Fuel nozzle swirlers for aircraft engines

Abstract

The present invention discloses a fuel nozzle vortex finder for an aircraft engine, comprising a fixing post, a connecting post, and a functional head. The fixing post is cylindrical, the connecting post is prismatic, and the functional head is truncated. The fixing post, the connecting post, and the functional head are coaxially connected in sequence. A conical groove is provided on the side of the functional head away from the fixing post, and a plurality of first functional holes and a plurality of second functional holes are provided in the conical groove. This structure can be integrated near the nozzle of a fuel nozzle and is composed of two circles of first functional holes and second functional holes evenly distributed circumferentially. The aperture of the first functional hole is larger than that of the second functional hole. The first functional hole is used to control the overall shape and position of the fuel mist cone, and the second functional hole is used to enhance the fuel atomization effect. This structure has low processing difficulty, short production cycle, simple and easy-to-control size, compact structure, light weight, and precise air vortex control, solving the technical problems of large mass and high processing difficulty in the prior art.

Description

Technical Field

[0001] The present invention relates to the field of aerospace, and in particular to a fuel nozzle swirler for an aero-engine. Background Art

[0002] As an important component of the engine combustion chamber, the fuel nozzle's high quality and stable and reliable performance are of great significance to aircraft engines. Fuel atomization effect is one of the important performance indicators of the fuel nozzle. In order to obtain high-quality fuel atomization effect, a fuel nozzle vortex finder is usually designed around the fuel nozzle to improve the fuel atomization quality. Generally, the fuel nozzle vortex finder is placed around the fuel nozzle nozzle. After the air passes through the compressor and enters the combustion chamber casing, a part of the compressed air passes through the spiral structure of the fuel nozzle vortex finder and is converted into a vortex, which further atomizes the mist cone sprayed from the fuel nozzle, promotes the mixing of fuel and air, increases the fuel surface area, and improves fuel combustion efficiency. Usually, the fuel nozzle vortex finder is installed at the fuel nozzle nozzle, and has several blades distributed circumferentially to separate multiple air channels and generate vortices. The prior art includes application number "201710504587.3" and invention name "A fuel nozzle vortex finder for the head of an aircraft engine combustion chamber". The applicant found that these general fuel nozzle vortex finders are mostly produced through forging and casting, additive manufacturing or welding after processing. The workpiece mass is large, the process route is complex, and the processing difficulty is high. Summary of the Invention

[0003] The object of the present invention is to provide a fuel nozzle swirler for an aircraft engine, so as to solve the technical problems of large mass and great processing difficulty in the prior art.

[0004] To achieve the above-mentioned objectives, the present invention provides a fuel nozzle vortex finder for an aircraft engine, comprising a fixing column, a connecting column and a functional head, wherein the fixing column is cylindrical, the connecting column is prismatic, and the functional head is frustum-shaped, and the fixing column, the connecting column and the functional head are coaxially connected in sequence; a conical groove is provided on a side of the functional head away from the fixing column, and a plurality of first functional holes and a plurality of second functional holes are provided in the conical groove.

[0005] Furthermore, the cross-section of the first functional hole and the cross-section of the second functional hole are both circular.

[0006] Furthermore, the plurality of first functional holes and the plurality of second functional holes are respectively arranged in a circular pattern with the center of the functional head as the center.

[0007] Furthermore, the diameter of the first functional hole is greater than the diameter of the second functional hole.

[0008] Furthermore, the second functional hole and the first functional hole are both through holes.

[0009] Furthermore, the axis of the second functional hole and the axis of the first functional hole both intersect with the axis of the fixing column, and the axis of the second functional hole and the axis of the first functional hole are parallel.

[0010] Furthermore, the diameter of the fixing column is smaller than the diameter of the circumscribed circle of the connecting column.

[0011] Furthermore, the fixing column is provided with a fixing through hole coaxial therewith.

[0012] Furthermore, a fourth conical hole coaxial with the connecting column is provided in the connecting column, and the small proximal end of the fourth conical hole is connected to the functional head, and the large diameter end is connected to the fixing through hole.

[0013] Furthermore, the functional head is provided with a connecting hole group coaxial therewith, and the connecting hole group includes a first conical hole, a second cylindrical hole, and a third conical hole connected in sequence, the first conical hole, the second cylindrical hole, and the third conical hole are all through holes, the small diameter end of the first conical hole and the small diameter end of the third conical hole are respectively connected to the two ends of the second cylindrical hole, and the large diameter end of the first conical hole is connected to the small diameter end of the fourth conical hole.

[0014] Based on the above technical solution, the present invention has the following advantages: The fuel nozzle swirler for aircraft engines provided by the present invention uses a circumferentially distributed circular hole structure to replace the rectangular slot structure separated by blades in conventional fuel nozzle swirlers. This reduces the processing difficulty and virtually eliminates the problem of heat treatment deformation. The overall structure of the fuel nozzle swirler is more compact, which can reduce the overall weight of the fuel spray system. This solves the technical problems of large mass and high processing difficulty in the existing technology. BRIEF DESCRIPTION OF THE DRAWINGS

[0015] Figure 1 It is a structural diagram of an embodiment of the present invention;

[0016] Figure 2 is a top view of an embodiment of the present invention;

[0017] Figure 3 yes Figure 2 Cross-sectional view in the AA direction;

[0018] Figure 4 yes Figure 2 Cross-sectional view in the middle BB direction;

[0019] Figure 5 yes Figure 2 Cross-sectional view in CC direction;

[0020] In the figure: 1-fixed; 2-connecting column; 3-functional head; 4-first functional hole; 5-second functional hole; 6-third tapered hole; 7-conical groove; 8-fixed through hole; 9-second cylindrical hole; 10-fourth tapered hole; 11-first tapered hole. DETAILED DESCRIPTION

[0021] In order to better understand the purpose, structure and function of the present invention, the fuel nozzle swirler for an aircraft engine of the present invention is further described in detail below with reference to the accompanying drawings.

[0022] In the description of the present invention, it should be noted that the terms "center," "longitudinal," "lateral," "upper," "lower," "front," "back," "left," "right," "vertical," "horizontal," "top," "bottom," "inner," and "outer" and the like, indicating orientations or positional relationships, are based on the orientations or positional relationships shown in the accompanying drawings and are intended solely to facilitate the description of the present invention and simplify the description. They are not intended to indicate or imply that the devices or components referred to must have a specific orientation, be constructed, or operate in a specific orientation. Therefore, they should not be construed as limiting the present invention. Furthermore, the terms "first," "second," and "third" are used for descriptive purposes only and should not be construed as indicating or implying relative importance.

[0023] To achieve the above-mentioned objectives, the present invention provides a fuel nozzle vortex finder for an aircraft engine, comprising a fixed column 1, a connecting column 2, and a functional head 3. The fixed column 1 is cylindrical, the connecting column 2 is prismatic, and the functional head 3 is frustum-shaped. The fixed column 1, the connecting column 2, and the functional head 3 are coaxially connected in sequence. A conical groove 7 is provided on a side of the functional head 3 away from the fixed column 1, and a plurality of first functional holes 4 and a plurality of second functional holes 5 are provided in the conical groove 7.

[0024] Furthermore, the cross-sections of the first functional hole 4 and the second functional hole 5 are both circular.

[0025] The fuel nozzle swirler structure in this application includes two circles of evenly distributed circumferential holes: first functional holes 4 and second functional holes 5. The first functional holes 4 have a larger diameter than the second functional holes 5. The first functional holes 4 are used to control the overall shape of the fuel spray cone, while the second functional holes 5 are used to enhance fuel atomization. During operation, a portion of the compressed air after the compressor enters the combustion chamber through the two circumferential holes in the fuel nozzle swirler. The resulting air vortex collides with the fuel ejected from the nozzle. The inner airflow promotes fuel breakup and atomization, enhancing combustion, while the outer airflow maintains the shape of the fuel spray cone and controls the flame shape.

[0026] Furthermore, the plurality of first functional holes 4 and the plurality of second functional holes 5 are respectively arranged in a circular pattern with the center of the functional head 3 as the center.

[0027] Furthermore, the diameter of the first functional hole 4 is greater than the diameter of the second functional hole 5 .

[0028] Furthermore, the third functional hole 6 and the first functional hole 4 are both through holes.

[0029] Furthermore, the axis of the second functional hole 5 and the axis of the first functional hole 4 both intersect with the axis of the fixing column 1 , and the axis of the second functional hole 5 and the axis of the first functional hole 4 are parallel.

[0030] Furthermore, the diameter of the fixing column 1 is smaller than the diameter of the circumscribed circle of the connecting column 2 .

[0031] Furthermore, the fixing column 1 is provided with a fixing through hole coaxial therewith.

[0032] Furthermore, a fourth conical hole 10 coaxial with the connecting column 2 is provided in the connecting column 2 , and the proximal small end of the fourth conical hole 10 is connected to the functional head 3 , and the large diameter end is connected to the through hole of the fixing 1 .

[0033] Furthermore, the functional head 3 is provided with a connecting hole group coaxial therewith, and the connecting hole group includes a first conical hole 11, a second cylindrical hole 9, and a third conical hole 6 connected in sequence. The first conical hole 11, the second cylindrical hole 9, and the third conical hole 6 are all through holes. The small diameter end of the first conical hole 11 and the small diameter end of the third conical hole 6 are respectively connected to the two ends of the second cylindrical hole 9, and the large diameter end of the first conical hole 11 is connected to the small diameter end of the fourth conical hole 10.

[0034] It should be noted that the conventional fuel nozzle vortex finder structure only contains a circle of circumferentially distributed blades, which has problems such as welding deformation, and the control and inspection of the blade surface dimensions are relatively difficult. If it is processed through forgings, there will be problems such as difficulty in design changes and long product iteration cycles, and the surface dimensions are also difficult to detect. The airflow channel of the conventional fuel nozzle vortex finder structure is relatively wide, and the incoming flow state has a greater impact on the generated air vortex, and the shape of the air vortex is difficult to control. Moreover, the conventional fuel nozzle vortex finder structure lacks the influence of the airflow on the generation and breakup of the oil film near the nozzle, and the impact it can have on the formation of the fog cone is very limited, and the promotion of fuel combustion is relatively small.

[0035] This application provides a fuel nozzle swirler structure with low machining difficulty, lightweight construction, and excellent atomization performance. Compared to conventional vane-type fuel nozzle swirlers, the fuel nozzle swirler provided by this application is easier to manufacture, has a more centralized structure, and has a lower overall mass. It is suitable for small-displacement aircraft engines. This fuel nozzle swirler structure is directly integrated into the fuel nozzle orifice. Its main structure comprises two circumferentially evenly distributed circles of holes. The outer circle has a slightly larger diameter, which controls the overall shape and position of the fuel spray cone, while the inner circle has a slightly smaller diameter, which enhances fuel atomization. The two circles of holes rotate in the same direction around the axis of the fuel nozzle orifice. When the aircraft engine is operating, they generate inner and outer vortexes, which together regulate the atomization quality of the fuel spray.

[0036] The fuel nozzle vortex finder structure of the present invention uses a circumferentially distributed circular hole structure to replace the rectangular slot structure separated by blades in a general fuel nozzle vortex finder. It has low processing difficulty and basically no problem of heat treatment deformation; dimensional control and detection are simpler and more accurate, design changes are convenient and quick, and product iterations are rapid; the azimuth angle control of the small holes in the circular hole structure is more detailed, and the air vortex is less affected by the incoming flow; the inner ring holes of the fuel nozzle vortex finder can be precisely aligned near the nozzle, directly affecting the generation of the fuel mist cone; the overall structure of the fuel nozzle vortex finder is more compact, which can reduce the overall weight of the fuel spray system.

[0037] It will be appreciated that the present invention has been described with reference to certain embodiments, and those skilled in the art will appreciate that various changes or equivalent substitutions may be made to these features and embodiments without departing from the spirit and scope of the present invention. Furthermore, under the teachings of the present invention, these features and embodiments may be modified to suit specific circumstances and materials without departing from the spirit and scope of the present invention. Therefore, the present invention is not limited to the specific embodiments disclosed herein, and all embodiments falling within the scope of the claims of this application are intended to be protected by the present invention.

Claims

1. A fuel nozzle vortex finder for an aircraft engine, characterized in that: The invention comprises a fixing column (1), a connecting column (2) and a functional head (3), wherein the fixing column (1) is cylindrical, the connecting column (2) is prismatic, and the functional head (3) is truncated. The fixing column (1), the connecting column (2) and the functional head (3) are coaxially connected in sequence; a conical groove (7) is provided on a side of the functional head (3) away from the fixing column (1), and a plurality of first functional holes (4) and a plurality of second functional holes (5) are provided in the conical groove (7); The plurality of first functional holes (4) and the plurality of second functional holes (5) are respectively arranged in a circular arrangement with the center of the functional head (3) as the center; the axis of the second functional hole (5) and the axis of the first functional hole (4) both intersect with the axis of the fixing column (1), and the axis of the second functional hole (5) and the axis of the first functional hole (4) are parallel; The diameter of the fixing column (1) is smaller than the diameter of the circumscribed circle of the connecting column (2); the fixing column (1) is provided with a fixing through hole coaxial with the fixing column; a fourth conical hole (10) coaxial with the fixing column (2) is provided in the connecting column (2); the small diameter end of the fourth conical hole (10) is connected to the functional head (3), and the large diameter end is connected to the fixing through hole; The functional head (3) is provided with a connecting hole group coaxial therewith, and the connecting hole group includes a first conical hole (11), a second cylindrical hole (9), and a third conical hole (6) which are connected in sequence. The first conical hole (11), the second cylindrical hole (9), and the third conical hole (6) are all through holes. The small diameter end of the first conical hole (11) and the small diameter end of the third conical hole (6) are respectively connected to the two ends of the second cylindrical hole (9), and the large diameter end of the first conical hole (11) is connected to the small diameter end of the fourth conical hole (10).

2. The fuel nozzle swirler for an aircraft engine according to claim 1, characterized in that: The cross-section of the first functional hole (4) and the cross-section of the second functional hole (5) are both circular.

3. The fuel nozzle swirler for an aircraft engine according to claim 2, characterized in that: The diameter of the first functional hole (4) is greater than the diameter of the second functional hole (5).

4. The fuel nozzle swirler for an aircraft engine according to claim 3, characterized in that: The second functional hole (5) and the first functional hole (4) are both through holes.

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