A magnesium hydride hydrogen storage hydrogen-fueling aircraft turbine engine

Abstract

A magnesium hydride-based hydrogen storage hydrogen-fueling aero-turbine engine is disclosed, relating to the field of aero-turbine engines. It includes an air intake, fan, high-pressure compressor, combustion chamber, high-pressure turbine, low-pressure turbine, mixing chamber, nozzle, magnesium hydride heat exchanger, magnesium hydride storage tank, and intermediate hydrogen storage tank. Magnesium hydride is used as a carrier for airborne hydrogen fuel, providing hydrogen fuel for the aero-turbine engine. Using magnesium hydride as a hydrogen storage material in a hydrogen-fueled aero-engine offers significant advantages in hydrogen storage system design and aircraft safety. A magnesium hydride heat exchange and hydrogen release device is installed after the core engine outlet. Magnesium hydride is supplied in groups from the magnesium hydride storage tank via a mechanical device for endothermic hydrogen release. The released hydrogen is piped to the intermediate hydrogen storage tank for temporary storage before being supplied to the core engine combustion chamber for combustion. The released magnesium hydride is returned to the storage tank. The high-temperature exhaust gas of the aero-engine continuously provides heat for the hydrogen release of magnesium hydride, eliminating the need for external energy for the hydrogen release process.

Description

Technical Field

[0001] This invention relates to the field of aircraft turbine engines, and in particular to a hydrogen-fueling aircraft turbine engine with magnesium hydride hydrogen storage. Background Technology

[0002] With the continuous development of aerospace technology, hydrogen fuel, due to its high energy density and environmentally friendly characteristics, is considered an ideal fuel for the future aviation field. However, the low density and gaseous nature of hydrogen pose challenges to its storage. In aviation applications, conventional compressed or liquefied hydrogen storage methods suffer from problems such as large volume, high cost, and safety hazards. Therefore, a more efficient and safer hydrogen storage method is needed.

[0003] Magnesium hydride (MgH2), as a solid hydrogen storage material, has been widely studied for hydrogen fuel storage and transportation due to its high hydrogen storage capacity and good hydrogen storage stability. Magnesium hydride has a hydrogen storage capacity of approximately 7.6 wt%, which is higher than that of liquid hydrogen and high-pressure hydrogen. Furthermore, storing hydrogen in solid form is safer, reducing the risk of leakage. Magnesium hydride can decompose and release hydrogen under high-temperature conditions, thus it can be combined with hydrogen-fired aircraft turbine engines to release hydrogen through heating, providing a stable fuel source for the engine. Summary of the Invention

[0004] The purpose of this invention is to address the above-mentioned needs by providing a magnesium hydride hydrogen storage hydrogen-fueling aero-turbine engine that can improve the energy efficiency and safety of aero-engines while reducing dependence on external energy sources. It utilizes magnesium hydride as a hydrogen fuel carrier to provide efficient and safe hydrogen fuel for aero-turbine engines.

[0005] This invention discloses a magnesium hydride hydrogen storage hydrogen-fueling aero-turbine engine. Based on an existing dual-rotor mixed-emission turbofan engine, it achieves hydrogen fuel supply for the aero-turbine engine by adding a magnesium hydride heat exchanger after the low-pressure turbine and by adding a magnesium hydride storage tank and an intermediate hydrogen storage tank outside the engine. Specifically:

[0006] A magnesium hydride hydrogen storage hydrogen-fueling aero-turbine engine includes a dual-rotor mixed-displacement turbofan engine basic assembly, which is provided with an air intake, a fan, a high-pressure compressor, a combustion chamber, a high-pressure turbine, a low-pressure turbine, a mixing chamber, and a nozzle. The basic assembly works together to generate thrust. The engine is characterized by further providing a magnesium hydride heat exchanger, a magnesium hydride storage tank, and an intermediate hydrogen storage tank.

[0007] The magnesium hydride heat exchanger is located behind the low-pressure turbine and is used to receive the high-temperature exhaust gas from the low-pressure turbine as a heat source, so that the magnesium hydride absorbs heat and releases hydrogen.

[0008] The magnesium hydride storage tank is located outside the engine and is used to store magnesium hydride. It is also supplied to the magnesium hydride heat exchanger for hydrogen release via a mechanical device.

[0009] The intermediate hydrogen storage tank is located outside the engine and connected between the magnesium hydride heat exchanger and the combustion chamber. It is used to temporarily store the hydrogen released from the magnesium hydride heat exchanger and supply it according to the hydrogen demand of the combustion chamber, thereby adjusting the matching between the magnesium hydride hydrogen release rate and the hydrogen combustion rate.

[0010] By utilizing the high-temperature exhaust gas from the turbine core to achieve the endothermic release of hydrogen from magnesium hydride, there is no need to provide external energy for the hydrogen release of magnesium hydride. The matching problem between the hydrogen release rate of magnesium hydride and the hydrogen combustion rate is solved through an intermediate hydrogen storage tank, enabling the use of magnesium hydride as a carrier for airborne hydrogen fuel to provide hydrogen fuel for aero-turbine engines.

[0011] Furthermore, the magnesium hydride storage tank is made of lightweight, high-strength, and corrosion-resistant material, and is filled with magnesium hydride particles. Magnesium hydride exhibits relatively stable hydrogen storage characteristics; it does not release hydrogen within the storage tank, but only absorbs heat and releases hydrogen in the heat exchanger.

[0012] Furthermore, the magnesium hydride heat exchanger has an internal heat conduction structure, including but not limited to spiral channels and finned structures, to improve heat exchange efficiency.

[0013] Furthermore, the intermediate hydrogen storage tank is made of high-strength, corrosion-resistant, and well-sealing materials to ensure the safe storage and supply of hydrogen.

[0014] Furthermore, a mechanical device and a regulating valve are provided. The mechanical device includes a delivery pump, a rotary valve, and a circulation pipeline. The mechanical device is used to transport magnesium hydride particles from the storage tank to a heat exchanger for hydrogen release. After the magnesium hydride is completely released in the heat exchanger, it is returned to the magnesium hydride storage tank. The regulating valve is used to adjust the hydrogen supply rate to ensure that the hydrogen supply matches the demand of the combustion chamber.

[0015] Furthermore, a safety monitoring and protection system is also provided, which includes a hydrogen leak detection device, temperature and pressure sensors, and a hydrogen flow controller. The hydrogen leak detection device is used to monitor hydrogen leaks in real time to ensure the safe operation of the system. The temperature and pressure sensors are used to monitor and adjust the temperature and pressure of the magnesium hydride heat exchanger in real time. The hydrogen flow controller is used to receive signals from the hydrogen leak detection device and the temperature and pressure sensors, and make decisions based on these signals. According to the needs of the combustion chamber, it precisely adjusts the hydrogen supply rate to ensure the stability and efficiency of the combustion process. The hydrogen flow controller is constructed using a programmable logic controller (PLC) to adjust the hydrogen supply rate. When a hydrogen leak or system abnormality is detected, it automatically cuts off the hydrogen supply to ensure the safe operation of the system and maximize the heat exchange efficiency.

[0016] This invention includes a complete structure of a benchmark dual-rotor hybrid turbofan engine. A magnesium hydride heat exchanger is added behind the low-pressure turbine for magnesium hydride to absorb heat and release hydrogen. A magnesium hydride storage tank is added externally to the engine for storing magnesium hydride. An intermediate hydrogen storage tank is used for matching and regulating the hydrogen combustion consumption rate and the magnesium hydride hydrogen release rate. Similar to conventional hybrid turbofan engines, this invention has a single nozzle outlet. The internal airflow passes through the magnesium hydride heat exchanger, then mixes with the external airflow before being discharged through the nozzle.

[0017] Compared with the prior art, the beneficial effects achieved by the technical solution of this invention are:

[0018] 1. This invention is aimed at hydrogen fuel cell aircraft turbine engines and uses magnesium hydride solid hydrogen storage material to supply hydrogen to the turbine engine. It has significant advantages over traditional hydrogen storage in terms of volume density and hydrogen storage stability, and brings great advantages in aircraft hydrogen storage system design and aircraft safety.

[0019] 2. This invention utilizes the high-temperature exhaust gas of a turbine engine to provide energy for the release of hydrogen from magnesium hydride. Compared with common schemes that rely on external energy supply to promote hydrogen release, this invention eliminates the need for additional external energy supply, thereby improving energy utilization. It also simplifies the system for externally supplying energy to magnesium hydride materials and reduces the system complexity of the aircraft.

[0020] 3. This invention is an improvement on the existing benchmark dual-rotor hybrid turbofan engine, with minimal modifications and high feasibility. Attached Figure Description

[0021] Figure 1 This is a schematic diagram illustrating the structure and operating principle of a magnesium hydride hydrogen storage and combustion turbine engine.

[0022] The markings in the diagram are as follows: 1. Inlet; 2. Fan; 3. High-pressure compressor; 4. Combustion chamber; 5. High-pressure turbine; 6. Low-pressure turbine; 7. Mixing chamber; 8. Nozzle; 9. Magnesium hydride heat exchanger; 10. Magnesium hydride storage tank; 11. Intermediate hydrogen storage tank; ① indicates the process of magnesium hydride being supplied to the heat exchanger through a mechanical device, completing heat exchange, and then returning to the magnesium hydride storage tank; ② indicates the process of magnesium hydride releasing hydrogen gas, flowing into the intermediate hydrogen storage tank, and then being supplied to the combustion chamber for combustion. Detailed Implementation

[0023] To make the technical problems, technical solutions, and beneficial effects of the present invention clearer and more understandable, the present invention will be further described in detail below with reference to the embodiments in the accompanying drawings.

[0024] like Figure 1As shown, this embodiment of the invention comprises a basic component of a dual-rotor mixed-emission turbofan engine, a magnesium hydride heat exchanger 9, a magnesium hydride storage tank 10, and an intermediate hydrogen storage tank 11. The basic component of the dual-rotor mixed-emission turbofan engine includes an intake duct 1, a fan 2, a high-pressure compressor 3, a combustion chamber 4, a high-pressure turbine 5, a low-pressure turbine 6, a mixing chamber 7, and a nozzle 8.

[0025] The air intake duct 1 is located at the front of the engine and is used to introduce external air.

[0026] The fan 2 is located behind the air intake duct 1 and is driven by the low-pressure turbine 6 to draw in and compress air.

[0027] The high-pressure compressor 3 is located behind the fan 2, further compressing the air drawn in by the fan 2 and increasing the air pressure and temperature.

[0028] The combustion chamber 4 is located behind the high-pressure compressor 3 and is used to receive the air compressed by the high-pressure compressor 3 and the hydrogen provided by the hydrogen storage and supply subsystem, mix them and ignite them to produce high-temperature and high-pressure gas.

[0029] The high-pressure turbine 5 is located behind the combustion chamber 4 and is used to receive high-temperature and high-pressure gas and drive it to rotate, thereby driving the high-pressure compressor 3 and the fan 2.

[0030] The low-pressure turbine 6 is located behind the high-pressure turbine 5 and is used to receive the gas after it has been expanded by the high-pressure turbine 5 and drive it to rotate, thereby driving the fan 2 and the fan or pump in the magnesium hydride heat exchanger 9.

[0031] The mixing chamber 7 is located behind the low-pressure turbine 6 and is used to mix the exhaust gas discharged from the low-pressure turbine 6 with the ambient air to reduce the exhaust temperature.

[0032] The nozzle 8 is located behind the mixing chamber 7 and is used to accelerate and discharge the mixed gas to generate thrust.

[0033] The magnesium hydride heat exchanger 9 is located at the outlet of the low-pressure turbine 6 and uses the high-temperature exhaust gas from the aircraft engine as a heat source to heat the magnesium hydride particles, causing them to decompose and produce hydrogen. The magnesium hydride heat exchanger 9 has an optimized heat conduction structure, such as spiral channels and finned structures, to improve heat exchange efficiency. The magnesium hydride heat exchanger 9 is connected to the intermediate hydrogen storage tank 11 via a pipeline.

[0034] The magnesium hydride storage tank 10 is located outside the engine, and the interior of the magnesium hydride storage tank 10 is filled with magnesium hydride particles; the magnesium hydride storage tank 10 is connected to the magnesium hydride heat exchanger 9 through a pipeline.

[0035] The intermediate hydrogen storage tank 11 is located between the magnesium hydride heat exchanger 9 and the combustion chamber 4, and is used to temporarily store the hydrogen released from the magnesium hydride heat exchanger 9 to ensure the stability and continuity of the hydrogen supply. The intermediate hydrogen storage tank 11 is connected to the hydrogen flow controller via a pipeline, and is also connected to the combustion chamber 4 via a pipeline.

[0036] This invention is based on the structure of a dual-rotor hybrid turbofan engine. A magnesium hydride heat exchanger 9 is added behind the low-pressure turbine 6 for magnesium hydride to absorb heat and release hydrogen. A magnesium hydride storage tank 10 is added outside the engine to store magnesium hydride. An intermediate hydrogen storage tank 11 is used for matching and regulating the hydrogen combustion consumption rate and the magnesium hydride hydrogen release rate. Similar to conventional hybrid turbofan engines, this invention has a single airflow outlet, a nozzle 8. The internal airflow passes through the magnesium hydride heat exchanger, then mixes with the external airflow, and is discharged together through the nozzle 8.

[0037] This invention may also include a safety monitoring and protection system, comprising a hydrogen leak detection device, temperature and pressure sensors, and a controller, for real-time monitoring and adjustment of the system's operating status to ensure safe operation. When a hydrogen leak or system abnormality is detected, the safety monitoring and protection system can automatically cut off the hydrogen supply and issue an alarm.

[0038] like Figure 1 As shown, the working principle of this invention embodiment is as follows:

[0039] During flight, the basic components 1-8 of the dual-rotor mixed-emission turbofan engine operate normally. Magnesium hydride is mechanically supplied from the magnesium hydride storage tank 10 to the magnesium hydride heat exchanger 9 as a cold source, while high-temperature gas flowing from the low-pressure turbine 6 flows into the magnesium hydride heat exchanger 9 as a heat source. Heating the magnesium hydride particles causes them to decompose and generate hydrogen. After heat exchange, the magnesium hydride absorbs heat and releases hydrogen. The released magnesium hydride is then mechanically transported back to the magnesium hydride storage tank 10. Hydrogen flows through pipelines to the intermediate hydrogen storage tank 11 for temporary storage and is supplied to the combustion chamber 4 at a rate sufficient to meet the hydrogen combustion rate. The supply rate can be precisely adjusted by setting a hydrogen flow controller. By utilizing the high-temperature exhaust gas from the turbine core to achieve the endothermic hydrogen release of magnesium hydride, and by using the intermediate hydrogen storage tank 11 to address the matching problem between the magnesium hydride hydrogen release rate and the hydrogen combustion rate, magnesium hydride is used as a carrier for airborne hydrogen fuel, providing hydrogen fuel for the aero-turbine engine. Figure 1 In the diagram, ① indicates the process where magnesium hydride is supplied to the heat exchanger via a mechanical device, completes the heat exchange, and then returns to the magnesium hydride storage tank; ② indicates the process where magnesium hydride releases hydrogen gas, flows into the intermediate hydrogen storage tank, and is then supplied to the combustion chamber for combustion.

[0040] This invention uses magnesium hydride as a carrier for airborne hydrogen fuel, providing hydrogen fuel for aero-turbine engines. Magnesium hydride, as a solid hydrogen storage material, has significant advantages over traditional hydrogen storage methods in terms of volumetric density and hydrogen storage stability. Using magnesium hydride as a hydrogen storage material for hydrogen-fueled aero-engines can bring significant advantages in hydrogen storage system design and aircraft safety. In the use of traditional solid hydrogen storage materials, the release of hydrogen requires external energy. This invention adds a magnesium hydride heat exchange and hydrogen release device after the core engine outlet of the aero-engine. Magnesium hydride is supplied in groups from the magnesium hydride storage tank through a mechanical device for endothermic hydrogen release. The released hydrogen is piped to an intermediate hydrogen storage tank for temporary storage before being supplied to the core engine combustion chamber for combustion. The released magnesium hydride is returned to the storage tank. This invention utilizes the high-temperature exhaust gas of the aero-engine to continuously provide heat for the hydrogen release of magnesium hydride, eliminating the need for external energy for hydrogen release. Simulation verification proves the feasibility of this invention. This invention enables efficient, safe, and environmentally friendly storage and supply of hydrogen, improves the fuel efficiency of aircraft engines, reduces environmental pollution, and enhances the overall performance and safety of aircraft.

[0041] The above embodiments are merely preferred embodiments of the present invention and should not be considered as limiting the scope of the present invention. All equivalent variations and improvements made within the scope of the present invention should still fall within the patent coverage of the present invention.

Claims

1. A magnesium hydride hydrogen storage hydrogen-fueling aero-turbine engine, comprising a dual-rotor mixed-flow turbofan engine basic assembly, including an air intake, fan, high-pressure compressor, combustion chamber, high-pressure turbine, low-pressure turbine, mixing chamber, and nozzle, wherein the basic assembly works collaboratively to generate thrust, characterized in that... It is also equipped with a magnesium hydride heat exchanger, a magnesium hydride storage tank, and an intermediate hydrogen storage tank; The magnesium hydride heat exchanger is located behind the low-pressure turbine and is used to receive the high-temperature exhaust gas from the low-pressure turbine as a heat source, so that the magnesium hydride absorbs heat and releases hydrogen. The magnesium hydride storage tank is located outside the engine and is used to store magnesium hydride. It is also supplied to the magnesium hydride heat exchanger for hydrogen release via a mechanical device. The intermediate hydrogen storage tank is located outside the engine and is connected between the magnesium hydride heat exchanger and the combustion chamber. The intermediate hydrogen storage tank is used to temporarily store the hydrogen released from the magnesium hydride heat exchanger and supply it according to the hydrogen demand of the combustion chamber, while adjusting the matching between the magnesium hydride hydrogen release rate and the hydrogen combustion rate. The internal airflow passes through a magnesium hydride heat exchanger and is then mixed with the external air before being discharged through the nozzle. By utilizing the high-temperature exhaust gas from the turbine core, magnesium hydride is used to absorb heat and release hydrogen, eliminating the need for external energy to power the release of hydrogen from magnesium hydride. An intermediate hydrogen storage tank is used to solve the problem of matching the hydrogen release rate of magnesium hydride with the hydrogen combustion rate, enabling the use of magnesium hydride as a carrier for airborne hydrogen fuel and providing hydrogen fuel for aero-turbine engines. It is also equipped with a mechanical device and a regulating valve. The mechanical device includes a delivery pump, a rotary valve and a circulation pipeline. The mechanical device is used to transport magnesium hydride particles from the storage tank to the heat exchanger for hydrogen release, and to recover the released magnesium hydride particles and refill them into the storage tank. The regulating valve is used to adjust the hydrogen supply rate to ensure that the hydrogen supply is matched with the demand of the combustion chamber.

2. The magnesium hydride hydrogen storage hydrogen-fueling aero-turbine engine as described in claim 1, characterized in that... The magnesium hydride storage tank is made of lightweight, high-strength, and corrosion-resistant material, and is filled with magnesium hydride particles.

3. The magnesium hydride hydrogen storage hydrogen-fueling aero-turbine engine as described in claim 1, characterized in that... The internal structure of the magnesium hydride heat exchanger includes a heat conduction structure, such as a spiral channel and a finned structure, to improve heat exchange efficiency.

4. The magnesium hydride hydrogen storage hydrogen-fueling aero-turbine engine as described in claim 1, characterized in that... The intermediate hydrogen storage tank is made of high-strength, corrosion-resistant, and well-sealing materials to ensure the safe storage and supply of hydrogen.

5. The magnesium hydride hydrogen storage hydrogen-fueling aero-turbine engine as described in claim 1, characterized in that... The system also includes a safety monitoring and protection system, comprising a hydrogen leak detection device, temperature and pressure sensors, and a hydrogen flow controller. The hydrogen leak detection device monitors hydrogen leaks in real time to ensure safe system operation. The temperature and pressure sensors monitor and regulate the temperature and pressure inside the magnesium hydride heat exchanger in real time. The hydrogen flow controller receives signals from the hydrogen leak detection device and the temperature and pressure sensors, and makes decisions based on these signals. It precisely adjusts the hydrogen supply rate according to the needs of the combustion chamber to ensure stable and efficient combustion. The hydrogen flow controller is built using a programmable logic controller (PLC) and can adjust the hydrogen supply rate. When a hydrogen leak is detected, it automatically cuts off the hydrogen supply to ensure safe system operation and maximize heat exchange efficiency.

6. The magnesium hydride hydrogen storage hydrogen-fueling aero-turbine engine as described in claim 1, characterized in that... The system also includes a safety monitoring and protection system, comprising a hydrogen leak detection device, temperature and pressure sensors, and a hydrogen flow controller. The hydrogen leak detection device monitors hydrogen leaks in real time to ensure safe system operation. The temperature and pressure sensors monitor and regulate the temperature and pressure inside the magnesium hydride heat exchanger in real time. The hydrogen flow controller receives signals from the hydrogen leak detection device and the temperature and pressure sensors, and makes decisions based on these signals. It precisely adjusts the hydrogen supply rate according to the needs of the combustion chamber to ensure stable and efficient combustion. The hydrogen flow controller is built using a programmable logic controller (PLC) to adjust the hydrogen supply rate. When a system abnormality is detected, it automatically cuts off the hydrogen supply to ensure safe system operation and maximize heat exchange efficiency.

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