Titanium-aluminum alloy light-weight aero-engine turbine blade

Abstract

The utility model discloses a titanium-aluminum alloy light-weight turbine blade of an aero-engine, and relates to the technical field of aero-engines. The titanium-aluminum alloy light-weight aero-engine turbine blade comprises a margin plate, and an air guide mechanism and an installation tenon mechanism are arranged on the outer wall of the margin plate. The air guide mechanism has the technical effects that the air guide plates and the air guide blades arranged on the outer walls of the air guide plates are matched with the air guide grooves and the air guide slopes of the air guide grooves, so that high-speed airflow entering the aero-engine can be guided and shunted, the airflow flowing path is optimized, airflow resistance and turbulent flow are reduced, and the airflow passing efficiency is improved; and meanwhile, the reinforcing frame is located in the inner cavity of the air guide plate, makes contact with the inner wall of the cavity and is fixedly connected with the inner side face of the mounting cover, and the dead weight of the air guide plate can be effectively reduced.

Description

Technical Field

[0001] This utility model relates to the field of aero-engine technology, specifically to a lightweight titanium-aluminum alloy aero-engine turbine blade. Background Technology

[0002] The engine is the power source and heart of an aircraft. As one of the key components of the engine, the blades of the aero-engine play an important role not only in the overall performance of the engine, but also directly in the reliability and durability of the engine. Lightweight blades can effectively reduce the engine's rotational inertia, reduce energy loss, improve fuel efficiency, and thus improve the aircraft's range and payload capacity.

[0003] Existing lightweight designs for aero-engine turbine blades often result in reduced structural strength, making them prone to deformation and fracture under complex operating conditions such as high temperatures and high-speed airflow. This severely impacts the blade's reliability and service life. Therefore, a new design is proposed... Utility Model Content

[0004] (a) Technical problems to be solved

[0005] To address the shortcomings of existing technologies, this invention provides a lightweight titanium-aluminum alloy aero-engine turbine blade, which solves the problem that lightweight design leads to a decrease in blade structural strength and makes it prone to deformation and breakage under complex operating conditions such as high temperature and high-speed airflow impact, seriously affecting the reliability and service life of the blade.

[0006] (II) Technical Solution

[0007] To achieve the above objectives, this utility model is implemented through the following technical solution: it includes a flange, and the outer wall of the flange is provided with an air guiding mechanism and a mounting tenon mechanism;

[0008] The air guiding mechanism includes an air guiding part and a reinforcing part;

[0009] The air guiding section includes an air guiding plate and multiple sets of guide vanes, and the reinforcement section includes multiple reinforcement blocks and multiple reinforcement frames;

[0010] The air guide plate is fixedly connected to the outer wall of the edge plate on one side. A cavity is opened inside the air guide plate. The outer walls of multiple reinforcing frames are located on the inner wall of the cavity and are in contact with the inner wall of the cavity. An installation cover is fitted on the outer wall of the air guide plate. The outer walls of multiple reinforcing frames are fixedly connected to the inner side of the installation cover. The edge plate and the air guide mechanism are made of titanium-aluminum alloy. Titanium-aluminum alloy can effectively reduce the weight of the air guide blades and achieve lightweight design.

[0011] Preferably, the mounting tenon mechanism includes a tenon, one side of which is fixedly connected to the outer wall of the edge plate. The outer wall of the tenon is provided with two sets of arc-shaped grooves, which can cooperate with the protruding structure of the corresponding component to achieve preliminary positioning and connection.

[0012] Preferably, the outer wall of the air guide plate is fixedly provided with multiple guide plates, and the outer walls of the multiple guide plates are fixedly connected to the outer walls of multiple sets of guide blades. The guide plates and guide blades work together to guide and divert the airflow.

[0013] Preferably, the outer wall of the air guide plate is provided with multiple air guide slots, and the outer wall of each of the multiple air guide slots is provided with multiple air guide slopes. The air guide slots and their air guide slopes optimize the airflow path, reduce airflow resistance and turbulence, and improve airflow efficiency.

[0014] Preferably, two fixed threaded sleeves are fixedly provided on the inner side of the air guide plate, and two bolts are provided through the outer wall of the mounting cover, extending to the inner side of the two fixed threaded sleeves. The outer walls of the two bolts are respectively threaded to the inner side of the two fixed threaded sleeves, and the two fixed threaded sleeves are threaded to the two bolts that are provided through the outer wall of the mounting cover and extend to its inner side, thereby further enhancing the connection stability between the air guide plate and the mounting cover.

[0015] Preferably, a dovetail tenon is fixedly provided on the side of the tenon away from the flange plate. The dovetail tenon further enhances the stability of the connection and prevents the blade from loosening or shifting during operation.

[0016] (III) Beneficial Effects

[0017] This invention provides a lightweight titanium-aluminum alloy aero-engine turbine blade. It possesses the following characteristics:

[0018] Beneficial effects:

[0019] (I) This lightweight titanium-aluminum alloy aero-engine turbine blade, through the guide plate and guide blade set on the outer wall of the air guide plate, together with the air guide groove and its guide slope, can guide and divert the high-speed airflow entering the aero-engine, optimize the airflow path, reduce airflow resistance and turbulence, improve airflow efficiency, and thus more efficiently convert the kinetic energy of the airflow into the mechanical energy of the turbine blade, thereby improving the power output and working efficiency of the aero-engine. At the same time, the reinforcement frame is located in the cavity inside the air guide plate, contacts the inner wall of the cavity and is fixedly connected to the inner side of the mounting cover, which can effectively reduce the self-weight of the air guide plate. Combined with multiple reinforcement blocks, a stable support system is formed, which effectively disperses the stress subjected to the air guide mechanism during operation and enhances the deformation resistance and damage resistance of the air guide mechanism. The detachable design of the reinforcement frame facilitates inspection and maintenance during maintenance, further improving the safety and reliability of the blade and reducing maintenance costs.

[0020] (II) In this lightweight titanium-aluminum alloy aero-engine turbine blade, the tenon in the mounting tenon mechanism is fixedly connected to the outer wall of the edge plate on one side. The two sets of arc grooves on the outer wall of the tenon can cooperate with the protruding structure of the corresponding component to achieve precise initial positioning and connection, ensuring the accuracy of blade installation. The dovetail tenon further enhances the stability of the connection and can effectively prevent the blade from loosening or shifting under complex operating conditions such as high-speed engine operation. Attached Figure Description

[0021] Figure 1 This is a schematic diagram of the overall structure of this utility model;

[0022] Figure 2 This is a schematic diagram of the air guide mechanism of this utility model;

[0023] Figure 3 This is a schematic diagram of the internal structure of the air guide mechanism of this utility model;

[0024] Figure 4 This is a schematic diagram of the mounting tenon mechanism of this utility model;

[0025] Figure 5 This utility model Figure 2 A magnified structural diagram of region A in the middle.

[0026] In the diagram: 1. Edge plate; 2. Air guide mechanism; 21. Air guide plate; 22. Mounting cover; 23. Guide vane; 24. Guide plate; 25. Reinforcing frame; 26. Bolt; 27. Fixed threaded sleeve; 28. Reinforcing block; 29. ​​Air guide groove; 210. Air guide slope; 3. Mounting tenon mechanism; 31. Tenon; 32. Arc groove; 33. Dovetail tenon. Detailed Implementation

[0027] The technical solutions of the present utility model will be clearly and completely described below with reference to the accompanying drawings of the embodiments. Obviously, the described embodiments are only some embodiments of the present utility model, and not all embodiments. Based on the embodiments of the present utility model, all other embodiments obtained by those of ordinary skill in the art without creative effort are within the protection scope of the present utility model.

[0028] Please see Figure 1-5 The present invention provides a technical solution: including a flange 1, and an air guiding mechanism 2 and a mounting tenon mechanism 3 are provided on the outer wall of the flange 1;

[0029] The air guide mechanism 2 includes an air guide section and a reinforcement section;

[0030] The air guiding section includes an air guiding plate 21 and multiple sets of guide vanes 23, and the reinforcement section includes multiple reinforcement blocks 28 and multiple reinforcement frames 25;

[0031] The air guide plate 21 is fixedly connected to the outer wall of the edge plate 1 on one side near the edge plate 1. The air guide plate 21 has a cavity inside. The outer walls of multiple reinforcing frames 25 are all located on the inner wall of the cavity and are in contact with the inner wall of the cavity. The outer wall of the air guide plate 21 is fitted with a mounting cover 22. The outer walls of multiple reinforcing frames 25 are fixedly connected to the inner side of the mounting cover 22. Multiple guide plates 24 are fixedly installed on the outer wall of the air guide plate 21. The outer walls of multiple guide plates 24 are fixedly connected to the outer walls of multiple sets of guide blades 23. Multiple air guide grooves 29 are opened on the outer wall of the air guide plate 21. Multiple air guide slopes 210 are opened on the outer wall of the multiple air guide grooves 29 respectively. Two fixed threaded sleeves 27 are fixedly installed on the inner side of the air guide plate 21. Two bolts 26 are inserted through the outer wall of the mounting cover 22 and extend to the inner side of the two fixed threaded sleeves 27. The outer walls of the two bolts 26 are threadedly connected to the inner side of the two fixed threaded sleeves 27 respectively.

[0032] The mounting tenon mechanism 3 includes a tenon 31. The side of the tenon 31 closest to the edge plate 1 is fixedly connected to the outer wall of the edge plate 1. Two sets of arc grooves 32 are provided on the outer wall of the tenon 31. A dovetail tenon 33 is fixedly provided on the side of the tenon 31 away from the edge plate 1.

[0033] When in use, high-speed airflow enters the interior of the aero-engine. The guide vane 24 on the outer wall of the guide vane 21 and the guide blade 23 work together to guide and split the airflow. The unique shape and arrangement of the guide blade 23 allow the airflow to impact the turbine blades at a more reasonable angle and speed, causing the blades to rotate. The guide slots 29 and the guide slopes 210 on the guide vane 21 optimize the airflow path, reduce airflow resistance and turbulence, improve airflow efficiency, and enhance the aerodynamic performance of the blades, thereby more effectively converting the kinetic energy of the airflow into the mechanical energy of the turbine blades to drive the aero-engine.

[0034] The reinforcing frame 25 is located in the cavity inside the air guide plate 21. Its outer wall contacts the inner wall of the cavity and is fixedly connected to the inner side of the mounting cover 22 to form a stable support structure. At the same time, multiple reinforcing blocks 28 also reinforce the air guide mechanism 2, dispersing the stress during operation and preventing the air guide plate 21 from deforming or being damaged by external forces such as airflow impact. This ensures that the air guide mechanism 2 remains stable in complex working environments, thereby guaranteeing the overall structural strength and reliability of the turbine blades. In addition, two fixed threaded sleeves 27 are fixedly installed on the inner side of the air guide plate 21 and are threadedly connected to two bolts 26 that penetrate the outer wall of the mounting cover 22 and extend to its inner side, further strengthening the connection stability between the air guide plate 21 and the mounting cover 22. Furthermore, the reinforcing frame 25 is designed to be detachable, allowing for inspection during maintenance, thus making the air guide plate 21 safer during use.

[0035] The mounting tenon mechanism 3 is responsible for connecting and fixing the turbine blade to other engine components. The side of the tenon 31 near the flange 1 is fixedly connected to the outer wall of the flange 1. The two sets of arc grooves 32 on the outer wall of the tenon 31 can cooperate with the protruding structure of the corresponding component to achieve initial positioning and connection. The setting of the dovetail tenon 33 further enhances the stability of the connection, prevents the blade from loosening or shifting during operation, and ensures that the turbine blade and other engine components work together stably.

[0036] It should be noted that, in this document, relational terms such as "first" and "second" are used only to distinguish one entity or operation from another, and do not necessarily require or imply any such actual relationship or order between these entities or operations. Furthermore, the terms "comprising," "including," or any other variations thereof are intended to cover non-exclusive inclusion, such that a process, method, article, or apparatus that comprises a list of elements includes not only those elements but also other elements not expressly listed, or elements inherent to such a process, method, article, or apparatus. Without further limitations, an element defined by the phrase "comprising one..." does not exclude the presence of other identical elements in the process, method, article, or apparatus that includes said element.

[0037] Although embodiments of the present invention have been shown and described, it will be understood by those skilled in the art that various changes, modifications, substitutions and alterations can be made to these embodiments without departing from the principles and spirit of the present invention, the scope of which is defined by the appended claims and their equivalents.

Claims

1. A lightweight titanium-aluminum alloy aero-engine turbine blade, comprising a rim plate (1), characterized in that: The outer wall of the flange (1) is provided with an air guiding mechanism (2) and a mounting tenon mechanism (3); The air guiding mechanism (2) includes an air guiding part and a reinforcing part; The air guide section includes an air guide plate (21) and multiple sets of guide vanes (23), and the reinforcement section includes multiple reinforcement blocks (28) and multiple reinforcement frames (25); The air guide plate (21) is fixedly connected to the outer wall of the edge plate (1) on one side near the edge plate (1). The air guide plate (21) has a cavity inside. The outer walls of the multiple reinforcing frames (25) are located on the inner wall of the cavity. The outer walls of the multiple reinforcing frames (25) are in contact with the inner wall of the cavity. The outer wall of the air guide plate (21) is fitted with an installation cover (22). The outer walls of the multiple reinforcing frames (25) are fixedly connected to the inner side of the installation cover (22).

2. The lightweight titanium-aluminum alloy aero-engine turbine blade according to claim 1, characterized in that: The mounting tenon mechanism (3) includes a tenon (31), the side of the tenon (31) near the edge plate (1) is fixedly connected to the outer wall of the edge plate (1), and the outer wall of the tenon (31) is provided with two sets of arc grooves (32).

3. The lightweight titanium-aluminum alloy aero-engine turbine blade according to claim 1, characterized in that: The outer wall of the air guide plate (21) is fixedly provided with multiple guide plates (24), and the outer walls of the multiple guide plates (24) are fixedly connected to the outer walls of multiple sets of guide blades (23).

4. The lightweight titanium-aluminum alloy aero-engine turbine blade according to claim 1, characterized in that: The outer wall of the air guide plate (21) is provided with a plurality of air guide grooves (29), and the outer wall of the plurality of air guide grooves (29) is provided with a plurality of air guide slopes (210).

5. The lightweight titanium-aluminum alloy aero-engine turbine blade according to claim 1, characterized in that: Two fixed threaded sleeves (27) are fixedly provided on the inner side of the air guide plate (21). Two bolts (26) are provided through the outer wall of the mounting cover (22) and extend to the inner side of the two fixed threaded sleeves (27). The outer walls of the two bolts (26) are respectively threaded to the inner side of the two fixed threaded sleeves (27).

6. The lightweight titanium-aluminum alloy aero-engine turbine blade according to claim 2, characterized in that: A dovetail tenon (33) is fixedly provided on the side of the tenon (31) away from the edge plate (1).

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