Brake cooling fan for aircraft brake cooling system

Abstract

A brake cooling fan for an aircraft brake cooling system comprises a hub and a plurality of blades. And the blades are uniformly distributed on the outer circumference of the hub. The upper airfoil surface and the lower airfoil surface of the blade are both airfoil molded surfaces. In combination with the use condition of the brake cooling fan, the airfoil profile well matched with the actual condition of the fan is designed, and the upper airfoil surface and the lower airfoil surface of the blade are of an asymmetric structure and have different mounting angles. The airfoil profile is high in lift force and low in resistance within the designed installation angle range, has a high lift-drag ratio under the designed working condition, can generate high air volume and high air pressure during working, and can achieve rapid cooling of main engine wheels of a current high-brake-energy aircraft. Meanwhile, the thickness is small, the occupied use space is small, the rotating speed is low, power consumption is reduced, and limited power driving work of the motor is cooled through an in-shaft brake. While high air volume and air pressure are generated and rapid cooling of the airplane wheel is achieved, the device has the advantages of being small in thickness, low in rotating speed and low in power consumption so as to meet the onboard power supply and installation requirements.

Description

Technical Field

[0001] The present invention relates to the field of aircraft brake cooling systems, and specifically to a brake cooling fan for cooling and reducing the temperature of the main brake wheel. Background Art

[0002] To solve problems such as high aircraft brake temperature and slow temperature reduction, there are currently two main methods: installing a brake cooling system on the main brake wheel and using ground cooling equipment. Compared with ground cooling equipment, the advantages of installing and using a cooling system on the main brake wheel are as follows: the cooling system can be activated immediately after the aircraft lands, and before the brake temperature reaches its peak, some heat energy has been eliminated through the cooling system, shortening the time for the aircraft to be ready for the next mission; at the same time, it is not restricted by ground equipment and ground crew, improving the self-supporting ability of the aircraft.

[0003] The brake cooling fan is an important component of the aircraft brake cooling system. It is installed at the end of the wheel axle of the wheel and is driven by a brake cooling motor installed inside the wheel axle of the wheel to generate air flow for cooling and reducing the temperature of the main brake wheel. With the development of industrial technology and aviation industry technology, the braking energy of aircraft is increasing, and the requirements for brake cooling capacity are getting higher and higher. At the same time, due to the increasing demand for functions such as tire pressure detection and wheel speed detection on aircraft, more and more products are installed at the end of the wheel axle of the wheel, leaving less and less space for the use of the brake cooling fan. The output power of the brake cooling motor installed in the narrow wheel axle of the wheel is limited. In the prior art, the brake cooling fan is thick in volume and occupies a large space, and cannot be installed simultaneously with equipment such as tire pressure detection and wheel speed detection; moreover, the air volume and air pressure generated under normal working conditions are relatively low. Forcibly increasing the rotational speed to increase the air volume and air pressure will result in a rapid increase in power consumption, causing the brake cooling motor to be overloaded and making it difficult to meet the current stage's requirements for aircraft wheel brake cooling and temperature reduction.

[0004] A brake cooling fan based on the design of an efficient airfoil is proposed. Through the design of variable cross-section and installation angle, the brake cooling fan can generate high air volume and air pressure while having a thin shape and low power consumption, meeting the current stage's requirements for aircraft wheel brake cooling and temperature reduction.

[0005] The fan used in the existing patent CN 109307025 A, "A Multi-wheel System Aircraft Main Wheel Brake Cooling System", is different from the brake cooling fan described in the present invention. The air volume and air pressure it generates are relatively small and cannot meet the requirements for brake cooling capacity in the current stage of high aircraft braking energy; the brake cooling fan of the present invention generates a larger air volume and air pressure to meet the current stage's requirements for aircraft wheel brake cooling and temperature reduction.

[0006] The cooling fan used in the existing patent CN 111907697 A, "Brake Cooling Fan Device", is only applicable to aircraft with relatively low brake energy and brake temperature, such as A320 and A350, and has a relatively long time to redispatch. The cooling capacity of this cooling fan is relatively low. Summary of the Invention

[0007] To overcome the deficiency of the cooling capacity of the brake cooling fan in the prior art, the present invention proposes a brake cooling fan for an aircraft brake cooling system.

[0008] The present invention includes a hub and a plurality of blades; the blades are evenly distributed on the outer circumference of the hub;

[0009] Along the span direction of the blade, multiple cross-sections are made of the blade to form multiple wing surfaces with different profile curves and wing surfaces with different profile curves, and each cross-section is smoothly transitioned and fitted along the span direction to form a shape;

[0010] Among the cross-sections of the airfoil, the root cross-section of the wing root is A-A, the tip cross-section of the wing tip is E-E, and the cross-sections at the lengths of 0.25H, 0.5H, and 0.75H from the root of the wing root to the tip of the wing are the B-B cross-section, the C-C cross-section, and the D-D cross-section respectively; in each of the cross-sections: the chord length L of the A-A cross-section a = 26.066 mm, and the installation angle α a = 20.4°; the chord length L of the B-B cross-section b = 23.459 mm, and the installation angle α b = 18.4°; the chord length L of the C-C cross-section c = 20.853 mm, and the installation angle α c = 16.5°; the chord length L of the D-D cross-section d = 18.246 mm, and the installation angle α d = 14.8°; the chord length L of the E-E cross-section e = 15.640 mm, and the installation angle α e = 13.3°.

[0011] The axial width of the hub is 1 mm to 2 mm larger than the root width of the blade.

[0012] The coordinates of the A-A profile of the blade are:

[0013] Table 1 Coordinates of the Fan Blade Cross-Section A-A

[0014]

[0015] The coordinates of the B-B profile of the blade are:

[0016] Table 2 Coordinates of the Fan Blade Cross-Section B-B

[0017]

[0018]

[0019] The coordinates of the C-C profile of the blade are as follows:

[0020] Table 3 Coordinates of the C-C section of the fan blade

[0021]

[0022] The coordinates of the D-D profile of the blade are as follows:

[0023] Table 4 Coordinates of the D-D section of the fan blade

[0024]

[0025] The coordinates of the E-E profile of the blade are as follows:

[0026] Table 5 Coordinates of the E-E section of the fan blade

[0027]

[0028]

[0029] The technical problem to be solved by the present invention is that the proposed brake cooling fan has the characteristics of thin thickness, low rotational speed and low power consumption while generating high air volume and air pressure to quickly cool down the main wheels, so as to meet the on-board power supply and installation requirements.

[0030] In combination with the operating conditions of the brake cooling fan, the present invention designs an airfoil that matches well with the actual operating conditions of the fan. The upper and lower airfoil surfaces of the blade adopt an asymmetric structure and have different installation angles. Within the designed installation angle range, the airfoil has high lift and low drag, and has a high lift-to-drag ratio under the designed operating conditions. When working, it can generate high air volume and high air pressure, and can quickly cool down the main wheels of the current high-brake-energy aircraft; at the same time, it has a thin thickness, occupies a small space, and has a low rotational speed to ensure low power consumption, and can be driven to work by the limited power of the in-axis brake cooling motor.

[0031] To verify the effect of the present invention, a comparative verification test was carried out between the present invention and the prior art, and the test results are shown in Table 1:

[0032] Table 6 Test results

[0033] Fan type Prior art The present invention Rotational speed 11000 r / min 6800 r / min Air volume <![CDATA[1m 3 / s]]> <![CDATA[1.8m 3 / s]]> Air pressure 400 Pa 600 Pa Description of the Drawings

[0034] Figure 1 is a schematic structural diagram of the present invention.

[0035] Figure 2 is a schematic diagram of the blade spanwise section.

[0036] Figure 3 is Figure 2 structural schematic diagrams of respective cross-sections therein; among them, Figure 3 a is the schematic diagram of the A-A cross-section, Figure 3 b is the B-B cross-section, Figure 3 c is the schematic diagram of the C-C cross-section, Figure 3 d is the schematic diagram of the D-D cross-section, Figure 3 e is the schematic diagram of the E-E cross-section.

[0037] Figure 4 is the coordinate schematic diagram of the airfoil of the fan blade.

[0038] Figure 5 is the performance curve of the present invention; among them, Figure 5 a is the airfoil lift CL curve, Figure 5 b is the drag CD curve, Figure 5 c is the lift-drag ratio CL / CD characteristic curve.

[0039] In the figure: 1. blade; 2. hub; 3. reinforcing rib; 4. motor shaft mounting hole; 5. upper airfoil surface; 6. lower airfoil surface. Specific embodiments

[0040] This embodiment is a brake cooling fan for an aircraft brake cooling system, including a plurality of blades 1, a hub 2, and a motor shaft mounting hole 4. The blade 1 is designed with an airfoil of an aircraft wing, and each cross-section has different cross-sections and installation angles; the blades are evenly distributed on the outer circumference of the hub.

[0041] The hub 2 has a motor shaft mounting hole 4 at its center, and the brake cooling fan is installed on the brake cooling motor shaft of the aircraft brake cooling system by a conventional method. A plurality of weight-reducing grooves are evenly distributed on the disk surface of the hub; the rib plates between the weight-reducing grooves form the reinforcing rib 4.

[0042] The axial width of the hub 2 is 1 mm to 2 mm larger than the root width of the blade 1; the reinforcing rib 13 can improve the strength of the brake cooling fan and prevent the brake cooling fan from deforming during high-speed rotation.

[0043] The blade 1 adopts an airfoil structure. The span H of the blade is 40 mm. A plurality of cross-sections are made along the span direction of the blade to form a plurality of cross-sections with different airfoils. Among the cross-sections with different airfoils, the root cross-section of the blade root is A-A, the tip cross-section of the blade tip is E-E, and the cross-sections at the lengths of 0.25H, 0.5H, and 0.75H from the blade root to the blade tip are the B-B cross-section, the C-C cross-section, and the D-D cross-section, respectively. In each of the cross-sections: the chord length L of the A-A cross-section a = 26.066 mm, and the installation angle α a= 20.4°; The chord length L of the B-B section b = 23.459 mm, the installation angle α b = 18.4°; The chord length L of the C-C section c = 20.853 mm, the installation angle α c = 16.5°; The chord length L of the D-D section d = 18.246 mm, the installation angle α d = 14.8°; The chord length L of the E-E section e = 15.640 mm, the installation angle α e = 13.3°

[0044] The A-A section of the blade is located at 0% of the blade span, and the coordinates of its profile are shown in Table 1.

[0045] Table 1 Coordinates of the fan blade section A-A

[0046]

[0047] The B-B section of the blade is located at 25% of the blade span, and the coordinates of its profile are shown in Table 2.

[0048] Table 2 Coordinates of the fan blade section B-B

[0049]

[0050] The C-C section of the blade is located at 50% of the blade span, and the coordinates of its profile are shown in Table 3.

[0051] Table 3 Coordinates of the fan blade section C-C

[0052]

[0053] The D-D section of the blade is located at 75% of the blade span, and the coordinates of its profile are shown in Table 4.

[0054] Table 4 Coordinates of the fan blade section D-D

[0055]

[0056] The E-E section of the blade is located at 100% of the blade span, and the coordinates of its profile are shown in Table 5.

[0057] Table 5 Coordinates of the fan blade section E-E

[0058]

[0059] Based on the installation angles of the profiles of the different airfoils and the coordinate points of the different airfoil profiles described in Tables 1 to 5,

[0060] Obtain the profile curves of the upper airfoil 5 and the profile curves of the lower airfoil 6 in each cross-section respectively. Smoothly transition the cross-sections along the span direction and fit them into shape to form the blade 1.

Claims

1. A brake cooling fan for an aircraft brake cooling system, characterized in that, It includes a hub and multiple blades; The blades are evenly distributed on the outer circumference of the hub; Along the span direction of the blade, multiple sections are made of the blade to form multiple wing surfaces with different profile curves and wing surfaces with different profile curves, and each section is smoothly transitioned and fitted along the span direction to form a shape; Among the sections of the airfoil, the root section is A-A, the tip section is E-E, and the sections at the 0.25H, 0.5H, and 0.75H length positions from the root to the tip are the B-B section, C-C section, and D-D section respectively; in each of the above sections: the chord length L of the A-A section a = 26.066 mm, and the installation angle α a = 20.4°; the chord length L of the B-B section b = 23.459 mm, and the installation angle α b = 18.4°; the chord length L of the C-C section c = 20.853 mm, and the installation angle α c = 16.5°; the chord length L of the D-D section d = 18.246 mm, and the installation angle α d = 14.8°; the chord length of the E-E section L e = 15.640 mm, installation angle α e = 13.3°.

2. The brake cooling fan for an aircraft brake cooling system according to claim 1, characterized in that, The axial width of the hub is 1 mm to 2 mm larger than the root width of the blade.

3. The brake cooling fan for an aircraft brake cooling system according to claim 1, characterized in that, The coordinates of the A-A profile of the blade are: Table 1 Coordinates of the A-A section of the fan blade 4. The brake cooling fan for an aircraft brake cooling system according to claim 1, characterized in that, The coordinates of the B-B profile of the blade are: Table 2 Coordinates of the B-B section of the fan blade 5. The brake cooling fan for an aircraft brake cooling system according to claim 1, characterized in that, The coordinates of the C-C profile of the blade are: Table 3 Coordinates of the C-C section of the fan blade 6. The brake cooling fan for an aircraft brake cooling system according to claim 1, characterized in that, The coordinates of the D-D profile of the blade are: Table 4 Coordinates of the D-D section of the fan blade 7. The brake cooling fan for an aircraft brake cooling system according to claim 1, characterized in that, The coordinates of the E-E profile of the blade are: Table 5 Coordinates of the E-E section of the fan blade

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