Turbine blade and spoiler structure for a turbine blade and gas turbine

Abstract

The application discloses a turbine blade, a turbulating rib structure for the turbine blade and a gas turbine. The turbulating structure for the turbine blade comprises at least two rows of turbulating ribs arranged on a cooling channel in the blade, each row comprises a plurality of turbulating ribs, the inclination directions of the plurality of turbulating ribs in each row are the same, and the turbulating ribs in one row are staggered with any adjacent row of turbulating ribs. The turbulating structure for the turbine blade provided by the application has the advantages that the heat exchange intensity of the turbulating ribs is ensured, and the heat exchange is more uniform.

Description

TECHNICAL FIELD

[0001] The present application relates to the field of gas turbine cooling technology, and in particular to a turbine blade, a turbulence structure for the turbine blade and a gas turbine. BACKGROUND

[0002] The gas turbine has the characteristics of light weight, small size, large single machine power, fast start, less pollution, high thermal efficiency and good economy. From the simple cycle mode of the gas turbine, it can be known that the specific power and performance can be improved by increasing the initial temperature of the gas. The turbine blade is located in a high-temperature, complex stress and harsh working environment, so whether the turbine blade can work safely and reliably is crucial to the operation of the engine. The performance indicators of the blade have become important indicators for measuring the development level of the engine, especially the ability of the turbine blade to withstand high temperature. At present, the front temperature of the gas turbine turbine blade has already exceeded the bearing temperature of the material. To ensure that the blade can work safely and reliably, a cooling method with stronger cooling capacity is adopted to reduce the temperature of the blade.

[0003] The gas turbine turbine blade works in a harsh environment of high temperature and high speed, and the design technology of the internal cooling structure of the turbine blade is one of the key technologies to ensure the safe operation of the gas turbine turbine blade. In the related art, the turbulence ribs inside the gas turbine turbine blade are usually inclined ribs with consistent inclination directions, and the heat exchange intensity is inconsistent. The end close to the gas flow direction is a strong heat exchange area, and the other end is a weak heat exchange area, causing uneven heat exchange. SUMMARY

[0004] The present application aims to at least partially solve one of the technical problems in the related art.

[0005] To this end, an embodiment of the present application proposes a turbulence structure for a turbine blade, which has the advantages of ensuring the heat exchange intensity of the turbulence ribs and making the heat exchange more uniform.

[0006] According to the turbulence structure for a turbine blade of the embodiment of the present application, the turbulence structure for a turbine blade includes at least two rows of turbulence ribs arranged on the internal cooling channel of the blade, each row including a plurality of turbulence ribs, the inclination directions of the plurality of turbulence ribs of each row being the same, and the turbulence ribs of one row being staggered with the turbulence ribs of any adjacent row.

[0007] The turbulence structure for a turbine blade according to the embodiment of the present application has the advantages of ensuring the heat exchange intensity of the turbulence ribs and making the heat exchange more uniform.

[0008] In some embodiments, the spacing between any one of the turbulence ribs in one row and the two turbulence ribs adjacent to the turbulence rib in the adjacent row is equal.

[0009] In some embodiments, the staggered distance of any two adjacent rows of the turbulence ribs in the column direction is greater than or equal to 0.

[0010] In some embodiments, the rib spacing between any two adjacent turbulence ribs of each row is p, and the rib spacing between the turbulence ribs of each row and the adjacent turbulence ribs of an adjacent row is p / 2.

[0011] In some embodiments, the height of the turbulence ribs beyond the surface of the cooling channel is e, and p / e<10.

[0012] In some embodiments, the turbulence ribs are distributed symmetrically along the center line of the cooling channel.

[0013] In some embodiments, the turbulence ribs have an inclination angle a, 30°<a<90°.

[0014] In some embodiments, the cross-sectional shape of the turbulence ribs is a parallelogram.

[0015] According to the turbine blade of the embodiment of the present application, the turbulence structure is arranged in the cooling channel of the blade body.

[0016] According to the gas turbine of the embodiment of the present application, the turbulence structure is arranged in the cooling channel of the turbine blade. BRIEF DESCRIPTION OF DRAWINGS

[0017] Figure 1 is a cross-sectional view of the turbulence structure for a turbine blade according to an embodiment of the present application.

[0018] Figure 2 is a cross-sectional view of the turbulence structure for a turbine blade according to another embodiment of the present application.

[0019] Reference signs: 1, turbulence rib. DETAILED DESCRIPTION

[0020] Embodiments of the present application are described in detail below, examples of which are shown in the accompanying drawings. The embodiments described below by reference to the drawings are exemplary and are intended to explain the present application, and should not be understood as limiting the present application.

[0021] According to the turbulence structure for a turbine blade of the embodiment of the present application, as Figure 1 and Figure 2As shown, the turbulence structure for the turbine blade includes at least two rows of turbulence ribs 1 arranged on the internal cooling channel of the blade, each row including a plurality of turbulence ribs 1, the plurality of turbulence ribs 1 in each row have the same tilting direction, and one row of turbulence ribs 1 is staggered with any adjacent row of turbulence ribs 1. The internal turbulence rib 1 structure in the related art is generally a slanted rib with the same tilting direction, which causes inconsistent heat exchange intensity along the tilting direction of the slanted rib, the end of the slanted rib close to the airflow incoming direction is a strong heat exchange area, and the other end of the slanted rib is a weak heat exchange area, which causes uneven heat exchange of the slanted rib and local overheating. The turbulence structure is arranged on the internal cooling channel of the blade, and the turbulence structure includes at least two rows of turbulence ribs 1, the two rows of turbulence ribs 1 are staggered with each other and have opposite tilting directions, the strong heat exchange area of one row of turbulence ribs 1 close to the airflow incoming direction cooperates with the weak heat exchange area of the other row of turbulence ribs 1 with opposite tilting direction, which makes the heat exchange coefficient in the cooling channel of the blade more uniform, ensures the heat exchange intensity of the turbulence structure, avoids local overheating of the component, and further improves the heat exchange effect of the turbulence rib 1. Increasing the number of rows of turbulence ribs 1 in the cooling channel can increase the number of turbulence ribs 1, increase the heat exchange area, and improve the heat exchange effect.

[0022] The turbulence structure for the turbine blade according to the embodiments of the present application has the advantages of ensuring the heat exchange intensity of the turbulence rib and making the heat exchange more uniform.

[0023] In some embodiments, as shown in Figure 1 and Figure 2 Any one turbulence rib 1 in one row is located at the same spacing as the two turbulence ribs 1 adjacent to the turbulence rib 1 in the adjacent row.

[0024] Specifically, one turbulence rib 1 is located between the two turbulence ribs 1 adjacent to it in the adjacent row in the column direction, and the turbulence rib 1 is located at the same spacing as the two turbulence ribs 1 in the adjacent row, which can uniformly heat and avoid local overheating caused by heat exchange dead angles.

[0025] In some embodiments, as shown in Figure 1 and Figure 2 The staggered distance of any two adjacent rows of turbulence ribs 1 in the column direction is greater than or equal to 0.

[0026] Specifically, the staggered distance refers to the distance at which one row of turbulence ribs 1 coincides with the adjacent row of turbulence ribs 1 in the column direction, the greater the staggered distance, the greater the area at which one row of turbulence ribs 1 coincides with the adjacent row of turbulence ribs 1 in the column direction, and when the staggered distance is the largest, the two rows of turbulence ribs 1 completely overlap and are spaced apart from each other. The turbulence rib 1 not only can cause airflow disturbance phenomenon, but also can cause part of the airflow to flow into the downstream from the airflow channel between the two turbulence ribs 1 adjacent in the column direction, which can accelerate the airflow flow and destroy the upstream boundary layer due to the narrow airflow channel between the turbulence ribs 1.

[0027] In some embodiments, as shown in Figure 1 and Figure 2 , the rib spacing between any two adjacent ribs 1 of each row is p, and the rib spacing between each row of ribs 1 and the adjacent ribs 1 of the adjacent row is p / 2.

[0028] Specifically, the plurality of ribs 1 of each row are equally spaced, the rib spacing between any two adjacent ribs 1 is p, and the distance between the end of the adjacent rib 1 of each row adjacent to the gas flow direction and the end of the adjacent rib 1 of the adjacent row adjacent to the gas flow direction is p / 2.

[0029] In some embodiments, as shown in Figure 1 and Figure 2 , the height of the rib 1 above the surface of the cooling channel is e, and p / e<10.

[0030] Specifically, when the ratio of the rib spacing p of each row of ribs 1 to the height e of the rib 1 above the surface of the cooling channel is less than 10, the cooling effect of the rib 1 is better, which can ensure the heat exchange intensity.

[0031] In some embodiments, as shown in Figure 1 and Figure 2 , the ribs 1 are centrally symmetrically distributed along the center line of the cooling channel.

[0032] Specifically, when there are three rows of ribs 1 in the cooling channel, the center line of the cooling channel coincides with the center line of one row of ribs 1, and the other two rows of ribs 1 are located on both sides of the center line of the cooling channel. The ribs 1 are centrally symmetric about the center line of the cooling channel, which reduces the processing difficulty and facilitates the foolproof design of the blade.

[0033] In some embodiments, as shown in Figure 2 , the inclination angle of the rib 1 is a, and 30°<a<90°.

[0034] Specifically, the inclination angle of the rib 1 is the angle between the end of the rib 1 adjacent to the gas flow direction and the gas flow direction. When the rib 1 is completely perpendicular to the gas flow direction, the inclination angle of the rib 1 is defined as 90°, and at this time the gas flow in the blade cooling channel is blocked by the rib 1 and it is difficult to pass through. When the inclination angle of the rib 1 is 30°, the rib 1 has too poor a flow disturbance effect to achieve the purpose of flow disturbance. Preferably, the inclination angle of the rib 1 is 45°.

[0035] In some embodiments, as shown in Figure 1 and Figure 2 , the cross-sectional shape of the rib 1 is a parallelogram.

[0036] Specifically, when the cross-sectional shape of the spoiler rib 1 is a parallelogram, the spoiler rib 1 has a good disturbance effect on the airflow, the spoiler rib 1 has a good fixing effect on the blade internal cooling channel, and the boundary layer on the wall surface of the parallelogram facing the cooling airflow flow direction is thin, the heat exchange capacity is strong, the parallelogram spoiler can better strengthen the heat exchange, and the flow resistance change is small.

[0037] According to the turbine blade of the embodiment of the present application, the spoiler structure is arranged in the cooling channel of the blade body.

[0038] The technical advantages of the turbine blade according to the embodiment of the present application are the same as those of the spoiler structure for the turbine blade described above, and will not be repeated here.

[0039] According to the gas turbine of the embodiment of the present application, the spoiler structure is arranged in the cooling channel of the turbine blade.

[0040] The technical advantages of the gas turbine according to the embodiment of the present application are the same as those of the spoiler structure for the turbine blade described above, and will not be repeated here.

[0041] In the description of the present application, it should be understood that the orientations or positional relationships indicated by the terms "center", "longitudinal", "transverse", "length", "width", "thickness", "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", "clockwise", "counterclockwise", "axial", "radial", "circumferential" are based on the orientations or positional relationships shown in the drawings, and are only for the convenience of describing the present application and simplifying the description, and therefore cannot be understood as indicating or implying that the devices or elements indicated must have a particular orientation, be constructed and operated in a particular orientation, and therefore cannot be understood as limiting the present application.

[0042] In addition, the terms "first" and "second" are only for descriptive purposes, and cannot be understood as indicating or implying relative importance or implicitly indicating the number of the indicated technical features. Therefore, the features defined with "first" and "second" can explicitly or implicitly include at least one of the features. In the description of the present application, the meaning of "a plurality of" is at least two, such as two, three, etc., unless otherwise specifically limited.

[0043] In the present application, unless specifically defined otherwise, the terms "mounting", "connected", "connecting", "fixed", "fixedly connected", "connection", "fixedly connected", "connected", "fixed", and the like should be construed broadly, for example, can be fixed connection, can be detachable connection, or integral; can be mechanical connection, can be electrical connection or communication with each other; can be directly connected, or indirectly connected through an intermediate medium, can be the internal communication of two elements or the interaction relationship between two elements, unless otherwise specifically defined. For those skilled in the art, the specific meaning of the above terms in the present application can be understood according to the specific circumstances.

[0044] In the present application, unless specifically defined otherwise, the first feature is "on" or "under" the second feature. The first and second features can be in direct contact, or the first and second features can be in indirect contact through an intermediate medium. Moreover, the first feature "above", "over" and "on" the second feature can be that the first feature is directly above or obliquely above the second feature, or only indicates that the horizontal height of the first feature is higher than that of the second feature. The first feature "below", "under" and "under" the second feature can be that the first feature is directly below or obliquely below the second feature, or only indicates that the horizontal height of the first feature is less than that of the second feature.

[0045] In the present application, the terms "one embodiment", "some embodiments", "example", "specific example", or "some examples" mean that the specific features, structures, materials or characteristics described in connection with the embodiment or example are included in at least one embodiment or example of the present application. In the present specification, the illustrative description of the above terms does not necessarily refer to the same embodiment or example. Moreover, the specific features, structures, materials or characteristics described can be combined in any appropriate manner in any one or more embodiments or examples. In addition, different embodiments or examples described in the specification and the features of different embodiments or examples can be combined and combined by those skilled in the art without contradiction.

[0046] Although the embodiments of the present application have been shown and described above, it should be understood that the above embodiments are exemplary and should not be construed as limiting the present application. Changes, modifications, replacements and variations of the above embodiments made by those skilled in the art are within the scope of the present application.

Claims

1. A flow-disrupting structure for turbine blades, characterized in that, include: At least two rows of baffle ribs are provided on the cooling channel inside the blade, each row includes multiple baffle ribs, the multiple baffle ribs in each row have the same inclination direction, and one row of baffle ribs is staggered with any adjacent row of baffle ribs. There are three rows of baffles in the cooling channel. The center line of the cooling channel coincides with the center line of one row of baffles. The other two rows of baffles are located on both sides of the center line of the cooling channel. The baffles are symmetrical about the center line of the cooling channel. The distance between any one of the deflection ribs in a row and the two deflection ribs adjacent to the deflection rib in the next row is equal. The stagger distance between any two adjacent rows of the deflector ribs in the column direction is greater than or equal to 0.

2. The turbulence-disrupting structure for turbine blades according to claim 1, characterized in that, The rib spacing between any two adjacent ribs in each row is p, and the rib spacing between the ribs in each row and the adjacent ribs in the next row is p / 2.

3. The turbulence-disrupting structure for turbine blades according to claim 2, characterized in that, The height of the turbulence ribs extending beyond the surface of the cooling channel is e, where p / e < 10.

4. The turbulence-disrupting structure for turbine blades according to claim 1, characterized in that, The tilt angle α of the spoiler rib is 30°. <a<90°。 5. The turbulence-disrupting structure for turbine blades according to claim 1, characterized in that, The cross-sectional shape of the turbulence rib is a parallelogram.

6. A turbine blade, characterized in that, The cooling channel of the blade body is provided with a turbulence structure, which is the turbulence structure as described in any one of claims 1-5.

7. A gas turbine, characterized in that, The turbine blades have a turbulence structure in their cooling channels, and the turbulence structure is as described in any one of claims 1-5.

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