Diaphragm with cooling structure, cooling channel and turbine blade

Abstract

This invention provides a baffle plate, a cooling channel, and turbine blades with a cooling structure, including a baffle plate body with multiple recesses or slits. The recesses and slits all originate from the lower edge of the baffle plate body and extend towards the upper edge. The elongated recesses and slits on the baffle plate of this invention can discharge the low-speed eddies generated near the bottom of the baffle plate by the turbulence ribs on the end wall, and interact with the channel flow to generate a strong near-wall secondary flow. This not only improves the convective heat transfer performance on the end wall but also enhances the heat transfer capacity of the baffle plate wall, thus improving the overall heat exchange capacity of the cooling channel.

Description

Technical Field

[0001] This invention relates to the field of cooling technology for high-temperature components of gas turbines or aero engines, specifically to a partition, cooling channel, and turbine blade with a cooling structure, particularly a partition, internal cooling channel, and turbine blade with an inclined elongated recess or slit. Background Technology

[0002] Increasing the turbine inlet gas temperature and pressure ratio is a major trend in improving the thermal efficiency of aero-engines and gas turbines. Therefore, there is an urgent need for more efficient and advanced cooling technologies to ensure the reliable operation of gas turbine blades. Since cooling air must be drawn from the compressor, enhanced cooling technology means a reduction in the amount of cooling fluid used, which is beneficial for improving the overall efficiency of aero-engines and gas turbines.

[0003] Existing turbine blades typically have a hollow structure and multiple internal cooling channels, which are defined by the pressure-side and suction-side walls of the turbine blade and baffles. Baffles are provided on the inner sides of the pressure-side and suction-side walls within the cooling channels, allowing the cooling fluid to flow within these channels and enhance the cooling of the turbine blades.

[0004] The current problem is that when the V-shaped turbulence ribs are tilted in the same direction as the cooling fluid flow, low-speed vortices accumulate on both sides of the channel (at the junction with the baffle), creating a low heat transfer zone. This accumulation of low-speed vortices and low heat transfer not only increases flow losses but also limits the heat transfer capacity of the cooling channel.

[0005] To further enhance the internal cooling performance of turbine blades, recesses are typically added to the inner wall of the pressure or suction side of the blade to enhance near-wall turbulence and heat transfer, as disclosed in the applicant's prior patent, CN108167026B, which describes a partition with recesses and an internal cooling channel for turbine blades. However, the walls of aero-engine turbine blades are typically very thin, and adding recesses to the wall significantly impacts structural strength. Furthermore, improvements to the cooling structure should not increase the blade's weight. Therefore, this invention proposes a cooling method that improves the heat transfer performance of the turbulence channel without significantly increasing the blade's weight or affecting the channel's structural strength. Summary of the Invention

[0006] In view of the deficiencies in the prior art, the purpose of this invention is to provide a baffle, a cooling channel and a turbine blade with a cooling structure.

[0007] According to the present invention, a partition with a cooling structure includes a partition body, wherein the partition body is provided with a plurality of recesses or a plurality of slits.

[0008] Both the recess and the slit originate from the lower edge of the partition body and extend toward the upper edge of the partition body.

[0009] Preferably, the plurality of the recesses or slits are arranged in a row at an angle on the partition body, with the angle facing the flow direction.

[0010] Preferably, the depth-to-width ratio of the recess is 0-10.

[0011] Preferably, a plurality of the recesses are provided on two or one of the sidewalls of the partition body.

[0012] Preferably, the depth of the recess is less than the thickness of the partition body.

[0013] Preferably, the depth of the slit is equal to the thickness of the partition body.

[0014] According to the present invention, a cooling channel is disposed inside a turbine blade, the cooling channel being defined by the inner end wall of the turbine blade and the baffle having a cooling structure.

[0015] Preferably, multiple baffles are arranged in parallel on the end wall, so that the cooling channel has multiple channels.

[0016] Preferably, one or more turbulence ribs are provided on the inner end wall of the turbine blade, and the recesses or slits are provided on the side of the turbulence ribs in a one-to-one correspondence.

[0017] The turbine blade provided by the present invention includes a baffle with a cooling structure and a cooling channel. The baffles define the end wall of the turbine blade to form a cooling channel, and the recesses or slits on the baffle bodies are correspondingly provided on the side of the turbulence ribs on the end wall.

[0018] Compared with the prior art, the present invention has the following beneficial effects: 1. The present invention provides multiple strip-shaped recesses or slits on the partition plate. The recesses on the side wall of the partition plate will generate a spiral secondary flow near the wall, which enhances the turbulence intensity near the wall and improves the heat exchange capacity of the side wall of the partition plate. Therefore, it improves the overall heat exchange capacity of the cooling channel without significantly increasing the pressure loss of the cooling channel.

[0019] 2. The present invention provides multiple strip-shaped recesses or slits on the partition plate, and the recesses or slits on the side wall of the partition plate help to reduce the weight of the turbine blades.

[0020] 3. The inclined recesses or slits on the baffle plate help to carry away the low-speed eddies generated by the turbulence ribs on the end wall, thereby enhancing the heat transfer performance on the end wall. At the same time, the heat transfer performance on the baffle plate is also significantly enhanced by the spiral eddies generated by the inclined recesses or slits.

[0021] 4. By setting inclined recesses and slits on the baffle, the present invention reduces the thickness of the flow boundary layer on both sides of the channel by removing the low-speed eddies in the area where the end wall is connected to the baffle, thereby improving the flowability of the cooling channel, improving the heat transfer uniformity of the turbulence rib wall, and enhancing the internal cooling performance of the turbine blades.

[0022] 5. By setting inclined recesses or slits on the baffle, the present invention increases the heat exchange area of ​​the cooling channel and improves the internal cooling performance of the turbine blades; on the other hand, the recesses and slits on the baffle increase the flow cross section of the cooling channel, thereby reducing the flow pressure loss. Attached Figure Description

[0023] Other features, objects, and advantages of the present invention will become more apparent from the following detailed description of non-limiting embodiments with reference to the accompanying drawings: Figure 1 This is a schematic diagram of the cooling channel at one angle in one embodiment of the present invention; Figure 2 This is a schematic diagram of the cooling channel from another angle in one embodiment of the present invention; Figure 3 This is a schematic diagram of the cooling channel at one angle in another embodiment of the present invention; Figure 4 This is a schematic diagram of the cooling channel from another angle in another embodiment of the present invention; The diagram shows: Detailed Implementation

[0024] The present invention will now be described in detail with reference to specific embodiments. These embodiments will help those skilled in the art to further understand the present invention, but do not limit the invention in any way. It should be noted that those skilled in the art can make several changes and improvements without departing from the concept of the present invention. These all fall within the protection scope of the present invention.

[0025] This invention discloses a baffle plate with a cooling structure, a cooling channel, and turbine blades. By setting elongated recesses or slits on the baffle plate, the low-speed vortex generated by the turbulence ribs on the end wall near the bottom of the baffle plate can be discharged and interact with the channel flow to generate a strong near-wall secondary flow. This not only improves the convective heat transfer performance on the end wall but also improves the heat transfer capacity of the baffle plate wall, thus enhancing the overall heat exchange capacity of the cooling channel.

[0026] The partition with a cooling structure provided by the present invention includes a partition body 18, on which a plurality of recesses 24 or a plurality of slits 26 are provided; the recesses 24 and slits 26 all originate from the lower edge of the partition body 18 and extend toward the upper edge of the partition body 18. The elongated recesses 24 or slits 26 are arranged obliquely in a row along the flow direction on the partition body. Compared with other arrangements, a staggered arrangement of the recesses 24 and slits 26 on the partition body 18 can achieve a better heat transfer enhancement effect.

[0027] like Figure 1 , Figure 2 The diagram shows a structural schematic of a partition plate using multiple inclined elongated recesses 24 as a cooling structure; as shown... Figure 3 , Figure 4 The diagram shows a partition structure using multiple inclined slits 26 as a cooling structure. Specifically, the depth-to-width ratio of the recesses 24 is 0-10, and the slits 26 are through-parts of the partition. Multiple recesses 24 are disposed on two or one sidewall of the partition body 18, and multiple inclined slits 26 are disposed within the partition body 18. The depth of the recesses 24 is less than the thickness of the partition body 18; specifically, the depth of the elongated recesses 24 is less than the thickness of the partition body 18 or less than half the thickness of the partition body 18. In a preferred embodiment, the elongated recesses 24 on both sides of the partition body 18 can be through-parts. The depth of the slits 26 is equal to the thickness of the partition body 18.

[0028] According to the present invention, a cooling channel is disposed inside a turbine blade. The cooling channel is defined by the inner end wall 20 of the turbine blade and the baffle with a cooling structure. In a preferred embodiment, multiple baffles are arranged in parallel on the end wall 20, resulting in multiple cooling channels. One or more baffles 22 are provided on the inner end wall 20 of the turbine blade, such that the cooling channel is defined by the baffles 22, the inner end wall 20 of the turbine blade, the baffle body 18, and recesses 24 or slits 26. The recesses 24 or slits 26 are arranged on the sides of the baffles 22 in a one-to-one correspondence.

[0029] The turbine blade provided by the present invention includes a baffle with a cooling structure and a cooling channel. The two ends of the baffle are respectively connected to the end wall 20. The end wall 20 is the internal cooling wall of the turbine blade, and a plurality of turbulence ribs 22 are arranged on the end wall 20. The plurality of baffles divide the internal cooling channel into a plurality of cooling sub-channels, and the recesses 24 or slits 26 on the baffle body 18 are correspondingly provided on the side of the turbulence ribs 22 on the end wall 20.

[0030] Example 1 This embodiment discloses a turbine blade, including an inner wall, a baffle, and a cooling channel. The inner wall includes a pressure side wall and a suction side wall. The two ends of the baffle are connected to the pressure side wall and the suction side wall, respectively. The cooling channel is defined by the baffle, the pressure side wall, and the suction side wall. Multiple baffles divide the cooling channel into multiple cooling channels. One or more baffles 22 are provided on the pressure side wall and / or the suction side wall. The baffle includes a baffle body 18 and multiple recesses 24 or slits 26, which are located on the baffle body 18 near the pressure or suction side of the turbine blade.

[0031] In existing turbine blades, the heat exchange capacity is low because the sidewall of the diaphragm is a smooth sidewall. Furthermore, since the diaphragm is connected to the pressure and suction sidewalls of the turbine blade, heat can be transferred to the cooling fluid through the diaphragm sidewall. However, this invention, by providing multiple inclined recesses 24 or slits 26 on the diaphragm, offers the following advantages over the prior art: 1. The indentation on the side wall of the baffle 18 will generate a spiral secondary flow near the wall, which will enhance the turbulence intensity near the wall and improve the heat transfer capacity of the side wall of the baffle. Therefore, it will improve the overall heat transfer capacity of the cooling channel without significantly increasing the pressure loss of the cooling channel.

[0032] 2. The recesses or slits on the sidewalls of the partition plate 18 help to reduce the weight of the turbine blades.

[0033] 3. The recesses 24 or slits 26 inclined on the partition plate 18 help to carry away the low-speed eddies generated by the turbulence ribs 22 on the end wall 20, thereby enhancing the heat transfer performance on the end wall. At the same time, the heat transfer performance on the partition plate is also significantly enhanced by the spiral eddies generated by the inclined recesses or slits.

[0034] 4. The inclined recesses and slits on the baffle 18 remove the low-speed vortex in the area where the end wall connects to the baffle, reduce the thickness of the flow boundary layer on both sides of the channel, improve the flowability of the cooling channel, improve the heat transfer uniformity of the turbulence rib wall, and enhance the internal cooling performance of the turbine blades.

[0035] 5. The inclined recesses or slits on the baffle plate 18 increase the heat exchange area of ​​the cooling channel and improve the internal cooling performance of the turbine blades; on the other hand, the recesses and slits on the baffle plate increase the flow cross section of the cooling channel, thus reducing the flow pressure loss.

[0036] 6. At the top of the turbine blades, the height of the internal flow channel gradually decreases and the flow accelerates. The recesses and slits on the baffles will play a more significant role in reducing flow drag and enhancing heat transfer.

[0037] Compared with the existing technology that only sets V-shaped ribs, the heat exchange performance of the present invention is improved by more than 20% and the weight is reduced by more than 3%; compared with the solution that sets a recess on the inner wall, the strength of the present application is significantly increased by more than 10%.

[0038] In the description of this application, it should be understood that the terms "upper", "lower", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", etc., indicate the orientation or positional relationship based on the orientation or positional relationship shown in the accompanying drawings. They are only for the convenience of describing this application and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation. Therefore, they should not be construed as limitations on this application.

[0039] Specific embodiments of the present invention have been described above. It should be understood that the present invention is not limited to the specific embodiments described above, and those skilled in the art can make various changes or modifications within the scope of the claims, which do not affect the essence of the present invention. Unless otherwise specified, the embodiments and features described in this application can be arbitrarily combined with each other.

Claims

1. A baffle with a cooling structure for separating internal cooling channels of turbine blades, characterized in that, Includes a partition body (18), on which a plurality of recesses (24) or a plurality of slits (26) are provided. Both the recess (24) and the slit (26) originate from the lower edge of the partition body (18) and extend toward the upper edge of the partition body (18).

2. The partition with a cooling structure according to claim 1, characterized in that, The multiple recesses (24) or slits (26) are arranged in a row at an angle on the partition body (18), with the angle facing the flow direction.

3. The partition with a cooling structure according to claim 1, characterized in that, The depth-to-width ratio of the recess (24) is 0-10.

4. The partition with a cooling structure according to claim 1, characterized in that, The plurality of said recesses (24) are provided on two or one of the sidewalls of the partition body (18).

5. The partition with a cooling structure according to claim 1, characterized in that, The depth of the recess (24) is less than the thickness of the partition body (18).

6. The partition with a cooling structure according to claim 1, characterized in that, The depth of the slit (26) is equal to the thickness of the partition body (18).

7. A cooling channel disposed inside a turbine blade, characterized in that, The cooling channel is defined by the inner end wall (20) of the turbine blade and the partition with a cooling structure as described in any one of claims 1-6.

8. The cooling channel according to claim 7, characterized in that, Multiple baffles are arranged in parallel on the end wall (20), so that the cooling channel has multiple baffles.

9. The cooling channel according to claim 7, characterized in that, One or more turbulence ribs (22) are provided on the inner end wall (20) of the turbine blade, and the recesses (24) or slits (26) are provided on the side of the turbulence ribs (22) in a one-to-one correspondence.

10. A turbine blade, characterized in that, Includes a partition with a cooling structure as described in any one of claims 1-6 and a cooling channel as described in any one of claims 7-9, wherein a plurality of said partitions define the end wall (20) of the turbine blade to form a cooling channel, and a recess (24) or slit (26) on the partition body (18) is correspondingly provided on the side of the turbulence rib (22) on the end wall (20).

Images