A flow-adjustable hot-air anti-icing system for a helicopter air intake

Abstract

The present application belongs to the field of helicopter inlet anti-icing design, and relates to a flow-adjustable helicopter inlet hot air anti-icing system, which comprises an inlet skin, a heat preservation skin, multiple partition frames, a flow control valve, an atmospheric temperature sensor, a control device and a gas supply pipeline. The flow of hot air into the anti-icing cavity can be automatically adjusted according to the ambient temperature, and heat waste can be avoided under the condition of meeting the anti-icing demand. The hot air in the inlet anti-icing cavity flows from back to front, which can effectively reduce the influence on the engine inlet air distortion. The multiple partition frames are used to distribute the hot air in the anti-icing cavity, which can reduce the height of the anti-icing cavity to 5-15 mm and improve the heat exchange efficiency. The heat preservation layer wrapped on the inlet heat preservation skin can effectively reduce heat loss.

Description

Technical Field

[0001] This invention belongs to the field of helicopter air intake anti-icing design, and relates to an adjustable flow helicopter air intake hot air anti-icing system. Background Technology

[0002] When a helicopter flies in an environment of -30℃ to 0℃, water vapor or ice crystals in the air will condense into ice on the surface of the aircraft. If large ice blocks are sucked into the engine, they will damage the engine blades, causing a decrease in power or even an in-flight shutdown. Therefore, measures need to be taken on the air intake at the front of the engine to prevent ice from forming on the surface.

[0003] Existing technologies mainly use high-temperature and high-pressure hot air, but the hot air flow rate cannot be adjusted according to demand, and the air distribution mainly uses stainless steel flute tubes, which are heavy and have low heating efficiency. Summary of the Invention

[0004] The purpose of this invention is to provide an adjustable flow rate helicopter air intake hot air anti-icing system that uses high-temperature, high-pressure hot air as a heat source to keep the surface temperature of the air intake at around 20°C, thus preventing surface icing. This invention features high heat exchange efficiency and simple and reliable control, and is used to ensure the safe flight of helicopters in icing environments.

[0005] Technical solution

[0006] An adjustable flow helicopter air intake hot air anti-icing system includes a control device 1, an atmospheric temperature sensor 2, an air supply line 3, a flow control valve 4, an insulation skin 6, a multi-layer frame 9, and an air intake skin 10.

[0007] The thermal insulation skin 6 is disposed outside the air intake skin 10, and the multiple partitions 9 are disposed between the thermal insulation skin 6 and the air intake skin 10; the thermal insulation skin 6, the multiple partitions 9 and the air intake skin 10 form an air intake anti-icing cavity, in which hot air flows.

[0008] The air supply pipeline 3 is connected to the air intake anti-icing chamber and the high temperature and high pressure air source, and the flow control valve 4 is installed on the air supply pipeline 3;

[0009] The control device 1 is connected to the atmospheric temperature sensor 2, and controls the opening of the flow control valve 4 according to the temperature value of the atmospheric temperature sensor 2, thereby controlling the flow rate of hot air entering the anti-icing cavity.

[0010] Preferably, the thermal insulation skin 6 includes an insulation layer to keep the ice-proof cavity warm and reduce heat loss.

[0011] Preferably, the hot air in the air intake anti-icing cavity enters from the rear end and flows out through the gap 8 at the front end of the air intake skin 10, flowing in the opposite direction to the cold air 7 in the air intake.

[0012] Preferably, the slit 8 at the front end of the intake duct skin 10 is located inside the intake duct lip, so that the hot air flowing out through the slit 8 at the front end of the intake duct skin 10 is drawn back into the intake duct, thereby realizing the reuse of waste heat.

[0013] Preferably, the slit 8 at the front end of the intake duct skin 10 is located on the outside of the intake duct lip, so that the hot air flowing out through the slit 8 at the front end of the intake duct skin 10 is directly discharged into the atmosphere, reducing the distortion of the engine intake airflow.

[0014] Preferably, the multi-partition frame 9 is provided with multiple through holes to distribute the flow of hot air in the air intake anti-icing cavity.

[0015] Preferably, the height of the air intake anti-icing cavity is set to 5-15mm, which provides high heating efficiency for the air intake skin 10.

[0016] Preferably, the multiple partitions 9 are connected and fixed to the intake duct skin 10 and the insulation skin 6, which can improve the rigidity of the intake duct and reduce the thickness of the intake duct skin, thereby further improving the heat exchange efficiency and reducing the system weight.

[0017] Preferably, the correspondence between hot air flow rate and ambient temperature is determined through simulation and experimentation, and the opening degree of flow control valve 4 is controlled according to the temperature value of atmospheric temperature sensor 2. Attached Figure Description

[0018] Figure 1 A schematic diagram of an adjustable flow rate helicopter air intake hot air anti-icing system provided by the present invention;

[0019] Explanation of reference numerals in the attached figures:

[0020] 1—Control device; 2—Ambient temperature sensor; 3—Gas supply pipeline;

[0021] 4—Flow control valve; 5—Hot air; 6—Insulation skin;

[0022] 7—Cold air; 8—Gap; 9—Multiple partitions;

[0023] 10—Intake duct skin. Detailed Implementation

[0024] The following is a detailed description of an adjustable flow helicopter air intake hot air anti-icing system provided by the present invention, with reference to the accompanying drawings.

[0025] like Figure 1As shown, an embodiment of the adjustable flow helicopter air intake hot air anti-icing system of the present invention includes a control device 1, an atmospheric temperature sensor 2, an air supply pipeline 3, a flow control valve 4, an insulation skin 6, a multi-layer frame 9, and an air intake skin 10.

[0026] The thermal insulation skin 6 is disposed outside the air intake duct skin 10, and the multiple partitions 9 are disposed between the thermal insulation skin 6 and the air intake duct skin 10; the thermal insulation skin 6, the multiple partitions 9 and the air intake duct skin 10 form an air intake duct anti-icing cavity, in which hot air flows; the air supply pipeline 3 connects the air intake duct anti-icing cavity and a high-temperature and high-pressure air source, and the flow control valve 4 is installed on the air supply pipeline 3; the control device 1 is connected to the atmospheric temperature sensor 2, and controls the opening of the flow control valve 4 according to the temperature value of the atmospheric temperature sensor 2, thereby controlling the flow rate of hot air entering the anti-icing cavity.

[0027] Preferably, the thermal insulation skin 6 includes a thermal insulation layer, and the outside of the thermal insulation skin 6 is wrapped with a thermal insulation layer composed of asbestos, rubber, etc., to insulate the ice-proof cavity and reduce heat loss.

[0028] Preferably, the hot air in the intake duct anti-icing cavity enters from the rear end and flows out through the gap 8 at the front end of the intake duct skin 10, flowing in the opposite direction to the cold air 7 in the intake duct. This allows for the reuse of waste heat or direct discharge into the atmosphere, reducing the distortion of the engine intake airflow.

[0029] Preferably, the slit 8 at the front end of the intake duct skin 10 is located inside the intake duct lip, so that the hot air flowing out through the slit 8 at the front end of the intake duct skin 10 is drawn back into the intake duct, thereby realizing the reuse of waste heat.

[0030] Preferably, the gap (8) at the front end of the intake duct skin 10 is located on the outside of the intake duct lip, so that the hot air flowing out through the gap 8 at the front end of the intake duct skin 10 is directly discharged into the atmosphere, thereby reducing the distortion of the engine intake airflow.

[0031] Preferably, the multi-partition frame 9 is provided with multiple through holes to distribute the flow of hot air in the air intake anti-icing cavity.

[0032] Preferably, the height of the air intake anti-icing cavity is set to 5-15mm, which provides high heating efficiency for the air intake skin 10.

[0033] Preferably, the multiple partitions 9 are connected and fixed to the intake duct skin 10 and the insulation skin 6, which can improve the rigidity of the intake duct and reduce the thickness of the intake duct skin, thereby further improving the heat exchange efficiency and reducing the system weight.

[0034] Preferably, the correspondence between hot air flow rate and ambient temperature is determined through simulation and experimentation, and the opening degree of flow control valve 4 is controlled according to the temperature value of atmospheric temperature sensor 2.

[0035] Another embodiment of the present invention is as follows: the air supply line 3 is connected to a high-temperature and high-pressure air source (generally an engine), and the hot air 5 enters the anti-icing cavity through the flow control valve 4. The anti-icing cavity is composed of an intake duct skin 10, an insulation skin 6, and multiple partitions 9. The insulation skin 6 is wrapped with an insulation layer composed of asbestos, rubber, etc., which can effectively reduce the heat loss inside the anti-icing cavity.

[0036] The air supply line 3 is connected to the rear end of the anti-icing cavity. Hot air flows from the rear to the front of the anti-icing cavity, heating the air intake duct skin during the flow. Then it flows out from the gap 8 at the lip position. After flowing out, it can heat the outer surface of the lip again. The flow direction of the hot air in the anti-icing cavity is opposite to that of the cold air 7 in the air intake duct.

[0037] Based on the anti-icing requirements of the intake duct surface, the multi-layered baffle 9 distributes the hot air flow within the anti-icing chamber. By eliminating traditional adjustment mechanisms such as flute-shaped tubes, guide strips, variable blades, and exhaust pipes, the height of the anti-icing chamber can be reduced to 5–15 mm, improving the heat exchange efficiency of hot air on the intake duct surface. The multi-layered baffle 9 is connected and fixed to the intake duct skin 10 and the insulation skin 6, which increases the rigidity of the intake duct and reduces the thickness of the intake duct skin 10, thereby further improving heat exchange efficiency and reducing system weight.

[0038] Atmospheric temperature sensor 2 is arranged on the outside of the body to detect the ambient temperature. Based on simulation calculations, experiments and other methods, the correspondence between ambient temperature and hot air flow rate is determined. The opening of flow control valve 4 is controlled by control device 1 to ensure that the hot air entering the anti-icing cavity can meet the heating requirements of the air intake surface without heating it too high, thus avoiding heat waste.

Claims

1. A variable flow helicopter inlet hot air anti-ice system, comprising: The control device (1), the atmospheric temperature sensor (2), the air supply pipeline (3), the flow control valve (4), the thermal insulation skin (6), the multiple partition frame (9) and the air inlet channel skin (10) are included. The thermal insulation skin (6) is arranged outside the air inlet channel skin (10), and the multiple partition frame (9) is arranged between the thermal insulation skin (6) and the air inlet channel skin (10); the thermal insulation skin (6), the multiple partition frame (9) and the air inlet channel skin (10) form an air inlet channel anti-icing cavity, and hot air flows in the cavity; a plurality of through holes are arranged on the multiple partition frame (9) to distribute the flow direction of the hot air in the air inlet channel anti-icing cavity. The air supply pipeline (3) is connected to the air inlet channel anti-icing cavity and a high-temperature and high-pressure air source, and the flow control valve (4) is installed on the air supply pipeline (3). The atmospheric temperature sensor is arranged outside the machine body to detect the ambient temperature, and the control device (1) is connected to the atmospheric temperature sensor (2) to control the opening of the flow control valve (4) according to the temperature value of the atmospheric temperature sensor (2), so as to control the flow of the hot air into the anti-icing cavity. The hot air in the air inlet channel anti-icing cavity enters from the rear end and flows out through the gap (8) at the front end of the air inlet channel skin (10), and the flow direction of the hot air is opposite to that of the cold air (7) in the air inlet channel.

2. The system of claim 1, wherein, The thermal insulation skin (6) contains a thermal insulation layer.

3. The system of claim 1, wherein, The gap (8) at the front end of the air inlet channel skin (10) is arranged inside the air inlet channel lip, and the hot air flowing out through the gap (8) at the front end of the air inlet channel skin (10) is sucked into the air inlet channel again.

4. The system of claim 1, wherein, The gap (8) at the front end of the air inlet channel skin (10) is arranged outside the air inlet channel lip, and the hot air flowing out through the gap (8) at the front end of the air inlet channel skin (10) is directly discharged into the atmosphere.

5. The system of claim 1, wherein, The height of the air inlet channel anti-icing cavity is 5-15 mm.

6. The system of claim 1, wherein, The multiple partition frame (9) is connected and fixed with the air inlet channel skin (10) and the thermal insulation skin (6).

7. The system of claim 1, wherein, The corresponding relationship between the hot air flow and the ambient temperature is determined through simulation and test, and the opening of the flow control valve (4) is controlled according to the temperature value of the atmospheric temperature sensor (2).

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