Dual-fuel hypersonic propulsion and power generation integrated system with chemical energy storage function and working method

Abstract

The invention discloses a dual-fuel hypersonic propulsion and power generation integrated system with a chemical energy storage function and a working method, and relates to the field of aero-engine energy management. The problems that an existing scramjet engine is unstable in aviation kerosene conveying and high-Mach-number combustion, thermal management and the like are solved. The system comprises an aviation kerosene tank, an aviation kerosene pump, an aviation kerosene-liquid metal heat exchanger, an ammonia storage tank and the like, the system combines chemical energy storage core characteristics of liquid ammonia, waste heat generated on the wall face of a combustion chamber is subjected to cascade recovery and efficient utilization, specifically, liquid metal serves as a heat conduction medium, redundant heat on the wall face of the combustion chamber is fully absorbed, and the heat conduction efficiency is improved. Liquid ammonia is heated through high-temperature liquid metal, liquid ammonia is promoted to absorb heat, gasify and crack, the liquid metal is further used for aviation fuel preheating, cascade transmission and efficient utilization of system energy are achieved, and the energy utilization rate of the whole system is greatly increased.

Description

Technical Field

[0001] This invention relates to the field of aero-engine energy management technology, specifically to a dual-fuel hypersonic propulsion and power generation integrated system with chemical energy storage and its operating method. Background Technology

[0002] Existing scramjet engines mostly use single-fuel aviation kerosene propulsion. Under hypersonic conditions with Mach numbers Ma≥8, there are problems such as insufficient heat sink of aviation kerosene and low flame propagation speed, which can easily lead to combustion instability and seriously restrict the reliable operation of the engine under extreme conditions. At the same time, a large amount of waste heat is generated on the combustion chamber wall of the engine. Existing technologies have low efficiency in recovering and utilizing this waste heat, failing to achieve effective energy utilization, resulting in system energy waste and poor overall energy efficiency.

[0003] In terms of airborne power generation, traditional power generation systems have poor coordination with propulsion systems, making it difficult to achieve stable power generation by relying on the energy cycle of the propulsion system, thus failing to meet the airborne power requirements of hypersonic aircraft. Furthermore, during aviation kerosene transportation, fuel consumption can easily cause pressure drops or even negative pressure in aviation kerosene storage tanks. Existing pressure regulation methods are complex in structure and have limited compensation effects, affecting the stability of the fuel supply system. In addition, existing engines lack chemical energy storage and dual-fuel co-combustion designs adapted to a wide range of Mach numbers, resulting in poor adaptability and an inability to balance propulsion efficiency and combustion stability at different flight Mach numbers.

[0004] In view of the technical shortcomings of scramjet engines in terms of fuel supply, combustion characteristics, thermal management and power generation integration, there is currently no effective integrated solution. Therefore, it is urgent to develop a power system that can achieve energy cascade utilization, stable combustion and coordinated propulsion and power generation to improve the overall performance of scramjet engines. Summary of the Invention

[0005] This invention aims to overcome problems in existing technologies such as jet fuel delivery, high Mach number combustion instability, and thermal management in scramjet engines. To address these issues, this invention proposes an integrated dual-fuel hypersonic propulsion and power generation system with chemical energy storage, along with its operating method. Furthermore, it leverages two-phase liquid metal magnetohydrodynamic (MHD) power generation technology to enhance onboard power generation capabilities.

[0006] To solve the above-mentioned technical problems, the present invention is achieved through the following technical solution: Option 1: This invention proposes a dual-fuel hypersonic propulsion and power generation integrated system with chemical energy storage, comprising: a jet fuel tank, a jet fuel pump, a jet fuel-liquid metal heat exchanger, an ammonia storage tank, a liquid ammonia pump, a mixer, a magnetohydrodynamic power generation channel, a gas-liquid two-phase separator, a cooling channel, an air intake, a combustion chamber, a tail nozzle, a gasbag, a pyrolysis gas pump, and a liquid metal pump; The outlet of the jet fuel storage tank is connected to the inlet of the jet fuel pump, the outlet of the jet fuel pump is connected to the cold end inlet of the jet fuel-liquid metal heat exchanger, and the cold end outlet of the jet fuel-liquid metal heat exchanger is connected to the first fuel inlet of the combustion chamber. The outlet of the ammonia storage tank is connected to the inlet of the liquid ammonia pump. The outlet of the liquid ammonia pump is connected to the cold end inlet of the mixer. The outlet of the mixer is connected to the inlet of the magnetohydrodynamic (MHD) power generation channel. The outlet of the MHD power generation channel is connected to the inlet of the gas-liquid two-phase separator. The gas phase outlet of the gas-liquid two-phase separator is connected to the inlet of the gas bag. The outlet of the gas bag is connected to the inlet of the pyrolysis gas pump. The pyrolysis gas pump is connected to the second fuel inlet of the combustion chamber. The liquid phase outlet of the gas-liquid two-phase separator is connected to the hot end inlet of the jet fuel-liquid metal heat exchanger. The hot end outlet of the jet fuel-liquid metal heat exchanger is connected to the inlet of the liquid metal pump. The outlet of the liquid metal pump is connected to the inlet of the cooling channel. The outlet of the cooling channel is connected to the hot end inlet of the mixer.

[0007] Furthermore, the jet fuel-liquid metal heat exchanger is an indirect heat exchanger.

[0008] Furthermore, an additional magnet is installed on the outside of the magnetohydrodynamic power generation channel.

[0009] Furthermore, the magnetohydrodynamic power generation channel is equipped with an ammonia cracking catalyst.

[0010] Furthermore, the system injects liquid ammonia into the mixer via a liquid ammonia pump, which drives the liquid metal to flow and vaporize during the heat absorption process.

[0011] Furthermore, the cooling channel covers the combustion chamber to cool it down.

[0012] Furthermore, the combustion chamber is provided with grooves to optimize the internal flow field distribution.

[0013] Furthermore, the airbag is installed inside the aviation kerosene storage tank to fill the empty volume of the aviation kerosene storage tank and to pre-pressurize the aviation kerosene.

[0014] Furthermore, the jet fuel storage tank, ammonia storage tank, and airbag outlet are all equipped with filling valves.

[0015] Option 2: The working method of the dual-fuel hypersonic propulsion and power generation integrated system with chemical energy storage as described in any one of Options 1, wherein the method includes: When the flight Mach number is below Ma8, the engine uses only aviation kerosene for combustion. Liquid metal is pumped out by a liquid metal pump, enters the cooling channel to absorb heat from the combustion chamber walls, and enters the magnetohydrodynamic power generation channel to generate electricity under the influence of a magnetic field. After power generation, the liquid metal enters the aviation kerosene-liquid metal heat exchanger to preheat the aviation kerosene. The aviation kerosene then enters the combustion chamber for combustion, and the liquid metal enters the cooling channel, completing a closed-loop cycle. Liquid ammonia in the ammonia storage tank is pumped out by a liquid ammonia pump and enters the cold end inlet of the mixer, where it undergoes thermal exchange with the liquid metal entering the hot end inlet of the mixer. It then undergoes cracking in the liquid metal power generation channel, and the cracked gas is stored in a gas bladder to maintain the pressure inside the aviation kerosene storage tank. When the flight Mach number is greater than Ma8, hydrogen and aviation kerosene are used as dual fuels. The cracked gas stored in the gasbag enters the combustion chamber and is mixed with aviation kerosene for combustion.

[0016] The advantages of this invention are: The present invention discloses a dual-fuel hypersonic propulsion and power generation integrated system with chemical energy storage. At low Mach numbers, only jet fuel is burned, and the cracked gas from the ammonia-driven LMMHD power generation is stored in a gasbag. This gasbag is used to fill the empty volume of the jet fuel tank and simultaneously pre-pressurizes the jet fuel to ensure the stability of fuel supply. At high Mach numbers, both jet fuel and ammonia cracked gas are burned simultaneously, effectively increasing the heat release of fuel and the flow rate of the propellant, thereby significantly increasing the system thrust and meeting the propulsion requirements at high Mach numbers.

[0017] The present invention discloses a dual-fuel hypersonic propulsion and power generation integrated system with chemical energy storage, which stores heat dissipation from the wall at low Mach numbers in the form of chemical energy at high density for propulsion at high Mach numbers, thereby improving the overall energy utilization rate over a wide speed range.

[0018] The present invention discloses a dual-fuel hypersonic propulsion and power generation integrated system with chemical energy storage. The liquid ammonia-driven LMMHD power generation system has a simple composition and high power density.

[0019] The present invention discloses a dual-fuel hypersonic propulsion and power generation integrated system with chemical energy storage. Combining the core characteristics of liquid ammonia's chemical energy storage, it implements cascaded recovery and efficient utilization of waste heat generated on the combustion chamber wall. Specifically, liquid metal is used as a heat conduction medium to fully absorb redundant heat from the combustion chamber wall. The high-temperature liquid metal is used to heat the liquid ammonia, causing it to absorb heat and vaporize and crack. The liquid metal is then used to preheat aviation kerosene, realizing cascaded energy transfer and efficient utilization of the system, and significantly improving the energy efficiency of the entire system.

[0020] The present invention discloses a dual-fuel hypersonic propulsion and power generation integrated system with chemical energy storage, which adopts a concave cavity combustion chamber design. By optimizing the internal flow field distribution of the combustion chamber, the stability of the mixed fuel combustion process is effectively enhanced, combustion fluctuations are suppressed, and fuel combustion efficiency is further improved, thus ensuring stable propulsion of the system. Attached Figure Description

[0021] Figure 1 This is a schematic diagram of the structure of a dual-fuel hypersonic propulsion and power generation integrated system with chemical energy storage as described in Embodiment 1.

[0022] Among them, there are: 1 jet fuel tank, 2 jet fuel pump, 3 jet fuel-liquid metal heat exchanger, 4 ammonia storage tank, 5 liquid ammonia pump, 6 mixer, 7 magnetohydrodynamic power generation channel, 8 gas-liquid two-phase separator, 9 cooling channel, 10 air intake, 11 combustion chamber, 12 tail nozzle, 13 airbag, 14 pyrolysis gas pump, and 15 liquid metal pump. Detailed Implementation

[0023] To make the objectives, technical solutions, and advantages of the embodiments of this application clearer, the technical solutions of the embodiments of this application will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only a part of the embodiments of this application, and not all of them.

[0024] Implementation Method 1, see [link] Figure 1 This embodiment describes a dual-fuel hypersonic propulsion and power generation integrated system with chemical energy storage, specifically including: aviation kerosene storage tank 1, aviation kerosene pump 2, aviation kerosene-liquid metal heat exchanger 3, ammonia storage tank 4, liquid ammonia pump 5, mixer 6, magnetohydrodynamic power generation channel 7, gas-liquid two-phase separator 8, cooling channel 9, air intake 10, combustion chamber 11, tail nozzle 12, airbag 13, pyrolysis gas pump 14, and liquid metal pump 15.

[0025] The outlet of the jet fuel storage tank 1 is connected to the inlet of the jet fuel pump 2, the outlet of the jet fuel pump 2 is connected to the cold end inlet of the jet fuel-liquid metal heat exchanger 3, and the cold end outlet of the jet fuel-liquid metal heat exchanger 3 is connected to the first fuel inlet of the combustion chamber 11. The outlet of the ammonia storage tank 4 is connected to the inlet of the liquid ammonia pump 5. The outlet of the liquid ammonia pump 5 is connected to the cold end inlet of the mixer 6. The outlet of the mixer 6 is connected to the inlet of the magnetohydrodynamic power generation channel 7. The outlet of the magnetohydrodynamic power generation channel 7 is connected to the inlet of the gas-liquid two-phase separator 8. The gas phase outlet of the gas-liquid two-phase separator 8 is connected to the inlet of the gas bag 13. The outlet of the gas bag 13 is connected to the inlet of the cracking gas pump 14. The outlet of the cracking gas pump 14 is connected to the second fuel inlet of the combustion chamber 11. The liquid phase outlet of the gas-liquid two-phase separator 8 is connected to the hot end inlet of the jet fuel-liquid metal heat exchanger 3. The hot end outlet of the jet fuel-liquid metal heat exchanger 3 is connected to the inlet of the liquid metal pump 15. The outlet of the liquid metal pump 15 is connected to the inlet of the cooling channel 9. The outlet of the cooling channel 9 is connected to the hot end inlet of the mixer 6.

[0026] Furthermore, a preferred embodiment is provided in which the jet fuel-liquid metal heat exchanger 3 is a wall-type heat exchanger.

[0027] Furthermore, in a preferred embodiment, the cooling channel 9 covers the combustion chamber 11.

[0028] Furthermore, in a preferred embodiment, an additional magnet is installed on the outside of the magnetohydrodynamic power generation channel 7.

[0029] Furthermore, a preferred embodiment is provided in which the system injects liquid ammonia into the mixer 6 via a liquid ammonia pump to ensure thorough mixing of the liquid ammonia and liquid metal, enhancing the mixing effect between the two and thus promoting thermodynamic exchange. The liquid ammonia drives the liquid metal to flow and vaporizes during the heat absorption process.

[0030] Furthermore, in a preferred embodiment, the magnetohydrodynamic power generation channel 7 is provided with an ammonia cracking catalyst.

[0031] Furthermore, in a preferred embodiment, the combustion chamber 11 is provided with a groove.

[0032] Furthermore, in a preferred embodiment, the airbag 13 is installed inside the aviation kerosene storage tank 1.

[0033] Furthermore, a preferred embodiment is provided in which the outlets of the aviation kerosene storage tank 1, the ammonia storage tank 4, and the airbag 13 are all equipped with filling valves.

[0034] Implementation Method 2: A working method based on the dual-fuel hypersonic propulsion and power generation integrated system with chemical energy storage described in Implementation Method 1, the method comprising: When the flight Mach number is below Ma8, the engine only uses aviation kerosene for combustion. Liquid metal is pumped out by liquid metal pump 15, enters cooling channel 9 to absorb heat from the combustion chamber wall, and enters magnetohydrodynamic power generation channel 7 to generate electricity under the action of a magnetic field. After power generation, the liquid metal enters aviation kerosene-liquid metal heat exchanger 3 to preheat the aviation kerosene. The aviation kerosene enters combustion chamber 11 for combustion, and the liquid metal enters cooling channel 9 to complete the closed cycle. Liquid ammonia in ammonia storage tank 4 is drawn out by liquid ammonia pump 5 and enters the cold end inlet of mixer 6 to exchange heat with the liquid metal entering the hot end inlet of mixer 6. Then, it is cracked in the liquid metal power generation channel. The cracked gas is stored in gasbag 13 to maintain the pressure in the aviation kerosene storage tank and avoid negative pressure to affect aviation kerosene transportation.

[0035] When the flight Mach number is greater than Ma8, hydrogen and aviation kerosene are used as dual fuels. The cracked gas stored in the airbag 13 enters the combustion chamber 11 and is mixed with aviation kerosene for combustion to improve the problem of unstable combustion at high Mach numbers.

[0036] In summary, this embodiment combines the core characteristics of liquid ammonia's chemical energy storage to achieve cascaded recovery and efficient utilization of waste heat generated on the combustion chamber walls. Specifically, liquid metal is used as a heat transfer medium to fully absorb redundant heat from the combustion chamber walls. The high-temperature liquid metal is used to heat the liquid ammonia, causing it to absorb heat and vaporize and crack. The liquid metal is then used to preheat aviation kerosene, realizing cascaded energy transfer and efficient utilization of the system, and significantly improving the overall energy efficiency of the system.

[0037] Those skilled in the art will understand that the above description is merely a preferred embodiment of the present invention, and the features described in the various embodiments and / or claims of this disclosure can be combined or combined in various ways, even if such combinations or combinations are not explicitly described in this disclosure. This is not intended to limit the present invention. Although the present invention has been described in detail with reference to the foregoing embodiments, those skilled in the art can still modify the technical solutions described in the foregoing embodiments or make equivalent substitutions for some of the technical features. Any modifications, equivalent substitutions, improvements, etc., made within the spirit and principles of the present invention should be included within the protection scope of the present invention.

[0038] Although preferred embodiments of the invention have been described, those skilled in the art, upon learning the basic inventive concept, can make other changes and modifications to these embodiments. Therefore, the appended claims are intended to be interpreted as including both the preferred embodiments and all changes and modifications falling within the scope of the invention. Clearly, those skilled in the art can make various alterations and modifications to the invention without departing from its spirit and scope. Thus, if these modifications and modifications of the invention fall within the scope of the claims and their equivalents, the invention is also intended to include these modifications and modifications.

Claims

1. A dual-fuel hypersonic propulsion and power generation integrated system with chemical energy storage, characterized in that, The system includes a jet fuel storage tank (1), a jet fuel pump (2), a jet fuel-liquid metal heat exchanger (3), an ammonia storage tank (4), a liquid ammonia pump (5), a mixer (6), a magnetohydrodynamic power generation channel (7), a gas-liquid two-phase separator (8), a cooling channel (9), an air intake (10), a combustion chamber (11), a tail nozzle (12), an airbag (13), a pyrolysis gas pump (14), and a liquid metal pump (15). The outlet of the aviation kerosene storage tank (1) is connected to the inlet of the aviation kerosene pump (2), the outlet of the aviation kerosene pump (2) is connected to the cold end inlet of the aviation kerosene-liquid metal heat exchanger (3), and the cold end outlet of the aviation kerosene-liquid metal heat exchanger (3) is connected to the first fuel inlet of the combustion chamber (11). The outlet of the ammonia storage tank (4) is connected to the inlet of the liquid ammonia pump (5), the outlet of the liquid ammonia pump (5) is connected to the cold end inlet of the mixer (6), the outlet of the mixer (6) is connected to the inlet of the magnetohydrodynamic power generation channel (7), the outlet of the magnetohydrodynamic power generation channel (7) is connected to the inlet of the gas-liquid two-phase separator (8), the gas phase outlet of the gas-liquid two-phase separator (8) is connected to the inlet of the gas bag (13), and the outlet of the gas bag (13) is connected to the inlet of the pyrolysis gas pump (14). The pyrolysis gas pump (14) is connected to the second fuel inlet of the combustion chamber (11), the liquid phase outlet of the gas-liquid two-phase separator (8) is connected to the hot end inlet of the jet fuel-liquid metal heat exchanger (3), the hot end outlet of the jet fuel-liquid metal heat exchanger (3) is connected to the inlet of the liquid metal pump (15), the outlet of the liquid metal pump (15) is connected to the inlet of the cooling channel (9), and the outlet of the cooling channel (9) is connected to the hot end inlet of the mixer (6).

2. The dual-fuel hypersonic propulsion and power generation integrated system with chemical energy storage according to claim 1, characterized in that, The jet fuel-liquid metal heat exchanger (3) is a partitioned heat exchanger.

3. The dual-fuel hypersonic propulsion and power generation integrated system with chemical energy storage according to claim 1, characterized in that, An additional magnet is installed on the outside of the magnetohydrodynamic power generation channel (7).

4. The dual-fuel hypersonic propulsion and power generation integrated system with chemical energy storage according to claim 3, characterized in that, The magnetohydrodynamic power generation channel (7) is equipped with an ammonia cracking catalyst.

5. The dual-fuel hypersonic propulsion and power generation integrated system with chemical energy storage according to claim 1, characterized in that, The system injects liquid ammonia into the mixer (6) via a liquid ammonia pump, which is used to drive the liquid metal to flow and vaporize during the heat absorption process.

6. The dual-fuel hypersonic propulsion and power generation integrated system with chemical energy storage according to claim 1, characterized in that, The cooling channel (9) covers the combustion chamber (11) and is used to cool the combustion chamber (11).

7. The dual-fuel hypersonic propulsion and power generation integrated system with chemical energy storage according to claim 1, characterized in that, The combustion chamber (11) is provided with grooves to optimize the flow field distribution inside the combustion chamber (11).

8. The dual-fuel hypersonic propulsion and power generation integrated system with chemical energy storage according to claim 1, characterized in that, The airbag (13) is installed inside the aviation kerosene storage tank (1) to fill the empty volume of the aviation kerosene storage tank and to pre-pressurize the aviation kerosene.

9. The dual-fuel hypersonic propulsion and power generation integrated system with chemical energy storage according to claim 1, characterized in that, The outlets of the aviation kerosene storage tank (1), ammonia storage tank (4), and airbag (13) are all equipped with filling valves.

10. The method for operating the dual-fuel hypersonic propulsion and power generation integrated system with chemical energy storage according to any one of claims 1-9, characterized in that, The method includes: When the flight Mach number is below Ma8, the engine only uses aviation fuel for combustion. Liquid metal is pumped out by liquid metal pump (15), enters the cooling channel (9) to absorb heat from the combustion chamber wall, enters the magnetohydrodynamic power generation channel (7) to generate electricity under the action of a magnetic field, and the liquid metal after power generation enters the aviation fuel-liquid metal heat exchanger (3) to preheat the aviation fuel. The aviation fuel enters the combustion chamber (11) for combustion, and the liquid metal enters the cooling channel (9) to complete the closed cycle. Liquid ammonia in the ammonia storage tank (4) is drawn out by liquid ammonia pump (5) and enters the cold end inlet of the mixer (6) to exchange heat with the liquid metal entering the hot end inlet of the mixer (6). Then, it is cracked in the liquid metal power generation channel. The cracked gas is stored in the gas bag (13) to maintain the pressure in the aviation fuel storage tank. When the flight Mach number is greater than Ma8, hydrogen and aviation kerosene are used as dual fuels. The cracked gas stored in the airbag (13) enters the combustion chamber (11) and is mixed with aviation kerosene for combustion.

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