The present disclosure relates generally to turbine engines that operate on the Ericsson cycle.
In general, the efficiency of conventional engines such as combustion engines may be poor due to lost thermal energy as consequence of the laws of thermodynamics. Most diesel engines, for example, have a thermal efficiency less than 50%, whereas gasoline-powered engines may even be considerably more inefficient. This is due to the fact that a substantial amount of heat is lost when fuel is converted into mechanical energy. Factors that may contribute to lost thermal energy include the temperature at which heat enters the engine and the temperature of the environment into which the engine exhausts its waste heat. In this regard, there is a need for an improved engine that is more efficient than conventional engines.
To minimize the limitations in the related art and other limitations that will become apparent upon reading and understanding the present specification, the following discloses embodiments of a new and useful Ericsson cycle turbine engine.
One embodiment may be an Ericsson cycle turbine engine, comprising: a centrifugal gas compressor being fed with a gas-liquid mixture and configured to separate a gas from the gas-liquid mixture and compress the gas; a shaft coupled to a downstream end of the centrifugal gas compressor and having an annular space traversing therein, the annular space being configured to permit the compressed gas to travel across the shaft a heat exchanger configured to heat the compressed gas; and a reaction turbine coupled to a downstream end of the shaft and configured to rotate the shaft when releasing the compressed gas, the reaction turbine further comprising a heat absorption plate; wherein the shaft may be disposed within the heat exchanger and fixedly coupled to the centrifugal gas compressor and the reaction turbine, such that when the reaction turbine rotates, the shaft and the centrifugal gas compressor may rotate. The centrifugal gas compressor may comprise: a rotating container configured to rotate about a central longitudinal axis and having an annular chamber configured to receive the gas-liquid mixture; a plurality of first cavities disposed within the rotating container and extending radially from the annular chamber to a plurality of separation chambers, such that the annular chamber may be in fluid communication with the plurality of separation chambers; a plurality of second cavities located within the rotating container and disposed adjacently between the plurality of separation chambers and the plurality of first cavities, the plurality of second cavities being in fluid communication with the plurality of separation chambers; and a plurality of compressed gas passages located radially inward from the plurality of separation chambers and in fluid communication between the plurality of separation chambers and the annular space of the shaft, such that the plurality of compressed gas passages may be configured to permit transfer of the compressed gas from the plurality of separation chambers into the annular space of the shaft. The Ericsson cycle turbine engine may further comprise a plurality of excess fluid passages in fluid communication with the plurality of second cavities, the plurality of excess fluid passages being configured to release a liquid without the compressed gas. The Ericsson cycle turbine engine may further comprise a plurality of outflow ports in fluid communication with the plurality of excess fluid passages. The liquid may be selected from the group of liquids consisting of: a mercury, an oil, a water, and a water-glycol mixture. The gas may be selected from the group of gases consisting of: a helium, an air, an argon, and an ammonia.
Another embodiment may be an Ericsson cycle turbine engine, comprising: a centrifugal gas compressor being fed with a gas-liquid mixture and configured to separate a gas from the gas-liquid mixture and compress the gas; a shaft coupled to a downstream end of the centrifugal gas compressor and having an annular space traversing therein, the annular space being configured to permit the compressed gas to travel across the shaft; a heat exchanger in heat exchange relationship with the shaft and configured to heat the compressed gas, such that isobaric expansion may be approached; and a reaction turbine coupled to a downstream end of the shaft and configured to rotate the shaft when releasing the compressed gas, the reaction turbine further comprising a heat absorption plate fixedly coupled to the downstream end of the shaft; wherein the shaft may be disposed within the heat exchanger; and wherein the centrifugal gas compressor, the shaft, and the reaction turbine may be centered about a central longitudinal axis and may be fixedly coupled to each other, such that when the reaction turbine rotates, the shaft and the centrifugal gas compressor may rotate. The centrifugal gas compressor may be a spinning wheel trompe configured to compress the gas via centrifugal acceleration, the centrifugal gas compressor comprising: a rotating container configured to rotate about the central longitudinal axis and having an annular chamber configured to receive the gas-liquid mixture; a plurality of first cavities disposed within the rotating container and extending radially from the annular chamber to a plurality of separation chambers, such that the annular chamber may be in fluid communication with the plurality of separation chambers; a plurality of second cavities located within the rotating container and disposed adjacently between the plurality of separation chambers and the plurality of first cavities, the plurality of second cavities being in fluid communication with the plurality of separation chambers; and a plurality of compressed gas passages located radially inward from the plurality of separation chambers and in fluid communication between the plurality of separation chambers and the annular space of the shaft, such that the plurality of compressed gas passages may be configured to permit transfer of the compressed gas from the plurality of separation chambers into the annular space of the shaft. The Ericsson cycle turbine engine may further comprise a plurality of excess fluid passages in fluid communication with the plurality of second cavities, the plurality of excess fluid passages being configured to release a liquid without the compressed gas. The Ericsson cycle turbine engine may further comprise a plurality of outflow ports in fluid communication with the plurality of excess fluid passages. The liquid may be selected from the group of liquids consisting of: a mercury, an oil, a water, and a water-glycol mixture. The gas may be selected from the group of gases consisting of: a helium, an air, an argon, and an ammonia.
Another embodiment may be an Ericsson cycle turbine engine, comprising: a tank having a liquid; a first heat exchanger configured to cool the liquid; a gas line configured to introduce gas into the liquid to create a gas-liquid mixture; a centrifugal gas compressor rotatably coupled to a downstream end of the tank and being fed with the gas-liquid mixture, the centrifugal gas compressor being configured to separate the gas from the gas-liquid mixture and compress the gas by near isothermal compression; a shaft coupled to a downstream end of the centrifugal gas compressor and having an annular space traversing therein, the annular space being configured to permit the compressed gas to travel across the shaft; a second heat exchanger in heat exchange relationship with the shaft and configured to heat the compressed gas, such that isothermal expansion may be approached; and a reaction turbine coupled to a downstream end of the shaft and configured to rotate the shaft when releasing the compressed gas, the reaction turbine further comprising a heat absorption plate; wherein the shaft may be disposed within the second heat exchanger; and wherein the centrifugal gas compressor, the shaft, and the reaction turbine may be centered about a central longitudinal axis and may be fixedly coupled to each other, such that when the reaction turbine rotates, the shaft and the centrifugal gas compressor may rotate. The centrifugal gas compressor may be a spinning wheel trompe configured to compress the gas via centrifugal acceleration, the centrifugal gas compressor comprising: a rotating container configured to rotate about the central longitudinal axis and having an annular chamber configured to receive the gas-liquid mixture; a plurality of first cavities disposed within the rotating container and extending radially from the annular chamber to a plurality of separation chambers, such that the annular chamber may be in fluid communication with the plurality of separation chambers; a plurality of second cavities located within the rotating container and disposed adjacently between the plurality of separation chambers and the plurality of first cavities, the plurality or second cavities being in fluid communication with the plurality of separation chambers; and a plurality of compressed gas passages located radially inward from the plurality of separation chambers and in fluid communication between the plurality of separation chambers and the annular space of the shaft, such that the plurality of compressed gas passages may be configured to permit transfer of the compressed gas from the plurality of separation chambers into the annular space of the shaft. The Ericsson cycle turbine engine may further comprise a plurality of excess fluid passages in fluid communication with the plurality of second cavities, the plurality of excess fluid passages being configured to release a liquid without the compressed gas. The Ericsson cycle turbine engine may further comprise a plurality of outflow ports in fluid communication with the plurality of excess fluid passages. The liquid may be selected from the group of liquids consisting of: a mercury, an oil, and a water-glycol mixture. The gas may be selected from the group of gases consisting of: a helium, an air, an argon, and an ammonia.
It is an object to provide an Ericsson cycle turbine engine that utilizes a centrifugal gas compressor that functions similar to a trompe. Unlike a trompe, however, the centrifugal gas compressor disclosed herein replaces the acceleration of gravity with centrifugal acceleration to build pressure. This may allow the centrifugal gas compressor to generate high pressure in a compact design.
It is an object to provide an Ericsson cycle turbine engine that utilizes a centrifugal gas compressor that compresses gas at a constant temperature (i.e., isothermal compression). Unlike most conventional gas compressors, which generally compress gas inefficiently due to the amount of inherent heating and work required, the centrifugal gas compressor utilized by the Ericsson cycle turbine engine preferably stores the inherent heating with the compressed gas during the compression process. In this manner, this would allow the work potential of the compressed gas to be roughly equivalent to the work required to compress the gas.
It is an object to overcome the limitations of the prior art.
These, as well as other components, steps, features, objects, benefits, and advantages, will now become clear from a review of the following detailed description of illustrative embodiments, the accompanying drawings, and the claims.
The drawings are illustrative embodiments. They do not illustrate all embodiments. They-do not set forth all embodiments. Other embodiments may be used in addition or instead. Details, which may be apparent or unnecessary, may be omitted to save space or for more effective illustration. Some embodiments may be practiced with additional components or steps and/or without all of the components or steps, which are illustrated. When the same numeral appears in different drawings, it is intended to refer to the same or like components or steps.
It is to be understood that the foregoing general description and the following detailed description are exemplary and explanatory only and are not to be viewed as being restrictive of the embodiments, as claimed. Further advantages of these embodiments will be apparent after a review of the following detailed description of the disclosed embodiments, which are illustrated schematically in the accompanying-drawings and in the appended claims.
In the following detailed description, numerous specific details are set forth in order to provide a thorough understanding of various aspects of one or more embodiments of the Ericsson cycle turbine engine. However, these embodiments may be practiced without some or all of these specific details. In other instances, well-known methods, procedures, and/or components have not been described in detail so as not to unnecessarily obscure the aspects of these embodiments.
Before the embodiments are disclosed and described, it is to be understood that these embodiments are not limited to the particular structures, process steps, or materials disclosed herein, but is extended to equivalents thereof as would be recognized by those ordinarily skilled in the relevant arts. It should also be understood that the terminology used herein is used for the purpose of describing particular embodiments only and is not intended to be limiting.
Reference throughout this specification to “one embodiment,” “an embodiment,” or “another embodiment” may refer to a particular feature, structure, or characteristic described in connection with the embodiments of the present disclosure. Thus, appearances of the phrases “in one embodiment” or “in an embodiment” in various places throughout this specification may not necessarily refer to the same embodiment.
Furthermore, the described features, structures, or characteristics may be combined in any suitable manner in various embodiments. In the following description, numerous specific details are provided, such as examples of materials, fasteners, sizes, lengths, widths, shapes, etc. . . . , to provide a thorough understanding of the embodiments. One skilled in the relevant art will recognize, however, that the scope of the disclosed embodiments can be practiced without one or more of the specific details, or with other methods, components, materials, etc. . . . . In other instances, well-known structures, materials, or operations are generally not shown or described in detail to avoid obscuring aspects of the disclosure.
In the following description, certain terminology is used to describe certain features of the embodiments of the Ericsson cycle turbine engine in accordance with the present disclosure. For example, as used herein, unless otherwise specified, the term “substantially” refers to the complete, or nearly complete, extent or degree of an action, characteristic, property, state, structure, item, or result. As an arbitrary example, an object that is “substantially” surrounded would mean that the object is either completely surrounded or nearly completely surrounded. The exact allowable degree of deviation from absolute completeness may in some cases depend on the specific context. However, generally speaking, the nearness of completion will be so as to have the same overall result as if absolute and total completion were obtained.
The use of“substantially” is equally applicable when used in a negative connotation to refer to the complete or near complete lack of an action, characteristic, property, state, structure, item, or result. As another arbitrary example, a composition that is “substantially free of” particles would either completely lack particles, or so nearly completely lack particles that the effect would be the same as if it completely lacked particles. In other words, a composition that is “substantially free of” an ingredient or element may still actually contain such item as long as there is no measurable effect thereof.
As used herein, the term “approximately” may refer to a range of values of 10% of a specific value. For example, the expression “approximately 150 inches” may comprise the values of 150 inches 10%, i.e. the values from 135 inches to 165 inches.
As used herein, the term “about” is used to provide flexibility to a numerical range endpoint by providing that a given value may be “a little above” or “a little below” the endpoint. In some cases, the term “about” is to include a range of not more than about two inches of deviation.
As used herein in this disclosure, the singular forms “a” and “the” may include plural referents, unless the context clearly dictates otherwise. Thus, for example, reference to an “opening” can include reference to one or more of such openings.
The present disclosure relates generally to engines, and more particularly, to turbine engines that operate on the Ericsson cycle. In general, the efficiency of conventional engines such as combustion engines may be poor due to lost thermal energy as consequence of the laws of thermodynamics. Most diesel engines, for example, have a thermal efficiency less than 50%, whereas gasoline-powered engines may even be considerably more inefficient. This is due to the fact that a substantial amount of heat is lost when fuel is converted into mechanical energy. Factors that may contribute to lost thermal energy include the temperature at which heat enters the engine and the temperature of the environment into which the engine exhausts its waste heat.
The Ericsson cycle turbine engine disclosed herein is preferably more efficient than conventional engines. The Ericsson cycle turbine engine may consume half the fuel of a diesel engine and approximately one-third the fuel of a gasoline or steam engine. As a result, the Ericsson cycle turbine engine is capable of increasing its thermal and operating efficiency. For example, when used with ships or unmanned undersea vehicles, the Ericsson cycle turbine engine may reduce inefficiencies and thus increase the range of operational distance.
In its basic configuration, the Ericsson cycle turbine engine may comprise: a centrifugal gas compressor, shaft, heat exchanger, and reaction turbine. The centrifugal gas compressor may be a spinning wheel trompe that receives gas entrained in a liquid or gas-liquid mixture. The centrifugal gas compressor may then separate the gas from the gas-liquid mixture and compressed that gas via centrifugal acceleration. The shaft may be coupled to a downstream end of the centrifugal gas compressor and may have an annular space to permit the compressed gas to travel therein. The heat exchanger may heat the compressed gas, such that isobaric expansion is approached. The reaction turbine may be coupled to a downstream end of the shaft and may rotate the shaft when releasing the compressed gas. In various embodiments, the Ericsson cycle turbine engine may further comprise a tank that provides the gas-liquid mixture to the centrifugal gas compressor and a heat absorption plate. The liquid may be mercury, oil, water, or water-glycol mixture. The gas may be helium, ambient air, argon, or ammonia.
In the accompany drawings, like reference numbers indicate like elements. Reference character 1000 depicts embodiments of the Ericsson cycle turbine engine.
As shown in
The tank 20 is preferably a structure having an interior space particularly suited for holding and storing a fluid (e.g., liquid 15 or gas 10, as shown in
The centrifugal gas compressor 100 is preferably a compressor that functions similarly to a trompe and may be rotatably coupled to a downstream end of the tank 20 via an inlet 30. Unlike a trompe, however, embodiments of the centrifugal gas compressor 100 preferably utilizes the acceleration of centrifugal force in order to build pressure. In particular, upon receiving the gas-liquid mixture 25 from the inlet 30, the centrifugal gas compressor 100 may be configured to spin or rotate about the central longitudinal axis 101 to create a centrifugal force that separates the gas 10 from the gas-liquid mixture 25. That separated gas 10 may then be transported to the annular space 200a of the shaft 200 due to the high pressure generated by the centrifugal gas compressor 100. Additional details about the centrifugal gas compressor 100 and its operations are discussed further below.
As the centrifugal gas compressor 100 separates the gas 10 from the from the gas-liquid mixture 25, the liquid 15 may also be separated as well, and in a preferred embodiment, that separated liquid 15 (and any excess gas 10) may be released or expelled from the centrifugal gas compressor 100 via outflow ports 136 of the centrifugal gas compressor 100. In various embodiments, the released liquid 15 may be recovered and fed back into the tank 20, such that the outflow ports 136 may be in fluid communication with the tank 20. In these embodiments, a pump may be implemented (not shown) to feed the released liquid 15 back into the tank 20. In this manner, the recovered liquid 15 may reenter the Ericsson cycle turbine engine 1000.
Accordingly, various embodiments of the tank 20 may utilize one or more pumps (not shown) that is self-priming, and in those embodiments, some liquid may be stored inside the pump(s) in order to initiate the pumping process. For example, a first pump may be implemented to initiate the transfer of the gas-liquid mixture 25 from the tank 20 into the inlet 30 of the centrifugal gas compressor 100. In other embodiments, an additional second pump may be implemented to recover liquid 15 released from the outflow ports 136 of the centrifugal gas compressor 100 by transferring that liquid 15 back into the tank 20. In other embodiments, however, the Ericsson cycle turbine engine 1000 may lack pumps and thus may not be self-priming. In these embodiments, other various means may be used to transport liquid 15 or gas-liquid mixture 25 into the centrifugal gas compressor 100.
As shown in
Regarding the second heat exchanger 300, various types of second heat exchangers 300 may be used for the thermos 50 (e.g., fluid heat exchangers, plate heat exchangers). For example, unlike the first heat exchanger 90, an exemplary embodiment of the second heat exchanger 300 may be a countercurrent flow heat exchange system where fluids may flow in opposing directions (e.g., liquid-gas). In this embodiment, the countercurrent flow heat exchange system may engage with the fins 56 of the shaft in order to apply heat towards the compressed gas 10 traveling downstream though the shaft 200. In an exemplary embodiment, as the compressed gas 10 travels downstream though the shaft 200 and thermos 50, the compressed gas 10 may also flow orthogonally from the shaft 200, through each fin 56 (i.e., towards the inner wall 54 of the thermos 50), and back towards the shaft 200. In this manner, heat may also efficiently transfer to the compressed gas 10 from the piping 57 of the heat exchanger 300 and towards the fins 56 of the shaft 200.
Turning to
If pressure is sufficient to produce supersonic flow, embodiments of each channel 410 may further comprise a choke 410a (shown in
In various embodiments, the Ericsson cycle turbine engine 1000 may further comprise a power take-off shaft 75, as shown in
Additionally, in various embodiments, the thermos 50 may further comprise a spark plug and/or fuel injector. The spark plug may be configured to produce a spark to create an ignition of combustion, whereas the fuel injector may be configured to spray fuel for combustion for the Ericsson cycle turbine engine 1000. In various embodiments, the thermos 50 may instead comprise a spark plug fuel injector (SPFI) 65, which may be a spark plug and fuel injector combination. In this embodiment, the SPFI may be spark plug having a gas supply inlet configured to deliver fuel directly to a combustion chamber, as shown in
In operation, liquid 15 stored in the tank 20 may be subject to cooling by a first heat exchanger 90. The cooled liquid 15 may also mix with gas 10 provided by the gas line 305 via diffusion to create a gas-liquid mixture 25 within the tank 20. The gas-liquid mixture 25 may then enter the annular chamber 107 of the centrifugal gas compressor 100 via the inlet 30. The centrifugal gas compressor 100, which functions similar to a trompe, preferably separates the gas 10 and liquid 15 from the gas-liquid mixture 25 via centrifugal acceleration.
Specifically, regarding the operation and inner workings of the centrifugal gas compressor 100, gas-liquid mixture 25 entering the annular chamber 107 may first flow into the first cavities 110 and then outwardly into the separation chambers 120. There, within the separation chambers 120, gas 10 is preferably separated from the gas-liquid mixture 25 when the centrifugal gas compressor 100 creates a centrifugal force via spinning or rotation. That centrifugal force generally causes the gas 10 and liquid 15 to separate with the separated gas 10 traveling inwardly towards the compressed gas passages 130 near the central longitudinal axis 101 (i.e., axis of rotation). In particular, columns of the gas-liquid mixture 25 within the separation chambers 120 may be subject to G forces, thereby increasing the weight of the gas-liquid mixture 25. This increase in weight may create outward pressure to the gas-liquid mixture 25. Given a bubble's tendency to rise to the surface, gas bubbles may create the buoyant force needed to separate the gas 10 from the liquid 15, such that the centrifugal gas compressor 100 may create bubbles within the gas-liquid mixture 25. This buoyant force may be the difference between the density of the substance in the void (i.e., gas 10) and the physical weight of the liquid 15 due to gravitational acceleration. Notably, any change in revolutions-per-minute may affect the pressure within the centrifugal gas compressor 100, and the speed of the falling column of liquid 15 generally must exceed the bubble's rise velocity in order to make the bubble sink inwards.
The size of the bubbles entering the centrifugal gas compressor 100 are preferably small, as small bubbles generally have a relatively large surface to volume ratio. Small bubbles also generally tend to have less buoyancy, which may lower the bubble's tendency to travel counter to the direction of flow. The size of small bubbles generally have a very high or greater surface area to volume ratio, which may be necessary to facilitate and increase the rate of heat transfer to the liquid 15. Given that the gas 10 being compressed may be in close proximity to the gas-liquid surface area, the liquid may extract heat from each compressed bubble at the same rate where the heat is being generated. As a result, the compression preferably becomes an isothermal event and the centrifugal gas compressor 100 may embody an ideal gas compressor. Therefore, the outlet temperature of the compressed gas 10 is preferably, substantially the same as the inlet temperature of the gas 10.
Regarding the liquid 15 portion, the separated liquid 15 may travel outwards radially towards the outer perimeter of the centrifugal gas compressor 100 and into second cavities 133 (shown in
Turning to the separated gas 10 portion, the compressed gas 10 exiting the centrifugal gas compressor 100 via the compressed gas passages 130 may be ported into the annular space 200a of the shaft 200. There, within the shaft 200, the compressed gas 10 may be subject to cooling from a second heat exchanger 300, such as for example a counterflow heat exchanger. The compressed gas 10 flowing downstream through the shall 200 (and possibly fins 56) is preferably subject to heat, such that isothermal expansion may be achieved. As the heated, compressed gas 10 travels downstream end of the shaft 200 and exits the heat exchanger 300, the compressed gas 10 is preferably expelled through the reaction turbine 400. There, the compressed gas 10 preferably actuates the reaction turbine 400 in a rotating manner when exiting the channels 410 of reaction turbine 400. In this manner, the reaction turbine 400 may further drive the Ericsson cycle turbine engine 1000, thereby improving its operating efficiency. In the event the release of gas maintains zero angular velocity, maximum efficiency may be achieved. Preferably, the reaction turbine 400 is disposed within a heated chamber (e.g., thermos), which can be heated by various means, and the heat is preferably maintained within the thermos 50 to help maintain operating efficiency.
In various embodiments, the type of liquid and gas may vary, depending on the application of the Ericsson cycle turbine engine 1000. For example, in various embodiments, any liquid 15 may be used, but mercury may generate the highest pressure due to its high density. Water may also be contemplated due to its high heat capacity, whereas oil may be used due its low vapor pressure.
Regarding the gas 10, various embodiments of gas 10 may be used, but exemplary embodiments of the gas 10 may be helium or air. In alternative embodiments, argon and ammonia may be used as gas 10 instead, depending on the situation. For example, if the gas 10 is air, a constant volume void may displace the same amount of water and the buoyant force of the bubble may increase in a linear fashion, as the flow of the water may also further increase the movement of the bubble away from the central longitudinal axis of rotation. The buoyant force of other gases 10, however, may vary.
The rotating container 105 may be configured to rotate along a central longitudinal axis 101 via the shaft 200 and thus may impart a centrifugal force to fluids stored or flowing inside the centrifugal gas compressor 100. Thus, as discussed above, the centrifugal gas compressor 100 may function similarly to a spinning wheel trompe in order to separate gas 10 from a gas-liquid mixture 25 and compress that gas 10 via centrifugal acceleration. The rotating container 105 may comprise an inlet 30 in fluid communication with an annular chamber 107, and the annular chamber 107, which is preferably disposed along the central longitudinal axis 101, preferably receives the gas-liquid mixture 99 from the tank 20.
Like the first cavities 110, the separation chambers 120 are also preferably positioned in an equidistant and diametrically opposing manner with respect to each other. This may allow the separation chambers 120 to maintain equal weight distribution for the centrifugal gas compressor 100, especially during rotational movement. In various embodiments, the separation chambers 120 may also be somewhat triangular in shape in order to allow gas that has been separated from the gas-liquid mixture 25 via centrifugal force to be compressed and funneled directly into the compressed gas passages 130.
As discussed above, centrifugal force may be used to compress the gas bubbles. The centrifugal force may be created by the centrifugal nature of the centrifugal gas compressor 100 and may increase the weight of a column of liquid (i.e., liquid from a radially inboard region to a radially outboard region) by subjecting the centrifugal gas compressor 100 to several thousand G forces. Notably, a wide range of final pressures can be achieved by adjusting RPM of the centrifuge.
The centrifugal force of a spinning column of liquid via the separation chambers 120 at different radii (“r”) may be calculated by determining the pressure P of a rotating fluid, as follows:
where P=pressure; ρ=density of the fluid in mass per volume; ω=angular velocity in radians per second; r=radius
In order to function efficiently, the path of the liquid transfer from the center of the centrifugal gas compressor 100 to the outside is preferably constant. Additionally, the flow rate generally must be greater than the speed in which the bubbles float to the center. Thus, the final pressure of the gas after the gas returns to the center or annular space 200a of the shaft 200 is preferably:
Therefore, the speed of the falling column of liquid 15 via the separation chambers 120 must exceed the bubble rise velocity in order to make the bubbles or gas sink. Preferably, in the centrifugal gas compressor 100, the buoyant force of the gas bubble may be directed radially inboard towards the central longitudinal axis 101 of the rotating container 105. To compress the gas 10, the bubble must be forced to move radially inwards and thus the buoyant force must be less than the centrifugal force acting on the gas bubble. In other words, the centrifugal force acting on the liquid intermediate within the separation chambers 120 must be greater than the buoyant force.
In an exemplary embodiment, the heat absorption plate 405 may be operably coupled to the downstream end of the shaft 200, which is preferably disposed along the axis of rotation or central longitudinal axis 101, and may be configured to absorb heat released from the compressed gas 10. Additionally, the channels 410 may radially extend from the center of the heat absorption plate 405. Importantly, each channel 410 may extend or traverse in a curved manner away from the shaft 200 or axis of rotation and may be positioned equidistant from each other, as shown in
As mentioned above, various types of heat exchangers 90 may be used (e.g., fluid heat exchangers, plate heat exchangers), and the tank 20 may be cooled in various ways. For example, in an exemplary embodiment, the heat exchanger 90 may be a countercurrent flow heat exchange system where fluids flow in opposite directions (e.g., liquid-gas). The countercurrent current flow heat exchange system may also allow the transfer of most heat from the heat (transfer) medium per unit mass due to the fact that the average temperature difference along any unit length is lower.
Importantly,
As mentioned above, various embodiments of the tank 20 may include a pump (not shown) that helps transfer fluids (e.g. gas 10, liquid 15, gas-liquid mixture 25) downstream from the tank 20 and into the inlet 30 of the centrifugal gas compressor 100. Additionally, in those embodiments, the pump may be self-priming, such that a required amount of liquid may be stored inside the pump in order to initiate the pumping process. In other embodiments, the tank 20 may lack a pump and may be self-priming.
The compressed gas 10 exiting the centrifugal gas compressor 100 preferably travels through the annular space 200a of the shaft 200 (and possibly fins 56) and may be heated by the heat exchanger 300, such as for example a counterflow heat exchanger. There, the compressed gas 10 flowing downstream through the shaft 200 is preferably subject to heat, such that isothermal expansion may be achieved. As the heated, compressed gas 10 travels downstream end of the shaft 200 and exits the heat exchanger 300, the compressed gas 10 may actuate the reaction turbine 400 by exiting the channels 410 of reaction turbine 400. In this manner, the reaction turbine 400 may further drive the Ericsson cycle turbine engine 1000, thereby improving efficiency of the Ericsson cycle turbine engine 1000. Preferably, the reaction turbine 400 is disposed within a heated chamber (e.g., thermos 50), which can be heated by various means, and the heat is preferably maintained within the thermos 50 in order to improve operating efficiency.
The foregoing description of the embodiments of the Ericsson cycle turbine engine has been presented for the purposes of illustration and description. While multiple embodiments are disclosed, other embodiments will become apparent to those skilled in the art from the above detailed description. As will be realized, these embodiments are capable of modifications in various obvious aspects, all without departing from the spirit and scope of the present disclosure. Accordingly, the detailed description is to be regarded as illustrative in nature and not restrictive.
Although embodiments of the Ericsson cycle turbine engine are described in considerable detail, other versions are possible. Therefore, the spirit and scope of the appended claims should not be limited to the description of versions included herein.
Except as stated immediately above, nothing which has been stated or illustrated is intended or should be interpreted to cause a dedication of any component, step, feature, object, benefit, advantage, or equivalent to the public, regardless of whether it is or is not recited in the claims. The scope of protection is limited solely by the claims that now follow, and that scope is intended to be broad as is reasonably consistent with the language that is used in the claims. The scope of protection is also intended to be broad to encompass all structural and functional equivalents.
This Application is continuation-in-part patent application of U.S. non-provisional patent application Ser. No. 17/536,259, filed on Nov. 29, 2021, titled “Ericsson Cycle Turbine Engine,” by inventor Geoffrey Robert Kemmerer, the contents of which are incorporated herein by this reference and to which priority is claimed. U.S. non-provisional patent application Ser. No. 17/536,259 claims the benefit of U.S. provisional patent application No. 63/121,580, filed on Dec. 4, 2020, titled “Ericsson Cycle Turbine Engine,” by inventor Geoffrey Robert Kemmerer, the contents of which are incorporated herein by this reference and to which priority is claimed.
The invention described herein may be manufactured and used by or for the government of the United States of America for governmental purposes without the payment of any royalties thereon or therefor.
Number | Name | Date | Kind |
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4984432 | Corey | Jan 1991 | A |
9618013 | Cherry et al. | Apr 2017 | B2 |
20150023807 | Cherry | Jan 2015 | A1 |
Number | Date | Country | |
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63121580 | Dec 2020 | US |
Number | Date | Country | |
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Parent | 17536259 | Nov 2021 | US |
Child | 17955705 | US |