A circumferential airflow homogenizing device, engine and aircraft

Abstract

This invention provides a circumferential airflow homogenizing device, an engine, and an aircraft. The device includes an annular cavity component, multiple air intake pipes, and multiple circumferential pipes. The annular cavity component is disposed outside and coaxially with the annular structure requiring air supply. The annular cavity has an outer annular surface and an inner annular surface. The multiple air intake pipes are symmetrically and evenly distributed on the outer annular surface of the annular cavity and communicate with the annular cavity. The multiple circumferential pipes are symmetrically and evenly distributed on the inner annular surface of the annular cavity and connected to the annular cavity at both ends. The air intake pipes and circumferential pipes are not coaxial. Airflow enters the annular cavity component through the air intake pipes, and after being homogenized in terms of flow rate and velocity within the annular cavity component, it flows to the annular structure through the circumferential pipes. The technical solution of this invention addresses the technical problem of the lack of a circumferential airflow homogenizing device for radially inlet annular structures in the prior art.

Description

Technical Field

[0001] This invention relates to the field of engine technology, and more particularly to a circumferential airflow uniform device, an engine, and an aircraft. Background Technology

[0002] In testing of annular components of turbine engines, such as the casing and afterburner, it is necessary to ensure that the flow rate and velocity of the intake airflow are distributed as uniformly as possible circumferentially. Existing airflow homogenization devices often employ a grid structure, where airflow flows axially along the pipeline, and the grid guides the airflow to achieve uniform distribution across the pipeline cross-section. However, devices for circumferential airflow homogenization of annular structures such as afterburners are rarely used. Furthermore, current grids are commonly used for axial airflow homogenization in pipelines and are not suitable for annular structures with radial intake, such as casings and afterburners. Additionally, the grid distribution and shape require iterative design, resulting in a complex structure and stringent requirements for installation location. Summary of the Invention

[0003] This invention provides a circumferential airflow homogenizing device, an engine, and an aircraft, which can solve the technical problem of the lack of a circumferential airflow homogenizing device for radial air intake annular structures in the prior art.

[0004] According to one aspect of the present invention, a circumferential airflow homogenizing device is provided. The device includes an annular cavity component, a plurality of air inlet pipes, and a plurality of circumferential pipes. The annular cavity component is disposed outside and coaxial with the annular structure to which air needs to be supplied. The annular cavity has an outer annular surface and an inner annular surface. The plurality of air inlet pipes are symmetrically and evenly distributed on the outer annular surface of the annular cavity and communicate with the annular cavity. The plurality of circumferential pipes are symmetrically and evenly distributed on the inner annular surface of the annular cavity and are connected to the annular cavity at both ends. The air inlet pipes and the circumferential pipes are not coaxial. The airflow enters the annular cavity component through the air inlet pipes, and after being homogenized in terms of flow rate and velocity within the annular cavity component, it flows to the annular structure through the circumferential pipes.

[0005] Furthermore, the axis of symmetry of the intake pipe is perpendicular to the outer annular surface, and the axis of symmetry of the circumferential pipe is perpendicular to the inner annular surface.

[0006] Furthermore, the intake pipe and the circumferential pipe are respectively arranged at both ends along the length direction of the annular cavity component, and the ratio of the length of the annular cavity component to the diameter of the intake pipe is a preset value.

[0007] Furthermore, the total flow area of ​​multiple circumferential pipes is greater than the total flow area of ​​multiple intake pipes.

[0008] Furthermore, the preset value ranges from 3 to 4.

[0009] According to another aspect of the present invention, an engine is provided, the engine including an annular structure requiring air supply and the annular cavity component described above in the present invention.

[0010] According to another aspect of the present invention, an aircraft is provided, the aircraft including the annular cavity component proposed above in the present invention.

[0011] According to another aspect of the present invention, an aircraft is provided, the aircraft including the engine described above.

[0012] The present invention provides a circumferential airflow homogenizing device, an engine, and an aircraft. The device homogenizes the flow rate and velocity of the airflow through an intake pipe and an annular cavity structure, and then delivers the air to the annular structure that needs air supply through circumferential pipes that are uniformly distributed along the axial direction. This can significantly improve the flow field quality of the annular structure. At the same time, the device is an axisymmetric annular cavity structure with good strength and stability, simple structure, and low manufacturing cost. Attached Figure Description

[0013] The accompanying drawings, which form part of this specification, are provided to further illustrate embodiments of the invention and, together with the textual description, explain the principles of the invention. It is obvious that the drawings described below are merely some embodiments of the invention, and those skilled in the art can obtain other drawings based on these drawings without any creative effort.

[0014] Figure 1 A schematic diagram of the structure of a circumferential airflow homogenizing device according to a specific embodiment of the present invention is shown;

[0015] Figure 2 A cross-sectional view of a circumferential airflow homogenizing device according to a specific embodiment of the present invention is shown. Detailed Implementation

[0016] It should be noted that, unless otherwise specified, the embodiments and features described in this application can be combined with each other. 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 a part of the embodiments of the present invention, and not all of them. The following description of at least one exemplary embodiment is merely illustrative and is in no way intended to limit the present invention or its application or use. 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.

[0017] It should be noted that the terminology used herein is for the purpose of describing particular embodiments only and is not intended to limit the exemplary embodiments according to this application. As used herein, the singular form is intended to include the plural form as well, unless the context clearly indicates otherwise. Furthermore, it should be understood that when the terms "comprising" and / or "including" are used in this specification, they indicate the presence of features, steps, operations, devices, components, and / or combinations thereof.

[0018] Unless otherwise specifically stated, the relative arrangement, numerical expressions, and values ​​of the components and steps set forth in these embodiments do not limit the scope of the invention. It should also be understood that, for ease of description, the dimensions of the various parts shown in the drawings are not drawn to actual scale. Techniques, methods, and devices known to those skilled in the art may not be discussed in detail, but where appropriate, such techniques, methods, and devices should be considered part of the specification. In all examples shown and discussed herein, any specific values ​​should be interpreted as merely exemplary and not as limitations. Therefore, other examples of exemplary embodiments may have different values. It should be noted that similar reference numerals and letters in the following figures denote similar items; therefore, once an item is defined in one figure, it need not be further discussed in subsequent figures.

[0019] like Figure 1 As shown, a circumferential airflow homogenizing device is provided according to a specific embodiment of the present invention. The device includes an annular cavity component, multiple air inlet pipes 1 and multiple circumferential pipes 3. The annular cavity component is disposed outside the annular structure that needs to be supplied with air and is coaxial with it. The annular cavity has an outer annular surface and an inner annular surface. The multiple air inlet pipes 1 are symmetrically and evenly distributed on the outer annular surface of the annular cavity and communicate with the annular cavity. The multiple circumferential pipes 3 are symmetrically and evenly distributed on the inner annular surface of the annular cavity and are connected to the annular cavity at both ends. The air inlet pipes 1 and the circumferential pipes 3 are not coaxial. The airflow enters the annular cavity component through the air inlet pipes 1, and after the flow rate and velocity are homogenized and distributed in the annular cavity component, it flows to the annular structure through the circumferential pipes 3.

[0020] This configuration provides a circumferential airflow homogenizing device. This device homogenizes the flow rate and velocity of the airflow through the inlet pipe 1 and the annular cavity structure 2, and then delivers the airflow to the annular structure requiring air supply through circumferential pipes 3 distributed axially. This significantly improves the flow field quality of the annular structure. Furthermore, this device is an axisymmetric annular cavity structure, exhibiting good strength and stability, simple structure, and low manufacturing cost. Compared with existing technologies, the technical solution of this invention solves the technical problem of the lack of a circumferential airflow homogenizing device for radially inlet annular structures.

[0021] Further, in this embodiment of the invention, the axis of symmetry of the intake pipe 1 is perpendicular to the outer annular surface, and the axis of symmetry of the circumferential pipe 3 is perpendicular to the inner annular surface. The intake pipe 1 and the circumferential pipe 3 are respectively disposed at both ends along the length direction of the annular cavity component. The ratio of the length of the annular cavity component to the diameter of the intake pipe 1 is a preset value. As a specific embodiment of the invention, the preset value ranges from 3 to 4. Figure 2 As shown in the cross-sectional view, the intake pipe 1 is located on the left side of the annular cavity component along its length, and the circumferential pipe 3 is located on the right side of the annular cavity component along its length. There are four intake pipes 1, evenly distributed at 90° intervals along the circumference, with a diameter of D1. The airflow enters one end of the annular cavity component (annular cavity) through the intake pipes 1. Due to the increased flow cross-sectional area within the annular cavity, the airflow velocity decreases after entering the annular cavity and moves circumferentially under the action of the pressure gradient, increasing circumferential uniformity. The length of the annular cavity is L. To ensure sufficiently uniform airflow, L is taken as 3 to 4 times D1, i.e., 3D1≤L≤4D1. At the other end of the annular cavity, there are 32 evenly distributed circumferential pipes 3 with a diameter of D2. After the airflow is decelerated through the annular cavity, it enters the annular component that needs air supply along the circumferential pipes 3. The number of circumferential pipes 3 and the diameter D2 depend on the flow area. Under the condition that the structure allows, the total flow area of ​​the multiple circumferential pipes 3 is set to be greater than the total flow area of ​​the multiple intake pipes 1.

[0022] Furthermore, in this embodiment of the invention, the circumferential airflow uniform device is an axially symmetrical thin-walled structure with good structural strength and stability. It can be manufactured by sheet metal welding or integrally formed by 3D printing.

[0023] According to another aspect of the invention, an engine is provided, comprising an annular structure requiring air supply and the annular cavity component described above. For example... Figure 2 As shown, the annular structure that requires air supply is structure 5 in the engine or test apparatus that requires air supply. It has a casing 4 on the outside and a circumferential pipe 3 to send the uniform airflow into the cavity of the casing 4. The incoming airflow is decelerated and distributed through the annular cavity and the pipeline, thereby improving the uniformity of the flow field between the casing 4 and the structure 5 and providing a circumferentially uniform airflow for the structure 5 that requires air supply.

[0024] In the numerical simulation of a certain tester, the relative standard deviation of the flow rate in the three circumferential pipes of the homogenizing device was 3%, and the relative standard deviation of the velocity field after homogenization was 13%, which showed good results. The present invention has an axisymmetric annular cavity structure with good strength and stability. At the same time, the structure is simple and reduces manufacturing costs.

[0025] According to another aspect of the present invention, an aircraft is provided, comprising either the annular cavity component or the engine described above. Since the annular cavity component described above can provide circumferentially uniform airflow to the annular mechanisms of the engine, such as the casing and afterburner, significantly improving airflow quality, its application in an aircraft can significantly enhance the aircraft's performance.

[0026] In summary, this invention provides a circumferential airflow homogenizing device, an engine, and an aircraft. This device homogenizes the flow rate and velocity of the airflow through an intake pipe and an annular cavity structure, and then delivers the air to the annular structure requiring air supply through axially uniformly distributed circumferential pipes. This significantly improves the flow field quality of the annular structure. Furthermore, this device is an axisymmetric annular cavity structure, exhibiting good strength and stability, simple structure, and low manufacturing cost. Compared with existing technologies, the technical solution of this invention solves the technical problem of the lack of a circumferential airflow homogenizing device for radially inlet annular structures.

[0027] For ease of description, spatial relative terms such as "above," "on top of," "on the upper surface of," "above," etc., are used herein to describe the spatial positional relationship of a device or feature as shown in the figures to other devices or features. It should be understood that spatial relative terms are intended to encompass different orientations in use or operation beyond the orientation of the device as described in the figures. For example, if the device in the figures were inverted, a device described as "above" or "on top of" other devices or structures would subsequently be positioned as "below" or "under" other devices or structures. Thus, the exemplary term "above" can include both "above" and "below." The device may also be positioned in other different ways (rotated 90 degrees or in other orientations), and the spatial relative descriptions used herein will be interpreted accordingly.

[0028] Furthermore, it should be noted that the use of terms such as "first" and "second" to define components is merely for the purpose of distinguishing the corresponding components. Unless otherwise stated, the above terms have no special meaning and therefore should not be construed as limiting the scope of protection of this invention.

[0029] The above description is merely a preferred embodiment of the present invention and is not intended to limit the invention. Various modifications and variations can be made to the present invention by those skilled in the art. Any modifications, equivalent substitutions, improvements, etc., made within the spirit and principles of the present invention should be included within the scope of protection of the present invention.

Claims

1. A circumferential airflow uniformizing device, characterized by, The device includes an annular cavity component, multiple air inlet pipes, and multiple circumferential pipes. The annular cavity component is disposed outside and coaxial with the annular structure that requires air supply. The annular cavity has an outer annular surface and an inner annular surface. The multiple air inlet pipes are symmetrically and evenly distributed on the outer annular surface of the annular cavity and communicate with the annular cavity. The multiple circumferential pipes are symmetrically and evenly distributed on the inner annular surface of the annular cavity and are connected to the annular cavity at both ends. The air inlet pipes and the circumferential pipes are not coaxial. Airflow enters the annular cavity component through the air inlet pipes, and after being uniformly distributed in terms of flow rate and velocity within the annular cavity component, it flows to the annular structure through the circumferential pipes.

2. The apparatus according to claim 1, characterized in that, The axis of symmetry of the intake pipe is perpendicular to the outer annular surface, and the axis of symmetry of the circumferential pipe is perpendicular to the inner annular surface.

3. The apparatus according to claim 2, characterized in that, The intake pipe and the circumferential pipe are respectively disposed at both ends along the length direction of the annular cavity component, and the ratio of the length of the annular cavity component to the diameter of the intake pipe is a preset value.

4. The apparatus according to claim 3, characterized in that, The total flow area of ​​the plurality of circumferential pipes is greater than the total flow area of ​​the plurality of intake pipes.

5. The apparatus according to claim 4, characterized in that, The preset value ranges from 3 to 4.

6. An engine, characterized in that, The engine includes an annular structure requiring air supply and an annular cavity component as described in any one of claims 1 to 5.

7. An aircraft, characterized in that, The aircraft includes the annular cavity component as described in any one of claims 1 to 5.

8. An aircraft, characterized in that, The aircraft includes the engine as described in claim 6.

Images