Aero-engine turbine blade with noise reduction function
By setting up a projection device, air ducting groove and diversion incline in the turbine blades of the aircraft engine, the gap is reduced by using the principle of thermal expansion and contraction, and the blades are fixed by the arc groove and triangular groove of the installation of the tenon, the turbine blades are solved by the operation of the turbine blades. The noise and stability problems are used to reduce noise and improve durability.
Patent Information
- Application Number
- CN202421053655.0
- Authority / Receiving Office
- CN · China
- Patent Type
- Utility models(China)
- Current Assignee / Owner
- Filing Date
- 2024-05-15
- Publication Date
- 2025-01-03
- Estimated Expiration
- 2034-05-15
AI Technical Summary
The aircraft engine turbine blades are difficult to maintain a long-lasting uniform speed and acceleration state during operation, resulting in noise generation. In the prior art, the gap between the tenon and the tongue and groove causes the blades to collide when the speed is reduced to generate noise.
A turbine blade of an aircraft engine with noise reduction function was designed. By setting up a projection device, the gap between the edge plate and the turbine disc is reduced by using the principle of thermal expansion and contraction, and the air duct and diversion slope are set to make the blade motion more stable. , use the installation tenon to fix the blades with arc grooves and triangular grooves to reduce reaction force.
By reducing the swing amplitude and vibration of the turbine blades, noise generation is reduced, while improving the stability and durability of the blades.
Smart Images
Figure CN222296315U_ABST
Abstract
Description
Technical Field
[0001] The utility model relates to the technical field of turbine blades, in particular to an aviation engine turbine blade with a noise reduction function. Background Art
[0002] Aircraft engine turbine blades are one of the key components of aircraft engines. They are installed on the turbine disk and work in high-temperature, high-pressure, and high-speed gas flow. The function of the turbine blades is to convert the thermal energy and pressure energy of the gas into mechanical energy, drive the turbine disk to rotate, and provide power for the aircraft. Turbine blades are usually made of high-temperature alloy materials and have the characteristics of high strength, high heat resistance, and high fatigue resistance.
[0003] In the prior art, when turbine blades are installed in the mortise and tenon, there is a certain gap between the tenon and the tenon. This gap allows the blades to be fine-tuned when subjected to centrifugal force, thereby ensuring the stability of the blades during operation. However, it is difficult for aircraft engines to maintain a long-term uniform speed and acceleration state during operation. When the aircraft engine slows down, the blades will collide in the gap, thereby generating noise. Utility Model Content
[0004] In view of the deficiencies in the prior art, the technical solution adopted by the utility model to solve the technical problems is: an aircraft engine turbine blade with a noise reduction function, comprising: an edge plate, a fitting groove is provided in the wall of the edge plate; a protrusion device, the outer wall of the protrusion device is slidably connected to the inner wall of the edge plate; a blade body, the bottom of the blade body is fixedly connected to the top of the edge plate; and a mounting tenon, the top of the mounting tenon is fixedly connected to the bottom of the edge plate.
[0005] Preferably, the protruding device includes a fixed block, a through groove is provided in the wall of the fixed block, the outer wall of the fixed block is slidably connected with a trapezoidal block, the side of the trapezoidal block away from the fixed block is fixedly connected with a sliding plate, a sliding groove is provided in the wall of the sliding plate, the outer wall of the sliding plate is slidably connected to the inner wall of the edge plate through a limiting groove, and the limiting groove is provided in the wall of the edge plate, the inner wall of the edge plate is fixedly connected to the outer wall of the fixed block, and the inner wall of the edge plate is slidably connected to the outer wall of the sliding groove, and the protruding device is provided to utilize the principle of thermal expansion and contraction to push the sliding plate to protrude on the side wall of the edge plate, and by reducing the gap between the edge plate and the turbine disk, the amplitude of the blade swinging is made smaller, thereby reducing noise.
[0006] Preferably, the blade body includes a blade body, a wind guide groove is provided in the wall of the blade body, a guide slope is provided on the outer wall of the wind guide groove near the middle of the blade body, a guide side wall is provided on the side wall of the wind guide groove, and the bottom of the blade body is fixedly connected to the top of the edge plate. By providing the wind guide groove and the guide slope, the movement of the blade body is made more stable, thereby reducing the vibration of the blade body.
[0007] Preferably, the mounting tenon includes a fixing tenon, a circular arc groove is opened in the wall of the fixing tenon, a tenon is arranged outside the circular arc groove, a triangular groove is opened in the wall of the tenon, the top of the fixing tenon is fixedly connected to the bottom of the edge plate, and the bottom of the fixing tenon is fixedly connected to the top of the tenon. By setting the mounting tenon, the auxiliary edge plate and the blade body are installed on the tenon groove of the turbine disk. By setting the circular arc groove and the triangular groove, the turbine blade is fixed while reducing the magnitude of the reaction force it receives.
[0008] The beneficial effects of the utility model are as follows:
[0009] 1. The utility model provides a protruding device. When the aircraft starts to climb, the heat of the gas flowing through the turbine blades increases, causing the fixed block inside the edge plate to expand, thereby pushing the sliding plate to protrude on the side wall of the edge plate. By reducing the gap between the edge plate and the turbine disc, the amplitude of the blade swinging is smaller, thereby reducing noise.
[0010] 2. The utility model makes the blade movement more stable by providing the air guide grooves and the guide slope, thereby reducing the vibration of the blade body.
[0011] 3. The utility model provides mounting tenons, and the auxiliary edge plate and the blade body are installed on the tenon groove of the turbine disk. The circular arc groove and the triangular groove are provided to fix the turbine blade while reducing the size of the reaction force, thereby making the turbine blade more durable. BRIEF DESCRIPTION OF THE DRAWINGS
[0012] Figure 1 It is the front view of the utility model;
[0013] Figure 2 It is a cross-sectional view of the utility model;
[0014] Figure 3 It is a schematic diagram of the structure of the utility model at A;
[0015] Figure 4 It is a structural schematic diagram of B of the utility model.
[0016] In the figure: 1, edge plate; 2, raised device; 3, blade body; 4, mounting tenon; 5, fitting groove; 21, fixing block; 22, through groove; 23, trapezoidal block; 24, sliding plate; 25, sliding groove; 26, limiting groove; 31, blade body; 32, air induction groove; 33, guide slope; 34, guide side wall; 41, fixing tenon; 42, arc groove; 43, tenon; 44, triangular groove. DETAILED DESCRIPTION
[0017] The present invention is further described in detail below in conjunction with the accompanying drawings and specific embodiments. The embodiments of the present invention are provided for the purpose of illustration and description, and are not intended to be exhaustive or to limit the present invention to the disclosed forms. Many modifications and variations are obvious to those of ordinary skill in the art. The embodiments are selected and described in order to better illustrate the principles and practical applications of the present invention, and to enable those of ordinary skill in the art to understand the present invention and design various embodiments with various modifications suitable for specific purposes.
[0018] Example: See Figure 1 - Figure 4 The utility model provides a technical solution: an aircraft engine turbine blade with noise reduction function, comprising: an edge plate 1, a fitting groove 5 is provided in the wall of the edge plate 1; a protrusion device 2, the outer wall of the protrusion device 2 is slidably connected to the inner wall of the edge plate 1; a blade body 3, the bottom of the blade body 3 is fixedly connected to the top of the edge plate 1; a mounting tenon 4, the top of the mounting tenon 4 is fixedly connected to the bottom of the edge plate 1, the protrusion device 2 comprises a fixing block 21, a through groove 22 is provided in the wall of the fixing block 21, and the fixing block 2 The outer wall of the edge plate 1 is slidably connected with a trapezoidal block 23, and a sliding plate 24 is fixedly connected to the side of the trapezoidal block 23 away from the fixed block 21. A sliding groove 25 is provided in the wall of the sliding plate 24. The outer wall of the sliding plate 24 is slidably connected with the inner wall of the edge plate 1 through a limiting groove 26, and the limiting groove 26 is provided in the wall of the edge plate 1. The inner wall of the edge plate 1 is fixedly connected with the outer wall of the fixed block 21, and the inner wall of the edge plate 1 is slidably connected with the outer wall of the sliding groove 25. Before the aircraft stops climbing and is ready to reduce the speed of the aircraft engine, due to When the front turbine blade rotates in the high-temperature gas flow, a certain amount of heat is accumulated inside itself, so the turbine blade as a whole has a certain amount of heat at this time. Since the turbine blade itself uses a special metal, it is difficult to generate thermal expansion, and the fixed block 21 inside the edge plate 1 does not use the same metal as the turbine blade, so the fixed block 21 is prone to thermal expansion under high temperature conditions. Since the upper and lower ends of the fixed block 21 do not contact the inner wall of the edge plate 1 and leave a gap, the side of the fixed block 21 away from the trapezoidal block 23 is attached to and fixed to the inner wall of the edge plate 1. Under thermal expansion, the fixed block 21 expands in all directions, so at this time, the fixed block 21 pushes the trapezoidal block 23 outward without squeezing the inner wall of the edge plate 1. The pushed trapezoidal block 23 will push the sliding plate 24 to move along the sliding groove 25. At the same time, a limiting groove 26 is provided to prevent the sliding plate 24 from falling off. At this time, the sliding plate 24 protrudes on the surface of the edge plate 1, thereby reducing the gap with the turbine disc, and reducing the shaking amplitude of the turbine blade by limiting the method, thereby reducing the generation of noise.
[0019] The blade body 3 includes a blade body 31, in which an air guide groove 32 is provided in the wall of the blade body 31, and an outer wall of the air guide groove 32 near the middle of the blade body 31 is provided with a guide slope 33, and a guide side wall 34 is provided on the side wall of the air guide groove 32. The bottom of the blade body 31 is fixedly connected to the top of the edge plate 1. Due to the setting of the guide slope 33 on the air guide groove 32, the airflow can smoothly enter the air guide groove 32 and flow through the guide side wall 34. The guide side wall 34 has a certain slope, so that when the airflow collides with the guide side wall 34, the force is transmitted to the surface of the blade body 31. The magnitude of these forces is difficult to counteract the huge centrifugal force generated by the turbine blades when rotating. Therefore, the air guide groove 32, the guide slope 33 and the guide side wall 34 are used to redirect these impact forces, and then offset them through the centrifugal force, thereby reducing the impact of the turbulent airflow on the blade body 3.
[0020] The mounting tenon 4 includes a fixing tenon 41, a circular arc groove 42 is provided in the wall of the fixing tenon 41, a tenon 43 is provided outside the circular arc groove 42, a triangular groove 44 is provided in the wall of the tenon 43, the top of the fixing tenon 41 is fixedly connected to the bottom of the edge plate 1, the bottom of the fixing tenon 41 is fixedly connected to the top of the tenon 43, the protrusions on the turbine disk correspond to the circular arc groove 42 on the fixing tenon 41 and the triangular groove 44 on the tenon 43 respectively, because the turbine blades are subjected to centrifugal force when the aircraft engine moves, at this time, the triangular groove 44 and the circular arc groove 42 not only play the role of fixing the position of the turbine blades, but also the triangular groove 44 and the circular arc groove 42 play the role of obliquely transmitting and dispersing the reaction force received, and partially offsetting the reaction force generated by the centrifugal force, so that the turbine blades are fixed while also reducing the magnitude of the reaction force received by the turbine blades due to the centrifugal force.
[0021] Working principle:
[0022] When in use, a raised device 2 is provided to reduce the gap between the turbine blades and the turbine disk when the turbine blades rotate. When the aircraft starts, the aircraft engine gradually accelerates. Under the accelerated condition, the turbine blades are affected by the centrifugal force, and the outer wall of one side of the edge plate 1 and the mounting tenon 4 fits tightly with the inner wall of one side of the turbine disk. At this time, the turbine blades are difficult to generate noise due to vibration. Before the aircraft stops climbing and prepares to reduce the speed of the aircraft engine, since the turbine blades have accumulated a certain amount of heat inside themselves when they rotated in the high-temperature gas flow, the turbine blades as a whole now have a certain amount of heat. Since the turbine blades themselves are made of special metal, it is difficult for them to generate thermal expansion. The fixing block 21 inside the edge plate 1 is not made of the same metal as the turbine blades, so the fixing block 21 is prone to thermal expansion under high temperature conditions. Since the upper and lower ends of the fixing block 21 are not in contact with the inner wall of the edge plate 1 and a gap is left, the fixing block 21 The side away from the trapezoidal block 23 is attached and fixed to the inner wall of the edge plate 1. Under thermal expansion, the fixed block 21 expands in all directions. Therefore, at this time, the fixed block 21 pushes the trapezoidal block 23 outward without squeezing the inner wall of the edge plate 1. At the same time, due to the opening of the through groove 22, the fixed block 21 parts above and below the through groove 22 are easy to expand inward, thereby further squeezing the trapezoidal block 23. Due to the inclined surface setting of the trapezoidal block 23, the pushed trapezoidal block 23 will push the sliding plate 24 to move along the sliding groove 25. At the same time, a limiting groove 26 is provided to prevent the sliding plate 24 from falling off. At this time, the sliding plate 24 protrudes on the surface of the edge plate 1, thereby reducing the gap with the turbine disk. When the aircraft engine slows down, the centrifugal force on the turbine blades is reduced, and the reduction in the gap causes the turbine blades to be limited. The shaking amplitude of the turbine blades is reduced by the limiting method, thereby reducing the generation of noise.
[0023] The blade body 3 is provided to comb the airflow, so that the turbine blades are more stable when rotating. The airflow that hits the blade body 31 moves along the curvature of the blade body 31 and finally flows to the position of the air guide groove 32. Due to the setting of the guide slope 33 on the air guide groove 32, the airflow can smoothly enter the interior of the air guide groove 32 and flow through the guide side wall 34. The guide side wall 34 has a certain slope, so that when the airflow collides with the guide side wall 34, the force is transmitted to the surface of the blade body 31. The magnitude of these forces is difficult to counteract the huge centrifugal force generated by the turbine blades when rotating. Therefore, the air guide groove 32, the guide slope 33 and the guide side wall 34 are used to redirect these impact forces, and then offset them through centrifugal force, thereby reducing the impact of the turbulent airflow on the blade body 3, and making the turbine blades rotate more stably.
[0024] The mounting tenon 4 is provided so that it is difficult for the turbine blade to separate from the turbine disk under the action of centrifugation. The mounting tenon 4 is installed into the turbine groove of the turbine disk until the outer wall of the turbine disk fits with the engaging groove 5. At this time, the protrusion on the turbine disk corresponds to the circular arc groove 42 on the fixing tenon 41 and the triangular groove 44 on the tenon 43 respectively. Since the turbine blade is subjected to centrifugal force when the aircraft engine moves, the triangular groove 44 and the circular arc groove 42 not only play the role of fixing the position of the turbine blade, but also the triangular groove 44 and the circular arc groove 42 play the role of obliquely transmitting and dispersing the reaction force received, and partially offsetting the reaction force generated by the centrifugal force, so that the turbine blade is fixed while also reducing the magnitude of the reaction force received by the turbine blade due to the centrifugal force, thereby making the turbine blade more durable.
[0025] Obviously, the described embodiments are only some embodiments of the present invention, not all embodiments. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field and related fields without creative work should fall within the scope of protection of the present invention. Structures, devices and operating methods not specifically described and explained in the present invention shall be implemented according to conventional means in the field unless otherwise specified and limited.
Claims
1. An aircraft engine turbine blade with noise reduction function, characterized in that: include: An edge plate (1), wherein a fitting groove (5) is provided in a wall of the edge plate (1); A protruding device (2), wherein the outer wall of the protruding device (2) is slidably connected to the inner wall of the edge plate (1); A blade body (3), the bottom of the blade body (3) being fixedly connected to the top of the edge plate (1); A mounting tenon (4) having a top portion fixedly connected to a bottom portion of the edge plate (1).
2. The aircraft engine turbine blade with noise reduction function according to claim 1, characterized in that: The protrusion device (2) comprises a fixed block (21), a through groove (22) is provided in the wall of the fixed block (21), a trapezoidal block (23) is slidably connected to the outer wall of the fixed block (21), a sliding plate (24) is fixedly connected to the side of the trapezoidal block (23) away from the fixed block (21), a sliding groove (25) is provided in the wall of the sliding plate (24), the outer wall of the sliding plate (24) is slidably connected to the inner wall of the edge plate (1) via a limiting groove (26), and the limiting groove (26) is provided in the wall of the edge plate (1).
3. The aircraft engine turbine blade with noise reduction function according to claim 2, characterized in that: The inner wall of the edge plate (1) is fixedly connected to the outer wall of the fixed block (21), and the inner wall of the edge plate (1) is slidably connected to the outer wall of the sliding groove (25).
4. The aircraft engine turbine blade with noise reduction function according to claim 1, characterized in that: The blade body (3) comprises a blade body (31), a wind guide groove (32) is provided in the wall of the blade body (31), a flow guide inclined surface (33) is provided on the outer wall of the wind guide groove (32) near the middle of the blade body (31), a flow guide side wall (34) is provided on the side wall of the wind guide groove (32), and the bottom of the blade body (31) is fixedly connected to the top of the edge plate (1).
5. The aircraft engine turbine blade with noise reduction function according to claim 1, characterized in that: The mounting tenon (4) comprises a fixing tenon (41), a circular arc groove (42) is provided in the wall of the fixing tenon (41), a tenon head (43) is provided outside the circular arc groove (42), and a triangular groove (44) is provided in the wall of the tenon head (43).
6. The aircraft engine turbine blade with noise reduction function according to claim 5, characterized in that: The top of the fixing tenon (41) is fixedly connected to the bottom of the edge plate (1), and the bottom of the fixing tenon (41) is fixedly connected to the top of the tenon head (43).