Methanol / aviation kerosene dual-fuel chemical regenerative hybrid aero-engine

Abstract

The invention discloses a methanol / aviation kerosene dual-fuel chemical regenerative hybrid aero-engine, relates to the technical field of environment-friendly processing, and solves the problems that the electricity demand of turboshaft engine airborne equipment is increased and the carbon emission of the engine is too high. A core engine system comprises an aviation fuel storage tank, an air inlet channel, an air compressor, a combustion chamber, a turbine system, an exhaust nozzle and a rotor wing, wherein the aviation fuel storage tank is communicated with the combustion chamber; the air inlet channel, the air compressor and the combustion chamber communicate in sequence. One part of the methanol reforming product is introduced into a combustion chamber to be mixed with aviation fuel for combustion, and the other part of the methanol reforming product generates power through a fuel cell; the combustion chamber, the turbine system and the exhaust nozzle are communicated, and fuel gas generated by the combustion chamber is introduced into the turbine system to drive the turbine system; the turbine system drives the gas compressor and the rotor wing. The fuel cell is used for generating electricity to meet the electricity demand of airborne equipment, the shaft power on the engine main shaft is reduced, the engine output power is effectively improved, and the operation stability of a core engine system is improved.

Description

Technical Field

[0001] The present invention relates to the field of aviation power technology, and in particular to a methanol / aviation kerosene dual-fuel chemical regenerative hybrid aviation engine. Background Art

[0002] High-temperature proton exchange membrane fuel cells have strong fuel applicability, especially under high-temperature conditions. They have low requirements for hydrogen purity and can even directly use fuel gas containing a small amount of carbon monoxide. In addition, due to their high energy conversion efficiency, wide temperature range, high power generation capacity, zero pollution emissions, no mechanical vibration and noise, and low radiation, they show great development potential in the future green aviation field.

[0003] Turboshaft engines are currently the primary power source for helicopters. With the continued expansion of helicopter applications across a wide range of missions in recent years, the number and complexity of onboard equipment has increased significantly, including electrical systems, displays and controls, navigation systems, communications equipment, trim mechanisms, and stability augmentation systems. This has led to a rapid increase in helicopter power requirements. Due to helicopters' unique capabilities, such as vertical takeoff and landing, hovering, and complex flight conditions, turboshaft engines are typically designed for short shaftlines, high speeds, and heavy loads. Their operating conditions also vary dramatically under varying flight conditions. Traditional approaches, which extract power from the engine's main shaft to power onboard equipment, can compromise the stability of core engine systems, reduce output power, increase fuel consumption and carbon emissions, and even reduce rotor thrust output, impacting flight performance. Therefore, helicopter onboard power generation technology faces new challenges, and there is an urgent need to develop a novel turboshaft engine power generation system to meet the growing power requirements of modern helicopters and ensure stable and efficient flight performance. Summary of the Invention

[0004] To address the aforementioned issues of increased power demand from existing turboshaft engine onboard equipment and excessive carbon emissions, this invention proposes a methanol / jet fuel dual-fuel, chemically regenerative hybrid aircraft engine. This invention uses fuel cells to generate electricity to meet the power needs of onboard equipment, reducing the power drawn from the engine's main shaft, effectively increasing engine output and improving the operational stability of the core engine system.

[0005] The present invention proposes a methanol / aviation kerosene dual-fuel chemical regenerative hybrid aircraft engine, which specifically includes a core engine system and a fuel cell system, which are connected; the core engine system includes an aviation kerosene storage tank, an air intake channel, a compressor, a combustion chamber, a turbine system, a tail nozzle and a rotor, and the aviation kerosene storage tank and the combustion chamber are connected; the air intake channel, the compressor and the combustion chamber are connected in sequence; the fuel cell system and the combustion chamber are connected, and a part of the products produced by methanol reforming are introduced into the combustion chamber; the combustion chamber, the turbine system and the tail nozzle are connected in sequence, and the fuel gas generated by the combustion of the fuel in the combustion chamber is introduced into the turbine system to drive the turbine system to work; the turbine system drives the compressor and the rotor respectively; another part of the products produced by methanol reforming are used to generate electricity.

[0006] Furthermore, the fuel cell system includes a methanol storage tank, a reforming reactor, a fuel diverter and a fuel cell, and the methanol storage tank, the reforming reactor and the fuel diverter are connected in sequence; the fuel diverter is connected to the combustion chamber and the anode of the fuel cell respectively; and one outlet of the compressor is connected to the cathode of the fuel cell.

[0007] Furthermore, the exhaust gas from the turbine system exchanges heat with the reforming reactor and is then discharged through a tail nozzle.

[0008] Furthermore, the cathode outlet of the fuel cell is connected to an inlet of the reforming reactor.

[0009] Furthermore, a pressure reducing valve is provided between the fuel distributor and the anode of the fuel cell.

[0010] Furthermore, a fuel pump is provided between the methanol storage tank and the reforming reactor.

[0011] Furthermore, the turbine system includes a gas turbine and a power turbine, and the combustion chamber, the gas turbine, the hot side of the power turbine reforming reactor and the tail nozzle are connected in sequence; the gas turbine drives the compressor; and the power turbine drives the rotor.

[0012] Furthermore, the power turbine drives the rotor through a gearbox.

[0013] Furthermore, a fuel pump is provided between the aviation fuel storage tank and the combustion chamber.

[0014] Furthermore, the fuel pump is connected to the fuel cell.

[0015] The beneficial effects of the methanol / aviation kerosene dual-fuel chemical regenerative hybrid aircraft engine described in the present invention are:

[0016] (1) The methanol / aviation kerosene dual-fuel chemical regenerative hybrid aircraft engine described in the present invention solves the problems of increased power demand for onboard equipment of existing turboshaft engines and excessive carbon emissions from the engine. By using fuel cells to generate electricity to meet the power demand of onboard equipment and reducing the shaft power extracted from the engine main shaft, the engine output power can be effectively increased and the operating stability of the core engine system can be improved. By using methanol fuel and cleverly utilizing the reforming reaction of alcohol fuel to achieve secondary utilization of exhaust waste heat, the energy utilization rate of the system can be improved. In addition, the excess alcohol-hydrogen fuel can be mixed with aviation kerosene for combustion, which can reduce the fuel consumption and carbon emissions of the engine.

[0017] (2) The methanol / aviation kerosene dual-fuel chemical regenerative hybrid aircraft engine described in the present invention can adjust the power generation by adjusting the fuel flow supplied to the fuel cell. Compared with the solution of carrying batteries, it can improve the flexibility and endurance of the system and enhance the adaptability of the aircraft when the flight conditions are more complex. BRIEF DESCRIPTION OF THE DRAWINGS

[0018] The drawings constituting a part of this application are used to provide a further understanding of the present invention. The illustrative embodiments of the present invention and their descriptions are used to explain the present invention and do not constitute improper limitations on the present invention.

[0019] In the attached figure:

[0020] Figure 1 This is a schematic structural diagram of a methanol / aviation kerosene dual-fuel chemical regenerative hybrid aircraft engine according to the present invention;

[0021] Among them: 1-jet fuel storage tank, 2-fuel pump 1, 3-air intake channel, 4-compressor, 5-combustion chamber, 6-gas turbine, 7-power turbine, 8-gearbox, 9-tail nozzle, 10-methanol storage tank, 11-fuel pump 2, 12-reforming reactor, 13-fuel splitter, 14-pressure reducing valve, 15-fuel cell. DETAILED DESCRIPTION

[0022] The following will clearly and completely describe the technical solutions of the present invention in conjunction with the accompanying drawings. Obviously, the embodiments described are only some of the embodiments of the present invention, not all of them. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without making any creative efforts shall fall within the scope of protection of the present invention.

[0023] In the description of the present invention, it should be noted that the terms "center," "upper," "lower," "left," "right," "vertical," "horizontal," "inner," "outer," and the like, indicating orientations or positional relationships, are based on the orientations or positional relationships shown in the accompanying drawings and are intended solely to facilitate the description of the present invention and simplify the description. They do not indicate or imply that the devices or components referred to must have a specific orientation, be constructed, or operate in a specific orientation. Therefore, they should not be construed as limitations on the present invention. Furthermore, the terms "first," "second," and "third" are used for descriptive purposes only and should not be construed as indicating or implying relative importance.

[0024] In the description of the present invention, it should be noted that, unless otherwise expressly specified or limited, the terms "installed," "connected," and "connected" should be understood in a broad sense. For example, they can refer to fixed connections, detachable connections, or integral connections; they can refer to mechanical connections or electrical connections; they can refer to direct connections or indirect connections through an intermediate medium; and they can refer to internal communication between two components. Those skilled in the art will understand the specific meanings of the above terms in the present invention based on the specific circumstances.

[0025] 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.

[0026] Specific implementation method 1: See Figure 1 This embodiment is described in detail. The methanol / jet fuel dual-fuel chemical regenerative hybrid aircraft engine described in this embodiment specifically includes a core engine system and a fuel cell system, and the core engine system and the fuel cell system are connected; the core engine system includes a jet fuel storage tank 1, an air intake channel 3, a compressor 4, a combustion chamber 5, a turbine system, a tail nozzle 9 and a rotor, and the jet fuel storage tank 1 and the combustion chamber 5 are connected; the air intake channel 3, the compressor 4 and the combustion chamber 5 are connected in sequence; the fuel cell system and the combustion chamber 5 are connected, and a part of the product produced by methanol reforming is introduced into the combustion chamber 5 to be burned together with the jet fuel and air in the combustion chamber 5; the combustion chamber 5, The turbine system and the tail nozzle 9 are connected in sequence, and a mixture of jet fuel, hydrogen, alcohol fuel and carbon monoxide is burned in the combustion chamber 5. The combustion gas generated by the combustion of the fuel in the combustion chamber 5 is introduced into the turbine system to drive the turbine system to work; the turbine system drives the compressor 4 and the rotor to work respectively; another part of the product produced by methanol reforming is used to generate electricity through the fuel cell 15. The fuel cell 15 generates electricity through the electrochemical reaction of hydrogen and oxygen to meet the electricity demand of the onboard equipment, reduce the shaft power extraction of the core engine system, and improve the output power of the engine, thereby improving the efficiency of the entire system.

[0027] The fuel cell system includes a methanol storage tank 10, a reforming reactor 12, a fuel diverter 13 and a fuel cell 15, and the methanol storage tank 10, the reforming reactor 12 and the fuel diverter 13 are connected in sequence; the fuel diverter 13 is connected to the combustion chamber 5 and the anode of the fuel cell 15 respectively, and a pressure reducing valve 14 is provided between the fuel diverter 13 and the anode of the fuel cell 15; the fuel diverter 13 divides the product after methanol reforming into two parts, one part with hydrogen as the main component flows through the pressure reducing valve 14 and enters the anode of the fuel cell 15 at an appropriate pressure to undergo an electrochemical reaction, and the rest is introduced into the combustion chamber 5 and mixed with jet fuel for combustion; the alcohol hydrogen fuel is introduced into the combustion chamber 5, and the mixture with jet fuel can improve the combustion characteristics, improve energy utilization efficiency, reduce the use of jet fuel, and reduce engine fuel consumption and carbon emissions; one outlet of the compressor 4 is connected to the cathode of the fuel cell 15, and air is sent to the cathode of the fuel cell 15.

[0028] The turbine system outlet is connected to the hot side of the reforming reactor 12. The exhaust gas from the turbine system exchanges heat with the reforming reactor 12 and is then discharged through the tail nozzle 9. The reforming reactor 12 and the chemical regenerator are integrated into a structure. The working fluids in the cold fluid channel are methanol fuel and water vapor, and the inner wall is coated with a catalyst. Under the heating effect of the high-temperature exhaust gas in the hot fluid channel, the methanol fuel and water vapor undergo a reforming reaction, resulting in products including hydrogen, carbon dioxide, carbon monoxide, and unreacted methanol fuel.

[0029] The fuel cell 15 is a high-temperature proton exchange membrane fuel cell, which performs well under the heat exchange conditions of high-temperature exhaust gas. The anode fuel is primarily hydrogen, with small amounts of carbon monoxide and alcohol-based fuels also included. The cathode outlet of the fuel cell 15 is connected to an inlet of the reforming reactor 12. The water vapor required for the reforming reaction in the reforming reactor 12 is generated by the electrochemical reaction within the fuel cell 15, and no external supply is required.

[0030] The turbine system includes a gas turbine 6 and a power turbine 7. The combustion chamber 5, the gas turbine 6, the power turbine 7, the hot side of the reforming reactor 12 and the tail nozzle 9 are connected in sequence. The tail gas discharged by the power turbine 7 is discharged through the tail nozzle 9 after completing heat exchange with the reforming reactor 12; the gas turbine 6 is connected to the compressor 4 through the rotor shaft to drive the compressor 4 to work; the power turbine 7 is connected to the gearbox 8 through the rotor shaft, and the gearbox 8 is connected to the rotor through the rotor shaft, thereby driving the rotor to rotate.

[0031] A fuel pump 1 2 is provided between the jet fuel storage tank 1 and the combustion chamber 5 . A fuel pump 2 11 is provided between the methanol storage tank 10 and the reforming reactor 12 .

[0032] The fuel pump 1 2 and the fuel pump 2 11 are both connected to the fuel cell 15 , and the energy required for normal operation is provided by the fuel cell 15 .

[0033] The specific working process of the methanol / aviation kerosene dual-fuel chemical regenerative hybrid aircraft engine described in the present invention is as follows:

[0034] In the core engine system, fuel pump 2 pumps aviation kerosene from the aviation kerosene storage tank 1 into the combustion chamber 5 through suction. The air intake duct 3 draws in a large amount of air from the outside atmosphere, which is then pressurized by the compressor 4 and passed into the combustion chamber 5. The aviation kerosene and air are mixed with the alcohol-hydrogen fuel diverted by the fuel diverter 13 and a small amount of carbon monoxide, and then combust, rapidly forming high-temperature, high-pressure combustion gas. This combustion gas flows to the gas turbine 6, driving it to rotate and produce work. Simultaneously, the compressor 4, which is connected to the gas turbine 6 via the rotor shaft, is also driven to produce work. The combustion gas then flows to the power turbine 7, driving it to rotate and produce work. The energy is then transferred through the rotor shaft to the gearbox 8 and then to the rotor, providing the driving force for the rotor's rotation, thereby providing sufficient lift for the helicopter to fly.

[0035] In the fuel cell system, fuel pump 2 11 pumps methanol from the methanol storage tank 10 into the cold fluid channel of the reforming reactor 12 through suction. At the same time, the high-temperature exhaust gas that has driven the power turbine 7 to complete work passes through the chemical regenerator to the hot fluid channel of the reforming reactor 12, providing thermal energy for the reforming reaction of the methanol through heat exchange, and then is discharged into the atmosphere through the tail nozzle 9; the inner wall of the reforming reactor 12 is coated with a catalyst. After the methanol fuel absorbs sufficient heat to vaporize, it undergoes a reforming reaction with the water vapor generated by the fuel cell 15 under the action of the catalyst, and the reaction produces hydrogen, carbon dioxide, a small amount of carbon monoxide and unreacted alcohol fuel. After being diverted by fuel diverter 13, a portion, primarily hydrogen, is reduced to an appropriate pressure by pressure reducing valve 14 and directed to the anode of high-temperature proton exchange membrane fuel cell 15. Simultaneously, high-pressure air drawn from the compressor interstage 4 serves as the cathode working fluid. These two components react electrochemically to generate electricity, meeting the power needs of onboard equipment. The generated water vapor is returned to reforming reactor 12 to continue its methanol reforming process, while unreacted air is discharged directly into the atmosphere. The remaining hydrogen, carbon monoxide, and unreacted alcohol-based fuel diverted by fuel diverter 13 are directed to combustion chamber 5, where they are mixed with jet fuel for combustion to support the core engine system's energy needs.

[0036] Summarizing the above-mentioned implementation cases, the methanol / aviation kerosene dual-fuel chemical regenerative hybrid aircraft engine described in the present invention solves the problems of increased power demand for onboard equipment and excessive carbon emissions in existing turboshaft engines. By using fuel cells 15 to generate electricity to meet the power demand of onboard equipment and reducing the shaft power extracted from the engine main shaft, the engine output power can be effectively increased and the operating stability of the core engine system can be improved. By using methanol fuel and cleverly utilizing the reforming reaction of alcohol fuels to achieve secondary utilization of exhaust waste heat, the system's energy utilization rate can be improved. In addition, the combustion of excess alcohol-hydrogen fuel mixed with aviation kerosene can reduce the engine's fuel consumption and carbon emissions. The methanol / aviation kerosene dual-fuel chemical regenerative hybrid aircraft engine described in the present invention can adjust the power generation by adjusting the fuel flow supplied to the fuel cell 15. Compared with the solution of carrying batteries, it can improve the system's flexibility and endurance, and enhance the aircraft's adaptability when flight conditions are more complex.

[0037] The specific embodiments described above further illustrate the objectives, technical solutions, and beneficial effects of the present invention. It should be understood that the above description is merely a specific embodiment of the present invention and is not intended to limit the invention. Reasonable combinations of the features described in the above embodiments are also possible. Any modifications, equivalent substitutions, improvements, etc. made within the spirit and principles of the present invention shall be included in the scope of protection of the present invention.

Claims

1. A methanol-jet fuel dual-fuel chemical regenerative hybrid aircraft engine, characterized by: The invention comprises a core engine system and a fuel cell system, wherein the core engine system and the fuel cell system are connected; the core engine system comprises an aviation fuel storage tank (1), an air intake passage (3), a compressor (4), a combustion chamber (5), a turbine system, a tail nozzle (9) and a rotor, wherein the aviation fuel storage tank (1) and the combustion chamber (5) are connected; the air intake passage (3), the compressor (4) and the combustion chamber (5) are connected in sequence; the fuel cell system and the combustion chamber (5) are connected, and a part of the product produced by methanol reforming is introduced into the combustion chamber (5); the combustion chamber (5), the turbine system and the tail nozzle (9) are connected in sequence, and the fuel gas generated by the combustion of the fuel in the combustion chamber (5) is introduced into the turbine system to drive the turbine system to work; The turbine system drives the compressor (4) and the rotor respectively; another part of the product produced by methanol reforming is used to generate electricity.

2. The methanol-jet fuel dual-fuel chemical regenerative hybrid aircraft engine according to claim 1, characterized in that: The fuel cell system comprises a methanol storage tank (10), a reforming reactor (12), a fuel diverter (13) and a fuel cell (15); the methanol storage tank (10), the reforming reactor (12) and the fuel diverter (13) are connected in sequence; the fuel diverter (13) is connected to the combustion chamber (5) and the anode of the fuel cell (15) respectively; and an outlet of the compressor (4) is connected to the cathode of the fuel cell (15).

3. The methanol-jet fuel dual-fuel chemical regenerative hybrid aircraft engine according to claim 2, characterized in that: The gas discharged from the turbine system exchanges heat with the reforming reactor (12) and is then discharged through the tail nozzle (9).

4. The methanol-jet fuel dual-fuel chemical regenerative hybrid aircraft engine according to claim 2, characterized in that: The cathode outlet of the fuel cell (15) is communicated with an inlet of the reforming reactor (12).

5. The methanol-jet fuel dual-fuel chemical regenerative hybrid aircraft engine according to claim 2, characterized in that: A pressure reducing valve (14) is provided between the fuel distributor (13) and the anode of the fuel cell (15).

6. The methanol-jet fuel dual-fuel chemical regenerative hybrid aircraft engine according to claim 2, characterized in that: A fuel pump is provided between the methanol storage tank (10) and the reforming reactor (12).

7. The methanol-jet fuel dual-fuel chemical regenerative hybrid aircraft engine according to claim 3, characterized in that: The turbine system comprises a gas turbine (6) and a power turbine (7); the combustion chamber (5), the gas turbine (6), the hot side of the reforming reactor (12) of the power turbine (7) and the tail nozzle (9) are connected in sequence; the gas turbine (6) drives the compressor (4); and the power turbine (7) drives the rotor.

8. The methanol-jet fuel dual-fuel chemical regenerative hybrid aircraft engine according to claim 7, characterized in that: The power turbine (7) drives the rotor through a gearbox (8).

9. The methanol-jet fuel dual-fuel chemical regenerative hybrid aircraft engine according to claim 6, characterized in that: A fuel pump is provided between the aviation fuel storage tank (1) and the combustion chamber (5).

10. The methanol-jet fuel dual-fuel chemical regenerative hybrid aircraft engine according to claim 9, characterized in that: The fuel pump is connected to the fuel cell (15).

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