Component for containing fluid fuel

Abstract

A component (1) for containing a fluid fuel to be impacted by shock waves incident on the component (1). The component (1) comprises: a chamber (5) configured to contain a fluid fuel; and a fuel filling line (3) configured to allow fluid fuel to be supplied to the chamber (5). At least a portion of the fuel filling line (3) follows a non-linear path.

Description

[0001] This invention relates to a component for containing fluid fuel, which will be subjected to a shock wave incident on the component. In particular, this invention relates to a component for containing fluid fuel, which will be subjected to a high-pressure quasi-spherical shock wave incident on the component, thereby generating a high local energy concentration within the fuel.

[0002] A component for containing fluid fuel to be impacted typically includes a chamber containing the fuel and one or more filler lines in the form of radial tubes passing through the component. The filler lines allow fuel to be supplied to the chamber. In such a component, it is advantageous to have tight control over the characteristics of the shock wave and the condition of the fuel, but the filler lines can introduce inconsistencies into the component, which may interfere with the characteristics of the shock wave. Furthermore, after the shock wave has struck the component, the filler lines can allow material (e.g., component material and / or external material) to be ejected downwards along the filler lines and into the chamber, thus negatively affecting the condition of the fuel.

[0003] The present invention aims to provide alternative component designs that reduce the harmful effects of filled pipelines.

[0004] From a first perspective, the present invention provides a component for containing fluid fuel, the fluid fuel being subjected to a shock wave incident on the component, the component comprising: A chamber configured to contain fluid fuel; and A fuel filling line configured to allow fluid fuel to be supplied to the chamber; At least a portion of the fuel filling pipeline follows a non-linear path.

[0005] Therefore, the present invention provides a component capable of holding (e.g., containing) fluid fuel (e.g., liquid and / or gas) such that the fluid fuel can be exposed to a shock wave. In particular, the component can be configured to hold the fluid fuel in a chamber such that the fluid fuel can be exposed to a high-pressure shock wave, thereby causing the fluid fuel to collapse and energy to concentrate within the fluid fuel, which may create the necessary conditions for nuclear fusion.

[0006] As will be seen, using the components according to the invention, fluid fuel can be supplied to the chamber via a fuel-filled pipeline, but the nonlinear path of the fuel-filled pipeline reduces or even eliminates the presence of material jets and / or exhaust gas impacts. Therefore, the interaction of the shock wave with the fluid fuel in the chamber is unaffected by such material jets and / or exhaust gas impacts, potentially leading to more efficient fuel collapse and thus higher fusion yields.

[0007] In one embodiment, the component includes a body. The body may include an inner wall and an outer wall. The outer wall may define the outer surface of the component. In some embodiments, at least a portion of the outer wall and / or the inner wall may be curved.

[0008] The body (e.g., the inner wall of the body) preferably defines a chamber configured to contain fluid fuel. The body (e.g., the inner wall of the body) preferably defines the periphery (surface area) of the chamber, such as the entire (surface area) periphery of the chamber (excluding the filling pipeline).

[0009] The body preferably also defines a fuel filling line. Preferably, the fuel filling line extends between the exterior of the component and the chamber (e.g., through the body of the component). Thus, preferably, the fuel filling line is configured to provide fluid communication between the exterior of the component and the chamber (i.e., fluidly connecting the exterior of the component and the chamber), for example, the chamber and the exterior of the component may be fluidly connected via the fuel filling line.

[0010] A linear path is a path in which the fuel filling line extends in a single direction between the outer and inner walls of a component. It should be understood that the term "non-linear" is intended to cover filling lines that include at least one change in direction along their path between the outer and inner walls of a component, such as curved paths, stepped paths, paths including one or more corners, zigzag paths, etc. Paths with multiple corners can be considered maze-like paths.

[0011] In an embodiment, the component (e.g., the body of the component) (except for the fuel filling line) is rotationally symmetrical about an axis of symmetry, such as an axis passing through the component (e.g., the body of the component) (e.g., the center of the body of the component) (e.g., an axis passing through the chamber (e.g., the center of the chamber)).

[0012] In embodiments, components (e.g., the body of a component) are configured to (e.g., substantially) manipulate input shock waves. It should be understood that, in order to be configured to manipulate input shock waves, components are designed to manipulate shock waves in a specific and intentional manner. Therefore, elements that have some influence on the propagation of shock waves solely due to their construction, but are not designed or intended to have a specific influence on input shock waves, should not be construed as being configured to manipulate input shock waves.

[0013] In an embodiment, manipulating the shock wave includes one or more of the following: accelerating the shock wave, decelerating the shock wave, reflecting a portion of the shock wave (e.g., reflecting a portion of the shock wave multiple times, such that portions of the shock wave are superimposed), and changing the shape of the shock wave by decelerating and / or accelerating different portions of the shock wave in different ways (e.g., slowing down a portion of the shock wave aligned with the chamber, such that the shock wave can bend around the chamber).

[0014] In one embodiment, the body is configured to spherically focus the input shock wave (e.g., toward the chamber (e.g., the center of the chamber)).

[0015] In an embodiment, the body has a sufficiently large thickness to effectively manipulate the input shock wave. The thickness of the body of the component can be defined as the shortest distance between the inner and outer walls (e.g., in a plane perpendicular to the axis of symmetry of the component) (e.g., from the chamber to the outside of the component (the body of the component).

[0016] In one embodiment, the thickness of the body is similar to (e.g., substantially equal to) the maximum size of the chamber (e.g., diameter). In another embodiment, the thickness of the body is greater than the maximum size of the chamber (e.g., diameter).

[0017] In an embodiment, the overall volume of the component (e.g., including the volume of the body and the cavity defined by the body) is significantly larger than the volume of the cavity.

[0018] In an embodiment, the thickness of the body is greater than 1 / 10 of the maximum size (e.g., diameter) of the cavity, for example, greater than 1 / 5 of the maximum size (e.g., diameter) of the cavity, for example, greater than 3 / 10 of the maximum size (e.g., diameter) of the cavity, for example, greater than 2 / 5 of the maximum size (e.g., diameter) of the cavity, for example, greater than half of the maximum size (e.g., diameter) of the cavity.

[0019] Components (e.g., the body of a component) may have any suitable and desired size, for example, to be determined by the specific application of the component. In one embodiment, the diameter and / or maximum size of the component is between 0.1 mm and 100 mm, for example between 1 mm and 50 mm, for example between 2 mm and 10 mm, for example about 3 mm, 5 mm or 8 mm.

[0020] In the embodiments, the thickness of the body is between 0.025 mm and 25 mm, for example between 0.25 mm and 12.5 mm, for example between 0.5 mm and 2.5 mm, for example about 0.75 mm, 1.25 mm or 2 mm.

[0021] In an embodiment, the maximum size of the chamber (e.g., diameter) is between 0.05 mm and 50 mm, for example between 0.5 mm and 25 mm, for example between 1 mm and 5 mm, for example about 1.5 mm, 2.5 mm or 4 mm.

[0022] In an embodiment, the width (e.g., diameter) of the fuel filling line is less than 100 micrometers, for example less than 50 micrometers, for example less than 10 micrometers, for example less than 5 micrometers, for example less than 2 micrometers.

[0023] In one embodiment, the filling conduit has a proximal end leading to a chamber (e.g., forming an opening in the inner wall of the body) and a distal end leading to the exterior of the component (e.g., forming an opening in the outer wall of the body).

[0024] In one embodiment, at least a portion of the fuel filling line follows a helical path.

[0025] In such an embodiment, the incident (and propagating) shock wave (e.g., the shock wave front) is not perpendicular to the central axis of the filling line as in the case of a linear radial filling line and a shock wave incident in the radial direction. Therefore, an acute angle is formed at the point where the shock wave front contacts the inner wall of the filling line. This point moves downwards along the filling line toward the chamber as the shock wave front propagates toward it. If this point moves downwards along the filling line faster than the impact of the material jet and / or the exhaust gas, the material jet and / or the exhaust gas will not reach the fuel in the chamber until after the shock wave front has reached it, and thus the problems associated with the material jet and / or the exhaust gas can be avoided. It should be understood that this point is not a moving physical substance; it is merely the point where the shock wave front intersects the inner wall.

[0026] In this embodiment, at least a portion of the fuel filling line follows an Archimedean spiral path. At each point on the portion of the filling line along the Archimedean spiral path, the fuel filling line forms the same angle with the radial direction (i.e., the propagation direction of the input spherical shock wave). The radial direction can be defined, for example, as the direction radially outward from the center of the component (e.g., the chamber of the component) in a plane perpendicular to the axis of symmetry of the component. Therefore, the shape of the fuel filling line has the same effect throughout the entire portion of the filling line along the Archimedean spiral path.

[0027] In an embodiment, the component (e.g., the body of the component) has a circular cross-section, for example, in a plane perpendicular to the axis of symmetry of the component (e.g., in the plane where the fuel filling line is located).

[0028] In one embodiment, the chamber has a circular cross-section, for example, in the plane where the fuel filling line is located.

[0029] The shape of the component and / or chamber can be adapted, for example, according to the characteristics of the shock wave and how the shock wave characteristics are manipulated, in any suitable and desired manner. In embodiments, the component (e.g., the body of the component) and / or chamber is substantially spherical.

[0030] In some embodiments, the component has an elliptical cross-section, for example, in a plane parallel to (e.g., encompassing) the component's axis of symmetry. Therefore, in some embodiments, the component is substantially oval (egg-shaped). An oval component can facilitate further manipulation (e.g., focusing) of the shock wave as it propagates into the component toward the chamber.

[0031] Preferably, one end of the oval component is more tapered, while the other end is more rounded. Preferably, the component has a maximum dimension (e.g., the longest dimension (major axis) of the oval body) that is parallel to (e.g., coaxial) the axis of symmetry of the component.

[0032] In an embodiment, the axis of symmetry of the (e.g., oval) component is coaxial with the axis of symmetry of the (e.g., spherical) chamber.

[0033] In one embodiment, the portion of the fuel filling line that follows an Archimedean spiral path forms an angle φ with the radial direction of the component at any point on the plane in which the fuel filling line lies.

[0034] In one embodiment, the fuel filling line is configured such that φ is greater than a first threshold. The first threshold can be the angle at which the material jet no longer reaches the chamber. Therefore, in such an embodiment, the negative impact of the material jet on fuel collapse can be avoided.

[0035] In this embodiment, the first threshold is in the range of 30° to 50°.

[0036] In one embodiment, the fuel filling line is configured such that φ is greater than a second threshold. The second threshold can be the angle at which the exhaust gas impact no longer reaches the chamber. Therefore, in such an embodiment, any negative impact on fuel collapse (e.g., lack of symmetry in the overall impact state) can be avoided.

[0037] In one embodiment, the fuel filling line is configured such that φ is less than a second threshold. The second threshold can be the angle at which the exhaust gas impact no longer reaches the chamber. Therefore, in such an embodiment, the exhaust gas impact can be allowed to reach the fluid fuel in the chamber. This can be advantageous because the exhaust gas impact can act as a preconditioner (e.g., preheater or precompressor) of the fluid fuel.

[0038] In this embodiment, the second threshold is in the range of 50° to 75°.

[0039] In this embodiment, the fuel filling line follows a path that includes one or more bends. The bends can help mitigate the impact of any material jet and / or exhaust gas.

[0040] In one embodiment, one or more of the corners are approximately 90°.

[0041] In embodiments (e.g., when the component has a circular cross-section), the fuel filling line includes, for example, one or more circumferential portions and one or more radial portions in the plane where the fuel filling line is located. In such embodiments, any material jets generated in the radial portions and / or exhaust gas impacts may be disrupted by the subsequent circumferential portions.

[0042] In embodiments, the fuel filling line may include one or more helical (e.g., Archimedes' helix) sections. In embodiments, the fuel filling line section near the chamber (e.g., the final section) may include a helical section. Such an embodiment may be advantageous compared to a radial fuel filling line section near the chamber, because it would allow any material jets and exhaust gas impacts generated in that final radial section to propagate into the chamber with minimal resistance. However, by forming the fuel filling line section near the chamber as a helical section, the advantages of helical filling lines discussed herein can be achieved for the section near the chamber.

[0043] In one embodiment, the component includes a first portion and a second portion, wherein the first portion and the second portion are configured to combine via adjacent surfaces on each of the first portion and the second portion to define a chamber. Such an embodiment may facilitate the manufacture of the component.

[0044] The first and second portions can be connected in any suitable and desirable manner to form a component. In some embodiments, the first portion may rest on the second portion (e.g., on top of the second portion), such that the first and second portions are adjacent to each other. Preferably, the first and second portions together form the body of the component. Preferably, the first and second portions together define a cavity.

[0045] The first and second portions can be any suitable and desired shape. In some embodiments, the first and / or second portions of the component are substantially rotationally symmetric about an axis (i.e., an axis of symmetry), such as an axis passing through the component (e.g., the body of the component) (e.g., the center of the body of the component) (e.g., an axis passing through a cavity (e.g., the center of the cavity). In some embodiments, when the first and second portions are assembled in the component, the first and second portions share the same axis of symmetry, such that the component is rotationally symmetric about the axis of symmetry.

[0046] In some embodiments, the first portion and / or the second portion has a substantially circular cross-section, for example, in a plane perpendicular to its axis of symmetry. In some embodiments, the diameter of the circular cross-section may vary across the first portion and / or the second portion (e.g., along the length of the axis of symmetry).

[0047] In embodiments, the first portion and the second portion each include a body. The body (each of the first and / or second portions) preferably includes an inner wall and an outer wall. The outer wall may define the outer surface of the first and / or second portions respectively (and thus define the outer surface of the component (e.g., the body of the component) when the first and second portions are assembled to form a part). In some embodiments, at least a portion of the outer wall and / or the inner wall may be curved.

[0048] For example, when the first part and the second part are assembled to form a component, the first part (e.g., the inner wall of the first part) and the second part (e.g., the inner wall of the second part) preferably define a cavity together. The first part (e.g., the inner wall of the first part) and the second part (e.g., the inner wall of the second part) preferably define the periphery (surface area) of the cavity together, such as the entire (surface area) periphery of the cavity (excluding the filling conduit).

[0049] In some embodiments, the fuel filling line is formed as a groove in the adjacent surface of one or both of the first and second portions. For example, the fuel filling line may be etched or machined into the first portion (the surface of the first portion) and / or the second portion (the surface of the second portion). In some embodiments, the first and / or second portions are formed in a mold that includes protrusions in the desired shape of the fuel filling line.

[0050] In one embodiment, the component includes a plate configured to be sandwiched between adjacent surfaces of a first portion and a second portion, wherein a fuel filling line is formed as a groove or slot in the plate. Such an embodiment may facilitate component manufacturing because the fuel filling line can be formed separately from the first and second portions.

[0051] In an embodiment, the components and chambers have a circular cross-section in the plane where the fuel filling line is located (e.g., in the plane where the fuel filling line is located). Preferably, the plate is annular.

[0052] In one embodiment, the component includes multiple filling lines (e.g., two filling lines). In an embodiment including two filling lines, the first line may be configured to connect to a fuel supply source to supply fluid fuel to the chamber, and the second filling line may be connected to a pressure sensor. By measuring the pressure at the second filling line, it can be determined whether fluid fuel has reached the chamber from the first filling line (e.g., the filling line is not blocked or fault-free), since the chamber is located between the first and second filling lines (e.g., the first and second filling lines are fluidly connected via the chamber). In another embodiment, the pressure sensor may be replaced by any other type of sensor capable of determining the presence of fluid fuel in the second filling line.

[0053] The component can be formed from any suitable and desired material. In some embodiments, the component is formed from a high-Z material. In some embodiments, the component is formed from a metal and / or a metal alloy. For example, the component can be formed from one or more of the following: gold, tungsten, copper, tantalum, and / or alloys containing one or more of gold, tungsten, tantalum, and / or copper. These materials can be advantageous due to their high density, high toughness, and / or high strength.

[0054] According to a second aspect of the present invention, a system is provided, the system comprising: Components as outlined in this article; and A device configured to generate (e.g., quasi-spherical) shock waves to be incident on the component.

[0055] The component (e.g., the body of the component) can be arranged to be used with any suitable and desired fuel. In embodiments, the fluid includes fuel, such as fuel for nuclear fusion. In embodiments, the fluid comprises one or more (e.g., all) of the following: deuterium, liquid deuterium, tritium, liquid tritium, deuterium-tritium (DT) gas, and deuterium-tritium (DT) liquid.

[0056] It should be understood that, as used herein, the term "impact resistance" is intended to mean "the pressure that must be applied to a medium in order to impart a unit particle velocity to a portion of that medium" (Henderson, "On the refraction of shockwaves," *Journal of Fluid Mechanics*, January 1989, Vol. 198, pp. 365-386). This impact resistance is equal to the product of the impact velocity and the density of the unimpacted material.

[0057] In one embodiment, the component includes multiple fill lines (e.g., two fill lines).

[0058] In an embodiment that includes two filling lines, the first line is configured to be connected to a fuel supply source to supply fluid fuel to the chamber, and the second filling line is configured to be connected to a pressure sensor.

[0059] In one embodiment, the system includes a pressure sensor fluidly connected to a second filling line.

[0060] Certain embodiments of the invention will now be described by way of example only with reference to the accompanying drawings, in which: Figure 1 A cross-sectional view of a component with conventional filling piping is shown; Figure 2 It is a simulated still image of the output of a conventional filling pipeline; Figure 3A cross-sectional view of a component with helical filling tubing is shown; Figure 4 It shows Figure 3 A schematic diagram of the components in use; Figures 5a to 5d Simulated still images of shock waves incident at different angles on a component with helical filling lines are shown; Figures 6a to 6d Simulated still images focused on the output of a spiral-filled pipeline at different angles are shown; Figure 7 A cross-sectional view of a component with another infilled piping design is shown; Figure 8 A close-up cross-sectional view of a component with another infilled piping design is shown; Figure 9 An exploded perspective view of a component with helical filling tubing is shown; Figure 10 An exploded perspective view of a component with an alternative infill pipeline design is shown. Figure 11 An exploded perspective view of a component with an alternative infill pipeline design is shown; and Figure 12 An exploded perspective view of another component is shown.

[0061] It should be understood that, as used herein, the terms “top,” “bottom,” “upper,” “lower,” “side,” “base,” “vertical,” “horizontal,” etc., are included for clarity and are intended to refer to the orientation shown in the accompanying drawings. It should be understood that, in use, components and systems may operate in any suitable and desired orientation.

[0062] It should be understood that each of the components described herein can be configured for use as part of a nuclear fusion process. Therefore, the fluid fuel mentioned herein can be a fusion-capable fuel, such as deuterium. If the fuel is placed under sufficiently high pressure, it will collapse, resulting in intense pressure and temperature within the collapsing fluid fuel, which may be sufficient to trigger fusion.

[0063] Figure 1 A cross-sectional view of a component 1 having a conventional radial filling line 3 is shown. Component 1 is circular in the plane of the cross-section. Component 1 defines an inner chamber 5 defined by a chamber wall 8. The inner chamber 5 is also circular in the plane of the cross-section. The filling line 3 allows fluid (e.g., gaseous) fuel to enter the inner chamber 5.

[0064] Although the shape of any component described herein can be adapted to desired shock wave characteristics, in the illustrated embodiment, component 1 is spherical. The filling conduit 3 has a proximal end 7 leading to chamber 5 and a distal end 9 leading to the exterior of component 1.

[0065] In use, fuel is supplied to the distal end 9 of the filling line 3, and the fuel passes through the filling line 3 and enters the chamber 5 at the proximal end 7.

[0066] Now about Figure 2 To explain the operation of the linear radial fuel line, the figure shows a still image taken from a simulation of a (e.g., spherical) shock wave incident on component 1 having a linear radial filler line 3.

[0067] The problem with linear radial fill lines (such as fill line 3 in component 1) is that when an impact in component 1 reaches fill line 3, the shock wave forces a lower-density material into fill line 3. This lower-density material can include lower-density materials used within the component itself, as well as lower-density materials from components of the system employing the component.

[0068] For example, the component can be suspended in a certain volume of PMMA (polymethyl methacrylate). This material forms a jet that travels faster than the impact in component 1, causing the material jet to penetrate the fuel in chamber 5 before the shock wave reaches the fuel. This introduces impurities into the fuel, which negatively impacts the energy concentration generated by the shock wave. Figure 2 The material jet 11 can be clearly seen in the simulated still image. Furthermore, it can be seen that the material jet 11 significantly precedes the shock wave 24 (e.g., Figure 2 (The darker areas are visible in the image) reach chamber 5. Therefore, the fuel in chamber 5 is significantly contaminated before the shock wave reaches chamber 5.

[0069] In the case of gaseous fuel, another potential problem with linear radially filled pipelines is the exhaust gas impact 13, which also... Figure 2 As shown in the diagram, the ejected gas impact is a product of residual fuel present in the filling line 3. This fuel is impacted before the shock wave reaches the fuel in chamber 5, and the gas impact in the filling line 3 is then ejected into chamber 5, resulting in irregularities in the fuel inside the chamber. This irregularity can negatively affect the fuel collapse characteristics. However, in this embodiment, the ejected gas impact may be advantageous, as will be explained below.

[0070] Figure 3A cross-sectional view of component 21 according to an embodiment of the present invention is shown. Component 21 has a chamber 25 (defined by a chamber wall 26) and a filling conduit 23. The filling conduit 23 has a proximal end 27 and a distal end 29, and is formed as part of an Archimedean spiral (e.g., https: / / mathworld.wolfram.com / ArchimedesSpiral.html (as defined).

[0071] Regarding the supply of fuel to chamber 25, the filling line 23 functions in the same manner as the filling line 3 provided in component 1. The filling line 23 forms an angle θ with the chamber wall 26 at its proximal end 27 (i.e., with the tangent 28 of the chamber wall 26 at the proximal end 27). Due to the Archimedean spiral shape of the filling line 23, at every point on the filling line 23, the filling line 23 also forms an angle θ with the tangent of the spherical impact shock wave at all points on the filling line 23. Therefore, at any given point, the filling line forms an angle φ with the radial direction 30, where φ = θ - 90°.

[0072] Reference Figure 4 The diagram illustrates the function of the helical filling line 23 as a shock wave propagates through component 21 toward chamber 25. For the purposes of the following explanation, the helical filling line 23 will be described in two dimensions. Figure 4 The situation is described. Therefore, the filling conduit will be considered to have an inner wall and an outer wall, where the inner wall is the wall closer to chamber 25.

[0073] from Figure 4 As can be seen, due to the helical shape of the filling line 23, the shock wave front 24 is not perpendicular to the central axis of the filling line 23 as in the case of the linear radial filling line 3. Therefore, an acute angle is formed at the point 28 where the shock wave front 24 contacts the inner wall of the filling line 23. As the shock wave front 24 propagates toward the chamber 25, point 28 moves downward toward the chamber along the filling line 23. If point 28 moves downward along the filling line 23 faster than the material jet 11, the jet will not reach the fuel in the chamber 25 until after the shock wave front 24 has reached the fuel in the chamber 25, and thus the problems associated with material ejection can be avoided.

[0074] Similarly, if point 28 moves downward along the filling line 23 faster than the exhaust gas impact 13, then the exhaust gas impact will not reach the fuel in chamber 25 until after the shock wave front 24 has reached the fuel in chamber 25, and thus any problems associated with the exhaust gas impact 13 can be avoided. It should be understood that point 28 is not a moving physical substance; it is merely the point where the shock wave front intersects with the inner wall.

[0075] The larger the value of θ, the faster point 28 moves. Therefore, there exists a threshold for θ at which point 28 travels faster than the material jet, and θ has a value at which point 28 travels faster than the exhaust gas impact. For the component 21 shown, these thresholds have been determined using simulations, as per [reference to...]. Figures 5a to 5d The explanation given.

[0076] Figures 5a to 5d Each of them is shown in the simulated incident on component 21 (according to Figure 3 Four still images taken at different times during the process of a spherical shock wave on the component (shown). The first, second, third, and fourth still images in each time series were taken at t = 0, t = 100 ns, t = 200 ns, and t = 280 ns, respectively, where t = 0 is the point where the shock wave first 24 is incident on the outer surface of component 21, and the subsequent still images show the progress of the shock wave first 24 through component 21.

[0077] Figure 5a The component 21 shown has a spiral-filled conduit 23, where θ = 120°. Figure 5a As can be seen in the third still image and most clearly in the fourth still image, a large jet of material is entering the fuel in chamber 25.

[0078] Figure 5b The component 21 shown has a spiral-filled conduit 23, where θ = 130°. Figure 5b In the fourth still image, it can be seen that the material jet is entering the fuel in chamber 25, but this jet is far less than... Figure 5a The jet present in the jet is significant. Therefore, increasing the θ value will reduce the jetting effect.

[0079] Figure 5c The component 21 shown has a spiral-filled conduit 23, where θ = 150°. Figure 5b As can be seen, no material jet enters the fuel in chamber 25.

[0080] same, Figure 5d The component 21 shown has a spiral filling line 23, where θ = 160°, and no material jet enters the fuel in the chamber 25.

[0081] Figures 6a to 6d The simulated still images captured at t = 260 ns are also shown. Figures 6a to 6d The still image is a close-up of the proximal end of the spiral-filled pipeline, allowing for a clearer view of any exhaust gas impacts 13 and material jets 11. Figure 6aThe value of the filled pipe 23 is θ = 120°. Figure 6b The value of the filled pipe 23 is θ = 140°. Figure 6c The value of the filled pipe 23 is θ = 150°, and Figure 6d The value of the filled pipeline 23 is θ = 160°.

[0082] exist Figure 6a In the image, both the exhaust gas impact 13 and the material jet 11 can be seen. Figure 6c and Figure 6d In the middle, neither the material jet 11 nor the exhaust gas impact 13 is visible. Figure 6b In the middle, there is no material jet 11, but the exhaust gas impact can be seen inside the filling pipeline 23 before the shock wave 24.

[0083] from Figures 5a to 5d and Figures 6a to 6d As can be seen from the simulation shown, the threshold of θ for point 28 to travel faster than the material jet (and therefore no material jet enters chamber 25) is between 120° and 140°, and the threshold of θ for point 28 to travel faster than the exhaust gas impact is between 140° and 150°. Since φ = θ - 90°, if the threshold is considered as the value of φ (i.e., in terms of the angle formed with the radial direction), then for this example, the threshold of φ for point 28 to travel faster than the material jet (and therefore no material jet enters chamber 25) is between 30° and 50°, and the threshold of φ for point 28 to travel faster than the exhaust gas impact is between 50° and 60°.

[0084] If the component is designed to eliminate any material jets and any exhaust gas impacts, a larger θ value would appear appropriate. However, a helical filler line with a larger θ value can introduce additional complexity. A larger θ value results in a longer filler line, thus reducing the overall density of the component. This reduction in density can affect how shock waves propagate through the component and, consequently, the successful collapse of the fuel. Therefore, a trade-off must be found between minimizing material jets and / or gas impacts and maintaining sufficient component density.

[0085] from Figures 6a to 6d It can be seen that the exhaust gas impact threshold is greater than the material jet threshold. In an embodiment, a value of θ between the material jet threshold and the exhaust gas impact threshold can be selected, such that there is an exhaust gas impact but no material jet. In an embodiment, it may be advantageous to use the exhaust gas impact to pre-condition (i.e., preheat / pre-compress) the fuel in the chamber before the shock wave reaches chamber 25.

[0086] Figure 7A cross-sectional view of a component 31 with a filler conduit 33 is shown, the filler conduit including a plurality of bends 32 located in the path of the filler conduit 33. In the illustrated embodiment, each bend 21 is a 90° bend. Due to the bends 32, the filler conduit 23 includes a plurality of radial portions 36 and a plurality of circumferential portions 34. Each pair of circumferential portions 34 is connected to the radial portion 36 via the bends 32. In the following, Figure 7 The filling tube design shown, which includes multiple bends, will be referred to as a "maze-style" filling tube.

[0087] and Figure 3 Similar to the spiral-filled line 23 shown, the labyrinthine-filled line 33 is designed to reduce or eliminate the presence of material jets and / or exhaust gas impacts at chamber 35. The material jets and / or exhaust gas impacts are forced to change direction at each of the corners 32. This change of direction reduces the velocity of the material, allowing the shock wave front to reach the fuel in chamber 35 before any material jets and / or exhaust gas impacts.

[0088] More specifically, the radial portion 36 represents the worst-case scenario, thus allowing the material jet and the impact of the expelled gas to propagate freely toward the chamber 35 within these portions. However, the circumferential portion 34 represents the best-case scenario, as it is parallel to the shock wave front (and therefore perpendicular to the propagation direction), thus preventing the material jet and the impact of the expelled gas from propagating toward the chamber 35 at all. Its purpose is to eliminate any jet and impact generated in the radial portion 36 by the subsequent circumferential portion 34.

[0089] The shape of the labyrinthine filling tube 33 (including the number of radial portions 36, circumferential portions 34, and / or corners 32) can be varied to help ensure that the fuel in the chamber 35 reaches the shock wave before any material jet and / or exhaust gas impact. Therefore, a large number of corners 32 can be used if the component is designed to eliminate any material jet and any exhaust gas impact.

[0090] However, if the filler line 33 includes a large number of bends 32, the filler line 33 will be longer, and therefore the overall density of component 31 will be reduced. This reduction in density may affect how shock waves propagate through the component, and thus may affect the successful collapse of the fuel. Therefore, a trade-off can be found between minimizing material jets and / or gas impacts and maintaining sufficient density in the component.

[0091] It can be seen that Figure 7 The gas-filled line 33 shown has a final portion near the chamber 35, which is a radial portion 36. Therefore, any material jets and exhaust gas impacts generated in this final radial portion will propagate into the chamber 35 with minimal resistance.

[0092] Figure 8 A cross-sectional view of component 41 with filling pipe 43 is shown. Figure 8 The filling line 43 in component 41 shown is Figure 7 The shown component 31 is a variant of the filler conduit 33, and follows the same path as the filler conduit 43, except that the final (proximal) radial portion is replaced by a helical portion 42. In the illustrated embodiment, the helical portion follows the path of an Archimedean spiral and as described above regarding... Figure 2 and Figure 3 It works as discussed.

[0093] Figure 9 Component 21 is shown (e.g., Figure 3 The diagram shows a perspective view of component 21. In this embodiment, component 21 is formed by a first portion 4 and a second portion 6. The first portion 4 and the second portion 6 each have adjacent surfaces 14 and 16. When adjacent surfaces 14 and 16 are placed together, the first portion 4 and the second portion 6 combine to define a chamber 25 in component 21.

[0094] As from Figure 9 As can be seen, the filler line 23 is formed as a groove in the adjacent surface 16 of the second portion 6. This groove can be machined or laser-etched into the adjacent surface 16. Therefore, the filler line 23 can have a generally semi-circular cross-section in a plane perpendicular to its axis. It should be understood that the filler line 23 can also be formed as a groove in the adjacent surface 14 of the first portion 4.

[0095] Furthermore, in embodiments where a tubular filling line is desired (e.g., having a circular cross-section in a plane perpendicular to its axis), complementary grooves can be cut into both the adjacent surfaces 14, 16 of the first portion 4 and the second portion 6, such that the tubular filling line is defined when the first and second portions are aligned. The advantage of cutting the filling line in only one adjacent surface is that rotational alignment of the first portion 4 and the second portion 6 may not be necessary.

[0096] Although in this embodiment, component 21 is formed by two parts 14 and 16, it should be understood that component 21 can be formed by any suitable and desired number of parts.

[0097] Figure 10A perspective view of component 51 is shown, which is formed by a first portion 54 and a second portion 56, wherein a joint 10 is provided between the first portion 54 and the second portion 56, the joint 10 including a step. In this embodiment, when viewed in a cross-section taken in a plane parallel to the axis 12 of component 51, the joint 10 includes a first radial portion 10a, a vertical portion 10b, and a second radial portion 10c. The radial portions 10a and 10c are also substantially perpendicular to the vertical portion 10b. In the illustrated embodiment, the vertical portion 10b and the second radial portion 10c are formed by an annular protrusion on the adjacent surface 516 of the second portion 56 and a complementary recess on the adjacent surface of the first portion 54.

[0098] The filling line 53 of component 51 is as follows: Figure 7 The described labyrinthine filling conduit includes multiple radial sections, circumferential sections 533, and corners. Further, the filling conduit 53 is configured to... Figure 9 A similar manner as described is formed as a groove in the adjacent surface 516 of the second portion 56. Due to the vertical portion 10b of the connector 10, the filling conduit 53 includes a vertical portion 57. This vertical portion 57 functions in the same manner as the circumferential portion 533, as it is parallel to the shock wave front.

[0099] Figure 11 It shows as Figure 10 A perspective view of component 61, a variant of component 51. Component 61 includes a spiral-filled conduit 63 instead of a labyrinthine-filled conduit 53, the spiral-filled conduit as described above. Figure 2 , Figure 3 and Figure 9 It forms and functions as described. Component 63 is otherwise identical to component 53, therefore regarding Figure 10 The given descriptions of joints and adjacent surfaces also apply. Figure 11 .

[0100] Figure 12 An exploded view of component 71, formed in an alternative manner, is shown. Figure 9 , Figure 10 and Figure 11 Like components 41, 51, and 61 shown, component 71 is formed in two parts that fit together to form chamber 75. However, with Figure 9 , Figure 10 and Figure 11 The components 41, 51, and 61 shown are different. Figure 12 The filling conduit 73 of the shown component 71 is not defined by either of the main parts. Instead, component 71 includes a plate 72 sandwiched between the two halves. The plate 72 defines the filling conduit 73.

[0101] Any of the methods described above (laser etching, machining, etc.) can be used to form the filled pipelines 73 in the board 72. Figure 12 In this design, component 71 has a labyrinthine filling pipeline, but it should be understood that plate 72 can be used to define any suitable filling pipeline shape (e.g., spiral). Forming the filling pipeline in a plate can be advantageous from a manufacturing perspective, especially when performing experiments in which many different filling pipeline designs are tested. By forming the filling pipeline in a plate, the main parts of the component can be standardized, which facilitates mass production.

[0102] In each of the illustrated embodiments, only a single fill line is shown. In embodiments, multiple fill lines (e.g., two fill lines) may be present in the components according to this disclosure. In an embodiment including two fill lines, the first line may be connected to a fuel supply source to supply fluid fuel to the chamber, and the second fill line may be connected to a pressure sensor. By measuring the pressure at the second fill line, it can be determined whether fluid fuel has reached the chamber from the first fill line (e.g., the fill line is not blocked or fault-free), since the chamber is located between the first and second fill lines. In embodiments, the pressure sensor may be replaced by any other type of sensor capable of determining the presence of fluid fuel in the second fill line.

[0103] In each of the illustrated embodiments, the entire filling conduit has the described nonlinear shape. However, in some embodiments, the filling conduit may only have a nonlinear portion (e.g., a portion near the chamber). This nonlinear portion may be sufficient to disrupt any material jets and / or exhaust gas impacts present in the linear portion of the filling conduit (e.g., a portion away from the chamber). Such embodiments may be easier to manufacture.

[0104] The components described herein can be manufactured in any suitable and desirable manner. In some embodiments, these components can be formed on a removable mandrel. For example, the mandrel can be dissolvable or collapseable to allow removal from the component after it has been formed. In some embodiments, the components can be formed in a mold. For example, the components can be formed from metal cast in a mold.

[0105] The component can be formed as a single piece or as two or more separate parts. If the component is formed as a single piece, it can later be separated into two or more parts (e.g., using a machine or laser cutting). Even if the component is formed as two or more parts, at least one surface of the component can be cut (e.g., using a machine or laser). This may help ensure that the two or more parts of the component fit together. It is important that the liquid fuel does not leak from the internal chambers of the component, therefore precise shaping or cutting of the component is required to ensure a flush fit between the parts.

[0106] Two or more parts can be placed together in any suitable and desired manner to form a component. In some embodiments, a first part of the component is lowered onto a second part of the component. To facilitate this, the first and second parts of the component are configured to move relative to each other in at least one direction.

[0107] The components described herein may be formed from a single material or a combination of different materials. In one embodiment, the component is formed from a single material, wherein the single material is a high impact resistance material (such as tantalum). In other embodiments, the component may be formed from a combination of high impact resistance materials and low impact resistance materials (e.g., layered formation). The component may contain one or more of the following: tungsten, steel, aluminum, gold, PMMA, and copper.

Claims

1. A component for containing fluid fuel, the fluid fuel being subjected to a shock wave incident on the component, the component comprising: A chamber configured to contain the fluid fuel; as well as A fuel filling line configured to allow the fluid fuel to be supplied to the chamber; At least a portion of the fuel filling pipeline follows a non-linear path.

2. The component as claimed in claim 1, wherein, At least a portion of the fuel filling pipeline follows a helical path.

3. The component as claimed in claim 2, wherein, At least a portion of the fuel filling pipeline follows an Archimedes spiral path.

4. The component as claimed in claim 1, 2, or 3, wherein, The component has a circular cross-section in the plane on which the fuel filling line is located.

5. The component as claimed in claim 4, wherein, The portion of the fuel filling line that follows an Archimedean spiral path forms an angle φ with the radial direction of the component at any point on the plane in which the fuel filling line is located.

6. The component as claimed in claim 5, wherein, The fuel filling line is configured such that φ is greater than a first threshold.

7. The component as claimed in claim 6, wherein, The first threshold is in the range of 30° to 50°.

8. The component as claimed in claim 5, 6, or 7, wherein, The fuel filling line is configured such that φ is greater than the second threshold.

9. The component as claimed in claim 5, 6, or 7, wherein, The fuel filling line is configured such that φ is less than a second threshold.

10. The component as claimed in claim 8 or 9, wherein, The second threshold is in the range of 50° to 60°.

11. The component as claimed in any of the preceding claims, wherein, The fuel filling pipeline follows a path that includes one or more bends.

12. The component as claimed in claim 11, wherein, One or more of the corners are approximately 90°.

13. The component as claimed in claim 11 or 12, wherein, On the plane in which the fuel filling line is located, the component has a circular cross-section, and the fuel filling line includes one or more circumferential portions and one or more radial portions.

14. The component as claimed in any of the preceding claims, wherein, The component includes a first portion and a second portion, wherein the first portion and the second portion are configured to combine via adjacent surfaces on each of the first portion and the second portion to define the chamber.

15. The component as claimed in claim 14, wherein, The fuel filling line is formed as a groove in the adjacent surface of one or both of the first and second portions.

16. The component as claimed in claim 14, wherein, The component further includes a plate configured to be sandwiched between the adjacent surfaces of the first portion and the second portion, wherein the fuel filling line is formed as a groove or slot in the plate.

17. The component as claimed in claim 16, wherein, On the plane where the fuel filling line is located, the component and the chamber have a circular cross-section, and the plate is annular.

18. A system comprising: The component as described in any of the preceding claims; as well as A device configured to generate a shock wave to be incident on the component.

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