A two-stage vortex generator with obliquely cut holes and radially rotating blades

Abstract

This invention relates to the field of combustion chamber vortex generators, specifically disclosing a two-stage vortex generator with obliquely cut orifices and radially rotating blades. The generator includes a first-stage obliquely cut orifice vortex generator, radial vortex blades, a rotating blade shaft, rotating blades, a vortex baffle, and a second-stage radial vortex generator. The first-stage obliquely cut orifice vortex generator is connected to the second-stage radial vortex generator via the radial vortex blades. The second-stage radial vortex generator is connected to the vortex baffle. The rotating blades are rotatably connected to the rotating blade shaft, which is located between the first-stage obliquely cut orifice vortex generator and the second-stage radial vortex generator, and is positioned near the airflow outlet end of the radial vortex blades. This two-stage vortex generator can increase the swirl intensity of the airflow passing through the second-stage vortex blades, improve the turbulence at the vortex generator outlet, and enhance fuel atomization quality and ignition performance.

Description

Technical Field

[0001] This invention relates to the field of combustion chamber vortex technology, specifically a two-stage vortex with obliquely cut holes and radially rotating blades. Background Technology

[0002] Combustion chamber ignition is the starting point and critical stage of aero-engine operation, extremely important for the normal operation and safety of the aircraft. Successful ignition is one of the most basic and crucial technical requirements for all aero-engines. Many factors influence combustion chamber ignition. From a state parameter perspective, these include combustion chamber inlet temperature, pressure, airflow, and ignition energy. From a design parameter perspective, these include fuel atomization quality, flow field structure, and fuel mist distribution. Swirlers introduce turbulence and vortices into the combustion chamber, promoting fuel-air mixing. The presence of these turbulence and vortices increases the contact area and diffusion velocity between fuel and air, thus better promoting fuel ignition and combustion. A reasonable vortex design and arrangement can adjust the distribution and transmission path of ignition energy, which helps to provide uniform and stable ignition energy. Traditional two-stage vortex designs combining oblique-hole vortexers and radial vortexers employ conventional designs, such as... Figure 2 As shown, the existing two-stage radial vortex generator is welded to the head of the combustion chamber. The first-stage oblique-hole vortex generator is restricted from moving axially by a baffle. The two-stage vortex generator, which combines the oblique-hole vortex generator and the radial vortex generator, cannot achieve the best effect of turbulence and vortex. The atomization performance after being combined with the fuel nozzle cannot meet the ignition requirements and affects the combustion stability in the flame tube. Summary of the Invention

[0003] The purpose of this invention is to provide a two-stage vortex generator with a combination of oblique-cut orifice and radial rotating blades. This addresses the problems of traditional two-stage vortex generator structures that combine oblique-cut orifice vortices and radial vortices. The first-stage oblique-cut orifice vortex generator and the second-stage radial vortex generator have different structural forms, resulting in poor shearing effect after combination and limited improvement in fuel atomization. Furthermore, the two-stage vortex generator cannot achieve the desired turbulence and vortex effects, impacting ignition performance and combustion stability. Additionally, the first-stage oblique-cut orifice vortex generator is mounted on the second-stage radial vortex generator via a baffle, making it impossible to ensure concentricity between the two, which can easily lead to performance differences among the multiple vortices.

[0004] The objective of this invention can be achieved through the following technical solutions:

[0005] A two-stage vortex generator with oblique-cut orifice combined radial rotating blades includes a first-stage oblique-cut orifice vortex generator, radial vortex blades, a rotating blade shaft, rotating blades, a vortex baffle, and a second-stage radial vortex generator. The first-stage oblique-cut orifice vortex generator is connected to the second-stage radial vortex generator through the radial vortex blades. The second-stage radial vortex generator is connected to the vortex baffle. The rotating blades are rotatably connected to the rotating blade shaft, which is connected between the first-stage oblique-cut orifice vortex generator and the second-stage radial vortex generator and is located near the flow outlet end of the radial vortex blades.

[0006] In a further embodiment, the vortex baffle is groove-shaped, with the bottom surface of the groove connected to the bottom surface of the secondary radial vortex. The vortex baffle is positioned between the radial vortex blades and the secondary radial vortex, and a radial range of motion is provided between the groove wall of the vortex baffle and the secondary radial vortex.

[0007] In a further embodiment, the oblique hole and inner wall of the first-stage oblique-cut hole vortex form a first flow guide channel in the axial direction of the first-stage oblique-cut hole vortex, and the first flow guide channel is used to guide the airflow to the axial outlet of the second-stage radial vortex.

[0008] In a further embodiment, a second flow channel is formed between the outer wall of the first-stage oblique-cut vortex generator and the bottom surface of the second-stage radial vortex generator. The second flow channel is used to guide the airflow to the axial outlet of the second-stage radial vortex generator and merges with the airflow guided by the first flow channel at the axial inlet of the second-stage radial vortex generator.

[0009] In a further embodiment, the radial vortex blades and the rotating blades are sequentially arranged within the second guide channel.

[0010] In a further embodiment, the radial vortex blades are used to guide the airflow to drive the rotating blades around the rotating blade axis.

[0011] In a further embodiment, the primary oblique-cut vortex generator is integrally formed.

[0012] In a further design, the first-stage oblique-cut vortex generator is welded together with the radial vortex generator blades and the second-stage radial vortex generator, and is also welded to the combustion chamber flame tube head through the vortex generator baffle.

[0013] In a further embodiment, the rotating blade is inserted into the rotating blade shaft and then connected to the radial vortex blade by welding.

[0014] In a further embodiment, the axial length of the rotating blade is less than the shaft of the rotating blade.

[0015] The beneficial effects of this invention are:

[0016] The first and second stage vortex generators of this invention adopt a separate design. When the airflow enters the combustion chamber, the airflow through the first stage oblique-cut vortex generator generates aerodynamic swirl force, which drives the rotating blades of the second stage radial vortex generator to rotate along the rotating blade axis through the radial vortex generator blades, thereby increasing the swirl intensity of the airflow through the second stage vortex generator blades. By utilizing the design of the first and second stage vortex generators with opposite swirl directions, the shear force is increased, and the turbulence at the vortex generator outlet is improved.

[0017] The rotating blades in the radial vortex blades of this invention can rotate around the rotating blade axis. For a two-stage vortex blade combining a first-stage oblique-cut hole vortex blade and a second-stage radial vortex blade, it can improve fuel atomization quality and ignition performance.

[0018] In this invention, during vortex generator installation, the first-stage oblique-cut vortex generator, radial vortex generator blades, rotating blade shaft, and second-stage radial vortex generator are connected together by welding. The vortex generator baffle is welded to the head of the combustion chamber flame tube, ensuring the concentricity of the first-stage oblique-cut vortex generator and the second-stage radial vortex generator, and reducing the performance differences between multiple vortex generators caused by eccentricity.

[0019] When the atomization effect is poor, the present invention can adjust the ignition performance and flame stability of the aero-engine by changing the radial vortex blades, the rotating blade shaft and the number of rotating blades. Attached Figure Description

[0020] To more clearly illustrate the technical solutions in the embodiments of the present invention or the prior art, the drawings used in the description of the embodiments or the prior art will be briefly introduced below. Obviously, the drawings described below are some embodiments of the present invention. For those skilled in the art, other drawings can be obtained based on these drawings without creative effort.

[0021] Figure 1 This is a cross-sectional schematic diagram of a two-stage vortex generator with obliquely cut holes and radially rotating blades according to the present invention;

[0022] Figure 2 This is a cross-sectional schematic diagram of a two-stage vortex generator in the related technology of this invention;

[0023] Figure 3 This is a schematic diagram of a two-stage vortex generator with obliquely cut holes and radially rotating blades according to an embodiment of the present invention;

[0024] In the figure: 1. First-stage oblique-cut vortex generator; 2. Radial vortex generator blade; 3. Rotating blade shaft; 4. Rotating blade; 5. Vortex generator baffle; 6. Second-stage radial vortex generator; 101. First guide channel; 102. Second guide channel. Detailed Implementation

[0025] The technical solutions of the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some embodiments of the present invention, and not all embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of the present invention.

[0026] A two-stage vortex generator with obliquely cut holes and radially rotating blades, such as Figure 1 As shown, it includes a primary oblique-hole vortex generator 1, a radial vortex generator blade 2, a rotating blade shaft 3, a rotating blade 4, a vortex generator baffle 5, and a secondary radial vortex generator 6. The primary oblique-hole vortex generator 1 is connected to the secondary radial vortex generator 6 through the radial vortex generator blade 2. The secondary radial vortex generator 6 is connected to the vortex generator baffle 5. The rotating blade 4 is rotatably connected to the rotating blade shaft 3. The rotating blade shaft 3 is connected between the primary oblique-hole vortex generator 1 and the secondary radial vortex generator 6, and is close to the flow outlet end of the radial vortex generator blade 2.

[0027] Its working principle or implementation method is as follows: when the airflow enters the combustion chamber, the airflow through the first-stage oblique-hole vortex generator generates aerodynamic swirling force. The blades are designed to rotate, and the swirling airflow formed by the radial vortex generator blades enables the rotating blades to rotate around the rotating blade axis, forming better turbulence and vortices. By utilizing the design of the first-stage oblique-hole vortex generator 1 and the second-stage radial vortex generator 6 with opposite rotation directions, the shear force is increased, the turbulence at the vortex generator outlet is improved, and the problem of poor fuel atomization effect leading to unsuccessful ignition and poor flame stability when the oblique-hole vortex generator is used in the combustion chamber is solved. This improves the atomization performance, ignition performance and flame stability of the aero-engine combustion chamber.

[0028] Based on the above working principle, some preferred embodiment structures or implementation methods are provided, such as... Figure 1 As shown, the vortex baffle 5 is grooved, with its bottom surface connected to the bottom surface of the secondary radial vortex 6. The vortex baffle 5 is positioned between the radial vortex blades 2 and the secondary radial vortex 6, and a radial range of motion is provided between the groove wall of the vortex baffle 5 and the secondary radial vortex 6. This radial range of motion ensures that the fuel nozzle can be smoothly inserted into the primary oblique-cut orifice vortex 1.

[0029] The rotating blade 4 can be inserted into the rotating blade shaft 3. After insertion, it is connected to the radial vortex blade 2 by welding. The axial length of the rotating blade 4 is less than that of the rotating blade shaft 3 to ensure that the rotating blade 4 will not get stuck when it rotates around the rotating blade shaft 3.

[0030] The oblique holes and inner wall of the first-stage oblique-hole vortex generator 1 form a first flow guide channel 101 along the axial direction of the first-stage oblique-hole vortex generator 1. The first flow guide channel 101 is used to guide the airflow to the axial outlet of the second-stage radial vortex generator 6. A second flow guide channel 102 is formed between the outer wall of the first-stage oblique-hole vortex generator 1 and the bottom surface of the second-stage radial vortex generator 6. The second flow guide channel 102 is used to guide the airflow to the axial outlet of the second-stage radial vortex generator 6, and merges with the airflow guided by the first flow guide channel 101 at the axial inlet of the second-stage radial vortex generator 6. The radial vortex blades 2 and the rotating blades 4 are sequentially arranged in the second flow guide channel.

[0031] The first-stage oblique-cut orifice vortex generator 1 is welded together with the radial vortex blade 2 and the second-stage radial vortex generator 6. Finally, the vortex baffle 5 is welded to the head of the combustion chamber flame tube. The first-stage oblique-cut orifice vortex generator 1 is integrated, which makes it easier to adjust as a whole. This ensures that the first-stage oblique-cut orifice vortex generator 1 and the second-stage radial vortex generator 6 are concentric, and the fuel nozzle can be smoothly inserted into the first-stage oblique-cut orifice vortex generator 1, thus completing the connection of the two-stage vortex generator with oblique-cut orifice combined radial rotating blades on the combustion chamber flame tube.

[0032] In practical use, when air enters the combustion chamber, the airflow forms a swirling airflow after entering the first guide channel 101. The airflow then enters the second guide channel 102, causing the rotating blades 4 to rotate around the rotating blade axis 3, increasing the intensity of the swirling airflow. This swirling airflow is opposite to the swirling airflow formed after passing through the first guide channel 101. When they meet, they generate a greater shear force, resulting in more effective turbulence and vortex formation, better fuel atomization, better ignition performance, and more stable combustion.

[0033] The three-dimensional structure of a two-stage vortex generator with obliquely cut holes and radially rotating blades is as follows: Figure 3 As shown. The number of radial vortex blades 2, rotating blade shaft 3 and rotating blades 4 can be multiple and can be set according to requirements. The rotation speed of rotating blades 4 and the intensity of swirling airflow in the second guide channel 102 can be controlled by adjusting the number of radial vortex blades 2, rotating blade shaft 3 and rotating blades 4 to improve the atomization performance, ignition performance and flame stability of the combustion chamber.

[0034] Those skilled in the art should understand that the connection achieved by welding in the above embodiments can also be achieved by other methods, such as hot pressing, or, when the process permits, by bonding or other means, to achieve the same fixing effect as welding.

[0035] It should be noted that the terms "first," "second," etc., used in this application are used to distinguish similar objects and are not necessarily used to describe a specific order or sequence. It should be understood that such data can be interchanged where appropriate for the embodiments of this application described herein. In this application, the terms "upper," "lower," "left," "right," "front," "rear," "top," "bottom," "inner," "outer," "middle," "vertical," "horizontal," "lateral," "longitudinal," etc., indicate the orientation or positional relationship based on the orientation or positional relationship shown in the accompanying drawings.

[0036] In the description of this specification, references to terms such as "an embodiment," "example," "specific example," etc., indicate that a specific feature, structure, material, or characteristic described in connection with that embodiment or example is included in at least one embodiment or example of the invention. In this specification, illustrative expressions of the above terms do not necessarily refer to the same embodiment or example. Furthermore, the specific features, structures, materials, or characteristics described may be combined in any suitable manner in one or more embodiments or examples.

[0037] The foregoing has shown and described the basic principles, main features, and advantages of the present invention. Those skilled in the art should understand that the present invention is not limited to the above embodiments. The embodiments and descriptions in the specification are merely illustrative of the principles of the invention. Various changes and modifications can be made to the invention without departing from its spirit and scope, and all such changes and modifications fall within the scope of the claimed invention.

Claims

1. A two-stage vortex generator with obliquely cut holes and radially rotating blades, characterized in that, It includes a primary oblique-hole vortex generator (1), a radial vortex generator blade (2), a rotating blade shaft (3), a rotating blade (4), a vortex generator baffle (5), and a secondary radial vortex generator (6). The primary oblique-hole vortex generator (1) is connected to the secondary radial vortex generator (6) through the radial vortex generator blade (2). The secondary radial vortex generator (6) is connected to the vortex generator baffle (5). The rotating blade (4) is rotatably connected to the rotating blade shaft (3). The rotating blade shaft (3) is connected between the primary oblique-hole vortex generator (1) and the secondary radial vortex generator (6) and is close to the flow outlet end of the radial vortex generator blade (2). The oblique hole and inner wall of the first-stage oblique hole vortex (1) form a first flow guide channel (101) in the axial direction of the first-stage oblique hole vortex (1). The first flow guide channel (101) is used to guide the airflow to the axial outlet of the second-stage radial vortex (6). A second flow channel (102) is formed between the outer wall of the first-stage oblique-cut hole vortex (1) and the bottom surface of the second-stage radial vortex (6). The second flow channel (102) is used to guide the airflow to the axial outlet of the second-stage radial vortex (6) and merge with the airflow guided by the first flow channel (101) at the axial inlet of the second-stage radial vortex (6).

2. The two-stage vortex generator with obliquely cut holes and radially rotating blades according to claim 1, characterized in that, The vortex baffle (5) is grooved, and the bottom surface of the groove is connected to the bottom surface of the secondary radial vortex (6). The vortex baffle (5) is set between the radial vortex blade (2) and the secondary radial vortex (6), and the groove wall of the vortex baffle (5) and the secondary radial vortex (6) have a radial range of motion.

3. A two-stage vortex generator with obliquely cut holes and radially rotating blades according to claim 1, characterized in that, The radial vortex blades (2) and the rotating blades (4) are sequentially arranged in the second flow channel.

4. A two-stage vortex generator with obliquely cut holes and radially rotating blades according to claim 1, characterized in that, The radial vortex blade (2) is used to guide the airflow to drive the rotating blade (4) around the rotating blade axis (3).

5. A two-stage vortex generator with obliquely cut holes and radially rotating blades according to claim 1, characterized in that, The first-stage oblique-cut vortex generator (1) is integrally set.

6. A two-stage vortex generator with obliquely cut holes and radially rotating blades according to claim 1, characterized in that, The first-stage oblique-cut vortex generator (1) is welded together with the radial vortex generator blade (2) and the second-stage radial vortex generator (6), and is welded to the head of the combustion chamber flame tube through the vortex generator baffle (5).

7. A two-stage vortex generator with obliquely cut holes and radially rotating blades according to claim 1, characterized in that, After the rotating blade (4) is inserted into the rotating blade shaft (3), it is connected to the radial vortex blade (2) by welding.

8. A two-stage vortex generator with obliquely cut holes and radially rotating blades according to claim 1, characterized in that, The axial length of the rotating blade (4) is less than that of the rotating blade shaft (3).

Images