Axial grading turbofan engine based on methanol fuel afterburning

Abstract

The invention discloses an axial grading turbofan engine based on methanol fuel afterburning, relates to the technical field of aero-engines, and solves the problems that an existing turbofan engine is high in carbon emission, high in overall NOx and difficult in heat efficiency improvement. The system comprises an air inlet channel, a fan, an air compressor, a combustion chamber, an afterburning chamber, a turbine, an exhaust nozzle and a fuel system, one end of the air inlet channel communicates with the atmosphere, and the other end of the air inlet channel communicates with the inlet end of the fan; the fan, the gas compressor, the combustion chamber, the afterburning chamber, the turbine and the exhaust nozzle are sequentially communicated; the fuel system provides aviation kerosene for the combustion chamber and provides methanol for the afterburning chamber; fuel gas generated by fuel combustion drives the turbine to do work; the turbine is connected with the fan and the gas compressor through a shaft and drives the fan and the gas compressor to work. Through axial grading afterburning, distribution of fuel in the axial position is optimized, the supply amount of the fuel in the two stages can be flexibly regulated and controlled, a more reasonable air distribution mode is matched, and the overall NOx level and carbon emission can be effectively reduced.

Description

Technical Field

[0001] The present invention relates to the technical field of aeroengines, and particularly to an axial staged turbofan engine based on methanol fuel afterburning. Background Art

[0002] In recent years, the impact of environmental protection issues on the aviation industry has been intensifying. Traditional aviation fuels, such as aviation kerosene, will release a large amount of carbon dioxide and harmful gases during the combustion process, and these emissions have a negative impact on the environment and climate change. Methanol, as a relatively clean alternative fuel, has low sulfur and low particulate emissions, and the main by-products generated during combustion are carbon dioxide and water. Therefore, the use of methanol fuel can significantly reduce emissions and help relieve the environmental pressure on the aviation industry.

[0003] Secondly, with the progress of fuel injection and combustion technologies, the methanol afterburning system has become increasingly feasible in aeroengines. Modern engine designs can precisely control the fuel injection amount and combustion process, thereby optimizing the fuel-air mixture and ensuring stable combustion effects. The afterburning technology can improve the thrust and efficiency of the engine under high-altitude and high-speed flight conditions, making methanol fuel exhibit good performance in practical applications. Summary of the Invention

[0004] In order to solve the problems of high carbon emissions, high overall NOx, and difficulty in further improving the thermal efficiency of existing turbofan engines mentioned above, the present invention hereby provides an axial staged turbofan engine based on methanol fuel afterburning. Through axial staged afterburning, the present invention optimizes the distribution of fuel in the axial position, can flexibly regulate the supply amount of fuel at two stages, and in combination with a more reasonable air distribution form, can effectively reduce the overall NOx level and carbon emissions.

[0005] The present invention provides an axial staged turbofan engine based on methanol fuel afterburning, which specifically includes an air inlet duct, a fan, a compressor, a combustion chamber, an afterburning chamber, a turbine, a tail nozzle, and a fuel system. One end of the air inlet duct is communicated with the atmosphere, and the other end is communicated with the fan inlet end; the fan, the compressor, the combustion chamber, the afterburning chamber, the turbine, and the tail nozzle are sequentially communicated; the fuel system supplies aviation kerosene to the combustion chamber and supplies methanol to the afterburning chamber; the fuel combustion generates gas to drive the turbine to do work; the turbine is connected to the fan and the compressor through a shaft to drive the fan and the compressor to work.

[0006] Furthermore, the fuel system includes an aviation kerosene storage tank and a methanol storage tank. The aviation kerosene storage tank is communicated with the combustion chamber, and the methanol storage tank is communicated with the afterburning chamber.

[0007] Furthermore, a filling valve is provided on the aviation kerosene storage tank.

[0008] Furthermore, a filling valve is provided on the methanol storage tank.

[0009] Further, the compressor includes a low-pressure compressor and a high-pressure compressor, and the fan, the low-pressure compressor, the high-pressure compressor, and the combustion chamber are connected in sequence.

[0010] Further, the turbine includes a high-pressure turbine and a low-pressure turbine, and the afterburning chamber, the high-pressure turbine, the low-pressure turbine, and the tail nozzle are connected in sequence; the high-pressure turbine drives the high-pressure compressor, and the low-pressure turbine drives the low-pressure compressor and the fan.

[0011] Further, the outlet end of the fan is communicated with the outer bypass duct.

[0012] The beneficial effects of an axial staged turbofan engine based on methanol fuel afterburning according to the present invention are as follows:

[0013] (1) The axial staged turbofan engine based on methanol fuel afterburning according to the present invention overcomes the problems of high carbon emissions, high overall NOx, and difficulty in further improving the thermal efficiency of existing turbofan engines. Through axial staged afterburning, the distribution of fuel in the axial position is optimized, the fuel supply to the two stages can be flexibly regulated, and the afterburning fuel can be quickly vaporized and burned using the heat generated by the primary combustion. Combined with a more reasonable air distribution form, the overall NOx level can be effectively reduced;

[0014] (2) The axial staged turbofan engine based on methanol fuel afterburning according to the present invention effectively improves the overall energy utilization rate of the engine system through the provided afterburning chamber, and can improve the thermal efficiency of the system without improving the performance of components;

[0015] (3) The axial staged turbofan engine based on methanol fuel afterburning according to the present invention effectively reduces the carbon emissions of the engine by supplementing methanol into the afterburning chamber. BRIEF DESCRIPTION OF THE DRAWINGS

[0016] The accompanying drawings forming a part of this application are used to provide a further understanding of the present invention. The schematic embodiments of the present invention and their descriptions are used to explain the present invention and do not constitute an improper limitation to the present invention.

[0017] In the drawings:

[0018] Figure 1 is a schematic structural diagram of an axial staged turbofan engine based on methanol fuel afterburning according to the present invention;

[0019] Wherein: 1 - air inlet duct; 2 - fan; 3 - low-pressure compressor; 4 - high-pressure compressor; 5 - combustion chamber; 6 - afterburning chamber; 7 - high-pressure turbine; 8 - low-pressure turbine; 9 - tail nozzle; 10 - aviation kerosene storage tank; 11 - methanol storage tank; 12 - outer bypass duct; 13 - inner bypass duct. DETAILED DESCRIPTION OF THE EMBODIMENTS

[0020] The technical solutions of the present invention will be clearly and completely described below in conjunction with the accompanying drawings. Obviously, the described embodiments are part of the embodiments of the present invention, rather than all of the embodiments. All other embodiments obtained by those of ordinary skill in the art based on the embodiments of the present invention without creative efforts shall fall within the protection scope of the present invention.

[0021] In the description of the present invention, it should be noted that the orientation or positional relationship indicated by the terms "center", "upper", "lower", "left", "right", "vertical", "horizontal", "inner", "outer", etc. is based on the orientation or positional relationship shown in the accompanying drawings. It is only for the convenience of describing the present invention and simplifying the description, rather than indicating or implying that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and thus should not be construed as a limitation to the present invention. In addition, the terms "first", "second", and "third" are only used for descriptive purposes and should not be construed as indicating or implying relative importance.

[0022] In the description of the present invention, it should be noted that unless otherwise clearly specified and defined, the terms "installed", "connected", and "connected" should be understood in a broad sense. For example, it can be a fixed connection, a detachable connection, or an integral connection; it can be a mechanical connection or an electrical connection; it can be directly connected or indirectly connected through an intermediate medium, and it can be the communication inside two elements. For those of ordinary skill in the art, the specific meanings of the above terms in the present invention can be understood according to specific situations.

[0023] In addition, the technical features involved in different embodiments of the present invention described below can be combined with each other as long as they do not conflict with each other.

[0024] Specific Embodiment 1: Refer to Figure 1Specifically describe this embodiment. An axial - staged turbofan engine based on methanol fuel after - burning specifically includes an inlet duct 1, a fan 2, a compressor, a combustion chamber 5, a re - combustion chamber 6, a turbine, a tail nozzle 9, and a fuel system. One end of the inlet duct 1 is in communication with the atmosphere, and the other end is in communication with the inlet end of the fan 2; the outlet end of the fan 2 is respectively in communication with the outer bypass duct 12 and the inner bypass duct 13. The air flowing into the outer bypass duct 12 is compressed by the outer bypass duct 12 and then discharged from the turbofan engine system to provide power for the aircraft. The outlet end of the fan 2 is in communication with the compressor through the inner bypass duct 13; the compressor, the combustion chamber 5, the re - combustion chamber 6, the turbine, and the tail nozzle 9 are connected in sequence; the fuel system supplies aviation kerosene to the combustion chamber 5 and methanol to the re - combustion chamber 6. In the re - combustion chamber 6, after - burning can further increase the thrust of the engine. The additional combustion stage can increase the temperature and pressure of the gas, thereby increasing the thrust of the engine, enabling the engine to be used in various environments, especially during acceleration or high - load flight; by adding methanol, the fuel supply amount at two levels can be flexibly adjusted, improving the combustion performance. Through the control of the main combustion and after - burning at two levels, an ideal temperature field is formed, while controlling the generation of NOx and reducing the NOx pollutant emission level; the gas generated by fuel combustion drives the turbine to do work; the turbine is connected to the fan 2 and the compressor through a shaft, driving the fan 2 and the compressor to work.

[0025] The fuel system includes an aviation kerosene storage tank 10 and a methanol storage tank 11. The aviation kerosene storage tank 10 is in communication with the combustion chamber 5, and the methanol storage tank 11 is in communication with the re - combustion chamber 6; aviation kerosene is stored in the aviation kerosene storage tank 10, and methanol is stored in the methanol storage tank 11. Compared with traditional fossil fuels, methanol releases less carbon dioxide during combustion, which can effectively reduce greenhouse gas emissions and contribute to combating climate change. The advantage of low - carbon emissions after methanol fuel combustion significantly reduces the carbon emissions of the engine. A filling valve is provided on the aviation kerosene storage tank 10. A filling valve is provided on the methanol storage tank 11.

[0026] The compressor includes a low - pressure compressor 3 and a high - pressure compressor 4. The fan 2, the low - pressure compressor 3, the high - pressure compressor 4, and the combustion chamber 5 are connected in sequence.

[0027] The turbine includes a high - pressure turbine 7 and a low - pressure turbine 8. The re - combustion chamber 6, the high - pressure turbine 7, the low - pressure turbine 8, and the tail nozzle 9 are connected in sequence; the high - pressure turbine 7 is coaxially arranged with the high - pressure compressor 4 and drives the high - pressure compressor 4 to work through a rotor shaft, providing power for it; the low - pressure turbine 8 is coaxially arranged with the fan 2 and the low - pressure compressor 3, and the low - pressure turbine 8 drives the fan 2 and the low - pressure compressor 3 to work through a rotor shaft, providing power for them.

[0028] The specific working process of an axial - staged turbofan engine based on methanol fuel after - burning according to the present invention is as follows:

[0029] Outside the turbofan engine, air from the distant oncoming flow enters the intake duct 1 under the suction of the external compressor. After being rectified by the wall of the intake duct 1, a uniform airflow with low speed and high pressure is formed and then introduced into the fan 2. In the fan 2, the air is pressurized and then divided into two paths. Most of the gas directly enters the outer bypass duct 12, and after being decompressed and accelerated by the wall of the outer bypass duct 12, it is ejected from the outlet to provide power for the aircraft. A small part of the gas enters the inner bypass duct 13 and flows into the low-pressure compressor 3.

[0030] The air in the low-pressure compressor 3 then flows into the high-pressure compressor 4 for three-stage pressurization. The high-temperature and high-pressure air formed enters the combustion chamber 5, where it is fully mixed with fuel and burned. The high-temperature and high-pressure combustion gas formed first enters the afterburner 6 to be fully mixed with methanol and burned. The high-temperature and high-pressure afterburned gas formed enters the high-pressure turbine 7 to drive the high-pressure turbine 7 to do work, providing power for the operation of the high-pressure compressor 4.

[0031] After the gas finishes doing work in the high-pressure turbine 7, it then flows into the low-pressure turbine 8 to do work, providing power for the fan 2 and the low-pressure compressor 3. The gas flowing out of the low-pressure turbine 8 finally enters the tail nozzle 9, where it is decompressed and accelerated and then quickly ejected to provide power for the aircraft.

[0032] Summarizing the above embodiments, an axial-stage turbofan engine based on methanol fuel afterburning described in the present invention overcomes the problems of high carbon emissions, relatively high overall NOx, and difficulty in further improving the thermal efficiency of existing turbofan engines. Through axial-stage afterburning, the distribution of fuel in the axial position is optimized, the supply of fuel at two stages can be flexibly regulated, and the afterburning fuel can be quickly vaporized and burned using the heat generated by primary combustion. Combined with a more reasonable air distribution form, the overall NOx level can be effectively reduced. An axial-stage turbofan engine based on methanol fuel afterburning described in the present invention effectively improves the overall energy utilization rate of the engine system by setting the afterburner 6, and can improve the thermal efficiency of the system without improving the performance of components. An axial-stage turbofan engine based on methanol fuel afterburning described in the present invention effectively reduces the carbon emissions of the engine by supplementing methanol into the afterburner 6, meeting the development goal of carbon emission reduction in China.

[0033] In the specific embodiments described above, the purpose, technical solutions, and beneficial effects of the present invention are further described in detail. It should be understood that the above are only specific embodiments of the present invention and are not used to limit the invention. It can also be a reasonable combination of the features described in the above embodiments. Any modifications, equivalent replacements, improvements, etc. made within the spirit and principles of the present invention shall be included within the protection scope of the present invention.

Claims

1. An axial - staged turbofan engine based on methanol fuel after - burning, characterized in that: It includes an air inlet (1), a fan (2), a compressor, a combustion chamber (5), a afterburner (6), a turbine, a nozzle (9) and a fuel system. One end of the air inlet (1) is in communication with the atmosphere, and the other end is in communication with the inlet end of the fan (2); the fan (2), the compressor, the combustion chamber (5), the afterburner (6), the turbine and the nozzle (9) are connected in sequence; the fuel system supplies aviation kerosene to the combustion chamber (5) and methanol to the afterburner (6); the gas generated by fuel combustion drives the turbine to do work; the turbine is connected to the fan (2) and the compressor through a shaft, and drives the fan (2) and the compressor to work.

2. The axial staged turbofan engine based on methanol fuel afterburning according to claim 1, wherein: The fuel system includes a kerosene storage tank (10) and a methanol storage tank (11). The kerosene storage tank (10) is in communication with the combustion chamber (5), and the methanol storage tank (11) is in communication with the afterburner (6).

3. The axial - staged turbofan engine based on methanol fuel after - burning according to claim 2, wherein: A filling valve is provided on the kerosene storage tank (10).

4. The axial - staged turbofan engine based on methanol fuel after - burning according to claim 2, wherein: A filling valve is provided on the methanol storage tank (11).

5. The axial staging turbofan engine based on methanol fuel afterburning according to claim 1, wherein: The compressor includes a low-pressure compressor (3) and a high-pressure compressor (4). The fan (2), the low-pressure compressor (3), the high-pressure compressor (4) and the combustion chamber (5) are connected in sequence.

6. The axial staged turbofan engine based on methanol fuel afterburning according to claim 5, characterized in that: The turbine includes a high-pressure turbine (7) and a low-pressure turbine (8). The afterburner (6), the high-pressure turbine (7), the low-pressure turbine (8) and the nozzle (9) are connected in sequence; the high-pressure turbine (7) drives the high-pressure compressor (4), and the low-pressure turbine (8) drives the low-pressure compressor (3) and the fan (2).

7. The axial - staged turbofan engine based on methanol fuel after - burning according to claim 1, wherein: The outlet end of the fan (2) is in communication with the outer duct (12).

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