A high aspect ratio turbine blade cooling structure with multidimensional turning

Abstract

The application belongs to the field of aero-engine design, and particularly relates to a high-vortex rotor blade cooling structure of a multi-dimensional rotary structure, which comprises a leading edge, a trailing edge, a blade back and a blade basin arranged in a ring shape in the blade; a first back rotary structure and a second back rotary structure are arranged on the inner side of the blade back, and a first basin rotary structure and a second basin rotary structure are arranged on the inner side of the blade basin; part of the cooling gas of the first back rotary structure flows out from the back film hole and the blade tip film hole, and another part of the cooling gas flows out from the leading edge; part of the cooling gas of the second back rotary structure flows out from the blade tip film hole, and another part of the cooling gas flows out from the trailing edge. Through three technical paths of "multi-dimensional rotary structure heat exchange enhancement", "differential distribution of cooling gas quantity to balance temperature" and "multi-path film covering protection", the heat exchange deficiency and temperature unevenness of the existing cooling structure are systematically solved, and the blade cooling efficiency, temperature uniformity and thermal shock resistance are comprehensively improved.

Description

A cooling structure for high-vortex rotor blades with a multi-dimensional rotating structure Technical Field

[0001] This application belongs to the field of aero-engine design, and specifically relates to a cooling structure for high-vortex rotor blades with a multi-dimensional rotating structure. Background Technology

[0002] With the continuous development of aviation technology, higher requirements are being placed on aero engines, especially in terms of thrust. To achieve higher thrust, engines need to have higher turbine inlet temperatures. Increased turbine inlet temperature means improved engine thermal efficiency, which in turn generates greater thrust. As shown in Figure 1, the heat transfer area in the chord region of the turbine rotor blade accounts for 50% to 60% of the total heat transfer area of ​​the blade. The cooling effect in this region plays a decisive role in the thermal protection of the entire blade. Currently, a composite cooling structure of "heat transfer ribs + film cooling holes" is commonly used in this region. Heat transfer ribs increase the surface area of ​​the internal cooling channels, improving convective heat transfer efficiency, while film cooling holes spray cool air onto the blade surface, forming a protective film that isolates the blade from the direct thermal impact of high-temperature combustion gases.

[0003] In existing technologies, as shown in Figure 2, cooling gas is typically drawn from the engine compressor and enters the blade root through the tenon-shaped intake channel. It first flows through a rotating structure formed by baffles, undergoing convective heat transfer with the inner wall and heat exchange ribs during this flow. After cooling the inner wall of the blade, the cool gas continues to flow along the internal channels and finally exits through film cooling holes on the outer wall, cooling the outer surface of the blade. The shortcomings of this approach are: although heat exchange ribs exist inside the blade, the cool gas flow velocity is slow, resulting in insufficient internal heat exchange capacity; furthermore, the uneven heat load distribution on the blade's facet and back sides leads to uneven temperature distribution, necessitating a more refined cooling design.

[0004] Existing cooling structures have limitations in improving cooling capacity, and it is necessary to explore more efficient and refined cooling structures. Summary of the Invention

[0005] To address the aforementioned issues, this application provides a multi-dimensional rotating high-vortex rotor blade cooling structure to solve the problem of insufficient cooling capacity in existing cooling structures.

[0006] The technical solution of this application is: a multi-dimensional rotating high-vortex rotor blade cooling structure, including a leading edge, trailing edge, blade back and blade base arranged in a ring inside the blade;

[0007] The inner side of the leaf back is provided with a first back-side rotation structure and a second back-side rotation structure, and the inner side of the leaf basin is provided with a first basin-side rotation structure and a second basin-side rotation structure.

[0008] The cold air of the first and second back-side rotary structures enters through the tenon; the blade back is provided with a plurality of back-side air film holes, which are connected to the first back-side rotary structure.

[0009] The leading edge, trailing edge, back of the leaf, and top of the leaf basin form the leaf tip, which is provided with a leaf tip air film pore. Part of the cold air from the first dorsal rotating structure flows out from the dorsal air film pore and the leaf tip air film pore, and another part of the cold air flows out from the leading edge; part of the cold air from the second dorsal rotating structure flows out from the leaf tip air film pore, and another part of the cold air flows out from the trailing edge.

[0010] The leaf basin is provided with a basin-side air film hole. Part of the cold air from the first basin-side rotating structure and the second basin-side rotating structure flows out from the basin-side air film hole, and another part of the cold air flows out from the leaf tip air film hole.

[0011] The cold air in the first back-side rotating structure, the second back-side rotating structure, the first basin-side rotating structure, and the second basin-side rotating structure all flows in a rotating manner.

[0012] The amount of cold air distributed inside the leaf basin and the leaf back is different.

[0013] Preferably, a first intermediate partition is provided between the first back-side rotary structure and the second back-side rotary structure. The first back-side rotary structure includes a first partition, a second partition, a first heat exchange rib, and a leading edge partition. The first and second partitions are arranged radially along the high-vortex rotor blades, and a first radial serpentine rotary channel is formed between the first partition, the second partition, the first intermediate partition, and the leading edge partition. The first heat exchange rib is disposed within the first radial serpentine rotary channel.

[0014] The cold air from the first rear rotating structure enters through the tenon and then enters between the first middle partition and the second partition.

[0015] The cold air from the first dorsal rotating structure enters through the tenon, flows along the first radial serpentine rotating channel, first flows between the first intermediate partition and the second partition, and then flows out between the first partition and the leading edge partition, finally reaching the blade tip.

[0016] Preferably, the second back-side rotary structure includes a third partition, a fourth partition, a trailing edge partition, and a second heat exchange rib. The third and fourth partitions are arranged radially along the high-vortex rotor blades, and the third partition, the fourth partition, the trailing edge partition, and the first intermediate partition form a second radial serpentine rotary channel. The second heat exchange rib is disposed within the second radial serpentine rotary channel.

[0017] The cool air from the second dorsal rotating structure enters through the tenon, flows along the second radial serpentine rotating channel, first flows between the first intermediate partition and the third partition, and then flows out between the fourth partition and the trailing edge partition, finally reaching the blade tip and trailing edge.

[0018] Preferably, the second heat exchange rib is also disposed between the third baffle and the trailing edge. The third baffle has multiple impact holes at the end near the blade tip, through which cold air enters between the third baffle and the trailing edge. The first and second heat exchange ribs are arranged in a cross pattern, and both have ribs with opposite inclination directions.

[0019] Preferably, the first intermediate partition is disposed between the first basin-side rotary structure and the second basin-side rotary structure. The first basin-side rotary structure includes a fifth partition and a third heat exchange rib. The fifth partition is arranged along the chord direction of the high-vortex rotor blades. There are multiple sets of the fifth partition, which are staggered and connected between the first partition and the first intermediate partition. The first intermediate partition, the first partition and the fifth partition form a first chord serpentine rotary channel.

[0020] The third heat exchange ribs are in multiple sets and are inclinedly arranged in the first chord-oriented serpentine rotating channel;

[0021] The cold air from the first rotating structure enters through the tenon, flows along the first chord serpentine rotating channel, and flows between the first middle partition, the first partition and the fifth partition, eventually reaching the leaf tip.

[0022] Preferably, the second basin-side rotary structure includes a sixth baffle and a fourth heat exchange rib. The sixth baffle is arranged along the chord direction of the high-vortex rotor blades. There are multiple sets of the sixth baffle, which are staggered and connected between the trailing edge baffle and the first intermediate baffle. A second chord-oriented serpentine rotary channel is formed between the first intermediate baffle, the trailing edge baffle and the sixth baffle.

[0023] The fourth heat exchange rib has multiple sets and is inclinedly arranged in the second chord-oriented serpentine rotating channel;

[0024] The third and fourth heat exchange ribs are arranged in a cross pattern, and each has ribs with opposite inclination directions.

[0025] The cool air from the second rotating structure enters through the tenon, flows along the second chord serpentine rotating channel, and flows between the first middle partition, the trailing edge partition, and the sixth partition, eventually reaching the leaf tip.

[0026] The multi-dimensional rotating high-vortex rotor blade cooling structure of this application has the following advantages:

[0027] By employing three major technical approaches—"enhanced heat transfer through multi-dimensional rotating structure," "differentiated distribution of cold air volume to balance temperature," and "multi-path air film coverage protection"—the system systematically solves the problems of insufficient heat transfer and uneven temperature in existing cooling structures. This achieves a comprehensive improvement in blade cooling efficiency, temperature uniformity, and thermal shock resistance, providing key technical support for the reliability and lifespan of high-thrust aero engines.

[0028] A multi-dimensional rotating cooling structure is adopted to cool both the basin side and the back side separately. This not only improves the heat transfer capacity of the blade's internal cavity but also achieves a more uniform temperature distribution, enhancing the overall thermal protection capability of the blade. This structural design has significant advantages in high-temperature and high-pressure environments. Attached Figure Description

[0029] Figure 1 is a schematic diagram of the cooling structure in the chord of a turbine rotor blade in the background art;

[0030] Figure 2 is a schematic cross-sectional view of the turbine rotor blade rotation cooling channel in the background art;

[0031] Figure 3 is a schematic diagram of the cooling structure of the high-vortex rotor blades of the multi-dimensional rotating structure of this application.

[0032] Figure 4 is a schematic diagram of the first back-side rotary structure and the second back-side rotary structure of this application;

[0033] Figure 5 is a schematic diagram of the first and second pot-side rotating structures of this application.

[0034] 1. Leading edge; 2. Trailing edge; 3. Leaf back; 4. Leaf basin; 5. First dorsal rotating structure; 6. Second dorsal rotating structure; 7. First basin-side rotating structure; 8. Second basin-side rotating structure; 9. Leaf tip air film pore; 10. First septum; 11. Second septum; 12. First heat exchange rib; 13. First middle septum; 14. Third septum; 15. Fourth septum; 16. Second heat exchange rib; 17. Impact hole; 18. Leading edge septum; 19. Trailing edge septum; 20. Fifth septum; 21. Third heat exchange rib; 22. Sixth septum; 23. Fourth heat exchange rib. Detailed Implementation

[0035] To make the objectives, technical solutions, and advantages of this application clearer, the technical solutions in the embodiments of this application will be described in more detail below with reference to the accompanying drawings. In the drawings, the same or similar reference numerals denote the same or similar elements or elements having the same or similar functions throughout. The described embodiments are only some, not all, of the embodiments of this application. The embodiments described below with reference to the accompanying drawings are exemplary and intended to explain this application, and should not be construed as limiting this application. All other embodiments obtained by those skilled in the art based on the embodiments of this application without inventive effort are within the scope of protection of this application. The embodiments of this application will be described in detail below with reference to the accompanying drawings.

[0036] The first aspect of this application provides a multi-dimensional rotating high-vortex rotor blade cooling structure, as shown in Figure 3, including a leading edge 1, a trailing edge 2, a blade back 3, and a blade base 4 arranged in a ring inside the blade.

[0037] The inner side of the leaf back 3 is provided with a first back-side rotating structure 5 and a second back-side rotating structure 6, and the inner side of the leaf basin 4 is provided with a first basin-side rotating structure 7 and a second basin-side rotating structure 8.

[0038] The cool air enters through the tenon of the first back-side rotating structure 5 and the second back-side rotating structure 6; the blade back 3 is provided with multiple back-side air film holes, which are connected to the first back-side rotating structure 5. The tenon of the blade is the part that connects to the blade disk.

[0039] The top of the leading edge 1, trailing edge 2, leaf back 3, and leaf basin 4 is the leaf tip, and the leaf tip is provided with a leaf tip air film hole 9. Part of the cold air from the first dorsal rotating structure 5 flows out from the dorsal air film hole and the leaf tip air film hole 9, and another part of the cold air flows out from the leading edge 1; part of the cold air from the second dorsal rotating structure 6 flows out from the leaf tip air film hole 9, and another part of the cold air flows out from the trailing edge 2.

[0040] The leaf basin 4 is provided with a basin-side air film hole. Part of the cold air from the first basin-side rotating structure 7 and the second basin-side rotating structure 8 flows out from the basin-side air film hole, and the other part of the cold air flows out from the leaf tip air film hole 9.

[0041] The cold air in the first back-side rotating structure 5, the second back-side rotating structure 6, the first basin-side rotating structure 7, and the second basin-side rotating structure 8 all flows in a rotating manner.

[0042] During cooling:

[0043] The cold air drawn from the compressor enters the first back-side rotary structure 5, the second back-side rotary structure 6, the first basin-side rotary structure 7, and the second basin-side rotary structure 8, respectively. During their flow, each structure engages in convective heat transfer with the inner wall and heat exchange ribs. Addressing the uneven temperature distribution between the basin and back sides, and the different amounts of cold air allocated within the blade basin 4 and blade back 3, the cold air, during its flow, divides the single rotary structure into two rotary structures—one basin-side and one back-side. This reduces the channel cross-sectional area, maintains a high flow velocity, and provides strong convective heat transfer cooling to the inner wall of the blade. Finally, the cold air exits through the film cooling vents, forming a film cooling the outer wall of the blade. This achieves higher cooling capacity and a more refined structure.

[0044] Referring to Figure 4, preferably, a first intermediate partition 13 is provided between the first back-side rotating structure 5 and the second back-side rotating structure 6. The first back-side rotating structure 5 includes a first partition 10, a second partition 11, and a first heat exchange rib 12. The first partition 10 and the second partition 11 are arranged radially along the high-vortex rotor blades, and a first radial serpentine rotating channel is formed between the first partition 10, the second partition 11, the first intermediate partition 13, and the leading edge partition 18. The first heat exchange rib 12 is disposed within the first radial serpentine rotating channel.

[0045] The cold air from the first back-side rotating structure 5 enters from the tenon, flows along the first radial serpentine rotating channel, first flows into the space between the first intermediate partition 13 and the second partition 11, and then flows out from the space between the first partition 10 and the leading edge partition 18, finally reaching the blade tip.

[0046] After the cold air flows out between the first partition 10 and the second partition 11, it can cool the leading edge 1.

[0047] By setting the first rear-side rotating structure 5, the cold air can uniformly and effectively cool the wall surface at different locations through rotating flow.

[0048] Preferably, the second back-side rotating structure 6 includes a third partition 14, a fourth partition 15, a trailing edge partition 19, and a second heat exchange rib 16. The third partition 14 and the fourth partition 15 are arranged radially along the high-vortex rotor blades, and the third partition 14, the fourth partition 15, the trailing edge partition 19, and the first intermediate partition 13 form a second radial serpentine rotating channel; the second heat exchange rib 16 is disposed within the second radial serpentine rotating channel.

[0049] The cold air from the second back-side rotating structure 6 enters from the tenon, flows along the second radial serpentine rotating channel, first flows between the first intermediate partition 13 and the third partition 14, and then flows out between the fourth partition 15 and the trailing edge partition 19, finally reaching the blade tip and trailing edge 2.

[0050] Preferably, the second heat exchange rib 16 is also disposed between the third baffle 14 and the trailing edge 2. The trailing edge baffle 19 has multiple impact holes 17 at one end near the blade tip, and the cold air enters the trailing edge 2 through the impact holes 17. The first heat exchange rib 12 and the second heat exchange rib 16 are arranged in a cross pattern, and both have ribs with opposite inclination directions to achieve rapid cooling in different directions.

[0051] Referring to Figure 5, preferably, the first intermediate partition 13 is disposed between the first basin-side rotary structure 7 and the second basin-side rotary structure 8. The first basin-side rotary structure 7 includes a fifth partition 20 and a third heat exchange rib 21. The fifth partition 20 is arranged along the chord direction of the high-vortex rotor blades. There are multiple sets of fifth partitions 20, which are staggered and connected between the first partition 10 and the first intermediate partition 13. The first intermediate partition 13, the first partition 10 and the fifth partition 20 form a first chord-oriented serpentine rotary channel.

[0052] The third heat exchange rib 21 has multiple sets and is inclinedly arranged in the first chord serpentine rotating channel;

[0053] The cold air from the first pot side rotating structure 7 enters from the tenon, flows along the first chord serpentine rotating channel, between the first intermediate partition 13, the first partition 10 and the fifth partition 20, and finally reaches the leaf tip.

[0054] The second basin-side rotary structure 8 includes a sixth baffle 22 and a fourth heat exchange rib 23. The sixth baffle 22 is arranged along the chord direction of the high-vortex rotor blades. There are multiple sets of the sixth baffle 22, which are staggered and connected between the trailing edge baffle 19 and the first intermediate baffle 13. The first intermediate baffle 13, the trailing edge baffle 19 and the sixth baffle 22 form a second chord-oriented serpentine rotary channel.

[0055] The fourth heat exchange rib 23 has multiple sets and is inclinedly arranged in the second chord serpentine rotating channel.

[0056] The third heat exchange rib 21 and the fourth heat exchange rib 23 are arranged in a cross pattern, and both have ribs with opposite inclination directions to achieve rapid cooling in different directions.

[0057] The cold air from the second side rotating structure 8 enters from the tenon, flows along the second chord serpentine rotating channel, between the first intermediate partition 13, the trailing edge partition 19 and the sixth partition 22, and finally reaches the blade tip.

[0058] Since the cross-sectional areas of the first basin-side rotating structure 7 and the second basin-side rotating structure 8 are relatively small, it is difficult to arrange traditional radial baffles. Therefore, chordal baffles are used to increase the cooling area.

[0059] The third heat exchange rib 21 and the fourth heat exchange rib 23 are both inclined to ensure a larger contact area for cold air. Furthermore, the third heat exchange rib 21 and the fourth heat exchange rib 23 are inclined in the same direction, but the cold air flows in in different directions, thus enhancing cooling at different locations.

[0060] The specific structures of the first back-side rotary structure 5, the second back-side rotary structure 6, the first basin-side rotary structure 7, and the second basin-side rotary structure 8 are not exactly the same, thus adapting to effective cooling at different locations.

[0061] The widths of the first heat exchange rib 12 to the fourth heat exchange rib 23 can be adjusted according to the actual situation, and the widths of the first heat exchange rib 12 to the fourth heat exchange rib 23 can all be different.

[0062] In summary, this application has the following advantages:

[0063] The multi-dimensional rotary cooling structure retains the advantages of traditional rotary cooling while effectively improving the heat exchange capacity of the blade cavity, resulting in better cooling effect and more uniform temperature distribution.

[0064] By employing three major technical approaches—"enhanced heat transfer through multi-dimensional rotating structure," "differentiated distribution of cold air volume to balance temperature," and "multi-path air film coverage protection"—the system systematically solves the problems of insufficient heat transfer and uneven temperature in existing cooling structures. This achieves a comprehensive improvement in blade cooling efficiency, temperature uniformity, and thermal shock resistance, providing key technical support for the reliability and lifespan of high-thrust aero engines.

[0065] The above description is merely a specific embodiment of this application, but the scope of protection of this application is not limited thereto. Any variations or substitutions that can be easily conceived by those skilled in the art within the technical scope disclosed in this application should be included within the scope of protection of this application. Therefore, the scope of protection of this application should be determined by the scope of the claims.

Claims

1. A cooling structure for high-vortex rotor blades with a multi-dimensional rotating structure, characterized in that, The blade includes a leading edge (1), a trailing edge (2), a back (3), and a leaf basin (4) arranged in a ring inside the blade. The back (3) has a first back-side rotating structure (5) and a second back-side rotating structure (6) on its inner side, and the leaf basin (4) has a first basin-side rotating structure (7) and a second basin-side rotating structure (8) on its inner side. Cool air enters the first back-side rotating structure (5) and the second back-side rotating structure (6) through tenons. The back (3) has multiple back-side air film pores, which communicate with the first back-side rotating structure (5). The leading edge (1), trailing edge (2), and leaf basin (4) are arranged in a ring inside the blade. The top of the leaf back (3) and leaf basin (4) is the leaf tip, and the leaf tip is provided with a leaf tip air film hole (9). Part of the cold air from the first back side rotating structure (5) flows out from the back side air film hole and the leaf tip air film hole (9), and another part of the cold air flows out from the leading edge (1); part of the cold air from the second back side rotating structure (6) flows out from the leaf tip air film hole (9), and another part of the cold air flows out from the trailing edge (2); the leaf basin (4) is provided with a basin side air film hole, and part of the cold air from the first basin side rotating structure (7) and the second basin side rotating structure (8) flows out from the basin side air film hole, and another part of the cold air flows out from the leaf basin (4). The cold air flows out through the pointed film hole (9); the cold air in the first back-side rotating structure (5), the second back-side rotating structure (6), the first basin-side rotating structure (7), and the second basin-side rotating structure (8) all flow in a rotating manner; the amount of cold air distributed inside the leaf basin (4) and the leaf back (3) is different; a first intermediate partition (13) is provided between the first back-side rotating structure (5) and the second back-side rotating structure (6), the first back-side rotating structure (5) includes a first partition (10), a second partition (11), a first heat exchange rib (12), and a leading edge partition (18); the first partition ( 10) and the second partition (11) are arranged radially along the high vortex rotor blades. A first radial serpentine rotating channel is formed between the first partition (10), the second partition (11), the first intermediate partition (13) and the leading edge partition (18). The first heat exchange rib (12) is located in the first radial serpentine rotating channel. The cold air of the first back-side rotating structure (5) enters from the tenon, flows along the first radial serpentine rotating channel, first flows into the space between the first intermediate partition (13) and the second partition (11), and then flows out from the space between the first partition (10) and the leading edge partition (18), and finally reaches the blade tip.

2. The high-vortex rotor blade cooling structure with a multi-dimensional rotating structure as described in claim 1, characterized in that, The second back-side rotating structure (6) includes a third partition (14), a fourth partition (15), a trailing edge partition (19), and a second heat exchange rib (16). The third partition (14) and the fourth partition (15) are arranged radially along the high-vortex rotor blades. The third partition (14), the fourth partition (15), the trailing edge partition (19), and the first intermediate partition (13) form a second radial serpentine rotating channel. The second heat exchange rib (16) is located in the second radial serpentine rotating channel. The cold air of the second back-side rotating structure (6) enters from the tenon and flows along the second radial serpentine rotating channel. It first flows into the space between the first intermediate partition (13) and the third partition (14), and then flows out from the space between the fourth partition (15) and the trailing edge partition (19), finally reaching the blade tip and the trailing edge (2).

3. The high-vortex rotor blade cooling structure with a multi-dimensional rotating structure as described in claim 2, characterized in that, The second heat exchange rib (16) is also disposed between the trailing edge baffle (19) and the trailing edge (2). The trailing edge baffle (19) has multiple impact holes (17) at the end near the blade tip. Cold air enters between the trailing edge baffle (19) and the trailing edge (2) through the impact holes (17). The first heat exchange rib (12) and the second heat exchange rib (16) are arranged in a cross pattern, and both have ribs with opposite inclination directions.

4. The high-vortex rotor blade cooling structure with a multi-dimensional rotating structure as described in claim 2, characterized in that, The first intermediate partition (13) is located between the first basin-side rotating structure (7) and the second basin-side rotating structure (8). The first basin-side rotating structure (7) includes a fifth partition (20) and a third heat exchange rib (21). The fifth partition (20) is arranged along the chord direction of the high-vortex rotor blade. There are multiple sets of the fifth partition (20) which are staggered between the first partition (10) and the first intermediate partition (13). A first chord-oriented serpentine rotating channel is formed between the first intermediate partition (13), the first partition (10) and the fifth partition (20). There are multiple sets of the third heat exchange rib (21) which are inclinedly arranged in the first chord-oriented serpentine rotating channel. The cold air of the first basin-side rotating structure (7) enters from the tenon and flows along the first chord-oriented serpentine rotating channel between the first intermediate partition (13), the first partition (10) and the fifth partition (20), and finally reaches the blade tip.

5. The high-vortex rotor blade cooling structure with a multi-dimensional rotating structure as described in claim 4, characterized in that, The second basin-side rotating structure (8) includes a sixth partition (22) and a fourth heat exchange rib (23). The sixth partition (22) is arranged along the chord direction of the high-vortex rotor blade. There are multiple sets of the sixth partition (22) which are staggered between the trailing edge partition (19) and the first intermediate partition (13). A second chord-oriented serpentine rotating channel is formed between the first intermediate partition (13), the trailing edge partition (19) and the sixth partition (22). There are multiple sets of the fourth heat exchange rib (23) which are inclinedly arranged in the second chord-oriented serpentine rotating channel. The third heat exchange rib (21) and the fourth heat exchange rib (23) are arranged crosswise, and there are ribs with opposite inclination directions. The cold air of the second basin-side rotating structure (8) enters from the tenon and flows along the second chord-oriented serpentine rotating channel between the first intermediate partition (13), the trailing edge partition (19) and the sixth partition (22), and finally reaches the blade tip.

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