Suspension system for cryogenic storage tanks

Abstract

A cryogenic system includes a cryogenic tank containing a liquid cryogen, a vacuum vessel surrounding the cryogenic tank and providing a vacuum space between an inner surface of the vacuum vessel and an outer surface of the cryogenic tank. The cryogenic system further includes a suspension system disposed within the vacuum space to support the cryogenic tank within the vacuum vessel and to maintain the cryogenic tank in a desired position within the vacuum vessel. The suspension system includes a plurality of roller elements disposed within the vacuum space and contacting the inner surface of the vacuum vessel and the outer surface of the cryogenic tank.

Description

Technical Field

[0001] This disclosure relates to cryogenic systems, and more specifically to cryogenic systems for turbine engines. Background Technology

[0002] The propulsion systems of commercial aircraft typically include one or more aircraft engines, such as turbofan jet engines. A turbofan jet engine can be mounted in a corresponding position within the aircraft's wing, for example, using a pylon suspended below the wing. These engines can be powered by aviation turbine fuel, which is typically a combustible hydrocarbon liquid fuel with a desired carbon number, such as kerosene. Aviation turbine fuel is a relatively power-intensive fuel, relatively easy to transport, and remains in the liquid phase under most of the environmental operating conditions of an aircraft. This fuel produces carbon dioxide upon combustion, and improvements are needed to reduce these carbon dioxide emissions in commercial aircraft.

[0003] Furthermore, current cooling methods in conventional turbine engine applications use either compressed air or conventional liquid jet fuel. Using compressed air for cooling may reduce the efficiency of the engine system. Additionally, as mentioned earlier, conventional liquid jet fuel produces carbon dioxide.

[0004] Therefore, some turbofan jet engines use cryogenic liquid fuels, such as liquefied natural gas (LNG) or liquid hydrogen, which may be more environmentally friendly and cheaper than traditional liquid jet fuels.

[0005] Therefore, there is a desire for aircraft systems propelled by turbofan jet engines that can operate using cryogenic liquid fuel. Thus, this disclosure pertains to an improved cryogenic system for turbofan jet engines. Attached Figure Description

[0006] The complete and practical disclosure of this disclosure, including its best mode, is set forth in the specification with reference to the accompanying drawings, wherein:

[0007] Figure 1 This is a schematic perspective view of an aircraft with an engine according to an embodiment of the present disclosure.

[0008] Figure 2 It is along Figure 1 A schematic cross-sectional view of a turbine engine taken from line 2-2, which is used as... Figure 1 The generator of the aircraft shown.

[0009] Figure 3 This is a schematic diagram of an embodiment of a fuel system according to the present disclosure.

[0010] Figure 4This is a side view of an embodiment of a cryogenic fuel system for an engine according to the present disclosure.

[0011] Figure 5 This is a side view of an embodiment of a cryogenic fuel system for an engine according to the present disclosure, particularly showing a suspension system for a cryogenic fuel system having a plurality of roller elements with an insulating layer arranged between the roller elements.

[0012] Figure 6 yes Figure 5 Cross-sectional view of the cryogenic fuel system along line 6-6.

[0013] Figure 7 This is a side view of an embodiment of a row of roller elements of a radial suspension system for a cryogenic fuel system for an engine according to the present disclosure.

[0014] Figure 8 This is a side view of another embodiment of a cryogenic fuel system for an engine according to the present disclosure, particularly showing a radial suspension system with multiple roller elements for a cryogenic fuel system.

[0015] Figure 9 yes Figure 8 A cross-sectional view of a cryogenic fuel system.

[0016] Figure 10 This is a side view of another embodiment of a cryogenic fuel system for an engine according to the present disclosure, particularly showing a suspension system for the cryogenic fuel system having multiple roller elements that provide radial and axial suspension for the liquid fuel reservoir of the cryogenic fuel system.

[0017] Figure 11A and 11B yes Figure 10 Front and side views of the cryogenic fuel system.

[0018] Figure 12 This is a perspective view of an embodiment of a suspension system with multiple roller elements for a cryogenic fuel system for an engine, according to the present disclosure.

[0019] Figure 13 This is a flowchart of an embodiment of a method for assembling a cryogenic system according to the present disclosure. Detailed Implementation

[0020] Reference will now be made in detail to the present embodiments of this disclosure, one or more examples of which are illustrated in the accompanying drawings. The detailed description uses numerals and letter reference numerals to denote features in the drawings. Similar or analogous reference numerals in the drawings and description have been used to denote similar or analogous portions of this disclosure.

[0021] The term "exemplary" is used herein to mean "serving as an example, instance, or illustration." Any implementation described herein as "exemplary" is not necessarily to be construed as superior to or advantageous to other implementations. Furthermore, unless explicitly stated otherwise, all embodiments described herein should be considered exemplary.

[0022] Unless the context clearly indicates otherwise, the singular forms “a,” “one,” and “the” include plural references.

[0023] The term "turbine" refers to a machine that, together with one or more compressors, a heating section (e.g., a combustion section), and one or more turbines, produces torque output.

[0024] The term "gas turbine engine" refers to an engine that has a turbine as its power source, either entirely or partially. Examples of gas turbine engines include turbofan engines, turboprop engines, turbojet engines, turboshaft engines, and hybrid versions of one or more of these engines.

[0025] The term "combustion section" refers to any heat addition system used in a turbine. For example, the term combustion section can refer to a section that includes one or more of a knock combustion assembly, a rotating detonation combustion assembly, a pulse detonation combustion assembly, or other suitable heat addition assemblies. In some exemplary embodiments, the combustion section may include an annular burner, a cylindrical burner, a tubular burner, a vortex burner (TVC), or other suitable combustion systems, or combinations thereof.

[0026] Unless otherwise stated, the terms “low” and “high,” or their respective degrees of comparison (e.g., lower, higher, where applicable), when used with compressors, turbines, shafts, or spool components, refer to relative speeds within the engine. For example, “low turbine” or “low-speed turbine” defines a component configured to operate at a speed (e.g., maximum permissible speed) lower than that of the engine’s “high turbine” or “high-speed turbine.”

[0027] The terms "front" and "rear" refer to relative positions within a gas turbine engine or vehicle, and specifically to the normal operating posture of the gas turbine engine or vehicle. For example, in the case of a gas turbine engine, "front" refers to the position closer to the engine inlet, while "rear" refers to the position closer to the engine nozzle or exhaust port.

[0028] As used herein, the terms "axial" and "axially" refer to a direction and orientation that extends substantially parallel to the centerline of the gas turbine engine. Furthermore, the terms "radial" and "radially" refer to a direction and orientation that extends substantially perpendicular to the centerline of the gas turbine engine. Additionally, as used herein, the terms "circumferential" and "circumferentially" refer to a direction and orientation that extends in an arc around the centerline of the gas turbine engine.

[0029] Unless otherwise stated herein, the terms “connection”, “attachment”, etc., refer to direct connection, fixation or attachment, as well as indirect connection, fixation or attachment via one or more intermediate parts or features.

[0030] As used herein, the terms “first,” “second,” and “third,” etc., are used interchangeably to distinguish one component from another and are not intended to indicate the location or importance of the individual components.

[0031] As used throughout this specification and claims, approximate language is applied to modify any quantitative expression that may allow variation without altering its underlying function. Therefore, values ​​modified by one or more terms such as “approximately,” “approximately,” and “substantially” are not limited to specified exact values. In at least some cases, approximate language may correspond to the precision of the instrument used to measure the value, or the precision of the method or machine used to construct or manufacture the component and / or system. For example, approximate language may refer to margins of 1%, 2%, 4%, 10%, 15%, or 20%. These approximate margins may apply to a single value, one or both endpoints defining a numerical range, and / or margins between the endpoints.

[0032] Throughout this document and throughout the specification and claims, scope limitations are combined and interchanged, and unless the context or language otherwise indicates otherwise, such scopes are identified and include all subscopes contained herein. For example, all scopes disclosed herein include endpoints, and endpoints may be combined independently of each other.

[0033] Traditional cryogenic storage tanks require a suspension system to support the tank containing refrigerant from an external vacuum vessel. Traditional suspension systems, including suspension pipes or rods, are common when both the refrigerant tank and the vacuum vessel are made of metal. However, when the refrigerant tank or vacuum vessel is made of composite materials, suspension / rod implementation becomes more challenging. For example, when the refrigerant tank and / or vacuum vessel are made of composite materials, specialized suspension components must be integrated within the windings of the composite tank and / or vessel.

[0034] Therefore, this disclosure relates to an improved suspension system for cryogenic systems. Specifically, the suspension system of this disclosure supports the cryogenic vessel (e.g., an internal tank containing refrigerant) of the cryogenic system relative to a vacuum vessel (e.g., an outer container). Specifically, the refrigerant tank can be a liquid hydrogen (LH2) tank or any other cryogenic tank with double walls (e.g., containing LHe, LN2, LO2, etc.). Therefore, the suspension system can be used with any cryogenic tank in a vacuum environment. More specifically, in one embodiment, the suspension system may include a plurality of roller elements (e.g., balls or wheels) arranged in rails or connected together via suspension members to facilitate assembly and / or positioning of the cryogenic tank within the vacuum vessel. Thus, in one embodiment, the suspension system provides very low parasitic heat load and easy access to the internal vacuum vessel for servicing. For example, the roller elements are arranged in the radial space between the refrigerant tank and the vacuum vessel and can be mechanically anchored to the reinforcement of the vacuum vessel. Furthermore, since the roller elements of the system only make point contact with both the vacuum vessel and the refrigerant tank, the suspension system results in low vaporization of the solution. Furthermore, this suspension system provides only point-to-point contact between the roller elements and the cryogenic tank, and between the roller elements and the vacuum vessel, thus providing a suspension system with a length distribution along the central axis of the cryogenic tank. Moreover, the suspension system with the roller elements described herein provides a system with increased dynamic stiffness and reduced vibration.

[0035] Now refer to the attached diagram, Figure 1 A perspective view of an aircraft 10, which can be implemented in various preferred embodiments, is shown. As shown, the aircraft 10 includes a fuselage 12, wings 14 attached to the fuselage 12, and a tail 16. The aircraft 10 also includes a propulsion system that generates the thrust required to propel the aircraft 10 during flight, taxiing operations, and other similar activities. Figure 1 The propulsion system for the aircraft 10 shown includes a pair of engines 100. In this embodiment, each engine 100 is attached to one of the wings 14 in an underwing configuration via a pylon 18. Although the engines 100 are... Figure 1 The engine 100 is shown attached to the wing 14 in an underwing configuration, but in other embodiments, the engine 100 may have an alternative configuration and be coupled to other parts of the aircraft 10. For example, the engine 100 may additionally or alternatively include one or more aspects coupled to other parts of the aircraft 10, such as, for example, the tail 16 and the fuselage 12.

[0036] The following text will refer to Figure 2 Further description, Figure 1 Each of the engines 100 shown is capable of selectively generating propulsive thrust for the aircraft 10. The amount of propulsive thrust can be controlled, at least in part, based on the volume of fuel supplied to the turbine engine 100 via the fuel system 200 (see [link to fuel system 200]). Figure 3 In the embodiments discussed herein, the fuel is a refrigerant fuel, such as liquid hydrogen fuel or liquefied natural gas (LNG), which is stored in the liquid fuel storage tank 206 of the fuel system 200 (see...). Figure 3 In some embodiments, at least a portion of the liquid fuel storage tank 206 may be located in each wing 14. Figure 1 The liquid fuel tank 206 may be located within the fuselage 12 between the wings 14, and a portion of the liquid fuel tank may be located within the fuselage 12 or the wings 14. However, the liquid fuel tank 206 may be located in other suitable locations within the fuselage 12 or the wings 14. The liquid fuel tank 206 may also be a separate tank, rather than a single integral unit; for example, two tanks, each located within a corresponding wing 14.

[0037] In the described embodiment, the generator is engine 100, particularly a high-bypass turbofan engine. Engine 100 may also be referred to herein as turbofan engine 100. Figure 2 It is used for Figure 1 A schematic cross-sectional view of one of the engines 100 in the propulsion system of the aircraft 10 shown. The turbofan engine 100 has an axial direction A (extending parallel to the longitudinal centerline 101, in...) Figure 2 (Shown for reference), radial direction R and circumferential direction. Circumferential direction ( Figure 2 (Not shown) extends in a direction of rotation about the axial direction A. The turbofan engine 100 includes a fan section 102 and a turbine 104 disposed downstream of the fan section 102.

[0038] Figure 2 The turbine 104 depicted includes a tubular housing 106 defining an annular inlet 108. The housing 106 surrounds a compressor section in series flow relationships, including a turbocharger or low-pressure (LP) compressor 110 and a high-pressure (HP) compressor 112; a combustion section 114; a turbine section including a high-pressure (HP) turbine 116 and a low-pressure (LP) turbine 118; and an exhaust nozzle section 120. The compressor section, combustion section 114, and turbine section together at least partially define a core airflow path 121 extending from the annular inlet 108 to the exhaust nozzle section 120. The turbofan engine also includes one or more drive shafts. More specifically, the turbofan engine includes a high-pressure (HP) shaft or spool 122 drivingly connecting the HP turbine 116 to the HP compressor 112, and a low-pressure (LP) shaft or spool 124 drivingly connecting the LP turbine 118 to the LP compressor 110.

[0039] Figure 2The fan section 102 described herein includes a fan 126 having a plurality of fan blades 128 spaced apart and coupled to a disk 130. The fan blades 128 and the disk 130 are rotatable together about a longitudinal centerline (axis) 101 via an LP shaft 124. The disk 130 is covered by a rotatable front hub 132 having an aerodynamic profile to facilitate airflow through the plurality of fan blades 128. Furthermore, an annular fan housing or outer nacelle 134 is provided, circumferentially surrounding at least a portion of the fan 126 and / or the turbine 104. The nacelle 134 is supported relative to the turbine 104 by a plurality of circumferentially spaced outlet guide vanes 136. A downstream section 138 of the nacelle 134 extends above the outer portion of the turbine 104 to define a bypass airflow passage 140 therebetween.

[0040] However, it should be understood that the turbofan engine 100 discussed herein is provided only as an example. In other embodiments, any other suitable engine may be used in conjunction with aspects of this disclosure. For example, in other embodiments, the turbofan engine 100 may be any other suitable gas turbine engine, such as a turboshaft engine, a turboprop engine, a turbojet engine, etc. In this way, it will be further appreciated that in other embodiments, the gas turbine engine may have other suitable configurations, such as other suitable numbers or arrangements of shafts, compressors, turbines, fans, etc. Furthermore, although the turbofan engine 100 is shown as a direct-drive, fixed-pitch turbofan engine 100, in other embodiments, the gas turbine engine may be a geared turbine engine (i.e., including a gearbox between a fan 126 and a shaft (e.g., LP shaft 124) driving the fan), or a variable-pitch turbine engine (i.e., including a fan 126 having a plurality of fan blades 128 rotatable about their respective pitch axes), etc. Furthermore, still in alternative embodiments, various aspects of this disclosure may be incorporated into or otherwise used with any other type of engine (e.g., a reciprocating engine), as described above.

[0041] refer to Figure 2 and Figure 3 The turbofan engine 100 is capable of operating in conjunction with the fuel system 200 and receiving a fuel flow from the fuel system 200. As will be further described below, the fuel system 200 includes a fuel delivery assembly 202 that provides a fuel flow from a liquid fuel tank 206 to the turbofan engine 100, and more specifically, to a fuel manifold (not shown) to the combustion section 114 of the turbine 104 of the turbofan engine 100.

[0042] More specifically, Figure 3A schematic diagram of a fuel system 200 according to an embodiment of the present disclosure is shown. This fuel system is configured to store fuel from an engine 100 in a liquid fuel tank 206 and deliver the fuel to the engine 100 via a fuel delivery assembly 202. In one embodiment, the fuel system 200 is adaptable to a vehicle having an engine 204 (e.g., engine 100) according to an exemplary embodiment of the present disclosure. More specifically, for Figure 3 In an exemplary embodiment, the carrier may be an aircraft carrier, such as Figure 1 The exemplary aircraft 10, and the engine 204 may be an aviation gas turbine engine, such as Figure 1 Exemplary engine 100 and / or Figure 2 An exemplary turbofan engine 100.

[0043] However, in other embodiments, the carrier may be any other suitable land or air carrier, and the engine 204 may be any other suitable engine mounted on or within the carrier in any suitable manner.

[0044] The exemplary fuel system 200 shown is typically a hydrogen fuel system configured to store hydrogen fuel and supply hydrogen fuel to engine 204.

[0045] For the illustrated embodiment, the fuel system 200 typically includes a liquid cryogenic fuel storage tank 206 for maintaining a first portion of the cryogenic fuel in a liquid phase. More specifically, the liquid cryogenic fuel storage tank 206 may be configured to store the first portion of the cryogenic fuel, such as hydrogen fuel, substantially entirely in the liquid phase. For example, the liquid cryogenic fuel storage tank 206 may be configured to store the first portion at a temperature of about -253°C or lower, and at a pressure greater than about 1 bar and less than about 10 bar, such as between about 3 bar and about 5 bar, or at other temperatures and pressures, to maintain the cryogenic fuel substantially in the liquid phase.

[0046] It should be understood that, as described herein, the term “substantially complete” used to describe the phase of a cryogenic fuel means that at least 99% of the mass of the portion of the cryogenic fuel is in the phase, or for example, at least 97.5%, at least 95%, at least 92.5%, at least 90%, at least 85%, or at least 75% of the mass of the portion of the cryogenic fuel is in the phase.

[0047] The fuel system 200 further includes a gaseous cryogenic fuel tank 208 configured to store a second portion of cryogenic fuel in the gaseous phase. The gaseous cryogenic fuel tank 208 can be configured to store the second portion of cryogenic fuel under increased pressure to reduce the necessary size of the gaseous cryogenic fuel tank 208 within the aircraft 10. For example, in one embodiment, the gaseous cryogenic fuel tank 208 can be configured to store the second portion of cryogenic fuel at pressures of at least about 100 bar, such as at least about 200 bar, such as at least about 400 bar, such as at least about 600 bar, such as at least about 700 bar, and up to about 1000 bar. The gaseous cryogenic fuel tank 208 can be configured to store the second portion of cryogenic fuel at temperatures within about 50°C of ambient temperature or between about -50°C and about 100°C.

[0048] It should be understood that, for the described embodiments, the gas cryogenic fuel storage tank 208 is more specifically a plurality of gas cryogenic fuel tanks. In such embodiments, the plurality of gas cryogenic fuel storage tanks are configured to reduce the overall size and weight required to contain the required volume of the second portion of cryogenic fuel in the gas phase at the required pressure.

[0049] As will be further understood, a significant portion of the total cryogenic fuel storage capacity of fuel system 200 is provided by liquid cryogenic fuel tank 206. For example, in some exemplary embodiments, fuel system 200 defines a maximum fuel storage capacity. Liquid cryogenic fuel tank 206 can provide more than 50% (in kilograms) of the maximum fuel storage capacity, with the remainder provided by gaseous cryogenic fuel tank 208. For example, in some exemplary aspects, liquid cryogenic fuel tank 206 can provide at least about 60% of the maximum fuel storage capacity, such as at least about 70%, such as at least about 80%, such as up to about 98%, such as up to about 95% of the maximum fuel storage capacity. The gas cryogenic fuel storage tank 208 can be configured to provide remaining fuel storage capacity, such as at least about 2% of the maximum fuel storage capacity, such as at least about 5% of the maximum fuel storage capacity, such as at least about 10% of the maximum fuel storage capacity, such as at least about 15% of the maximum fuel storage capacity, such as at least about 20% of the maximum fuel storage capacity, such as up to 50% of the maximum fuel storage capacity, such as up to about 40% of the maximum fuel storage capacity.

[0050] Still referencing Figure 3The fuel system 200 further includes a fuel delivery assembly 202. The fuel delivery assembly 202 typically includes a liquid cryogenic delivery assembly 212 in fluid communication with a liquid cryogenic fuel tank 206, a gas cryogenic delivery assembly 214 in fluid communication with a gas cryogenic fuel tank 208, and a regulator assembly 216 in fluid communication with the liquid cryogenic delivery assembly 212 and the gas cryogenic delivery assembly 214 for supplying cryogenic fuel to the engine 204.

[0051] The cryogenic delivery assembly 212 typically includes a pump 218 and a heat exchanger 220 located downstream of the pump 218. The pump 218 is configured to provide a first portion of cryogenic fuel in liquid phase from the cryogenic fuel reservoir 206 through the cryogenic delivery assembly 212. Operation of the pump 218 can be increased or decreased to achieve a change in the volume of the first portion of cryogenic fuel passing through the cryogenic delivery assembly 212 and reaching the regulator assembly 216 and the engine 204. The pump 218 can be any suitable pump configured to provide a flow of cryogenic fuel. For example, in some exemplary aspects, the pump 218 can be configured as a cryogenic pump.

[0052] Still referencing Figure 3 It should be understood that the liquid cryogenic fuel storage tank 206 can be defined with a fixed volume such that when the liquid cryogenic fuel storage tank 206 supplies cryogenic fuel to the fuel system 200 substantially entirely in the liquid phase, the volume of the liquid cryogenic fuel in the liquid cryogenic fuel storage tank 206 decreases, and this volume is composed of, for example, gaseous cryogenic fuel. Furthermore, during the normal process of storing the first portion of the cryogenic fuel in the liquid phase, a certain amount of the first portion of the cryogenic fuel may vaporize.

[0053] To prevent the internal pressure within the liquid cryogenic fuel storage tank 206 from exceeding a required pressure threshold, the fuel system 200 is configured to allow the removal of gaseous cryogenic fuel from the liquid cryogenic fuel storage tank 206. More specifically, in one embodiment, the fuel delivery assembly 202 of the fuel system 200 includes a vaporization fuel assembly 222 configured to receive gaseous cryogenic fuel from the liquid cryogenic fuel storage tank 206. The vaporization fuel assembly 222 typically includes a vaporization compressor 224 and a vaporization tank 226. The vaporization tank 226 is in fluid communication with the liquid cryogenic fuel storage tank 206 and further in fluid communication with the gaseous cryogenic delivery assembly 214.

[0054] During operation, gaseous fuel from liquid cryogenic fuel storage tank 206 can be received in vaporization fuel assembly 222, compressed by vaporization compressor 224, and supplied to vaporization storage tank 226. Vaporization storage tank 226 can be configured to store gaseous cryogenic fuel at a pressure lower than the pressure of the second portion of cryogenic fuel in gaseous cryogenic fuel storage tank 208.

[0055] Referring again to the cryogenic gas delivery assembly 214, the cryogenic gas delivery assembly 214 typically includes a three-way vaporization valve 228 defining a first input 230, a second input 232, and an output 234. The first input 230 may be in fluid communication with a cryogenic fuel storage tank 208 for receiving a second portion of the cryogenic fuel flow in the gas phase from the cryogenic fuel storage tank 208. In the described embodiment, the second input 232 is in fluid communication with a vaporization fuel assembly 222 for receiving a cryogenic fuel flow from, for example, a vaporization tank 226 of the vaporization fuel assembly 222. The three-way vaporization valve 228 may be configured to combine and / or alternate the flows from the first input 230 and the second input 232 into a single cryogenic fuel flow through the output 234. In the illustrated embodiment, the three-way vaporization valve 228 is an active valve such that the amount of cryogenic fuel supplied from the first input 230 to the output 234 can be actively controlled compared to the amount of cryogenic fuel supplied from the second input 232 to the output 234. In other exemplary embodiments, the three-way vaporization valve 228 may be a passive valve.

[0056] The fuel system 200 may also include a gaseous hydrogen delivery assembly flow regulator 236 (“GHDA flow regulator” 236). The GHDA flow regulator 236 may be configured as an actively controlled variable flow valve, configured to provide a variable flow rate ranging from 0% (e.g., fully closed position) to 100% (e.g., fully open position), and multiple intermediate flow rates in between. As briefly mentioned, the regulator assembly 216 is in fluid communication with the liquid cryogenic delivery assembly 212 and the gas cryogenic delivery assembly 214 for supplying gaseous cryogenic fuel to the engine 204.

[0057] In addition, still refer to Figure 3The regulator assembly 216 includes a three-way regulator valve 238. The three-way regulator valve 238 defines a first input 240, a second input 242, and an output 244. The first input 240 may be in fluid communication with the gas cryogenic delivery assembly 214 for receiving a second portion of cryogenic fuel in the gas phase from the gas cryogenic fuel storage tank 208 (and, for example, the vaporization fuel assembly 222). The second input 242 is in fluid communication with the liquid cryogenic delivery assembly 212 for receiving a first portion of cryogenic fuel in the gas phase from the liquid cryogenic fuel storage tank 206 (vaporized using, for example, a heat exchanger 220). The three-way regulator valve 238 may be configured to combine and / or alternate the flows from the first input 240 and the second input 242 into a single cryogenic gas flow through the output 244. In the illustrated embodiment, the three-way regulator valve 238 is an active three-way regulator valve, such that the amount of cryogenic gas supplied to the output 244 from the first input 240 can be actively controlled compared to the amount of cryogenic gas supplied to the output 244 from the second input 242. In other exemplary embodiments, the three-way regulator valve 238 may be a passive valve.

[0058] For the illustrated embodiment, regulator assembly 216 also includes regulator assembly flow regulator 245 (“RA flow regulator” 245) and flow meter 248. RA flow regulator 245 can be configured as an actively controlled variable flow valve, configured to provide a variable flow rate ranging from 0% (e.g., fully closed position) to 100% (e.g., fully open position), and a plurality of intermediate flow rates in between.

[0059] As previously described, the liquid fuel storage tank 206 of the fuel system 200 contains liquid cryogenic fuel. Therefore, the fuel must be maintained at a cryogenic temperature so that it remains substantially entirely in the liquid phase. To maintain such a temperature, the liquid fuel storage tank 206 is surrounded by a vacuum container, which creates a vacuum space between the liquid fuel storage tank 206 and the vacuum container. Furthermore, as previously described, the liquid fuel storage tank 206 requires a suspension system to support it within the vacuum container. Therefore, this disclosure relates to an improved suspension system for cryogenic fuel systems. In particular, the liquid fuel storage tank 206 containing the refrigerant can be a liquid hydrogen (LH2) tank or any other cryogenic tank with double walls (e.g., containing LHe, LN2, LO2, etc.). Therefore, the suspension system described herein can be used in any cryogenic tank with a vacuum environment.

[0060] More specifically, in one embodiment, such as Figure 4As shown, a cryogenic fuel system 250 according to the present disclosure is illustrated. As shown, the cryogenic fuel system 250 includes a cryogenic tank 252 (e.g., a liquid fuel tank 206) containing a liquid refrigerant and a vacuum container 254 surrounding the cryogenic tank 252. Thus, as shown, the vacuum container 254 provides a vacuum space 256 between the inner surface 258 of the vacuum container 254 and the outer surface 260 of the cryogenic tank 252. In the illustrated embodiment, the vacuum container 254 includes a removable cover 282 (see, for example...). Figure 4 ).

[0061] In a further embodiment, the cryogenic storage tank 252 and the vacuum container 254 can be made of any suitable material. For example, in one embodiment, one or both of the cryogenic storage tank 252 and the vacuum container 254 can be made of a composite material. In an alternative embodiment, one or both of the cryogenic storage tank 252 and the vacuum container 254 can be made of a metallic material.

[0062] In addition, such as Figure 5-12 As shown, the cryogenic fuel system 250 includes a suspension system 262 arranged within a vacuum space 256 to support the cryogenic tank 252 within the vacuum container 254 and to hold the cryogenic tank 252 in the desired position within the vacuum container 254. Furthermore, in one embodiment, particularly as shown... Figure 5 , 8 As shown in Figure 10, the suspension system 262 includes a plurality of roller elements 264 arranged within the vacuum space 256 and contacting the inner surface 258 of the vacuum container 254 and the outer surface 260 of the cryogenic tank 252. Thus, the roller elements 264 contact the inner surface 258 of the vacuum container 254 and the outer surface 260 of the cryogenic tank 252 at multiple different points along the longitudinal length of the cryogenic tank 252 to support the cryogenic tank 252 within the vacuum container 254, thereby maintaining the cryogenic tank 252 within the vacuum container 254 in a desired position (e.g., a central position within the vacuum container 254).

[0063] In certain embodiments, such as Figure 5 , 10 As shown in 11A and 11B, the suspension system 262 may include a roller element 264, which provides axial and radial suspension, for example, in the axial direction A and the radial direction R, respectively. For example, particularly as... Figure 5 , Figure 11A and Figure 11BAs shown, the suspension system 262 can provide suspension in the axial direction A using one or more axial suspension members 284, which can be positioned at any suitable location along the cryogenic tank 252, such as at the front or rear of the cryogenic tank 252. In such an embodiment, the axial suspension member 284 may have a generally dome shape with one or more holes for receiving a subset of the roller elements 264. Furthermore, as... Figure 5 , 11A As shown in 11B, the axial suspension member 284 may include one or more locking features 275 (e.g., protrusions, notches, etc.) that lock the axial suspension member 284 to the radial suspension member 268. Furthermore, as... Figure 11A and 11B As shown, the locking feature 275 may be circumferentially spaced around the axial suspension member 284 to provide sufficient locking.

[0064] Furthermore, in some embodiments, the cryogenic storage tank 252 can slide relative to the vacuum container 254 via the roller element 264. Therefore, in one embodiment, the removable cover 282 of the vacuum container 254 (see...) Figure 4 It can be easily opened, allowing the cryogenic storage tank 252 to slide inside.

[0065] In one embodiment, for example, such as Figure 5-12 As shown, multiple roller elements 264 can be connected via one or more guide rails 266 ( Figure 12 ) or one or more radial suspension members 268 or rod members (e.g., see Figure 5 , 7 8 and 10) are connected together. More specifically, such as Figure 5-10 As shown, a plurality of roller elements 264 are connected together via radial suspension members 268, and the roller elements 264 may be ball bearings 270 connected together via radial suspension members 268. In such an embodiment, as Figure 5 and 7 As shown in Figure -8, the radial suspension member 268 can extend through the ball bearing 270, as... Figure 7 As shown by the dashed line in the image.

[0066] In a further embodiment, such as Figure 12 As shown, a plurality of roller elements 264 are connected together via guide rails 266. The plurality of roller elements 264 may be cylindrical roller elements 272, similar to wheels, and are connected together via guide rails 266. Furthermore, in one embodiment, as... Figure 12 As shown, the first guide rail 267 and the second guide rail 269 can be arranged on opposite sides of one or more rows of cylindrical roller elements 272.

[0067] In these embodiments, the first and second guide rails 267 and 269 may each include one or more flanges 271 and 273 for securing the guide rail 266 to the inner surface 258 of the vacuum container 254 and the outer surface 260 of the cryogenic storage tank 252 (see...). Figure 4 ).

[0068] Furthermore, in one embodiment, such as Figure 5 , 8 As shown in Figure 10, the plurality of roller elements 264 can be arranged in multiple rows 274 of roller elements 264. Therefore, in such an embodiment, as... Figure 6 , 9 As shown in 11A and 11B, multiple rows 274 of the roller element 264 can be circumferentially spaced around the cryogenic storage tank 252 within the vacuum space 256.

[0069] In additional embodiments, such as Figure 8 and 9 As shown, the suspension system 262 may further include at least one ring member 276 connecting multiple rows of roller elements 264 together. More specifically, in one embodiment, as shown, the suspension system 262 may include a first ring member 278 at a front position of the cryogenic tank 252 and a second ring member 280 at a rear position of the cryogenic tank 252. It should be further understood that the ring member 276 described herein may be located at any other suitable position along the length of the cryogenic tank 252, such as at a midpoint of the cryogenic tank 252. Thus, the ring member 276 is provided to maintain the arrangement of the roller elements 264 within the vacuum space 256 and to hold the cryogenic tank 252 within the vacuum container 254 in the desired position.

[0070] Special Reference Figure 5 and 6 The suspension system 262 may also include one or more insulating members 265 arranged between one or more (or each) roller elements 264. Thus, the insulating members 265 are further configured to facilitate the suspension of the cryogenic tank 252 within the vacuum container 254.

[0071] Now for reference Figure 13 A flowchart illustrating an embodiment of a method 300 for assembling a cryogenic system according to this disclosure is shown. Generally, method 300 is described herein with reference to the turbojet engine 100 described above. However, it should be understood that the disclosed method 300 can be used for any other engine or suitable cryogenic application, such as a superconducting generator with any suitable configuration. Furthermore, although for illustrative and discussion purposes, Figure 13The steps are described in a specific order, but the method described herein is not limited to any particular order or arrangement. Using the disclosure provided herein, those skilled in the art will understand that various steps of the method can be omitted, rearranged, combined, and / or modified in various ways.

[0072] As shown at (302), method 300 includes a suspension system having a plurality of roller elements circumferentially fixed around a cryogenic tank containing liquid refrigerant. As shown at (304), method 300 includes sliding the cryogenic tank into a vacuum container via the plurality of roller elements, such that a radial space is created between the inner surface of the vacuum container and the outer surface of the cryogenic tank, and the plurality of roller elements contact the inner surface of the vacuum container and the outer surface of the cryogenic tank. As shown at (306), method 300 includes creating a vacuum in the radial space, wherein the suspension system supports the cryogenic tank within the vacuum container and holds the cryogenic tank in a desired position within the vacuum container.

[0073] In a particular embodiment, method 300 may include opening a removable cover of the vacuum container before sliding the cryogenic tank into the vacuum container via a plurality of roller elements, and then closing the removable cover once the cryogenic tank has slid into place. In such an embodiment, a suspension system including roller elements is configured to facilitate the assembly and positioning of the cryogenic tank within the vacuum container.

[0074] In a particular embodiment, Figure 13 Method 300 may further include circumferentially fixing a radial suspension system having a plurality of roller elements around the cryogenic tank. Furthermore, method 300 may include axially fixing an axial suspension system having first and second axial suspension members and a plurality of roller elements relative to the cryogenic tank. Thus, method 300 also includes assembling the radial suspension system with the first axial suspension member and sliding the cryogenic tank into a vacuum container via the plurality of roller elements, such that a space is created between the inner surface of the vacuum container and the outer surface of the cryogenic tank, and the plurality of roller elements engage the inner surface of the vacuum container and the outer surface of the cryogenic tank. Furthermore, method 300 may include locking the radial suspension to the first axial suspension member, assembling the second axial suspension member, and then locking the first and second axial members to the radial suspension system. Assembly can then be completed by covering the open dome area with a cap welded, bolted, or adhesively attached. Subsequently, method 300 may include creating a vacuum in the radial space, wherein the suspension system supports the cryogenic tank within the vacuum container and holds the cryogenic tank in a desired position within the vacuum container.

[0075] although Figure 1The aircraft 10 shown is an airplane, but the embodiments described herein can also be applied to other aircraft 10, including, for example, helicopters, unmanned aerial vehicles (UAVs), and ship propulsion. Furthermore, the embodiments described herein can also be applied to applications other than turbojet engines, such as superconducting generators. The engine described herein is a gas turbine engine, but the embodiments described herein can also be applied to other engines. Additionally, engine 100 is an example of a generator using cryogenic fuel, but this fuel can be used as fuel for other generators. For example, the generator could be a fuel cell (hydrogen fuel cell), in which hydrogen is supplied to the fuel cell to generate electricity by reacting with air. Such a generator can be used in a variety of applications, including stationary power generation systems (including gas turbines and hydrogen fuel cells) and other vehicles besides the aircraft 10 explicitly described herein, such as small boats, ships, cars, trucks, etc. Furthermore, the cryogenic systems described herein can be used in superconducting machines, such as superconducting generators, which can be used in a variety of applications, such as renewable energy and MRI machines.

[0076] Further aspects are provided by the following topics:

[0077] A cryogenic system includes: a cryogenic tank containing a liquid refrigerant; a vacuum container surrounding the cryogenic tank and providing a vacuum space between an inner surface of the vacuum container and an outer surface of the cryogenic tank; and a suspension system disposed within the vacuum space to support the cryogenic tank within the vacuum container and hold the cryogenic tank in a desired position within the vacuum container, the suspension system including a plurality of roller elements disposed within the vacuum space and contacting the inner surface of the vacuum container and the outer surface of the cryogenic tank.

[0078] According to the cryogenic system described in the foregoing clause, the plurality of roller elements of the suspension system are arranged in the vacuum space in the radial and axial directions.

[0079] According to any of the preceding clauses, in a cryogenic system, the plurality of roller elements arranged in the vacuum space in the axial direction are held in place by one or more axial suspension members, and the plurality of roller elements arranged in the vacuum space in the radial direction are held in place by one or more radial suspension members.

[0080] According to any of the preceding clauses of the cryogenic system, wherein the one or more axial suspension members include one or more locking features configured to lock the one or more axial suspension members relative to the one or more radial suspension members.

[0081] According to any of the preceding clauses, in a cryogenic system, the plurality of roller elements are connected together via one or more guide rails, and the plurality of roller elements include cylindrical roller elements connected together via the one or more guide rails.

[0082] In any of the preceding clauses, the cryogenic system wherein the plurality of roller elements includes ball bearings.

[0083] In any of the preceding clauses of the cryogenic system, wherein one or more radial suspension members extend through the ball bearing.

[0084] According to any of the preceding clauses, the cryogenic system further includes one or more insulating members disposed between one or more of the plurality of roller elements.

[0085] According to any of the preceding clauses, in the cryogenic system, the plurality of roller elements are arranged in multiple rows of roller elements, the multiple rows of roller elements being circumferentially spaced around the cryogenic tank within the vacuum space.

[0086] According to any of the preceding clauses, the cryogenic system, wherein the suspension system further includes at least one ring member connecting the multiple rows of roller elements together.

[0087] According to any of the preceding clauses, the cryogenic storage tank is slidable relative to the vacuum container in the cryogenic system.

[0088] The cryogenic system according to any of the foregoing clauses, wherein the vacuum container includes a removable lid.

[0089] The cryogenic system according to any of the foregoing clauses, wherein the cryogenic system is part of one of a turbojet engine or a superconducting generator.

[0090] In any of the preceding clauses, the cryogenic system wherein both the cryogenic storage tank and the vacuum container are made of composite materials.

[0091] A method of assembling a cryogenic system, the method comprising: circumferentially fixing a suspension system having a plurality of roller elements around a cryogenic tank containing a liquid refrigerant; sliding the cryogenic tank into a vacuum container via the plurality of roller elements such that a radial space is created between an inner surface of the vacuum container and an outer surface of the cryogenic tank, and the plurality of roller elements contact the inner surface of the vacuum container and the outer surface of the cryogenic tank; and creating a vacuum within the radial space, wherein the suspension system supports the cryogenic tank within the vacuum container and holds the cryogenic tank within the vacuum container in a desired position.

[0092] The method according to any of the foregoing clauses further includes opening a removable cover of the vacuum container before sliding the cryogenic tank into the vacuum container via the plurality of roller elements, and subsequently closing the removable cover once the cryogenic tank has slid into place.

[0093] The method according to any of the foregoing clauses further includes connecting the plurality of roller elements together via one or more guide rails, wherein the plurality of roller elements includes cylindrical roller elements connected together via the one or more guide rails.

[0094] The method according to any of the foregoing clauses further includes connecting the plurality of roller elements together via one or more radial suspension members, wherein the plurality of roller elements includes ball bearings connected together via the one or more radial suspension members.

[0095] The method according to any of the foregoing clauses further includes: arranging the plurality of roller elements in the vacuum space in the axial direction via one or more axial suspension members and in the radial direction via one or more radial suspension members; and securing the one or more axial suspension members to the one or more radial suspension members via one or more locking features on the one or more axial suspension members.

[0096] A cryogenic fuel system for a turbojet engine, the cryogenic fuel system comprising: a cryogenic tank containing liquid cryogenic fuel for the turbojet engine; a vacuum container surrounding the cryogenic tank and providing a vacuum space between an inner surface of the vacuum container and an outer surface of the cryogenic tank; and a plurality of roller elements arranged within the vacuum space and contacting the inner surface of the vacuum container and the outer surface of the cryogenic tank at a plurality of different points along a longitudinal length of the cryogenic tank to support the cryogenic tank within the vacuum container and hold the cryogenic tank within the vacuum container in a desired position.

[0097] This written description uses examples to disclose this disclosure, including best practices, and also enables any person skilled in the art to practice this disclosure, including making and using any device or system and performing any incorporated methods. The patentable scope of this disclosure is defined by the claims, but may include other examples that would occur to a person skilled in the art. Such other examples are intended to be within the scope of the claims if they include structural elements that are not indistinguishable from the literal language of the claims, or if they include equivalent structural elements that are not substantially different from the literal language of the claims.

Claims

1. A cryogenic system, characterized in that, include: Cryogenic storage tanks for containing liquid refrigerant; A vacuum container that surrounds the cryogenic storage tank and provides a vacuum space between the inner surface of the vacuum container and the outer surface of the cryogenic storage tank; and A suspension system, arranged within the vacuum space, is provided to support the cryogenic tank within the vacuum container and maintain the cryogenic tank in a desired position within the vacuum container. The suspension system includes a plurality of roller elements arranged radially and axially within the vacuum space and contacting the inner surface of the vacuum container and the outer surface of the cryogenic tank. The plurality of roller elements arranged in the vacuum space in the axial direction are held in place by one or more axial suspension members, and the plurality of roller elements arranged in the vacuum space in the radial direction are held in place by one or more radial suspension members. The one or more axial suspension members include one or more locking features configured to lock the one or more axial suspension members relative to the one or more radial suspension members.

2. The cryogenic system according to claim 1, characterized in that, The plurality of roller elements are connected together via one or more guide rails, and the plurality of roller elements include cylindrical roller elements connected together via the one or more guide rails.

3. The cryogenic system according to claim 1, characterized in that, The plurality of roller elements mentioned above include ball bearings.

4. The cryogenic system according to claim 3, characterized in that, The one or more radial suspension members thereunder extend through the ball bearing.

5. The cryogenic system according to claim 1, characterized in that, The suspension system further includes one or more insulating members disposed between one or more of the plurality of roller elements.

6. The cryogenic system according to claim 1, characterized in that, The plurality of roller elements are arranged in multiple rows of roller elements, which are circumferentially spaced around the cryogenic storage tank within the vacuum space.

7. The cryogenic system according to claim 6, characterized in that, The suspension system further includes at least one ring member that connects the multiple rows of roller elements together.

8. The cryogenic system according to claim 1, characterized in that, The cryogenic storage tank is slidable relative to the vacuum container.

9. The cryogenic system according to claim 1, characterized in that, The vacuum container mentioned above includes a removable lid.

10. The cryogenic system according to claim 1, characterized in that, The cryogenic system is part of either a turbojet engine or a superconducting generator.

11. The cryogenic system according to claim 1, characterized in that, Both the cryogenic storage tank and the vacuum container are made of composite materials.

12. A method for assembling a cryogenic system, characterized in that, The method includes: A suspension system with multiple roller elements is fixed circumferentially around a cryogenic storage tank containing liquid refrigerant; The cryogenic storage tank is slid into the vacuum container via the plurality of roller elements, such that a radial space is created between the inner surface of the vacuum container and the outer surface of the cryogenic storage tank, and the plurality of roller elements contact the inner surface of the vacuum container and the outer surface of the cryogenic storage tank. A vacuum is generated within the radial space, wherein the suspension system supports the cryogenic tank within the vacuum container and holds the cryogenic tank within the vacuum container in a desired position; and The plurality of roller elements are arranged in the vacuum space in the axial direction via one or more axial suspension members and in the radial direction via one or more radial suspension members, and the one or more axial suspension members are fixed to the one or more radial suspension members via one or more locking features on the one or more axial suspension members.

13. The method according to claim 12, characterized in that, The method further includes opening a removable cover of the vacuum container before sliding the cryogenic tank into the vacuum container via the plurality of roller elements, and then closing the removable cover once the cryogenic tank has slid into place.

14. The method according to claim 12, characterized in that, The method further includes connecting the plurality of roller elements together via one or more guide rails, wherein the plurality of roller elements includes cylindrical roller elements connected together via the one or more guide rails.

15. The method according to claim 12, characterized in that, The plurality of roller elements mentioned above include ball bearings.

16. A cryogenic fuel system for a turbojet engine, characterized in that, The cryogenic fuel system includes: A cryogenic storage tank that contains liquid cryogenic fuel for the turbojet engine; A vacuum container that surrounds the cryogenic storage tank and provides a vacuum space between the inner surface of the vacuum container and the outer surface of the cryogenic storage tank; and Multiple roller elements are arranged radially and axially within the vacuum space and contact the inner surface of the vacuum container and the outer surface of the cryogenic storage tank at multiple different points along the longitudinal length of the cryogenic storage tank, in order to support the cryogenic storage tank within the vacuum container and hold the cryogenic storage tank in a desired position within the vacuum container. The plurality of roller elements arranged in the vacuum space in the axial direction are held in place by one or more axial suspension members, and the plurality of roller elements arranged in the vacuum space in the radial direction are held in place by one or more radial suspension members. The one or more axial suspension members include one or more locking features configured to lock the one or more axial suspension members relative to the one or more radial suspension members.

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