NOISE-REDUCING PROPELLER BLADE

Abstract

The invention relates to a propeller blade (10) which includes at least one root section (20) which is the starting part and which connects to the propeller hub, which forms the effective surface area that directs the air during rotational motion, and which includes at least one end section (40) at the opposite end of the end where the said wing section (30) connects to the said root section (20), in order to provide the ability to take off, cruise and maneuver in a certain direction by generating thrust in unmanned aerial vehicles.Accordingly, its novelty is characterized by the fact that it contains at least one intake surface (31) which is the upper surface of the wing body (30) of the mentioned propeller blade (10) where the flow is accelerated more and the pressure is reduced, it contains at least one pressure surface (32) which is located in the lower neighborhood of the mentioned intake surface (31) and where more pressure is generated compared to the intake surface (31), and it contains at least one tip curve (41) which is formed by the gradual curvature of the surface geometry in the mentioned tip region (40) and has at least one curvature angle (42) of 20 degrees upwards from the wing body (30). Figure 1

Description

1 TARIFF NOISE-REDUCING PROPELLER BLADE TECHNICAL AREA 5 The invention generates thrust in unmanned aerial vehicles to enable takeoff, cruising, and in a specific direction. To provide maneuverability, the initial section, which is attached to the propeller hub... rotational movement containing at least one root region that enables the connection to be made at least one wing fuselage that forms the effective surface area that directs the air during this process 10 containing, the end where the aforementioned wing fuselage connects with the aforementioned root region It relates to a propeller blade that includes at least one end region located at the opposite end. PREVIOUS TECHNIQUE Propeller systems used in unmanned aerial vehicles and the components of these systems. to improve the aerodynamic and acoustic performance of propeller blades Technical studies are gaining importance. Propeller systems, rotary motion. by accelerating the air in a specific direction, it creates thrust and the vehicle It performs its primary thrust function throughout all phases of flight, from takeoff to landing. This 20 Therefore, in the technical field, energy that provides higher efficiency at the same thrust level. reducing fuel consumption, increasing flight stability, and at the same time being particularly quiet. Developing propeller designs that reduce environmental impact is important. It is becoming a target, especially in urban applications, sensitive tasks, and Considering user-facing operating scenarios, the propeller geometry is both 25 Optimizing existing systems in terms of both performance and acoustics is preferred. This stands out as a factor that directly affects its feasibility. In propeller blades used in current technology, due to the nature of rotational motion... Flow conditions along the wing are not the same at every point. Circumference 30 with radius. Changes in speed result in different aerodynamic load distributions in different regions of the wing, and This results in different flow regimes. This situation means that in some regions the flow is more... easily becoming disordered, vortex structures growing, and turbulence increasing This leads to irregular flow patterns caused by the propeller blade's output. 2 This causes the thrust to fluctuate over time, negatively affecting flight stability. It also increases wear and tear on mechanical components by increasing the vibration level. This both speeds things up and creates a noticeable inconvenience for the user. These types of flow irregularities also affect the character of the sound, causing humming or This causes the tonal noise to become more pronounced. 5 In addition, current technical solutions address the issues arising under different operating conditions. It cannot always adequately control noise sources. Propeller The noise not only increases the total sound level, but also at certain frequencies Due to the intensified sound components, it has a more disturbing effect on human perception. 10 This creates restrictions on usage, especially in residential areas. Increased turbulence and unstable flow increase energy consumption, thus affecting flight performance. This reduces the duration. It requires more power to produce the same thrust, and this This situation becomes a significant disadvantage, especially in battery-powered systems. Therefore, unwanted noise generation and turbulence occur with the current technology. 15 different uses that can more effectively reduce productivity losses caused by New approaches are needed that can yield consistent results in these scenarios as well. It is heard. In conclusion, all the problems mentioned above require an innovation in the relevant technical field. This has made it necessary to do it. A BRIEF DESCRIPTION OF THE INVENTION The present invention aims to eliminate the aforementioned disadvantages and the related technical 25 It involves a noise-reducing propeller blade, designed to bring new advantages to the field. One aim of the invention is to create a gradually increasing tip curvature at the tip and a 20° By reducing turbulence and irregular flow structures formed at the tip thanks to the curvature angle The goal is to develop a propeller blade that reduces noise levels. 30 Another purpose of the invention is the cross-sectional shape of the suction surface and pressure surface of the E-423 airfoil. By adjusting it to suit its profile, it contributes to a more controlled flow. 3 providing and aiming for more efficient energy use with more stable thrust production. The goal is to reveal the propeller blade. All the purposes mentioned above and those that will emerge from the detailed explanation below. The present invention aims to achieve this by generating thrust in unmanned aerial vehicles for a specific number of 5 the starting part to provide the ability to take off, cruise and maneuver in one direction at least one root section which allows the connection to be made to the propeller hub containing, forming the effective surface area that directs air during rotational motion. containing at least one wing fuselage, the aforementioned root region of the said wing fuselage a propeller containing at least one end section located at the opposite end of the end to which it is connected 10 It is the wing. Accordingly, the innovation lies in the wing body of the aforementioned propeller blade. The surface that is at least the upper surface, where the flow accelerates more and the pressure decreases. containing an absorption surface, located in the lower vicinity of the aforementioned absorption surface and at least one pressure surface where more pressure is generated compared to the suction surface. its inclusion, the surface geometry in the aforementioned end region gradually increases by 15 formed by the curvature of the wing and at least one angle of 20 degrees upwards from the wing fuselage. It must contain at least one bending region with a bending angle. Thus, in the tip region By reducing the resulting irregular flow structures and associated turbulence, the user Unwanted noise that negatively affects comfort is reduced. A characteristic feature of a possible construction of the invention is the connection of the aforementioned root region. at least one connecting lug with a protruding shape that allows it to be fixed in place. It includes. Thus, the propeller blade is positioned correctly at the attachment point. It is ensured that it is fixed firmly, preventing damage that occurs during rotational movement. The safe transfer of goods is possible. 25 Another possible configuration feature of the invention is the aforementioned connecting lug. It must contain at least one mounting hole that allows for connection. This allows the mounting elements to pass through the mounting hole, ensuring a secure connection. It is ensured that it is established in this way. 30 BRIEF DESCRIPTION OF THE FIGURE 4 Figure 1 shows a representative perspective view of the propeller blade, which is the subject of the invention. It has been given. Figure 2 shows a representative side view of the propeller blade that is the subject of the invention. DETAILED DESCRIPTION OF THE INVENTION This detailed explanation of the invention only serves to better understand the subject. This is explained with examples that will not create any limiting effect. Figure 1 shows a representative perspective view of the propeller blade (10) that is the subject of the invention. The aforementioned propeller blade (10) is given. It is used on all, including drones. It is used in unmanned aerial vehicles. Propeller blade (10), rotary motion the basic element that creates thrust by pushing or dragging the surrounding air during the process It is a component and plays a critical role in the execution and maintenance of the flight. 15 The propeller blade (10) that is the subject of the invention has an unwanted occurrence during operation. by contributing to the reduction of flow effects, a more balanced and efficient thrust. This ensures energy production. In this way, flight performance is improved and energy is saved. its use is being made more efficient and things like noise that affect user comfort are being addressed. Negative aspects are reduced. The subject of the invention is a propeller blade (10), micro UAV 20 They can be designed to be suitable for use in various applications, and preferred in a given configuration, approximately 240-260 mm diameter and 100-115 mm slope (pitch) It possesses these values. The subject of the invention is a propeller blade (10) with at least one root zone (20) 25 It is located. The mentioned root region (20) is the starting point of the propeller blade (10). is the most critical part for the propeller blade (10) to work together with the system. It is one of the regions. Because the root region (20) is the propeller blade (10) of the propeller. It enables connection to the hub, and the hub in question connects directly. or indirectly connected to the motor shaft. Thus the propeller blade (10) is connected to the motor shaft. It works by taking the rotational motion. Therefore, the root region (20), propeller the wing (10) must be held firmly, its shape must be maintained during operation and will ensure the protection of its position and the safe transfer of forces It is arranged in this way. The root zone (20) contains at least one connecting ear (21). The aforementioned connection The ear (21) enables the attachment of the propeller blade (10) to the relevant attachment point. It functions as a connecting element with a protruding shape. The connecting lug. (21) helps to ensure the correct alignment of the propeller blade (10) during assembly. and the loads generated during operation are controlled more effectively. It contributes to the transfer of the rotation of the propeller blade (10). to prevent loosening, slipping or unwanted movement during use By transitioning to a more stable and secure working environment, the aim is to achieve this. The subject of the invention is a propeller blade (10) with at least one mounting lug (21) on it. There is a mounting hole (22). The aforementioned mounting hole (22) is for the propeller blade. (10) ensure that it is securely joined with the relevant fasteners during assembly. This is the opening that allows the mounting hole (22) to pass through. by fixing the propeller blade (10) to the correct position at the connection point. 15 It helps. Thus, under the forces generated during the work. to prevent undesirable situations such as the connection loosening or slipping It is being passed. The subject of the invention, the propeller blade (10), includes at least one wing body (30). 20 The aforementioned wing body (30) functions aerodynamically as a propeller blade (10). It is the main part that does the work, and thrust production mainly depends on the interaction of this part with the air. This happens through it. When the propeller blade (10) rotates, it pushes the air back. The surface area that directs the thrust is largely the wing body (30). The trunk (30) gradually moves forward starting from the root zone (20) 25 It is a structure that extends in a sloping manner and shows continuity throughout its width and thickness. In the preferred configuration of the invention, the wing body (30) is from root to tip. It tapers gradually, reaching approximately 35 mm in the root section, in the middle region. with cord widths of approximately 25 mm and approximately 15 mm at the end cross-section. is shaped. In a preferred configuration of the invention, the wing body (30) 30 Twist is applied throughout, approximately 0° in the root zone (20), in the middle with a stepped torsion angle of approximately +6° in the region and approximately +12° at the end section The transition is made possible thanks to this structure, the rotation of the propeller blade (10) The air it encounters during this process is more evenly distributed along the wing. 6 It is directed in this way. Thus, thrust generation becomes more stable, vibration and The aim is to reduce flow irregularities that can lead to efficiency loss. Figure 2 shows a representative side view of the propeller blade that is the subject of the invention. The wing body (30) contains at least one intake surface (31). The mentioned intake 5 The surface (31) is the upper surface of the wing body (30) and the working surface of the propeller blade (10). the surface where the flow accelerates more and consequently the pressure decreases It states that the wing body (30) contains at least one pressure surface (32). The mentioned pressure surface (32) is the lower surface of the wing body (30), and the white ray During the redirection, a relatively higher pressure region was formed, opposite 10 It represents the surface. The pressure difference between these two surfaces affects the propeller blade. (10) to accelerate the air in a certain direction and as a result produce thrust It makes it possible. In the preferred configuration of the invention, the suction surface (31) and the pressure surface (32) are 15 Its cross-sectional shape is designed to conform to the E-423 airfoil profile. That is to say... The curvature and thickness distribution of both surfaces allow for more controlled flow over the surfaces. the tendency to separate and irregular flow by being selected in a way that will allow its progress The aim is to reduce noise generation from the source. The preferred method of the invention is... In its design, the E-423 airfoil section is created with a spline-based geometry and 20 Instead of sharp / segmented transitions, smoothed surface transitions enhance continuity. is provided. The subject of the invention is a propeller blade (10) which includes at least one end section (40). The mentioned tip area (40) is 25 on the propeller blade (10) of the wing body (30). continuing outwards and corresponding to the tip of the propeller blade (10) It is a section. Circumferential velocity during the rotational motion of the propeller blade (10), radius As it grows, working conditions are most pronounced in the end region (40) It appears. In other words, the part of the propeller blade (10) near the tip. simultaneously moving at a higher speed and directing the flow 30 It plays a more critical role in this regard. Therefore, the white ray at the tip. such as becoming disordered, the growth of vortex structures and their transformation into noise. Adverse effects tend to be concentrated mostly in the extremity region (40). 7 There is at least one end bend (41) on the end region (40). The mentioned end The curve (41) of the surface geometry at the tip of the propeller blade (10) created by bending in this way and aimed at directing the flow in a more controlled manner. It is a shaping. The gradual nature of this end bend (41) prevents a sudden break or sharp fracture. Instead of a transition, a transition that increases as it progresses toward the end along the end region (40) 5 This means that the flow is smoother at the end. The aim is to change direction. The size of the tip bend (41) is at least one bend The angle of curvature (42) is expressed as follows: The mentioned angle of curvature (42) is the distance from the wing body. (30) the end curve formed by curling upwards (41) the referenced main It expresses the angle it makes according to geometry. The angle of curvature (42), preferred in the invention 10 In its resulting structure, the angle is 20°. In this way, the end bend (41) is specific and repeatable. The flow formed in the end region (40) is defined by a geometric parameter. It contributes to reducing their irregularities. The subject of the invention is to determine the angle of curvature of the propeller blade (10) as (42) 20°, 15 a bend that will create sufficient effect in directing the flow in the end region (40) It is aimed at ensuring that the end bend (41) with this value is random at the end flow. a more controlled flow regime that will reduce the likelihood of turbulence due to breaks It aims to create irregular flow structures at the end and the associated irregular flow patterns. reducing turbulence, thus more stable thrust of the propeller blade (10) 20 the noise level produced affects user comfort. is reduced. In addition, thanks to the gradual increase in the tip curvature (41), both geometric continuity is preserved and a sudden wall is formed in the end region of the flow (40). By enabling it to change direction without encountering its effect, the corrective effect targeted by the invention is achieved. The effect is achieved in a more balanced manner. In the preferred design of the invention, 25 smoother flow at the tip compared to classic propeller geometries As a result, ambient noise is reduced by approximately 10 dB at a distance of 1 meter. In light of all that has been explained, the working principle of the invention is as follows: propeller By accelerating the air backward during the rotational movement of the wing (10), it creates a thrust of 30 irregular flow effects occurring especially in the end region (40) during production is reduced. For this reason, the end region (40) is created gradually. Thanks to the end bend (41), more controlled flow direction is ensured. The fold (41) is defined by the fold angle (42) and the preferred fold of the invention 8 In its structure, the bend angle (42) is determined to be 20°, at the end This helps to reduce the tendency of the flow to turn into turbulence with sudden interruptions. is provided. Thus, turbulence-induced flow irregularities in the end region (40) 5 By reducing the propeller blade (10), it produces a more stable thrust, consequently noise levels are being reduced and energy use is becoming more efficient. a contribution is being made. The scope of protection of the invention is set out in the claims attached hereto and is strictly limited to these 10. The detailed explanation cannot be limited to the examples given. Because in technology... A specialist, without deviating from the main theme of the invention, will do what is described above. It is clear that similar structures can emerge in light of this. 9 REFERENCE NUMBERS GIVEN IN THE FIGURE Propeller Blade Root Region 21 Connection Ear 5 22 Mounting Holes Wing Fuselage 31 Suction Surfaces 32 Pressure Surface 10 40 End Zones 41 End Bends 42° Fold Angle

Claims

REQUESTS 1. The invention generates thrust in unmanned aerial vehicles to enable takeoff, cruising, and movement in a specific direction. To ensure maneuverability, the starting section and propeller 5 containing at least one root region (20) that enables connection to the umbilicus, forming the effective surface area that directs the air during rotational motion. containing at least one wing fuselage (30), the aforementioned wing fuselage (30) The end that is at the opposite end of the end that is connected to the mentioned root region (20) It is a propeller blade (10) with a small tip area (40); its characteristic is; 10 the upper surface of the wing body (30) of the mentioned propeller blade (10) at least one suction point, which is the surface where the flow accelerates more and the pressure drops. including the surface (31), in the lower neighborhood of the mentioned absorption surface (31) at least one where there is more pressure than on the suction surface (31) containing pressure surface (32), surface 15 in the mentioned end region (40). formed by the gradual curvature of its geometry and from the wing body (30) having at least one bend angle of 20 degrees upwards (42) It includes an end bend (41).

2. According to claim 1, a propeller blade (10) has the characteristic of; the aforementioned root 20 protruding form that enables fixing to the connection point of the region (20) It has at least one connection ear (21).

3. According to claim 2, a propeller blade (10) has the following characteristic; the aforementioned connection. at least one mounting on the ear (21) that provides the connection 25 It contains the hole (22).

4. According to claim 1, a propeller blade (10) with the characteristic of having a diameter of 240-260 mm and It has a slope of 100-115 mm.

5. According to claim 1, a propeller blade (10) has the characteristic of; in the root region (20) 35 with a cord width of 25 mm in the middle section and 15 mm at the end section (40). It is having.

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