Propeller ice preventing and removing system using heating gas film

Abstract

The invention discloses a propeller anti-icing and de-icing system utilizing a heating gas film, which comprises a rectification cap hood, a blade, a blade heat exchanger, a gas supply system and a rectification cap hood heat exchanger, the blade is arranged in the rectification cap hood, the blade heat exchanger is arranged behind the blade, the rectification cap hood heat exchanger is arranged behind the rectification cap hood, and the gas supply system is arranged in the rectification cap hood. The air supply system is installed behind the blade heat exchanger and the rectification cap heat exchanger, ice prevention and removal of the propeller are achieved through a heating air film, and the air supply system has the advantages of being low in energy consumption, fast in response and good in ice prevention uniformity.

Description

Technical Field

[0001] This invention relates to a propeller de-icing system utilizing a heated gas film. Background Technology

[0002] When an aircraft passes through clouds containing supercooled water droplets, icing can occur on its windward surfaces, such as the propeller, leading to decreased flight performance and posing a serious safety hazard.

[0003] Currently, mainstream anti-icing methods include hot gas anti-icing, electric heating anti-icing, and airbag de-icing. While propeller electric heating anti-icing technology is relatively mature, it suffers from high power consumption and battery capacity degradation in low-temperature environments, which is particularly detrimental to electric vertical takeoff and landing (EVTOL) aircraft. Airbag de-icing technology has drawbacks such as limited de-icing range, altered blade aerodynamic shape, and increased weight. Related patented technologies, such as impact-film structure anti-icing systems, suffer from poor film adhesion and uneven heat transfer. De-icing solutions based on propeller parameter adjustment or lubricating oil cooling have drawbacks such as flight safety risks, complex structures, and high energy consumption. Summary of the Invention

[0004] The purpose of this invention is to provide a propeller anti-icing and de-icing system that utilizes a heated gas film to solve the above-mentioned technical problems.

[0005] To achieve the above objectives, the present invention adopts the following technical solution:

[0006] A propeller anti-icing and de-icing system utilizing a heated gas film includes a rectifier cap, blades, a blade heat exchanger, an air supply system, and a rectifier cap heat exchanger. The blades are installed inside the rectifier cap, the blade heat exchanger is installed behind the blades, the rectifier cap heat exchanger is installed behind the rectifier cap, and the air supply system is installed behind the blade heat exchanger and the rectifier cap heat exchanger.

[0007] Based on the above technical solution, the gas supply system includes a gas cylinder, a pressure regulating valve, a pressure stabilizing valve, and internal high-pressure dry nitrogen. The pressure stabilizing valve is installed at the front end of the gas cylinder, the pressure regulating valve is installed at the front end of the pressure stabilizing valve, and the internal high-pressure dry nitrogen is filled inside the gas cylinder.

[0008] Based on the above technical solution, the blade heat exchanger includes an air guide pipe A, an insulation layer A, a heat sink, a coolant conduit A, and a tapered bend joint A. The insulation layer A is fixedly connected inside the air guide pipe A. The heat sink is fixedly connected to the center inside the air guide pipe A. The coolant conduit A is fixedly connected to the top rear of the air guide pipe A. The tapered bend joint A is fixedly connected to the rear of the air guide pipe A.

[0009] Based on the above technical solution, the rectifier cap heat exchanger includes an air guide pipe B, an insulation layer B, heat exchange plates, a coolant conduit B, and a tapered bend joint B. The insulation layer B is fixedly connected inside the air guide pipe B, the heat exchange plates are fixedly connected at the center inside the air guide pipe B, the coolant conduit B is fixedly connected at the top rear of the air guide pipe B, and the tapered bend joint B is fixedly connected at the rear of the air guide pipe B.

[0010] Compared with the prior art, the present invention has the following advantages: The present invention achieves propeller anti-icing and de-icing by utilizing a heated gas film, which has the advantages of low energy consumption, fast response and good anti-icing uniformity; the system utilizes the motor to heat the gas, which is energy-saving and environmentally friendly, and the gas film has a large coverage area, which can effectively suppress airflow separation and improve flight safety. Attached Figure Description

[0011] Figure 1 This is a schematic diagram of the external structure of the present invention.

[0012] Figure 2 This is a schematic diagram of the gas supply system structure of the present invention.

[0013] Figure 3 This is a schematic diagram of the blade heat exchanger structure of the present invention.

[0014] Figure 4 This is a schematic diagram of the rectifier cap heat exchanger structure of the present invention.

[0015] In the diagram: 1. Rectifier cap, 2. Blade, 3. Plate heat exchanger, 4. Gas supply system, 5. Rectifier cap heat exchanger, 6. Gas cylinder, 7. Pressure regulating valve, 8. Pressure stabilizing valve, 9. Internal high-pressure dry nitrogen, 10. Gas duct A, 11. Insulation layer A, 12. Heat sink, 13. Coolant conduit A, 14. Conical bend joint A, 15. Gas duct B, 16. Insulation layer B, 17. Heat exchange plate, 18. Coolant conduit B, 19. Conical bend joint B. Detailed Implementation

[0016] The present invention will be further described in detail below with reference to the accompanying drawings and specific embodiments.

[0017] like Figure 1-4 As shown, a propeller anti-icing and de-icing system utilizing a heated air film includes a rectifier cap 1, blades 2, blade heat exchangers 3, an air supply system 4, and a rectifier cap heat exchanger 5. The blades 2 are installed inside the rectifier cap 1, the blade heat exchanger 3 is installed behind the blades 2, the rectifier cap heat exchanger 5 is installed behind the rectifier cap 1, and the air supply system 4 is installed behind the blade heat exchanger 3 and the rectifier cap heat exchanger 5.

[0018] The gas supply system 4 includes a gas cylinder 6, a pressure regulating valve 7, a pressure stabilizing valve 8, and internal high-pressure dry nitrogen 9. The pressure stabilizing valve 8 is installed at the front end of the gas cylinder 6, the pressure regulating valve 7 is installed at the front end of the pressure stabilizing valve 8, and the internal high-pressure dry nitrogen 9 is filled inside the gas cylinder 6.

[0019] The blade heat exchanger 3 includes an air guide pipe A10, an insulation layer A11, a heat sink 12, a coolant conduit A13, and a tapered bend joint A14. The insulation layer A11 is fixedly connected inside the air guide pipe A10. The heat sink 12 is fixedly connected to the center inside the air guide pipe A10. The coolant conduit A13 is fixedly connected to the top rear of the air guide pipe A10. The tapered bend joint A14 is fixedly connected to the rear of the air guide pipe A10.

[0020] The rectifier cap heat exchanger 5 includes an air guide pipe B15, an insulation layer B16, a heat exchange plate 17, a coolant conduit B18, and a tapered bend joint B19. The insulation layer B16 is fixedly connected inside the air guide pipe B15. The heat exchange plate 17 is fixedly connected to the center inside the air guide pipe B15. The coolant conduit B18 is fixedly connected to the top rear of the air guide pipe B15. The tapered bend joint B19 is fixedly connected to the rear of the air guide pipe B15.

[0021] The working principle of this invention is as follows: When this invention is in operation, the icing sensor on the aircraft first detects the icing signal and transmits it to the aircraft's control system. Then, the gas cylinder 6 of the gas supply system 4 outputs stable high-pressure nitrogen through the pressure stabilizing valve 8 and the pressure regulating valve 7. Then, the nitrogen enters the blade heat exchanger 3 and the rectifier cap heat exchanger 5 respectively, and absorbs the heat of the motor coolant in the coolant conduit A13 and coolant conduit B18 through the heat sink 12 and heat exchange fins 17. The heated gas is introduced into the air film hole at the leading edge of the blade 2 through the conical bent joint A14, and at the same time enters the gap between the inner and outer walls of the rectifier cap 1 through the conical bent joint B19. Finally, it is ejected from the air film hole and forms a heat-insulating and heating air film on the propeller surface, achieving efficient anti-icing and de-icing.

[0022] The above description represents a preferred embodiment of the present invention. For those skilled in the art, any changes, modifications, substitutions, and variations made to the implementation methods without departing from the principles and spirit of the present invention, based on the teachings of the present invention, still fall within the protection scope of the present invention.

Claims

1. A propeller anti-icing and de-icing system utilizing a heated gas film, comprising a rectifier cap (1), blades (2), a blade heat exchanger (3), an air supply system (4), and a rectifier cap heat exchanger (5), characterized in that: The rectifier cap (1) has blades (2) installed inside. The blade heat exchanger (3) is installed behind the blades (2). The rectifier cap heat exchanger (5) is installed behind the rectifier cap (1). The air supply system (4) is installed behind the blade heat exchanger (3) and the rectifier cap heat exchanger (5).

2. The propeller anti-icing and de-icing system utilizing a heated gas film according to claim 1, characterized in that: The gas supply system (4) includes a gas cylinder (6), a pressure regulating valve (7), a pressure stabilizing valve (8), and internal high-pressure dry nitrogen (9). The pressure stabilizing valve (8) is installed at the front end of the gas cylinder (6), the pressure regulating valve (7) is installed at the front end of the pressure stabilizing valve (8), and the internal high-pressure dry nitrogen (9) is filled inside the gas cylinder (6).

3. The propeller anti-icing and de-icing system utilizing a heated gas film according to claim 1, characterized in that: The blade heat exchanger (3) includes an air duct A (10), an insulation layer A (11), a heat sink (12), a coolant conduit A (13), and a tapered bend joint A (14). The insulation layer A (11) is fixedly connected inside the air duct A (10). The heat sink (12) is fixedly connected at the center inside the air duct A (10). The coolant conduit A (13) is fixedly connected at the top rear of the air duct A (10). The tapered bend joint A (14) is fixedly connected at the rear of the air duct A (10).

4. A propeller anti-icing and de-icing system utilizing a heated gas film according to claim 1, characterized in that: The rectifier cap heat exchanger (5) includes an air duct B (15), an insulation layer B (16), a heat exchange plate (17), a coolant conduit B (18), and a tapered bend joint B (19). The insulation layer B (16) is fixedly connected inside the air duct B (15). The heat exchange plate (17) is fixedly connected at the center inside the air duct B (15). The coolant conduit B (18) is fixedly connected at the top rear of the air duct B (15). The tapered bend joint B (19) is fixedly connected at the rear of the air duct B (15).

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