Rear cone vibration absorption structure of aero-engine turbine
By designing the vibration absorption structure of vibration absorption cavity, communication pipe, barrier plate and damping spring in the rear cone of the aircraft engine, the problems of waste space and poor vibration prevention effects in the cone design are solved, and efficient absorption and suppression of the pulsation of the airflow after turbine is achieved.
Patent Information
- Application Number
- CN202411700337.3
- Authority / Receiving Office
- CN · China
- Patent Type
- Applications(China)
- Current Assignee / Owner
- Filing Date
- 2024-11-26
- Publication Date
- 2025-03-07
Smart Images
Figure CN119572322A_ABST
Abstract
Description
Technical Field
[0001] The present application belongs to the technical field of aircraft engine turbine rear cone design, and specifically relates to an aircraft engine turbine rear cone vibration absorption structure. Background Art
[0002] A cone is arranged behind the turbine of an aircraft engine to construct the inner flow path surface of the airflow path behind the turbine and form a diffuser structure to reduce the aerodynamic separation and loss of the main airflow.
[0003] The rear cone of an aircraft engine turbine is usually designed as a single-layer or double-layer gyroid structure, which is generally a hollow structure with a large internal cavity and a large amount of space waste.
[0004] In addition, currently, in order to reduce the airflow pulsation after the aircraft engine turbine, additional vibration-proof structures are usually designed, which will occupy additional space and usually need to take into account the cooling effect. The vibration absorption capacity is limited and the vibration-proof effect is not good.
[0005] This application is proposed in view of the above-mentioned technical defects. Summary of the invention
[0006] The purpose of the present application is to provide a vibration absorbing structure for the rear cone of an aircraft engine turbine, so as to overcome or alleviate at least one of the known technical defects.
[0007] The technical solution of this application is: A vibration absorption structure for a rear cone of an aircraft engine turbine, comprising a vibration absorption cavity, a connecting pipe, a baffle plate, and a damping spring: The vibration absorbing chamber is arranged inside the cone; The baffle plate is arranged in the vibration absorbing cavity, dividing the vibration absorbing cavity into a connecting cavity and a damping cavity; the baffle plate is densely covered with damping holes; The damping spring is arranged in the damping cavity and abuts against the side wall of the damping cavity and between the baffle plate; The connecting pipe is connected between the vibration absorbing cavity and the cone, and connects the connecting cavity and the outer wall surface of the cone.
[0008] According to at least one embodiment of the present application, in the above-mentioned aircraft engine turbine rear cone vibration absorption structure, there are multiple connecting pipes.
[0009] According to at least one embodiment of the present application, in the above-mentioned aircraft engine turbine rear cone vibration absorption structure, the acoustic cavity frequency of the vibration absorption cavity is consistent with the main frequency of the measured turbine rear airflow pulsation.
[0010] According to at least one embodiment of the present application, in the above-mentioned aircraft engine turbine rear cone vibration absorption structure, there are multiple damping springs.
[0011] According to at least one embodiment of the present application, in the above-mentioned aircraft engine turbine rear cone vibration absorption structure, the natural frequency of the damping spring is consistent with the measured main frequency of the turbine rear airflow pulsation.
[0012] According to at least one embodiment of the present application, in the above-mentioned aircraft engine turbine rear cone vibration absorption structure, there are multiple groups of vibration absorption chambers and their corresponding connecting pipes, baffles, and damping springs, which are distributed circumferentially in the cone and grouped according to the pulsation frequency of the airflow after the turbine. The acoustic cavity frequency of each group of vibration absorption chambers and the natural frequency of the damping spring are consistent with a pulsation frequency of the airflow after the turbine.
[0013] This application has at least the following beneficial technical effects: Provided is an aircraft engine turbine rear cone vibration absorption structure, which fully utilizes the space inside the cone for design, does not occupy additional space, avoids unnecessary space waste, does not need to consider cooling factors, has strong designability and operability, can utilize a larger internal space for vibration absorption, can achieve better vibration isolation effect, and can cancel other additional vibration isolation structure designs. BRIEF DESCRIPTION OF THE DRAWINGS
[0014] Figure 1 is a schematic diagram of a vibration absorbing structure of a turbine rear cone of an aircraft engine provided in an embodiment of the present application; Figure 2 It is a schematic diagram of a baffle provided in an embodiment of the present application being arranged in a vibration absorbing cavity and cooperating with a damping spring to absorb vibration; Figure 3 It is a schematic diagram of a connecting pipe designed in an embodiment of the present application with a square cross section, which absorbs radar waves incident on the surface of the cone from the rear through multiple refractions; in: 1-vibration absorption chamber; 2-cone; 3-connecting pipe; 4-blocking plate; 5-damping spring; 6-turbine; A-connecting cavity; B-damping cavity.
[0015] In order to better illustrate the present embodiment, some parts of the drawings may be omitted, enlarged or reduced, and do not represent the size of the actual product. In addition, the drawings are only used for illustrative purposes and should not be construed as limitations on the present application. DETAILED DESCRIPTION
[0016] In order to make the technical solution and advantages of the present application clearer, the technical solution of the present application will be described in further detail in detail and in detail with reference to the accompanying drawings. It can be understood that the specific embodiments described here are only partial embodiments of the present application, which are only used to explain the present application, not to limit the present application. It should be noted that, for the convenience of description, only the parts related to the present application are shown in the accompanying drawings, and other related parts can refer to the general design.
[0017] In addition, unless otherwise defined, the technical terms or scientific terms used in the description of this application shall have the usual meanings understood by those of ordinary skill in the art to which this application belongs. The words used in the description of this application to indicate orientation are only used to indicate relative directions or positional relationships. When the absolute position of the described object changes, its relative positional relationship may also change accordingly. The word "include" used in the description of this application indicates that the elements or objects appearing before the word include the elements or objects listed after the word and their equivalents, but does not exclude other elements or objects.
[0018] In addition, it should be noted that, unless otherwise clearly specified and limited, the words "installation", "connection" and similar terms used in the description of this application should be understood in a broad sense. For example, the connection can be a fixed connection or a detachable connection; it can be a mechanical connection or an electrical connection; it can be a direct connection or an indirect connection through an intermediate medium. Technical personnel in the field can understand its specific meaning in this application according to the specific circumstances.
[0019] An aircraft engine turbine rear cone vibration absorption structure, such as Figure 1 As shown, it includes a vibration absorbing chamber 1, a connecting pipe 3, a blocking plate 4, and a damping spring 5.
[0020] The vibration absorbing cavity 1 is a hollow structure composed of thin-walled plates, which is arranged inside the cone 2, and a single-side outer wall partially bulges outward.
[0021] The connecting pipe 3 is connected between the vibration absorption chamber 1 and the cone 2, supporting the vibration absorption chamber 1 in the cone 2, and connecting the inner wall of the vibration absorption chamber 1 and the outer wall of the cone 2, so that the pulsation of the airflow after the turbine can be absorbed into the vibration absorption chamber 1, thereby absorbing and suppressing the pulsation of the airflow after the turbine.
[0022] In order to ensure reliable support for the vibration absorbing chamber 1, multiple connecting pipes 3 may be designed.
[0023] In order to enhance the absorption and suppression effect of the pulsation of the airflow after the turbine, the volume of the vibration absorption chamber 1 can be designed so that the acoustic cavity frequency of the vibration absorption chamber 1 is consistent with the main frequency of the measured pulsation of the airflow after the turbine, so that the pulsation of the airflow after the turbine can resonate with the acoustic cavity of the vibration absorption chamber 1, so that the pulsation energy can be quickly attenuated.
[0024] The baffle plate 4 is a thin-walled plate structure, which is arranged in the vibration absorption chamber 1 to divide the vibration absorption chamber 1 into a connecting chamber A and a damping chamber B. The baffle plate 4 is densely covered with damping holes, which can further absorb and dissipate the pulsation energy of the airflow after the turbine, weaken the pulsation of the airflow after the turbine, and enhance the absorption and suppression effect of the pulsation of the airflow after the turbine.
[0025] The baffle plate 4 can slide in the vibration absorption chamber 1, and the damping spring 5 is arranged in the damping chamber B, abutting against the side wall of the damping chamber B and the baffle plate 4. There can be multiple springs, and the natural frequency is consistent with the main frequency of the measured air flow pulsation after the turbine, so that the pulsation energy can be quickly attenuated through resonance, further enhancing the absorption and suppression effect of the air flow pulsation after the turbine, such as Figure 2 shown.
[0026] The natural frequency of the damping spring 5 is calculated as follows: ; in, is the natural frequency of the damping spring 5; is the stiffness coefficient of the damping spring 5; It is the equivalent pressure borne by the damping spring 5.
[0027] Taking into account that there may be multiple pulsation frequencies of the airflow after the turbine, it is possible to design multiple groups of vibration absorption chambers 1 and their corresponding connecting pipes 3, baffles 4, and damping springs 5, which are distributed circumferentially in the cone 2 and grouped according to the pulsation frequency of the airflow after the turbine. The acoustic cavity frequency of each group of vibration absorption chambers 1 and the natural frequency of the damping spring 5 are consistent with a pulsation frequency of the airflow after the turbine, so that the pulsation of the airflow after the turbine can be comprehensively and effectively suppressed at all frequencies.
[0028] Considering that cone 2 is the main scattering source of backward radar signals, the cross section of connecting pipe 3 can be designed to be square, which can absorb radar waves incident on the surface of cone 2 from the rear through multiple refractions, such as Figure 3 As shown, the reflected signal of the radar wave is reduced, the radar detectability is reduced, there is no need to set up too many additional radar absorbing structures, and the space occupied by the radar absorbing structures is reduced.
[0029] The aircraft engine turbine rear cone vibration absorption structure disclosed in the above-mentioned embodiment makes full use of the space inside the cone 2 for design, does not occupy additional space, avoids unnecessary waste of space, and does not need to consider cooling factors. It has strong designability and operability, can utilize a larger internal space for vibration absorption, can achieve better vibration isolation effect, and can cancel other additional vibration isolation structure designs.
[0030] So far, the technical solution of the present application has been described in conjunction with the preferred embodiments shown in the accompanying drawings. Those skilled in the art should understand that the scope of protection of the present application is obviously not limited to these specific embodiments. Without departing from the principles of the present application, those skilled in the art can make equivalent changes or substitutions to the relevant technical features, and the technical solutions after these changes or substitutions will fall within the scope of protection of the present application.
Claims
1. An aircraft engine turbine rear cone vibration absorption structure, characterized in that: It comprises a vibration absorbing chamber (1), a connecting pipe (3), a baffle plate (4), and a damping spring (5): The vibration absorption chamber (1) is arranged inside the cone (2); The baffle plate (4) is arranged in the vibration absorption chamber (1) to divide the vibration absorption chamber (1) into a connecting chamber (A) and a damping chamber (B); the baffle plate (4) is densely covered with damping holes; The damping spring (5) is arranged in the damping chamber (B) and abuts against the side wall of the damping chamber (B) and between the baffle plate (4); The connecting pipe (3) is connected between the vibration absorbing cavity (1) and the cone (2), and is connected between the connecting cavity (A) and the outer wall surface of the cone (2).
2. The aircraft engine turbine rear cone vibration absorption structure according to claim 1, characterized in that: There are multiple connecting pipes (3).
3. The aircraft engine turbine rear cone vibration absorption structure according to claim 1, characterized in that: The acoustic cavity frequency of the vibration absorption cavity (1) is consistent with the main frequency of the measured air flow pulsation after the turbine.
4. The aircraft engine turbine rear cone vibration absorption structure according to claim 1, characterized in that: There are multiple damping springs (5).
5. The aircraft engine turbine rear cone vibration absorption structure according to claim 1, characterized in that: The natural frequency of the damping spring (5) is consistent with the main frequency of the measured air flow pulsation after the turbine.
6. The aircraft engine turbine rear cone vibration absorption structure according to claim 1, characterized in that: There are multiple groups of vibration absorption chambers (1) and their corresponding connecting pipes (3), baffles (4), and damping springs (5), which are distributed in the cone (2) along the circumferential direction and grouped according to the pulsation frequency of the airflow after the turbine. The acoustic cavity frequency of each group of vibration absorption chambers (1) and the natural frequency of the damping springs (5) are consistent with a pulsation frequency of the airflow after the turbine.