Sand prevention device for air inlet channel of helicopter engine

Abstract

The utility model relates to the technical field of helicopter engine air inlets, in particular to a helicopter engine air inlet sand prevention device which comprises a sand prevention device body structure and a bypass valve structure, when an airplane takes off, a bypass valve baffle is closed to prevent sand dust from entering an engine, and when the airplane is located at the high altitude, the bypass valve baffle is opened to prevent sand dust from entering the engine. The main body structure of the sand prevention device comprises a frame body and a filter screen used for filtering air, and the bypass valve structure increases the air inflow of an engine when the helicopter flies to the high altitude.

Description

TECHNICAL FIELD

[0001] The application relates to the technical field of helicopter engine air inlet channels, in particular to a sand prevention device for a helicopter engine air inlet channel. BACKGROUND

[0002] The helicopter engine plays a vital role, which not only provides power to enable the helicopter to realize vertical take-off, ascent, descent, hovering and flight in various directions, but also maintains flight stability, guarantees load capacity and adapts to different flight conditions including high temperature, low temperature and high altitude.

[0003] When the helicopter flies at low altitude or takes off, the rotation of the propeller will bring up sand dust, and the sand dust entering the engine air inlet channel will have an impact on the engine, so the front of the existing engine air inlet channel is provided with a sand prevention device.

[0004] The prior art in the above has the following defects: when the helicopter flies to high altitude, the closed structure in front of the sand prevention device reduces the entry of air into the air inlet channel, resulting in a decrease in the power of the engine. CONTENT OF THE UTILITY MODEL

[0005] The application provides a sand prevention device for a helicopter engine air inlet channel in order to increase the engine air intake when the helicopter flies to high altitude.

[0006] The above technical purpose of the application is achieved by the following technical scheme:

[0007] A sand prevention device for a helicopter engine air inlet channel comprises a sand prevention device main body structure (1) and a bypass valve structure (2), the bypass valve structure (2) comprises a valve baffle (21), the valve baffle (21) is arranged on the front side of the bypass valve structure (2), when the aircraft takes off, the valve baffle (21) is closed to prevent sand dust from entering the engine, when the aircraft is at high altitude, the valve baffle (21) is opened, the sand prevention device main body structure (1) comprises a frame body and a filter screen (11) for filtering air.

[0008] By adopting the above scheme, when the aircraft is flying at low altitude or taking off, the valve baffle is closed, so that air enters the helicopter engine through the sand prevention device main body structure, and the filter screen blocks the sand dust outside, when the helicopter flies to high altitude, the valve baffle is opened, part of the air enters the engine at the valve baffle, thereby increasing the air intake of the engine, and the filter screen further filters the sand dust, thereby increasing the engine power when the helicopter flies to high altitude.

[0009] Optionally, the surface of the sand prevention device main body structure is corrugated, for increasing the contact area of air and the filter screen.

[0010] By using the above scheme, the contact area of the filter screen and the air is increased, thereby increasing the filtering efficiency of the sand prevention device.

[0011] In summary, the present application has the following technical effects:

[0012] By setting the flap baffle, the air intake of the helicopter engine is increased when flying at high altitudes. BRIEF DESCRIPTION OF DRAWINGS

[0013] Figure 1 is a schematic diagram of the overall structure of the present application;

[0014] Figure 2 is Figure 1 is an enlarged view of A in

[0015] Figure 3 is a partial structure sectional view intended to emphasize the flap control structure of the present application.

[0016] In the figure, 1 is the main structure of the sand prevention device; 11 is the filter screen; 2 is the bypass flap structure; 21 is the flap baffle; 3 is the flap control structure; 31 is the first supporting rod; 32 is the second supporting rod; 4 is the linear servo; 5 is the connecting rod. DETAILED DESCRIPTION

[0017] The present application will be further described in detail below in conjunction with the drawings.

[0018] Referring to Figure 1 and Figure 2 , a sand prevention device for a helicopter engine air inlet passage includes a sand prevention device main structure 1 and a bypass flap structure 2, the bypass flap structure 2 includes a flap baffle 21, the flap baffle 21 is arranged on the front side of the bypass flap structure 1, when the aircraft takes off, the flap baffle 21 is closed, when the aircraft is at high altitude, the flap baffle 21 is opened, the sand prevention device main structure 1 includes a frame body and a filter screen 11 for filtering air. When the aircraft is flying at low altitude or taking off, the flap baffle 21 is closed, so that the air enters the helicopter engine at the sand prevention device main structure 1, the filter screen 11 blocks the sand and dust outside, when the helicopter flies to high altitude, the flap baffle 21 is opened, part of the air enters the engine at the flap baffle 21, thereby increasing the air intake of the engine, and the filter screen 11 further filters the sand and dust, thereby increasing the engine power when the helicopter flies to high altitude.

[0019] The surface of the filter screen 11 is corrugated, increasing the contact area of the filter screen 11 and the air, thereby increasing the filtering efficiency of the filter screen 11, and because the folds of the filter screen 11 are small, they are not shown in Figure 1 .

[0020] Referring to Figure 3The bypass valve structure 2 is internally provided with a valve control structure 3 for controlling the opening and closing of the valve baffle 21, the valve control structure 3 comprises a first supporting rod 31 and a second supporting rod 32, the first supporting rod 31 is hinged to the outer cover of the bypass valve structure 2, one end of the second supporting rod 32 is hinged to the first supporting rod 31, the other end of the second supporting rod 32 is hinged to the valve, the valve control structure 3 is provided with two groups, and a connecting rod 5 is arranged between the two first supporting rods 31, the two ends of the connecting rod 5 are connected with the first supporting rods 31 respectively, a linear actuator 4 is hinged to the inner side surface of the sand prevention device main structure 1, and the other end of the linear actuator 4 is hinged to the connecting rod 5. The linear actuator 4 drives the connecting rod 5 to move, thereby simultaneously driving the two groups of first supporting rods to move, thereby driving the second supporting rod to move and driving the valve baffle 21 to move, thereby realizing the opening and closing of the valve baffle 21.

[0021] The specific implementation principle of the present application is that when the airplane takes off, the valve baffle 21 is closed, and when the airplane is in high altitude, the valve baffle 21 is opened, the sand prevention device main structure 1 comprises a frame body and a filter screen 11 for filtering air. When the airplane is flying at low altitude or taking off, the valve baffle 21 is closed, so that the air enters the helicopter engine at the sand prevention device main structure 1, and the filter screen 11 blocks the sand and dust outside, when the helicopter flies to high altitude, the valve baffle 21 is opened, part of the air enters the engine at the valve baffle 21, thereby increasing the air intake of the engine, and the filter screen 11 further filters the sand and dust, thereby increasing the engine power when the helicopter flies to high altitude.

[0022] The specific embodiment is only an explanation of the present application, and is not a limitation of the present application, and those skilled in the art can make non-creative modifications to the embodiment according to the needs after reading the present specification, but as long as the scope of the claims of the present application is within the scope of the patent law.

Claims

1. A sand prevention device for a helicopter engine inlet duct, characterised in that: The sand prevention device main body structure (1) and the bypass valve structure (2) are included, the bypass valve structure (2) includes a valve baffle (21), the valve baffle (21) is arranged on the front side of the bypass valve structure (2), when the airplane takes off, the valve baffle (21) is closed, and sand and dust is prevented from entering the engine, when the airplane is in high altitude, the valve baffle (21) is opened, the sand prevention device main body structure (1) includes a frame body and a filter screen (11) for filtering air; The surface of the filter screen (11) is corrugated; The bypass valve structure (2) is internally provided with a valve control structure (3) for controlling the opening and closing of the valve baffle (21), the valve control structure (3) includes a first supporting rod (31) and a second supporting rod (32), the first supporting rod (31) is hinged to the outer cover of the bypass valve structure (2), one end of the second supporting rod (32) is hinged to the first supporting rod (31), the other end of the second supporting rod (32) away from the first supporting rod (31) is hinged to the valve, the valve control structure (3) is provided with two groups, and a connecting rod (5) is arranged between the two first supporting rods (31), the two ends of the connecting rod (5) are connected with the first supporting rods (31) respectively, the inner side surface of the sand prevention device main body structure (1) is hinged with a linear actuator (4), the other end of the linear actuator (4) is hinged with the connecting rod (5); the linear actuator (4) drives the connecting rod (5) to move, so as to simultaneously drive the two groups of first supporting rods to move, so as to drive the second supporting rod to move and drive the valve baffle (21) to move, so as to realize the opening and closing of the valve baffle (21).

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