An aeroengine turbine blade

Abstract

The present invention discloses an aeroengine turbine blade, belonging to the technical field of aviation equipment. The key points of its technical solution include a tenon head. The upper end surface of the tenon head is fixedly connected with a rim plate. The upper end surface of the rim plate is fixedly connected with a blade. Two flow guiding plates are fixedly connected to the front end surface of the blade. The flow guiding plates form three air flow channels on the outer wall of the blade, guiding the high-pressure air flow blown to one side of the blade close to the tenon head to another point of the blade with relatively low pressure, that is, the end close to the flanging, thereby reducing the separation area on the outer wall of the blade. The eddy current intensity and size of the separation area are reduced, thereby effectively reducing noise. A complete and continuous air flow heat insulation layer is formed between the high-temperature air flow on the outer wall of the blade and the blade surface, thereby reducing the blade surface temperature, and solving the problems that the existing aeroengine turbine blade generates huge noise during operation due to air operation, and the outer wall of the blade is subjected to a large heat load, resulting in a reduction in the reliability of the turbine blade.

Description

Technical Field

[0001] The present invention relates to the technical field of aviation equipment, and particularly relates to an aviation engine turbine blade. Background Art

[0002] The turbine is one of the important components in an aero-gas turbine engine. Its function is to convert most of the available thermal energy of the gas into mechanical work of the turbine. As one of the key components of the engine, the turbine blade rotates at high speed under high-temperature and high-pressure conditions, and the airflow on its surface is very complex. Therefore, the quality of the turbine blade design is related to the performance of the entire engine.

[0003] During operation, the existing aviation engine turbine blades generate huge noise due to air operation, and the heat load on the outer wall of the blade is relatively large, resulting in a reduction in the reliability of the turbine blade. Summary of the Invention

[0004] In view of the above problems, the present invention proposes an aviation engine turbine blade to solve the above problems.

[0005] The present invention is implemented as follows. An aviation engine turbine blade includes a tenon head. The upper end surface of the tenon head is fixedly connected with a rim plate. The upper end surface of the rim plate is fixedly connected with a blade. Two flow guiding plates are fixedly connected to the front end surface of the blade. A flanging is provided on the side of the blade away from the rim plate.

[0006] Preferably, in order to guide the airflow, the flow guiding plate of the aviation engine turbine blade of the present invention is in an "S" shape.

[0007] Preferably, in order to form an air flow channel, the flow guiding plate is perpendicularly arranged with respect to the outer wall of the blade in the aviation engine turbine blade of the present invention.

[0008] Preferably, in order to facilitate the airflow to turn back, the flanging is turned up towards the side of the flow guiding plate 4 in the aviation engine turbine blade of the present invention.

[0009] Preferably, in order to improve the anti-vibration effect of the blade, the blade is made of anti-vibration alloy in the aviation engine turbine blade of the present invention.

[0010] Preferably, in order to improve the wear resistance of the tenon head, the outer wall of the tenon head is coated with wear-resistant paint in the aviation engine turbine blade of the present invention.

[0011] Compared with the prior art, the beneficial effects of the present invention are as follows:

[0012] By setting a deflector plate, the deflector plate forms three air flow channels on the outer wall of the blade, guiding the high-pressure air flow blown to one side of the blade near the tenon to another point of the blade with relatively low pressure, that is, one end near the flanging, thereby reducing the separation area on the outer wall of the blade, reducing the eddy current intensity and size in the separation area, and thus effectively reducing noise. At the same time, the air flow guided by the deflector plate to the flanging folds back along the guide of the flanging after entering the inner side of the flanging. At this time, a complete and continuous air flow heat insulation layer is formed between the high-temperature air flow on the outer wall of the blade and the blade surface, thereby reducing the blade surface temperature, reducing the heat load on the outer wall of the blade, and improving reliability. BRIEF DESCRIPTION OF THE DRAWINGS

[0013] Figure 1 is the overall structure diagram of the present invention;

[0014] Figure 2 is the enlarged structure diagram of part a of the present invention;

[0015] In the figure, 1 is the tenon; 2 is the flange; 3 is the blade; 4 is the deflector plate; 5 is the flanging. DETAILED DESCRIPTION OF THE EMBODIMENTS

[0016] In order to make the objectives, technical solutions and advantages of the present invention clearer and more understandable, the present invention will be further described in detail below with reference to the accompanying drawings and embodiments. It should be understood that the specific embodiments described herein are only used to explain the present invention and are not used to limit the present invention.

[0017] In the description of the present invention, it should be understood that the orientation or positional relationship indicated by the terms "length", "width", "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", etc. is based on the orientation or positional relationship shown in the drawings, and is only for the convenience of describing the present invention and simplifying the description, rather than indicating or implying that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and therefore should not be construed as a limitation of the present invention. In addition, in the description of the present invention, the meaning of "a plurality" is two or more unless otherwise specifically defined.

[0018] Please refer to Figure 1-2 , the present invention provides the following technical solutions: including a tenon 1, the upper end surface of the tenon 1 is fixedly connected with a flange 2, the upper end surface of the flange 2 is fixedly connected with a blade 3, the front end surface of the blade 3 is fixedly connected with two deflector plates 4, and a flanging 5 is arranged on one side of the blade 3 away from the flange 2.

[0019] In this embodiment: By providing a deflector 4, the deflector 4 forms three air flow channels on the outer wall of the blade 3, guiding the high-pressure air flow blown to one side of the blade 3 near the tenon 1 to another point of the blade 3 with relatively lower pressure, that is, one end near the flanging 5, thereby reducing the separation zone on the outer wall of the blade. The eddy current intensity and size of the separation zone are reduced, thus effectively reducing noise. At the same time, the air flow guided by the deflector 4 to the flanging 5 folds back to the blade 3 along the guidance of the flanging 5 after entering the inner side of the flanging 5. At this time, a complete and continuous air flow heat insulation layer is formed between the high-temperature air flow on the outer wall of the blade 3 and the surface of the blade 3, thereby reducing the surface temperature of the blade 3, reducing the heat load on the outer wall of the blade 3, and improving reliability.

[0020] As a technical optimization scheme of the present invention, the deflector 4 is in an "S" shape.

[0021] In this embodiment: The deflector 4 is in an "S" shape, which plays a role in buffering the air flow and making the rapid air flow slower.

[0022] As a technical optimization scheme of the present invention, the deflector 4 is perpendicularly arranged with respect to the outer wall of the blade 3.

[0023] In this embodiment: The deflector 4 is perpendicularly arranged with respect to the outer wall of the blade 3, thereby playing an insulating role and facilitating the division to form three air flow guiding channels.

[0024] As a technical optimization scheme of the present invention, the flanging 5 is turned up towards the side of the deflector 4.

[0025] In this embodiment: The flanging 5 is turned up towards the side of the deflector 4. After the air flow enters the inner side of the flanging 5, it folds back to the blade 3 along the guidance of the flanging 5, forming a complete and continuous air flow heat insulation layer between the high-temperature air flow on the outer wall of the blade 3 and the surface of the blade 3, which is beneficial for temperature reduction.

[0026] As a technical optimization scheme of the present invention, the blade 3 is an anti-vibration alloy.

[0027] In this embodiment: The blade 3 is an anti-vibration alloy, which can quickly convert vibration into heat energy and dissipate it through the internal friction of the alloy's internal structure, thereby achieving the anti-vibration effect and extending the service life.

[0028] As a technical optimization scheme of the present invention, the outer wall of the tenon 1 is coated with wear-resistant paint.

[0029] In this embodiment: The outer wall of the tenon 1 is coated with wear-resistant paint, thereby improving the wear resistance of the outer wall of the tenon 1.

[0030] Working principle and usage process of the present invention: By providing a flow deflector 4, the flow deflector 4 forms three air flow channels on the outer wall of the blade 3, guiding the high-pressure air flow blown to one side of the blade 3 near the tenon 1 to another point of the blade 3 with relatively low pressure, that is, one end near the flange 5, thereby reducing the separation zone on the outer wall of the blade. The eddy current intensity and size in the separation zone are reduced, effectively reducing noise. At the same time, the air flow guided by the flow deflector 4 to the flange 5 folds back to the blade 3 along the guidance of the flange 5 after entering the inner side of the flange 5. At this time, a complete and continuous air flow heat insulation layer is formed between the high-temperature air flow on the outer wall of the blade 3 and the surface of the blade 3, thereby reducing the surface temperature of the blade 3, reducing the heat load on the outer wall of the blade 3, and improving reliability.

[0031] The above are only the preferred embodiments of the present invention and are not intended to limit the present invention. Any modifications, equivalent replacements, improvements, etc. made within the spirit and principle of the present invention shall be included within the protection scope of the present invention.

Claims

1. An aeroengine turbine blade, comprising a tenon head (1), characterized in that: The upper end surface of the tenon (1) is fixedly connected with a flange plate (2), the upper end surface of the flange plate (2) is fixedly connected with a blade (3), the front end surface of the blade (3) is fixedly connected with two flow guide plates (4), and a flanging (5) is arranged on one side of the blade (3) away from the flange plate (2); The flanging (5) is turned up towards the side of the flow guide plate (4); The flow guide plates (4) form three air flow channels on the outer wall of the blade (3), so that the high-pressure air flow blown to one side of the blade (3) close to the tenon (1) is guided to the other end of the blade (3) with relatively low pressure, that is, the end close to the flanging (5).

2. The aero-engine turbine blade according to claim 1, wherein: The flow guide plate (4) is in an "S" shape; 3. An aero-engine turbine blade according to claim 1, characterized in that: The flow guide plate (4) is perpendicular to the outer wall of the blade (3); 4. The aero-engine turbine blade according to claim 1, wherein: The blade (3) is made of anti-vibration alloy; 5. A turbine blade of an aeroengine according to claim 1, characterized in that: The outer wall of the tenon (1) is coated with wear-resistant paint.

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