Double-walled turbine blade and gas turbine

Abstract

The application discloses a double-wall turbine blade and a gas turbine, and the double-wall turbine blade comprises an outer shell and an inner shell, the outer shell is sleeved with the inner shell, an annular flow channel is formed between the outer shell and the inner shell and surrounds the inner shell, a trailing edge flow channel and a gas outlet communicating with the trailing edge flow channel are arranged at a trailing edge of the blade, the trailing edge flow channel is located at the rear side of the annular flow channel, a leading edge flow channel is defined in the inner shell and is close to a leading edge of the blade, a leading edge flow channel and an annular flow channel are communicated through an impact hole arranged on the front wall of the inner shell, an inner shell flow channel is defined in the inner shell and is located at the rear side of the leading edge flow channel, an opening is arranged on the rear side of the inner shell and communicates the inner shell flow channel with the trailing edge flow channel, and the blade is further provided with an air inlet communicating with each of the leading edge flow channel and the inner shell flow channel. The annular flow channel is defined between the outer shell and the inner shell through the double-wall structure design, the heat exchange area of the cold air in the blade can be significantly increased, the cooling efficiency and the heat exchange capacity can be greatly improved, and the cooling effect on the pressure surface and the suction surface of the blade can be significantly improved.

Description

TECHNICAL FIELD

[0001] The present application relates to the field of gas turbine technology, in particular to a double-wall turbine blade and a gas turbine with the same. BACKGROUND

[0002] A gas turbine is an important power machine, which has important applications in many fields such as aviation propulsion, ship propulsion and power generation. The turbine inlet temperature of the gas turbine is much higher than the heat-resistant limit temperature of high-temperature alloy, so corresponding measures must be taken to reduce the blade operating temperature, and therefore blade cooling has become one of the major key technologies for ensuring the safe and reliable operation of the gas turbine.

[0003] The high-temperature blade of the turbine generally adopts a hollow structure, and the inside of the blade is cooled by high-pressure gas extracted from the compressor. The currently widely used cooling methods of the blade mainly include impingement cooling, ribbed serpentine channel cooling, column rib cooling and film cooling, but the heat transfer enhancement capacity of these cooling methods is still limited and cannot meet the operating conditions of advanced gas turbines with higher heat load. Moreover, with the development of technology over the past few decades, the research on the above-mentioned cooling methods has been relatively sufficient, and the cooling effect has reached the technical limit. If the cooling effect is to be greatly improved, the existing typical internal structure of the blade is difficult to achieve. SUMMARY

[0004] The present application aims to at least partially solve one of the problems in the related art. To this end, the embodiments of the present application propose a double-wall turbine blade with enhanced heat transfer capacity and cooling efficiency.

[0005] The embodiments of the present application also propose a gas turbine with the double-wall turbine blade.

[0006] The double-wall turbine blade of the embodiments of the present application comprises an outer shell and an inner shell, the outer shell is sleeved on the inner shell, an annular flow channel surrounding the inner shell is formed between the outer shell and the inner shell, a trailing edge flow channel and a gas outlet communicating with the trailing edge flow channel are provided at a trailing edge of the blade, the trailing edge flow channel is located at the rear side of the annular flow channel, a leading edge flow channel is defined in the inner shell near a leading edge of the blade, a front wall of the inner shell is provided with an impingement hole communicating the leading edge flow channel and the annular flow channel, an inner shell flow channel is defined in the inner shell at the rear side of the leading edge flow channel, an opening is provided at the rear side of the inner shell and communicates the inner shell flow channel and the trailing edge flow channel, and the blade further has an air inlet communicating with each of the leading edge flow channel and the inner shell flow channel.

[0007] The blade of the gas turbine provided by the embodiment of the present application is designed by a double-layer structure, an annular flow channel is defined between the outer shell and the inner shell, the cooling gas is sprayed from the impact hole on the front side of the inner shell to impact and cool the inner wall surface of the leading edge, and then is divided into two parts to flow backward along the annular flow channel, in the process, the two flows of cooling gas flow through the inner wall surface of the pressure surface and the inner wall surface of the suction surface respectively, and finally is sprayed from the trailing edge. The arrangement can significantly increase the heat exchange area of the cooling gas in the blade, and the cooling gas can take away more heat under the condition of unchanged flow, greatly improving the cooling efficiency and heat exchange capacity, and significantly improving the cooling effect on the pressure surface and the suction surface of the blade.

[0008] In some embodiments, the annular flow channel is provided with a first column rib structure, the first column rib structure comprises a plurality of first column ribs, one end of the first column rib is connected with the inner shell, and the other end of the first column rib is connected with the outer shell.

[0009] In some embodiments, the first column rib is located on both sides of the inner shell.

[0010] In some embodiments, the trailing edge is provided with a second column rib structure, the second column rib structure comprises a plurality of second column ribs, and the plurality of second column ribs define the trailing edge flow channel.

[0011] In some embodiments, the inner shell is provided with a partition plate, and the partition plate is used to isolate the leading edge flow channel and the inner shell flow channel.

[0012] In some embodiments, the inner shell is provided with a plurality of flow channel walls extending along the length direction of the blade, the plurality of flow channel walls define a serpentine inner shell flow channel, and the serpentine inner shell flow channel comprises a plurality of flow channel segments extending along the length direction of the blade.

[0013] In some embodiments, the plurality of flow channel walls are arranged at intervals in the leading edge-trailing edge direction, the flow channel segment close to the leading edge is in communication with the air inlet, and the flow channel segment close to the trailing edge is in communication with the opening.

[0014] In some embodiments, the front wall of the inner shell is a flat plate structure, and the two side walls of the inner shell are arc-shaped structures.

[0015] In some embodiments, the air outlet is located behind the trailing edge flow channel.

[0016] The gas turbine of another aspect of the embodiment of the present application comprises the blade according to any one of the above embodiments. BRIEF DESCRIPTION OF DRAWINGS

[0017] Figure 1 is the profile view of the blade of the gas turbine provided by the embodiment of the present application.

[0018] Figure 2This is an AA cross-sectional view of the blades of a gas turbine provided in an embodiment of the present invention.

[0019] Figure 3 yes Figure 2 BB cross-sectional view.

[0020] Figure 4 This is a schematic diagram of the second column rib structure provided in one embodiment of the present invention.

[0021] Figure 5 This is a schematic diagram of the second column rib structure provided in another embodiment of the present invention.

[0022] Figure label:

[0023] 100 leaves

[0024] Outer shell 1, annular flow channel 12, first column rib 121

[0025] 2. Inner shell; 21. Inner shell flow channel; 22. Opening; 23. Flow channel wall; 24. Flow channel section; 25. Impact hole.

[0026] Leading edge 3, leading edge flow channel 31

[0027] Trailing edge 4, trailing edge channel 41, air outlet 42, second pillar rib 43

[0028] Pressure surface 5, suction surface 6, partition 71

[0029] First air intake 81, second air intake 82. Detailed Implementation

[0030] Embodiments of the present invention are described in detail below, examples of which are illustrated in the accompanying drawings. The embodiments described below with reference to the accompanying drawings are exemplary and intended to explain the present invention, and should not be construed as limiting the present invention.

[0031] The following is based on Figures 1-5 This invention describes a double-walled turbine blade 100 provided in an embodiment of the present invention. The blade 100 has a leading edge 3 and a trailing edge 4. As those skilled in the art will know, the leading edge 3 is the wider side of the outer contour of the blade 100, and the trailing edge 4 is the narrower side of the outer contour of the blade 100. The two outer wall surfaces of the blade 100 are an inwardly concave pressure surface 5 and an outwardly protruding suction surface 6, respectively.

[0032] The vane 100 comprises an outer shell 1 and an inner shell 2, the outer shell 1 is sleeved on the inner shell 2, and an annular flow channel 12 is formed between the outer shell 1 and the inner shell 2 and surrounds the inner shell 2. The tail edge 4 of the vane 100 is provided with a tail edge flow channel 41 and an air outlet 42 communicating with the tail edge flow channel 41. The tail edge flow channel 41 is located at the rear side of the annular flow channel 12, that is, the tail edge flow channel 41 is closer to the tail edge 4 of the vane 100 than the annular flow channel 12. The inner shell 2 defines a leading edge flow channel 31 at the leading edge 3 of the vane 100. The front wall of the inner shell 2 is provided with an impact hole 25 communicating the leading edge flow channel 31 and the annular flow channel 12. That is, the wall surface of the inner shell 2 close to the leading edge 3 of the vane 100 is provided with the impact hole 25 penetrating the inner shell 2. The cooling gas in the leading edge flow channel 31 enters the annular flow channel 12 through the impact hole 25, impacts the corresponding inner wall surface of the leading edge 3, cools the leading edge 3, and then flows along the annular flow channel 12 to the tail edge 4. In the process, the cooling gas flows through the corresponding inner wall surface of each of the pressure surface 5 and the suction surface 6, enters the tail edge flow channel 41, and then flows along the tail edge flow channel 41 and is sprayed out of the air outlet 42 at the tail edge 4. The flow of the cooling gas in the annular flow channel 12 can effectively cool the pressure surface 5 and the suction surface 6.

[0033] The inner shell 2 defines an inner shell flow channel 21 at the rear side of the leading edge flow channel 31. That is, the inner shell flow channel 21 is located at the rear side of the leading edge flow channel 31. The rear side of the inner shell 2 is provided with an opening 22 communicating the inner shell flow channel 21 and the tail edge flow channel 41. The cooling gas in the inner shell flow channel 21 flows out of the inner shell 2 through the opening 22, enters the tail edge flow channel 41, and then flows along the tail edge flow channel 41 and is sprayed out of the air outlet 42 at the tail edge 4 after being combined with the cooling gas in the annular flow channel 12, so as to cool the tail edge 4 of the vane 100.

[0034] The vane 100 is also provided with an air inlet communicating each of the leading edge flow channel 31 and the inner shell flow channel 21. The cooling gas enters the leading edge flow channel 31 and the inner shell flow channel 21 from the air inlet.

[0035] The vane of the gas turbine provided by the embodiment of the present application has a double-layer structure design. The annular flow channel is defined between the outer shell and the inner shell. The cooling gas is sprayed out of the impact hole at the front side of the inner shell, impacts the inner wall surface of the leading edge, and then is divided into two parts and flows backward along the annular flow channel. In the process, the two parts of the cooling gas flow through the inner wall surface of the pressure surface and the inner wall surface of the suction surface, respectively, and are finally sprayed out of the tail edge. Such a design can significantly increase the heat exchange area of the cooling gas inside the vane. Under the condition that the flow rate is unchanged, the cooling gas can carry away more heat, greatly improves the cooling efficiency and heat exchange capacity, and significantly improves the cooling effect of the pressure surface and the suction surface of the vane.

[0036] Therefore, the vane of the gas turbine provided by the embodiment of the present application can significantly improve the heat exchange capacity of the internal structure and greatly improve the cooling effect of the cooling gas on the high-temperature vane.

[0037] For the convenience of description, the length direction of the blade 100 shown in Figure 2 is taken as the up-down direction, and the leading edge-trailing edge direction is taken as the front-rear direction, and the technical solutions of the embodiments of the present application are described, and the up-down direction and the front-rear direction are indicated by arrows in Figure 2 .

[0038] In some embodiments, as shown in Figure 2 and Figure 3 , the inner shell 2 has a partition plate 71 located between the leading edge flow channel 31 and the inner shell flow channel 21, for isolating the leading edge flow channel 31 and the inner shell flow channel 21. Specifically, as shown in Figure 1 , the partition plate 71 extends in the vertical direction and is connected to the two side wall surfaces of the inner shell 2.

[0039] As shown in Figure 2 , the air inlet is arranged at the bottom of the blade 100, and the air inlet includes a first air inlet 81 and a second air inlet 82. The first air inlet 81 is in communication with the bottom of the leading edge flow channel 31, and the cooling air flows upward from the first air inlet 81 into the leading edge flow channel 31. The second air inlet 82 is in communication with the bottom of the inner shell flow channel 21, and the cooling air flows upward from the second air inlet 82 into the inner shell flow channel 21.

[0040] In some embodiments, as shown in Figure 3 , the front wall of the inner shell 2 is a flat plate structure, the two side walls of the inner shell 2 are arc-shaped structures, and the two side wall surfaces of the inner shell 2 are arc-shaped structures matched with the structure of the outer shell 1.

[0041] Specifically, the front wall of the inner shell 2 extends in the length direction of the blade 100, and a plurality of impact holes 25 are distributed on the front wall of the inner shell 2 and penetrate the front wall. The impact holes 25 are opposite to the inner wall surface of the leading edge 3. The cooling air enters the leading edge flow channel 31 through the first air inlet 81 and flows upward, is ejected forward through the impact holes 25, enters the annular flow channel 12, and has an impact cooling effect on the inner wall surface of the leading edge 3. After impacting the inner wall surface of the leading edge 3, the cooling air is divided into two parts, which respectively enter the annular flow channel 12 from the two sides and flow along the annular flow channel 12 to the trailing edge 4.

[0042] In some embodiments, the leading edge 3 can also be provided with a plurality of air outlets, but it should be noted that part of the cooling air in the annular flow channel 12 can be ejected from the air outlets of the leading edge 3 to better cool the leading edge 3, but another part of the cooling air will still flow backward through the annular flow channel 12.

[0043] In some embodiments, the first column rib structure is arranged in the annular flow channel 12, and the first column rib structure comprises a plurality of first column ribs 121. One end of the first column rib 121 is connected to the inner shell 2, and the other end of the first column rib 121 is connected to the outer shell 1. The cooling gas entering the annular flow channel 12 flows along the gaps formed between the first column ribs 121. The first column ribs 121 not only increase the heat exchange area, but also enhance the structural strength of the blade 100.

[0044] As shown in Figs. 1 and 2, the first column rib 121 is arranged on both sides of the inner shell 2, and the first end of the first column rib 121 is connected to one outer side surface of the inner shell 2, and the second end is connected to the inner wall surface of the outer shell 1. The first column rib 121 is arranged in the up-down direction and the circumferential direction around the inner shell 2. Figure 2 Figure 3 As shown in Figs. 1 and 2, the first column rib 121 is arranged on both sides of the inner shell 2, and the first end of the first column rib 121 is connected to one outer side surface of the inner shell 2, and the second end is connected to the inner wall surface of the outer shell 1. The first column rib 121 is arranged in the up-down direction and the circumferential direction around the inner shell 2.

[0045] Further, the heat conduction effect of the first column rib 121 can also reduce the temperature difference between the inner shell 2 and the outer shell 1 to a certain extent, so that the temperature inside and outside the blade 100 is more uniform, and the thermal stress is reduced.

[0046] Optionally, the first column rib 121 is a cylindrical rib or a prismatic rib. Preferably, the first column rib 121 is a prismatic rib, for example, the cross-sectional shape of the first column rib 121 is a quadrangular prism. Compared with the cylindrical rib, the prismatic rib has higher heat exchange enhancement capability, so that the blade 100 provided by the embodiment of the present application has better cooling effect.

[0047] In some embodiments, as shown in Figs. 1 and 2, the second column rib structure is arranged at the trailing edge, and the second column rib structure comprises a plurality of second column ribs 43, and the plurality of second column ribs 43 define a trailing edge flow channel 41. The cooling gas entering the trailing edge flow channel 41 passes between the second column ribs 43 and changes direction after contacting the second column ribs 43, so as to realize the tumbling of the cooling gas at the trailing edge, prolong the flow time of the cooling gas in the trailing edge flow channel 41, and further improve the heat dissipation effect. Figure 2 Figure 3 As shown in Figs. 1 and 2, the two ends of the second column rib 43 are respectively connected to the two side wall surfaces of the inner side of the outer shell 1, and the plurality of second column ribs 43 are arranged in the up-down direction and the front-back direction. The second column rib structure not only increases the heat exchange area and enhances the heat exchange effect, but also enhances the structural strength of the trailing edge 4.

[0048] As shown in Figs. 1 and 2, the two ends of the second column rib 43 are respectively connected to the two side wall surfaces of the inner side of the outer shell 1, and the plurality of second column ribs 43 are arranged in the up-down direction and the front-back direction. The second column rib structure not only increases the heat exchange area and enhances the heat exchange effect, but also enhances the structural strength of the trailing edge 4. Figure 2 Figure 3 Further, the plurality of second column ribs 43 in the second column rib structure are staggered. As shown in Figs. 1 and 2, the plurality of second column ribs 43 are staggered in the up-down direction and the front-back direction.

[0049] Further, the plurality of second column ribs 43 in the second column rib structure are staggered. As shown in Figs. 1 and 2, the plurality of second column ribs 43 are staggered in the up-down direction and the front-back direction. Figure 2 ​​​As shown, the second column ribs 43 are arranged in multiple rows, each row including multiple second column ribs 43 arranged in the front-rear direction, and adjacent rows of second column ribs 43 are arranged in the up-down direction. In this way, the length of the trailing edge flow channel 41 can be further extended, the flow time of the cooling gas in the trailing edge flow channel 41 is extended, and the heat dissipation cooling effect is improved.

[0050] Optionally, the second column ribs 43 are cylindrical ribs or prismatic ribs. Preferably, the second column ribs 43 are prismatic ribs, for example, as shown in Figure 4 As shown, the cross-sectional shape of the second column ribs 43 is rhombus. As shown in Figure 5 As shown, the cross-section of the second column ribs 43 is rectangular. The arrows in the figure are the flow direction of the cooling gas. Compared with cylindrical ribs, prismatic ribs have higher heat transfer enhancement capability, so that the blade 100 provided by the embodiment of the present application has better cooling effect.

[0051] In some embodiments, as shown in Figure 2 and Figure 3 A plurality of flow channel walls 23 extending in the length direction of the blade 100 (up-down direction) are arranged in the inner shell 2, and the plurality of flow channel walls 23 define a serpentine inner shell flow channel 21, which includes a plurality of flow channel segments 24 extending in the length direction of the blade (up-down direction). The plurality of flow channel walls 23 are arranged in the front-rear direction, the flow channel segment 24 near the leading edge 3 is in communication with the second air inlet 82, and the flow channel segment 24 near the trailing edge 4 is in communication with the opening 22.

[0052] Specifically, as shown in Figure 2 and Figure 3 Two vertically arranged flow channel walls 23 are arranged in the inner shell 2, and the two flow channel walls 23 are arranged in the front-rear direction to define a serpentine inner shell flow channel 21 in the inner space of the inner shell 2 behind the leading edge flow channel 31, and the inner shell flow channel 21 includes three vertically extending flow channel segments 24, and adjacent flow channel segments 24 are connected end to end. The second air inlet 82 is in communication with the bottom of the frontmost flow channel segment 24, and the rearmost flow channel segment 24 is in communication with the opening 22, and further in communication with the trailing edge flow channel 41.

[0053] The serpentine inner shell flow channel 21 extends the length and time of the flow path of the cooling gas in the inner shell flow channel 21, thereby further improving the heat transfer capacity of the cooling gas and enhancing the heat transfer effect.

[0054] It can be understood that in other embodiments, a larger number of flow channel walls 23 can be arranged in the inner shell 2 to further extend the length of the inner shell flow channel 21.

[0055] Optionally, the opening 22 arranged at the rear side of the inner shell 2 can be a hole or a slit.

[0056] Optionally, the air outlet 42 can be a hole or a slit.

[0057] Preferably, as shown in Figure 2 and Figure 3 The air outlet 42 is located behind the trailing edge flow channel 41. The air outlet 42 is arranged at the last end of the shell 1, so that the air outlet 42 is on the air inlet side of the trailing edge flow channel 41, which can maximize the length of the trailing edge flow channel 41 and ensure that the cooling air can maximize the contact cooling of the trailing edge 4.

[0058] The cooling principle and process of the blade 100 in the above embodiment will be described below. Figure 2 and Figure 3 The cooling principle and process of the blade 100 in the above embodiment will be described below.

[0059] The flow path of the cooling air inside the blade 100 is specifically shown by arrows in Figure 2 and Figure 3 A part of the cooling air enters the leading edge flow channel 31 from the first air inlet 81 at the bottom, and then is sprayed out through the impingement hole 25 on the front wall of the inner shell 2 to cool the leading edge 3. Another part of the cooling air enters the inner shell flow channel 21 from the second air inlet 82 at the bottom, and flows backward along the serpentine inner shell flow channel 21, and flows into the trailing edge flow channel 41 from the opening 22 at the rear side of the inner shell 2.

[0060] The cooling air sprayed out of the impingement hole 25 is divided into two parts and flows towards the trailing edge 4 along the annular flow channel 12. In the annular flow channel 12, the cooling air is in contact with the first column rib structure for heat exchange, and also in contact with the inner wall surface corresponding to the pressure surface 5 and the suction surface 6 for heat exchange, thereby effectively cooling the pressure surface 5 and the suction surface 6. The cooling air flowing out of the annular flow channel 12 converges with the cooling air flowing out of the inner shell flow channel 21, and then enters the trailing edge flow channel 41, flows through the trailing edge flow channel 41, and is sprayed out of the air outlet 42, thereby effectively cooling the trailing edge 4, and the second column rib structure in the trailing edge 4 enhances the heat exchange.

[0061] The leading edge 3 of the blade of the gas turbine in the above embodiment uses impingement cooling, the trailing edge 4 uses column rib channel cooling, and the middle part uses double-layer structure cooling. The double-layer structure design cools the inner wall surface corresponding to the pressure surface 5 and the suction surface 6, which has stronger heat exchange capacity than the traditional ribbed channel, the heat exchange area of the cooling air is significantly increased, and the cooling air will carry away more heat under the same flow, thereby greatly improving the utilization efficiency of the cooling air. And the column rib structure is used in the annular flow channel 12 to further enhance the heat exchange capacity. Therefore, the blade 100 provided by the embodiment of the present application has good cooling effect.

[0062] Another embodiment of the present application provides a gas turbine comprising the blade 100 of any of the above embodiments. In the description of the present application, it needs to be understood that the orientation or positional relationship indicated by the terms "center", "longitudinal", "lateral", "length", "width", "thickness", "upper", "lower", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", "clockwise", "counterclockwise", "axial", "radial", "circumferential" and the like is based on the orientation or positional relationship shown in the drawings, and is only for the convenience of describing the present application and simplifying the description, and does not indicate or imply that the device or element indicated must have a particular orientation, be constructed and operated in a particular orientation, and therefore cannot be understood as a limitation of the present application.

[0063] In addition, the terms "first", "second", "third", etc. are only used for descriptive purposes and cannot be understood as indicating or implying relative importance or implicitly indicating the number of technical features indicated. Therefore, the features defined with "first", "second", etc. can explicitly or implicitly include at least one of the features. In the description of the present application, the meaning of "a plurality of" is at least two, for example, two, three, etc., unless otherwise explicitly specified and limited.

[0064] In the present application, unless otherwise explicitly specified and limited, the terms "mounting", "connecting", "connecting", "fixing" and the like should be understood broadly, for example, it can be fixedly connected, or it can be detachably connected, or it can be integrated; it can be mechanically connected, or it can be electrically connected or in communication with each other; it can be directly connected, or it can be indirectly connected through an intermediate medium; it can be the internal communication or interaction relationship of two elements, unless otherwise explicitly limited. For those skilled in the art, the specific meaning of the above terms in the present application can be understood according to the specific circumstances.

[0065] In the present application, unless otherwise explicitly specified and limited, the first feature "on" or "under" the second feature can be that the first and second features are in direct contact, or the first and second features are in indirect contact through an intermediate medium. Moreover, the first feature "above", "over" and "on" the second feature can be that the first feature is directly above or obliquely above the second feature, or it can only mean that the horizontal height of the first feature is higher than that of the second feature. The first feature "below", "under" and "under" the second feature can be that the first feature is directly below or obliquely below the second feature, or it can only mean that the horizontal height of the first feature is less than that of the second feature.

[0066] In this disclosure, the terms "one embodiment", "some embodiments", "an example", "a specific example", or "some examples" mean that a particular feature, structure, material, or characteristic is included in at least one embodiment or example of the present disclosure. The illustrative appearances of the above-mentioned terms in various places in the specification are not necessarily referred to the same embodiment or example. Moreover, the particular features, structures, materials, or characteristics can be combined in any suitable manner in one or more embodiments or examples. Furthermore, the terminology "comprising" is used in the disclosure as comprising, but not limited to, any indicated features, integers, steps or components. It is also to be understood that the terminology "comprising" can be replaced by the terminology "consisting of" or "consisting essentially of" in some embodiments or examples.

[0067] Although the above-mentioned embodiments have been shown and described, it is to be understood that the above-mentioned embodiments are exemplary, and should not be understood as limiting the present disclosure, and the changes, modifications, replacements and variations of the above-mentioned embodiments made by those skilled in the art are within the protection scope of the present disclosure.

Claims

1. A double-walled turbine blade, characterized by, The turbine blade comprises: an outer shell and an inner shell, the outer shell being sleeved on the inner shell, an annular flow channel being formed between the outer shell and the inner shell and surrounding the inner shell, a trailing edge flow channel being provided at a trailing edge of the blade, an air outlet being in communication with the trailing edge flow channel, the trailing edge flow channel being located at a rear side of the annular flow channel, a leading edge flow channel being defined in the inner shell near a leading edge of the blade, a front wall of the inner shell being provided with an impact hole in communication with the leading edge flow channel and the annular flow channel, an inner shell flow channel being defined in the inner shell at a rear side of the leading edge flow channel, an opening being provided at a rear side of the inner shell in communication with the inner shell flow channel and the trailing edge flow channel, the blade further comprising an air inlet in communication with each of the leading edge flow channel and the inner shell flow channel; a partition plate being provided in the inner shell and separating the leading edge flow channel and the inner shell flow channel; cooling air in the inner shell flow channel flows out of the inner shell through the opening into the trailing edge flow channel, and is sprayed out of the air outlet at the trailing edge after flowing along the trailing edge flow channel after being combined with cooling air in the annular flow channel.

2. The turbine blade according to claim 1, wherein a first column rib structure is provided in the annular flow channel, the first column rib structure comprising a plurality of first column ribs, one end of each of the first column ribs being connected to the inner shell, and the other end of each of the first column ribs being connected to the outer shell.

3. The turbine blade according to claim 2, wherein the first column ribs are located on both sides of the inner shell.

4. The turbine blade according to claim 1, wherein a second column rib structure is provided at the trailing edge, the second column rib structure comprising a plurality of second column ribs, the plurality of second column ribs defining the trailing edge flow channel.

5. The turbine blade according to claim 1, wherein a plurality of flow channel walls extending along the length of the blade are provided in the inner shell, the plurality of flow channel walls defining a serpentine-shaped inner shell flow channel, the serpentine-shaped inner shell flow channel comprising a plurality of flow channel segments extending along the length of the blade.

6. The turbine blade according to claim 5, wherein the plurality of flow channel walls are arranged at intervals in the leading edge-trailing edge direction, the flow channel segment near the leading edge being in communication with the air inlet, and the flow channel segment near the trailing edge being in communication with the opening.

7. The turbine blade according to claim 1, wherein the front wall of the inner shell is a flat plate structure, and the two side walls of the inner shell are arc-shaped structures.

8. The double-walled turbine blade of claim 1, wherein the air outlet is located at the rear of the trailing edge flow channel.

9. A gas turbine engine characterized by, the turbine comprises the blade according to any one of claims 1-8.

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