Turbine guide vane lower margin plate cooling structure

Abstract

The invention provides a turbine guide vane lower margin plate cooling structure and relates to the technical field of aero-engines, a lower margin plate comprises an upper-layer wall and a lower-layer wall, the upper-layer wall covers the lower-layer wall, and a cavity located between the upper-layer wall and the lower-layer wall is defined; a partition wall is arranged in the cavity and divides the cavity into a gas collection cavity and a heat exchange cavity, the gas collection cavity and the heat exchange cavity are overlapped, the gas collection cavity is close to the lower layer wall, and the heat exchange cavity is close to the upper layer wall; and the gas collection cavity is communicated with the heat exchange cavity through a channel arranged on the partition wall.

Description

Technical Field

[0001] This invention relates to the field of aero-engine technology, and more specifically to a cooling structure for the lower edge plate of a turbine guide vane. Background Technology

[0002] During aero-engine operation, the temperature of the exhaust gas in front of the turbine continuously increases, exceeding the temperature resistance level of the metal. To improve aero-engine efficiency, it is necessary to enhance the cooling effect of the turbine blades (i.e., guide vanes). Current turbine guide vane designs incorporate a vertical plate structure in the middle of the lower edge plate to facilitate the installation and fixation of the guide vanes. For example... Figure 1 As shown, the vertical plate 6 divides the inner cavity of the lower edge plate into a front cavity 5 and a rear cavity 7, correspondingly dividing the lower edge plate into an upstream region 4 and a downstream region 8. Cooling gas is introduced from the front cavity 5 to cool the upstream region 4.

[0003] When cooling the downstream region 8, a relatively long film cooling orifice is provided to guide the cooling gas from the front chamber 5 to the rear chamber 7 for film cooling. The problem with this design is that the film cooling orifice is too long, and it is easy to deviate during drilling, causing the outlet position of the film cooling orifice to be off-center. In addition, during engine operation, the cooling gas flowing out of the film cooling orifice will deviate towards the suction side with lower pressure, resulting in poor film cooling coverage in the downstream region 8. Summary of the Invention

[0004] The purpose of this invention is at least to provide a cooling structure for the lower edge plate of a turbine guide vane, which can reduce the dissipation of cooling gas, concentrate the cooling gas to exchange heat with the upper wall, enhance the cooling effect, and improve the cooling efficiency.

[0005] The following provides a brief overview of one or more aspects to offer a basic understanding of them. This overview is not an exhaustive summary of all conceived aspects, nor is it intended to identify key or decisive elements of all aspects, nor to define the scope of any or all aspects. Its sole purpose is to present some concepts of one or more aspects in a simplified form to prepare for the more detailed descriptions that follow.

[0006] One embodiment of the present invention provides a cooling structure for the lower edge plate of a turbine guide vane. The lower edge plate includes an upper wall and a lower wall, with the upper wall covering the lower wall and defining a cavity between the upper and lower walls. A partition wall is provided within the cavity, dividing the cavity into an air collecting cavity and a heat exchange cavity. The air collecting cavity and the heat exchange cavity are arranged overlappingly, with the air collecting cavity closer to the lower wall and the heat exchange cavity closer to the upper wall. The air collecting cavity and the heat exchange cavity are connected through a channel provided on the partition wall.

[0007] In some embodiments, the lower wall has a flow channel that communicates with the gas collection chamber.

[0008] In some embodiments, the lower edge plate includes a vertical plate and a front cavity, and a flow channel passes through the vertical plate, connecting the front cavity and the gas collection cavity.

[0009] In some embodiments, a partition is provided inside the heat exchange chamber, which divides the heat exchange chamber into a first heat exchange chamber and a second heat exchange chamber, which are arranged side by side.

[0010] In some embodiments, the upper wall is provided with air film holes, which are connected to the first heat exchange chamber and are used to form an air film on the surface of the upper wall.

[0011] In some embodiments, the air film pores are located in the anterior region of the throat of the rim plate.

[0012] In some embodiments, an airflow outlet is provided on the side of the upper wall, and the airflow outlet is connected to the second heat exchange chamber; the lower wall has a flow guiding channel, which is connected to the air collection chamber, and the airflow outlet is opposite to and away from the flow guiding channel.

[0013] In some embodiments, the projected area of ​​the first heat exchange cavity on the lower wall is smaller than the projected area of ​​the second heat exchange cavity on the lower wall.

[0014] In some embodiments, a plurality of turbulence columns are provided in the first heat exchange cavity and the second heat exchange cavity; the turbulence columns extend along the layout direction of the upper wall and the lower wall.

[0015] The present invention relates to a turbine guide vane lower edge cooling structure for cooling the downstream region of the edge plate. The gas collecting chamber collects the cooling gas, reducing its dissipation. Due to the gas collecting chamber, the volume of the heat exchange chamber is relatively reduced, allowing for concentrated heat exchange between the cooling gas and the upper wall, enhancing the cooling effect and improving cooling efficiency. Attached Figure Description

[0016] The above-described features and advantages of the present invention will be better understood after reading the following detailed description of embodiments of the present disclosure in conjunction with the accompanying drawings. In the drawings, components are not necessarily drawn to scale, and components having similar related properties or features may have the same or similar reference numerals. Wherein:

[0017] Figure 1 This is a schematic diagram of the structure of the inner cavity of the lower edge plate;

[0018] Figure 2 This is a schematic diagram of the cooling structure of the lower edge plate of the turbine guide vane, according to some embodiments;

[0019] Figure 3 yes Figure 2 Cross-sectional view of AA;

[0020] Figure 4 yes Figure 2 Cross-sectional view of BB;

[0021] Figure 5 yes Figure 2 Cross-sectional view of CC;

[0022] Figure 6 This is a schematic diagram showing the division of the guide vane edge plate area. Detailed Implementation

[0023] The present invention will now be described in detail with reference to the accompanying drawings and specific embodiments. It should be noted that the aspects described below with reference to the accompanying drawings and specific embodiments are merely exemplary and should not be construed as limiting the scope of protection of the present invention in any way.

[0024] It should be understood that the terms “system,” “device,” “unit,” and / or “module” used herein are one method of distinguishing different components, elements, parts, sections, or assemblies at different levels. However, if other words can achieve the same purpose, they may be replaced by other expressions.

[0025] Figure 1 This is a schematic diagram of the structure of the inner cavity of the lower edge plate. (See diagram below.) Figure 1 As shown, the vertical plate 6 divides the interior of the lower edge plate into a front cavity 5 and a rear cavity 7, correspondingly dividing the lower edge plate into an upstream region 4 and a downstream region 8. Cooling gas is introduced from the front cavity 5 to cool the upstream region 4. The turbine guide vane lower edge plate cooling structure described in this specification is used to cool the downstream region 8 of the lower edge plate.

[0026] The cooling structure of the lower edge plate of the turbine guide vane is described in detail below with reference to the accompanying drawings.

[0027] Figure 2 This is a schematic diagram of the cooling structure of the lower edge plate of the turbine guide vane, according to some embodiments. Figure 3 yes Figure 2 Cross-sectional view of AA. Figure 4 yes Figure 2 Cross-sectional view of BB. Figure 5 yes Figure 2 A cross-sectional view of CC. It should be noted that... Figure 4 and Figure 5 The dashed arrows shown indicate the direction of gas flow.

[0028] like Figure 3 As shown, the lower edge plate includes an upper wall 20 and a lower wall 10, with the upper wall 20 covering the lower wall 10. The upper wall 20 and the lower wall 10 are overlapped along the overlap direction of the upper wall 20 and the lower wall 10 (see [reference]). Figure 3 The upper wall 20 is close to the guide vane body 2, and the lower wall 10 is far away from the guide vane body 2.

[0029] The upper wall 20 and the lower wall 10 cooperate to define a cavity between them. A partition wall 30 is provided within the cavity, dividing it into a gas collecting chamber 201 and a heat exchange chamber. The gas collecting chamber and the heat exchange chamber are arranged overlappingly, with the gas collecting chamber 201 closer to the lower wall 10 and the heat exchange chamber closer to the upper wall 20 along the overlap direction. The gas collecting chamber 201 and the heat exchange chamber are connected by a channel provided on the partition wall 30.

[0030] In some embodiments, such as Figure 3 As shown, the lower wall 10 has a flow channel 101, which communicates with the gas collection chamber 201. Figure 2 As shown, there are multiple flow channels 101. The flow channels 101 penetrate the vertical plate 6, connecting the front cavity 5 and the gas collecting cavity 201, and introducing the cooling gas in the front cavity 5 into the gas collecting cavity 201 along the flow channels 101. The front cavity 5 is located in... Figure 2 The blank area 50 shown. The gas collecting chamber 201 collects the cooling gas introduced from the front chamber 5, reducing the dissipation of this portion of the cooling gas. Due to the setting of the gas collecting chamber 201, the volume of the heat exchange chamber is relatively reduced, which can concentrate the cooling gas to exchange heat with the upper wall 20, enhance the cooling effect, and improve the cooling efficiency.

[0031] In some embodiments, the channel of the partition wall 30 includes a plurality of impact holes 303. Cooling gas collected in the gas collecting chamber 201 can flow to the heat exchange chamber through the plurality of impact holes 303. In some embodiments, due to the better cooling effect of the upstream region 4, the temperature of the region in the downstream region 8 near the upstream region 4 is relatively low, and the temperature of the region in the downstream region 8 far from the upstream region 4 is relatively high. The number of impact holes 303 is along the direction from the downstream region 8 to the upstream region 4 (i.e., along...). Figure 2 The temperature decreases in the Q direction (as shown), meaning the impact holes 303 are densely arranged in areas with relatively high temperatures and sparsely arranged in areas with relatively low temperatures. This provides a stronger cooling effect to the areas with relatively high temperatures, thereby reducing the temperature difference on the lower edge plate surface. The upstream region 4 of the corresponding front cavity 5 is located... Figure 2 The blank area 50 is shown. In some embodiments, a plurality of impact holes 303 provided on the partition wall 30 extend upward to the upper layer wall 20, so that the cooling gas passing through the impact holes 303 impacts the upper layer wall 20, thereby cooling the upper layer wall 20. Specifically, the partition wall 30 portion defining the impact holes 303 is such that the hole wall of the impact holes 303 protrudes upward to the upper layer wall 20. The cooling gas impacts the upper layer wall 20 through the impact holes 303, and the cooling gas blocked by the upper layer wall 20 fills the heat exchange chamber, enhancing the cooling effect on the upper layer wall 20.

[0032] It is necessary to understand that Figure 2 The diagram shows a cross-sectional view of the lower edge cooling structure, with the upper wall 20 in... Figure 3 The overlapping direction shown can cover Figure 2 The diagram shows the first heat exchange chamber 301, the turbulence column 302, the impact hole 303, and the second heat exchange chamber 401. For a description of the first heat exchange chamber 301, the turbulence column 302, the impact hole 303, and the second heat exchange chamber 401, please refer to [reference needed]. Figure 3 , Figure 4 and Figure 5 Related content.

[0033] When using film cooling, the rim plate needs to have film cooling holes. For example... Figure 6 As shown, arranging film cooling holes in the rear throat region 1 increases aerodynamic losses, which is detrimental to turbine efficiency. Furthermore, during engine operation, the cooling gas flowing from the film cooling holes tends to drift towards the lower-pressure suction side 22, resulting in poor film coverage on the downstream region 8. Therefore, in some embodiments, it is necessary to divide the downstream region 8 into zones and configure separate cooling methods. The division of the downstream region 8 can be based on… Figure 6 The process is carried out in the area of ​​the flange shown. Figure 6 The area shown by the diagonal lines is the posterior throat region 1. Figure 6 The blank area shown is the anterior throat region 3. The anterior throat region 3, which is included in the downstream region 8, is divided into sections for film cooling. The posterior throat region 1, which is included in the downstream region 8, is divided into sections for cooling other than film cooling.

[0034] In some embodiments, a partition 40 is provided within the heat exchange chamber, dividing the heat exchange chamber into a first heat exchange chamber 301 and a second heat exchange chamber 401, which are arranged side by side. A small portion of the first heat exchange chamber 301 corresponds to the pre-throat region 3 portion included in the downstream region 8, and a large portion of the first heat exchange chamber 301 corresponds to the post-throat region 1 portion included in the downstream region 8. The second heat exchange chamber 401 corresponds to the post-throat region 1 portion included in the downstream region 8. The partition 40... Figure 3 The overlapping direction shown can cover Figure 2 The gas collecting chamber 201 is shown.

[0035] A portion of the cooling gas entering the gas collecting chamber 201 enters the first heat exchange chamber 301 through the impact hole 303 on the partition wall 30, while the other portion enters the second heat exchange chamber 401 through the impact hole 303 on the partition wall 30. The first heat exchange chamber 301 cools the pressure side 21 of the downstream region 8. The second heat exchange chamber 401 cools the suction side 22 of the downstream region 8.

[0036] In some embodiments, such as Figure 4As shown, the upper wall 20 is provided with film cooling holes 304, which communicate with the first heat exchange chamber 301. The film cooling holes 304 guide the cooling gas in the first heat exchange chamber 301 outward to form a film cooling gas on the surface of the upper wall 20. In some embodiments, the film cooling holes 304 are located on the front side of the first heat exchange chamber 301, and the outlet of the film cooling holes 304 faces the rear side of the first heat exchange chamber 301 away from the upstream region 4. The cooling gas flowing out of the film cooling holes 304 forms an acute angle with the surface of the upper wall 20 and flows towards the rear side of the film cooling holes 304, forming a film cooling gas on the surface of the upper wall 20 behind the outlet of the film cooling holes 304. The "front side" referred to in this specification is the side close to the upstream region 4 along the Q direction (or... Figure 2 The blank area 50 shown is on one side, and the rear side is the side away from the upstream area 4 along the Q direction. The gas film formed on the surface of the upper wall 20 can isolate the high-temperature combustion gas, and because the gas film holes 304 are set close to the upstream area 4, the cooling gas flowing to the rear side of the first heat exchange chamber 301 flows back to the gas film holes 304 on the front side of the first heat exchange chamber 301 and is discharged. This recirculation structure focuses on reducing the temperature of the relatively high rear area in the downstream area 8, reducing the temperature difference between the upstream and downstream of the flange, and reducing local thermal stress.

[0037] In some embodiments, the projected area of ​​the first heat exchange cavity 301 on the lower wall 10 is smaller than the projected area of ​​the second heat exchange cavity 401 on the lower wall 10. This helps to ensure that the surface of the lower edge plate corresponding to the first heat exchange cavity 301 is covered by a gas film, thus isolating the high-temperature combustion gas.

[0038] In some embodiments, such as Figure 2 As shown, the film air hole 304 is located in the front region 3 of the throat of the flange. The film air hole is not arranged in the rear region 1 of the throat to reduce aerodynamic losses.

[0039] In some embodiments, such as Figure 5 As shown, an airflow outlet 402 is provided on the side of the upper wall 20. The airflow outlet 402 is connected to the second heat exchange chamber 401. Cooling gas enters the second heat exchange chamber 401 through the impact hole 303 and then exits through the airflow outlet 402. In some embodiments, multiple airflow outlets 402 are provided on the side of the upper wall 20. In some embodiments, the airflow outlets 402 are opposite to and away from the guide channel 101. By keeping the airflow outlets 402 away from the guide channel 101, the cooling gas entering through the guide channel 101 can flow along the longest path in the second heat exchange chamber 401, which is beneficial to ensuring the cooling effect of the second heat exchange chamber 401. The cooling gas exits from the airflow outlet 402 on the side of the second heat exchange chamber 401, which can prevent the combustion gas from backflowing from the gap between the front and rear adjacent edge plates. At the same time, the cooling gas exiting from the airflow outlet 402 can play a certain role in cooling the adjacent edge plates.

[0040] In some embodiments, a plurality of turbulence-inducing columns 302 are disposed within the first heat exchange cavity 301 and the second heat exchange cavity 401, extending along the layout direction of the upper wall 20 and the lower wall 10. Cooling gas is agitated by the turbulence-inducing columns 302 as it flows within the first heat exchange cavity 301 and the second heat exchange cavity 401 to enhance turbulent heat transfer. In some embodiments, the plurality of turbulence-inducing columns 302 are arranged at intervals within the first heat exchange cavity 301 and the second heat exchange cavity 401. In some embodiments, the plurality of turbulence-inducing columns 302 are evenly spaced within the first heat exchange cavity 301 or the second heat exchange cavity 401. In other embodiments, the distribution density of the plurality of turbulence-inducing columns 302 is adjusted according to heat transfer requirements. For example, in regions with relatively high temperatures, the heat transfer requirements are greater, corresponding to a denser distribution of the turbulence-inducing columns 302; in regions with relatively low temperatures, the heat transfer requirements are smaller, corresponding to a sparser distribution of the turbulence-inducing columns 302. In some embodiments, the turbulence-inducing columns 302 can be replaced by turbulence-inducing ribs.

[0041] The basic concepts have been described above. It is clear that the detailed disclosure above is merely illustrative and does not constitute a limitation of this specification, especially for those skilled in the art. Furthermore, unless expressly stated in the claims, the order of elements and sequences, the use of numbers and letters, or other names in this specification are not intended to limit the order of the processes and methods described herein. Although various examples of currently considered useful embodiments of the invention have been discussed in the foregoing disclosure, it should be understood that such details are for illustrative purposes only, and the appended claims are not limited to the disclosed embodiments. Rather, the claims are intended to cover all modifications and equivalent combinations that conform to the substance and scope of the embodiments described herein.

Claims

1. A cooling structure for the lower edge plate of a turbine guide vane, characterized in that, The lower edge plate includes an upper wall and a lower wall, the upper wall covering the lower wall and defining a cavity between the upper wall and the lower wall; A partition wall is provided inside the cavity, which divides the cavity into a gas collection chamber and a heat exchange chamber. The gas collection chamber and the heat exchange chamber are arranged overlappingly, with the gas collection chamber close to the lower wall and the heat exchange chamber close to the upper wall. The gas collection chamber and the heat exchange chamber are connected by a channel provided on the partition wall.

2. The cooling structure according to claim 1, characterized in that, The lower wall has a flow channel, which is connected to the gas collection chamber.

3. The cooling structure according to claim 2, characterized in that, The lower edge plate includes a vertical plate and a front cavity, and the flow channel passes through the vertical plate, connecting the front cavity and the gas collection cavity.

4. The cooling structure according to claim 1, characterized in that, A partition is provided inside the heat exchange chamber, which divides the heat exchange chamber into a first heat exchange chamber and a second heat exchange chamber, which are arranged side by side.

5. The cooling structure according to claim 4, characterized in that, The upper wall is provided with air film pores, which are connected to the first heat exchange chamber. The air film pores are used to form an air film on the surface of the upper wall.

6. The cooling structure according to claim 5, characterized in that, The air film pores are located in the anterior region of the throat of the edge plate.

7. The cooling structure according to claim 4, characterized in that, An airflow outlet is provided on the side of the upper wall, and the airflow outlet is connected to the second heat exchange chamber; The lower wall has a flow channel that is connected to the air collection chamber, and the air outlet is opposite to and away from the flow channel.

8. The cooling structure according to claim 4, characterized in that, The projected area of ​​the first heat exchange cavity on the lower wall is smaller than the projected area of ​​the second heat exchange cavity on the lower wall.

9. The cooling structure according to claim 4, characterized in that, Multiple turbulence columns are provided inside the first heat exchange cavity and the second heat exchange cavity; The turbulence-disrupting columns extend along the layout direction of the upper and lower walls.

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