Aviation turbine blade with multi-level cooling structure
Through the multi-level cooling structure design, including curved blades and airflow paths, the problem of poor heat dissipation of solid blades is solved, efficient heat dissipation is achieved, and the reliability of the blades and engine performance are improved.
Patent Information
- Application Number
- CN202422846420.3
- Authority / Receiving Office
- CN · China
- Patent Type
- Utility models(China)
- Current Assignee / Owner
- Filing Date
- 2024-11-21
- Publication Date
- 2025-09-16
- Estimated Expiration
- 2034-11-21
AI Technical Summary
Existing aviation turbine blades are solid structures. Although they enhance the pressure-bearing capacity, their heat dissipation performance is poor and heat is easily accumulated, affecting the blade reliability and engine performance.
A multi-level cooling structure is designed, including curved blades, heat dissipation base, guide strips, reinforcement strips and air outlets, to form an air flow loop, thereby increasing the heat dissipation area and efficiency.
It effectively improves the heat dissipation capacity of the blades, ensures good performance in high temperature environments, and guarantees stable operation of the equipment.
Smart Images
Figure CN223344113U_ABST
Abstract
Description
Technical Field
[0001] The utility model belongs to the technical field of cooling blades, and more specifically relates to an aviation turbine blade with a multi-level cooling structure. Background Art
[0002] Aviation turbine blades are responsible for converting high-temperature and high-pressure gas into mechanical energy in order to improve the thermal efficiency and reliability of the blades.
[0003] During the use of aircraft turbine blades, in order to ensure the strength of the blades, the blades are usually set to a solid structure. This practice can indeed enhance the blades' ability to cope with the pressure under various complex working conditions to a certain extent. On the other hand, solid blades have poor heat dissipation performance. The solid structure is not conducive to the rapid dissipation of heat. Heat easily accumulates inside the blades and cannot be effectively conducted away in a timely manner. This causes the blades to be in a high temperature state for a long time, further exacerbating the degradation of the blade material performance, reducing the reliability and stability of the blades, and also having an adverse impact on the performance and safe operation of the aircraft engine. Utility Model Content
[0004] The embodiments of the present disclosure relate to aviation turbine blades with a multi-level cooling structure, so as to solve the problem raised in the above-mentioned background technology that in order to ensure the strength of the blades, the blades are usually set to a solid structure. This approach can indeed enhance the ability of the blades to cope with the pressure under various complex working conditions to a certain extent. On the other hand, the blades with a solid structure perform poorly in terms of heat dissipation performance, and the solid structure is not conducive to the rapid dissipation of heat. Heat is easily accumulated inside the blades and cannot be conducted out in a timely and effective manner.
[0005] The purpose and effect of the multi-level cooling structure of the aviation turbine blade of the present utility model are achieved by the following specific technical means:
[0006] In a first aspect of the present disclosure, a multi-level cooling structure aviation turbine blade is provided, comprising: a blade, wherein the shape of the blade is an arc-shaped structure design, and a heat dissipation base is welded inside the blade; the blade comprises: an air inlet, wherein the shape of the air inlet is a circular hole structure design, and the air inlet is opened at the top of the blade.
[0007] As a preferred solution of the present invention, the blade further comprises: a guide bar, the guide bar is designed in the shape of an arc-shaped bar structure, and the guide bar is fixedly arranged on the top of the blade.
[0008] As a preferred solution of the present invention, the blade also includes: a reinforcement strip, which is designed in the shape of an arc-shaped strip structure and is welded to the inside of the blade, with a matching air hole in the middle of the reinforcement strip, and the top of the reinforcement strip is integrally connected to the guide strip; an air outlet, which is designed in the shape of a circular hole structure and is opened at both ends of the blade.
[0009] As a preferred solution of the present invention, the heat dissipation base includes: a reinforcement base, the reinforcement base is designed in the shape of an arc-shaped base structure, and the reinforcement base is fixedly arranged on the top of the heat dissipation base.
[0010] As a preferred solution of the present invention, the heat dissipation base further includes: a reinforcement groove, the reinforcement groove is designed in the shape of an arc-shaped groove structure, and the number of the reinforcement grooves is set to three, and the reinforcement grooves are opened on the top of the reinforcement base.
[0011] As a preferred solution of the present invention, the heat dissipation base further includes: a reinforcement protrusion, the reinforcement protrusion is shaped like a semicircular protrusion structure, and the reinforcement protrusion is integrally arranged on the inner side of the reinforcement groove.
[0012] Compared with the prior art, the present invention has the following beneficial effects:
[0013] Through the setting of the heat dissipation base, when the airflow continuously flows into the internal space of the blade, the airflow will flow through the reinforcement grooves, which are designed in multiple groups. This significantly increases the originally relatively limited heat dissipation area of the blade. The existence of three reinforcement grooves provides more ways for heat to dissipate, thus laying a solid foundation for improving the heat dissipation capacity of the entire blade. The reinforcement protrusions are set in an integrated manner on the inner side of the reinforcement grooves. These reinforcement protrusions further expand the heat dissipation area by virtue of their positional relationship with the reinforcement grooves. In this way, the heat inside the blade can be effectively dissipated faster and more fully, thereby greatly improving the heat dissipation effect of the entire blade, ensuring that the blade can still maintain good performance in complex and high-temperature working environments, and providing strong protection for the stable operation of related equipment. BRIEF DESCRIPTION OF THE DRAWINGS
[0014] Figure 1 It is a schematic diagram of the overall axial side three-dimensional structure of the utility model.
[0015] Figure 2 It is a schematic diagram of the disassembled structure of the blade of the present utility model.
[0016] Figure 3 This is a structural schematic diagram of the heat dissipation base of the utility model.
[0017] Figure 4 This utility model Figure 3 Schematic diagram of the locally enlarged structure at point A in the middle.
[0018] Figure 5 It is a schematic diagram of the reinforcing strip structure of the present utility model.
[0019] Figure 6 This utility model Figure 5 Schematic diagram of the locally enlarged structure at point B in the middle.
[0020] In the figure, the corresponding relationship between the component names and the drawing numbers is as follows:
[0021] 1. Blade; 101. Air inlet; 102. Guide strip; 103. Reinforcement strip; 104. Air outlet; 2. Heat dissipation base; 201. Reinforcement seat; 202. Reinforcement groove; 203. Reinforcement protrusion. DETAILED DESCRIPTION
[0022] The embodiments of the present invention are described in further detail below with reference to the accompanying drawings and examples.
[0023] Example: As shown in the attached Figure 1 To the attached Figure 6 As shown:
[0024] The utility model provides an aviation turbine blade with a multi-level cooling structure, comprising: a blade 1, the blade 1 is designed in an arc-shaped structure, and a heat dissipation base 2 is welded inside the blade 1; the blade 1 comprises: an air inlet 101, the air inlet 101 is designed in a circular hole structure, and the air inlet 101 is opened at the top of the blade 1; a guide bar 102, the guide bar 102 is designed in an arc-shaped bar structure, and the guide bar 102 is fixedly arranged at the top of the blade 1; a reinforcement bar 103, the reinforcement bar 103 is designed in an arc-shaped bar structure, and the reinforcement bar 103 is welded inside the blade 1, a matching air hole is opened in the middle of the reinforcement bar 103, and the top of the reinforcement bar 103 is integrally connected to the guide bar 102; an air outlet 104, the air outlet 104 is designed in a circular hole structure, and the air outlet 104 is opened at both ends of the blade 1.
[0025] Among them, the heat dissipation base 2 includes: a reinforcement seat 201, the reinforcement seat 201 is shaped like an arc-shaped seat structure design, and the reinforcement seat 201 is fixedly set on the top of the heat dissipation base 2; a reinforcement groove 202, the reinforcement groove 202 is shaped like an arc-shaped groove structure design, and the number of the reinforcement grooves 202 is set to three, and the reinforcement grooves 202 are opened on the top of the reinforcement seat 201; a reinforcement protrusion 203, the reinforcement protrusion 203 is shaped like a semicircular protrusion structure design, and the reinforcement protrusion 203 is integrally set on the inner side of the reinforcement groove 202.
[0026] The specific usage and function of this embodiment: During the use of the blade 1, the air inlet 101 and the air outlet 104 will form a circulation loop to circulate inside the blade 1. The guide strip 102 set on the blade 1 will guide the airflow into the interior of the blade 1 to a certain extent, thereby increasing the airflow rate inside the blade 1 and improving the heat dissipation efficiency.
[0027] When the airflow flows into the blade 1, the airflow passes through the reinforcement groove 202, which increases the heat dissipation area inside the blade 1. The reinforcement protrusion 203 is integrally arranged inside the reinforcement groove 202, which further increases the heat dissipation area and thus improves the heat dissipation effect.
Claims
1. Multi-level cooling structure aviation turbine blade, characterized in that: include: The blade (1) is designed in an arc-shaped structure, and a heat dissipation base (2) is welded inside the blade (1); the blade (1) includes an air inlet (101), the air inlet (101) is designed in a circular hole structure, and the air inlet (101) is opened at the top of the blade (1).
2. The multi-level cooling structure aviation turbine blade according to claim 1, characterized in that: The blade (1) further comprises a guide bar (102), the guide bar (102) is designed in the shape of an arc-shaped bar structure, and the guide bar (102) is fixedly arranged on the top of the blade (1).
3. The multi-level cooling structure aviation turbine blade according to claim 2, characterized in that: The blade (1) further comprises: a reinforcing strip (103), the reinforcing strip (103) being designed in the shape of an arc-shaped strip structure, and the reinforcing strip (103) being welded to the inside of the blade (1), a matching air hole being provided in the middle of the reinforcing strip (103), and the top of the reinforcing strip (103) being integrally connected to the guide strip (102); and an air outlet (104), the air outlet (104) being designed in the shape of a circular hole structure, and the air outlet (104) being provided at both ends of the blade (1).
4. The multi-level cooling structure aviation turbine blade according to claim 1, characterized in that: The heat dissipation base (2) comprises a reinforcement base (201), the reinforcement base (201) is designed in the shape of an arc-shaped base structure, and the reinforcement base (201) is fixedly arranged on the top of the heat dissipation base (2).
5. The multi-level cooling structure aviation turbine blade according to claim 4, characterized in that: The heat dissipation base (2) further comprises: a reinforcement groove (202), the reinforcement groove (202) is in the shape of an arc-shaped groove structure design, and the number of the reinforcement grooves (202) is set to three, and the reinforcement grooves (202) are opened on the top of the reinforcement seat (201).
6. The multi-level cooling structure aviation turbine blade according to claim 5, characterized in that: The heat dissipation base (2) further comprises a reinforcing protrusion (203), the reinforcing protrusion (203) being in the shape of a semicircular protrusion structure, and the reinforcing protrusion (203) being integrally arranged inside the reinforcing groove (202).