Airfoil and turbine engine

Abstract

An airfoil and a turbine engine are used for improving the cooling effect. The airfoil comprises a front cavity area, a middle cavity area and a rear cavity area which are arranged in the chordwise direction from the front edge to the tail edge. The middle cavity area comprises a suction side cavity and a pressure side cavity which are transversely arranged from the suction side wall to the pressure side wall, the suction side cavity and the pressure side cavity extend in the radial direction from the blade root to the blade top, and the suction side cavity and the pressure side cavity are communicated through a first rotary channel. The first rotary channel is located at the top or the bottom of the suction side cavity and the pressure side cavity and used for cooling fluid to flow from the suction side cavity to the pressure side cavity through the first rotary channel.

Description

Technical Field

[0001] This invention relates to cooling design, specifically to an airfoil and a turbine engine. Background Technology

[0002] In aero-engines, the high-pressure turbine is located downstream of the combustion chamber outlet, directly subjected to the impact of high-temperature combustion gases. It bears a high heat load and operates under extremely harsh conditions. Currently, the inlet temperature of aero-engine high-pressure turbines can reach up to 2000K, far exceeding the allowable temperature of the turbine blade metal. Therefore, efficient cooling designs are essential to ensure the turbine blades operate stably for extended periods. The key issue in efficient cooling technology for high-pressure turbine blades is how to rationally design the internal cooling structure of the high-pressure turbine blades based on the external heat exchange conditions, minimizing the temperature and temperature gradient of the high-pressure turbine blades within a limited cooling gas volume, and thus extending their service life. Summary of the Invention

[0003] The purpose of this invention is to provide an airfoil and a turbine engine for improving cooling performance.

[0004] In a first aspect, the present invention provides an airfoil. According to an embodiment of the present invention, the airfoil includes a front chamber region, a middle chamber region, and a rear chamber region arranged chordally from the leading edge to the trailing edge. The middle chamber region includes a suction side chamber and a pressure side chamber arranged laterally from the suction side wall to the pressure side wall. The suction side chamber and the pressure side chamber extend radially from the blade root to the blade tip. The suction side chamber and the pressure side chamber are connected by a first rotating channel. The first rotating channel is located at the top or bottom of the suction side chamber and the pressure side chamber, and is used for cooling fluid to flow from the suction side chamber to the pressure side chamber through the first rotating channel.

[0005] In one or more embodiments, the lateral width of the suction-side chamber is smaller than the lateral width of the pressure-side chamber.

[0006] In one or more embodiments, the middle chamber region is provided with a plurality of suction-side chambers, at least a portion of the suction-side chambers are located on the posterior side of the larynx, and the suction-side chambers located on the posterior side of the larynx are closed by the suction sidewall; the pressure-side chambers are connected to an air film pore penetrating the pressure sidewall.

[0007] In one or more embodiments, a portion of the suction-side chamber is located in the larynx or anterior to the larynx, and the suction-side chamber located in the larynx and anterior to the larynx communicates with an air film pore penetrating the suction-side wall.

[0008] In one or more embodiments, the suction-side chamber located in front of the throat and the suction-side chamber located behind the throat are connected by a second rotary channel located at the top or bottom of the suction-side chamber, for cooling fluid to flow from the suction-side chamber located in front of the throat to the suction-side chamber located behind the throat via the second rotary channel.

[0009] In one or more embodiments, each of the middle chamber regions includes at least one end of the pressure-side chamber, the end of the pressure-side chamber being the last chamber in the middle chamber region into which the cooling fluid flows from bottom to top.

[0010] In one or more embodiments, at least one of the suction-side chambers is provided with a first cooling fluid inlet at the bottom for cooling fluid to enter the middle chamber region from the first cooling fluid inlet.

[0011] In one or more embodiments, the ratio of the chordal length of the suction-side chamber to the lateral width of the suction-side chamber ranges from 1 to 4:1.

[0012] In one or more embodiments, the chordal length of the suction-side chamber is greater than or equal to the chordal length of the walls on both sides of the suction-side chamber.

[0013] In one or more embodiments, the anterior chamber region includes a leading edge inner chamber extending radially from the blade root to the blade tip for cooling fluid to flow from bottom to top, the leading edge inner chamber being located on the pressure side of the throat and the suction-side chamber anterior to the throat.

[0014] In one or more embodiments, a plurality of radially arranged impact holes are provided between the leading edge inner chamber and the throat and the suction side chamber on the front side of the throat, for cooling fluid to flow from the leading edge inner chamber through the impact holes to the throat and the suction side chamber on the front side of the throat, thereby achieving impact cooling.

[0015] In one or more embodiments, the front chamber region further includes a leading edge outer chamber, which extends radially from the blade root to the blade tip and is located between the leading edge wall, the pressure sidewall, the suction sidewall, and the leading edge inner chamber; an impact hole is provided between the leading edge outer chamber and the leading edge inner chamber for cooling fluid to flow from the leading edge inner chamber through the impact hole to the leading edge outer chamber, thereby achieving impact cooling; the leading edge outer chamber is connected to a film pore penetrating the leading edge wall, the pressure sidewall, and the suction sidewall.

[0016] In one or more embodiments, the leading edge inner chamber is provided with a second cooling fluid inlet at the bottom for cooling fluid to enter the leading chamber region from the second cooling fluid inlet.

[0017] In one or more embodiments, the front chamber region includes a leading edge inner chamber and a leading edge outer chamber, both of which extend radially from the blade root to the blade tip. The leading edge outer chamber is located between the leading edge wall, the pressure sidewall, the suction sidewall, and the leading edge inner chamber. The leading edge inner chamber is used for cooling fluid to flow from bottom to top. An impact hole is provided between the leading edge outer chamber and the leading edge inner chamber for cooling fluid to flow from the leading edge inner chamber through the impact hole to the leading edge outer chamber, thereby achieving impact cooling. The leading edge outer chamber is connected to a film pore penetrating the leading edge wall, the pressure sidewall, and the suction sidewall.

[0018] In one or more embodiments, the rear chamber region includes a trailing edge chamber extending radially from the blade root to the blade tip for cooling fluid to flow from bottom to top. The suction side chamber and the trailing edge chamber are connected by a third rotary channel located at the top of the suction side chamber and the trailing edge chamber for cooling fluid to flow from the trailing edge chamber to the suction side chamber via the third rotary channel.

[0019] In one or more embodiments, the trailing edge chamber communicates with a film pore penetrating the pressure sidewall, and the trailing edge chamber is closed by the suction sidewall.

[0020] In one or more embodiments, at least one of the trailing edge chambers communicates with the trailing edge slit.

[0021] Secondly, the present invention provides a turbine engine, wherein, according to an embodiment of the present invention, the turbine engine includes the airfoil described above.

[0022] The embodiments of the present invention possess at least one of the following beneficial effects:

[0023] The cooling fluid first cools the suction-side blade in the suction-side chamber, and then enters the pressure-side chamber to cool the pressure-side blade. As the cooling fluid flows, the temperature increases and the pressure decreases. Therefore, the cooling fluid first cools the suction-side blade, which improves the cooling effect on the suction-side blade. Without increasing the amount of cooling fluid used, the high temperature of the suction-side blade is reduced, thereby reducing the temperature gradient of the high-pressure turbine blade and improving the service life of the high-pressure turbine blade. Attached Figure Description

[0024] The above and other features, properties and advantages of the present invention will become more apparent from the following description taken in conjunction with the accompanying drawings and embodiments, wherein:

[0025] Figure 1 A three-dimensional view of the moving blades of a high-pressure turbine;

[0026] Figure 2 As an example of a high-pressure turbine blade in Figure 1 Cross-sectional view at point AA;

[0027] Figure 3 for Figure 2 Flow diagram of the intermediate chamber region of a high-pressure turbine blade;

[0028] Figure 4 for Figure 2 Flow diagram of the intermediate chamber region of a high-pressure turbine blade;

[0029] Figure 5 For another embodiment of the high-pressure turbine blades Figure 1 Cross-sectional view at point AA;

[0030] Figure 6 For yet another embodiment of the high-pressure turbine blades in Figure 1 Cross-sectional view at point AA;

[0031] Figure 7 for Figure 6 Flow diagram of the first intermediate chamber region of the high-pressure turbine blade;

[0032] Figure 8 For another embodiment of the high-pressure turbine blades in Figure 1 Cross-sectional view at point AA;

[0033] Figure label:

[0034] 1-High-pressure turbine blades;

[0035] 2-Air film pores;

[0036] 3-Leading edge;

[0037] 3a - Leading edge wall;

[0038] 4-Caudal margin;

[0039] 5-Suction sidewall;

[0040] 6-Pressure sidewall;

[0041] 7-Leaf root;

[0042] 8-Leaf tip;

[0043] 9-Anterior chamber region;

[0044] 9a-Leading edge chamber;

[0045] 9b - Leading edge outer chamber;

[0046] 10 - First intermediate chamber region;

[0047] 10a - The first suction side chamber of the first middle chamber region;

[0048] 10b - The second suction side chamber in the first middle chamber region;

[0049] 10c - The third suction side chamber in the first middle chamber region;

[0050] 10d - The fourth suction side chamber in the first middle chamber region;

[0051] 10e - The first pressure-side chamber in the first intermediate chamber region;

[0052] 10f - The second pressure-side chamber in the first intermediate chamber region;

[0053] 10g - the third pressure side chamber of the first intermediate chamber region;

[0054] 10h - The first rotating passage in the first intermediate chamber area;

[0055] 10i - The second rotary passage in the first middle chamber region;

[0056] 11-Second middle chamber region;

[0057] 11a - The first suction side chamber of the second middle chamber region;

[0058] 11b - The second suction side chamber in the second middle chamber region;

[0059] 11c - The third suction side chamber in the second middle chamber region;

[0060] 11d - The pressure-side chamber of the second intermediate chamber region;

[0061] 11e - The first rotary passage in the second middle chamber region;

[0062] 12-Posterior chamber region;

[0063] 12a-Caudal chamber;

[0064] 12b - Third turning passage;

[0065] 13 - First cooling fluid inlet;

[0066] 14 - Impact hole;

[0067] 15- Tail edge split;

[0068] 16-Tenon. Detailed Implementation

[0069] 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.

[0070] 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.

[0071] 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.

[0072] An airfoil is installed inside the turbine engine as the turbine blade. In one embodiment, the gas turbine engine uses an airfoil as the moving blade of the high-pressure turbine. The high-temperature, high-pressure gas impacts the moving blade of the high-pressure turbine to do work, thereby converting the thermal energy of the gas into mechanical energy. Figure 1 The external structure of a high-pressure turbine blade 1 is shown, with some external structures omitted, such as the film gas vent 2 described later. Figure 1 As shown, the high-pressure turbine blade 1 has a leading edge 3, a trailing edge 4, a suction sidewall 5, a pressure sidewall 6, a blade root 7, and a blade tip 8. The chord direction is the central axis from the leading edge 3 to the trailing edge 4, and is parallel to... Figure 2 , Figure 5 , Figure 6 and Figure 8 The mid-arc lines of the cross-sectional shape of the high-pressure turbine blade 1 shown coincide, with the azimuthal description "front" pointing chordally towards the leading edge 3, and the azimuthal description "rear" pointing chordally towards the trailing edge 4. The radial direction extends from the blade root 7 to the blade tip 8, with the azimuthal descriptions "top" and "upper" pointing radially towards the blade tip 8, and the azimuthal descriptions "bottom" and "lower" pointing radially towards the blade root 7. The transverse direction extends from the suction sidewall 5 to the pressure sidewall 6, and is perpendicular to both the chordal and radial directions. Figure 1 AA in the diagram shows Figure 2 , Figure 5 , Figure 6 and Figure 8 The cutting surface is perpendicular to the radial direction. Figure 2 , Figure 5 , Figure 6 and Figure 8 The internal cooling chamber structure of the high-pressure turbine blade 1 in different embodiments is shown.

[0073] like Figure 2 , Figure 5 , Figure 6 and Figure 8 As shown, the cooling chamber structure of the high-pressure turbine blade 1 includes a front chamber region 9, middle chamber regions 10 and 11, and a rear chamber region 12. The front chamber regions 9, middle chamber regions 10 and 11, and rear chamber region 12 are arranged chordally from the leading edge 3 to the trailing edge 4. The front chamber region 9 is located in front of the middle chamber regions 10 and 11, and the middle chamber regions 10 and 11 are located in front of the rear chamber region 12. The front chamber region 9 is used to cool the leading edge 3 and the blade body between the suction sidewall 5 and the pressure sidewall 6 adjacent to the leading edge 3. The rear chamber region 12 is used to cool the trailing edge 4 and the blade body between the suction sidewall 5 and the pressure sidewall 6 adjacent to the trailing edge 4. The middle chamber regions 10 and 11 are used to cool the middle section of the blade body. The high-pressure turbine blade 1 may have one or more middle chamber regions, and the cooling fluid does not flow between different middle chamber regions. Figure 2 , Figure 5 In the illustrated embodiment, the high-pressure turbine blade 1 has only one intermediate chamber region, namely the first intermediate chamber region 10. Figure 6 and Figure 8 In the embodiment shown, the high-pressure turbine blade 1 is provided with two intermediate chamber regions, namely a first intermediate chamber region 10 and a second intermediate chamber region 11. The cooling fluid in the first intermediate chamber region 10 does not flow into the second intermediate chamber region 11, and the cooling fluid in the second intermediate chamber region 11 does not flow into the first intermediate chamber region 10.

[0074] like Figure 2 , Figure 5 , Figure 6 and Figure 8 As shown, each intermediate chamber region 10(11) includes suction-side chambers 10a-10d (11a-11c) and pressure-side chambers 10e-10g (11d). The suction-side chambers 10a-10d (11a-11c) and the pressure-side chambers 10e-10g (11d) are arranged laterally from the suction-side wall 5 to the pressure-side wall 6. The suction-side chambers 10a-10d (11a-11c) are located on the suction side of the pressure-side chambers 10e-10g (11d), and the pressure-side chambers 10e-10g (11d) are located on the pressure side of the suction-side chambers 10a-10d (11a-11c). The suction-side chambers 10a-10d (11a-11c) are used to cool the blade adjacent to the suction-side wall 5, and the pressure-side chambers 10e-10g (11d) are used to cool the blade adjacent to the pressure-side wall 6. For Figure 2 Further integration Figure 3 and Figure 4 ,for Figure 6 Further integration Figure 7 And continue to refer to Figure 5 and Figure 8Each intermediate chamber region 10(11) has suction-side chambers 10a-10d (11a-11c) and pressure-side chambers 10e-10g (11d) extending radially. The suction-side chambers 10a-10d (11a-11c) and pressure-side chambers 10e-10g (11d) in each intermediate chamber region 10(11) are connected by a first rotary channel 10h (11e). The first rotary channel 10h (11e) is located at the top or bottom of the suction-side chambers 10a-10d (11a-11c) and pressure-side chambers 10e-10g (11d) for cooling fluid to flow from the suction-side chambers 10a-10d (11a-11c) through the first rotary channel 10h (11e) to the pressure-side chambers 10e-10g (11d). The pressure side wall 5 of the high-pressure turbine blade 1 is often cooled by film cooling, but the suction side wall 5 of the high-pressure turbine blade 1 often uses less film cooling to reduce aerodynamic losses. This makes the blade body adjacent to the suction side wall 5 more prone to local high heat load areas compared to the blade body adjacent to the pressure side wall 6. In the embodiment of the present invention, the cooling fluid first cools the suction side blade body in the suction side chambers 10a to 10d (11a to 11c), and then enters the pressure side chambers 10e to 10g (11d) to cool the pressure side blade body. As the flow temperature of the cooling fluid increases and the pressure decreases, the cooling fluid first cools the suction side blade body to improve the cooling effect on the suction side blade body. Without increasing the amount of cooling fluid used, the high temperature of the suction side blade body is reduced, thereby reducing the temperature gradient of the high-pressure turbine blade 1 and improving the service life of the high-pressure turbine blade 1.

[0075] Each intermediate chamber region 10(11) may be provided with one or more suction-side chambers 10a-10d (11a-11c) and one or more pressure-side chambers 10e-10g (11d). Figure 2 In the illustrated embodiment, the first intermediate chamber region 10 is provided with three suction-side chambers 10a-10c and two pressure-side chambers 10e and 10f. Figure 5 In the illustrated embodiment, the first intermediate chamber region 10 is provided with four suction-side chambers 10a-10d and three pressure-side chambers 10e-10g. Figure 6 In the illustrated embodiment, the first intermediate chamber region 10 is provided with three suction-side chambers 10a-10c and one pressure-side chamber 10e, and the second intermediate chamber region 11 is provided with two suction-side chambers 11a and 11b and one pressure-side chamber 11d. Figure 8 In the embodiment shown, the first middle chamber region 10 is provided with three suction-side chambers 10a to 10c and one pressure-side chamber 10e, and the second middle chamber region 11 is provided with three suction-side chambers 11a to 11c and one pressure-side chamber 11d.

[0076] Cooling fluid can flow sequentially or in parallel between the multiple suction-side chambers 10a–10d (11a–11c) in each intermediate chamber region 10(11). Figure 2 In the illustrated embodiment, cooling fluid flows in parallel between the three suction-side chambers 10a-10c, while a single stream of cooling fluid flows in three separate paths within each of the three suction-side chambers 10a-10c. Figure 5 In the illustrated embodiment, cooling fluid flows in parallel between the four suction-side chambers 10a to 10d, while a single stream of cooling fluid splits into four separate streams flowing within each of the four suction-side chambers 10a to 10d. Figure 6 In the illustrated embodiment, in the first middle chamber region 10, cooling fluid flows sequentially between the first suction-side chamber 10a, the second suction-side chamber 10b, and the third suction-side chamber 10c; cooling fluid flows in parallel between the second suction-side chamber 10b and the third suction-side chamber 10c; and a stream of cooling fluid in the first suction-side chamber 10a splits into two streams, flowing into the second suction-side chamber 10b and the third suction-side chamber 10c respectively. Figure 6 In the illustrated embodiment, in the second middle chamber region 11, cooling fluid flows sequentially between the first suction-side chamber 11a and the second suction-side chamber 11b, with the cooling fluid in the first suction-side chamber 11a flowing into the second suction-side chamber 11b. Figure 8 In the illustrated embodiment, in the first middle chamber region 10, cooling fluid flows sequentially between the first suction-side chamber 10a, the second suction-side chamber 10b, and the third suction-side chamber 10c; cooling fluid flows in parallel between the second suction-side chamber 10b and the third suction-side chamber 10c; and a stream of cooling fluid in the first suction-side chamber 10a splits into two streams, flowing into the second suction-side chamber 10b and the third suction-side chamber 10c respectively. Figure 8 In the illustrated embodiment, in the second middle chamber region 11, cooling fluid flows sequentially between the first suction-side chamber 11a and the second suction-side chamber 11b. Cooling fluid in the first suction-side chamber 11a flows into the second suction-side chamber 11b. Cooling fluid in the third suction-side chamber 11c is not from the same source as the first suction-side chamber 11a and the second suction-side chamber 11b, nor does it receive cooling fluid from the first suction-side chamber 11a and the second suction-side chamber 11b, as detailed below.

[0077] Multiple suction-side chambers 10a-10d (11a-11c) in which cooling fluid flows sequentially can be connected by a rotary channel. The rotary channel can be located at the top or bottom of the suction-side chambers 10a-10d (11a-11c), and its structure can refer to the first rotary channel 10h (11e).

[0078] Cooling fluid can flow sequentially or in parallel between the multiple pressure-side chambers 10e to 10g (11d) in each intermediate chamber region 10 (11). Figure 2 In the illustrated embodiment, cooling fluid flows sequentially between the first pressure-side chamber 10e and the second pressure-side chamber 10f, with the cooling fluid in the first pressure-side chamber 10e flowing into the second pressure-side chamber 10f. Figure 5 In the embodiment shown, the cooling fluid flows sequentially between the first pressure-side chamber 10e, the second pressure-side chamber 10f, and the third pressure-side chamber 10g, while the cooling fluid flows in parallel between the second pressure-side chamber 10f and the third pressure-side chamber 10g. A stream of cooling fluid in the first pressure-side chamber 10e splits into two streams and flows into the second pressure-side chamber 10f and the third pressure-side chamber 10g, respectively.

[0079] Multiple pressure-side chambers 10e to 10g (11d) in which cooling fluid flows sequentially can be connected by a rotary channel. The rotary channel can be located at the top or bottom of the pressure-side chambers 10e to 10g (11d), and its structure can refer to the first rotary channel 10h (11e).

[0080] The pressure-side chambers 10e–10g (11d) in each intermediate chamber region 10(11) can receive cooling fluid from one or more suction-side chambers 10a–10d (11a–11c). Figure 2 In the illustrated embodiment, the first pressure-side chamber 10e receives cooling fluid from three suction-side chambers 10a-10c. Figure 5 In the illustrated embodiment, the first pressure-side chamber 10e receives cooling fluid from four suction-side chambers 10a-10d. Figure 6 In the illustrated embodiment, in the first intermediate chamber region 10, the first pressure-side chamber 10e receives cooling fluid from two suction-side chambers 10b and 10c. Figure 6 In the illustrated embodiment, in the second intermediate chamber region 11, the pressure-side chamber 11d receives cooling fluid from a suction-side chamber 11b. Figure 8 In the illustrated embodiment, in the first intermediate chamber region 10, the first pressure-side chamber 10e receives cooling fluid from two suction-side chambers 10b and 10c. Figure 8 In the illustrated embodiment, in the second intermediate chamber region 11, the pressure-side chamber 11d receives cooling fluid from two suction-side chambers 11b and 11c.

[0081] Continue to refer to Figure 2 , Figure 5 , Figure 6 and Figure 8In each intermediate chamber region 10 (11), the lateral width of the suction side chambers 10a to 10d (11a to 11c) can be smaller than the lateral width of the pressure side chambers 10e to 10g (11d), so that the lateral distance from the inner wall of the suction side chambers 10a to 10d (11a to 11c) to the suction side wall 5 is smaller than the lateral distance from the inner wall of the pressure side chambers 10e to 10g (11d) to the pressure side wall 6. This enhances the heat exchange of cooling fluid between the suction side chambers 10a to 10d (11a to 11c) and the suction side wall 5, reduces the lateral temperature difference of the suction side blade, improves the cooling effect on the suction side blade, and reduces the high temperature of the suction side blade without increasing the amount of cooling fluid used, thereby reducing the temperature gradient of the high pressure turbine blade 1 and improving the working life of the high pressure turbine blade 1.

[0082] like Figure 2 , Figure 5 , Figure 6 and Figure 8 As shown, in an embodiment where multiple suction-side chambers 10a-10d (11a-11c) are provided in the middle chamber region 10 (11), at least some of the suction-side chambers 10a-10d (11a-11c) can be located on the rear side of the throat, where the throat is located at the chordal position with the smallest gas flow area between two circumferentially adjacent high-pressure turbine blades 1. The suction-side chambers 10a-10d (11a-11c) located on the rear side of the throat are closed by suction sidewalls 5, and the suction sidewalls 5 on the lateral upper outer side of the suction-side chambers 10a-10d (11a-11c) are not provided with film cooling holes, thereby reducing the aerodynamic losses of the high-pressure turbine blades 1. Figure 2 In the illustrated embodiment, all three suction side chambers 10a-10c are located posterior to the larynx, and all three suction side chambers 10a-10c are sealed by suction sidewalls 5. The suction sidewalls 5 on the lateral upper outer sides of the three suction side chambers 10a-10c do not have air film pores. Figure 5 In the illustrated embodiment, all four suction side chambers 10a-10d are located on the posterior side of the larynx, and all four suction side chambers 10a-10d are sealed by suction sidewalls 5. The suction sidewalls 5 on the transversely upper outer sides of the four suction side chambers 10a-10d do not have air film pores. Figure 6 In the illustrated embodiment, one suction-side chamber 10a is located in the larynx and anterior to the larynx, while the remaining four suction-side chambers 10b, 10c, 11a, and 11b are located posterior to the larynx. All four suction-side chambers 10b, 10c, 11a, and 11b are enclosed by suction-side walls 5. The suction-side walls 5 on the lateral upper outer sides of the four suction-side chambers 10b, 10c, 11a, and 11b do not have air film pores. Figure 8In the illustrated embodiment, one suction side chamber 10a is located in the larynx and the front side of the larynx, and the other five suction side chambers 10b, 10c, 11a, 11b, and 11c are located in the posterior side of the larynx. All five suction side chambers 10b, 10c, 11a, 11b, and 11c are closed by suction side walls 5. The suction side walls 5 on the lateral upper outer sides of the five suction side chambers 10b, 10c, 11a, 11b, and 11c are not provided with air film holes.

[0083] like Figure 2 , Figure 5 , Figure 6 and Figure 8 As shown, the pressure-side chambers 10e to 10g (11d) are connected to the film cooling holes 2 penetrating the pressure-side wall 6. Cooling fluid flows out from the film cooling holes 2 through the pressure-side chambers 10e to 10g (11d), forming a cooling film on the pressure-side wall 6, suppressing heat exchange between the high-temperature combustion gas and the pressure-side wall 6, and improving the cooling effect. Figure 2 , Figure 5 , Figure 6 and Figure 8 In the embodiment shown, each pressure-side chamber 10e to 10g (11d) is provided with an air film hole 2.

[0084] Continue to refer to Figure 6 and Figure 8 In an embodiment where multiple suction-side chambers 10a-10d (11a-11c) are provided in the middle chamber region 10 (11), at least some of the suction-side chambers 10a-10d (11a-11c) can be located in the throat or in front of the throat. The suction-side chambers 10a-10d (11a-11c) located in the throat and in front of the throat are connected to the air film holes 2 penetrating the suction side wall 5. Cooling fluid flows out from the air film holes 2 from the suction-side chambers 10a-10d (11a-11c) located in the throat and in front of the throat, forming a cooling air film on the suction side wall 5, suppressing the heat exchange between the high-temperature combustion gas and the suction side wall 5, improving the cooling effect, and minimizing aerodynamic losses to the high-pressure turbine blades 1. Figure 6 In the illustrated embodiment, a suction-side chamber 10a is located in the larynx and anterior to the larynx, and the suction-side chamber 10a is provided with an air film port 2. Figure 8 In the illustrated embodiment, a suction-side chamber 10a is located in the larynx and anterior to the larynx, and the suction-side chamber 10a is provided with an air film port 2. Figure 6 and Figure 8 In the embodiment shown, the suction side chamber 10a is provided with 1 to 2 rows of air film holes 2, and a plurality of air film holes 2 in each row of air film holes 2 are arranged radially, and each row of air film holes 2 includes 10 to 20 air film holes 2.

[0085] Continue to refer to Figure 6 and Figure 8In an embodiment where some suction-side chambers 10a-10d (11a-11c) in the middle chamber region 10(11) are located in the larynx and anterior to the larynx, and some suction-side chambers 10a-10d (11a-11c) are located posterior to the larynx, the suction-side chambers 10a-10d (11a-11c) located in the larynx and anterior to the larynx and the suction-side chambers 10a-10d (11a-11c) located posterior to the larynx are... ~11c) can be connected by the second rotating channel 10i, which is located at the top or bottom of the suction side chambers 10a~10d (11a~11c), and is used for cooling fluid to flow from the suction side chambers 10a~10d (11a~11c) located in the throat and in front of the throat through the second rotating channel 10i to the suction side chambers 10a~10d (11a~11c) located behind the throat. The high-temperature combustion gas directly impacts the leading edge 3, resulting in a higher thermal load on the leading edge 3. Compared to the suction side chambers 10a-10d (11a-11c) located behind the throat, the suction side chambers 10a-10d (11a-11c) located in front of the throat are closer to the leading edge 3, and therefore the temperature of the blade body there is higher. The cooling fluid first cools the blade body around the throat in the suction side chambers 10a-10d (11a-11c) located in front of the throat, and then enters the suction side chambers 10a-10d (11a-11c) located behind the throat to cool the blade body around the throat. As the temperature of the cooling fluid increases and the pressure decreases with the flow, the cooling effect of the cooling fluid on the blade body near the leading edge 3 is better than that on the blade body behind it. Without increasing the amount of cooling fluid used, the high temperature of the blade body near the leading edge 3 is reduced, thereby reducing the temperature gradient of the high-pressure turbine blade 1 and improving the service life of the high-pressure turbine blade 1. In combination with the foregoing, Figure 6 In the illustrated embodiment, cooling fluid located in the first suction-side chamber 10a, situated in the throat and anterior to the throat, enters through the second rotary channel 10i into the second suction-side chamber 10b and the third suction-side chamber 10c, situated posterior to the throat. In conjunction with the foregoing, in Figure 8 In the embodiment shown, the cooling fluid in the first suction side chamber 10a located in the throat and the front side of the throat enters the second suction side chamber 10b and the third suction side chamber 10c located in the rear side of the throat through the second rotary channel 10i.

[0086] like Figure 2 , Figure 5 , Figure 6 and Figure 8As shown, each intermediate chamber region 10 (11) may include at least one end pressure-side chamber 10e-10g (11d). The end pressure-side chambers 10e-10g (11d) are the last chambers in the intermediate chamber region 10 (11) where the cooling fluid enters. The cooling fluid flows from bottom to top in the end pressure-side chambers 10e-10g (11d). As the cooling fluid pressure decreases with flow, the pressure is at its minimum when the cooling fluid enters the end pressure-side chambers 10e-10g (11d), resulting in insufficient power for the cooling fluid flow. The cooling fluid flows from bottom to top in the end pressure-side chambers 10e-10g (11d), and the flow direction is consistent with the direction of the centrifugal force of the high-pressure turbine blade 1 when the high-pressure turbine rotates, so that the centrifugal force promotes the flow of the cooling fluid. In conjunction with the foregoing, in Figure 2 In the illustrated embodiment, the second pressure-side chamber 10f is the last chamber in the first intermediate chamber region 10 where the cooling fluid enters. The second pressure-side chamber 10f is the end pressure-side chamber of the first intermediate chamber region 10. The cooling fluid in the second pressure-side chamber 10f flows from bottom to top. Therefore, the rotary channel connecting the first pressure-side chamber 10e and the second pressure-side chamber 10f is located at the bottom of the pressure-side chambers 10e and 10f, and the first rotary channel 10h connecting the suction-side chambers 10a-10c and the pressure-side chamber 10e is located at the top of the suction-side chambers 10a-10c and the pressure-side chamber 10e. In conjunction with the foregoing, in Figure 5 In the illustrated embodiment, the second pressure-side chamber 10f and the third pressure-side chamber 10g are the last chambers in the first intermediate chamber region 10 where the cooling fluid enters. Both the second pressure-side chamber 10f and the third pressure-side chamber 10g are the end pressure-side chambers of the first intermediate chamber region 10. The cooling fluid in the second pressure-side chamber 10f and the third pressure-side chamber 10g flows from bottom to top. Therefore, the rotary channel connecting the first pressure-side chamber 10e, the second pressure-side chamber 10f, and the third pressure-side chamber 10g is located at the bottom of the pressure-side chambers 10e-10f, and the first rotary channel 10h connecting the suction-side chambers 10a-10d and the pressure-side chamber 10e is located at the top of the suction-side chambers 10a-10d and the pressure-side chamber 10e. In conjunction with the foregoing, in Figure 6In the illustrated embodiment, the first pressure-side chamber 10e is the last chamber in the first intermediate chamber region 10 where the cooling fluid enters. The first pressure-side chamber 10e is the end pressure-side chamber of the first intermediate chamber region 10. The cooling fluid in the first pressure-side chamber 10e flows from bottom to top. Therefore, the first rotary channel 10h connecting the first pressure-side chamber 10e, the second suction-side chamber 10b, and the third suction-side chamber 10c is located at the bottom of the suction-side chambers 10b and 10c and the pressure-side chamber 10e. The second rotary channel 10i connecting the first suction-side chamber 10a, the second suction-side chamber 10b, and the third suction-side chamber 10c is located at the top of the suction-side chambers 10a and 10c. In conjunction with the foregoing, in Figure 6 In the illustrated embodiment, the pressure-side chamber 11d is the last chamber in the second intermediate chamber region 11 where the cooling fluid enters. The pressure-side chamber 11d is the end pressure-side chamber of the second intermediate chamber region 11. The cooling fluid in the pressure-side chamber 11d flows from bottom to top. Therefore, the first rotary channel 11e connecting the pressure-side chamber 11d and the second suction-side chamber 11b is located at the bottom of the pressure-side chamber 11d and the suction-side chamber 11b, and the rotary channel connecting the first suction-side chamber 11a and the second suction-side chamber 11b is located at the top of the suction-side chambers 11a and 11b. In conjunction with the foregoing, in Figure 8 In the described embodiment, the first pressure-side chamber 10e is the last chamber in the first middle chamber region 10 where the cooling fluid enters. The first pressure-side chamber 10e is the end pressure-side chamber of the first middle chamber region 10. The cooling fluid in the first pressure-side chamber 10e flows from bottom to top. Therefore, the first rotating channel 10h connecting the first pressure-side chamber 10e, the second suction-side chamber 10b, and the third suction-side chamber 10c is located at the bottom of the suction-side chambers 10b and 10c and the pressure-side chamber 10e. The second rotating channel 10i connecting the first suction-side chamber 10a, the second suction-side chamber 10b, and the third suction-side chamber 10c is located at the top of the suction-side chambers 10a and 10c. In conjunction with the foregoing, in... Figure 8 In the embodiment described, the pressure-side chamber 11d is the last chamber in which the cooling fluid enters in the second middle chamber region 11. The pressure-side chamber 11d is the end pressure-side chamber of the second middle chamber region 11. The cooling fluid in the pressure-side chamber 11d flows from bottom to top. Thus, the first rotary channel 11e connecting the pressure-side chamber 11d and the second suction-side chamber 11b and the third suction-side chamber 11c is located at the bottom of the pressure-side chamber 11d, the suction-side chambers 11b and 11c, and the rotary channel connecting the first suction-side chamber 11a and the second suction-side chamber 11b is located at the top of the suction-side chambers 11a and 11b.

[0087] For the intermediate chamber region 10 (11), at least one suction-side chamber 10a-10d (11a-11c) may have a first cooling fluid inlet 13 at its bottom, through which cooling fluid enters the intermediate chamber region 10 (11). As the cooling fluid temperature increases and the pressure decreases, the cooling fluid at the first cooling fluid inlet 13 has the lowest temperature and the highest pressure, possessing the strongest cooling capacity. The cooling fluid at the cooling fluid inlet 13 flows directly into the suction-side chambers 10a-10d (11a-11c) for cooling, reducing the high temperature of the suction-side blade without increasing the amount of cooling fluid used, thereby reducing the temperature gradient of the high-pressure turbine blade 1 and improving its service life. Figure 2 In the illustrated embodiment, the three suction-side chambers 10a-10c are provided with a unified first cooling fluid inlet 13 at the bottom. A stream of cooling fluid splits from the first cooling fluid inlet 13 into three paths, entering the first suction-side chamber 10a, the second suction-side chamber 10b, and the third suction-side chamber 10c respectively, thereby entering the middle chamber region 10. Figure 5 In the illustrated embodiment, the four suction-side chambers 10a-10d are provided with a first integrated cooling fluid inlet 13 (not shown in the figure) at the bottom. A stream of cooling fluid splits from the first cooling fluid inlet 13 into four paths, entering the first suction-side chamber 10a, the second suction-side chamber 10b, the third suction-side chamber 10c, and the fourth suction-side chamber 10d respectively, thereby entering the middle chamber region 10. Figure 6 In the illustrated embodiment, the first suction-side chamber 10a has a first cooling fluid inlet 13 at its bottom. Cooling fluid enters the first suction-side chamber 10a from the first cooling fluid inlet 13, thereby entering the first middle chamber region 10. Figure 6 In the illustrated embodiment, the first suction-side chamber 11a has a first cooling fluid inlet 13 (not shown in the figure) at its bottom. Cooling fluid enters the first suction-side chamber 11a from the first cooling fluid inlet 13, thereby entering the second middle chamber region 11. Figure 8 In the embodiment shown, the first suction side chamber 11a is provided with a first cooling fluid inlet 13 (not shown in the figure) at the bottom. Cooling fluid enters the first suction side chamber 11a from the first cooling fluid inlet 13, thereby entering the second middle chamber region 11.

[0088] like Figure 2 , Figure 5 , Figure 6 and Figure 8As shown, the ratio of the chordal length of the suction side chambers 10a-10d (11a-11c) to the lateral width of the suction side chambers 10a-10d (11a-11c) can range from 1 to 4:1. The lateral width of the suction side chambers 10a-10d (11a-11c) is less than or equal to the chordal length, thereby enhancing the heat exchange of the cooling fluid between the suction side chambers 10a-10d (11a-11c) and the suction side wall 5, reducing the lateral temperature difference of the suction side blades, improving the cooling effect on the suction side blades, and reducing the high temperature of the suction side blades without increasing the amount of cooling fluid used, thereby reducing the temperature gradient of the high-pressure turbine blades 1 and improving the service life of the high-pressure turbine blades 1.

[0089] exist Figure 2 In the illustrated embodiment, the ratio of the chordal length to the lateral width of the suction-side chambers 10a-10c is 4:1. Figure 5 In the illustrated embodiment, the ratio of the chordal length to the lateral width of the suction-side chambers 10a-10d is 4:1. Figure 6 In the illustrated embodiment, the ratio of the chordal length to the lateral width of the suction-side chambers 10a-10c, 11a, and 11b is 1-2:1. Figure 8 In the illustrated embodiment, the ratio of the chordal length to the lateral width of the suction-side chambers 10a-10c and 11a-11 is 1-2:1.

[0090] like Figure 2 , Figure 5 , Figure 6 and Figure 8 As shown, the chordal length of the suction side chambers 10a-10d (11a-11c) can be greater than or equal to the chordal length of the walls on both sides of the suction side chambers 10a-10d (11a-11c). This reduces the thermal resistance of the walls on both sides of the suction side chambers 10a-10d (11a-11c), improves the cooling effect of the cooling fluid on the surrounding blades of the suction side chambers 10a-10d (11a-11c), and reduces the high temperature of the suction side blades without increasing the amount of cooling fluid used, thereby reducing the temperature gradient of the high-pressure turbine blade 1 and improving the service life of the high-pressure turbine blade 1.

[0091] like Figure 2 , Figure 5 , Figure 6 and Figure 8 As shown, the anterior chamber region 9 may include an inner anterior chamber 9a and an outer anterior chamber 9b, both extending radially. The outer anterior chamber 9b is disposed around the inner anterior chamber 9a, and is located between the anterior wall 3a, the pressure sidewall 6, the suction sidewall 5, and the inner anterior chamber 9a. Figure 2 , Figure 5 , Figure 6 and Figure 8 In the illustrated embodiment, the anterior chamber region 9 is provided with a leading edge inner chamber 9a and multiple leading edge outer chambers 9b. The multiple leading edge inner chambers 9a are distributed around the leading edge inner chamber 9a. One leading edge outer chamber 9b is located between the leading edge wall 3a and the leading edge inner chamber 9a, and one leading edge outer chamber 9b is located between the pressure sidewall 6 and the leading edge inner chamber 9a. Figure 2 and Figure 5 In the illustrated embodiment, the two leading-edge outer chambers 9b are located between the suction sidewall 5 and the leading-edge inner chamber 9a. Figure 6 and Figure 8 In the illustrated embodiment, a leading-edge outer chamber 9b is located between the suction sidewall 5 and the leading-edge inner chamber 9a. The leading-edge inner chamber 9a is used for cooling fluid to flow from bottom to top. A second cooling fluid inlet (not shown) may be provided at the bottom of the leading-edge inner chamber 9a, through which the cooling fluid enters the leading-edge inner chamber 9a and flows from bottom to top, thus entering the front chamber region 9. An impact hole 14 is provided between the leading-edge outer chamber 9b and the leading-edge inner chamber 9a, through which the cooling fluid flows from the leading-edge inner chamber 9a to the leading-edge outer chamber 9b. The cooling fluid forms an impact jet through the impact hole 14, impacting the inner wall surface of the leading-edge outer chamber 9b, thereby achieving impact cooling and improving the cooling effect. Figure 2 , Figure 5 , Figure 6 and Figure 8 In the illustrated embodiment, each leading-edge outer chamber 9b is equipped with an impact hole 14 connecting to the leading-edge inner chamber 9a. The leading-edge outer chamber 9b is connected to a film cooling hole 2 penetrating the leading-edge wall 3a, pressure side wall 6, and suction side wall 5. Cooling fluid flows out from the film cooling hole 2 through the leading-edge outer chamber 9b, forming a cooling film on the leading-edge wall 3a, pressure side wall 6, and suction side wall 5, suppressing heat exchange between the high-temperature combustion gas and the walls of the high-pressure turbine blade 1, thus improving the cooling effect. Figure 2 , Figure 5 , Figure 6 and Figure 8In the illustrated embodiment, each leading-edge outer chamber 9b is equipped with a film cooling port 2 connecting to one of the leading-edge wall 3a, pressure sidewall 6, and suction sidewall 5. The leading-edge outer chamber 9b located between the leading-edge wall 3a and the leading-edge inner chamber 9a is equipped with a film cooling port 2 connecting to the leading-edge wall 3a. The leading-edge outer chamber 9b located between the pressure sidewall 6 and the leading-edge inner chamber 9a is equipped with a film cooling port 2 connecting to the pressure sidewall 6. The leading-edge outer chamber 9b located between the suction sidewall 5 and the leading-edge inner chamber 9a is equipped with a film cooling port 2 connecting to the suction sidewall 5. High-temperature combustion gases directly impact the leading edge 3, resulting in a higher heat load on the leading edge 3 and the adjacent blade. The leading-edge chamber region 9 employs a composite cooling structure combining impact cooling and film cooling. This reduces the high temperature of the leading edge 3 and the adjacent blade without increasing the amount of cooling fluid used, thereby reducing the temperature gradient of the high-pressure turbine blade 1 and improving its service life.

[0092] like Figure 2 , Figure 5 , Figure 6 and Figure 8 As shown, for the leading edge outer chamber 9b located between the leading edge wall 3a and the leading edge inner chamber 9a, the leading edge outer chamber 9b is provided with a row of impact holes 14 and 4 to 6 rows of air film holes 2. The multiple impact holes 14 in the row of impact holes 14 are arranged radially, and the multiple air film holes 2 in each row of air film holes 2 are arranged radially. Each row of air film holes 2 includes 10 to 20 air film holes 2.

[0093] like Figure 2 , Figure 5 , Figure 6 and Figure 8 As shown, for the leading edge outer chamber 9b located between the suction sidewall 5 and the leading edge inner chamber 9a, and for the leading edge outer chamber 9b located between the pressure sidewall 6 and the leading edge inner chamber 9a, each leading edge outer chamber 9b is provided with a row of impact holes 14. The ratio of the chordal length of the leading edge outer chamber 9b to the diameter of the impact hole 14 is (2-4):1, and the ratio of the lateral width of the leading edge outer chamber 9b to the diameter of the impact hole 14 is (1-2):1. Multiple impact holes 14 in a row are arranged radially, and a row of impact holes 14 includes 8-12 impact holes 14. Figure 2 and Figure 5 In the illustrated embodiment, the ratio of the chordal length of the leading edge outer chamber 9b to the diameter of the impact hole 14 is 4:1, and the ratio of the lateral width of the leading edge outer chamber 9b to the diameter of the impact hole 14 is 1:1. Figure 6 and Figure 8 In the embodiment shown, the ratio of the chordal length of the leading edge outer chamber 9b to the diameter of the impact hole 14 is 3:1, and the ratio of the lateral width of the leading edge outer chamber 9b to the diameter of the impact hole 14 is 1:1.

[0094] like Figure 2 , Figure 5 , Figure 6 and Figure 8 As shown, for the leading edge outer chamber 9b located between the suction sidewall 5 and the leading edge inner chamber 9a, and for the leading edge outer chamber 9b located between the pressure sidewall 6 and the leading edge inner chamber 9a, each leading edge outer chamber 9b is provided with 1 to 2 rows of air film holes 2, and multiple air film holes 2 in each row of air film holes 2 are arranged radially, and each row of air film holes 2 includes 10 to 20 air film holes 2.

[0095] like Figure 6 and Figure 8 As shown, the anterior margin chamber 9a can be located on the pressure side of the suction-side chambers 10a-10d (11a-11c) on the larynx and the anterior side of the larynx. The anterior margin chamber 9a is located laterally inner to the suction-side chambers 10a-10d (11a-11c) on the larynx and the anterior side of the larynx and is closer to the pressure side wall 6. The suction-side chambers 10a-10d (11a-11c) on the larynx and the anterior side of the larynx are located between the anterior margin chamber 9a and the suction side wall 5. In conjunction with the foregoing, in Figure 6 and Figure 8 In the embodiment shown, the leading edge inner chamber 9a may be disposed laterally inside the first suction side chamber 10a and closer to the pressure side wall 6, with the first suction side chamber 10a located between the leading edge inner chamber 9a and the suction side wall 5.

[0096] Continue to refer to Figure 8 Multiple radially arranged impact holes 14 can be provided between the leading edge inner chamber 9a and the throat and the suction-side chambers 10a-10d (11a-11c) on the front side of the throat. Cooling fluid flows from the leading edge inner chamber 9a through the impact holes 14 to the throat and the suction-side chambers 10a-10d (11a-11c) on the front side of the throat. The cooling fluid forms an impact jet through the impact holes 14, impacting the inner wall surface of the throat and the suction-side chambers 10a-10d (11a-11c) on the front side of the throat, thereby achieving impact cooling and improving the cooling effect. In conjunction with the foregoing, in Figure 8 In the illustrated embodiment, a plurality of radially arranged impact holes 14 are provided between the leading edge inner chamber 9a and the first suction-side chamber 10a. Cooling fluid forms an impact jet through the impact holes 14 to impact the inner wall surface of the first suction-side chamber 10a. Figure 6 Compared to the first suction-side chamber 10a, where cooling fluid is supplied by the first cooling fluid inlet 13, without increasing the amount of cooling fluid used, that is, in Figure 8 In the embodiment shown, the amount of cooling fluid used in the leading edge inner chamber 9a is no higher than Figure 6 Under the premise of the total amount of cooling fluid used in the leading edge inner chamber 9a and the first suction side chamber 10a in the embodiment shown, Figure 8 The first suction-side chamber 10a shown is supplied with cooling fluid in the form of impact cooling to improve the cooling effect.

[0097] exist Figure 8 In the illustrated embodiment, the first suction-side chamber 10a is provided with a row of impact holes 14, and a plurality of impact holes 14 in the row of impact holes 14 are arranged radially, the row of impact holes 14 including 8 to 12 impact holes 14. The ratio of the chordal length of the first suction-side chamber 10a to the diameter of the impact hole 14 is (2 to 4):1, and the ratio of the lateral width of the leading edge outer chamber 9b to the diameter of the impact hole 14 is (1 to 2):1. Preferably, the ratio of the lateral width of the leading edge outer chamber 9b to the diameter of the impact hole 14 is 1:1.

[0098] like Figure 2 , Figure 5 , Figure 6 and Figure 8 As shown, the rear chamber region 12 may include a trailing edge chamber 12a for cooling the trailing edge 4 and the blade adjacent to the trailing edge 4. The rear chamber region 12 may have one or more trailing edge chambers 12a. Figure 5 and Figure 8 In the illustrated embodiment, a trailing edge chamber 12a is provided in the rear chamber region 12. Figure 2 and Figure 6 In the illustrated embodiment, the rear chamber region 12 is provided with two trailing edge chambers 12a, which are arranged chordally from the leading edge 3 to the trailing edge 4, with one trailing edge chamber 12a located in front of the other. The trailing edge chambers 12a extend radially for cooling fluid to flow from bottom to top. A third cooling fluid inlet (not shown) may be provided at the bottom of the trailing edge chamber 12a for cooling fluid to enter the trailing edge chamber 12a from bottom to top and thus enter the rear chamber region 12. The suction-side chambers 10a-10d (11a-11c) and the trailing edge chamber 12a are connected by a third rotating channel 12b. The third rotating channel 12b is located at the top of the suction-side chambers 10a-10d (11a-11c) and the trailing edge chamber 12a, allowing cooling fluid to flow from the trailing edge chamber 12a to the suction-side chambers 10a-10d (11a-11c) via the third rotating channel 12b. This increases the amount of cooling fluid in the trailing edge chamber 12a without increasing the total amount of cooling fluid in the suction-side chambers 10a-10d (11a-11c) and the trailing edge chamber 12a, thereby improving the cooling effect on the trailing edge 4, reducing the high temperature of the trailing edge 4, and extending the service life of the high-pressure turbine blade 1. In conjunction with the foregoing, Figure 8In the embodiment shown, the trailing edge chamber 12a adjacent to the middle chamber region 11 and the third suction side chamber 11c of the second middle chamber region 11 are connected by a third rotating channel 12b. The third rotating channel 12b is located at the top of the third suction side chamber 11c and the trailing edge chamber 12a, and is used for cooling fluid to flow from the trailing edge chamber 12a to the third suction side chamber 11c through the third rotating channel 12b. The structure of the third rotating channel 12b can be referred to the first rotating channel 10h.

[0099] like Figure 2 , Figure 5 , Figure 6 and Figure 8 As shown, the trailing edge chamber 12a can be connected to the film cooling hole 2 penetrating the pressure sidewall 6, allowing cooling fluid to flow out from the film cooling hole 2 through the trailing edge chamber 12a, forming a cooling film on the pressure sidewall 6 adjacent to the trailing edge 4. This suppresses heat exchange between the high-temperature combustion gas and the pressure sidewall 6, improving the cooling effect. Figure 2 , Figure 5 , Figure 6 and Figure 8 In the illustrated embodiment, each trailing edge chamber 12a is provided with a film cooling hole 2. The trailing edge chamber 12a is sealed by a suction sidewall 5, and the suction sidewall 5 on the lateral upper outer side of the trailing edge chamber 12a is not provided with a film cooling hole, thereby reducing the aerodynamic losses of the high-pressure turbine blade 1. Figure 2 , Figure 5 , Figure 6 and Figure 8 In the embodiment shown, each trailing edge chamber 12a is enclosed by a suction sidewall 5.

[0100] like Figure 2 , Figure 5 , Figure 6 and Figure 8 As shown, at least one trailing edge chamber 12a in the rear chamber region 12 is connected to a trailing edge slit 15, allowing cooling fluid to flow out from the trailing edge chamber 12a through the trailing edge slit 15, thereby cooling the trailing edge 4. Figure 2 and Figure 6 In the embodiment shown, the trailing edge chamber 12a located on the rearmost side is provided with a trailing edge slit 15.

[0101] like Figure 1 As shown, the aforementioned first cooling fluid inlet 13, second cooling fluid inlet and third cooling fluid inlet can be disposed in the tenon 16 of the high-pressure turbine blade 1.

[0102] A flow-enhancing structure can be installed within the cooling chamber to improve the flow of cooling fluid, thereby enhancing the cooling effect. This flow-enhancing structure can be a rib, a circular boss, etc., protruding from the inner wall of the cooling chamber. The ratio of the lateral width of the flow-enhancing structure protruding from the inner wall of the cooling chamber to the lateral width of the cooling chamber is in the range of 1:(5~10). Figure 2 , Figure 5 and Figure 6 In the illustrated embodiment, except for the leading edge inner chamber 9a and leading edge outer chamber 9b of the front chamber region 9, all other cooling chambers can be equipped with turbulence structures. Figure 8 In the illustrated embodiment, except for the leading edge inner chamber 9a and leading edge outer chamber 9b of the front chamber region 9 and the first suction side chamber 10a of the first middle chamber region 10, all other cooling chambers may be provided with turbulence structures.

[0103] Although the present invention has been disclosed above with reference to embodiments, it is not intended to limit the present invention. Any person skilled in the art can make possible changes and modifications without departing from the spirit and scope of the present invention.

Claims

1. An airfoil component, characterized in that, It includes the anterior chamber region, the middle chamber region, and the posterior chamber region, which are arranged chordally from the leading edge to the trailing edge; The intermediate chamber region includes a suction-side chamber and a pressure-side chamber arranged laterally from the suction side wall to the pressure side wall. The suction-side chamber and the pressure-side chamber extend radially from the blade root to the blade tip. The suction-side chamber and the pressure-side chamber are connected by a first rotating channel. The first rotating channel is located at the top or bottom of the suction-side chamber and the pressure-side chamber, and is used for cooling fluid to flow from the suction-side chamber to the pressure-side chamber through the first rotating channel.

2. The airfoil according to claim 1, characterized in that: The lateral width of the suction-side chamber is smaller than the lateral width of the pressure-side chamber.

3. The airfoil according to claim 1, characterized in that: The central chamber region is provided with a plurality of suction side chambers, at least some of which are located on the posterior side of the larynx and are closed by the suction side walls. The pressure-side chamber is connected to an air film pore that penetrates the pressure-side wall.

4. The airfoil according to claim 3, characterized in that: Part of the suction-side chamber is located in the larynx or in front of the larynx, and the suction-side chamber located in the larynx and in front of the larynx is connected to an air film hole that penetrates the suction-side wall.

5. The airfoil according to claim 4, characterized in that: The suction side chamber located in the throat and the front side of the throat and the suction side chamber located in the back side of the throat are connected by a second rotating channel. The second rotating channel is located at the top or bottom of the suction side chamber and is used for cooling fluid to flow from the suction side chamber located in the throat and the front side of the throat to the suction side chamber located in the back side of the throat through the second rotating channel.

6. The airfoil according to claim 1, characterized in that: Each of the middle chamber regions includes at least one end pressure-side chamber, the end pressure-side chamber being the last chamber in the middle chamber region into which the cooling fluid flows from bottom to top.

7. The airfoil according to claim 1, characterized in that: At least one of the suction-side chambers is provided with a first cooling fluid inlet at the bottom for cooling fluid to enter the middle chamber region from the first cooling fluid inlet.

8. The airfoil according to claim 1, characterized in that: The ratio of the chordal length of the suction-side chamber to the lateral width of the suction-side chamber ranges from 1 to 4:

1.

9. The airfoil according to claim 1, characterized in that: The chordal length of the suction-side chamber is greater than or equal to the chordal length of the walls on both sides of the suction-side chamber.

10. The airfoil according to claim 5, characterized in that: The front chamber region includes a leading edge inner chamber that extends radially from the blade root to the blade tip for cooling fluid to flow from bottom to top. The leading edge inner chamber is located on the pressure side of the throat and the suction side chamber anterior to the throat.

11. The airfoil according to claim 10, characterized in that: A plurality of impact holes are arranged radially between the leading edge inner chamber and the throat and the suction side chamber on the front side of the throat, so that cooling fluid can flow from the leading edge inner chamber through the impact holes to the throat and the suction side chamber on the front side of the throat, thereby achieving impact cooling.

12. The airfoil according to claim 10, characterized in that: The front chamber region also includes a leading edge outer chamber, which extends radially from the blade root to the blade tip and is located between the leading edge wall, the pressure side wall, the suction side wall and the leading edge inner chamber; An impact hole is provided between the leading edge outer chamber and the leading edge inner chamber, so that cooling fluid can flow from the leading edge inner chamber through the impact hole to the leading edge outer chamber, thereby achieving impact cooling; The leading edge outer chamber is connected to an air film pore that penetrates the leading edge wall, the pressure side wall, and the suction side wall.

13. The airfoil according to claim 10, characterized in that: The leading edge inner chamber has a second cooling fluid inlet at the bottom, through which cooling fluid enters the leading chamber region.

14. The airfoil according to claim 1, characterized in that: The front chamber region includes a leading edge inner chamber and a leading edge outer chamber. Both the leading edge inner chamber and the leading edge outer chamber extend radially from the leaf root to the leaf tip. The leading edge outer chamber is located between the leading edge wall, the pressure side wall, the suction side wall, and the leading edge inner chamber. The leading edge inner chamber is used for cooling fluid to flow from bottom to top. An impact hole is provided between the leading edge outer chamber and the leading edge inner chamber, so that cooling fluid can flow from the leading edge inner chamber to the leading edge outer chamber through the impact hole, thereby achieving impact cooling. The leading edge outer chamber is connected to an air film pore that penetrates the leading edge wall, the pressure side wall, and the suction side wall.

15. The airfoil according to claim 1, characterized in that: The rear chamber region includes a trailing edge chamber that extends radially from the blade root to the blade tip, for cooling fluid to flow from the bottom to the top. The suction side chamber and the trailing edge chamber are connected by a third rotating channel located at the top of the suction side chamber and the trailing edge chamber, for cooling fluid to flow from the trailing edge chamber to the suction side chamber through the third rotating channel.

16. The airfoil according to claim 15, characterized in that: The trailing edge chamber is connected to a film pore penetrating the pressure sidewall, and the trailing edge chamber is sealed by the suction sidewall.

17. The airfoil according to claim 15, characterized in that: At least one of the tail edge chambers is connected to the tail edge slit.

18. A turbine engine, characterized in that, Includes the airfoil as described in any one of claims 1 to 17.

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