An aeroengine fuel nozzle swirler

Abstract

The utility model relates to the technical field of engine, disclose an aero-engine fuel nozzle swirler, including swirler, the oil guide cone surface, oil inlet plane, second taper, second cylindrical surface, first taper, first cylindrical surface, four aspects are set gradually from the end portion on swirler, swirler is provided with a plurality of rectangular fuel flow channel, and rectangular fuel flow channel starting end is located on oil inlet plane, and the terminal end is located on first cylindrical surface, second taper and fuel oil taper in the nozzle cooperate, form the sealing surface, ensure that fuel oil can only pass through from rectangular fuel flow channel, the oil guide cone surface and fuel oil export in the nozzle cooperate, control fuel oil flow capacity, the utility model discloses can make swirler have very thin, high-precision fuel flow channel, can improve the atomization effect of fuel oil greatly when swirler works, and swirler simple structure, solid durable, the manufacturing cost is lower, is applicable to the field with higher requirement such as aero-engine.

Description

Technical Field

[0001] This utility model relates to the field of engine technology, specifically to a fuel nozzle swirler for an aircraft engine. Background Technology

[0002] In aero engines, swirlers are primarily used in the fuel supply system, especially in the fuel mixing and atomization process. They utilize the principle of rotating fluid to ensure thorough mixing of fuel and air, guaranteeing effective fuel atomization within the engine combustion chamber, thereby improving combustion efficiency and reducing emissions. Swirlers in aero engines are typically installed in front of the fuel nozzles, and their main function is to disperse fuel into small droplets using the centrifugal force generated by the rotating airflow. This increases the contact area between fuel and air, ensuring more complete and uniform combustion.

[0003] Existing ultra-fine, high-precision fuel channels have certain defects in size, arrangement, and relative position, which result in unsatisfactory atomization effects when applied to demanding fields such as aero engines, thus affecting the performance of aero engines during use and preventing them from reaching their optimal levels. Utility Model Content

[0004] The purpose of this invention is to provide a fuel nozzle swirler for aero-engines, which solves the problem of poor atomization effect caused by defects in the arrangement and position of the fuel flow channel in existing swirlers.

[0005] This utility model is achieved through the following technical solution: a fuel nozzle swirler for an aircraft engine, comprising a swirler, wherein the swirler is provided with, from one end, a guide cone surface, an inlet plane, a second cone surface, a second cylindrical surface, a first cone surface, a first cylindrical surface, and four other surfaces in sequence; the swirler is provided with multiple rectangular fuel flow channels, the starting end of each rectangular fuel flow channel being located on the inlet plane and the ending end being located on the first cylindrical surface; the second cone surface cooperates with the fuel cone surface inside the nozzle to form a sealing surface, ensuring that fuel can only pass through the rectangular fuel flow channels; the guide cone surface cooperates with the fuel outlet inside the nozzle to control the fuel flow rate.

[0006] To better realize this utility model, the plurality of rectangular fuel flow channels are further arranged in pairs and at equal intervals.

[0007] To better realize this utility model, the rectangular fuel flow channel is further divided into four parts.

[0008] To better realize this utility model, the width of the rectangular fuel flow channel is 0.26±0.01mm, the angle formed by the bottom surface of the rectangular fuel flow channel and the axis of the cyclone separator is 143.2°±10′, the maximum depth of the rectangular fuel flow channel is 0.41mm, and the total length is 2.37mm.

[0009] To better realize this utility model, the distance between the side of the rectangular fuel flow channel and the axis of the cyclone separator is 0.8±0.05mm, and the distance between the starting end of the rectangular fuel flow channel and the axis of the cyclone separator is 0.79±0.05mm.

[0010] To better realize this utility model, the hydrocyclone is further made of 9Cr18Mo material, and after quenching and tempering treatment, the hardness is ≥50HRC.

[0011] Compared with the prior art, this utility model has the following advantages and beneficial effects:

[0012] This invention enables the cyclone separator to have an extremely fine and high-precision fuel flow channel, which can significantly improve the fuel atomization effect when the cyclone separator is working. In addition, the cyclone separator itself has a simple structure, is sturdy and durable, and has a low manufacturing cost, making it suitable for fields with high requirements such as aero engines. Attached Figure Description

[0013] Figure 1 This is a schematic diagram of the overall structure of this utility model.

[0014] Figure 2 This is a frontal view of the overall structure of this utility model.

[0015] Figure 3 This is a schematic diagram of the overall structure of this utility model from the left view angle.

[0016] Figure 4 This is a cross-sectional view of a rectangular fuel flow channel structure.

[0017] Wherein: 1-swirler; 101-four-sided; 102-first cylindrical surface; 103-first conical surface; 104-second conical surface; 105-oil inlet plane; 106-oil guide conical surface; 107-second cylindrical surface; 108-rectangular fuel flow channel. Detailed Implementation

[0018] The technical solutions of the present utility model will be clearly and completely described below with reference to the accompanying drawings of the embodiments. Obviously, the described embodiments are only some embodiments of the present utility model, and not all embodiments. Based on the embodiments of the present utility model, all other embodiments obtained by those of ordinary skill in the art without creative effort are within the protection scope of the present utility model.

[0019] In the description of this utility model, it should be noted that, unless otherwise explicitly specified and limited, the terms "installation," "connection," and "joining" should be interpreted broadly. For example, they can refer to a fixed connection, a detachable connection, or an integral connection; they can refer to a mechanical connection or an electrical connection; they can refer to a direct connection or an indirect connection through an intermediate medium; and they can refer to the internal connection of two components. Those skilled in the art can understand the specific meaning of the above terms in this utility model based on the specific circumstances. Example 1:

[0020] This embodiment provides a fuel nozzle swirler for an aircraft engine, specifically as follows: Figures 1-4 As shown, the device includes a cyclone separator 1, which, from its end, is sequentially provided with an oil guide cone surface 106, an oil inlet plane 105, a second cone surface 104, a second cylindrical surface 107, a first cone surface 103, a first cylindrical surface 102, and four facets 101. The cyclone separator 1 has multiple rectangular fuel flow channels 108, with the starting end of each rectangular fuel flow channel 108 located on the oil inlet plane 105 and the ending end located on the first cylindrical surface 102. When the cyclone separator 1 is installed in the nozzle, the second cylindrical surface 107 is inserted into the nozzle, and the second cone surface 104 cooperates with the fuel cone surface inside the nozzle to form a sealing surface, ensuring that fuel can only pass through the rectangular fuel flow channels 108. The oil guide cone surface 106 cooperates with the fuel outlet inside the nozzle to control the fuel flow rate. The oil guide cone 106 cooperates with the nozzle to form the first flow channel, where the fuel is accelerated and rotated, and then enters the second flow channel composed of multiple rectangular fuel flow channels 108, and then is atomized and sprayed out.

[0021] Multiple rectangular fuel flow channels 108 are arranged in pairs and equidistantly. In this embodiment, four rectangular fuel flow channels 108 are specifically selected. The width of each rectangular fuel flow channel 108 is 0.26±0.01mm, the angle formed between the bottom surface of each rectangular fuel flow channel 108 and the axis of the cyclone separator 1 is 143.2°±10′, the maximum depth of each rectangular fuel flow channel 108 is 0.41mm, and the total length is 2.37mm. The distance between the side of each rectangular fuel flow channel 108 and the axis of the cyclone separator 1 is... The distance is 0.8±0.05mm, and the distance from the starting end of the rectangular fuel flow channel 108 to the axis of the hydrocyclone 1 is 0.79±0.05mm; the hydrocyclone 1 is made of 9Cr18Mo, which is a high-carbon chromium martensitic stainless steel material. After quenching and tempering, the hardness is ≥50HRC, which has high hardness and wear resistance; small deformation, good dimensional stability, and strong corrosion resistance, which can ensure that the hydrocyclone 1 works stably under working parameters and has a long service life.

[0022] With the above settings, the cyclone separator 1 can have an extremely fine and high-precision fuel flow channel. When the cyclone separator 1 is working, it can greatly improve the fuel atomization effect, making it suitable for fields with high requirements such as aero engines. Example 2:

[0023] This embodiment provides a method for processing a fuel nozzle swirler for an aero-engine, specifically including:

[0024] Step S1: The selected bar stock is clamped on the machine tool, and the machine tool is used to process the bar stock in sequence to form four sides 101, the first cylindrical surface 102, the first conical surface 103, the second cylindrical surface 107, the second conical surface 104, the oil inlet plane 105, and the oil guide conical surface 106, to obtain the semi-finished hydrocyclone 1; the processing technology of the four sides 101 can be CNC milling or wire cutting, and the corners are rounded, and the symmetry of its form and position tolerance is required to be 0.01mm;

[0025] Step S2: Use a clamping fixture to clamp the semi-finished hydrocyclone 1, and then clamp the fixture on a five-axis machining center. The clamping and positioning accuracy of the clamping fixture is 0.0005mm.

[0026] Step S3: The five-axis machining center uses a cutting tool to machine a rectangular fuel flow channel 108 on the semi-finished hydrocyclone 1 in a roughing and finishing manner. The starting end of the rectangular fuel flow channel 108 is located on the oil inlet plane 105, and the ending end is located on the first cylindrical surface 102. The machining is then completed.

[0027] The roughing-finishing method in step 3 is as follows: during roughing, a layered processing method is used, with the processing depth of each layer controlled at 0.3mm; then, a semi-finishing process is carried out using the same layered processing method, with the processing depth of each layer controlled at 0.1mm, leaving a margin of 0.01mm on the sides and bottom of the rectangular fuel flow channel 108; finally, the finishing process is carried out, which requires that the finishing be completed in one go.

[0028] The cutting edge length of the cutter is 0.05-0.1 mm longer than the depth of the rectangular fuel flow channel 108, the diameter of the cutter is 0.2 mm, and the cutting edge length is 0.5 mm.

[0029] The above description is merely a preferred embodiment of the present utility model and is not intended to limit the present utility model in any way. Any simple modifications or equivalent changes made to the above embodiments based on the technical essence of the present utility model shall fall within the protection scope of the present utility model.

Claims

1. A fuel nozzle swirler for an aircraft engine, characterized in that, The device includes a cyclone separator (1), which has, from its end, a guide cone (106), an inlet plane (105), a second cone (104), a second cylindrical surface (107), a first cone (103), a first cylindrical surface (102), and four sides (101). The cyclone separator (1) has multiple rectangular fuel flow channels (108), with the starting end of the rectangular fuel flow channel (108) located on the inlet plane (105) and the ending end located on the first cylindrical surface (102). The second cone (104) cooperates with the fuel cone in the nozzle to form a sealing surface, ensuring that fuel can only pass through the rectangular fuel flow channel (108). The guide cone (106) cooperates with the fuel outlet in the nozzle to control the fuel flow rate.

2. The aero-engine fuel nozzle swirler according to claim 1, characterized in that: Multiple rectangular fuel flow channels (108) are arranged in pairs and at equal intervals.

3. The aero-engine fuel nozzle swirler according to claim 2, characterized in that: There are four rectangular fuel flow channels (108).

4. The aero-engine fuel nozzle swirler according to claim 3, characterized in that: The rectangular fuel flow channel (108) has a width of 0.26±0.01mm, the bottom surface of the rectangular fuel flow channel (108) forms an angle of 143.2°±10′ with the axis of the cyclone separator (1), the maximum depth of the rectangular fuel flow channel (108) is 0.41mm, and the total length is 2.37mm.

5. The aero-engine fuel nozzle swirler according to claim 4, characterized in that: The distance between the side of the rectangular fuel flow channel (108) and the axis of the cyclone separator (1) is 0.8±0.05mm, and the distance between the starting end of the rectangular fuel flow channel (108) and the axis of the cyclone separator (1) is 0.79±0.05mm.

6. A fuel nozzle swirl converter for an aircraft engine according to any one of claims 1-5, characterized in that: The hydrocyclone (1) is made of 9Cr18Mo and has a hardness ≥50HRC after quenching and tempering.

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