A cooling structure, a spoiler unit and a turbine blade

Abstract

The utility model relates to a cooling structure, turbulence unit and turbine blade relates to aircraft technical field to solve the problem of turbine blade trailing edge cooling performance is poor, radial distribution uneven in the prior art. The cooling structure of the utility model, including turbulence rib and turbulence column, the periphery of turbulence rib sets at least 2 turbulence columns. The utility model can increase the contact area between turbine blade pressure side wall surface and suction side wall surface, thereby enhancing the pressure -bearing capacity of turbine blade, and promoting structural strength.

Description

Technical Field

[0001] This utility model relates to the field of aircraft technology, and in particular to a cooling structure, a turbulence unit, and a turbine blade. Background Technology

[0002] Turbine inlet temperature is a crucial parameter affecting engine performance, therefore efficient cooling technologies are required to cool the turbine blades.

[0003] Currently, most of the spoiler structures used on the trailing edge of turbine blades are cylindrical, teardrop-shaped, or oblong. When the cooling air enters radially along the blade height, the flow rate is laterally distributed and flows through the spoiler. The turbine blade gradually becomes thinner in the lateral direction, which causes the internal cooling airflow to accelerate in the lateral direction, while the airflow in the radial direction decelerates. Furthermore, the airflow pressure gradually increases in the radial direction. At the same time, the cooling air flows radially and is continuously heated, resulting in a decrease in the cooling capacity of the cooling air at higher radial positions and less outflow. This leads to an uneven distribution of the outflowing air film at the trailing edge in the radial direction, resulting in poor cooling performance. Utility Model Content

[0004] Based on the above analysis, this utility model aims to provide a cooling structure, a turbulence unit, and turbine blades to solve the problems of poor cooling performance at the trailing edge of turbine blades and uneven radial distribution of the cooling air film in the prior art.

[0005] The objective of this utility model is mainly achieved through the following technical solutions:

[0006] A cooling structure includes a baffle rib and baffle columns, wherein at least two baffle columns are disposed around the baffle rib;

[0007] Along the airflow path, the turbulence ribs cause secondary airflow diversion to the turbulence column, and / or the turbulence column causes secondary airflow diversion to the turbulence ribs.

[0008] Furthermore, the rib includes an oncoming surface and rib side surfaces, with the rib side surfaces disposed at both ends of the oncoming surface along the airflow direction; the rib side surfaces are wave-shaped.

[0009] Furthermore, the turbulence rib is a long strip rib with both ends set in a circular or elliptical shape.

[0010] Furthermore, the cross-sectional shape of the turbulence column is circular.

[0011] Furthermore, the spoiler ribs form an angle of 0-60° with the direction from the leading edge to the trailing edge of the turbine blade.

[0012] Furthermore, the spoiler pillars are arranged opposite to the side of the rib, and the angle between the line connecting the two spoiler pillars and the spoiler rib is 30° to 90°.

[0013] A turbulence-dissipating unit includes multiple sets of the aforementioned cooling structures arranged in an alternating pattern;

[0014] The angle between the line connecting the two aforementioned spoiler pillars and the spoiler rib gradually decreases along the direction from the trailing edge to the leading edge of the turbine blade;

[0015] The angle between the rib and the direction from the leading edge to the trailing edge of the turbine blade gradually decreases from the root to the tip of the turbine blade.

[0016] A turbine blade includes the aforementioned turbulence unit.

[0017] Furthermore, it also includes trailing edge ribs disposed at the half-slit of the turbine blade.

[0018] Furthermore, the trailing edge rib has a conical structure.

[0019] Compared with the prior art, the present invention can achieve at least one of the following beneficial effects:

[0020] (1) The cooling structure of this utility model, the turbulence ribs and turbulence columns form a “%” type structure, which can reduce flow resistance, enhance heat exchange capacity, and make radial heat transfer distribution more uniform; at the same time, the “%” type structure formed by the turbulence ribs and turbulence columns can increase the contact area between the pressure side wall and the suction side wall of the turbine blade, thereby enhancing the structural load-bearing capacity and improving the structural strength.

[0021] (2) The turbulence unit of this utility model can play a good guiding effect on the cooling air by setting multiple sets of staggered cooling structures, thereby ensuring sufficient cooling air volume at the higher radial position of the turbine blade trailing edge and improving cooling performance.

[0022] (3) The turbine blade of this utility model, by setting trailing edge ribs, enables the cooling gas to form a gas film cooling on the trailing edge surface of the turbine blade after passing through the trailing edge ribs, which plays a covering and protection role on the trailing edge of the turbine blade, reduces the direct scouring of the trailing edge of the turbine blade by high-temperature gas, and improves the cooling effect. Attached Figure Description

[0023] The accompanying drawings are for illustrative purposes only and are not intended to limit the scope of the invention. Throughout the drawings, the same reference numerals denote the same parts.

[0024] Figure 1 This is a schematic diagram of the cooling structure of Embodiment 1 of this utility model;

[0025] Figure 2 This is a schematic diagram of the turbulence unit in Embodiment 2 of this utility model;

[0026] Figure 3This is a simulation diagram of the cooling airflow direction in Embodiment 2 of this utility model;

[0027] Figure 4 This is a schematic diagram of the turbine blade structure of Embodiment 3 of this utility model.

[0028] Figure 5 This is a schematic diagram of the tail edge rib structure of Embodiment 4 of this utility model;

[0029] Figure 6 This is a partial structural schematic diagram of the turbine blade of Embodiment 4 of this utility model.

[0030] Figure label:

[0031] 1-Break rib; 2-Break column; 3-Tail edge rib. Detailed Implementation

[0032] The preferred embodiments of the present invention will now be described in detail with reference to the accompanying drawings, which constitute a part of this application and are used together with the embodiments of the present invention to illustrate the principles of the present invention, but are not intended to limit the scope of the present invention.

[0033] Example 1

[0034] A specific embodiment of this utility model discloses a cooling structure, such as... Figure 1 As shown, it includes a baffle rib 1 and a baffle column 2, with at least two baffle columns 2 arranged around the baffle rib 1; along the airflow path, the baffle rib 1 generates airflow diversion on the baffle column 2 for secondary diversion, and / or the baffle column 2 generates airflow diversion on the baffle rib 1 for secondary diversion.

[0035] For example, two spoiler pillars 2 are arranged around the spoiler rib 1, and the two spoiler pillars 2 are respectively arranged above and below the spoiler rib in a direction perpendicular to the direction from the leading edge to the trailing edge of the turbine blade.

[0036] For example, the spoiler rib 1 includes an oncoming surface and a rib side surface, with the rib side surface disposed at both ends of the oncoming surface in the direction of airflow; the rib side surface is a wave-shaped side surface.

[0037] For example, the spoiler rib 1 can be a long strip rib with round or elliptical ends.

[0038] Preferably, the rib side is a wave-shaped side. The wave-shaped outer wall of the turbulence rib 1 can enhance the turbulence, increase the heat exchange area, and enhance the heat exchange capacity, so that the trailing edge of the turbine blade can achieve a better cooling effect.

[0039] For example, the cross-sectional shape of the turbulence column 2 can be circular, teardrop-shaped, or elliptical.

[0040] Preferably, the cross-sectional shape of the turbulence column 2 is circular, which gives the turbulence column 2 the characteristics of high flow resistance, strong heat exchange effect and easy processing.

[0041] In some embodiments, the friction rib 1 forms an angle of 0-60° with the direction from the leading edge to the trailing edge of the turbine blade, thereby allowing more cooling airflow at the high radial position and making the radial heat transfer distribution at the trailing edge of the turbine blade more uniform.

[0042] In some embodiments, the spoiler columns 2 are arranged opposite to the side of the rib, and the angle between the line connecting the two spoiler columns 2 and the spoiler rib 1 is 30° to 90°.

[0043] The cooling structure of this utility model has at least two turbulence columns arranged around the turbulence rib 1, which can reduce flow resistance, enhance heat exchange capacity, and make radial heat transfer distribution more uniform. At the same time, the turbulence rib 1 and the turbulence columns 2 can increase the contact area between the pressure side wall and the suction side wall of the turbine blade, thereby enhancing the structural load-bearing capacity and improving the structural strength.

[0044] Example 2

[0045] A specific embodiment of this utility model discloses a turbulence-disrupting unit, such as... Figure 2 As shown, it includes multiple sets of staggered cooling structures.

[0046] In some embodiments, the angle between the line connecting the two spoiler pillars 2 and the spoiler rib 1 gradually decreases along the direction from the trailing edge to the leading edge of the turbine blade; the angle between the spoiler rib 1 and the direction from the leading edge to the trailing edge of the turbine blade gradually decreases along the root of the turbine blade to the tip of the blade, such as... Figure 3 This allows cooling air to flow in along both sides of the spoiler column 2 or spoiler rib 1, causing the cooling air to deflect from the top of the turbine blade along the spoiler rib 1 at the angle formed by the spoiler column 2 and the spoiler rib 1 toward the trailing edge of the turbine blade, thus guiding the cooling air.

[0047] The turbulence unit of this invention, by setting up multiple sets of staggered cooling structures, can play a good guiding effect on the cooling air, thereby ensuring sufficient cooling air volume at the higher radial position of the turbine blade trailing edge and improving cooling performance.

[0048] Example 3

[0049] A specific embodiment of this utility model discloses a turbine blade, such as... Figure 4 As shown, it includes the turbulence unit of Embodiment 2.

[0050] Example 4

[0051] A specific embodiment of this utility model discloses a turbine blade, such as... Figures 5-6As shown, the difference from Embodiment 3 is that it also includes a trailing edge rib 3 disposed at the semi-slit of the turbine blade. The trailing edge rib 3 is used to reduce the trailing edge temperature of the turbine blade and improve the protection effect on the turbine blade.

[0052] Furthermore, the trailing edge rib 3 is configured as a conical structure, for example, a triangular pyramid structure or a quadrangular pyramid mechanism. The trailing edge rib 3 includes a cone base and a cone apex, with the cone apex positioned along the direction from the leading edge to the trailing edge of the turbine blade. This allows the cooling gas to form a gas film on the trailing edge surface of the turbine blade after passing through the trailing edge rib 3, forming gas film cooling. This provides a covering and protection function for the trailing edge of the turbine blade, reducing the direct scouring of the turbine blade trailing edge by the high-temperature combustion gas.

[0053] Preferably, the height of the trailing edge rib 3 is the same as the height of the trailing edge of the turbine blade, and the spacing is 1-5 times the height of the trailing edge of the turbine blade, so as to prevent the cooling effect from being weakened due to excessively large or small spacing of the trailing edge rib 3.

[0054] The turbine blade of this invention, by setting trailing edge ribs 3, enables the cooling gas to form a gas film cooling on the trailing edge surface of the turbine blade after passing through the trailing edge ribs 3, which covers and protects the trailing edge of the turbine blade, reduces the direct scouring of the trailing edge of the turbine blade by high-temperature combustion gas, and improves the cooling effect.

[0055] The above description is only a preferred embodiment of the present utility model, but the protection scope of the present utility model is not limited thereto. Any changes or substitutions that can be easily conceived by those skilled in the art within the technical scope disclosed in the present utility model should be included within the protection scope of the present utility model.

Claims

1. A cooling structure, characterized in that, It includes a baffle rib (1) and a baffle column (2), and at least two baffle columns (2) are arranged around the baffle rib (1); Along the airflow path, the turbulence rib (1) causes secondary airflow diversion to the turbulence column (2), and / or the turbulence column (2) causes secondary airflow diversion to the turbulence rib (1).

2. The cooling structure according to claim 1, characterized in that, The turbulence rib (1) includes an oncoming surface and a rib side surface, wherein the rib side surface is disposed at both ends of the oncoming surface along the airflow direction; the rib side surface is a wave-shaped side surface.

3. The cooling structure according to claim 1, characterized in that, The turbulence rib (1) is a long rib with both ends set in a circular or elliptical shape.

4. The cooling structure according to claim 1, characterized in that, The cross-sectional shape of the turbulence column (2) is circular.

5. The cooling structure according to claim 2, characterized in that, The turbulence rib (1) forms an angle of 0-60° with the direction from the leading edge to the trailing edge of the turbine blade.

6. The cooling structure according to claim 2, characterized in that, The turbulence column (2) is arranged opposite to the side of the rib, and the angle between the line connecting the two turbulence columns (2) and the turbulence rib (1) is 30° to 90°.

7. A turbulence-disrupting unit, characterized in that, Includes multiple sets of cooling structures as described in any one of claims 1-6, arranged in an alternating pattern; The angle between the line connecting the two turbulence pillars (2) and the turbulence rib (1) gradually decreases along the direction from the trailing edge to the leading edge of the turbine blade; The angle between the turbulence rib (1) and the direction from the leading edge to the trailing edge of the turbine blade gradually decreases from the root to the tip of the turbine blade.

8. A turbine blade, characterized in that, Includes the turbulence unit as described in claim 7.

9. The turbine blade according to claim 8, characterized in that, It also includes trailing edge ribs (3) provided at the half-slit of the turbine blade.

10. The turbine blade according to claim 9, characterized in that, The tail rib (3) has a conical structure.

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