Combined cooling structure with partition plate for turbine blade of gas turbine

Abstract

The invention discloses a combined cooling structure with a partition plate for a turbine blade of a gas turbine, which is characterized in that film holes are formed in the wall surface of a blade body of the turbine blade, a cold air channel is arranged in the blade body of the turbine blade, an impact plate is arranged in the cold air channel, and the impact plate and the wall surface of the blade body are spaced to form an impact cavity; the impact plate is provided with impact holes, partition plates are arranged in the impact cavity and divide the impact cavity into a plurality of impact sub-cavities and hollow cavities in the length direction of the impact cavity, the impact sub-cavities are correspondingly communicated with the impact holes and the air film holes, and the hollow cavities are sealed cavities defined by the partition plates, the impact plate and the wall face of the blade body. According to the turbine blade, the partition plates are arranged in the impact cavity to construct the multiple impact sub-cavities and the hollow cavity, the impact sub-cavities can force impacted cold air to only flow out of the air film holes in the corresponding areas, and therefore the influence of transverse flow on downstream impact cooling is reduced, the hollow cavity is a sealed cavity, no cold air exists in the hollow cavity, and the impact cooling effect is good. The actual space of the impact cavity is reduced, so that the utilization rate of cold air can be improved.

Description

Technical Field

[0001] The present invention relates to the technical field of turbine blade cooling, and in particular to a combined cooling structure with partitions for gas turbine blades. Background Art

[0002] The operating environment temperature of the gas turbine blades is relatively high. In order to ensure that the turbine blade material operates within the allowable temperature range, the blade body adopts a variety of cooling forms. Among them, the combined cooling form of impingement cooling and film cooling is the most commonly used and efficient cooling structure. For example, an impingement bushing is arranged inside the blade body, and film holes are designed on the outer surface of the blade body. The cold air hits the blade body wall through the impingement holes, and then passes through the film holes to form film cooling on the outer surface of the blade body; there is also a double-wall combined cooling form that has received more attention in recent years. The double-wall cooling structure consists of two layers of wall surfaces, the inner wall surface is in contact with the cooling airflow, and the outer wall surface is exposed to a high-temperature environment. The cooling passes through the impingement holes and impacts the downstream spoiler column, thereby enhancing the heat exchange capacity, and finally flows out through the film holes to form an air film on the outer wall surface, which plays a role in heat insulation and cooling. These blade cooling structures all have a combined cooling form of impingement cooling and film cooling, but this combined cooling form of blade impingement and film cooling has a lateral flow effect, that is, the cold air after the upstream impingement does not flow out from the nearest film hole, but flows downstream, which will affect the effect of the lateral downstream impingement cooling. At the same time, the impingement chamber space is large, which affects the utilization rate of the cold air. Summary of the Invention

[0003] The technical problem to be solved by the present invention is that, in response to the defects and shortcomings of the existing technology, a combined cooling structure with baffles for gas turbine turbine blades is proposed. The combined cooling structure with baffles for gas turbine turbine blades is provided with baffles in the impact cavity to construct multiple impact sub-cavities and hollow cavities. The impact sub-cavities can force the cold air after the impact to flow out only from the air film holes in the corresponding areas, thereby reducing the impact of the lateral flow on the downstream impact cooling, and the hollow cavity is a sealed cavity with no cold air in it, so the actual space of the impact cavity is reduced, thereby improving the utilization rate of the cold air.

[0004] An embodiment of the present invention is a combined cooling structure with baffles for gas turbine blades, wherein air film holes are provided on the blade wall of the turbine blade, a cooling air channel is provided in the blade body of the turbine blade, an impact plate is provided in the cooling air channel, and the impact plate and the blade wall are spaced apart to form an impact cavity, the impact plate is provided with impact holes, and a baffle is provided in the impact cavity, the baffle separates the impact cavity into a plurality of impact sub-cavities and hollow cavities in the length direction of the impact cavity, the impact sub-cavities are correspondingly connected to the impact holes and the air film holes, and the hollow cavity is a sealed cavity surrounded by the baffle, the impact plate and the blade wall.

[0005] The embodiment of the present invention is a combined cooling structure with baffles for gas turbine blades, wherein an impact hole is provided on the impact plate, an air film hole is provided on the blade wall, and a baffle is provided in the impact cavity. The baffle separates the impact cavity into a plurality of impact sub-cavities and a hollow cavity in its length direction. The impact sub-cavities are connected to the impact holes and the air film holes, and the hollow cavity is a sealed cavity surrounded by the baffle, the impact plate and the blade wall. Therefore, the plurality of impact sub-cavities separated by the baffle can force the cold air after the impact to flow out only from the air film holes in the corresponding area, thereby reducing the influence of the lateral flow on the downstream impact cooling, and the hollow cavity is a sealed cavity with no cold air in it, so the actual space of the impact cavity is reduced, thereby improving the utilization rate of the cold air.

[0006] In some embodiments, the impingement holes and the film cooling holes are both disposed adjacent to the baffle.

[0007] In some embodiments, the longitudinal section of the hollow cavity is triangular, two sides of the triangle are the two baffles, and the other side is the impact plate, and the two baffles intersect on the blade wall and form a corner of the triangle.

[0008] In some embodiments, the longitudinal section of the impact sub-cavity is trapezoidal, the side of the trapezoid is the partition, the long side of the trapezoid is the blade wall, and the short side is the impact plate.

[0009] In some embodiments, a plurality of the hollow cavities and a plurality of the impact sub-cavities are arranged alternately.

[0010] In some embodiments, the adjacent impact sub-cavities include a first impact sub-cavity and a second impact sub-cavity, and the first partition plate surrounding the first impact sub-cavity and the second partition plate surrounding the second impact sub-cavity form the hollow cavity.

[0011] In some embodiments, the impact holes include multiple columns arranged at intervals along the length direction of the impact plate, each column includes multiple impact holes arranged at intervals in the width direction of the impact plate, and the film holes include multiple columns arranged at intervals in the length direction of the blade wall, each column includes multiple film holes arranged at intervals in the width direction of the blade wall.

[0012] In some embodiments, each of the impact sub-cavities is connected to at least one row of the impact holes and one row of the air film holes.

[0013] In some embodiments, the included angle a between the partition and the blade wall satisfies: 30°≤a≤60°.

[0014] In some embodiments, the partition is a curved plate or a straight plate. BRIEF DESCRIPTION OF THE DRAWINGS

[0015] Figure 1It is an axonometric view of a combined cooling structure with baffles for gas turbine blades according to an embodiment of the present invention.

[0016] Figure 2 It is a longitudinal cross-sectional schematic diagram of a combined cooling structure with baffles for gas turbine blades according to an embodiment of the present invention.

[0017] Figure 3 It is a longitudinal cross-sectional schematic diagram of a combined cooling structure with baffles for gas turbine blades according to another embodiment of the present invention.

[0018] Figure 4 It is a longitudinal cross-sectional schematic diagram of a combined cooling structure with baffles for gas turbine blades according to another embodiment of the present invention.

[0019] Figure 5 This is a schematic structural diagram of a combined cooling structure with baffles for gas turbine blades according to an embodiment of the present invention, wherein the blade body wall is schematically represented as the peripheral wall of the turbine blade.

[0020] Reference numerals:

[0021] Impact plate 1, blade wall 2, impact hole 3, air film hole 4, first baffle 5, second baffle 6, impact sub-cavity 7, hollow cavity 8. DETAILED DESCRIPTION

[0022] The embodiments of the present invention are described in detail below, and examples of the embodiments are shown in the accompanying drawings. The embodiments described below with reference to the accompanying drawings are exemplary and intended to be used to explain the present invention, but should not be understood as limiting the present invention.

[0023] like Figure 1-Figure 5 As shown, the turbine blade of an embodiment of the present invention is provided with air film holes 4 on the blade wall 2 of the turbine blade, the cooling impact assembly includes an impact plate 1 and the blade wall 2, a cold air channel is provided in the blade of the turbine blade, an impact plate 1 is provided in the cold air channel, the blade wall 2 and the impact plate 1 are separated to form an impact cavity, the impact plate 1 is provided with impact holes 3, and a partition is provided in the impact cavity, the partition separates the impact cavity into a plurality of impact sub-cavities 7 and a hollow cavity 8 in its length direction, the impact sub-cavity 7 corresponds to the impact hole 3 and the air film hole 4, and the hollow cavity 8 is a sealed cavity surrounded by the partition, the impact plate 1 and the blade wall 2.

[0024] It can be understood that the present application uses partitions to separate multiple impact sub-cavities 7 in the impact cavity. When the cold air is ejected toward the blade wall 2 through the impact hole 3, the cold air will form air film cooling on the surface of the blade wall 2 after passing through the air film hole 4. Compared with the traditional scheme, the impact sub-cavity 7 will force the cold air after the impact to flow out only from the air film hole 4 in the corresponding area, thereby reducing the impact of lateral flow on downstream impact cooling, and the hollow cavity 8 is a sealed cavity with no cold air in it, so the actual space of the impact cavity is reduced, which is conducive to improving the utilization rate of the cold air.

[0025] The turbine blade of the embodiment of the present invention has an impact hole 3 on the impact plate 1, an air film hole 4 on the blade wall 2, and a partition plate in the impact cavity. The partition plate separates the impact cavity into a plurality of impact sub-cavities 7 and a hollow cavity 8 in the length direction. The impact sub-cavities 7 are connected to the impact holes 3 and the air film holes 4, and the hollow cavity 8 is a sealed cavity surrounded by the partition plate, the impact plate 1 and the blade wall 2. Therefore, the multiple impact sub-cavities 7 separated by the partition plate can force the cold air after the impact to flow out only from the air film holes 4 in the corresponding area, thereby reducing the influence of the lateral flow on the downstream impact cooling, and the hollow cavity 8 is a sealed cavity. There is no cold air in it, so the actual space of the impact cavity is reduced, thereby improving the utilization rate of the cold air.

[0026] In addition, it is understandable that the structural design of the partition increases the heat exchange area, and the heat of the blade wall 2 can be conducted out through the partition, and then the heat can be quickly discharged through convection heat exchange with the cold fluid, thereby improving the heat exchange efficiency.

[0027] Furthermore, the baffles can also serve as reinforcement plates to support the blade structure, enhancing the structural strength of the turbine blade. At the same time, the baffles maintain the impact distance between the impact plate 1 and the blade wall 2, preventing contact between the impact plate 1 and the blade wall 2 due to the impact force.

[0028] In addition, the partition can also serve as a guide plate to achieve a rectifying effect and be used to adjust the fluid flow path. Different impact chambers can be divided according to design requirements. For example, the impact holes 3 and the air film holes 4 in the impact chamber can be one-to-one, one-to-many, many-to-one, or many-to-many, thereby improving the flexibility of the design.

[0029] It should be noted that the blade wall surface 2 in this application can be a peripheral plate or top plate of the outer wall of a turbine blade. For example, the blade wall surface 2 can be the top plate of the blade, with the impact plate 1 spaced apart on the inner side of the top plate. Cold air from below impinges on the cooling plate, forming a cooling air film on the top plate to cool the top plate. It is understood that the blade wall surface 2 can also be other side walls of the blade, depending on the specific cooling requirements, which is not limited here.

[0030] For example, Figure 5As shown, the blade wall 2 is the peripheral plate of the turbine blade, and the impact plate 1 is vertically arranged on the inner side of the blade wall 2. After the cold air impacts from the inside to the outside, a cooling air film is formed on the peripheral wall to cool the blade.

[0031] In some embodiments, as Figure 1 As shown, the impact hole 3 and the air film hole 4 are both arranged adjacent to the partition plate. Thus, the partition plate can guide the cold air after the impact toward the air film hole 4, thereby improving the air film cooling effect.

[0032] In some embodiments, as Figure 1-Figure 3 As shown, the longitudinal cross-section of the hollow cavity 8 is triangular, with two baffles on two sides and the impingement plate 1 on the other side. The two baffles intersect on the blade wall 2 to form a corner of the triangle. The advantage of this design is that the connection area between the hollow cavity 8 and the blade wall 2 is minimized. Because the hollow cavity 8 does not contain cooling air, it does not affect the heat transfer of the blade wall 2. At the same time, the hollow cavity 8 occupies part of the impingement cavity space, which allows the limited cooling air to be more concentrated on the blade wall 2, thereby cooling the blade wall 2 more effectively.

[0033] Preferably, if Figure 2 As shown, the longitudinal section of the impact sub-cavity 7 is trapezoidal, the side of the trapezoid is a partition, the long side of the trapezoid is the blade wall 2, and the short side is the impact plate 1, which can also make the limited amount of cooling air more concentrated on the blade wall 2, and cool the blade wall 2 more effectively.

[0034] like Figure 1 As shown, multiple hollow cavities 8 are alternately arranged with multiple impact sub-cavities 7. Thus, on the one hand, the hollow cavities 8 and adjacent impact sub-cavities 7 can share a partition plate, thereby saving costs, and on the other hand, the arrangement of the impact holes 3 and the air film holes 4 is more uniform, and the cooling effect is better.

[0035] Specifically, the baffle includes a first baffle 5 and a second baffle 6 that enclose an impact sub-cavity 7, and the first baffle 5 and the second baffle 6 extend obliquely toward the blade wall 2 in a direction away from each other, and the connection ends of the first baffle 5 and the second baffle 6 and the impact plate 1 are spaced apart in the length direction of the impact plate 1, and the impact hole 3 is located at the gap between the first baffle 5 and the second baffle 6. Figure 1 As shown, the impact sub-cavity 7 is a trapezoid that is narrow at the top and wide at the bottom, and the impact hole 3 is located at the top of the trapezoid. The impact cold air can flow along the first partition plate 5 and the second partition plate 6 toward the corresponding air film hole 4 at the same time, and the cooling effect is good.

[0036] Further, if Figure 1As shown, adjacent impact sub-cavities 7 include a first impact sub-cavity 7 and a second impact sub-cavity 7. The first partition 5 enclosing the first impact sub-cavity 7 and the second partition 6 enclosing the second impact sub-cavity 7 form a hollow cavity 8. The partitions corresponding to two adjacent impact sub-cavities 7 can enclose a hollow cavity 8 located between the two, eliminating the need for dedicated partitions for the hollow cavity 8, further saving costs and meeting the requirement for alternating arrangement of impact sub-cavities 7 and hollow cavities 8.

[0037] Preferably, the impact holes 3 include multiple columns arranged at intervals along the length direction of the impact plate 1, each column includes multiple impact holes 3 arranged at intervals in the width direction of the impact plate 1, and the air film holes 4 include multiple columns arranged at intervals in the length direction of the blade wall 2, each column includes multiple air film holes 4 arranged at intervals in the width direction of the blade wall 2.

[0038] Furthermore, each impact sub-cavity 7 is connected to at least one row of impact holes 3 and one row of air film holes 4. In other words, the impact holes 3 and air film holes 4 connected to each impact sub-cavity 7 are not limited to one row. Figure 2 As shown, one impact sub-cavity 7 is connected to one row of impact holes 3 and one row of air film holes 4. Figure 3 As shown, one impact sub-cavity 7 is connected to one row of impact holes 3 and two rows of air film holes 4. After the cold air is impacted, it flows out from different air film holes 4. The specific design can be flexibly based on the needs to improve the rectification effect.

[0039] In some embodiments, the angle a between the baffle and the blade wall 2 satisfies the following: 30°≤a≤60°. For example, a can be 30°, 45°, and 60°. It is understood that properly setting the angle facilitates better guidance of the cold air after the impact, thereby improving the cooling effect. For example, when the angle between the baffle and the blade wall 2 is too large, the tops of adjacent baffles are far apart, and the impact hole 3 located between them is also far away from the baffle, which is not conducive to the rapid guidance of the cold air. When the angle between the baffle is too small, the impact sub-cavity 7 may be too small, and the cooling efficiency may not be improved.

[0040] Optionally, the partition is a curved plate. That is, the partition can be designed as a straight plate or a curved plate according to the requirements, such as Figure 4 As shown, the curved partition can further increase the heat exchange area and further compress the volume of the impact sub-cavity 7, so that the limited amount of cold air is more concentrated on the blade wall 2, thereby cooling the blade wall 2 more effectively.

[0041] Optionally, the partition is a straight plate or a structure of other shapes, as long as it can meet the construction of the impact sub-cavity and achieve the effect of blocking the cross flow.

[0042] In the description of the present invention, it should be understood that the terms "center", "longitudinal", "lateral", "length", "width", "thickness", "up", "down", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inside", "outside", "clockwise", "counterclockwise", "axial", "radial", "circumferential" and the like to indicate orientations or positional relationships based on the orientations or positional relationships shown in the accompanying drawings, and are only for the convenience of describing the present invention and simplifying the description, rather than indicating or implying that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and therefore should not be understood as limiting the present invention.

[0043] Furthermore, the terms "first" and "second" are used for descriptive purposes only and should not be construed as indicating or implying relative importance or implicitly specifying the number of the technical features being referred to. Thus, a feature defined as "first" or "second" may explicitly or implicitly include at least one such feature. In the description of the present invention, "plurality" means at least two, such as two, three, etc., unless otherwise specifically defined.

[0044] In the present invention, unless otherwise specified or limited, the terms "installed," "connected," "connect," "fixed," etc. should be understood in a broad sense. For example, they can refer to fixed connection, detachable connection, or integration; mechanical connection, electrical connection, or communication; direct connection or indirect connection through an intermediate medium; internal communication between two elements or interaction between two elements, unless otherwise specified. Those skilled in the art will understand the specific meanings of the above terms in the present invention based on specific circumstances.

[0045] In the present invention, unless otherwise expressly specified or limited, when a first feature is "above" or "below" a second feature, it may mean that the first and second features are in direct contact, or that the first and second features are in indirect contact through an intermediary. Furthermore, when a first feature is "above," "above," or "above" a second feature, it may mean that the first feature is directly above or diagonally above the second feature, or simply means that the first feature is at a higher level than the second feature. When a first feature is "below," "below," or "below" a second feature, it may mean that the first feature is directly below or diagonally below the second feature, or simply means that the first feature is at a lower level than the second feature.

[0046] In the present invention, the terms "one embodiment", "some embodiments", "examples", "specific examples", or "some examples" mean that the specific features, structures, materials or characteristics described in conjunction with the embodiment or example are included in at least one embodiment or example of the present invention. In this specification, the schematic expressions of the above terms do not necessarily refer to the same embodiment or example. Moreover, the specific features, structures, materials or characteristics described can be combined in any one or more embodiments or examples in a suitable manner. In addition, those skilled in the art can combine and combine different embodiments or examples described in this specification and the features of different embodiments or examples without contradiction.

[0047] Although the embodiments of the present invention have been shown and described above, it will be understood that the above embodiments are illustrative and are not to be construed as limitations on the present invention. A person skilled in the art may change, modify, replace and modify the above embodiments within the scope of the present invention.

Claims

1. A cooling structure with a baffle for a gas turbine blade, characterized in that: An air film hole is provided on the blade wall of the turbine blade, a cooling air channel is provided in the blade body of the turbine blade, an impact plate is provided in the cooling air channel, and the impact plate and the blade wall are separated to form an impact cavity, an impact hole is provided on the impact plate, and a partition is provided in the impact cavity, and the partition separates the impact cavity into a plurality of impact sub-cavities and hollow cavities in the length direction of the impact cavity, and the impact sub-cavities are connected to the impact holes and the air film holes correspondingly, and the hollow cavity is a sealed cavity surrounded by the partition, the impact plate and the blade wall.

2. The combined cooling structure with baffles for gas turbine blades according to claim 1, characterized in that: The impingement holes and the film cooling holes are both arranged adjacent to the partition plate.

3. The combined cooling structure with baffles for gas turbine blades according to claim 1, characterized in that: The longitudinal section of the hollow cavity is triangular, two sides of the triangle are the two partitions, and the other side is the impact plate. The two partitions intersect on the wall surface of the blade and form a corner of the triangle.

4. The combined cooling structure with baffles for gas turbine blades according to claim 3, characterized in that: The longitudinal section of the impact sub-cavity is trapezoidal, the side of the trapezoid is the partition, the long side of the trapezoid is the blade wall, and the short side is the impact plate.

5. The combined cooling structure with baffles for gas turbine blades according to claim 4, characterized in that: The plurality of hollow cavities and the plurality of impact sub-cavities are arranged alternately.

6. The combined cooling structure with baffles for gas turbine blades according to claim 5, characterized in that: The adjacent impact sub-cavities include a first impact sub-cavity and a second impact sub-cavity, and the first partition plate surrounding the first impact sub-cavity and the second partition plate surrounding the second impact sub-cavity form the hollow cavity.

7. The combined cooling structure with baffles for gas turbine blades according to claim 1, characterized in that: The impact holes include multiple columns arranged at intervals along the length direction of the impact plate, and each column includes multiple impact holes arranged at intervals in the width direction of the impact plate. The film holes include multiple columns arranged at intervals in the length direction of the blade wall, and each column includes multiple film holes arranged at intervals in the width direction of the blade wall.

8. The combined cooling structure with baffles for gas turbine blades according to claim 7, characterized in that: Each of the impact sub-cavities is correspondingly connected to at least one row of the impact holes and one row of the air film holes.

9. The combined cooling structure with baffles for gas turbine blades according to claim 2, characterized in that: The included angle a between the partition and the blade wall satisfies: 30°≤a≤60°.

10. The combined cooling structure with baffles for gas turbine blades according to claim 1, characterized in that: The partition is a curved plate or a straight plate.

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