Rotary engine, components thereof, and methods

Abstract

A rotary engine, components thereof, and related methods are provided. The engine is modular and adjustable to accommodate various requirements and preferences. The system includes a combustion assembly having a housing and a power rotor positioned therein. The power rotor rotates in a first direction from the start of each combustion process to the end of each exhaust process. The system also includes a compression assembly coupled to the combustion assembly such that the compression rotor rotates in the first direction from the start of each intake process to the end of each compression process. A tank assembly in fluid communication with the compression assembly and the combustion assembly provides stability to the system and eliminates or reduces transient losses.

Description

[Technical Field]

[0001] CROSS-REFERENCE TO RELATED APPLICATIONS This application claims priority pursuant to 35 U.S.C. 119(e) to U.S. Provisional Patent Application No. 62 / 884,771, filed August 9, 2019, and U.S. Provisional Patent Application No. 62 / 894,567, filed August 30, 2019, the entire disclosures of which are incorporated herein by reference. This application also claims priority to U.S. Patent Application No. 16 / 732,318, filed January 1, 2020, the entire disclosure of which is incorporated herein by reference.

[0002] The present invention relates generally to engines, and more particularly to rotary engines, components thereof, and related methods. [Background technology]

[0003] Most existing internal combustion engines fall into two major categories: gas turbine engines and reciprocating engines, each with its own advantages and disadvantages. For example, gas turbine engines have a very high power-to-weight ratio when compared to reciprocating engines. Gas turbine engines also tend to be smaller in size than equivalently powered reciprocating engines. Due to these advantages, the aircraft industry has moved almost exclusively to the use of gas turbine engines (except for small aircraft applications). Reciprocating engines, on the other hand, tend to be more fuel-efficient and more responsive to changes in power settings. Reciprocating engines also tend to be less expensive than equivalently powered gas turbine engines. Due to these advantages, the automotive industry has moved almost exclusively to the use of reciprocating engines. While there are many differences between gas turbine and reciprocating engines, each relies on the expansion of fluids associated with the combustion process.

[0004] Gas turbine engines, such as "jet" engines, utilize the combustion of an energy-rich fuel to generate thermal energy, which is then utilized to power a turbine. More specifically, the thermal energy from the combustion process is utilized to heat a quantity of working fluid, thereby causing the working fluid to expand. The expanding working fluid is channeled through the blades of the turbine, thereby causing the turbine to rotate. The rotation of the turbine can be utilized in a variety of ways, depending on the particular application of the gas turbine.

[0005] U.S. Pat. No. 2,168,726, the entire disclosure of which is incorporated herein by reference, teaches a "turbojet" having a turbine that powers a compressor. The compressor draws a fluid (air) flow into the front of the turbojet and expels the fluid from the rear, thereby generating thrust. A portion of the compressed fluid flow is diverted to a combustion chamber to enable the combustion process and serve as the working fluid during the subsequent expansion process. After expanding through the turbine, thereby powering the compressor, the working fluid recombines with the main flow. The result is high-velocity exhaust gases ("jet thrust").

[0006] U.S. Patent Nos. 2,478,206 ("Redding"), 2,504,414 ("Hawthorne"), 2,505,660 ("Baumann"), 2,526,409 ("Price"), 2,526,941 ("Fishbein"), 2,541,098 ("Redding"), 2,702,985 ("Howell"), and 3,153,907 ("Griffith"), the entire disclosures of each of which are incorporated herein by reference, teach various configurations of "turboprops." Generally speaking, turboprops are similar to turbojets, except that turboprops utilize a majority of the fluid flow to drive a propeller, thus providing reduced jet thrust compared to that of a turbojet. In a similar manner, turboshafts (such as those used to power helicopter rotors or generators) utilize even more fluid flow, thereby further reducing or eliminating jet thrust. Conversely, "turbofans" (high or low bypass) utilize fluid flow to drive large fans for the purpose of increasing or otherwise modifying jet thrust.

[0007] Reciprocating engines also use the combustion of energy-rich fuels to generate heat energy, but this energy is used to expand a combustion chamber rather than power a turbine. As the combustion chamber expands, the piston is driven linearly from its top dead center position to its bottom dead center position. At some point, depending on the engine's configuration, the expanding gases are expelled from the cylinder, allowing more fuel and air (the "charge") to be drawn into the chamber for the subsequent combustion process. While reciprocating engines can utilize external compression sources (such as superchargers or turbochargers), compression is typically achieved by moving the piston from bottom dead center to top dead center before combustion. In this way, the piston shuttles between bottom dead center and top dead center, giving the engine its name.

[0008] The reciprocating action of a reciprocating engine increases costs and maintenance due to its complex mechanical motion (as opposed to the relatively simple rotation of a turbine), but its combustion chamber is exposed to only intermittent periods of combustion, thereby allowing the combustion chamber to cool and / or prevent it from overheating. Conversely, gas turbine engines utilize continuous combustion (the combustion chamber of a gas turbine engine is sometimes referred to as a "burner") and often require expensive materials and regular maintenance to enable the engine to withstand high temperatures for extended periods. Therefore, it would be beneficial to have a system and method for enabling intermittent combustion without the need for complex mechanical motion.

[0009] Gas turbine engines operate using the Brayton cycle, a constant-pressure cycle requiring a compressor, a burner (combustion chamber), and an expansion turbine. The efficiency of the Brayton cycle is highly dependent on the pressure in the combustion chamber relative to the ambient pressure. Reciprocating engines, on the other hand, typically operate using the Otto cycle or the Diesel cycle, each with a similarly high dependence on compression ratio.

[0010] U.S. Pat. No. 367,496 ("Atkins"), the entire disclosure of which is incorporated herein by reference, teaches a reciprocating engine having an expansion ratio greater than its compression ratio, thereby utilizing a thermodynamic cycle now known as the Atkinson cycle (Atkins found that a 2:1 ratio "gave good results"). The Atkinson cycle offers improved fuel economy over comparable Otto cycle engines, but suffers from a loss of power at low speeds. U.S. Pat. No. 2,817,322 ("Miller"), the entire disclosure of which is incorporated herein by reference, teaches a supercharged engine that "rejects air from the cylinder" (e.g., by leaving a valve open during the first portion of the compression stroke) during the compression stroke so that "substantially less air than the cylinder's total volumetric capacity is trapped" during combustion. In this way, the Miller cycle obtains an expansion ratio greater than the compression ratio, similar to the Atkinson cycle, but without (or with little) power loss at low speeds. Unfortunately, the Miller cycle still suffers from inefficiencies, such as the general inefficiencies of reciprocating engines and the specific inefficiencies associated with the Miller cycle's substantially extended intake stroke. Therefore, it would be beneficial to have a system and method for maximizing the efficiency of internal combustion engines. Summary of the Invention

[0011] The present invention includes a system and method for maximizing the efficiency of an internal combustion engine while minimizing its cost and weight and while minimizing its maintenance requirements. The system includes a compression assembly for compressing a fluid to the pressure required for combustion (e.g., greater than 220 psi) and a tank assembly for holding a large volume of compressed fluid. The combustion assembly of the present invention is configured to receive a small portion of the compressed volume of air for each power stroke. In this manner, the engine's power stroke is independent of the engine's compression stroke, thereby eliminating or otherwise minimizing transition losses associated therewith.

[0012] Unlike gas turbines that utilize the Brayton cycle, the present invention utilizes a cycle (the "Riley cycle") that does not require continuous combustion to rotate the turbine. Instead, the Riley cycle allows for intermittent combustion in conjunction with maintaining continuous rotational motion without the need for reciprocating motion. In this way, the Riley cycle achieves the benefits of a reciprocating engine with the benefits of a gas turbine engine.

[0013] Unlike reciprocating engines using the Otto and Diesel cycles, the present invention does not require alternating expansion strokes with compression strokes. Instead, the Riley cycle allows for repeated expansion strokes, with each expansion stroke associated with a partial rotation of the power rotor. In this way, engines utilizing the Riley cycle are easier to manufacture, more fuel efficient, and require less maintenance.

[0014] Like the Atkinson cycle, the Riley cycle can maximize the expansion ratio of a fuel. However, unlike the Atkinson cycle, the Riley cycle does not require complex reciprocating components. Instead, the Riley cycle can maximize the expansion rate by controlling the length of time the inlet valve is open, thereby controlling the size of the charge. In this way, the Riley cycle provides users with the flexibility to use alternative fuels and / or change fuels as and when needed and / or desired.

[0015] Similar to engines using the Miller cycle, the present invention controls the efficiency of the system by controlling the time the inlet valve remains open. However, the Miller cycle achieves this advantage by maintaining the inlet valve in an open position while the compression chamber contracts. In other words, the Miller cycle achieves its efficiency by expelling a portion of the charge from the combustion chamber before compressing it. This approach necessarily requires that the expelled portion of the charge be first drawn into the chamber before being expelled from the chamber. The Riley cycle does not require any portion of the charge to be expelled. Instead, the Riley cycle increases efficiency by controlling the initial size of the charge (by controlling when the inlet valve opens, and thus the duration the inlet valve is open), thereby eliminating the need to expel some of the charge.

[0016] The combustion assembly of the present invention includes a power rotor having a first blade. When a first charge is ignited adjacent to the first blade, the first blade is forced toward an exhaust port, thereby driving the power rotor. The combustion assembly is configured such that movement of the first blade toward the exhaust port maximizes usable energy (expansion) from the first charge. As the first blade passes the exhaust port, expanded fluid from the first charge is expelled from the exhaust port. In some embodiments, the power rotor includes multiple blades, including a second blade configured to expel the first charge through the exhaust port, such as following ignition of a second charge. In some embodiments, the first blade is configured to expel the first charge through the exhaust port, such as following ignition of the second charge.

[0017] The combustion assembly of the present invention further includes a first isolator rotor positioned aft of the ignition point and configured to prevent or otherwise inhibit expansion of the charge away from the respective blades. In some embodiments, the first isolator rotor is positioned immediately ahead of the exhaust port to prevent exhaust gases from bypassing the exhaust port. In some embodiments, the combustion assembly includes multiple isolator rotors, including a second isolator rotor positioned immediately ahead of the exhaust port to prevent exhaust gases from bypassing the exhaust port. Each isolator rotor includes at least one receptacle for receiving one or more blades of the power rotor, thereby allowing the power rotor to rotate past the isolator rotor. In this manner, the combustion assembly can perform continuously repeating power strokes while simultaneously skipping one or more power strokes as and when needed and / or desired.

[0018] The present invention improves upon and / or incorporates existing technology. In some embodiments, the engine is capable of idling at 2,500 revolutions per minute. In some embodiments, the engine has a linear power and torque curve. In some embodiments, the engine overspeeds at 30,000 revolutions per minute or more. In some embodiments, the engine facilitates independent control over cycle-by-cycle injection. In some embodiments, parasitic losses are dramatically reduced over existing technology. In some embodiments, the engine is capable of stratified injection and ignition. In some embodiments, the engine avoids problems associated with shuttling probability. In some embodiments, the engine avoids problems associated with compressor stall. In some embodiments, the engine avoids problems associated with sealing. In some embodiments, the engine facilitates pre-chamber combustion. In some embodiments, the engine includes on-the-fly adaptive compression ratio functionality, on-the-fly altitude compensation functionality, and / or on-the-fly adaptive fuel technology. In some embodiments, the engine is air-cooled. In some embodiments, the engine's thermal signature is virtually nonexistent. In some embodiments, the engine provides an improved power-to-weight ratio and / or improved emissions when compared to existing technology. In some embodiments, the engine operates with substantially no NOx emissions.

[0019] The foregoing and other objects are intended to be illustrative of the present invention and are not meant to be limiting. Many possible embodiments of the present invention are possible and will become readily apparent from a review of the following specification and the accompanying drawings, which form a part thereof. Various features and subcombinations of the invention may be employed without reference to other features and subcombinations. Other objects and advantages of the present invention will become apparent from the following description taken in conjunction with the accompanying drawings, which illustrate, by way of illustration and example, embodiments of the invention and various features thereof. [Brief explanation of the drawings]

[0020] Preferred embodiments of the invention, which illustrate the best mode contemplated by applicants for applying the principles thereof, are set forth in the following description, shown in the drawings, particularly and distinctly pointed out and pointed out in the appended claims.

[0021] [Figure 1] 1 is a cross-sectional schematic view of one embodiment of the present invention having a tank assembly positioned between a compression assembly and a combustion assembly, the embodiment shown not including an impeller. [Figure 2] FIG. 1 is a schematic diagram of one embodiment of the present invention having a compression assembly positioned directly adjacent to a combustion assembly, the embodiment shown having an exhaust system that extends in the direction of fluid flow around the engine. [Figure 3] 1 is a schematic diagram of an embodiment of a compression assembly having a relief valve and an outlet valve, the relief valve in a closed configuration and the outlet valve in an open configuration. [Figure 4] 1 is a schematic diagram of an embodiment of a compression assembly having a relief valve and an outlet valve, the relief valve in an open configuration and the outlet valve in a closed configuration. [Figure 5] 1 is a schematic diagram of an embodiment of a combustion assembly showing an exhaust system having multiple exhaust branches and an exhaust valve for controlling which branch exhaust is discharged, the exhaust valve being in a first configuration for discharging the combustion exhaust through a catalytic converter. [Figure 6] FIG. 1 is a schematic diagram of an embodiment of a combustion assembly showing an exhaust system having multiple exhaust branches and an exhaust valve for controlling which branch exhaust is discharged, the exhaust valve being in a second configuration for discharging unburned exhaust so that it does not pass through a catalytic converter and be discharged. [Figure 7] 1 is a cross-sectional view of a compression assembly of the present invention, a particular embodiment of a combustion assembly having substantially the same configuration. [Figure 8] 1 is an end view of a compression rotor of the present invention, a particular embodiment of a power rotor having substantially the same configuration. [Figure 9] FIG. 1 is an end view of the isolator of the present invention. [Figure 10] 1 is a cross-sectional view of a compression housing of the present invention, a particular embodiment of a combustion housing having substantially the same configuration. [Figure 11] FIG. 2 is an end view of the rotary valve of the present invention. [Figure 12] FIG. 2 is a cross-sectional view of the compression assembly of the present invention, the compression assembly being shown prior to the first intake stroke. [Figure 13-16] Each shows the same cross-sectional view as FIG. 12 at a different time during the first intake stroke. [Figure 17-20] 12 at different times during the first compression stroke. [Figure 21] 1 is a cross-sectional view of a combustion assembly of the present invention, the combustion assembly being shown prior to the first power stroke; [Figure 22-25] Each shows the same cross section as FIG. 21 at a different time during the first power stroke. [Figure 26-29] Each shows the same cross section as FIG. 21 at a different time during the first exhaust stroke. [Figure 30-31] Each shows a cross-sectional view of a compression assembly of the present invention, and a particular embodiment of a combustion assembly having substantially the same configuration. [Figure 32-33] Each shows a cross-sectional view of a compression assembly of the present invention, and a particular embodiment of a combustion assembly having substantially the same configuration. [Figure 34] 1 shows a cross-sectional view of a compression assembly of the present invention. [Figure 35] 1 is a cross-sectional schematic view of one embodiment of the present invention having opposed forward and aft fan assemblies and a shroud extending therebetween; [Figure 36] 1 is a cross-sectional schematic view of one embodiment of the present invention having an aft fan assembly and a shroud extending therefrom; [Figure 37]1 is a cross-sectional schematic view of one embodiment of the present invention having a forward fan assembly and a shroud extending therefrom; [Figure 38] 38 shows a cross-sectional view of one embodiment of the system of FIG. 35, FIG. 36, or FIG. 37. [Figure 39] 38 shows a cross-sectional view of one embodiment of the system of FIG. 35, FIG. 36, or FIG. 37. [Figure 40] FIG. 1 is an isometric view of one embodiment of an engine assembly of the present invention. [Figure 41] FIG. 41 is a top view of the engine assembly of FIG. [Figure 42] FIG. 41 is a front view of the engine assembly of FIG. [Figure 43] 43 is an isometric cross-sectional view of the engine assembly of FIG. 40, the engine assembly being cut along line 43-43 of FIG. 41. [Figure 44] 44 is a top cross-sectional view of the engine assembly of FIG. 40, the engine assembly being cut along line 44-44 of FIG. 42. [Figure 45] 45 is a side cross-sectional view of the engine assembly of FIG. 40, with the engine assembly cut along line 45-45 of FIG. 42 and the fan assembly removed for clarity. [Figure 46-53] 1 is an exploded perspective view of the engine of the present invention, with certain components identified from each view for clarity; [Figure 54] FIG. 54 is a perspective view of the engine of FIGS. [Figure 55] FIG. 1 is a perspective view of the engine of the present invention, with the combustion housing, tank housing, compression housing, and gear housing shown in transparent form to facilitate visualization of the components located therein. [Figure 56] FIG. 1 illustrates an isometric cross-sectional view of one embodiment of the present invention. [Figure 57] FIG. 57 is a top view of the embodiment of FIG. 56. [Figure 58] FIG. 57 is a top cross-sectional view of the embodiment of FIG. 56. [Figure 59]FIG. 2 is a partial view of a compression assembly of one embodiment of the present invention, shown in a closed configuration during a first compression stroke. [Figure 60-61] Each shows a partial view of the compression assembly of FIG. 14A with a portion of the outlet port shown in fluid communication with the void created by the receptacle of the isolator rotor of the compression assembly, with the compression assembly remaining in a closed configuration in each view. [Figure 62-64] Each shows a partial view of the compression assembly of FIG. 59, with the compression assembly in an open configuration in each view. [Figure 65] FIG. 60 is a partial view of the compression assembly of FIG. 59, with the compression assembly in a closed configuration at the end of the first compression stroke. [Figure 66] FIG. 60 is a partial view of the compression assembly of FIG. 59, shown at the beginning of the second compression stroke. [Figure 67] 1 is a cross-sectional view of one embodiment of the present invention, showing the intake port in an open configuration. [Figure 68-72] 1A-1C are partially translucent views of combustion housings of various embodiments of the present invention, the housings defining an ignition chamber and an ignition tunnel. [Figure 73] FIG. 1 is an isometric view of a tank housing having a support ledge according to one embodiment of the present invention. [Figure 74] FIG. 74 is an isometric cross-sectional view of the tank housing of FIG. [Figure 75] FIG. 74 is an isometric view of a rotary valve according to an embodiment of the present invention, the rotary valve configured to mate with the tank housing of FIG. 73. [Figure 76] FIG. 76 is an isometric cross-sectional view of the rotary valve of FIG. [Figure 77] 1 shows a rotor with a recessed area on the inner diameter. [Figure 78] 1 shows a portion of a housing having a recessed area on the inner diameter. [Figure 79]77 positioned within the housing of FIG. 78, with the recessed areas aligned and the vent system in fluid communication therewith. [Figure 80] 1 shows a rotor with a recessed area near the inner diameter. [Figure 81] 1 shows a portion of a housing having a recessed area near the inner diameter. [Figure 82] 80 positioned within the housing of FIG. 81 with the recessed areas aligned and the vent system in fluid communication therewith. [Figure 83] FIG. 1 is a partially translucent view illustrating one embodiment of the present invention having three fuel injectors, each associated with one of a compression assembly, a tank assembly, and a combustion assembly to facilitate injection of fuel into each. DETAILED DESCRIPTION OF THE INVENTION

[0022] Where necessary, detailed embodiments of the present invention are disclosed herein. However, it should be understood that the disclosed embodiments are merely illustrative of the principles of the present invention, which may be embodied in various forms. Therefore, the specific structural and functional details disclosed herein should not be construed as limiting, but merely as a basis for the claims and as a representative basis for teaching those skilled in the art how to variously use the present invention in virtually any appropriately detailed structure.

[0023] 1-2 , certain embodiments of the present invention include an internal combustion engine 10 capable of generating jet propulsion 14. In some embodiments, at least a portion of the jet propulsion is generated by an impeller 13 configured to draw a fluid flow (“bypass fluid”) 12 through one or more drive shafts 20, synchronous shafts 30, etc. In some embodiments, one or more shafts extend through the engine such that thermal energy from the engine is transferred to the bypass fluid, thereby cooling the engine. In some embodiments, the engine includes and / or is associated with one or more other cooling means (in addition to and / or instead of the aforementioned air-cooling systems), such as a water-cooling system, a heat sink system, a separate air-cooling system, etc. In some embodiments, the present invention can include and / or operate an afterburner system 500, such as a now-known or later-developed system.

[0024] The engine 10 of the present invention includes a compression assembly 100 for compressing a compressible fluid (“air”) from a first pressure (“inlet pressure”) to a second pressure (“outlet pressure”). The inlet pressure may be ambient air pressure, although it will be understood that the inlet pressure may be higher or lower than ambient air pressure. Additionally, some embodiments of the present invention are configured to supplement or replace the compression assembly 100 with one or more other compression means, now known or later developed, such as a compression turbine, a centrifugal compressor, etc. In some embodiments, the system includes and / or is associated with one or more turbochargers, superchargers, etc.

[0025] 7-10 , the compression assembly 100 includes a compression housing 110 and a compression rotor 120 positioned therein. The compression housing 110 defines an inner surface 112, and the compression rotor 120 defines a corresponding outer surface 122 displaced therefrom to define at least one compression chamber 115, with the compression assembly positioned therebetween. In some embodiments, the compression housing 110 includes a compression shroud 113 positioned between a first compression plate 114 and a second compression plate 116. In some embodiments, the first compression plate 114 is parallel to the second compression plate 116. In some embodiments, the compression housing 110 defines one or more inlet ports 111 and / or one or more outlet ports 119, e.g., one or more ports defined by the compression shroud 113 and / or one or more compression plates. In some embodiments, the inlet ports are in fluid communication with a breather system, such as a now-known or later-developed breather system.

[0026] 40-45, some embodiments of the present invention include a breather system 70 having one or more air scoops 72 for directing air or other fluids to a compression assembly 100. In some embodiments, each air scoop 72 includes a forward portion configured to receive a quantity of air and direct it into a tubing system in fluid communication with the compression assembly. In some embodiments, the air scoops 72 further include an aft portion extending beyond the tubing system to allow excess fluid and / or debris to exit the air scoop, thereby preventing or otherwise inhibiting it from entering the tubing system. In some embodiments, the air scoops 72 extend from an exterior surface of the engine shroud 60, such as a cowl, nacelle, or the like.

[0027] In some embodiments, a forward portion of the air scoop 72 defines a first cross-section and at least a portion of a second portion defines a second cross-section that is smaller than the first cross-section, thereby increasing fluid flow into the tubing system. In some embodiments, the tubing system includes a circumferential tube 74 that extends at least partially around the circumference of the engine shroud 60. In some embodiments, the tubing system includes at least one radial tube 75 that extends between the engine shroud 60 and the compression assembly 100. In some embodiments, the one or more radial tubes 75 provide structural support to hold the internal combustion engine 10 in place relative to the engine shroud 60.

[0028] In some embodiments, a fan assembly is positioned at least partially within a shroud 60, such as a fan blade assembly including a plurality of fan blades 62 extending from a fan hub 65. In some embodiments, the fan hub 65 defines an open center section configured to direct air toward the engine, for example, toward the engine's impeller 13, the interior volume of one or more shafts of the engine, etc. In some embodiments, the inner surface of the fan hub defines a curved slope such that a first cross-sectional area at the distal end of the fan hub (i.e., the forward end of the hub) is greater than a second cross-sectional area displaced from the distal end of the fan hub (i.e., the aft end of the hub and / or the region between the aft and forward ends of the hub). In this manner, the fan hub can compress air as it is directed toward the impeller, shaft, or other features of the engine (i.e., ram induction, etc.).

[0029] Referring again to Figures 7-10, the compression rotor 120 includes compression members 125, such as fins, blades, etc., that extend from an outer surface 122 of the compression rotor 120 toward the inner surface 112 of the compression housing 110, thereby defining a first end of a compression section of the chamber 115. The compression rotor 120 further includes an expansion member that defines a second end of an intake section of the compression chamber 115. It will be appreciated that in some embodiments, one or more compression members 125 of the compression rotor 120 also function as an expansion member, such that each compression member 125 separates a compression section from an adjacent intake section. In some embodiments, the housing 110 and the compression rotor 120 are configured such that a small gap exists between the inner surface 112 of the compression housing 110 and the distal end of the compression member 125 (and / or expansion member, if applicable). The small gap is designed to provide clearance while minimizing airflow between adjacent compression and intake sections. It will be appreciated that as the compression rotor rotates within the compression housing, certain sections of the compression chamber 115 alternate between being part of the intake section and being the compression section.

[0030] As the compression rotor 120 rotates during the intake stroke, the expansion members move away from their respective inlet ports 111 such that the volume of the intake section of the compression chamber 115 increases, thereby increasing the amount of fluid therein. In some embodiments, the inlet ports 111 are located at or near a first end of the intake section of the compression chamber. It will be appreciated that each intake stroke of an intake section can occur simultaneously with the compression stroke of an adjacent compression section.

[0031] As the compression rotor 120 rotates during the compression stroke, the compression members move toward their respective outlet ports 119 such that the volume of the compression section of the compression chamber 115 decreases, thereby increasing the pressure therein. In some embodiments, the outlet ports 119 are located at or near the second end of the compression section of the compression chamber. In some embodiments, the outlet ports are movable between open and closed configurations (e.g., via outlet valves 150, see FIG. 3 ), thereby preventing or otherwise inhibiting fluid from moving out of the compression section until the compression stroke is complete. In some embodiments, the outlet valves 150 are slide valves, ball valves, rotary valves, or any other electrical, mechanical, hydraulic, and / or other (now known or later developed) mechanisms and / or means, alone or in combination with one or more of the same.

[0032] In some embodiments, the compression assembly 100 includes one or more relief valves 160 for eliminating or otherwise reducing pressure buildup during the compression stroke, such as by selectively opening and closing relief ports 169 defined by the compression housing. In this manner, the system is configured to selectively eliminate or otherwise reduce power requirements associated with compressing the fluid when additional fluid compression is not required. In some embodiments, the relief ports 169 are positioned toward the second end of the compression section of the chamber, such as at or near the outlet port 119. In some embodiments, opening the relief port places the relief port in fluid communication with the atmosphere, thereby allowing excess pressure to be vented to the atmosphere. In some embodiments, opening the relief port places the relief port in fluid communication with a holding vessel, such as a low-pressure holding vessel, thereby facilitating fluid storage. In some embodiments, the compression assembly includes multiple relief ports and / or relief valves.

[0033] 3 and 4 , some embodiments of the present invention, such as those discussed below when one or more rotors are utilized to effectively open and close the outlet port, include at least one relief port 169 diametrically opposed to the outlet port 119. In some embodiments, the profile of the relief port 169 is configured to minimize trapped air during the compression cycle. In some embodiments, the profile of the relief port 169 matches the profile of the opposing outlet port 119. In some embodiments, the relief valve 160 is synchronized with the outlet port such that only one of the relief port and the outlet port is open at any one time, thereby preventing venting of the tank assembly 300 through the relief valve 169. In other embodiments, opening the relief port 169 and the outlet port 119 simultaneously facilitates venting of the tank assembly 300 through the compression assembly 100.

[0034] Referring again to Figures 7-10, the compression assembly 100 includes one or more isolators 130 to further divide the compression chamber 115. Each isolator 130 defines an outer surface 132 and one or more receptacles 135 recessed therefrom. Each isolator rotor is positioned and timed relative to its respective compression rotor such that the receptacles can receive compression members, thereby allowing the compression members to move between sections of the compression chamber. It will be appreciated that particular embodiments of the present invention include various numbers of isolator rotors, compression members, etc. to accommodate sizing, power, and timing requirements and / or preferences. It will further be appreciated that particular embodiments of the present invention include compression members having various sizes and configurations, such as rounded, square, angular fillets, gussets, etc.

[0035] Each receptacle 135 of the isolator rotor is configured to receive a compression member at the end of the compression stroke, thereby allowing the compression member to move beyond the second end of the compression section of the compression chamber. At all other times, the outer surface of the isolator is positioned adjacent to the outer surface of the compression rotor (with a small gap as described above) to define the front end of the compression section of the compression chamber. In some embodiments, the isolator further defines the first end of the inlet section of the compression chamber.

[0036] In some embodiments, each section of the compression chamber is in constant fluid communication with each adjacent section, such as through respective gaps between the rotors and / or between the rotor and the housing. In this manner, the system provides constant fluid communication between the systems while facilitating the generation of compression and the intake of fluid. In some embodiments, the housing includes inlet ports 111 located immediately beyond each isolator. When a compression (or other) member passes through the corresponding inlet port, the resulting vacuum forces fluid into the inlet section of the compression chamber.

[0037] In some embodiments, the housing includes outlet ports 119 positioned immediately prior to each isolator. When a compression member passes through a corresponding outlet port, the corresponding compression chamber is closed. In some embodiments, one or more valves (reed valves, rotary valves, etc.) are associated with the outlet ports to facilitate fluid flow through the outlet ports just prior to the compression section being closed (when pressure is greatest). In some embodiments, the compression assembly is configured to prevent or otherwise inhibit fluid flow through the outlet ports at other times.

[0038] In some embodiments, the system includes one or more rotary valves 320 as part of one or more valve assemblies. Referring to FIG. 11 , certain embodiments of the rotary valve define one or more openings designed to allow fluid to exit the compression assembly at one or more appropriate times, while preventing or otherwise inhibiting such fluid flow at other times. In some embodiments, the valve assembly includes one or more mechanisms and / or means for advancing and / or retarding its timing, such as through one or more adjustment mechanisms or other adjustment means, e.g., electrical, mechanical, hydraulic, and / or other (now known or later developed) mechanisms and / or means, alone or in combination with one or more of the same.

[0039] 59-66, some isolators 130 of the present invention are configured to move an outlet port between an open and a closed configuration relative to a compression section of a compression chamber 115. In this manner, a separate valve is not required, and pressure buildup associated with engaging a compression member with a corresponding receptacle can be eliminated or otherwise reduced. In some embodiments, each compression member includes a leading portion and an opposing trailing portion, each configured to engage with a respective leading portion and trailing portion of a respective receptacle as the compression member 115 moves from one section of the compression chamber to another.

[0040] In some embodiments, the present invention includes a tank assembly 300 for holding compressed fluid. In some embodiments, the tank assembly 300 is in fluid communication with the compression chamber when its corresponding section is at or near maximum pressure (e.g., just before the compression section is closed). In some embodiments, the volume of the tank assembly is significantly greater than the volume of the compression chamber, thereby providing stability to the system. In some embodiments, the tank assembly includes one or more pressure relief or other means for maintaining pressure below a maximum threshold, thereby preventing overpressure associated with operation of the compression assembly and / or facilitating its pressure optimization. In some embodiments, a relief valve is in fluid communication with the atmosphere. In some embodiments, the relief valve is in fluid communication with a holding vessel, such as a high-pressure holding vessel.

[0041] The present invention is configured for use in a variety of environments, such as on the ground and at high altitudes. In some embodiments, the system includes a means for compensating for changes in altitude, such as by including one or more pressure relief valves. In some embodiments, the pressure relief valve, or one or more other means for regulating pressure, can be adjusted (e.g., left on) to maximize or otherwise optimize engine performance. In some embodiments, the pressure relief valve is configured to be left open, allowing the engine to just coast with little flow restriction. In some such embodiments, the system is configured to shut off (and / or allows) fuel, such as allowing the system to function as a giant air pump with little or no restriction. In some embodiments, the system is configured to divert air from the compression chambers, such as when the tank assembly is at or near a maximum or other threshold pressure. In some such embodiments, the system is configured to maintain one or more compression chambers in an open configuration, thereby reducing the overall system load by preventing pressure buildup in the compression chambers. In some embodiments, the system is configured to increase power when needed or desired.

[0042] It will be appreciated that in some embodiments, one or more compression assemblies are stacked (functionally and / or literally) with one or more other compression assemblies, thereby facilitating the generation of higher pressures and / or generating the desired pressure in a shorter time (i.e., stacked in series). It will further be appreciated that in some embodiments, one or more compression assemblies operate adjacent (i.e., in parallel) to one or more other compression assemblies (functionally and / or literally). It will further be appreciated that one or more compression assemblies can be activated and / or deactivated as needed or desired to provide versatility. In this manner, the present invention enables superior power performance and superior efficiency. In some embodiments, the system includes a primary rotor operating at a first pressure and a secondary rotor operating at a second pressure lower than the first pressure. In this manner, the system includes versatility associated with the use of the same.

[0043] In some embodiments, the tank assembly 300 includes a tank shroud 311 positioned between a first tank plate and a second tank plate. In some embodiments, the first tank plate is parallel to the second tank plate. In some embodiments, the tank assembly 300 defines one or more relief ports, such as one or more ports defined by the tank shroud 311 and / or one or more tank plates. In some embodiments, the tank assembly extends from the compression assembly 100 such that the first tank plate also functions as part of the compression housing 110, such as the second compression plate 116. In some embodiments, the tank assembly 300 extends from the combustion assembly 200 such that the second tank plate also functions as part of the combustion housing 210, such as the first combustion plate 214.

[0044] 1-2 , some embodiments of the rotary engine 10 of the present invention include a combustion assembly 200 for facilitating internal combustion. The combustion assembly 200 is in fluid communication with a source of high-pressure fluid, such as a high-pressure tank plate 300, a compression assembly 100, or a compression turbine (not shown). In some embodiments, the source of high-pressure fluid has a gauge pressure greater than 30 pounds per square inch. In some embodiments, the gauge pressure is greater than 50 pounds per square inch. In some embodiments, the gauge pressure is approximately 300 pounds per square inch. In some embodiments, the gauge pressure is sufficient to deliver compressed fluid to the engine's combustion chamber to facilitate combustion without requiring compression of the fluid within the combustion chamber. In some embodiments, the gauge pressure is sufficient to deliver compressed fluid to the expansion section of the engine's combustion chamber while the expansion section is expanding (while the expansion member is moving away from the intake port) and facilitate combustion within the expansion section of the combustion chamber to further expand the expansion section.

[0045] In a manner similar to that discussed above for the compression assembly, combustion assembly 200 includes a combustion housing 210 and a power rotor 220 positioned therein. Combustion housing 210 defines an inner surface, and the power rotor defines a corresponding outer surface displaced therefrom to define a combustion chamber 215 between which the combustion assembly is positioned. In some embodiments, combustion housing 210 includes a combustion shroud 213 positioned between a first combustion plate 214 and a second combustion plate 216. In some embodiments, first combustion plate 214 is parallel to second combustion plate 216. In some embodiments, combustion housing 210 defines one or more intake ports 211 and / or one or more outlet ports 219, e.g., one or more ports defined by combustion shroud 213 and / or one or more combustion plates.

[0046] The power rotor 220 includes expansion members 225, such as fins, blades, etc., that extend from the outer surface of the power rotor toward the inner surface of the combustion housing, thereby defining the second end of the expansion section of the combustion chamber 215. The power rotor 220 further includes an exhaust member that defines the first end of the exhaust section of the combustion chamber 215. It will be appreciated that in some embodiments, one or more expansion members 125 of the power rotor 120 also function as exhaust members, such that each expansion member 125 separates a combustion section from an adjacent exhaust section. In some embodiments, the combustion housing 210 and the power rotor 220 are configured such that a small gap exists between the inner surface of the combustion housing 210 and the distal end of the expansion member 225 (and / or exhaust member, if applicable). The small gap is designed to provide clearance while minimizing combustion blow-by. It will be appreciated that as the power rotor rotates within the combustion housing, certain sections of the combustion chamber 215 alternate between being part of the combustion section and being the exhaust section.

[0047] As the power rotor 120 rotates during a power stroke, the expansion members move away from their respective intake ports 211 such that the volume of the combustion section of the combustion chamber 215 increases, thereby providing a means for converting combustion power into mechanical energy during the engine's power stroke. In some embodiments, the intake ports 211 are located at or near a first end of the expansion section of the combustion chamber. It will be appreciated that in some embodiments, each power stroke of the combustion chamber can occur simultaneously with the exhaust stroke of the combustion chamber.

[0048] As the power rotor 220 rotates during the exhaust stroke, the exhaust members move toward their respective exhaust ports 219 so that exhaust gases exit the combustion chamber. In some embodiments, the exhaust ports 219 are located at or near the second end of the exhaust section of the combustion chamber 215.

[0049] 5 and 6 , some embodiments of the present invention include an exhaust system 600 having a catalytic converter 605 or other means for reducing emissions. In some embodiments, the exhaust system 600 includes a first branch 610 for passing fluid through the catalytic converter 605 and a second branch 620 that does not pass the fluid through the catalytic converter. In some embodiments, the exhaust system includes an exhaust trunk 630 coupled to each of the first branch 610 and the second branch 620, and an associated exhaust valve 650. In some such embodiments, the exhaust valve 650 is configured to move between a first configuration and a second configuration, thereby directing the exhaust through the first branch 610 or the second branch 620, respectively. In this manner, the exhaust system facilitates the discharge of combusted exhaust (through the first branch) and uncombusted exhaust (e.g., when compressed fluid is pumped through a combustion assembly to drive a combustion rotor at low load requirements) through the second branch 620 without causing undesired cooling of the catalytic converter 605.

[0050] In some embodiments, the systems of the present invention utilize reluctor wheels, Hall effect sensors, electronic digital optical sensors, digital mechanical hydraulic controls, or any other electrical, mechanical, hydraulic, and / or other (now known or later developed) mechanisms and / or means, alone or in combination with one or more of the same.

[0051] Referring back to Figures 7-10, the combustion assembly includes one or more isolators 230 to further divide the combustion chamber 215. Each isolator 230 defines an outer surface and one or more receptacles 235 recessed therefrom. Each isolator rotor is positioned and timed relative to its respective power rotor so that the receptacles can receive an expansion member, thereby allowing the expansion member to move between sections of the combustion chamber. It will be understood that particular embodiments of the present invention include various numbers of isolator rotors, expansion members, etc. to accommodate sizing, power, and timing requirements and / or preferences. Furthermore, it will be understood that particular embodiments of the present invention include expansion members having various sizes and configurations, such as rounded, square, angular fillets, gussets, etc.

[0052] Each receptacle 235 of the isolator rotor is configured to receive an expansion member at the end of the exhaust stroke, thereby allowing the expansion member to move beyond the second end of the exhaust section of the combustion chamber. At all other times, the outer surface of the isolator is positioned adjacent to the outer surface of the power rotor (with a small gap as described above) to define the second end of the exhaust section of the combustion chamber. In some embodiments, the isolator further defines the first end of the expansion section of the combustion chamber.

[0053] In some embodiments, each section of the combustion chamber is in constant fluid communication with each adjacent section, such as through respective gaps between the rotors and / or between the rotor and the housing. In this manner, the system provides constant fluid communication between the systems while facilitating power generation and exhaust. In some embodiments, the housing includes an exhaust port positioned immediately prior to each isolator. When the expansion member passes through the corresponding exhaust port, the corresponding exhaust section of the chamber is closed.

[0054] In some embodiments, combustion housing 210 includes intake ports 211 positioned immediately beyond each isolator. When a combustion (or other) member passes through the corresponding intake port, a quantity of compressed fluid ("working fluid") is permitted to enter the intake section of the combustion chamber in connection with the engine's power stroke. In some embodiments, one or more valves (reed valves, rotary valves, etc.) are associated with the intake port to facilitate fluid flow through the intake port in connection with the expansion section opening (generally prior to ignition). In some embodiments, the compression assembly is configured to prevent or otherwise inhibit fluid flow through the intake port at other times.

[0055] In some embodiments, the valve assembly includes one or more rotary valves 310 designed to allow working fluid to enter the combustion assembly at one or more appropriate times while preventing or inhibiting the flow of such fluid at other times. In some embodiments, the valve assembly includes one or more mechanisms and / or means for advancing and / or retarding that timing, such as through one or more adjustment mechanisms or other adjustment means, e.g., electrical, mechanical, hydraulic, and / or other (now known or later developed) mechanisms and / or means, alone or in combination with one or more of the same.

[0056] In some embodiments, the system is configured to utilize a variety of fuel types and ignition systems, and / or the present invention can otherwise meet associated requirements and / or preferences. In some embodiments, the system includes an adjustable ignition timing system and / or an adjustable injection timing system. In some embodiments, one or more timing or other systems can be adjusted digitally, mechanically, hydraulically, or otherwise.

[0057] In some embodiments, the system includes multiple combustion chambers. In some such embodiments, the system is configured to selectively reduce and / or eliminate combustion in one or more combustion chambers at strategic times, such as at cruise altitude. In some embodiments, the system is configured to add or increase combustion at other times, such as during takeoff or climb. In some embodiments, the system utilizes port fuel injection. In other embodiments, the system utilizes direct fuel injection. In some embodiments, the system includes one or more chambers to facilitate direct-injected pre-chamber combustion. In some embodiments, the system utilizes one or more throttle bodies.

[0058] 7, some embodiments of the present invention include a combustion and / or compression assembly having a rectangular cavity in which one or more isolators are positioned. In some such embodiments, the associated assembly is configured with a biasing member for biasing each isolator into a predetermined position relative to a respective compression rotor, power rotor, etc. In this manner, the system is configured to provide some tolerance for debris generated within and / or migrating into the respective chambers.

[0059] 7, some embodiments of the present invention include a cleaning feature 138 for preventing or otherwise inhibiting carbon or other buildup on a rotor, such as an isolator rotor. In some embodiments, the cleaning feature is a blade, scraper, or the like extending from the housing of an associated assembly. In some such embodiments, the distal end of the cleaning feature 138 is configured to engage the outer surface of the rotor and / or the inner surface of the housing to eliminate that buildup, such as by facilitating a wiping action, or the like.

[0060] In some embodiments, the system is configured to operate at high rotational speeds, such as above 5,000 rpm. In some embodiments, gaps within the system, such as gaps between rotors, rotor blades, interior walls, etc., are sized and configured to eliminate or otherwise minimize airflow and / or compression losses from one or more chambers and / or across one or more barriers when the system is operating at high rotational speeds. In some embodiments, a sealant, such as water, is injected and / or otherwise provided into one or more interior regions, such as the compression assembly, combustion assembly, etc. In some such embodiments, the system is configured such that the sealant creates a seal to eliminate or otherwise minimize airflow and / or compression losses from one or more chambers and / or across one or more barriers when the system is operating at low rotational speeds, such as below 5,000 rpm. In some embodiments, the sealant is specially configured to minimize corrosion or other adverse effects on the system. In some embodiments, one or more components are formed from a material and / or the material is treated to minimize corrosion or other adverse effects associated with the fluid.

[0061] Referring back to FIG. 1 , some embodiments of the present invention include a gear assembly 400, such as a gear assembly positioned in the front inlet region of an engine. In some embodiments, the gear assembly includes multiple gears associated with each rotor, thereby providing a means for synchronizing their rotation. In some embodiments, the gears are configured so that each rotor rotates at the same speed as each of the other rotors. In some embodiments, the gears are configured so that one or more isolator rotors rotate at a faster or slower speed than the respective power rotor or compression rotor, such as in a configuration where each isolator rotor includes more blades than receptacles. For example, in some embodiments, an isolator rotor with one receptacle rotates twice as fast as an associated power rotor with two blades, such that a single receptacle of the isolator rotor engages with each of two members of the power rotor during one rotation of the power rotor. In some embodiments, each gear is configured to drive the rotation of a respective shaft, thereby driving the rotation of a respective impeller, rotor, etc. In some embodiments, a single shaft is coupled to multiple rotors, thereby driving the rotation of each.

[0062] 35, 36, 37, 38, and 39, some embodiments of the present invention include one or more fan assemblies 80, such as a fan assembly 80 positioned at the aft end of the engine, the front end of the engine, or both. In some embodiments, the fan assembly 80 is mechanically engaged with one or more shafts of the present invention, such as a tube extending through a power (and / or compression) rotor, a tube extending through one or more isolator rotors, etc. In this manner, the system is configured to drive rotation of a plurality of fan blades about the shaft, thereby drawing air across the exterior of the engine (e.g., for engine cooling) and / or drawing air from the engine (e.g., for propulsion). In some embodiments, the system further includes an engine shroud 60 extending from and / or between the one or more fan assemblies 80. In this manner, the fan blades are configured to draw fluid into and / or push fluid into an interior region defined by the engine shroud 60. In some embodiments, at least a portion of the engine is positioned within the interior region defined by the engine shroud 60.

[0063] 46-54, some embodiments of the present invention include a method of assembling an engine. In some embodiments, the method includes associating one or more drive shafts 20 with one or more drive gears 22 and / or one or more synchronizer shafts 30, such as synchronizer gears 32. In some embodiments, the one or more shafts define a cylindrical shape having a longitudinal central axis. In some embodiments, the one or more shafts define opposed front and rear openings and a hollow interior region extending therebetween, thereby facilitating airflow through the shafts. In some embodiments, the method includes engaging each shaft with a gear housing 410, such as a gear plate, gear shroud, or the like. In some embodiments, the method includes extending the one or more shafts through respective holes defined by the gear housing. In some embodiments, the method further includes enclosing the gears within the gear housing 410, such as by installing the front plate 114 of the compression assembly 100 to the gear housing 410, such that the front plate 114 of the compression assembly 100 doubles as the rear plate of the gear housing 410. It will be appreciated that in other embodiments, the gear housing includes a rear plate (not shown) that is separate from the front plate 114 of the compression assembly.

[0064] Some embodiments of the present invention include a method of assembling a compressor assembly 100. In some embodiments, the method includes extending one or more shafts through an opening defined by a front plate 114 of a compressor housing 110. In some embodiments, the front plate 114 defines two displaced holes, such as bores, configured to facilitate an airtight seal around the respective shafts. In some embodiments, the method of assembling a compressor assembly includes securing a compressor rotor 120 to a first shaft, such as a power shaft 20, a synchronous shaft 30, or the like. In some such embodiments, the method further includes securing an isolator rotor 130 to a second shaft, such as a power shaft 20, a synchronous shaft 30, or the like. The method further includes associating the first shaft with a second shaft, such as via a gear assembly or the like, and clocking the compression rotor relative to the isolator rotor such that one or more compression members of the compression rotor are periodically received by one or more receptacles of the isolator rotor as the compression rotor rotates in a first rotational direction (clockwise or counterclockwise) about a central axis of the first shaft and the isolator rotor rotates in a second rotational direction (counterclockwise or clockwise) about a central axis of the second shaft, thereby facilitating continuous unidirectional rotation of the compression rotor.

[0065] In some embodiments, a method of assembling a compression assembly includes extending one or more shafts through respective voids defined by the compression shroud 113 of the compression housing 110, such as a first void associated with the compression rotor and a second void associated with the isolator rotor. In some embodiments, each void is cylindrical such that the compression shroud defines multiple curved inner walls 112, such as a first curved inner wall defined by a first radius associated with the compression rotor and / or a second curved inner wall defined by a second radius associated with the isolator rotor. It will be appreciated that in some embodiments, the second void is rectangular, as discussed above, to facilitate fluid storage, such as to facilitate movement of one or more isolator rotors. In some embodiments, the first and second voids intersect one another such that the combination of the voids resembles a figure eight. In some embodiments, the voids are configured to allow installation of the compression shroud on one or more rotors coupled to one or more respective shafts, such as the compression rotor, the isolator rotor, etc. In some embodiments, the voids are configured to allow one or more rotors to be installed on respective shafts extending through such voids. In some embodiments, the method further includes enclosing the rotors within the compression housing 110, such as by installing a rear plate 116 of the compression housing 110, thereby defining one or more compression chambers having inlet ports 111 and outlet ports 119 associated with allowing fluid to enter and exit the compression chambers, respectively. In some embodiments, the width of the inlet ports is equal to or substantially equal to the width of the compression chambers (i.e., as measured along the longitudinal axis of the engine's power shaft). In other embodiments, the width of the inlet ports is less than the width of the compression chambers. In yet other embodiments, the width of the inlet ports is greater than the width of the compression chambers.

[0066] Some embodiments of the present invention include a method of assembling a combustion assembly 200. In some embodiments, the method includes extending one or more shafts through an opening defined by a front plate 214 of a combustion housing 210. In some embodiments, the front plate 214 defines two displaced holes, such as holes, configured to facilitate an airtight seal around the respective shafts. In some embodiments, the method of assembling a combustion assembly includes securing a power rotor 220 to a first shaft, such as the power shaft 20. In some such embodiments, the method further includes securing an isolator rotor 230 to a second shaft, such as the synchronous shaft 30. The method further includes associating the first shaft with the second shaft, such as via a gear assembly or the like, and clocking the power rotor relative to the isolator rotor such that one or more expansion members of the power rotor are periodically received by one or more receptacles of the isolator rotor as the power rotor rotates in a first rotational direction (clockwise or counterclockwise) about the central axis of the first shaft and the isolator rotor rotates in a second rotational direction (counterclockwise or clockwise) about the central axis of the second shaft, thereby facilitating continuous unidirectional rotation of the power rotor.

[0067] In some embodiments, a method of assembling a combustion assembly includes extending one or more shafts through respective voids defined by the combustion shroud 213 of the combustion housing 210, such as a first void associated with a power rotor and a second void associated with an isolator rotor. In some embodiments, each void is cylindrical such that the combustion shroud defines multiple curved inner walls 212, such as a first curved inner wall defined by a first radius associated with the power rotor and / or a second curved inner wall defined by a second radius associated with the isolator rotor. It will be appreciated that in some embodiments, the second void is rectangular, as discussed above, to facilitate fluid storage, such as to facilitate movement of one or more isolator rotors. In some embodiments, the first and second voids intersect one another such that the combination of the voids resembles a figure eight. In some embodiments, the voids are configured to allow installation of the combustion shroud on one or more rotors coupled to one or more respective shafts, such as a power rotor, an isolator rotor, etc. In some embodiments, the voids are configured to allow one or more rotors to be installed on respective shafts extending through such voids. In some embodiments, the method further includes enclosing the rotors within the combustion housing 210, such as by installing a rear plate 216 of the combustion housing 210, thereby defining one or more combustion chambers having intake ports 211 and exhaust ports 219 associated with directing fluid into and out of the combustion chambers, respectively. In some embodiments, the width of the exhaust ports is equal to or substantially equal to the width of the combustion chambers (i.e., as measured along the longitudinal axis of the engine's power shaft). In other embodiments, the width of the exhaust ports is less than the width of the combustion chambers. In yet other embodiments, the width of the exhaust ports is greater than the width of the combustion chambers.In some embodiments, the cross-section of the exhaust system (and / or one or more branches of the exhaust system) is tapered and / or otherwise larger than the cross-section of the combustion chamber, such as to facilitate scavenging or otherwise help draw exhaust from the combustion chamber. In some embodiments, the cross-section of the exhaust system (and / or one or more branches of the exhaust system) is tapered and / or otherwise larger than the cross-section of the combustion chamber, such as to restrict exhaust and / or facilitate various types of controlled combustion. In some embodiments, the exhaust system is configured so that air flowing through the exhaust system helps draw exhaust fluid from the exhaust section of the combustion chamber, such as by orienting outlet ports of the exhaust system relative to the flow of fluid around the exhaust system.

[0068] It will be understood that the respective volumes of the compression and combustion chambers can be varied to meet various requirements, such as by making the compression chamber volumes larger than, equal to, or smaller than the respective combustion chamber volumes. Furthermore, it will be understood that the total volume of the multiple combustion and / or compression chambers can be varied, such as by adding or removing one or more such chambers and / or by reconfiguring, disabling (i.e., opening a relief valve), redesigning, or otherwise modifying them. It will also be understood that the volume of each chamber can be varied by changing one or more parameters of the respective assemblies, such as the rotor width (i.e., measured along the longitudinal axis of the engine's power shaft), the rotor outer diameter, the positioning of the inlet / intake ports relative to the outlet / exhaust ports, and / or the diameter of the inner surface of the respective housing. In some embodiments, the shaft diameter varies along its length, thereby facilitating the use of larger or smaller rotors as needed or desired. In some such embodiments, the shaft is a single piece that is machined or formed with various diameters. In other embodiments, the shaft includes a first portion extending from a second portion, the first portion having an outer diameter smaller than the outer diameter of the second portion. In some embodiments, a larger compressor volume (single or combined) is utilized to store excess compressed air, such as to drive additional mechanisms and / or to facilitate driving a power rotor with compressed air during times of low power requirements. In other embodiments, the volume of the combustion assembly is larger than the volume of the compression assembly, thereby achieving efficiencies associated with maximizing power capture during the expansion stroke (i.e., the efficiencies that the Atkins and Miller cycles attempt to achieve in reciprocating engines).

[0069] In some embodiments, the tank assembly of the present invention is configured to hold working fluid for multiple charges such that when the tank assembly is open to the combustion assembly, the pressure within the tank assembly remains high enough to pump the fluid into the combustion chamber (i.e., negligible pressure drop). In some embodiments, the tank assembly is configured to hold the fluid at a pressure high enough that when the tank assembly is open to the combustion assembly, the pressure within the tank assembly is sufficient to pump the fluid into the combustion chamber at a pressure high enough to facilitate combustion (i.e., acceptable pressure drop). In some embodiments, opening the combustion chamber to the tank assembly creates a pressure drop within the tank assembly associated with the pressurized fluid within the tank assembly pumping the fluid into the combustion chamber. In some embodiments, one or more compression assemblies pump fluid into the tank assembly while the tank assembly is open to the combustion chamber, thereby counteracting at least some of the pressure drop associated with opening the combustion chamber to the tank assembly. In some embodiments, one or more mechanisms are utilized to selectively increase or decrease the volume of an interior region of the tank assembly, thereby facilitating maintaining a relatively constant pressure within the tank assembly while the intake port of the combustion assembly moves between an open configuration and a closed configuration.

[0070] In some embodiments, a method of assembling a combustion assembly includes defining an ignition chamber 250 in fluid communication with a combustion chamber 215 of the present invention (see FIG. 68). In some embodiments, a first ignition tunnel 252 extends between the ignition chamber 250 and the combustion chamber 215, thereby facilitating expansion from the ignition chamber into the combustion chamber following ignition in the ignition chamber, thereby facilitating ignition in the combustion chamber. In some embodiments, an ignition means 16, such as a plasma plug, extends into the ignition chamber 250 to facilitate ignition in the ignition chamber. It will be understood that in some embodiments, the system includes ignition means extending into the combustion chamber instead of, or in addition to, ignition means extending into the ignition chamber. It will further be understood that some embodiments of the present invention do not include an ignition chamber, and / or the ignition chamber is the same as the combustion chamber.

[0071] In some embodiments, a means for providing fuel 15, such as a fuel injector, extends into the ignition chamber and / or is otherwise positioned proximate to the ignition chamber 250 to create an air-fuel ratio in the ignition chamber 250 with good ignition capability. In some embodiments, the air-fuel ratio in the ignition chamber 250 is greater than the air-fuel ratio in the combustion chamber. In some embodiments, at least a portion of the charge (such as fuel, compressed working fluid, and / or the like) is directed to the ignition chamber through a second ignition tunnel 254. In some embodiments, the combustion assembly is configured such that at least a portion of the charge circulates through the ignition chamber immediately prior to ignition, thereby facilitating mixing of the air and fuel and / or otherwise facilitating ignition (e.g., by facilitating obtaining a favorable air-fuel mixture, etc.). In some embodiments, the circulation increases the air-fuel mixture in the ignition chamber.

[0072] Some embodiments of the present invention include a method of assembling a tank assembly 300. In some embodiments, the method includes extending one or more shafts through an opening defined by a front plate of a tank housing 310. It will be appreciated that in some embodiments, the front plate of the tank assembly also functions as the rear plate 116 of the compression housing 110. In some embodiments, the front plate defines two offset holes, such as holes, configured to facilitate an airtight seal around the respective shafts. In some embodiments, the method of assembling a tank assembly 300 includes securing a rotary valve 320 to a first shaft, such as the power shaft 20. The method further includes associating a first shaft with a power rotor of the combustion assembly, such as by coupling the power rotor to the first shaft, and rotating the rotary valve clockwise relative to the power rotor such that one or more openings 321 of the rotary valve 320 are periodically aligned with one or more intake ports of the combustion assembly when the first shaft rotates in a first rotational direction (clockwise or counterclockwise) about a central axis of the first shaft, thereby moving an intake port 211 of the combustion assembly 200 between an open configuration and a closed configuration to control fluid flow from the tank assembly to a combustion chamber 215 of the combustion assembly. In some embodiments, one or more fuel injectors are aligned (positioned and oriented) with the intake port of the combustion assembly and configured to inject fuel into the combustion assembly when the intake port is in the open configuration. In some embodiments, the fuel injector is positioned at least partially within the interior volume of the tank assembly and is configured to prevent or otherwise inhibit fuel from remaining within the tank assembly, such as by directing fuel towards the intake port while fluid from the tank assembly is pumped through the intake port, thereby pumping fuel therewith.

[0073] In some embodiments, the method of assembling a tank assembly includes extending one or more shafts (such as power tubes, sync tubes, and / or the like) through a void defined by the tank shroud 313 of the tank housing 310. In some embodiments, the void is configured to allow the tank shroud to be installed over a rotary valve. In some embodiments, the void is configured to allow the rotary valve to be installed on a shaft extending through such void. In some embodiments, the method further includes enclosing the tank housing 310, such as by installing a back plate of the tank housing, thereby defining one or more tank chambers for storing pressurized fluid, the tank chambers having at least one port through which the fluid is received, such as an outlet port of an associated compression assembly, and at least one port through which the fluid is discharged from the tank assembly, such as an intake port of an associated combustion assembly.

[0074] Referring to Figures 73-76, some embodiments of the present invention include one or more means for preventing or otherwise reducing blow-by from the intake port. In some embodiments, the rotary valve 320 includes a tapered region to provide additional support and / or rigidity. In some embodiments, the tank housing includes a corresponding region, such as a corresponding tapered region, to provide additional support to the rotary valve. In some embodiments, the tapered region of the tank housing defines a path to allow fluid to flow toward an opening in the rotary valve when the opening is aligned with the intake valve of the combustion assembly, thereby facilitating fluid flow to the combustion chamber of the combustion assembly. In some embodiments, the engine is configured such that fluid entering the tank assembly must flow around one or more shafts of the engine as it flows toward the intake port of the combustion assembly. In this manner, heat transfer between the shaft and the fluid can be increased.

[0075] It will be understood that in some embodiments, one or more combustion assemblies are stacked (functionally and / or literally) with one or more other combustion assemblies (i.e., stacked in series). It will further be understood that in some embodiments, one or more combustion assemblies are (functionally and / or literally) operating adjacent to (i.e., in parallel with) one or more other combustion assemblies. It will further be understood that one or more combustion assemblies can be activated and / or deactivated (partially or fully) as needed or desired to provide versatility. In this manner, the present invention enables superior power performance and superior efficiency.

[0076] It will be appreciated that some embodiments of the present invention include one or more compression assemblies positioned before one or more tank assemblies and / or one or more combustion assemblies. It will further be appreciated that in some embodiments, one or more combustion assemblies are positioned before one or more tank assemblies and / or compression assemblies, such as when air preheating is necessary and / or desired. In some such embodiments, one or more exhaust manifolds extend from a front portion of the engine toward the rear of the engine. It will further be appreciated that some embodiments of the present invention include gears positioned before, after, and / or within one or more combustion assemblies, tank assemblies, and / or compression assemblies.

[0077] It will be appreciated that engines of the present invention can be configured to operate in a first direction (i.e., power shaft rotating in a clockwise direction) or a second direction (counterclockwise). It will be further appreciated that some embodiments of the present invention include pairing a first engine operating in a first direction with a second engine operating in a second direction, such as by positioning the first and second engines on opposite left and right wings of the aircraft, thereby eliminating or otherwise reducing torque effects associated therewith.

[0078] Some embodiments of the present invention include an internal combustion engine 10 having a combustion assembly 200. The combustion assembly 200 includes a combustion housing 210 having an inner surface 212 that defines an interior region. A power rotor 220 is positioned within the interior region of the combustion housing 210, with the power rotor 220 having an outer surface 222 that is offset from the inner surface 212 of the combustion housing 210, thereby defining a combustion chamber 215. An expansion member 225 extends from the outer surface 222 of the power rotor 220 toward the inner surface 212 of the combustion housing 210, thereby dividing the combustion chamber into an expansion section and an exhaust section during the engine's power stroke. The exhaust section is configured to facilitate the discharge of an expanded working fluid, such as a working fluid, a first charge, a second charge, etc., and associated combustion byproducts. The expansion section is configured to facilitate the generation of power associated with the expansion of the working fluid, such as a working fluid, a first charge, a second charge, etc. In some embodiments, the combustion assembly includes multiple power rotors. In some embodiments, one or more of the power rotors includes a plurality of expansion members.

[0079] In some embodiments, the expansion member 225 is coupled to the power rotor 220 such that the expansion member moves through the combustion chamber 215 as the power rotor 220 rotates about the first axis. In some embodiments, the distal end of the expansion member 225 remains a first distance from the first axis as the power rotor 220 rotates about the first axis. In some embodiments, the first axis remains fixed relative to the combustion housing 210 of the engine. In some embodiments, the first axis remains fixed relative to the ignition means 16 of the combustion assembly, such as a spark plug, glow plug, or plasma plug. In some embodiments, the first axis remains fixed relative to the combustion chamber 215 of the combustion assembly. In some embodiments, the first axis remains fixed relative to the intake port 211 and / or exhaust port 219 of the combustion assembly, with the intake port 211 located at a first end of the combustion chamber 215 and the exhaust port 219 located at a second end of the combustion chamber 215.

[0080] Some embodiments of the present invention include a combustion isolator 230 positioned at least partially within an interior region of combustion housing 210, the combustion isolator 230 having an outer surface 232 positioned adjacent to outer surface 222 of power rotor 220 to define at least a portion of the first and / or second ends of combustion chamber 215. In some embodiments, combustion isolator 230 defines a receptacle 235 configured to receive expansion member 225 of power rotor 220 as expansion member 225 moves from exhaust port 219 toward intake port 211 to facilitate ejection of working fluid of a previously ignited and expanded first charge, second charge, etc., charge from the combustion chamber, facilitate continuous unidirectional rotation of power rotor 220 (e.g., by facilitating repeated engagement and disengagement of the expansion member with / from one or more receptacles), facilitate resetting the combustion assembly for a subsequent combustion process, etc. In some embodiments, the combustion assembly includes multiple isolators. In some embodiments, one or more of the isolators include a plurality of receptacles.

[0081] Some embodiments of the present invention include a compression assembly 100. In some embodiments, the compression assembly 100 includes a compression housing 110 having an inner surface 112 that defines an interior region. A compression rotor 120 is positioned within the interior region of the compression housing 110, the compression rotor 120 having an outer surface 122 that is offset from the inner surface 112 of the compression housing 110, thereby defining a compression chamber 115. A compression member 125 extends from the outer surface 122 of the compression rotor 120 toward the inner surface 112 of the compression housing 110, thereby dividing the compression chamber into an intake section and a compression section during a compression stroke of the compression assembly. The intake section is configured to facilitate drawing a compressible fluid, such as a working fluid used by a combustion assembly, into the compression chamber. The compression section is configured to facilitate compression of the fluid such that compression of the working fluid in the combustion chamber is not required. In some embodiments, the compression assembly includes multiple compression rotors. In some embodiments, one or more compression rotors include multiple compression members.

[0082] In some embodiments, the compression member 125 is coupled to the compression rotor 120 such that the compression member moves through the compression chamber 115 as the compression rotor 120 rotates about the first axis. In some embodiments, the distal end of the compression member 125 remains a first distance from the first axis as the compression rotor 120 rotates about the first axis. In some embodiments, the first axis remains fixed relative to the compression housing 110 of the engine. In some embodiments, the first axis remains fixed relative to the compression chamber 115 of the compression assembly. In some embodiments, the first axis remains fixed relative to the inlet port 111 and / or the outlet port 119 of the compression assembly, with the inlet port 111 positioned at a first end of the compression chamber 115 and the outlet port 119 positioned at a second end of the compression chamber 115.

[0083] Some embodiments of the present invention include a compression isolator 130 positioned at least partially within the interior region of the compression housing 110, the compression isolator 130 having an outer surface 132 positioned adjacent the outer surface 122 of the compression rotor 120 to define at least a portion of the first and / or second ends of the compression chamber 115. In some embodiments, the compression isolator 130 defines a receptacle 135 configured to receive the compression member 125 of the compression rotor 120 as the compression member 125 moves from the output port 119 toward the inlet port 111 to facilitate ejection of compressed fluid from the compression chamber, facilitate continuous unidirectional rotation of the compression rotor 120 (e.g., by facilitating repeated engagement and disengagement of the compression member with / from one or more receptacles), facilitate resetting the compression assembly for a subsequent compression process, etc. In some embodiments, the compression assembly includes multiple isolators. In some embodiments, one or more isolators include multiple receptacles.

[0084] Referring to Figures 77-82, some embodiments of the present invention include a vent system for preventing or otherwise inhibiting air from being exhausted from an engine and / or controlling such exhaust. In some embodiments, one or more rotors and / or the housing define recessed regions 705 such that when the rotor is positioned within the housing, the recessed regions form voids surrounding (directly or displaced from) the respective tubes. In this manner, blow-by gases (compressed air blow-by, combustion blow-by, etc.) that may travel between the housing wall and the rotor must enter the voids before reaching the shaft. In some embodiments, a vent system 700, such as a positive crankcase ventilation ("PCV") system, is in fluid communication with the voids, thereby exhausting fluid from the voids before the fluid reaches the shaft. In some embodiments, the vent system includes and / or is connected to a valve 710, such as a PCV valve. In some embodiments, the system utilizes seals 720, such as ring seals, to prevent or otherwise inhibit fluid that may migrate through voids from migrating from the respective chambers between the shaft and the respective housing. In this manner, unnecessary venting can be reduced or eliminated. It will be appreciated that some embodiments include recessed areas formed in the housing rather than the rotor, some embodiments include recessed areas formed in the rotor rather than the housing, and some embodiments include partial or complete recesses formed in each of the housing and rotor. In some embodiments, the vent system returns at least some fluid to the breather system, such as upstream of a filter in the breather system. In some embodiments, the vent system directs fluid to a location downstream of the breather system, for example, directly to the compression housing, tank housing, etc.

[0085] Referring to FIG. 83, some embodiments include multiple fuel injection systems. In some embodiments, the invention includes a means for injecting fuel into a breather system and / or a means for otherwise injecting fuel into incoming air prior to compressing the air in a compression assembly. In some embodiments, the invention includes a means for injecting fuel into a tank assembly and / or a means for otherwise directing fuel into compressed air before the air enters a combustion assembly. In some embodiments, the invention includes a means for injecting fuel into a combustion assembly, such as an ignition chamber, and / or directly into a combustion chamber.

[0086] In some embodiments, the compressor rotor of the present invention rotates about a first axis and the isolator of the present invention rotates about a second axis, the first axis being parallel to but offset from the first axis. In some embodiments, the compressor rotor is coupled to a drive shaft extending from the combustion assembly such that the first axis coincides with the longitudinal central axis of the drive shaft. In some such embodiments, the isolator rotor is coupled to a synchronizing shaft extending from the combustion assembly such that the second axis coincides with the longitudinal central axis of the synchronizing shaft. In other embodiments, the compressor rotor is coupled to the synchronizing shaft and / or the isolator rotor is coupled to the drive shaft. In some embodiments, each rotor is coupled to a respective shaft such that the rotational speed of each rotor is equal to the rotational speed of the respective shaft.

[0087] Although specific terms have been used in the foregoing description for brevity, clarity, and understanding, such terms are used for purposes of description and are intended to be broadly construed, and no unnecessary limitations should be implied therefrom beyond the requirements of the prior art. Moreover, the description and illustration of the invention is by way of example, and the scope of the invention is not limited to the exact details shown or described.

[0088] While the foregoing detailed description of the invention has been described with reference to exemplary embodiments, showing and describing the best mode contemplated for carrying out the invention, it will be understood that certain changes, modifications, or variations, other than those specifically described herein, may be made in embodying and constructing the above-described invention and may be accomplished by those skilled in the art without departing from the spirit and scope of the invention, and that such changes, modifications, or variations are considered to be within the full scope of the invention. It is therefore intended to cover all changes, modifications, variations, or equivalents that fall within the true spirit and scope of the invention and the underlying principles disclosed and claimed herein. The scope of the invention is therefore intended to be limited only by the appended claims, and all matter contained in the above description and shown in the accompanying drawings shall be interpreted as illustrative and not in a limiting sense.

[0089] Having now described the features, discoveries and principles of the invention, the manner in which it is constructed and used, the features of construction, and the advantageous, new and useful results obtained, the new and useful structures, devices, elements, arrangements, components and combinations are set forth in the appended claims.

[0090] It is also to be understood that the following claims are intended to cover all of the general and specific features of the invention described herein, and all statements of the scope of the invention that may be made as a matter of language therebetween.

Claims

1. An engine, a compression assembly configured to compress a working fluid; a combustion assembly configured to generate power from the expansion of the working fluid; and A drive shaft; A synchronous shaft; Equipped with the compression assembly a compression housing having an inner surface defining an interior region, a compression rotor disposed within the interior region of the compression housing, the compression rotor having an outer surface displaced from the inner surface of the compression housing, thereby defining a compression chamber; a compression member extending from the outer surface of the compression rotor toward the inner surface of the compression housing, the compression member coupled to the compression rotor such that the compression member moves through the compression chamber as the compression rotor rotates about a first axis; a compression isolator disposed at least partially within the interior region of the compression housing, the compression isolator having an outer surface disposed adjacent the outer surface of the compression rotor to define at least a portion of a first end of the compression chamber; the compression isolator defines a first receptacle configured to receive the compression member as it passes through the compression isolator; the compression isolator rotates about a second axis parallel to but displaced from the first axis; the combustion assembly a combustion housing having an interior surface defining an interior region; a power rotor positioned within the interior region of the combustion housing, the power rotor having an outer surface displaced from the inner surface of the combustion housing, thereby defining a combustion chamber; an expansion member extending from the outer surface of the power rotor toward the inner surface of the combustion housing, thereby dividing the combustion chamber into an expansion section and an exhaust section; a combustion isolator extending at least partially within the interior region of the combustion housing, the combustion isolator defining a second receptacle configured to receive the expansion member; the power rotor rotates in a first direction; the combustion isolator rotates in a second direction opposite the first direction; rotation of the combustion isolator is synchronized with rotation of the power rotor such that the expansion member moves in and out of communication with the second receptacle of the combustion isolator as the expansion member rotates past the combustion isolator, thereby facilitating continuous unidirectional rotation of the power rotor; The drive shaft a power rotor coupled to the power rotor and extending from the combustion chamber; the power rotor is coupled to the compression rotor such that the rotational speed of the power rotor is equal to the rotational speed of the compression rotor; The synchronous shaft a combustion isolator coupled to the combustion assembly and extending from the combustion assembly; the combustion isolator is coupled to the compression isolator such that the rotational speed of the combustion isolator is equal to the rotational speed of the compression isolator; the combustion assembly is configured to generate power from the expansion of the working fluid; the engine allows for the ability to independently configure intake compression to power exhaust ratio during operation of the engine; The engine, wherein independently configuring the intake compression to power exhaust ratio comprises switching the compression assembly between a compression configuration and a non-compression configuration.

2. 10. The engine of claim 1, wherein a quantity of working fluid compressed during a first compression stroke of the engine is greater than a quantity of working fluid expanded during a first combustion stroke of the engine, the first compression stroke being driven by power generated from the first combustion stroke.

3. The engine of claim 2 , wherein at least a portion of the power required to compress the working fluid by the compression assembly is provided by expansion of the working fluid in the combustion assembly.

4. 4. The engine of claim 3, wherein the compression assembly is configured to be switchable between a compressed and non-compressed configuration, and wherein the compression assembly is switched between the compressed and non-compressed configurations by switching a relief port between a closed and an open configuration, and wherein the compression assembly is configured to compress working fluid when it is in the compressed configuration and is configured not to compress working fluid when it is not in the compressed configuration, thereby reducing the amount of power required to drive the compression assembly at such times.

5. 5. The engine of claim 4, wherein the compression assembly defines a relief port switchable between a closed configuration and an open configuration, thereby switching the compression assembly between the compressed and non-compressed configurations, respectively.

6. a partition assembly positioned between the compression assembly and the combustion assembly and extending from the compression assembly to the combustion assembly, the partition assembly defining a channel configured for a working fluid to travel from the compression assembly to the combustion assembly; the divider assembly further defines a tank assembly for holding a first quantity of working fluid, the tank assembly being in fluid communication with the channel; The engine of claim 2 , wherein the first amount of the working fluid is greater than the amount of the working fluid compressed during the first compression stroke.

7. 3. The engine of claim 2, wherein the working fluid enters the combustion chamber at a first gauge pressure, the first gauge pressure being greater than 50 pounds per square inch.

8. A method for generating power from an engine, comprising: Expanding a first quantity of working fluid within a combustion assembly of the engine during a first power stroke of the engine; compressing a second quantity of working fluid in a compression assembly of the engine during a first compression stroke of the engine, the first power stroke of the engine compressing the second quantity of working fluid simultaneously with the first compression stroke of the engine such that the engine has a first intake compression to power exhaust ratio; flowing the second quantity of the working fluid through a partition assembly located between the compression assembly and the combustion assembly and extending from the compression assembly to the combustion assembly, the partition assembly defining a channel configured to move the second quantity of the working fluid from the compression assembly to the combustion assembly; varying the intake compression to power exhaust ratio of the engine during operation of the engine immediately after the first compression stroke of the engine; changing the intake compression to power exhaust ratio of the engine by switching the compression assembly between a compression configuration and a non-compression configuration; the combustion assembly a combustion housing having an interior surface defining an interior region; a power rotor positioned within the interior region of the combustion housing, the power rotor having an outer surface displaced from the inner surface of the combustion housing, thereby defining a combustion chamber; an expansion member extending from the outer surface of the power rotor toward the inner surface of the combustion housing, thereby dividing the combustion chamber into an expansion section and an exhaust section; the compression assembly a compression housing having an inner surface defining an interior region, a compression rotor disposed within the interior region of the compression housing, the compression rotor having an outer surface displaced from the inner surface of the compression housing, thereby defining a compression chamber; a compression member extending from the outer surface of the compression rotor toward the inner surface of the compression housing, the compression member coupled to the compression rotor such that the compression member moves through the compression chamber as the compression rotor rotates about a first axis; a compression isolator disposed at least partially within the interior region of the compression housing, the compression isolator having an outer surface disposed adjacent the outer surface of the compression rotor to define at least a portion of a first end of the compression chamber; the compression isolator defines a first receptacle configured to receive the compression member as it passes through the compression isolator; the compression isolator rotates about a second axis parallel to but displaced from the first axis; method.

9. The method of claim 8 , wherein the second amount of working fluid is greater than the first amount of working fluid.

10. The method of claim 9 , wherein at least a portion of the power required to compress the working fluid by the compression assembly is provided by expansion of the working fluid in the combustion assembly.

11. The compression assembly configured to compress a working fluid when in the compression configuration; the compression assembly is configured so that it does not compress working fluid when it is not in the compression configuration, thereby reducing the amount of power required to drive the compression assembly at such times; changing the intake compression to power exhaust ratio of the engine immediately after the first compression stroke of the engine includes switching the compression assembly to a non-compressing configuration; 11. The method of claim 10, wherein switching the compression assembly out of the compressed configuration includes switching a relief port of the compression assembly from a closed configuration to an open configuration.

12. 10. The method of claim 9, further comprising transferring a first quantity of working fluid from a tank assembly of the engine to the combustion chamber, the first quantity of working fluid being drawn from a third quantity of working fluid in the tank assembly, the third quantity of working fluid being greater than the second quantity of working fluid.

13. 9. The method of claim 8, wherein the first quantity of working fluid enters the combustion chamber at a first gauge pressure, the first gauge pressure being greater than 50 pounds per square inch.

14. An engine as described in claim 1, wherein the rotation of the combustion isolator is synchronized with the rotation of the power rotor so that the expansion member switches between a connected and disconnected state with the second receptacle of the combustion isolator as the expansion member rotates past the combustion isolator, thereby promoting continuous unidirectional rotation of the power rotor.

15. 10. The engine of claim 1, further comprising: a vent system in fluid communication with a first location of the combustion housing, the first location being positioned between the combustion chamber and an outer surface of the drive shaft to prevent fluid from migrating out of the combustion housing along the outer surface of the drive shaft.

16. the combustion assembly a combustion isolator extending at least partially within the interior region of the combustion housing, the combustion isolator defining a second receptacle configured to receive the expansion member; the power rotor rotates in a first direction; the combustion isolator rotates in a second direction, the second direction being opposite to the first direction; rotation of the combustion isolator is synchronized with rotation of the power rotor such that the expansion member switches between communication with the second receptacle of the combustion isolator and communication with the second receptacle of the combustion isolator as the expansion member rotates past the combustion isolator, thereby facilitating continuous unidirectional rotation of the power rotor; The drive shaft is a power rotor coupled to the power rotor and extending from the combustion chamber; the power rotor is coupled to the compression rotor such that the rotational speed of the power rotor is equal to the rotational speed of the compression rotor; The synchronous shaft is a combustion isolator coupled to the combustion assembly and extending from the combustion assembly; the combustion isolator is coupled to the compression isolator such that the rotational speed of the combustion isolator is equal to the rotational speed of the compression isolator; The method of claim 8.

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