Patent Application
20250223050
The present disclosure relates generally to a system for managing a hydrogen fuel system and storage tank aboard an aircraft.
Reduction and/or elimination of carbon emissions generated by aircraft operation is a stated goal of aircraft manufacturers and airline operators. Gas turbine engines compress incoming core airflow, mix the compressed airflow with fuel that is ignited in a combustor to generate a high energy exhaust gas flow. The use of alternate fuels such as hydrogen may provide substantial reductions in undesirable emissions. The nature of alternate fuels such as hydrogen requires alternate monitoring and management processes and devices in order to practically realize the reduced emission benefits while maintaining a current level of operational control and safety.
A method of managing a hydrogen fuel system for a propulsion system of an aircraft, the method according to an exemplary embodiment of this disclosure includes, among other possible things, determining that the hydrogen fuel system is operating outside of a predefined operating range based on information that is indicative of operation of the hydrogen fuel and storage system and/or propulsion system operation, obtaining information relating to at least one aircraft operating characteristic, and determining a corrective action pertaining to the hydrogen fuel and storage system that maintains an acceptable operating condition of the aircraft propulsion system in view of the determined operation outside of the operating parameter.
A hydrogen fuel and storage system for a propulsion system of an aircraft according to another exemplary embodiment of this disclosure includes, among other possible things, at least one fuel tank that is configured to store a hydrogen based fuel, at least one sensor that generates information that is indictive of a condition of the at least one fuel tank, a controller that is programmed to receive information from the at least one sensor, determine that the hydrogen fuel and storage system is operating outside of a predefined operating range based on information that is indicative of operation of the hydrogen fuel and storage system and/or propulsion system operation, obtaining information relating to at least one aircraft operating characteristic, and to determine a corrective action that pertains to the hydrogen fuel and storage system that maintains an acceptable operating condition of the aircraft propulsion system in view of the determined operation outside of the operating parameter.
An aircraft propulsion system according to another exemplary embodiment of this disclosure includes, among other possible things, an engine that is configured to generate a propulsive thrust through combustion of a hydrogen based fuel, a hydrogen fuel and storage system that includes at least one fuel tank that is configured to store a hydrogen based fuel, and at least one sensor that generates information indictive of a condition of the at least one fuel tank, and a controller that is programmed to receive information form the at least one sensor, determine that the hydrogen fuel and storage system is operating outside of a predefined operating range based on information indicative of operation of the hydrogen fuel and storage system and/or propulsion system operation, obtaining information relating to at least one aircraft operating characteristic, and to determine a corrective action that pertains to the hydrogen fuel and storage system that maintains an acceptable operating condition of the aircraft propulsion system in view of the determined operation outside of the operating parameter.
Although the different examples have the specific components shown in the illustrations, embodiments of this invention are not limited to those particular combinations. It is possible to use some of the components or features from one of the examples in combination with features or components from another one of the examples.
These and other features disclosed herein can be best understood from the following specification and drawings, the following of which is a brief description.
The example propulsion system comprises a gas turbine engine 20 in the form of a turbofan that generally incorporates a fan section 22, a compressor section 24, a combustor section 26 and a turbine section 28. The fan section 22 drives air along a bypass flow path B in a bypass duct defined within a nacelle 30. The compressor section 24 drives air along a core flow path C into the combustor section 26. In the combustor section 26, the compressed air is mixed with fuel from the fuel system 32 and burnt to generate an exhaust gas flow that expands through the turbine section 28 and is exhausted through an exhaust nozzle 36. Although depicted as a turbofan turbine engine in the disclosed non-limiting embodiment, it should be understood that the concepts described herein are not limited to use with turbofans as the teachings may be applied to other types of gas turbine engines.
The example hydrogen fuel system 32 includes fuel tanks 34A-B that are configured to store hydrogen. Hydrogen is stored in a liquid state that requires the control of temperatures below typical ambient temperatures encountered during aircraft operation. The pressures within the fuel tanks 34A-B are also controlled to pressures not typically encountered with the use of conventional carbon based fuels. Accordingly, monitoring of the example fuel system 32 to maintain the fuel in a desired state is warranted. The example fuel system 32 is monitored by a controller that determines corrective actions to address conditions that deviate from a predefined operating range. The corrective actions may be automatically initiated or may be provided to a decision making authority, such as a pilot, to prompt action to safeguard aircraft operation.
Although hydrogen is disclosed by way of example, other systems that utilized other non-carbon based fuels may also benefit from this disclosure and are within the contemplation of this disclosure. Moreover, the disclosed features may also be beneficial in an engine configured to operate with traditional carbon fuels and/or biofuels, such as sustainable aviation fuel.
The fuel system 32 includes pumps 44 A-B that generate a fuel flow 42 to the combustor section 26 of the engine 20. Each of the tanks 34A-B include a temperature sensor 48A-B and a pressure sensor 50A-B. Other sensors may be provided proximate the fuel tanks 34A-B to sense leaks. In one disclosed example, leak sensors 52A-B are disposed proximate to the each of the tanks 34A-B. All of the temperature sensors 48A-B, pressure sensors 50A-B, and leak sensors 52A-B generate information that is communicated to a controller 38. Moreover, engine operating and aircraft operating parameters may also provide an indication of fuel system operation and are utilized to ascertain a health of the fuel system 32. The temperature, pressure and other sensor information are schematically shown as being communicated to the controller 38 by arrows 56, 64 and 66.
The example fuel system 32 may further include a conduit 114 and control valve 112 that provides for transfer of hydrogen fuel between the fuel tanks 34A-B. Each of the fuel tanks 34A-B may also include a purge conduit 118A-B and a purge valve 116A-B to enable venting of fuel away from the aircraft 18. The example fuel system 32 further includes a fire suppression system that is schematically shown at 54A-B within each of the fuel tanks 34A-B. Moreover, an ejection system indicated schematically at 46A-B for ejecting or dropping one or both of the fuel tanks 34A-B from the aircraft 18 may be provided for each of the fuel tanks 34A-B.
Referring to
The example controller 38 is a device and system for performing necessary computing or calculation operations for operation of the fuel system 32. The controller 38 may be specially constructed for operation of the fuel system 32, or it may comprise at least a general-purpose computer selectively activated or reconfigured by software programs stored in a memory device 72 and executed by processor 70. The controller 38 may further be part of full authority digital engine control (FADEC) or an electronic engine controller (EEC).
The example processor 70 may include one or more microprocessors, microcontrollers, application specific integrated circuits (ASICs), or the like. The memory device 104 may include any one or combination of volatile memory elements (e.g., random access memory (RAM, such as DRAM, SRAM, SDRAM, VRAM, etc.)) and/or nonvolatile memory elements (e.g., ROM, hard drive, tape, CD-ROM, etc.). Moreover, the memory device 72 may incorporate electronic, magnetic, optical, and/or other types of storage media. The memory 72 stores software that provides instructions which, when executed by the processor 70, cause the processor 70 to implement the various operations and/or generate instructions for operating the fuel system 32.
The example controller 32 may include one or more machine learning algorithms 74 to determined possible corrective actions based on the information received by a communication interface 68 of the controller 38. In one disclosed example, the machine learning algorithm 74 is a neural network. The neural network may be trained with historical data relating to modeled responses to input information relating to engine, aircraft and fuel system operation. The neural network may further be trained with (e.g., descriptions of subsystem and their content and associated redactions) and/or may be trained with the models themselves (e.g., analyzing contents of various model elements beyond their metadata description(s)). Although a neural network is disclosed by way of example, other machine learning algorithms may be utilized to process information and determine a corrective action. Accordingly, other machine learning algorithms may be utilized within the scope and contemplation of this disclosures.
Accordingly, the example controller 38 receives information indictive of engine operation 58, aircraft operation 60 and fuel system operation and determines a recommended corrective action 76 as an output 62. The corrective action 76 may be automatically sent as a command signal 78 to initiate operation of the fuel system 32 to remedy the detected deviation from desired operation. The corrective action 76 may be part of a prompt 80 that is sent to a display 40 to communicate to a decision making authority the proposed corrective action 76. Upon acceptance of the corrective action, a command signal 82 may be sent to the fuel system 32 to prompt action.
Referring to
The controller 38 uses the machine learning algorithm 74 to make determine what type of corrective action 76 is appropriate. The determination of the appropriate corrective action 76 is determined, at least in part, on a severity of the detected condition. The controller 38 determines a severity level, indicated schematically at 122, based on the inputs 84. The example severity level 122 includes a high risk as indicated at 92, a high risk with mitigating circumstances as is indicated at 94 and a low risk as indicated at 96.
The high risk indicated at 92 pertains to a malfunction that poses a high risk to continued normal operation and one where engine and aircraft operation do not limit the types of corrective action that may be available. The high risk indicated at 94 pertains to malfunctions that poses may risk to continued normal operation and one where engine and aircraft operation limits available corrective actions. Either of the high risk 92, 94 severity levels 122 warrant attention and some type of corrective action in order to continue engine and aircraft operation.
The low risk indicated at 96 pertains to malfunctions that don't pose a risk to continued normal operation. Such low risks may warrant a review of the fuel system 32 upon landing or at the next scheduled maintenance operation. Although several different severity levels 122 are shown and described by way of example, additional severity levels may be included and are within the scope and contemplation of this disclosure.
The controller 38 uses the various inputs 84 to ascertain the severity level 122. The example inputs include information from the temperature sensors 48A-B, pressure sensors 50A-B, leak detectors 52A-B of the fuel system 32. The information from the various sensors of the fuel system 32 are referred to cumulatively as sensor date 56. Moreover, the amount of fuel within the fuel system 32 and storage tanks 34A-B is provided to the controller 38 and indicated at 55. Information from fire and smoke sensors is provided as indicated at 88. The inputs 84 includes aircraft information such as location and altitude indicated at 60A and speed ambient conditions around the aircraft as indicated at 60B. Other information includes information on engine operation as indicated at 58 and air and marine traffic data as indicated at 86. It should be appreciated that although several forms of information from various sources are disclosed by way of example, other sources and types of information may also be utilized without limit and are within the scope and contemplation of this disclosure.
The input information 84 is used by the controller 38, and specifically, the machine learning algorithm 74 to determine the severity level 122 and further a recommended corrective action 76. The controller 38 may also provide automatic notification as indicated at 90 of a detected severity level 122. The notification may be directly to the pilot of the aircraft and further to outside authorities such as air traffic controllers, engine manufacturers, airport, aircraft manufactures along with any other outside entity that has an interest in operation of the aircraft.
The recommended corrective actions 76 may be provided as a predetermined set of actions based on the determined severity level 122. Alternatively, the corrective actions 76 may be defined based on teaching of the machine learning algorithm based on historical inputs, defined models, and/or any other known machine learning teaching methods.
In the disclosed example, the corrective actions 76 are paired with one of the determined severity levels 122. In response to the high risk severity level as indicated at 92, the corrective action may include operation of a fire suppression system to extinguish uncontrolled combustion as indicated at 100. The corrective action may also include actuating one or both of the ejection system 46A-B to remove one or both of the fuel tanks 34A-B from the aircraft 18 as indicated at 102.
In response to the high risk severity level indicated at 94, corrective actions may include extinguishment as indicated at 100 or purging of one of the tanks 34A-B as is indicated at 106. Purging of the tanks 34A-B would include operation of one or both of the purge valves 116A-B to evacuate fuel from the aircraft 18 through a corresponding one of the purge conduits 118A-B.
In the high risk severity level indicated at 94, ejection of the fuel tanks 34A-B is not an option. Accordingly, one possible corrective action 76 includes a recommendation as to when ejection of the fuel tanks 34A-B may become possible as is indicated at 104.
In the low risk severity level indicated at 96, the possible corrective actions include purging of one of the tanks or moving fuel between the tanks as indicated at 110. Movement of fuel between the fuel tanks 34A-B may be a viable corrective action when one of the fuel tanks 34A-B is not operating as desired and the other fuel tank 34A-B has sufficient capacity to accept additional fuel. The controller 38 initiates operation of the transfer valve 112 to move fuel between the tanks 34A-B and remedy the detected operating deviation.
Moreover, in the low risk level 96, it is an option to simply proceed with the flight as normal while recognizing that increased monitoring may be warranted as is indicated at 108. Although several corrective actions have been shown and described by way of example, additional corrective actions are possible within the contemplation and scope of this disclosure.
For each of the corrective actions, the controller 38 may generate the output 62 to control a portion of the fuel system 32 that corresponds to the recommended corrective action. For example, pumps 44A-B and may be adjusted and/or shut off as appropriate to facilitate the respective corrective action 76. Moreover, any other fuel system component such as valves and/or pumps would be actuated and operated in a manner corresponding to the corrective action. Additionally, the controller 38 may further alter control of engine and aircraft operation in a manner that corresponds with changing operational capacities the result from corrective actions applied to the fuel system 32.
The output 62 from the controller 38 may automatically trigger the determined corrective action or may trigger a prompt for a decision making authority to accept the recommended action. The decision making authority would include the pilot of the aircraft. The decision making authority may also include another system onboard the aircraft that is accorded final control over aircraft operation.
A method of managing a hydrogen fuel system 32 for a propulsion system 20 of an aircraft 18, the method according to an exemplary embodiment of this disclosure, among other possible things includes determining that the hydrogen fuel system 32 is operating outside of a predefined operating range based on information that is indicative of operation of the hydrogen fuel and storage system and/or propulsion system operation, obtaining information relating to at least one aircraft operating characteristic, and determining a corrective action 76 pertaining to the hydrogen fuel and storage system that maintains an acceptable operating condition of the aircraft propulsion system 20 in view of the determined operation outside of the operating parameter.
In a further embodiment of the foregoing, the method further includes automatically executing the determined corrective action 76.
In a further embodiment of any of the foregoing, the method further includes automatically executing the determined corrective action 76 when the determined corrective action 76 is one of a predetermined set of corrective actions.
In a further embodiment of any of the foregoing, the method further includes generating a recommendation prompt 80 that communicates the determined corrective action 76 to a decision making authority and executing the corrective action 76 in response to a signaled acceptance by the decision making authority.
In a further embodiment of any of the foregoing, the method further includes obtaining information that is indicative of operation of the hydrogen fuel and storage system with at least one sensor.
In a further embodiment of any of the foregoing methods, the corrective action 76 includes an adjustment to an operating parameter of the hydrogen fuel and storage system.
In a further embodiment of any of the foregoing methods, the corrective action 76 includes a transfer of fuel between different hydrogen fuel storage tanks 34.
In a further embodiment of any of the foregoing methods, the corrective action 76 includes purging a hydrogen fuel tank 34.
In a further embodiment of any of the foregoing methods, the corrective action 76 includes actuating a fire suppression system.
In a further embodiment of any of the foregoing methods, the corrective action 76 includes removing a hydrogen fuel tank from the aircraft 18.
In a further embodiment of any of the foregoing methods, the corrective action 76 includes a modification to a current flight profile.
In a further embodiment of any of the foregoing, the method further includes determining a risk 122 to continued aircraft operation within a predefined operating range and further determining the corrective action 76 based on the determined risk.
In a further embodiment of any of the foregoing methods, the determined corrective action 76 is facilitated by a machine learning algorithm 74 that is programmed to evaluate the information indicative of operation of the fuel system 32 and/or of the propulsion system 20 along with possible corrective actions and to determine a recommended corrective action 76.
A hydrogen fuel and storage system for a propulsion system 20 of an aircraft 18 according to another exemplary embodiment of this disclosure, among other possible things includes at least one fuel tank 34 that is configured to store a hydrogen based fuel, at least one sensor that generates information that is indictive of a condition of the at least one fuel tank 34, a controller 38 that is programmed to receive information from the at least one sensor, determine that the hydrogen fuel and storage system is operating outside of a predefined operating range based on information that is indicative of operation of the hydrogen fuel and storage system and/or propulsion system operation, obtaining information relating to at least one aircraft operating characteristic, and to determine a corrective action 76 that pertains to the hydrogen fuel and storage system that maintains an acceptable operating condition of the aircraft propulsion system 20 in view of the determined operation outside of the operating parameter.
In a further embodiment of the foregoing hydrogen fuel storage system, the controller 38 is further programmed to automatically execute the determined corrective action 76.
In a further embodiment of any of the foregoing hydrogen fuel storage systems, the controller 38 is further programmed to generate a recommendation prompt 80 that communicates the determined corrective action 76 to a decision making authority and execute the corrective action 76 in response to a signaled acceptance by the decision making authority.
In a further embodiment of any of the foregoing hydrogen fuel storage systems, the controller 38 is further programmed to determine a risk 122 to continued aircraft operation within a predefined operating range and to determine the corrective action 76 based on the determined risk 122.
An aircraft propulsion system 20 according to another exemplary embodiment of this disclosure, among other possible things includes an engine 20 that is configured to generate a propulsive thrust through combustion of a hydrogen based fuel, a hydrogen fuel and storage system that includes at least one fuel tank 34 that is configured to store a hydrogen based fuel, and at least one sensor 48/50 that generates information indictive of a condition of the at least one fuel tank 34, and a controller 38 that is programmed to receive information form the at least one sensor 48/50, determine that the hydrogen fuel and storage system is operating outside of a predefined operating range based on information indicative of operation of the hydrogen fuel and storage system and/or propulsion system operation, obtaining information relating to at least one aircraft operating characteristic, and to determine a corrective action 76 that pertains to the hydrogen fuel and storage system that maintains an acceptable operating condition of the aircraft propulsion system 20 in view of the determined operation outside of the operating parameter.
In a further embodiment of the foregoing aircraft propulsion system 20, the controller 38 is further programmed to automatically execute the determined corrective action 76 when the predetermined corrective action determined corrective action 76 is one of a predetermined set of corrective actions and to generate a recommendation prompt 80 that communicates the determined corrective action 76 to a decision making authority and execute the corrective action 76 in response to a signaled acceptance by the decision making authority when the predetermined corrective action is not within the predetermined set of corrective actions.
In a further embodiment of any of the foregoing aircraft propulsion systems, the controller 38 is further programmed to determine a risk 122 to continued aircraft operation within a predefined operating range and to determine the corrective action 76 based on the determined risk 122.
Accordingly, the example propulsion system 20 utilizes a machine learning algorithm 74 to process information indicative of operation of the hydrogen based fuel and storage system and recommend and/or implement corrective actions to aid in operation of the aircraft 18.
Although an example embodiment has been disclosed, a worker of ordinary skill in this art would recognize that certain modifications would come within the scope of this disclosure. For that reason, the following claims should be studied to determine the scope and contents of this disclosure.
