claim 1 or claim 12, wherein at least one of the ramjets operates at an inlet speed M₀Between mach 1.5 and mach 2.0.

32. Apparatus according to claim 1 or claim 12, wherein at least one of the ramjets operates at an inlet speed M₀At least 2.0 mach number.

33. Apparatus according to claim 1 or claim 12, wherein at least one of the ramjets operates at an inlet speed M₀At least 2.5 mach number.

34. Apparatus according to claim 1 or claim 12, wherein at least one of the ramjets operates at an inlet speed M₀At least a mach number of 3.0.

35. Apparatus according to claim 1 or claim 12, wherein at least one of the ramjets operates at an inlet speed M₀Between mach 3.0 and mach 4.5.

36. Apparatus according to claim 1 or claim 12, wherein at least one of the ramjets operates at an inlet speed M₀Approximately mach 3.5.

37. Apparatus according to claim 1 or claim 12, wherein the rotor comprises a central disc.

38. The apparatus of claim 37 wherein said central disk axis tapers radially outwardly.

39. The apparatus of claim 1 or claim 12 wherein said rotor is formed from a metal mold assembly.

40. The apparatus of claim 39, wherein the metal mold assembly is comprised of titanium.

41. The apparatus of claim 39, wherein said rotor is comprised of silicon carbide.

42. The apparatus of claim 1 or claim 12, wherein the rotor is constructed of carbon fiber coated silicon carbide embedded titanium metal substrate.

43. The apparatus of claim 1 or claim 12, wherein the rotor is formed from a carbon fiber epoxy composite.

44. The apparatus of claim 43, wherein said rotor is formed from high strength fiber coils.

45. The device of claim 44, wherein said high strength fiber coil is comprised of monofilament carbon fiber.

46. The device of claim 44, wherein said high tenacity fibrous loops are comprised of Kevlar (Kevlar) fibers.

47. The apparatus of claim 39, wherein the metal mold assembly is comprised of silicon carbide filaments.

48. The apparatus of claim 1 or claim 12, wherein one or more of the ramjets further comprises a silicon carbide combustion chamber.

49. The apparatus of claim 48, wherein the silicon carbide combustion chamber is further defined by a monolithic silicon carbide segment.

50. The apparatus of claim 1 or claim 12, wherein one or more of said ramjets comprises a replaceable combustion chamber insert.

51. A method for generating power, comprising:

(a) providing one or more unshrouded rotatable propulsion unit shields between the first inner mounting box and the second outer mounting box;

(b) supplying an oxidizable fuel to the one or more shroudless thrust units;

(c) oxidizing said fuel in one or more of said unshrouded thrust units for

(1) Generating gas and overflowing therefrom and serving

(2) Generating a motive force generated by a propulsion reaction of said overflowed fuel gas to (A) said one or more unshrouded thrust units, and (B) said second externally mounted cartridge

(d) Propelling one or more of said shroudless thrust units at a speed in excess of mach 1 by supplying an incoming air stream as a motive force, said thrust units further characterized by: the thrust unit being at least partially shrouded in a configuration wherein said thrust unit is dependent upon at least a portion of a second mounting box to assist in compressing a portion of said incoming supply of air when said thrust unit is in close proximity to said mounting box;

(e) rotating an output shaft operatively connected to one of the one or more thrust units;

(f) whereby power is provided to the output shaft.

52. The method of claim 51, wherein the speed of the one or more thrust units is at least Mach 3.0.

53. The method of claim 51, wherein the speed of the one or more thrust units is between Mach 3.0 and Mach 4.5.

54. The method of claim 51, wherein the one or more thrust units are operated at a speed approximately at Mach 3.5.

55. The method of claim 51, wherein said fuel is selected from the group consisting of gaseous hydrocarbon fuels.

56. The method of claim 55, wherein said fuel is substantially natural gas.

57. The method of claim 51, wherein the step of supplying fuel includes injecting fuel into the air stream at a point between said first and said second mounting boxes upstream of said one or more ramjets.

58. The method of claim 51, further comprising generating electricity.

59. The method of claim 58, further comprising recovering heat energy from said combustion gases.

60. The method of claim 59, wherein said heat energy recovery step comprises transferring heat energy from said combustion gas to an auxiliary working fluid.

61. The method of claim 60, wherein said secondary working fluid is water, and wherein heating said water produces steam.

62. The method of claim 60, wherein said thermal energy recovery step comprises indirectly heating said water with said combustion gases in a heat recovery annulus.

63. The method of claim 61, further comprising directing said steam to a steam turbine, said steam powering said steam turbine to produce shaft work.

64. The method of claim 63, further comprising generating electricity from said shaft work of said steam turbine.

65. The method of claim 51, further comprising controlling boundary layer drag while said rotor rotates at supersonic speeds.

66. The method of claim 65, wherein said substantially controlling boundary layer drag further comprises maintaining a partial vacuum along at least a portion of a radius of said rotor.

67. The method of claim 65, further comprising providing said supplied air flow at a rate sufficient to: sufficient to provide internal cooling to the petal rotor caps.