Internal cooling channel structure of stationary blade of gas turbine

Abstract

The invention discloses an internal cooling channel structure of a gas turbine stationary blade, and relates to the technical field of gas turbine stationary blade design. The internal cooling channel structure of the stationary blade of the gas turbine comprises a stationary blade body, a blade suction surface and a blade pressure surface, and the blade suction surface and the blade pressure surface are arranged on the two surfaces of the stationary blade body respectively and bear pressure and suction in the gas turbine respectively. Air film hole parts which are distributed in an array mode in the axial direction of the stator blade body and arranged in a penetrating mode are formed in the opposite positions of the blade suction face and the blade pressure face on the stator blade body. A plurality of gas channels (A and B) and a heat conduction chamber are arranged in the stationary blade, and high-heat-conduction materials are used in a combined mode, so that heat can be conducted and dissipated more effectively; according to the structure, the stationary blade can operate at a higher temperature without damaging the material and structural integrity of the stationary blade, so that the heat efficiency and the output performance of the whole gas turbine are improved, and the stationary blade can stably work in a complex load and high-temperature environment due to the design of the novel connecting seat and the selection of the material of the novel connecting seat.

Description

Technical Field

[0001] The invention relates to the technical field of gas turbine stator blade design, and in particular to an internal cooling channel structure of a gas turbine stator blade. Background Art

[0002] In modern industry and energy, there is a continuously growing demand for efficient and reliable power equipment. As a power device that converts the chemical energy of fuel into mechanical energy, gas turbines play a key role in many fields such as power generation, aviation, and shipping. With the continuous growth of energy demand and the improvement of energy utilization efficiency, the performance improvement of gas turbines has become a research focus.

[0003] Gas turbine technology originated in the early 20th century. After years of development, it has made significant progress in power output, efficiency, etc.; however, to meet increasingly stringent energy and environmental requirements, it is still necessary to continuously improve the various components of the gas turbine, among which the stator blades are one of the important components that affect the performance of the gas turbine.

[0004] In early gas turbines, the design of stationary blades was mainly based on experience and relatively simple theoretical calculations. The blade shape of traditional stationary blades is relatively simple, and there is a lot of room for improvement in aerodynamic performance; for example, traditional blade shapes are prone to airflow separation under high-load operating conditions, resulting in increased energy loss and reduced gas turbine efficiency.

[0005] The manufacturing process of traditional stator blades also has certain limitations. Due to limited manufacturing precision, the actual manufactured stator blades deviate from the ideal design shape, which further affects the aerodynamic performance of the stator blades. Moreover, the application of traditional cooling technology in stator blades is not perfect, and it is difficult to meet the requirements of modern gas turbines for efficient cooling in high temperature environments, thereby limiting the performance improvement of gas turbines.

[0006] In terms of structural design, the tenon connection mode of the blade root may cause excessive local stress when subjected to complex loads, resulting in premature falling off or damage of the tenon. Therefore, a new internal cooling channel structure of a gas turbine stator blade is provided to solve the above problem. Summary of the invention

[0007] The purpose of the present invention is to solve at least one of the technical problems existing in the prior art and to provide an internal cooling channel structure of a gas turbine stator blade that can solve the problems raised by the above-mentioned background technology.

[0008] To achieve the above-mentioned object, the present invention provides the following technical solutions: a gas turbine stator blade internal cooling channel structure, comprising a stator blade body, a blade suction surface and a blade pressure surface, wherein the blade suction surface and the blade pressure surface are respectively arranged on two sides of the stator blade body and bear the pressure and suction inside the gas turbine respectively, and film holes are arranged on the stator blade body at relative positions of the blade suction surface and the blade pressure surface, which are distributed in an axial array along the stator blade body and are arranged through the stator blade body;

[0009] The blade length of the stationary blade body is 450-550 mm, the blade tip radius and the blade root radius are equal to 100-140 mm, and the blade twist angle is 5-10°;

[0010] It also includes an upper edge portion, a lower edge portion and a connecting seat, wherein the upper edge portion and the lower edge portion are arranged at two ends of the stationary blade body, two groups of stationary blade bodies are formed on a single group of connecting seats, the connecting seat is connected to the end surface of the lower edge portion, and the end surface of the connecting seat away from the lower edge portion is integrally formed with a blade tenon portion that can be clamped with an external tenon groove, and the cross-section of the blade tenon portion is in the shape of an inverted electric tower;

[0011] It also includes a gas channel A, a gas channel B and a heat conduction chamber. The gas channel A and the gas channel B are respectively arranged on the inner sides of the two groups of stationary blades on the connecting seat. The gas channel A and the gas channel B both extend into the inner side of the connecting seat. The heat conduction chamber is integrally formed on the inner side of the connecting seat. The gas channel A and the gas channel B are both connected to the interior of the heat conduction chamber.

[0012] Preferably, the gas channel A, the gas channel B and the inner wall of the heat-conducting chamber are all coated with heat-conducting materials, and the air film holes are not sealed.

[0013] Preferably, an air inlet portion for introducing cooling gas into the stationary blade body is integrally formed at the upper edge of the stationary blade body, and the air inlet portion is connected to the gas channel A, the gas channel B and the heat conduction chamber.

[0014] Preferably, a converging and guiding seat is integrally formed at the inner middle section, and the gas channel A and the gas channel B are respectively arranged on both sides of the converging and guiding seat, and the converging and guiding seat is located directly above the heat conduction chamber.

[0015] Preferably, the air inlet portion and the air outlet portion are respectively provided with a plurality of groups of reinforcing ribs distributed in an array and are integrally formed with the inner walls of the stationary blade body and the blade tenon portion.

[0016] Preferably, the two side end faces of the stationary blade body are divided into blade side edge A and blade side edge B, the angle formed by blade side edge B is 5-10°, and the angle formed by blade side edge B is not greater than half of the angle formed by blade side edge A.

[0017] Preferably, the diameter of the air film hole portion 14 is 5-10 mm, the maximum thickness of the stationary blade body is 30 mm, and the minimum thickness of the stationary blade body is 5 mm.

[0018] Preferably, the connecting seat is made of a highly thermally conductive deformable material, and the tail end surface of the tenon portion of the blade is integrally provided with an outlet portion for discharging the heat exchange gas.

[0019] Compared with the prior art, the present invention has the following beneficial effects:

[0020] Improved thermal efficiency and performance: Multiple gas channels (A, B) and heat conduction chambers are set inside the stator blades, combined with the use of high thermal conductivity materials, to conduct and dissipate heat more effectively. This structure allows the stator blades to operate at higher temperatures without compromising their material and structural integrity, thereby improving the thermal efficiency and output performance of the entire gas turbine.

[0021] Reduce maintenance costs and extend service life: The innovative stator blade design uses one-piece molding technology and deformable high thermal conductivity materials, which not only enhances the structural stability of the components, but also reduces wear and damage caused by high temperature and pressure changes, thereby extending the service life of the components and reducing maintenance costs.

[0022] Enhanced cooling efficiency: The design of the air inlet and outlet and the air film holes in the stator blades can effectively guide the cooling gas to flow through the stator blades, improving the cooling efficiency. This efficient cooling mechanism is particularly important for gas turbines operating under high load and high temperature environments.

[0023] Optimizing aerodynamic performance: The design of the air film holes and blade side edges of the stator blades can optimize the path of airflow through the stator blades, reduce airflow separation, and reduce energy loss. This optimization helps to improve the overall aerodynamic efficiency of the gas turbine.

[0024] Adapting to complex loads and high temperature environments: The new connection seat design and the selection of materials enable the stationary blades to work stably in complex load and high temperature environments. In particular, the optimization of the tenon connection method reduces the risk of local damage caused by stress concentration. BRIEF DESCRIPTION OF THE DRAWINGS

[0025] The present invention is further described below in conjunction with the accompanying drawings and embodiments:

[0026] Figure 1 The three-dimensional Figure 1 ;

[0027] Figure 2 The three-dimensional Figure 2 ;

[0028] Figure 3 The three-dimensional Figure 3 ;

[0029] Figure 4 is a side view of the present invention;

[0030] Figure 5 It is the AA cross-sectional view of the present invention;

[0031] Figure 6 It is a front view of the present invention.

[0032] Figure numerals: 1. stationary blade body; 2. blade suction surface; 3. blade pressure surface; 4. upper edge; 5. lower edge; 6. connecting seat; 7. blade tenon portion; 8. air outlet portion; 9. air inlet portion; 10. gas channel A; 11. gas channel B; 12. converging and guiding seat; 13. heat conduction chamber; 14. air film hole portion; 15. blade side edge A; 16. blade side edge B; 17. reinforcing rib. DETAILED DESCRIPTION

[0033] This section will describe in detail the specific embodiments of the present invention. The preferred embodiments of the present invention are shown in the accompanying drawings. The purpose of the accompanying drawings is to supplement the description of the text part of the specification with graphics, so that people can intuitively and vividly understand each technical feature and the overall technical solution of the present invention, but it cannot be understood as a limitation on the scope of protection of the present invention.

[0034] In the description of the present invention, it should be understood that descriptions involving orientations, such as up, down, front, back, left, right, etc., and orientations or positional relationships indicated are based on the orientations or positional relationships shown in the accompanying drawings, and are only for the convenience of describing the present invention and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and therefore should not be understood as a limitation on the present invention.

[0035] In the description of the present invention, "greater than", "less than", "exceed" etc. are understood as not including the number itself, and "above", "below", "within" etc. are understood as including the number itself. If there is a description of "first" or "second", it is only used for the purpose of distinguishing technical features, and cannot be understood as indicating or implying relative importance or implicitly indicating the number of the indicated technical features or implicitly indicating the order of the indicated technical features.

[0036] In the description of the present invention, unless otherwise clearly defined, terms such as setting, installing, connecting, etc. should be understood in a broad sense, and technicians in the relevant technical field can reasonably determine the specific meanings of the above terms in the present invention based on the specific content of the technical solution.

[0037] Embodiment 1:

[0038] See also Figure 1-6The present invention provides a technical solution: a gas turbine stator blade internal cooling channel structure, comprising a stator blade body 1, a blade suction surface 2 and a blade pressure surface 3, wherein the blade suction surface 2 and the blade pressure surface 3 are respectively arranged on two sides of the stator blade body 1 and bear the pressure and suction inside the gas turbine respectively, and film holes 14 are arranged at the relative positions of the blade suction surface 2 and the blade pressure surface 3 on the stator blade body 1 and are distributed in an array along the axial direction of the stator blade body 1 and are arranged through the stator blade body 1;

[0039] The blade length of the stationary blade body 1 is 450 mm, the blade tip radius and the blade root radius are equal to 100 mm, and the blade twist angle is 5°;

[0040] It also includes an upper edge portion 4, a lower edge portion 5 and a connecting seat 6, the upper edge portion 4 and the lower edge portion 5 are respectively arranged at the two ends of the stationary blade body 1, two groups of stationary blade bodies 1 are formed on a single group of connecting seats 6, the connecting seat 6 is connected to the end surface of the lower edge portion 5, and the end surface of the connecting seat 6 away from the lower edge portion 5 is integrally formed with a blade tenon portion 7 that can be clamped with an external tenon groove, and the cross-section of the blade tenon portion 7 is in the shape of an inverted electric tower;

[0041] It also includes a gas channel A10, a gas channel B11 and a heat-conducting chamber 13. The gas channel A10 and the gas channel B11 are respectively arranged on the inner sides of the two groups of stationary blade bodies 1 on the connecting seat 6. The gas channel A10 and the gas channel B11 both extend into the inner side of the connecting seat 6. The heat-conducting chamber 13 is integrally formed on the inner side of the connecting seat 6. The gas channel A10 and the gas channel B11 are both connected to the interior of the heat-conducting chamber 13.

[0042] Preferably, the gas channel A10 , the gas channel B11 and the inner wall of the heat-conducting chamber 13 are coated with heat-conducting material, and the air film hole 14 is not sealed.

[0043] Preferably, an air inlet portion 9 for introducing cooling gas into the stationary blade body 1 is integrally formed at the upper edge portion 4 of the stationary blade body 1 , and the air inlet portion 9 is connected to the gas channel A10 , the gas channel B11 and the heat conduction chamber 13 .

[0044] Preferably, a converging and guiding seat 12 is integrally formed at the inner middle section of the heat exchanger 6 , and the gas channel A10 and the gas channel B11 are respectively arranged on both sides of the converging and guiding seat 12 , and the converging and guiding seat 12 is located directly above the heat conduction chamber 13 .

[0045] Preferably, the air inlet portion 9 and the air outlet portion 8 are respectively provided with a plurality of groups of reinforcing ribs 17 distributed in an array and are integrally formed with the inner wall of the stationary blade body 1 and the blade tenon portion 7 .

[0046] Preferably, the two side end faces of the stationary blade body 1 are respectively set as blade side edge A15 and blade side edge B16, the angle formed by the blade side edge B16 is 5°, and the angle formed by the blade side edge B16 is not greater than half of the angle formed by the blade side edge A15.

[0047] Preferably, the diameter of the air film hole 14 is 5 mm, the maximum thickness of the stationary blade body 1 is 30 mm, and the minimum thickness of the stationary blade body 1 is 5 mm.

[0048] Preferably, the connecting seat 6 is made of a highly thermally conductive deformable material, and the tail end surface of the blade tenon portion 7 is integrally provided with an outlet portion 8 for discharging the heat exchange gas.

[0049] Embodiment 2:

[0050] See also Figure 1-6 The present invention provides a technical solution: a gas turbine stator blade internal cooling channel structure, comprising a stator blade body 1, a blade suction surface 2 and a blade pressure surface 3, wherein the blade suction surface 2 and the blade pressure surface 3 are respectively arranged on two sides of the stator blade body 1 and bear the pressure and suction inside the gas turbine respectively, and film holes 14 are arranged at the relative positions of the blade suction surface 2 and the blade pressure surface 3 on the stator blade body 1 and are distributed in an array along the axial direction of the stator blade body 1 and are arranged through the stator blade body 1;

[0051] The blade length of the stationary blade body 1 is 500 mm, the blade tip radius and the blade root radius are equal to 120 mm, and the blade twist angle is 7°;

[0052] It also includes an upper edge portion 4, a lower edge portion 5 and a connecting seat 6, the upper edge portion 4 and the lower edge portion 5 are respectively arranged at the two ends of the stationary blade body 1, two groups of stationary blade bodies 1 are formed on a single group of connecting seats 6, the connecting seat 6 is connected to the end surface of the lower edge portion 5, and the end surface of the connecting seat 6 away from the lower edge portion 5 is integrally formed with a blade tenon portion 7 that can be clamped with an external tenon groove, and the cross-section of the blade tenon portion 7 is in the shape of an inverted electric tower;

[0053] It also includes a gas channel A10, a gas channel B11 and a heat-conducting chamber 13. The gas channel A10 and the gas channel B11 are respectively arranged on the inner sides of the two groups of stationary blade bodies 1 on the connecting seat 6. The gas channel A10 and the gas channel B11 both extend into the inner side of the connecting seat 6. The heat-conducting chamber 13 is integrally formed on the inner side of the connecting seat 6. The gas channel A10 and the gas channel B11 are both connected to the interior of the heat-conducting chamber 13.

[0054] Preferably, the gas channel A10 , the gas channel B11 and the inner wall of the heat-conducting chamber 13 are coated with heat-conducting material, and the air film hole 14 is not sealed.

[0055] Preferably, an air inlet portion 9 for introducing cooling gas into the stationary blade body 1 is integrally formed at the upper edge portion 4 of the stationary blade body 1 , and the air inlet portion 9 is connected to the gas channel A10 , the gas channel B11 and the heat conduction chamber 13 .

[0056] Preferably, a converging and guiding seat 12 is integrally formed at the inner middle section of the heat exchanger 6 , and the gas channel A10 and the gas channel B11 are respectively arranged on both sides of the converging and guiding seat 12 , and the converging and guiding seat 12 is located directly above the heat conduction chamber 13 .

[0057] Preferably, the air inlet portion 9 and the air outlet portion 8 are respectively provided with a plurality of groups of reinforcing ribs 17 distributed in an array and are integrally formed with the inner wall of the stationary blade body 1 and the blade tenon portion 7 .

[0058] Preferably, the two side end faces of the stationary blade body 1 are respectively set as blade side edge A15 and blade side edge B16, the angle formed by the blade side edge B16 is 8°, and the angle formed by the blade side edge B16 is not greater than half of the angle formed by the blade side edge A15.

[0059] Preferably, the diameter of the air film hole 14 is 7 mm, the maximum thickness of the stationary blade body 1 is 30 mm, and the minimum thickness of the stationary blade body 1 is 5 mm.

[0060] Preferably, the connecting seat 6 is made of a highly thermally conductive deformable material, and the tail end surface of the blade tenon portion 7 is integrally provided with an outlet portion 8 for discharging the heat exchange gas.

[0061] Embodiment three:

[0062] See also Figure 1-6 The present invention provides a technical solution: a gas turbine stator blade internal cooling channel structure, comprising a stator blade body 1, a blade suction surface 2 and a blade pressure surface 3, wherein the blade suction surface 2 and the blade pressure surface 3 are respectively arranged on two sides of the stator blade body 1 and bear the pressure and suction inside the gas turbine respectively, and film holes 14 are arranged at the relative positions of the blade suction surface 2 and the blade pressure surface 3 on the stator blade body 1 and are distributed in an array along the axial direction of the stator blade body 1 and are arranged through the stator blade body 1;

[0063] The blade length of the stationary blade body 1 is 550 mm, the blade tip radius and the blade root radius are equal to 140 mm, and the blade twist angle is 10°;

[0064] It also includes an upper edge portion 4, a lower edge portion 5 and a connecting seat 6, the upper edge portion 4 and the lower edge portion 5 are respectively arranged at the two ends of the stationary blade body 1, two groups of stationary blade bodies 1 are formed on a single group of connecting seats 6, the connecting seat 6 is connected to the end surface of the lower edge portion 5, and the end surface of the connecting seat 6 away from the lower edge portion 5 is integrally formed with a blade tenon portion 7 that can be clamped with an external tenon groove, and the cross-section of the blade tenon portion 7 is in the shape of an inverted electric tower;

[0065] It also includes a gas channel A10, a gas channel B11 and a heat-conducting chamber 13. The gas channel A10 and the gas channel B11 are respectively arranged on the inner sides of the two groups of stationary blade bodies 1 on the connecting seat 6. The gas channel A10 and the gas channel B11 both extend into the inner side of the connecting seat 6. The heat-conducting chamber 13 is integrally formed on the inner side of the connecting seat 6. The gas channel A10 and the gas channel B11 are both connected to the interior of the heat-conducting chamber 13.

[0066] Preferably, the gas channel A10 , the gas channel B11 and the inner wall of the heat-conducting chamber 13 are coated with heat-conducting material, and the air film hole 14 is not sealed.

[0067] Preferably, an air inlet portion 9 for introducing cooling gas into the stationary blade body 1 is integrally formed at the upper edge portion 4 of the stationary blade body 1 , and the air inlet portion 9 is connected to the gas channel A10 , the gas channel B11 and the heat conduction chamber 13 .

[0068] Preferably, a converging and guiding seat 12 is integrally formed at the inner middle section of the heat exchanger 6 , and the gas channel A10 and the gas channel B11 are respectively arranged on both sides of the converging and guiding seat 12 , and the converging and guiding seat 12 is located directly above the heat conduction chamber 13 .

[0069] Preferably, the air inlet portion 9 and the air outlet portion 8 are respectively provided with a plurality of groups of reinforcing ribs 17 distributed in an array and are integrally formed with the inner wall of the stationary blade body 1 and the blade tenon portion 7 .

[0070] Preferably, the two side end faces of the stationary blade body 1 are respectively set as blade side edge A15 and blade side edge B16, the angle formed by the blade side edge B16 is 10°, and the angle formed by the blade side edge B16 is not greater than half of the angle formed by the blade side edge A15.

[0071] Preferably, the diameter of the air film hole 14 is 10 mm, the maximum thickness of the stationary blade body 1 is 30 mm, and the minimum thickness of the stationary blade body 1 is 5 mm.

[0072] Preferably, the connecting seat 6 is made of a highly thermally conductive deformable material, and the tail end surface of the blade tenon portion 7 is integrally provided with an outlet portion 8 for discharging the heat exchange gas.

[0073] ※Measurement and experiment were conducted on the gas turbine stator blade structure in Example 2. The measurement and experiment results are shown in the following table:

[0074]

[0075]

[0076]

[0077] The thermal efficiency of the stator blades under different temperature and load conditions was experimentally verified, showing a significant performance improvement.

[0078] Long-term operation tests were carried out under high temperature and high pressure environments to evaluate the wear and service life of the stator blades, proving their superior durability.

[0079] The optimization effect of airflow passing through the stator blades is verified through wind tunnel experiments or computational fluid dynamics (CFD) simulations, showing lower energy losses and higher aerodynamic efficiency.

[0080] The embodiments of the present invention are described in detail above with reference to the accompanying drawings. However, the present invention is not limited to the above embodiments. Various changes can be made within the knowledge scope of ordinary technicians in the technical field without departing from the purpose of the present invention.

Claims

1. A gas turbine stator blade internal cooling channel structure, characterized in that: include: A stationary blade body (1), a blade suction surface (2) and a blade pressure surface (3), wherein the blade suction surface (2) and the blade pressure surface (3) are arranged on two sides of the stationary blade body (1) and bear the pressure and suction inside the gas turbine respectively, and air film holes (14) are arranged in an array along the axial direction of the stationary blade body (1) and are arranged through the stationary blade body (1) at relative positions of the blade suction surface (2) and the blade pressure surface (3); The blade length of the stationary blade body (1) is 450-550 mm, the blade tip radius and the blade root radius are equal to each other, both being 100-140 mm, and the blade twist angle is 5-10°; An upper edge portion (4), a lower edge portion (5) and a connecting seat (6), wherein the upper edge portion (4) and the lower edge portion (5) are respectively arranged at two ends of the stationary blade body (1), two groups of stationary blade bodies (1) are formed on a single group of connecting seats (6), the connecting seat (6) is connected to the end surface of the lower edge portion (5), and the end surface of the connecting seat (6) away from the lower edge portion (5) is integrally provided with a blade tenon portion (7) that can be engaged with an external tenon groove, and the cross section of the blade tenon portion (7) is in the shape of an inverted electric tower; A gas channel A (10), a gas channel B (11) and a heat conduction chamber (13), wherein the gas channel A (10) and the gas channel B (11) are respectively arranged on the inner side of two groups of stationary blade bodies (1) on the connecting seat (6), and the gas channel A (10) and the gas channel B (11) both extend into the inner side of the connecting seat (6), and the heat conduction chamber (13) is integrally formed on the inner side of the connecting seat (6), and the gas channel A (10) and the gas channel B (11) are both connected to the interior of the heat conduction chamber (13).

2. The internal cooling channel structure of a gas turbine stator blade according to claim 1, characterized in that: The inner walls of the gas channel A (10), the gas channel B (11) and the heat-conducting chamber (13) are all coated with heat-conducting materials, and the air film hole portion (14) is not sealed.

3. The internal cooling channel structure of a gas turbine stator blade according to claim 2, characterized in that: An air inlet portion (9) for introducing cooling gas into the stationary blade body (1) is integrally formed at the upper edge portion (4) of the stationary blade body (1), and the air inlet portion (9) is connected to the gas channel A (10), the gas channel B (11) and the heat conduction chamber (13).

4. The internal cooling channel structure of a gas turbine stator blade according to claim 3, characterized in that: A converging and guiding seat (12) is integrally formed at the inner middle section of the above-mentioned 6, and the gas channel A (10) and the gas channel B (11) are respectively arranged on both sides of the converging and guiding seat (12), and the converging and guiding seat (12) is located directly above the heat conduction chamber (13).

5. The internal cooling channel structure of a gas turbine stator blade according to claim 4, characterized in that: The air inlet portion (9) and the air outlet portion (8) are respectively provided with a plurality of groups of reinforcing ribs (17) distributed in an array and integrally formed with the inner wall of the stationary blade body (1) and the blade tenon portion (7).

6. The internal cooling channel structure of a gas turbine stator blade according to claim 5, characterized in that: The two side end surfaces of the stationary blade body (1) are respectively configured as a blade side edge A (15) and a blade side edge B (16), the included angle formed by the blade side edge B (16) is 5-10°, and the included angle formed by the blade side edge B (16) is not greater than half of the included angle formed by the blade side edge A (15).

7. The internal cooling channel structure of a gas turbine stator blade according to claim 6, characterized in that: The aperture of the air film hole (14) is 5-10 mm, the maximum thickness of the stationary blade body (1) is 30 mm, and the minimum thickness of the stationary blade body (1) is 5 mm.

8. The internal cooling channel structure of a gas turbine stator blade according to claim 7, characterized in that: The connecting seat (6) is made of a highly heat-conductive deformable material, and the tail end surface of the blade tenon portion (7) is integrally provided with an outlet portion (8) for discharging heat exchange gas.

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