Range-extending gas turbine power device for low-altitude flight

Abstract

The invention discloses a range-extended gas turbine power device for low-altitude flight, which belongs to the field of power devices and comprises a liquid oxygen tank, a liquid oxygen nozzle, a liquid ammonia tank, a liquid ammonia nozzle, a preheating vaporization device, an electric control cracking device, a range-extended gas turbine only generating electricity, a driving motor, a super capacitor and a conversion device. The gas turbine focuses on efficient combustion, power generation and energy supply, the driving motor is responsible for adapting to the operation working condition, the conversion device is responsible for converting and stably transferring electric energy, and the super capacitor flexibly stores and discharges the electric energy; ammonia fuel is used as energy of the device, carbon emission is effectively reduced, light weight and miniaturization can be kept, and the cruising ability of the device is improved.

Description

Technical Field

[0001] The invention belongs to the field of power devices, and relates to a range-extended combustion engine power device for low-altitude flight. Background Art

[0002] Compared with piston engines, gas turbine engines eliminate complex mechanisms such as valve distribution and timing, greatly simplifying their thermodynamic cycle process, breaking through their dependence on traditional fuels. They can use low-carbon or even carbon-free fuels such as alcohol, renewable fuel, hydrogen, and ammonia, better responding to the development direction of the "dual carbon strategy."

[0003] In the wave of electrification of new energy power devices, the electrification of low-altitude flight power devices has gradually attracted attention with the rise of the concept of "low-altitude flight". However, current electric aircraft generally face the problem of insufficient cruising distance due to the low energy density of batteries. Summary of the invention

[0004] In combination with the above background technology, the present invention proposes a range-extended combustion engine power device for low-altitude flight. The device uses ammonia fuel as energy, which not only effectively reduces carbon emissions, but also improves the endurance of the device.

[0005] To achieve the above objectives, the present invention is implemented through the following technical solutions.

[0006] A range-extending combustion engine power unit for low-altitude flight, comprising a liquid oxygen tank, a liquid oxygen nozzle, a liquid ammonia tank, a liquid ammonia nozzle, a preheating vaporization device, an electronically controlled cracking device, a range-extending combustion engine for power generation only, a drive motor, a supercapacitor and a conversion device;

[0007] The liquid oxygen tank is connected to the preheating vaporization device through a liquid oxygen nozzle, the liquid ammonia tank is connected to the preheating vaporization device through a liquid ammonia nozzle, the preheating vaporization device is connected to the range-extending gas engine that only generates electricity through an electronically controlled cracking device, the conversion device includes a first conversion device, a second conversion device and a third conversion device, the range-extending gas engine that only generates electricity is connected to the drive motor through the first conversion device, the range-extending gas engine that only generates electricity is connected to the supercapacitor through the second conversion device, and the drive motor is connected to the supercapacitor through the third conversion device.

[0008] In the above technical solution, the shells of the liquid ammonia tank and the liquid oxygen tank are subjected to strengthening, corrosion protection and thermal insulation treatment.

[0009] In the above technical solution, the preheating vaporization device mixes liquid ammonia and liquid oxygen sprays and heats them to 600K, so that the atomized droplets are converted into gas, and the preheated ammonia and oxygen are sent to the electric-controlled cracking device through the internal gas-liquid separation equipment.

[0010] In the above technical solution, the electrically controlled cracking device is used to decompose ammonia into hydrogen and nitrogen.

[0011] In the above technical solution, the controllable ratio of ammonia decomposition of the electric-controlled cracking device is 0-30%.

[0012] In the above technical solution, the drive motor includes a kinetic energy recovery device for converting the kinetic energy of deceleration or braking into electrical energy.

[0013] In the above technical solution, the conversion device is used to transfer the electric energy generated by the range-extended combustion engine, supercapacitor, and drive motor that only generates electricity to corresponding components for use or storage.

[0014] In the above technical scheme, the ammonia fuel introduced into the range extender engine for power generation only maintains a two-stage combustion of "rich burn + lean burn", with an initial equivalence ratio of 1.2 for rich burn and an overall equivalence ratio of 0.5 for lean burn. A selective non-catalytic reduction device is installed in front of the exhaust port to absorb and purify pollutants such as nitrogen oxides and unburned ammonia in the exhaust gas.

[0015] Beneficial effects:

[0016] The present invention proposes a range-extending gas engine power device for low-altitude flight, including a liquid oxygen tank, a liquid oxygen nozzle, a liquid ammonia tank, a liquid ammonia nozzle, a preheating vaporization device, an electronically controlled cracking device, a range-extending gas engine that only generates electricity, a drive motor, a supercapacitor, and a conversion device; when the present invention is working, liquid ammonia and liquid oxygen are sprayed into the preheating vaporization device and the electronically controlled cracking device through a special nozzle for heating and cracking, and then introduced into the range-extending gas engine that only generates electricity for "rich combustion + lean combustion" two-stage combustion, driving the turbine to rotate so that the generator generates the most electrical energy, which is stably supplied to the supercapacitor and the drive motor through the conversion device, driving the external lift and the propulsion device to move. The present invention uses ammonia fuel as energy, which not only effectively reduces carbon emissions, but also keeps it small and lightweight and improves the endurance of the device. BRIEF DESCRIPTION OF THE DRAWINGS

[0017] Figure 1 It is a schematic diagram of the connection of components of a range-extended combustion engine power device for low-altitude flight according to the present invention;

[0018] Figure 2 It is a functional schematic diagram of the conversion device in the present invention.

[0019] In the figure: 1 is a liquid oxygen tank, 2 is a liquid oxygen nozzle, 3 is a liquid ammonia tank, 4 is a liquid ammonia nozzle, 5 is a preheating vaporization device, 6 is an electric-controlled cracking device, 7 is a range-extended gas turbine for power generation only, 8 is a drive motor, 9 is a supercapacitor, 10 is a first conversion device, 11 is a second conversion device, and 12 is a third conversion device. DETAILED DESCRIPTION

[0020] In order to make the purpose, technical solution and advantages of the embodiments of the present invention clearer, the technical solution in the embodiments of the present invention will be clearly and completely described below in conjunction with the drawings in the embodiments of the present invention. Obviously, the described embodiments are part of the embodiments of the present invention, not all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without creative work are within the scope of protection of the present invention.

[0021] Example

[0022] A range-extending combustion engine power device for low-altitude flight, comprising a liquid oxygen tank 1, a liquid oxygen nozzle 2, a liquid ammonia tank 3, a liquid ammonia nozzle 4, a preheating vaporization device 5, an electric-controlled cracking device 6, a range-extending combustion engine 7 for power generation only, a drive motor 8, a supercapacitor 9, a first conversion device 10, a second conversion device 11, and a third conversion device 12;

[0023] The shells of the liquid ammonia tank 3 and the liquid oxygen tank 1 have been treated with strengthening, anti-corrosion, thermal insulation, etc., and can store the liquid ammonia and liquid oxygen inside them stably for a long time without leakage, corrosion, vaporization, etc.;

[0024] The liquid ammonia nozzle 4 and the liquid oxygen nozzle 2 are adapted to the physical and chemical properties of liquid ammonia and liquid oxygen, and achieve the best atomization effect and produce the smallest atomized droplets without clogging;

[0025] The preheating vaporization device 5 fully mixes the liquid ammonia and liquid oxygen spray and heats them to 600K, so that the atomized droplets are converted into gas, and the preheated ammonia and oxygen are sent to the electric-controlled cracking device 6 through the internal gas-liquid separation device;

[0026] The electronically controlled cracking device 6 can decompose ammonia into hydrogen and nitrogen, increase the flame speed of combustion and reduce the delay time of ignition; the ammonia decomposition ratio of the device can be adjusted to 0-30%, and hydrogen, ammonia and oxygen can be evenly mixed to facilitate subsequent premixed combustion;

[0027] The range extender gas engine 7 for power generation only operates only at certain operating points with high thermal efficiency and power generation efficiency. The high-temperature and high-pressure gas generated by internal combustion drives the turbine to rotate and output the most shaft work, generating the most electricity.

[0028] The drive motor 8 includes a kinetic energy recovery device, which can convert the kinetic energy of deceleration or braking into electrical energy;

[0029] The supercapacitor 9 has the characteristics of rapid charging and discharging, large instantaneous charging and discharging power, and can also be used as an emergency power supply. The components have a wide operating temperature range, a long cycle life, and are easy to maintain and operate.

[0030] The conversion device can safely and stably transfer the electric energy generated by the range extender, supercapacitor, and drive motor that only generate electricity to other components for use or storage;

[0031] like Figure 1 As shown, the use of liquid ammonia tank 3 and liquid oxygen tank 1 to store fuel liquid ammonia and combustion-supporting agent liquid oxygen can greatly reduce the volume occupied by the device. At the same time, the entire device does not need to obtain oxygen from the outside, and is less affected by changes in the external atmospheric environment (air rarefaction, temperature, humidity, etc.), and the ability to adapt to the environment is greatly enhanced.

[0032] like Figure 1 , 2 As shown, the drive motor 8 can be divided into four operating conditions according to the required workload, namely, idling, general operating condition, sudden acceleration and braking; in general operating condition, the electricity generated by the range-extending engine 7 that only generates electricity is supplied to the drive motor 8 via path I of the first conversion device 10; at idling, the electricity generated by the range-extending engine 7 that only generates electricity is greater than the power required by the drive motor 8, and the excess electricity is supplied to the supercapacitor 9 via path II of the second conversion device 11; during sudden acceleration, the electricity generated by the range-extending engine 7 that only generates electricity is less than the power required by the drive motor 8, and the supercapacitor 9 supplies power to the drive motor together with path III of the third conversion device 12 and path I; during braking, the kinetic energy recovery device of the drive motor 8 converts kinetic energy into electrical energy and supplies it to the supercapacitor 9 via path IV of the third conversion device 12.

[0033] The working principle of a range-extending combustion engine power unit for low-altitude flight is as follows:

[0034] When the present invention is working, liquid ammonia and liquid oxygen are sprayed through a special nozzle into the preheating vaporization device and the electronically controlled cracking device for heating and cracking, and then introduced into the range-extending engine for power generation only for "rich combustion + lean combustion" two-stage combustion, driving the turbine to rotate so that the generator generates the most electrical energy, which is stably supplied to the supercapacitor and the drive motor through the conversion device, driving the external lift and pushing the device to move. The present invention uses ammonia fuel as energy, which not only effectively reduces carbon emissions, but also keeps the device small and lightweight and improves endurance.

[0035] The foregoing is merely a specific embodiment of the present invention, which enables those skilled in the art to understand or implement the present invention. Various modifications to these embodiments will be apparent to those skilled in the art, and the general principles defined herein may be implemented in other embodiments without departing from the spirit or scope of the present invention. Therefore, the present invention will not be limited to the embodiments shown herein, but rather to the widest scope consistent with the principles and novel features claimed herein.

Claims

1. A range-extended combustion engine power device for low-altitude flight, characterized in that: It includes a liquid oxygen tank, a liquid oxygen nozzle, a liquid ammonia tank, a liquid ammonia nozzle, a preheating vaporization device, an electronically controlled cracking device, a range-extending combustion engine for power generation only, a drive motor, a supercapacitor and a conversion device; The liquid oxygen tank is connected to the preheating vaporization device through a liquid oxygen nozzle, the liquid ammonia tank is connected to the preheating vaporization device through a liquid ammonia nozzle, the preheating vaporization device is connected to the range-extending gas engine that only generates electricity through an electronically controlled cracking device, the conversion device includes a first conversion device, a second conversion device and a third conversion device, the range-extending gas engine that only generates electricity is connected to the drive motor through the first conversion device, the range-extending gas engine that only generates electricity is connected to the supercapacitor through the second conversion device, and the drive motor is connected to the supercapacitor through the third conversion device.

2. The range-extending combustion engine power device for low-altitude flight according to claim 1 is characterized in that: The shells of the liquid ammonia tank and the liquid oxygen tank are treated with strengthening, corrosion prevention and thermal insulation.

3. The range-extending combustion engine power device for low-altitude flight according to claim 1 is characterized in that: The preheating vaporization device sprays and mixes liquid ammonia and liquid oxygen and heats them to 600K, so that the atomized droplets are converted into gas, and the preheated ammonia and oxygen are sent to the electric-controlled cracking device through the internal gas-liquid separation equipment.

4. The range-extending combustion engine power device for low-altitude flight according to claim 1 is characterized in that: The electrically controlled cracking device is used to decompose ammonia into hydrogen and nitrogen.

5. The range-extending combustion engine power device for low-altitude flight according to claim 1 is characterized in that: The controllable ratio of ammonia decomposition of the electric-controlled cracking device is 0-30%.

6. The range-extending combustion engine power device for low-altitude flight according to claim 1 is characterized in that: The drive motor includes a kinetic energy recovery device for converting the kinetic energy of deceleration or braking into electrical energy.

7. The range-extending combustion engine power device for low-altitude flight according to claim 1 is characterized in that: The conversion device is used to transfer the electric energy generated by the range-extending combustion engine, supercapacitor, and drive motor that only generates electricity to corresponding components for use or storage.

8. The range-extending combustion engine power device for low-altitude flight according to claim 1 is characterized in that: The ammonia fuel introduced into the range extender for power generation only maintains a two-stage combustion of "rich burn + lean burn", with an initial rich burn equivalence ratio of 1.2 and an overall lean burn equivalence ratio of 0.

5. A selective non-catalytic reduction device is installed in front of the exhaust port to absorb and purify nitrogen oxides and unburned ammonia in the exhaust gas.

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