aerofoil

Abstract

An airfoil for improving cooling effectiveness of the airfoil, the airfoil having a leading edge, a trailing edge and two side walls enclosing a hollow cavity for cooling air flow, the two side walls including a pressure side wall and a suction side wall, the cavity including a plurality of chamber regions separated from each other, at least one of the plurality of chamber regions having a plurality of outer passages and a plurality of inner passages, each of the outer passages being adjacent to one of the two side walls and communicating with an outer wall surface of the side wall through a film hole, the plurality of inner passages being disposed inboard of the plurality of outer passages, each of the outer passages communicating with the inner passages through an impingement hole; in at least one of the chamber regions, the flow sequence of the cooling air includes: the inner passages communicated by the outer passages adjacent to the pressure side wall, the inner passages communicated by the outer passages adjacent to the suction side wall.

Description

TECHNICAL FIELD

[0001] The present application relates to aero-engine cooling design, in particular to a wing profile. BACKGROUND

[0002] The development of modern aero-engine technology promotes the continuous increase of high-pressure turbine inlet temperature, and the high-pressure turbine inlet temperature of the current advanced aero-engine is close to 2000K or so, far exceeding the working temperature of the metal material used. At the same time, the technical personnel have begun to focus on the development of aero-engine with high-pressure turbine inlet temperature reaching 2100-2200K. Therefore, in order to ensure the long-term efficient and stable operation of the high-pressure turbine blade, more advanced cooling technology needs to be used for the turbine blade. SUMMARY

[0003] The purpose of the present application is to provide a wing profile for improving the cooling effect of the wing profile.

[0004] According to the embodiment of the present application, the wing profile has a leading edge, a trailing edge and two side walls, the leading edge, the trailing edge and the two side walls enclose a hollow cavity for cooling airflow, the two side walls include a pressure side wall and a suction side wall, the cavity includes a plurality of chamber regions separated from each other, at least one of the plurality of chamber regions has a plurality of outer channels and a plurality of inner channels, each of the outer channels is adjacent to one of the two side walls and communicates with the outer wall surface of the side wall through a film hole, the plurality of inner channels are arranged inside the plurality of outer channels, and each of the outer channels communicates with the inner channel through an impact hole.

[0005] In at least one of the chamber regions, the flow sequence of the cooling gas includes: the inner channel communicated by the outer channel adjacent to the pressure side wall, the inner channel communicated by the outer channel adjacent to the suction side wall.

[0006] In one or more embodiments, each of the inner channels communicated with the outer channel only communicates with one of the outer channels.

[0007] In one or more embodiments, the wing profile further has a root and a tip, the wing profile extends radially from the root to the tip, and the inner channels and the outer channels extend along the radial direction.

[0008] The plurality of inner channels are communicated through a rotation channel, and the rotation channel is arranged at the root or arranged at the tip.

[0009] In one or more embodiments, the cooling gas enters the chamber region from the inner channel communicated by the outer channel adjacent to the pressure side wall.

[0010] In one or more embodiments, a spoiler column is arranged in the outer channel.

[0011] In one or more embodiments, the inner passages are provided with ribs.

[0012] In one or more embodiments, at least one of the plurality of chamber regions comprises a front chamber region, the front chamber region further comprising a leading edge passage;

[0013] The leading edge passage is adjacent to the leading edge and communicates with the outer wall surface of the leading edge through film holes, and the leading edge passage communicates with the inner passage communicated by the impact hole of the outer passage adjacent to the pressure side wall;

[0014] The flow sequence of the cooling gas in the front chamber region comprises: the inner passage communicated by the outer passage adjacent to the pressure side wall, the leading edge passage, and the inner passage communicated by the outer passage adjacent to the suction side wall.

[0015] In one or more embodiments, a plurality of the inner passages of the front chamber region communicate with the outer passage adjacent to the suction side wall, wherein at least one of the inner passages is in front in chordwise direction and another of the inner passages is behind in chordwise direction, and the flow sequence of the cooling gas in the front chamber region comprises: the inner passage in front in chordwise direction and the inner passage behind in chordwise direction.

[0016] In one or more embodiments, at least one of the plurality of chamber regions comprises a middle chamber region.

[0017] Embodiments of the present application have at least one of the following beneficial effects:

[0018] 1. The flow sequence design of the cooling gas ensures that the relatively high temperature parts of the pressure side wall, the leading edge and the suction side wall of the airfoil member can be fully cooled, and at the same time realizes fine distribution and control of the cooling gas, and improves the utilization efficiency and cooling efficiency of the cooling gas.

[0019] 2. The outer passage enhances the flow of the cooling gas, strengthens the heat exchange, the impact hole realizes impact cooling of the outer passage, the film hole realizes film cooling of the outer wall surface of the airfoil member, improves the cooling effect, and improves the utilization efficiency and cooling efficiency of the cooling gas.

[0020] 3. The separated plurality of chamber regions can accurately control the cooling gas flow obtained by each chamber region, avoid the situation that the cooling gas flow is insufficient in some chamber regions and the cooling gas flow is excessive in some chamber regions due to the cross flow of the cooling gas between different chamber regions, ensure that each chamber region obtains sufficient and accurate cooling gas flow, not only ensure the cooling effect of each chamber region, but also improve the utilization efficiency and cooling efficiency of the cooling gas of the airfoil member 1. BRIEF DESCRIPTION OF DRAWINGS

[0021] The above described and other features, properties, and advantages of the present application will become more apparent by reference to the following description of the application taken in conjunction with the accompanying drawings and examples in which:

[0022] Figure 1 is a schematic view of the exterior of an airfoil;

[0023] Figure 2 is a cross-sectional view of an airfoil;

[0024] Figure 3 is a flow path diagram of the leading chamber region of an airfoil;

[0025] Figure 4 is a flow path diagram of the mid-chamber region of an airfoil;

[0026] Figure 5 is a schematic view of a combination of impingement holes and trip strakes;

[0027] Figure 6 is a schematic view of a combination of impingement holes and trip strakes;

[0028] Figure 7 is a schematic view of a combination of impingement holes and trip strakes;

[0029] Figure 8 is a schematic view of a combination of impingement holes and trip strakes;

[0030] Figure 9 is a schematic view of a combination of impingement holes and trip strakes;

[0031] Figure 10 is a schematic view of a combination of impingement holes and trip strakes;

[0032] Figure 11 is a schematic view of a combination of impingement holes and trip strakes;

[0033] Figure 12 is a schematic view of a combination of impingement holes and trip strakes;

[0034] Figure 13 is a schematic view of a combination of impingement holes and trip strakes;

[0035] Figure 14 is a schematic view of a combination of impingement holes and trip strakes;

[0036] Figure 15 is a schematic view of a combination of impingement holes and trip strakes;

[0037] Figure 16 is a schematic view of a combination of impingement holes and trip strakes;

[0038] Figure 17 is a cross-sectional view of an airfoil of Example Three;

[0039] Figure 18 Cross-sectional view of an airfoil for example four;

[0040] Reference signs:

[0041] 1 - airfoil;

[0042] 2 - leading edge;

[0043] 3 - trailing edge;

[0044] 4 - pressure side wall;

[0045] 5 - suction side wall;

[0046] 6 - cavity;

[0047] 7 - front chamber area, 701 - first front inner passage, 702 - second front inner passage, 703 - third front inner passage, 704 - first front outer passage, 705 - second front outer passage, 706 - third front outer passage, 707 - leading edge passage, 708 - front cold air passage inlet, 709 - fourth front inner passage, 710 - fifth front inner passage, 711 - fourth front outer passage, 712 - fifth front outer passage, 713 - sixth front outer passage;

[0048] 8 - middle chamber area, 801 - first middle inner passage, 802 - second middle inner passage, 803 - third middle inner passage, 804 - fourth middle inner passage, 805 - first middle outer passage, 806 - second middle outer passage, 807 - third middle outer passage, 808 - middle cold air passage inlet, 809 - fifth middle inner passage, 810 - sixth middle inner passage, 811 - seventh middle inner passage, 812 - eighth middle inner passage, 813 - fourth middle outer passage, 814 - fifth middle outer passage, 815 - sixth middle outer passage, 816 - ninth middle inner passage, 817 - tenth middle inner passage, 818 - eleventh middle inner passage, 819 - seventh middle outer passage, 820 - eighth middle outer passage, 821 - ninth middle outer passage;

[0049] 9 - rear chamber area, 901 - first rear inner passage, 902 - second rear inner passage;

[0050] 10 - film hole;

[0051] 11 - outer layer wall;

[0052] 12 - inner layer wall;

[0053] 13 - impingement hole;

[0054] 14 - root;

[0055] 15 - tip;

[0056] 16 - turning passage;

[0057] 17-Tenon;

[0058] 18-Breakthrough column;

[0059] 19- Tail edge split. Detailed Implementation

[0060] The present invention will be further described below with reference to specific embodiments and accompanying drawings. More details are set forth in the following description in order to provide a full understanding of the present invention. However, the present invention can obviously be implemented in many other ways different from those described herein. Those skilled in the art can make similar extensions and derivations based on actual application situations without departing from the spirit of the present invention. Therefore, the scope of protection of the present invention should not be limited by the content of this specific embodiment.

[0061] It should be noted that these and other accompanying drawings are merely examples and are not drawn to scale, and should not be construed as limiting the scope of protection of the present invention.

[0062] The terms “first”, “second”, etc., are used interchangeably to distinguish one feature from another and are not intended to indicate that each feature must be located in the position shown in the figure in each embodiment.

[0063] Example 1

[0064] Figure 1 The external structure of the airfoil 1 is shown, with the air film holes 10 on its outer wall surface omitted. Figure 2 shows the airfoil 1 in... Figure 1 Sectional structure at point AA.

[0065] like Figure 1 and Figure 2 As shown, the airfoil 1 has a leading edge 2, a trailing edge 3, and two sidewalls 4 and 5. The leading edge 2, trailing edge 3, and two sidewalls 4 and 5 enclose a hollow cavity 6 for cooling airflow. The chord direction of the airfoil 1 points to the central axis connecting the leading edge 2 and the trailing edge 3, and... Figure 2 The airfoil 1 shown has its mid-curve coincident in cross-sectional shape. The two sidewalls 4 and 5 include pressure sidewalls and suction sidewalls, with one sidewall 4 being a pressure sidewall and the other sidewall 5 being a suction sidewall. Therefore, in the following description, the pressure sidewall corresponds to reference numeral 4, and the suction sidewall corresponds to reference numeral 5. The airfoil 1 also has a root 14 and an end 15, extending radially from the root 14 to the end 15. The cavity 6 includes three chamber regions 7, 8, or 9 separated from each other: a front chamber region 7, a middle chamber region 8, and a rear chamber region 9. Each chamber region 7, 8, or 9 is supplied with a separate cooling airflow, and each cooling airflow flows only in one chamber region 7, 8, or 9, cooling that chamber region 7, 8, or 9. The number of separated chamber regions in the cavity 6 is not limited to three; it can be multiple, i.e., two or more.

[0066] The separated chamber regions can precisely regulate the cooling gas flow obtained by each chamber region, avoiding the situation that the cooling gas flows between different chamber regions, resulting in insufficient cooling gas in some chamber regions and excessive cooling gas in some chamber regions, ensuring that each chamber region obtains sufficient and precise cooling gas flow, not only ensuring the cooling effect of each chamber region, but also improving the cooling gas utilization efficiency and cooling efficiency of the airfoil 1.

[0067] As shown in Figure 2 , the front chamber region 7 has a plurality of outer passages and a plurality of inner passages, and the inner passages and the outer passages extend in the radial direction. For example, the front chamber region 7 has three inner passages: a first front inner passage 701, a second front inner passage 702, and a third front inner passage 703, and the front chamber region 7 has three outer passages: a first front outer passage 704, a second front outer passage 705, and a third front outer passage 706. The number of inner passages and outer passages is not limited to three, but can be two or more. In the following description, "outer passage" refers to any one of the first front outer passage 704, the second front outer passage 705, and the third front outer passage 706, and "inner passage" refers to any one of the first front inner passage 701, the second front inner passage 702, and the third front inner passage 703.

[0068] As shown in Figure 2 , each outer passage 704, 705, or 706 is adjacent to one of the two side walls 4, 5 and communicates with the outer wall surface of the side wall 4 or 5 through the film hole 10. For example, the first front outer passage 704 is adjacent to the pressure side wall 4, the second front outer passage 705 is adjacent to the suction side wall 5, and the third front outer passage 706 is adjacent to the suction side wall 5. The section of the side wall between the outer wall surface and the outer passage 704, 705, or 706 is commonly referred to as the outer layer wall 11, which corresponds to the inner layer wall 12 described below. The film hole 10 penetrates the outer layer wall 11 and has an outlet on the outer wall surface of the side wall 4 or 5 and an inlet communicating with the outer passage 704, 705, or 706. The cooling gas in the outer passage 704, 705, or 706 enters the film hole 10 from the inlet and then flows out of the outlet to form a gas film on the outer wall surface of the side wall 4 or 5. The film holes 10 are arranged in rows in the radial direction. The number of rows of film holes 10 and the number of film holes 10 in a single row are determined according to the volume of the outer passage 704, 705, or 706 or the volume of the inner passage 701, 702, or 703 communicating with the outer passage 704, 705, or 706. For example, the outer layer wall 11 of each outer passage 704, 705, or 706 is provided with 1-2 rows of film holes 10, and the number of film holes 10 in a single row is 14-20.

[0069] Referring to Figure 2three inner channels 701, 702, 703 are correspondingly arranged inside the three outer channels 704, 705, 706, and thus form inner layer walls 12 between each outer channel 704, 705 or 706 and the corresponding inner channel 701, 702 or 703, each outer channel 704, 705 or 706 is connected to the corresponding inner channel 701, 702 or 703 through an impingement hole 13, the "corresponding" means that the first front outer channel 704 is connected to the first front inner channel 701, the second front outer channel 705 is connected to the second front inner channel 702, and the third front outer channel 706 is connected to the third front inner channel 703. In each inner layer wall 12, the impingement hole 13 penetrates the inner layer wall 12, has an inlet connected to the corresponding inner channel 701, 702 or 703, and has an outlet connected to the corresponding outer channel 704, 705 or 706, cooling gas in the inner channel 701, 702 or 703 enters the impingement hole 13 from the inlet, and then flows out of the outlet to impinge and cool the outer channel 704, 705 or 706, the impingement holes 13 are arranged in the radial direction (perpendicular to the plane of the paper in the figure) on the inner layer wall 12, and the volume of the inner channel 704, 705 or 706 is determined according to the cooling gas distribution requirement. Figure 2

[0070] Referring to Figure 2 , each inner channel 701, 702 or 703 connected to an outer channel 704, 705 or 706 is only connected to one outer channel 704, 705 or 706. In Figure 2 the embodiment shown, the first front inner channel 701 is only connected to the first front outer channel 704, the second front inner channel 702 is only connected to the second front outer channel 705, and the third front inner channel 703 is only connected to the third front outer channel 706. This makes each inner channel only supply cooling gas to one outer channel, enabling accurate control of the cooling gas flow rate obtained by each outer channel, avoiding the situation where an inner channel supplies cooling gas to multiple outer channels, resulting in insufficient cooling gas for some outer channels and excessive cooling gas for some outer channels, ensuring that each outer channel obtains sufficient and accurate cooling gas flow rate, not only ensuring the effect of impingement cooling and film cooling at each outer channel, but also improving cooling gas utilization efficiency and cooling efficiency.

[0071] The outer channels enhance the flow of cooling gas and strengthen heat exchange, the impingement holes 13 achieve impingement cooling of the outer channels, the film holes 10 achieve film cooling of the outer wall surface of the airfoil 1, improve the cooling effect, and improve the cooling gas utilization efficiency and cooling efficiency.

[0072] Figure 3 The flow channel structure of the front chamber region 7 of the airfoil 1 is shown, a plurality of inner channels 701, 702, 703 are connected through a rotary channel 16, as Figure 3 ​As shown, the rotary channels 16 are arranged at the root 14 or at the tip 15, arranged along the transverse direction intersecting the radial direction, to achieve the communication of the plurality of inner channels 701, 702, 703, exemplarily, the communication of the first front inner channel 701, the second front inner channel 702 and the third front inner channel 703 is achieved by two rotary channels 16, one rotary channel 16 arranged at the tip 15 to communicate the top of the first front inner channel 701 and the top of the second front inner channel 702, and the other rotary channel 16 arranged at the root 14 to communicate the bottom of the second front inner channel 702 and the bottom of the third front inner channel 703.

[0073] The plurality of inner channels and the rotary channels 16 enable the sufficient flow of the cooling gas, strengthen the heat exchange, improve the cooling effect, and improve the cooling gas utilization efficiency and the cooling efficiency.

[0074] As shown in Figure 2 and Figure 3 The cooling gas enters the first front inner channel 701 from the front cooling gas channel inlet 708 at the bottom of the tenon 17, i.e. the cooling gas enters the front chamber region 7 from the inner channel communicating with the outer channel adjacent to the pressure side wall 4, and then enters the second front inner channel 702 through the rotary channel 16 at the tip 15, which makes the flow sequence of the cooling gas in the front chamber region 7 include: the inner channel communicating with the outer channel adjacent to the pressure side wall 4, and the inner channel communicating with the outer channel adjacent to the suction side wall 5.

[0075] Compared with the outside of the suction side wall 5, the outside of the pressure side wall 4 has a higher static pressure, so in the cooling gas flow path design, the pressure side wall 4 and the part close to the pressure side wall 4 have a relatively high priority, and the suction side wall 5 and the part close to the suction side wall 5 have a relatively low priority. The cooling gas first flows through the inner channel communicating with the outer channel adjacent to the pressure side wall 4, at this time, the flow of the cooling gas is relatively large, and the pressure is relatively high, which sufficiently cools the pressure side wall 4 of the airfoil 1 and the part close to the pressure side wall 4, and at the same time, it flows out from the gas film hole 10 against the relatively high static pressure on the outside of the pressure side wall 4 to form a gas film on the outer wall surface of the pressure side wall 4, and then flows through the inner channel communicating with the outer channel adjacent to the suction side wall 5, at this time, the pressure of the cooling gas is reduced, which cools the suction side wall 5 of the airfoil 1 and the part close to the suction side wall 5, and at the same time, it flows out from the gas film hole 10 against the relatively low static pressure on the outside of the suction side wall 5 to form a gas film on the outer wall surface of the suction side wall 5. This not only ensures that the pressure side wall 4 and the part close to the pressure side wall 4 are sufficiently cooled, but also realizes the fine distribution and control of the cooling gas, and improves the cooling gas utilization efficiency and the cooling efficiency.

[0076] Continuing to refer to Figure 2In the plurality of inner passages 701, 702, 703 of the front chamber region 7, the second front inner passage 702 and the third front inner passage 703 are connected to the second front outer passage 705 and the third front outer passage 706 respectively, which are adjacent to the suction side wall 5, wherein the second front inner passage 702 is in front chord-wise and the third front inner passage 703 is in back chord-wise, and the cooling air in the second front inner passage 702 enters the third front inner passage 703 through the turning passage 16 at the root 14, which makes the flow sequence of the cooling air in the front chamber region 7 include: the inner passage in front chord-wise, the inner passage in back chord-wise.

[0077] In the part of the two side walls 4, 5 close to the leading edge 2, the outer side of the part in front chord-wise has higher static pressure than the outer side of the part in back chord-wise, and similarly, in the front chamber region 7, the part in front chord-wise has higher static pressure than the part in back chord-wise, so in the cooling air flow path design, the part in front chord-wise has relatively high priority and the part in back chord-wise has relatively low priority. The cooling air flows through the inner passage in front chord-wise first, at this time, the flow of the cooling air is relatively large and the pressure is relatively high, which sufficiently cools the part in front chord-wise and flows out from the film hole 10 against the relatively high static pressure of the outer side to form a gas film on the outer wall surface, and when the cooling air flows through the inner passage in back chord-wise, the pressure of the cooling air is reduced, which cools the part in back chord-wise and flows out from the film hole 10 against the relatively low static pressure of the outer side to form a gas film on the outer wall surface. This not only ensures that the parts in front chord-wise and in back chord-wise can be sufficiently cooled, but also realizes fine distribution and control of the cooling air, improves the utilization efficiency and cooling efficiency of the cooling air.

[0078] As Figure 2As shown, the front chamber region 7 further comprises a leading edge passage 707 adjacent to the leading edge 2 and communicating with the outer wall surface of the leading edge 2 through film holes 10 penetrating the wall of the leading edge 2, the film holes 10 having an inlet communicating with the leading edge passage 707 and an outlet communicating with the outer wall surface of the leading edge 2, cooling air in the leading edge passage 707 enters the film holes 10 from the inlet and flows out of the outlet to form a film on the outer wall surface of the leading edge 2. The film holes 10 are arranged in rows in the radial direction, the number of rows of film holes 10 and the number of film holes 10 in a single row are determined according to the volume of the leading edge passage 707 or the volume of the inner passage communicated by the leading edge passage 707, for example, 4-8 rows of film holes 10 are provided, and the number of film holes 10 in a single row is 14-20. The leading edge passage 707 communicates with the inner passage adjacent to the outer passage of the pressure side wall 4 through impingement holes 13, i.e. communicates with the first front inner passage 701, the impingement holes 13 are arranged in the radial direction on the wall between the leading edge passage 707 and the first front inner passage 701, the impingement holes 13 have an inlet communicating with the first front inner passage 701 and an outlet communicating with the leading edge passage 707, cooling air in the first front inner passage 701 enters the impingement holes 13 from the inlet and flows out of the outlet to impingement cool the leading edge passage 707, the first front inner passage 701 receives cooling air from the bottom, the cooling air flows radially upward, since the radial position of the impingement holes 13 on the wall between the leading edge passage 707 and the first front inner passage 701 is lower than the turning passage 16 at the tip 15, the cooling air first flows through the impingement holes 13 and enters the leading edge passage 707 from the impingement holes 13, then flows to the turning passage 16 at the tip 15 and enters the second front inner passage 702, and finally flows to the turning passage 16 at the root 14 and enters the third front inner passage 703, which makes the flow sequence of the cooling air in the front chamber region 7 include: the inner passage adjacent to the outer passage of the pressure side wall 4, the leading edge passage 707, the inner passage adjacent to the outer passage of the suction side wall 5.

[0079] In airfoil 1, the leading edge 2 has a higher temperature than the portion of the front chamber region 7 near the suction sidewall 5, and the outer side of the leading edge 2 has a higher static pressure than the outer side of the suction sidewall 5. Therefore, in the cooling airflow path design, the leading edge 2 has a relatively high priority, while the portion near the suction sidewall 5 has a relatively low priority. The cooling gas first flows through the leading edge channel 707. At this time, the temperature of the cooling gas is relatively low, the flow rate is relatively large, and the pressure is relatively high, which fully cools the relatively high-temperature leading edge 2. At the same time, it flows out from the film gas hole 10 to counteract the relatively high static pressure on the outer side of the leading edge 2, forming a film gas on the outer wall surface of the leading edge 2. When it flows through the inner channel connected to the outer channel of the adjacent suction sidewall 5, the pressure of the cooling gas decreases, which cools the relatively low-temperature portion near the suction sidewall 5. At the same time, it flows out from the film gas hole 10 to counteract the relatively low static pressure on the outer side of the suction sidewall 5, forming a film gas on the outer wall surface of the suction sidewall 5. This not only ensures that the relatively high-temperature leading edge 2 is adequately cooled, but also enables precise distribution and control of the cooling gas, improving the utilization efficiency and cooling efficiency of the cooling gas.

[0080] Reference Figure 2 At the same time, combined Figures 5 to 16 The external passages 704, 705, and 706 of the anterior chamber region 7 are equipped with... Figures 5 to 16 The shown turbulence column 18 turbulents the cooling air to enhance heat transfer. Both ends of the turbulence column 18 are connected to the corresponding inner wall 12 and outer wall 11, respectively. The arrangement of the impact hole 13 and the turbulence column 18 is determined based on the approximate chordal dimensions of the outer channels 704, 705, or 706. For example, the chordal dimension of the outer channels 704, 705, or 706 is limited, with a chordal dimension to the diameter of the impact hole 13 ratio of (2–5):1, and the ratio of the diameter of the turbulence column 18 within the outer channels 704, 705, or 706 to the diameter of the impact hole 13 ratio of (0.8–1.2):1. Figures 5 to 10 Three exemplary arrangements of the impact hole 13 and the baffle column 18 for an outer channel with limited chordal dimensions are shown. Figure 5 and Figure 6 A combined arrangement is shown. Taking any one of the outer channels 704, 705 and 706 as an example, the turbulence columns 18 and impact holes 13 in the outer channels 704, 705 or 706 are arranged alternately in the radial direction to form a row, and the radial distance between adjacent turbulence columns 18 and impact holes 13 is the same. Figure 7 and Figure 8Another combination arrangement is shown, for example, with respect to any one of the outer passages 704, 705, and 706, in which a row of radially aligned turbulence posts 18 is provided in the outer passage 704, 705, or 706, with the radially adjacent turbulence posts 18 having the same radial distance therebetween, and a row of radially aligned impingement holes 13 is provided, with the radially adjacent impingement holes 13 having the same radial distance therebetween, the row of impingement holes 13 and the row of turbulence posts 18 being spaced chordally, and the impingement holes 13 being chordally aligned with the turbulence posts 18. Figure 9 and Figure 10 Another combination arrangement is shown, for example, with respect to any one of the outer passages 704, 705, and 706, in which a row of radially aligned turbulence posts 18 is provided in the outer passage 704, 705, or 706, with the radially adjacent turbulence posts 18 having the same radial distance therebetween, and a row of radially aligned impingement holes 13 is provided, with the radially adjacent impingement holes 13 having the same radial distance therebetween, the row of impingement holes 13 and the row of turbulence posts 18 being spaced chordally, and the impingement holes 13 being chordally misaligned with the turbulence posts 18. Illustratively, the outer passage 704, 705, or 706 has a large chordal dimension, with the ratio of the chordal dimension to the impingement hole 13 diameter being (6-8): 1, Figures 11 to 16 Three combination arrangements of impingement holes 13 and turbulence posts 18 for outer passages having a large chordal dimension are illustratively shown, Figure 11 and Figure 12 Another combination arrangement is shown, for example, with respect to any one of the outer passages 704, 705, and 706, in which three radially aligned and chordally equidistant turbulence posts 18 and three radially aligned and chordally equidistant impingement holes 13 are provided in the outer passage 704, 705, or 706, with the radially adjacent turbulence posts 18 and impingement holes 13 having the same radial distance therebetween. Figure 13 and Figure 14 Another combination arrangement is shown, for example, with respect to any one of the outer passages 704, 705, and 706, in which three rows are provided in the outer passage 704, 705, or 706, in each row, a radially aligned and chordally equidistant turbulence post 18 and a radially aligned and chordally equidistant impingement hole 13 are provided, with the radially adjacent turbulence posts 18 and impingement holes 13 having the same radial distance therebetween, the three rows having the same chordal distance, and the turbulence posts 18 and impingement holes 13 of the different rows being chordally aligned and chordally alternating. Figure 15 and Figure 16Another arrangement is shown. Taking any one of the outer channels 704, 705, and 706 as an example, two rows of radially arranged baffle columns 18 are provided in the outer channels 704, 705, or 706. The radial distance between radially adjacent baffle columns 18 in each row is the same. Two rows of impact holes 13 are arranged radially, and the radial distance between radially adjacent impact holes 13 in each row is the same. Each row of impact holes 13 and each row of baffle columns 18 are spaced apart and alternately arranged in the chord direction. The impact holes 13 and baffle columns 18 in different rows are offset from each other in the chord direction, and the impact holes 13 in different rows are aligned in the chord direction. The baffle columns 18 in different rows are aligned in the chord direction. In one or more other embodiments, the baffle columns 18 protrude from the outer wall 11 to the inner wall 12, have a gap with the inner wall 12, and are not connected to the inner wall 12.

[0081] Ribs are provided in the inner channels 701, 702 or 703 of the front chamber region 7. The ribs are not shown in the figure. They are used to enhance the convective heat transfer of the inner channels. Whether to arrange ribs depends on the actual volume of the inner channels 701, 702 or 703. For example, ribs are provided in the first front inner channel 701 and the second front inner channel 702 of the front chamber region 7. The ribs protrude from the inner wall of the inner channel into the inner channel. For example, the ratio of the size of the protruding rib to the size of the inner channel in its protruding direction is 1:(5 to 10).

[0082] like Figure 2 As shown, the central chamber region 8 has multiple external channels and multiple internal channels extending radially. Exemplarily, the central chamber region 8 has four internal channels: a first internal channel 801, a second internal channel 802, a third internal channel 803, and a fourth internal channel 804, and three external channels: a first external channel 805, a second external channel 806, and a third external channel 807. The number of internal channels is not limited to four; it can be multiple, i.e., two or more. The number of external channels is not limited to three; it can be multiple, i.e., two or more. In the following description, "external channel" refers to any one of the first external channel 805, the second external channel 806, and the third external channel 807, and "internal channel" refers to any one of the first internal channel 801, the second internal channel 802, the third internal channel 803, and the fourth internal channel 804.

[0083] like Figure 2As shown, each of the middle outer passages 805, 806 or 807 of the middle chamber region 8 is adjacent to one of the two side walls 4, 5 and communicates with the outer wall surface of the side wall 4 or 5 through the gas film holes 10, for example, the first middle outer passage 805 is adjacent to the pressure side wall 4, the second middle outer passage 806 is adjacent to the pressure side wall 4, and the third middle outer passage 807 is adjacent to the suction side wall 5. The gas film holes 10 penetrate the outer layer wall 11, have an outlet on the outer wall surface of the side wall 4 or 5, and have an inlet communicating with the outer passage 805, 806 or 807, the cooling gas in the outer passage 805, 806 or 807 enters the gas film hole 10 from the inlet, and then flows out from the outlet and forms a gas film on the outer wall surface of the side wall 4 or 5, the gas film holes 10 are arranged in rows in the radial direction, the number of rows of gas film holes 10 and the number of gas film holes 10 in a single row are determined according to the volume of the outer passage 805, 806 or 807 or the volume of the inner passage 801, 802 or 804 communicating with the outer passage 805, 806 or 807, for example, 1-2 rows of gas film holes 10 are arranged on the outer layer wall 11 of each outer passage 805, 806 or 807, and the number of gas film holes 10 in a single row is 14-20.

[0084] With reference to Figure 2 , the four inner passages 801, 802, 803, 804 are arranged inside the three outer passages 805, 806, 807, wherein the first middle inner passage 801 is arranged inside the first middle outer passage 805, the second middle inner passage 802 is arranged inside the second middle outer passage 806, the third middle inner passage 803 is further arranged inside the second middle inner passage 802, and the fourth middle inner passage 804 is arranged inside the third middle outer passage 807. Each outer passage 805, 806 or 807 communicates with the corresponding inner passage 801, 802 or 804 through the impingement hole 13, and "corresponding" means that the first middle outer passage 805 communicates with the first middle inner passage 801, the second middle outer passage 806 communicates with the second middle inner passage 802, and the third middle outer passage 807 communicates with the fourth middle inner passage 804. In each inner layer wall 12, the impingement hole 13 penetrates the inner layer wall 12, has an inlet communicating with the corresponding inner passage 801, 802 or 804, and has an outlet communicating with the corresponding outer passage 805, 806 or 807, the cooling gas in the inner passage 801, 802 or 804 enters the impingement hole 13 from the inlet, and then flows out from the outlet to impinge and cool the outer passage 805, 806 or 807, the impingement holes 13 are arranged in the radial direction (perpendicular to the paper surface in the middle) on the inner layer wall 12, and the volume of the inner passage 801, 802 or 804 is determined according to the cooling gas distribution requirement. Figure 2

[0085] With reference to Figure 2 , each inner passage 801, 802 or 804 communicating with an outer passage 805, 806 or 807 only communicates with one outer passage 805, 806 or 807. Figure 2 ​In the shown embodiment, the first middle inner passage 801 only communicates with the first middle outer passage 805, the second middle inner passage 802 only communicates with the second middle outer passage 806, and the fourth middle inner passage 804 only communicates with the third middle outer passage 807. The effect of such arrangement is consistent with the corresponding content described above, and thus will not be repeated here.

[0086] The effect of the arrangement of the outer passages, the impingement holes 13 and the film holes 10 is consistent with the corresponding content described above, and thus will not be repeated here.

[0087] Figure 4 The flow path structure of the middle chamber region 8 of the airfoil 1 is shown, and the plurality of inner passages 801, 802, 803, 804 communicate through the turn-around passages 16, as shown in Figure 4 As shown, the turn-around passages 16 are arranged at the root 14 or at the tip 15, and are arranged along the transverse direction intersecting the radial direction, to realize the communication of the plurality of inner passages 801, 802, 803, 804. Exemplarily, the first middle inner passage 801, the second middle inner passage 802, the third middle inner passage 803, and the fourth middle inner passage 804 are communicated through three turn-around passages 16, wherein one turn-around passage 16 is arranged at the tip 15 to communicate the top of the first middle inner passage 801 and the top of the second middle inner passage 802, one turn-around passage 16 is arranged at the root 14 to communicate the bottom of the second middle inner passage 802 and the bottom of the third middle inner passage 803, and one turn-around passage 16 is arranged at the tip 15 to communicate the top of the third middle inner passage 803 and the top of the fourth middle inner passage 804.

[0088] The effect of the arrangement of the plurality of inner passages and the turn-around passages 16 is consistent with the corresponding content described above, and thus will not be repeated here.

[0089] As shown in Figure 2 and Figure 4 The cooling air enters the first middle inner passage 801 from the middle cooling air passage inlet 808 at the bottom of the tenon 17, i.e. the cooling air enters the middle chamber region 8 from the inner passage communicating with the outer passage adjacent to the pressure side wall 4, and then enters the second middle inner passage 802 from the turn-around passage 16 at the tip 15, enters the third middle inner passage 803 from the turn-around passage 16 at the root 14, and finally enters the fourth middle inner passage 804 from the turn-around passage 16 at the tip 15, which makes the flow sequence of the cooling air in the middle chamber region 8 include: the inner passage communicating with the outer passage adjacent to the pressure side wall 4, and the inner passage communicating with the outer passage adjacent to the suction side wall 5. The effect of such arrangement is consistent with the corresponding content described above, and thus will not be repeated here.

[0090] The turbulence columns 18 are arranged in the outer passages of the middle chamber region 8 to disturb the cooling air and strengthen the heat exchange. The combined arrangement of the turbulence columns 18 and the impingement holes 13 is the same as that of the front chamber region 7 described above, and thus will not be repeated here.

[0091] Ribs are provided in the inner channels 801, 802, 803 or 804 of the middle chamber region 8. The ribs are not shown in the figure. They are used to enhance the convective heat transfer of the inner channels. Whether to arrange ribs depends on the actual volume of the inner channels 801, 802, 803 or 804. For example, ribs are provided in the first inner channel 801 and the second inner channel 802 of the middle chamber region 8. The ribs protrude from the inner wall of the inner channel into the inner channel. For example, the ratio of the size of the protruding rib to the size of the inner channel in the protruding direction is 1:(5 to 10).

[0092] like Figure 2 As shown, the outer channels of the front chamber region 7 and the middle chamber region 8 are provided only in portions of the pressure sidewall 4 and the suction sidewall 5, and these portions of the pressure sidewall 4 and the suction sidewall 5 with the outer channels are specific high heat load areas. In one or more other embodiments, the outer channels of the front chamber region 7 and the middle chamber region 8 are provided throughout the entire pressure sidewall 4 and the suction sidewall 5.

[0093] In the anterior chamber region 7 and the middle chamber region 8, the diameter of the impact hole 13 is, exemplary, 0.8–1.5 mm. In the anterior chamber region 7 and the middle chamber region 8, the number of impact holes 13 in each row is determined according to the volume of the internal channel they communicate with; exemplaryly, the number of impact holes in each row is 8–12. In the anterior chamber region 7 and the middle chamber region 8, the ratio of the diameter of the impact hole 13 communicating with the external channel to the impact distance of the external channel communicating with it is, exemplary, 1:(0.5–1). In the anterior chamber region 7 and the middle chamber region 8, the ratio of the diameter of the air film orifice 10 to the diameter of the impact hole 13 communicating with it is, exemplary, (0.4–0.6):1.

[0094] like Figure 2 As shown, the rear chamber region 9 has a plurality of internal channels that extend radially. Exemplarily, the rear chamber region 9 has two internal channels: a first rear internal channel 901 and a second rear internal channel 902.

[0095] Cooling air enters the first rear inner channel 901 through the rear cooling air channel inlet at the bottom of tenon 17. As shown in Figure 2, the first rear inner channel 901 is connected to the pressure side wall 4 through the air film hole 10. The air film hole 10 penetrates the wall of the pressure side wall 4, has an outlet located on the outer wall surface of the pressure side wall 4, and has an inlet connected to the first rear inner channel 901. Cooling air in the outer channel enters the air film hole 10 from the inlet, flows out from the outlet, and forms an air film on the outer wall surface of the pressure side wall 4. The air film holes 10 are arranged in a row radially.

[0096] like Figure 2As shown, the first rear inner passage 901 and the second rear inner passage 902 are communicated through the impingement holes 13 arranged radially on the wall between the first rear inner passage 901 and the second rear inner passage 902, the impingement holes 13 penetrating the wall, having an inlet communicating with the first rear inner passage 901 and an outlet communicating with the second rear inner passage 902, the cooling air in the first rear inner passage 901 flows into the impingement holes 13 from the inlet and flows out of the outlet to impinge and cool the second rear inner passage 902.

[0097] As shown in Figure 1 and Figure 2 , the airfoil 1 has a trailing edge split 19 at the trailing edge 3, and the second rear inner passage 902 has turbulence columns 18 arranged radially in rows, the turbulence columns 18 having two ends respectively connected to the two side walls of the second rear inner passage 902, the cooling air in the second rear inner passage 902 flows out of the trailing edge split 19 after impinging the turbulence columns 18. Exemplarily, the second rear inner passage 902 has one to three rows of turbulence columns 18 arranged in the chord direction.

[0098] In the present embodiment, the airfoil 1 is exemplarily a high-pressure turbine blade, in another embodiment or multiple embodiments, the airfoil 1 is another blade in a gas turbine.

[0099] Embodiment Two

[0100] Embodiment Two uses the element numbers and part of the content of Embodiment One, wherein the same numbers are used to represent the same or similar elements, and the same technical content is selectively omitted. The omitted part can refer to the description of Embodiment One, and Embodiment Two will not be repeated here.

[0101] Continuing to refer to Figure 2 , in the middle chamber region 8, the second middle inner passage 802 and the third middle inner passage 803 are no longer communicated through the rotation passage 16, but through the impingement holes 13 arranged radially on the wall between the second middle inner passage 802 and the third middle inner passage 803, the impingement holes 13 having an inlet communicating with the second middle inner passage 802 and an outlet communicating with the third middle inner passage 803, the cooling air in the second middle inner passage 802 flows into the impingement holes 13 from the inlet and flows out of the outlet to impinge and cool the third middle inner passage 803.

[0102] Embodiment Three

[0103] Embodiment Three uses the element numbers and part of the content of Embodiment One, and further refers to Figure 17 , wherein the same numbers are used to represent the same or similar elements, and the same technical content is selectively omitted. The omitted part can refer to the description of Embodiment One, and Embodiment Three will not be repeated here.

[0104] Figure 17The cross-sectional structure of the airfoil 1 of embodiment three at A-A is shown. Figure 1

[0105] As shown in Figure 17 , the middle chamber region 8 has a plurality of outer passages and a plurality of inner passages, the inner passages and the outer passages extend in the radial direction, exemplarily, the middle chamber region 8 has four inner passages: a fifth middle inner passage 809, a sixth middle inner passage 810, a seventh middle inner passage 811, and an eighth middle inner passage 812, and the middle chamber region 8 has three outer passages: a fourth middle outer passage 813, a fifth middle outer passage 814, and a sixth middle outer passage 815. The number of inner passages is not limited to four, and can be multiple, i.e. two or more than two, and the number of outer passages is not limited to three, and can be multiple, i.e. two or more than two. In the following description, “outer passage” refers to any one of the fourth middle outer passage 813, the fifth middle outer passage 814, and the sixth middle outer passage 815, and “inner passage” refers to any one of the fifth middle inner passage 809, the sixth middle inner passage 810, the seventh middle inner passage 811, and the eighth middle inner passage 812.

[0106] As shown in Figure 17 , each outer passage 813, 814, or 815 of the middle chamber region 8 is adjacent to one of the two side walls 4, 5 and communicates with the outer wall surface of the side wall 4 or 5 through the film hole 10, exemplarily, the fourth middle outer passage 813 is adjacent to the pressure side wall 4, the fifth middle outer passage 814 is adjacent to the pressure side wall 4, and the sixth middle outer passage 815 is adjacent to the suction side wall 5. The film hole 10 penetrates the outer layer wall 11, has an outlet on the outer wall surface of the side wall 4 or 5, and has an inlet communicating with the outer passage 813, 814, or 815, the cooling gas in the outer passage 813, 814, or 815 enters the film hole 10 from the inlet, and then flows out from the outlet and forms a gas film on the outer wall surface of the side wall 4 or 5, the film holes 10 are arranged in rows in the radial direction, the number of rows of film holes 10 and the number of film holes 10 in a single row are determined according to the volume of the outer passage 813, 814, or 815 or the volume of the inner passage 809, 812, or 811 and 810 communicating with the outer passage 813, 814, or 815, exemplarily, the outer layer wall 11 of each outer passage 813, 814, or 815 is provided with 1-2 rows of film holes 10, and the number of film holes 10 in a single row is 14-20.

[0107] Referring to Figure 17 ​, four inner passages 809, 810, 811, 812 are arranged inside three outer passages 813, 814, 815, wherein the fifth inner passage 809 is arranged inside the fourth outer passage 813, the sixth inner passage 810 and the seventh inner passage 811 are arranged inside the fifth outer passage 814, and the eighth inner passage 812 is arranged inside the sixth outer passage 815. Each outer passage 813, 814 or 815 is communicated with a corresponding inner passage 809, 812 or 810 and 811 through an impingement hole 13, and the "corresponding" means that the fourth outer passage 813 is communicated with the fifth inner passage 809, the fifth outer passage 814 is communicated with the sixth inner passage 810, and the fifth outer passage 814 is further communicated with the seventh inner passage 811, and the sixth outer passage 815 is communicated with the eighth inner passage 812. In each inner layer wall 12, the impingement hole 13 penetrates the inner layer wall 12, has an inlet communicated with the corresponding inner passage 809, 810, 811 or 812, and has an outlet communicated with the corresponding outer passage 813, 814 or 815, and the cooling gas in the inner passage 809, 810, 811 or 812 enters the impingement hole 13 from the inlet, and then flows out of the outlet to impact cool the outer passage 813, 814 or 815, and the impingement holes 13 are arranged in the radial direction (in the direction perpendicular to the paper surface) on the inner layer wall 12, and the volume of the inner passage 809, 810, 811 or 812 is determined according to the distribution requirement of the cooling gas. Figure 2

[0108] Referring to Figure 17 , each inner passage 809, 810, 811 or 812 communicated with the outer passage 813, 814 or 815 is only communicated with one outer passage 813, 814 or 815. In the embodiment shown in the figure, the fifth inner passage 809 is only communicated with the fourth outer passage 813, the sixth inner passage 810 is only communicated with the fifth outer passage 814, and the seventh inner passage 811 is only communicated with the fifth outer passage 814. The effect of such arrangement is consistent with the foregoing corresponding content, and will not be described here. Figure 17

[0109] The effects of the arrangement of the outer passages, the impingement holes 13 and the gas film holes 10 are consistent with the foregoing corresponding content, and will not be described here.

[0110] ​​Multiple inner channels 809, 810, 811, and 812 are connected by a rotary channel 16. The rotary channel 16 is located at the root 14 or at the end 15, and is arranged laterally along the intersecting radial directions to achieve the connection of multiple inner channels 809, 810, 811, and 812. For example, the fifth inner channel 809, the sixth inner channel 810, the seventh inner channel 811, and the eighth inner channel 812 are realized by three rotary channels 16. One rotary channel 16 is located at the end 15, connecting the top of the fifth inner channel 809 and the top of the sixth inner channel 810; one rotary channel 16 is located at the root 14, connecting the bottom of the sixth inner channel 810 and the bottom of the seventh inner channel 811; and one rotary channel 16 is located at the end 15, connecting the top of the seventh inner channel 811 and the top of the eighth inner channel 812.

[0111] The effects of setting up multiple inner channels and rotary channels 16 are the same as the corresponding content mentioned above, and will not be repeated here.

[0112] like Figure 17 As shown, the cooling air enters the fifth inner channel 809 through the intercooling air inlet 808 at the bottom of the tenon 17. That is, the cooling air enters the middle chamber region 8 through the inner channel connected to the outer channel adjacent to the pressure sidewall 4. The cooling air then enters the sixth inner channel 810 through the rotary channel 16 located at the end 15, then enters the seventh inner channel 811 through the rotary channel 16 located at the root 14, and finally enters the eighth inner channel 812 through the rotary channel 16 located at the end 15. This makes the flow sequence of the cooling air in the middle chamber region 8 include: the inner channel connected to the outer channel adjacent to the pressure sidewall 4, and the inner channel connected to the outer channel adjacent to the suction sidewall 5. The effect of this arrangement is consistent with the corresponding content mentioned above, and will not be repeated here.

[0113] A turbulence column 18 is installed in the outer channel of the middle chamber region 8 to turbulent the cooling gas and enhance heat exchange. The combination arrangement of the turbulence column 18 and the impact hole 13 is the same as the corresponding content mentioned above, and will not be repeated here.

[0114] Ribs are provided in the inner channels 809, 810, 811 or 812 of the middle chamber region 8. The ribs are not shown in the figure. They are used to enhance the convective heat transfer of the inner channels. Whether to arrange ribs depends on the actual volume of the inner channels 809, 810, 811 or 812. For example, ribs are provided in the fifth inner channel 809 and the sixth inner channel 810 of the middle chamber region 8. The ribs protrude from the inner wall of the inner channel into the inner channel. For example, the ratio of the size of the protruding rib to the size of the inner channel in the protruding direction is 1:(5 to 10).

[0115] Example 4

[0116] Embodiment four uses the same element numbers and some contents of embodiment one, and further refers to Figure 18 wherein the same numbers are used to represent the same or similar elements and repeated description on the same technical contents is omitted. The description on the omitted part can refer to embodiment one, and embodiment four will not be repeated here.

[0117] Figure 18 shows the cross-sectional structure of the airfoil 1 of embodiment four at A-A in Figure 1 .

[0118] As shown in Figure 18 , the front chamber region 7 has a plurality of outer passages and a plurality of inner passages, the inner passages and the outer passages extend in the radial direction, exemplarily, the front chamber region 7 has two inner passages: a fourth front inner passage 709, a fifth front inner passage 710, and the front chamber region 7 has three outer passages: a fourth front outer passage 711, a fifth front outer passage 712, a sixth front outer passage 713. The number of inner passages is not limited to two, and can be multiple, i.e. two or more than two, and the number of outer passages is not limited to three, and can be multiple, i.e. two or more than two. In the following description, “outer passage” refers to any one of the fourth front outer passage 711, the fifth front outer passage 712, and the sixth front outer passage 713, and “inner passage” refers to any one of the fourth front inner passage 709 and the fifth front inner passage 710.

[0119] As shown in Figure 18 , each outer passage 711, 712 or 713 is adjacent to one of the two side walls 4, 5 and communicates with the outer wall surface of the side wall 4 or 5 through the film hole 10, exemplarily, the fourth front outer passage 711 is adjacent to the pressure side wall 4, the fifth front outer passage 712 is adjacent to the suction side wall 5, and the sixth front outer passage 713 is adjacent to the suction side wall 5. The section of the side wall between the outer wall surface and the outer passage 711, 712 or 713 is often referred to as the outer layer wall 11, which corresponds to the inner layer wall 12 described later, the film hole 10 penetrates the outer layer wall 11, has an outlet on the outer wall surface of the side wall 4 or 5, and has an inlet communicating with the outer passage 711, 712 or 713, the cooling gas in the outer passage 711, 712 or 713 enters the film hole 10 from the inlet, and then flows out of the outlet and forms a gas film on the outer wall surface of the side wall 4 or 5, the film holes 10 are arranged in rows in the radial direction, and the number of rows of film holes 10 and the number of film holes 10 in a single row are determined according to the volume of the outer passage 711, 712 or 713 or the volume of the inner passage 709 or 710 communicating with the outer passage 711, 712 or 713, exemplarily, 1-2 rows of film holes 10 are arranged on the outer layer wall 11 of each outer passage 711, 712 or 713, and the number of film holes 10 in a single row is 14-20.

[0120] Referring to Figure 18Two inner channels 709 and 710 are disposed inside the three outer channels 711, 712 and 713. The fourth front inner channel 709 is disposed between the fourth front outer channel 711 and the fifth front outer channel 712, and the fifth front inner channel 710 is disposed inside the sixth front outer channel 713. This forms an inner wall 12 between each outer channel 711, 712 or 713 and the corresponding inner channel 709 or 710. Each outer channel 711, 712 or 713 corresponds to the inner channel 709 or 710 through an impact hole 13. The term "corresponds" means that the fourth front outer channel 711 is connected to the fourth front inner channel 709, the fifth front outer channel 712 is connected to the fourth front inner channel 709, and the sixth front outer channel 713 is connected to the fifth front inner channel 710. In each inner wall 12, an impact hole 13 penetrates the inner wall 12, having an inlet connecting to the corresponding inner channel 709 or 710, and an outlet connecting to the corresponding outer channel 711, 712, or 713. Cooling gas in the inner channel 709 or 710 enters the impact hole 13 from the inlet and then flows out from the outlet to the outer channel 711, 712, or 713 for impact cooling. The impact hole 13 is located radially on the inner wall 12 (in... Figure 2 Arranged perpendicular to the paper surface, the volume of the inner channels 709 or 710 is determined according to the cooling air distribution requirements.

[0121] The effects of the outer channel, impact hole 13 and air film hole 10 are the same as those described above, and will not be repeated here.

[0122] In addition to being connected to the fourth front inner channel 709 via the impact hole 13, the fifth front outer channel 712 is also connected to the fifth front inner channel 710 via the rotary channel 16. The rotary channel 16 is located at the root 14 or the end 15 and is arranged laterally along the intersecting radial direction, connecting the fifth front outer channel 712 and the fifth front inner channel 710.

[0123] The passageway configuration of the fourth front inner channel 709, the fifth front inner channel 710, and the fifth front outer channel 712 allows for sufficient flow of cooling air, enhances heat exchange, improves cooling effect, and increases cooling air utilization efficiency and cooling efficiency.

[0124] like Figure 18 As shown, the cooling air enters the fourth front inner channel 709 from the front cooling air channel inlet 708 at the bottom of the tenon 17. That is, the cooling air enters the front chamber region 7 from the inner channel connected to the outer channel adjacent to the pressure side wall 4. The cooling air then enters the fifth front inner channel 710 via the fifth front outer channel 712. This makes the flow sequence of the cooling air in the front chamber region 7 include: the inner channel connected to the outer channel adjacent to the pressure side wall 4, and the inner channel connected to the outer channel adjacent to the suction side wall 5. The effect of this arrangement is consistent with the corresponding content mentioned above, and will not be repeated here.

[0125] likeFigure 18 As shown, the front chamber region 7 further comprises a leading edge passage 707 adjacent to the leading edge 2 and communicating with the outer wall surface of the leading edge 2 through film holes 10, the film holes 10 penetrating the wall of the leading edge 2, having an inlet communicating with the leading edge passage 707 and having an outlet communicating with the outer wall surface of the leading edge 2, the cooling air in the leading edge passage 707 enters the film holes 10 from the inlet and flows out of the outlet to form a film on the outer wall surface of the leading edge 2. The film holes 10 are arranged in rows along the radial direction, the number of rows and the number of film holes 10 in a single row are determined according to the volume of the leading edge passage 707 or the volume of the inner passage communicated by the leading edge passage 707, and exemplarily, 4-8 rows of film holes 10 are provided, and the number of film holes 10 in a single row is 14-20. The leading edge passage 707 communicates with the inner passage communicated by the outer passage adjacent to the pressure side wall 4 through impingement holes 13, i.e. communicates with the fourth front inner passage 709, the impingement holes 13 are arranged in rows along the radial direction on the wall between the leading edge passage 707 and the fourth front inner passage 709, the impingement holes 13 have an inlet communicating with the fourth front inner passage 709 and an outlet communicating with the leading edge passage 707, the cooling air in the fourth front inner passage 709 enters the impingement holes 13 from the inlet and flows out of the outlet to impingement cool the leading edge passage 707, the fourth front inner passage 709 receives cooling air from the bottom, the cooling air flows radially upward, enters the leading edge passage 707 from the impingement holes 13, and at the same time enters the fifth front outer passage 712 from the impingement holes 13, the cooling air in the fifth front outer passage 712 enters the fifth front inner passage 710 from the return passage 16, which makes the flow sequence of the cooling air in the front chamber region 7 include: the inner passage communicated by the outer passage adjacent to the pressure side wall 4, the leading edge passage 707, the inner passage communicated by the outer passage adjacent to the suction side wall 5. The effect of such arrangement is consistent with the corresponding content described above, and will not be described here.

[0126] The outer passage of the front chamber region 7 is provided with turbulence columns 18 to disturb the cooling air and strengthen heat exchange, and the combination of the impingement holes 13 and the turbulence columns 18 is consistent with the corresponding content described above, and will not be described here.

[0127] The inner passage 709 or 710 of the front chamber region 7 is provided with ribs, which are not shown in the figure, and are used to strengthen the convective heat exchange of the inner passage, whether the ribs are arranged or not is determined according to the actual volume of the inner passage 709 or 710, and exemplarily, the fourth front inner passage 709 of the front chamber region 7 is provided with ribs, the ribs protrude into the inner passage from the inner wall of the inner passage, and exemplarily, the ratio of the protruding size of the ribs to the size of the inner passage in the protruding direction is 1:(5-10).

[0128] As Figure 18As shown, the middle chamber region 8 has multiple external channels and multiple internal channels extending radially. Exemplarily, the middle chamber region 8 has three internal channels: a ninth internal channel 816, a tenth internal channel 817, and an eleventh internal channel 818, and three external channels: a seventh external channel 819, an eighth external channel 820, and a ninth external channel 821. The number of internal channels is not limited to three; it can be multiple, i.e., two or more. The number of external channels is not limited to three; it can be multiple, i.e., two or more. In the following description, "external channel" refers to any one of the seventh external channel 819, the eighth external channel 820, and the ninth external channel 821, and "internal channel" refers to any one of the ninth internal channel 816, the tenth internal channel 817, and the eleventh internal channel 818.

[0129] like Figure 18 As shown, each outer channel 819, 820 or 821 of the middle chamber region 8 is adjacent to one of the two sidewalls 4 and 5 and is connected to the outer wall surface of the sidewall 4 or 5 through the air film hole 10. For example, the seventh middle outer channel 819 is adjacent to the pressure sidewall 4, the eighth middle outer channel 820 is adjacent to the pressure sidewall 4, and the ninth middle outer channel 821 is adjacent to the suction sidewall 5. The air film hole 10 penetrates the outer wall 11, has an outlet located on the outer wall surface of the side wall 4 or 5, and has an inlet communicating with the outer channel 819, 820 or 821. Cooling gas in the outer channel 819, 820 or 821 enters the air film hole 10 from the inlet, flows out from the outlet, and forms an air film on the outer wall surface of the side wall 4 or 5. The air film holes 10 are arranged in rows radially. The number of rows of air film holes 10 and the number of single-row air film holes 10 are determined according to the volume of the outer channel 819, 820 or 821 they communicate with or the volume of the inner channel 816, 817 or 818 communicating with the outer channel 819, 820 or 821. For example, each outer wall 11 of the outer channel 819, 820 or 821 is provided with 1 to 2 air film holes 10, and the number of single-row air film holes 10 is 14 to 20.

[0130] Reference Figure 18three inner channels 816, 817, 818 are correspondingly arranged inside three outer channels 819, 820, 821, each outer channel 819, 820 or 821 is communicated with a corresponding inner channel 816, 817 or 818 through an impact hole 13, the "corresponding" means that the seventh outer channel 819 is communicated with the ninth inner channel 816, the eighth outer channel 820 is communicated with the tenth inner channel 817, and the ninth outer channel 821 is communicated with the eleventh inner channel 818. In each inner layer wall 12, the impact hole 13 penetrates the inner layer wall 12, has an inlet communicated with a corresponding inner channel 816, 817 or 818, and has an outlet communicated with a corresponding outer channel 819, 820 or 821, cooling gas in the inner channel 816, 817 or 818 enters the impact hole 13 from the inlet, and then flows out of the outlet to impact cool the outer channel 819, 820 or 821, the impact hole 13 is arranged on the inner layer wall 12 in the radial direction (in the direction perpendicular to the paper surface), and the volume of the inner channel 816, 817 or 818 is determined according to the distribution requirement of the cooling gas. Figure 2

[0131] Referring to Figure 18 , each inner channel 816, 817 or 818 communicated with an outer channel 819, 820 or 821 is only communicated with one outer channel 819, 820 or 821. In Figure 18 the embodiment shown, the ninth inner channel 816 is only communicated with the seventh outer channel 819, the tenth inner channel 817 is only communicated with the eighth outer channel 820, and the eleventh inner channel 818 is only communicated with the ninth outer channel 821. The effect of such arrangement is consistent with the foregoing corresponding content, and will not be described here.

[0132] The effects of the outer channels, the impact holes 13 and the gas film holes 10 are consistent with the foregoing corresponding content, and will not be described here.

[0133] The plurality of inner channels 816, 817, 818 are communicated through the rotary channels 16, the rotary channels 16 are arranged at the root 14 or at the tip 15, and are arranged in the transverse direction intersecting the radial direction, so as to realize the communication of the plurality of inner channels 816, 817, 818. Exemplarily, the ninth inner channel 816, the tenth inner channel 817 and the eleventh inner channel 818 are communicated through two rotary channels 16, wherein one rotary channel 16 is arranged at the tip 15 and communicates the top of the ninth inner channel 816 and the top of the tenth inner channel 817, and the other rotary channel 16 is arranged at the root 14 and communicates the bottom of the tenth inner channel 817 and the bottom of the eleventh inner channel 818.

[0134] The effects of the plurality of inner channels and the rotary channels 16 are consistent with the foregoing corresponding content, and will not be described here.

[0135] ​The cooling gas enters the ninth inner channel 816 from the middle cooling gas passage inlet 808 at the bottom of the tenon 17, i.e. the cooling gas enters the middle chamber region 8 from the inner channel communicating with the outer channel adjacent to the pressure side wall 4, and then enters the tenth inner channel 817 via the rotation channel 16 at the tip 15, and then enters the eleventh inner channel 818 via the rotation channel 16 at the root 14, so that the flow sequence of the cooling gas in the middle chamber region 8 includes: the inner channel communicating with the outer channel adjacent to the pressure side wall 4, the inner channel communicating with the outer channel adjacent to the suction side wall 5. The effect of such arrangement is consistent with the foregoing corresponding content, and will not be described here.

[0136] The outer channel of the middle chamber region 8 is provided with a turbulence column 18 for turbulence of the cooling gas and heat exchange enhancement. The combined arrangement of the turbulence column 18 and the impact hole 13 is consistent with the foregoing corresponding content, and will not be described here.

[0137] The inner channel 816, 817 or 818 of the middle chamber region 8 is provided with a rib, which is not shown in the figure, for convective heat exchange enhancement of the inner channel. Whether the rib is arranged or not is determined according to the actual volume size of the inner channel 816, 817 or 818. Exemplarily, the ninth inner channel 816 of the middle chamber region 8 is provided with a rib, which protrudes from the inner wall of the inner channel into the inner channel. Exemplarily, the ratio of the protruding size of the rib to the size of the inner channel in the protruding direction is 1:(5-10).

[0138] Although the present application is disclosed with the above embodiments, it is not intended to limit the present application, and any person skilled in the art can make possible changes and modifications without departing from the spirit and scope of the present application.

Claims

1. An airfoil having a leading edge, a trailing edge, and two sidewalls enclosing a hollow cavity for cooling airflow, the two sidewalls including a pressure sidewall and a suction sidewall, characterized by, The cavity comprises a plurality of chamber regions separated from each other, at least one of the plurality of chamber regions has a plurality of outer passages and a plurality of inner passages, each of the outer passages is adjacent to one of the two side walls and communicates with the outer wall surface of the side wall through a film hole, the plurality of inner passages is arranged inside the plurality of outer passages, each of the outer passages communicates with the inner passage through an impingement hole, the cooling gas enters the chamber region from the inner passage communicated by the outer passage adjacent to the pressure side wall; In at least one of the chamber regions, the flow sequence of the cooling gas comprises: the inner passage communicated by the outer passage adjacent to the pressure side wall, the inner passage communicated by the outer passage adjacent to the suction side wall; Wherein, At least one of the plurality of chamber regions comprises a front chamber region, the front chamber region further comprises a leading edge passage; The leading edge passage is adjacent to the leading edge and communicates with the outer wall surface of the leading edge through a film hole, the leading edge passage communicates with the inner passage communicated by the outer passage adjacent to the pressure side wall through an impingement hole; The flow sequence of the cooling gas in the front chamber region comprises: the inner passage communicated by the outer passage adjacent to the pressure side wall, the leading edge passage, the inner passage communicated by the outer passage adjacent to the suction side wall.

2. The airfoil of claim 1, wherein, Each of the inner passages communicated with the outer passages only communicates with one of the outer passages.

3. The airfoil of claim 1, wherein, The airfoil further has a root and a tip, the airfoil extends radially from the root to the tip, the inner passages and the outer passages extend along the radial direction; The plurality of inner passages are communicated through a rotation passage, the rotation passage is arranged at the root or arranged at the tip.

4. The airfoil of claim 1, wherein, A spoiler column is arranged in the outer passage.

5. The airfoil of claim 1, wherein, A rib is arranged in the inner passage.

6. The airfoil of Claim 1, wherein, The plurality of inner passages of the front chamber region communicate with the outer passage adjacent to the suction side wall, wherein at least one of the inner passages is in front in chordwise direction and the other inner passage is in rear in chordwise direction, the flow sequence of the cooling gas in the front chamber region comprises: the inner passage in front in chordwise direction, the inner passage in rear in chordwise direction.

7. The airfoil of any one of claims 1-5, wherein, At least one of the plurality of chamber regions comprises a middle chamber region.

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