Magnesium hydride hydrogen storage hydrogen combustion aviation turbine engine

Abstract

The invention discloses a hydrogen-fired aviation turbine engine for storing hydrogen through magnesium hydride, and relates to the field of aviation turbine engines. Comprising an air inlet channel, a fan, a high-pressure compressor, a combustion chamber, a high-pressure turbine, a low-pressure turbine, a mixing chamber, a spray pipe, a magnesium hydride heat exchanger, a magnesium hydride storage tank and a middle hydrogen storage tank. Magnesium hydride is used as a carrier of airborne hydrogen fuel, and hydrogen fuel is provided for an aviation turbine engine. Magnesium hydride is used as a hydrogen storage material of a hydrogen fuel aero-engine, and great advantages are brought in the aspects of hydrogen storage system design, aircraft safety and the like. A magnesium hydride heat exchange and hydrogen release device is additionally arranged behind an outlet of a core machine, magnesium hydride is supplied from a magnesium hydride storage tank in a circulating and grouping mode through a mechanical device for heat absorption and hydrogen release, released hydrogen enters a middle hydrogen storage tank through a pipeline to be temporarily stored and then is supplied to a combustion chamber of the core machine for combustion, and the magnesium hydride after hydrogen release returns to the storage tank. High-temperature tail gas of an aero-engine is used for continuously providing heat for hydrogen release of magnesium hydride, and energy does not need to be provided for hydrogen release of magnesium hydride from the outside.

Description

Technical Field

[0001] The invention relates to the field of aviation turbine engines, in particular to a hydrogen-burning aviation turbine engine using magnesium hydride to store hydrogen. Background Art

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

[0003] As a solid hydrogen storage material, magnesium hydride (MgH2) has been widely studied for the storage and transportation of hydrogen fuel due to its high hydrogen storage capacity and good hydrogen storage stability. The hydrogen storage capacity of magnesium hydride is about 7.6wt% (weight percentage), which has a higher hydrogen storage density than liquid hydrogen and high-pressure hydrogen, and storing hydrogen in solid form is safer, reducing the risk of leakage. Magnesium hydride can decompose and release hydrogen under high temperature conditions, so it can be combined with hydrogen-fired aviation turbine engines to achieve hydrogen release through heating, providing a stable fuel source for the engine. Summary of the invention

[0004] The purpose of the present invention is to provide a hydrogen-burning aviation turbine engine with magnesium hydride hydrogen storage to improve the energy utilization and safety of aviation engines and reduce dependence on external energy sources in response to the above needs. Magnesium hydride is used as a hydrogen fuel carrier to provide efficient and safe hydrogen fuel for aviation turbine engines.

[0005] The hydrogen-burning aviation turbine engine with magnesium hydride hydrogen storage described in the present invention is based on the existing dual-rotor mixed-displacement turbofan engine. By installing a magnesium hydride heat exchanger behind the low-pressure turbine and adding a magnesium hydride storage tank and an intermediate hydrogen storage tank outside the engine, magnesium hydride is used as a hydrogen fuel carrier to provide hydrogen fuel for the aviation turbine engine. Specifically:

[0006] A hydrogen-burning aviation turbine engine with magnesium hydride hydrogen storage, comprising a dual-rotor mixed-displacement turbofan engine basic component, provided with an air inlet, a fan, a high-pressure compressor, a combustion chamber, a high-pressure turbine, a low-pressure turbine, a mixing chamber, and a nozzle, wherein the basic components work together to generate thrust, and the engine is characterized in that it is also provided with 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 high-temperature exhaust gas from the low-pressure turbine as a heat source to allow the magnesium hydride to absorb heat and release hydrogen;

[0008] The magnesium hydride storage tank is arranged outside the engine, and is used to store magnesium hydride, and is circulated into the magnesium hydride heat exchanger through a mechanical device to release hydrogen;

[0009] The intermediate hydrogen storage tank is arranged outside the engine and connected between the magnesium hydride heat exchanger and the combustion chamber, and 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, so as to adjust the matching between the hydrogen release rate of magnesium hydride and the hydrogen combustion rate;

[0010] By utilizing the high-temperature exhaust gas of the turbine core engine to achieve the endothermic hydrogen release of magnesium hydride, there is no need to provide energy from the outside for the hydrogen release of magnesium hydride. The matching problem of the hydrogen release rate of magnesium hydride and the hydrogen combustion rate is solved by an intermediate hydrogen storage tank, so that magnesium hydride can be used as a carrier of airborne hydrogen fuel to provide hydrogen fuel for aviation turbine engines.

[0011] Furthermore, the magnesium hydride storage tank is made of a light, high-strength, corrosion-resistant material and is filled with magnesium hydride particles. The hydrogen storage property of magnesium hydride is relatively stable, and magnesium hydride does not release hydrogen in the magnesium hydride storage tank, but only absorbs heat and releases hydrogen in the heat exchanger.

[0012] Furthermore, a heat conduction structure is provided inside the magnesium hydride heat exchanger, including but not limited to a spiral channel and a fin structure, to improve the heat exchange efficiency.

[0013] Furthermore, the intermediate hydrogen storage tank is made of a material with high strength, corrosion resistance and good sealing performance 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 the magnesium hydride particles from the storage tank to the heat exchanger for hydrogen release. After the magnesium hydride has completely released hydrogen in the heat exchanger, the magnesium hydride returns 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, a temperature and pressure sensor, 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 sensor is 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 sensor, and make decisions based on these signals, and accurately adjust the hydrogen supply rate according to the needs of the combustion chamber to ensure the stability and efficiency of the combustion process; the hydrogen flow controller is constructed using a programmable logic controller PLC, which can adjust the hydrogen supply rate. When hydrogen leakage or system abnormality is detected, the hydrogen supply is automatically cut off to ensure the safe operation of the system and maximize the heat exchange efficiency.

[0016] The present invention includes a complete structure of a standard dual-rotor mixed-displacement 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 outside 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. The scheme of the present invention is the same as that of a traditional mixed-displacement turbofan engine. The inner airflow passes through the magnesium hydride heat exchanger, and then is mixed with the outer air and discharged from the nozzle together.

[0017] Compared with the prior art, the technical solution of the present invention has the following beneficial effects:

[0018] 1. The present invention is aimed at hydrogen-fueled aviation turbine engines and uses magnesium hydride solid hydrogen storage materials to supply hydrogen for turbine engines. It has obvious advantages over traditional hydrogen storage in terms of volume density and hydrogen storage stability, and brings great advantages in aircraft hydrogen storage system design, aircraft safety, etc.

[0019] 2. The present invention utilizes the high temperature exhaust gas of the turbine engine to provide energy for the release of hydrogen from magnesium hydride. Compared with the common scheme of promoting hydrogen release by external energy supply, no additional energy supply from the outside is required, thus improving energy utilization. At the same time, the system for external energy supply to the magnesium hydride material is simplified, thus reducing the system complexity of the aircraft.

[0020] 3. The present invention is an improvement on the existing benchmark twin-rotor mixed-displacement turbofan engine, with small changes in the scheme and high feasibility. BRIEF DESCRIPTION OF THE DRAWINGS

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

[0022] The marks in the figure are: 1. air 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 represents the process in which magnesium hydride is supplied to the heat exchanger through a mechanical device and returns to the magnesium hydride storage tank after completing the heat exchange; ② represents the process in which magnesium hydride releases hydrogen, flows into the intermediate hydrogen storage tank and is then supplied to the combustion chamber for combustion. DETAILED DESCRIPTION

[0023] In order to make the technical problems, technical solutions and beneficial effects to be solved by the present invention clearer and more understandable, the present invention is further described in detail below in conjunction with the embodiments of the accompanying drawings.

[0024] like Figure 1As shown, the embodiment of the present invention comprises a dual-rotor mixed-displacement turbofan engine basic component, a magnesium hydride heat exchanger 9, a magnesium hydride storage tank 10, and an intermediate hydrogen storage tank 11. The dual-rotor mixed-displacement turbofan engine basic component comprises an air inlet 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 end of the engine and is used to introduce external air.

[0026] The fan 2 is located behind the air inlet 1 and is driven by the low-pressure turbine 6 to inhale and compress air.

[0027] The high-pressure compressor 3 is located behind the fan 2 and further compresses the air sucked in by the fan 2 to increase 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 and ignite them, and generate high-temperature and high-pressure combustion gas.

[0029] The high-pressure turbine 5 is located behind the combustion chamber 4 and is used to receive high-temperature and high-pressure combustion 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 combustion gas 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 combustion gas exhausted by the low-pressure turbine 6 with the external 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 arranged at the outlet of the low-pressure turbine 6, and is used to utilize the high-temperature exhaust gas discharged from the aircraft engine as a heat source to heat the magnesium hydride particles to promote their decomposition and generate hydrogen. The magnesium hydride heat exchanger 9 is internally designed with an optimized heat conduction structure, such as a spiral channel, a fin structure, etc., to improve the heat exchange efficiency. The magnesium hydride heat exchanger 9 is connected to the intermediate hydrogen storage tank 11 through 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 arranged 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 through a pipeline, and is connected to the combustion chamber 4 through a pipeline.

[0036] The embodiment of the present invention is based on the structure of a dual-rotor mixed-displacement 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 for storing 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. The present invention is the same as a traditional mixed-displacement turbine engine. There is an airflow outlet of the nozzle 8. The internal airflow passes through the magnesium hydride heat exchanger, and then is mixed with the external air and discharged from the nozzle 8 together.

[0037] The embodiment of the present invention may also be provided with a safety monitoring and protection system, which includes a hydrogen leak detection device, a temperature and pressure sensor, and a controller, etc., for real-time monitoring and adjusting the working state of the system to ensure the safe operation of the system. When a hydrogen leak or system abnormality is detected, the safety monitoring and protection system can automatically cut off the hydrogen supply and sound an alarm.

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

[0039] During flight, the basic components 1 to 8 of the twin-rotor mixed-displacement turbofan engine work normally. Magnesium hydride is supplied from the magnesium hydride storage tank 10 to the magnesium hydride heat exchanger 9 by a mechanical device as a cold source. The high-temperature gas flowing out of the low-pressure turbine 6 flows into the magnesium hydride heat exchanger 9 as a heat source, and the magnesium hydride particles therein are heated to decompose and generate hydrogen. After heat exchange, the magnesium hydride absorbs heat and releases hydrogen, and the magnesium hydride after hydrogen release is transported back to the magnesium hydride storage tank 10 by a mechanical device. The hydrogen flows into the intermediate hydrogen storage tank 11 through a pipeline for temporary storage, and is supplied to the combustion chamber 4 as fuel for combustion at a supply rate that meets the hydrogen combustion rate. The supply rate can be accurately adjusted by setting a hydrogen flow controller. By utilizing the high-temperature exhaust gas of the turbine core engine to achieve the heat absorption and hydrogen release of magnesium hydride, and by using the intermediate hydrogen storage tank 11 to solve the matching problem of the hydrogen release rate and the hydrogen combustion rate of magnesium hydride, the overall use of magnesium hydride as a carrier of airborne hydrogen fuel is realized to provide hydrogen fuel for aviation turbine engines. Figure 1 In the figure, mark ① indicates the process in which magnesium hydride is supplied into the heat exchanger through a mechanical device and returns to the magnesium hydride storage tank after completing the heat exchange; ② indicates the process in which magnesium hydride releases hydrogen, flows into the intermediate hydrogen storage tank, and then is supplied into the combustion chamber for combustion.

[0040] The present invention uses magnesium hydride as a carrier of airborne hydrogen fuel to provide hydrogen fuel for aviation turbine engines. Magnesium hydride, as a solid hydrogen storage material, has obvious advantages over traditional hydrogen storage in terms of volume density and hydrogen storage stability. Using magnesium hydride as a hydrogen storage material for hydrogen fuel aircraft engines can bring great advantages in hydrogen storage system design, aircraft safety, etc. In the use of traditional solid hydrogen storage materials, the release of hydrogen from solid hydrogen storage materials requires external energy. The present invention installs a magnesium hydride heat exchange and hydrogen release device after the core engine outlet of the aircraft engine, and supplies magnesium hydride from the magnesium hydride storage tank through a mechanical device in a cyclic group to absorb heat and release hydrogen. The released hydrogen enters the intermediate hydrogen storage tank through a pipeline for temporary storage and then is supplied to the core engine combustion chamber for combustion, and the magnesium hydride after hydrogen release returns to the storage tank. The present invention uses the high-temperature exhaust gas of the aircraft engine to continuously provide heat for the release of hydrogen from magnesium hydride, without the need to provide energy from the outside for the release of hydrogen from magnesium hydride. The feasibility of the scheme of the present invention has been proved by simulation verification. The present invention realizes 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 only preferred embodiments of the present invention and cannot be considered to limit the scope of the present invention. All equivalent changes and improvements made within the scope of the present invention should still fall within the scope of the present invention.

Claims

1. A hydrogen-burning aviation turbine engine with magnesium hydride hydrogen storage, comprising a dual-rotor mixed-displacement turbofan engine basic assembly, equipped with an air inlet, a fan, a high-pressure compressor, a combustion chamber, a high-pressure turbine, a low-pressure turbine, a mixing chamber, and a nozzle, wherein the basic assembly works in coordination 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 high-temperature exhaust gas from the low-pressure turbine as a heat source to allow the magnesium hydride to absorb heat and release hydrogen; The magnesium hydride storage tank is arranged outside the engine, and is used to store magnesium hydride, and is circulated into the magnesium hydride heat exchanger through a mechanical device to release hydrogen; The intermediate hydrogen storage tank is arranged outside the engine and 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 hydrogen release rate of magnesium hydride and the hydrogen combustion rate; The internal airflow passes through the magnesium hydride heat exchanger, and then mixes with the external air and is discharged from the nozzle together. The high-temperature exhaust gas of the turbine core engine is used to achieve the heat absorption and hydrogen release of magnesium hydride. There is no need to provide energy from the outside for the hydrogen release of magnesium hydride. The matching problem of the hydrogen release rate of magnesium hydride and the hydrogen combustion rate is solved by the intermediate hydrogen storage tank, so that magnesium hydride can be used as a carrier of airborne hydrogen fuel to provide hydrogen fuel for aviation turbine engines.

2. The hydrogen-burning aviation turbine engine with magnesium hydride hydrogen storage as claimed in claim 1, characterized in that The magnesium hydride storage tank is made of a light, high-strength, corrosion-resistant material and is filled with magnesium hydride particles.

3. The hydrogen-burning aviation turbine engine with magnesium hydride hydrogen storage as claimed in claim 1, characterized in that The interior of the magnesium hydride heat exchanger is provided with a heat conduction structure, including but not limited to a spiral channel and a fin structure, to improve the heat exchange efficiency.

4. The hydrogen-burning aviation turbine engine with magnesium hydride hydrogen storage as claimed in claim 1, characterized in that The intermediate hydrogen storage tank is made of high-strength, corrosion-resistant, and well-sealed materials to ensure safe storage and supply of hydrogen.

5. The hydrogen-burning aviation turbine engine with magnesium hydride hydrogen storage as claimed in claim 1, characterized in that A mechanical device and a regulating valve are also provided. The mechanical device includes a delivery pump, a rotary valve and a circulation pipeline. The mechanical device is used to transport the magnesium hydride particles from the storage tank to the heat exchanger for hydrogen release, and to recover the magnesium hydride particles after hydrogen release and refill them into the storage tank; the regulating valve is used to adjust the hydrogen supply rate to ensure that the hydrogen supply amount matches the demand of the combustion chamber.

6. The hydrogen-burning aviation turbine engine with magnesium hydride hydrogen storage as claimed in claim 1, characterized in that A safety monitoring and protection system is also provided, which includes a hydrogen leak detection device, a temperature and pressure sensor, 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 sensor is used to monitor and adjust the temperature and pressure inside 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 sensor, and make decisions based on these signals, and accurately adjust the hydrogen supply rate according to the needs of the combustion chamber to ensure the stability and efficiency of the combustion process; the hydrogen flow controller is constructed using a programmable logic controller PLC, which can adjust the hydrogen supply rate. When hydrogen leakage or system abnormality is detected, the hydrogen supply is automatically cut off to ensure the safe operation of the system and maximize the heat exchange efficiency.

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