Gas turbine blades and gas turbines

Abstract

The present invention provides a gas turbine blade and a gas turbine. The gas turbine blade of the present invention comprises: a blade body having a cooling cavity and a cooling channel connected to the cooling cavity; a throttle element located within the cooling channel and / or located at the inlet of the cooling channel, the throttle element being made of a shape memory alloy and having different shapes corresponding to different temperatures. When the temperature of the cooling gas entering the cooling channel rises from a first preset temperature to a second preset temperature, the throttle element contracts and deforms from the first preset shape to the second preset shape. When the throttle element contracts and deforms from the first preset shape to the second preset shape, the flow cross-section of the cooling channel increases, thereby increasing the flow rate of the cooling gas flowing into the cooling channel. The gas turbine blade of the present invention has the advantages of reducing excessive consumption of cooling gas and reducing efficiency losses of the gas turbine.

Description

Technical Field

[0001] The present invention relates to the technical field of gas turbines, and in particular to a gas turbine blade and a gas turbine. Background Art

[0002] In the related art, gas turbine blades use throttle orifice plates made of high-temperature alloys to control blade cooling. Under low operating conditions, the cooling air flow rate obtained by the blades will not be further fine-tuned, resulting in excessive cooling of the blades and excessive consumption of cooling air, causing efficiency loss of the gas turbine. Summary of the Invention

[0003] This invention is based on the inventors' discovery and understanding of the following facts and problems: the cross-sectional area of ​​the orifice plate, which controls the flow rate, is fixed. The cooling air flow rate cannot be controlled by varying the cross-sectional area, resulting in the air flow rate not matching the optimal characteristics of the combustion engine operating conditions. Under the same operating conditions, changes in cooling air temperature are not reflected in the cooling air flow rate.

[0004] The present invention aims to solve one of the technical problems in the related art at least to a certain extent. To this end, an embodiment of the present invention provides a gas turbine blade and a gas turbine.

[0005] A gas turbine blade according to an embodiment of the present invention includes:

[0006] a blade body, the blade body having a cooling cavity and a cooling channel communicating with the cooling cavity, the cooling channel being adapted to allow cooling gas to pass through;

[0007] A throttling element, wherein the throttling element is located in the cooling channel, and / or the throttling element is arranged at the inlet of the cooling channel, the throttling element is made of shape memory alloy material, the throttling element has different shapes corresponding to different temperatures so that the throttling element has a first preset shape and a second preset shape, when the temperature of the cooling gas entering the cooling channel rises from the first preset temperature to the second preset temperature, the throttling element shrinks and deforms from the first preset shape to the second preset shape, and when the throttling element shrinks and deforms from the first preset shape to the second preset shape, the flow cross-section of the cooling channel increases so as to increase the flow rate of the cooling gas flowing into the cooling channel.

[0008] Therefore, the gas turbine blade according to the embodiment of the present invention has the advantage of reducing excessive consumption of cooling gas and reducing efficiency loss of the gas turbine.

[0009] In some embodiments, the thickness direction of the throttling element is consistent with the extension direction of the cooling channel, and in a cross section perpendicular to the thickness direction of the throttling element, the projected area of ​​the throttling element decreases when the throttling element shrinks and deforms from the first preset shape to the second preset shape.

[0010] In some embodiments, the blade body includes a main body portion and a throttle orifice plate, the cooling channel includes a connected air inlet channel and a connecting channel, the throttle orifice plate has the air inlet channel, the main body portion has the connecting channel and the cooling cavity, the throttle orifice plate is arranged at the inlet of the connecting channel of the main body portion, the shape of the air inlet channel is adapted to the shape of the connecting channel, the throttling element is arranged on the throttle orifice plate, and on a cross section perpendicular to the thickness direction of the throttling element, at least part of the projection of the throttling element in the first preset shape coincides with at least part of the projection of the cooling channel.

[0011] In some embodiments, the throttling element is located on a side of the throttling orifice plate facing away from the main body.

[0012] In some embodiments, the throttling element is located in the intake passage and connected to an inner wall surface of the intake passage.

[0013] In some embodiments, there are multiple throttling elements and multiple cooling channels, and the multiple throttling elements are matched with the multiple cooling channels in a one-to-one correspondence.

[0014] In some embodiments, the throttling element is in the form of a sheet or a mesh.

[0015] In some embodiments, when the throttling element is in the first preset shape, a ratio of a flow cross-section of the cooling channel to a total flow cross-section of the cooling channel is (0.5-0.8):1.

[0016] In some embodiments, the first preset temperature is less than or equal to 100° C., and the second preset temperature is greater than or equal to 600° C.

[0017] The present invention also provides a gas turbine comprising the above-mentioned gas turbine blades. BRIEF DESCRIPTION OF THE DRAWINGS

[0018] Figure 1 is a schematic diagram of a gas turbine blade according to an embodiment of the present invention.

[0019] Figure 2 Schematic diagram of a throttling orifice plate and a throttling element according to an embodiment of the present invention.

[0020] Figure 3 Schematic diagram of a throttling orifice plate and a throttling element according to an embodiment of the present invention.

[0021] Reference numerals:

[0022] Gas turbine blade 100;

[0023] Blade body 1, cooling cavity 11, cooling channel 12, first end surface 121, connecting channel 122;

[0024] Throttle element 2;

[0025] Throttle orifice plate 3, air intake channel 31. DETAILED DESCRIPTION

[0026] The embodiments of the present invention are described in detail below, and examples of the embodiments are shown in the accompanying drawings. The embodiments described below with reference to the accompanying drawings are exemplary and intended to be used to explain the present invention, but should not be understood as limiting the present invention.

[0027] The following describes a gas turbine blade 100 according to an embodiment of the present invention with reference to the accompanying drawings. Figures 1 to 3 As shown, a gas turbine blade 100 according to an embodiment of the present invention includes a blade body 1 and a throttling element 2 .

[0028] The blade body 1 has a cooling cavity 11 and a cooling channel 12 communicating with the cooling cavity 11 . The cooling channel 12 is adapted to receive cooling gas. The throttling element 2 is located in the cooling channel 12 and / or is provided at the inlet of the cooling channel 12 .

[0029] The throttle element 2 is made of a shape memory alloy and has different shapes corresponding to different temperatures, resulting in a first predetermined shape and a second predetermined shape. When the temperature of the cooling gas entering the cooling channel 12 rises from the first predetermined temperature to the second predetermined temperature, the throttle element 2 contracts and deforms from the first predetermined shape to the second predetermined shape. When the throttle element 2 contracts and deforms from the first predetermined shape to the second predetermined shape, the flow cross-section of the cooling channel 12 increases, thereby increasing the flow rate of the cooling gas flowing into the cooling channel 12.

[0030] The present invention is based on the inventor's discovery and understanding of the following facts and problems: the flow control hole cross-sectional area of ​​the throttle orifice plate is fixed, the size of the cold air flow cannot be controlled by changing its flow area, the air flow rate does not match the optimal characteristics of the gas turbine operating conditions, and the change of the cold air temperature will not be reflected in the cold air flow rate.

[0031] According to an embodiment of the present invention, the gas turbine blade 100 is provided with a throttling element 2 at least one of the inside and the inlet of the cooling channel 12. Thus, on a cross section perpendicular to the extension direction of the cooling channel 2, the projection of the throttling element 2 can coincide with the projection of the cooling channel 2, thereby reducing the flow area of ​​the cooling channel 12 and further reducing the flow rate of the cooling gas flowing into the cooling channel 12.

[0032] The throttling element 2 is made of a shape memory alloy and has different shapes corresponding to different temperatures. The throttling element 2 has a first preset shape and a second preset shape. Specifically, the projected area of ​​the throttling element 2 in the first preset shape, along a cross section perpendicular to the direction in which the cooling channel 2 extends, is greater than the projected area of ​​the throttling element 2 in the second preset shape, along a cross section perpendicular to the direction in which the cooling channel 2 extends. In other words, when the throttling element 2 contracts and deforms from the first preset shape to the second preset shape, the flow cross-section of the cooling channel 12 increases, thereby increasing the flow rate of the cooling gas flowing into the cooling channel 12, thereby allowing more cooling gas to cool the blade body 1.

[0033] When the temperature of the cooling gas entering the cooling channel 12 rises from a first preset temperature to a second preset temperature, the throttle element 2 contracts and deforms from the first preset shape to the second preset shape. Specifically, when the temperature of the cooling gas entering the cooling channel 12 rises, the throttle element 2 contracts, increasing the flow cross-section of the cooling channel 12 so that more cooling gas can enter the blade body 1 for cooling, thereby ensuring effective cooling of the blade body 1. In other words, as the operating conditions of the gas turbine change, the temperature of the cooling gas entering the blade body 1 changes (the cooling gas temperature increases under high operating conditions). The gas turbine blade 100 according to this embodiment of the present invention is capable of adjusting the flow cross-section of the cooling channel 12 based on the temperature of the cooling gas. This allows the flow rate of the cooling gas entering the blade body 1 to be dependent on the cooling gas temperature. This allows the amount of cooling gas used to be reduced while maintaining sufficient cooling gas to cool the blade body 1. This prevents overcooling of the blade body 1, reduces excessive cooling gas consumption, and reduces gas turbine efficiency losses.

[0034] Therefore, the gas turbine blade 100 according to the embodiment of the present invention has the advantage of reducing excessive consumption of cooling gas and reducing efficiency loss of the gas turbine.

[0035] The present invention also provides a gas turbine. The gas turbine according to an embodiment of the present invention includes a gas turbine blade 100 according to an embodiment of the present invention. In related art, changes in cooling air temperature are not reflected in the cooling air flow rate, and the cooling air flow rate received by the blade is not further finely adjusted, resulting in overcooling of the blade and excessive cooling air consumption, which causes efficiency loss in the gas turbine. The gas turbine blade 100 according to an embodiment of the present invention is provided with a throttling element 2. This allows the cooling air temperature to change when operating conditions change, i.e., the cooling air temperature entering the blade body 1 changes. The throttling element 2 on the blade body 1 can contract or expand according to the temperature of the cooling air entering the blade body 1 to adjust the flow cross-section of the cooling channel 12, thereby making the flow rate entering the corresponding blade body 1 dependent on the cooling air temperature. This reduces overcooling of the blade body 1, thereby reducing excessive cooling air consumption and reducing efficiency loss in the gas turbine.

[0036] Therefore, the gas turbine according to the embodiment of the present invention has the advantages of reducing excessive consumption of cooling gas and reducing efficiency loss of the gas turbine.

[0037] like Figures 1 to 3 As shown, a gas turbine blade 100 according to an embodiment of the present invention includes a blade body 1 and a throttling element 2 .

[0038] The blade body 1 has a cooling cavity 11 and a cooling channel 12 connected to the cooling cavity 11. The cooling channel 12 is suitable for passing cooling gas. Specifically, the cooling channel 12 is suitable for being connected to the rotor of the gas turbine. The cooling gas can pass into the cooling channel 12 so as to enter the cooling cavity 11.

[0039] like Figure 1 As shown, in some embodiments, the blade body 1 has a plurality of cooling channels 12. For example, each blade body 1 has two or three cooling channels 12.

[0040] The throttling element 2 is made of a shape memory alloy material. The throttling element 2 has different shapes corresponding to different temperatures, so that the throttling element 2 has a first preset shape and a second preset shape. Specifically, the shape memory alloy is a martensitic phase transformation alloy with a very regular atomic arrangement and a volume change of less than 0.5%. This alloy will deform under the action of an external force. When the external force is removed, it can return to its original shape under certain temperature conditions. This alloy can return to its high-temperature phase shape when heated and to its low-temperature phase shape when cooled, which is called the two-way memory effect. The throttling element 2 made of the shape memory alloy material has a first preset shape and a second preset shape after being subjected to an external force (training). The throttling element 2 with the first preset shape can shrink to the second preset shape when the temperature increases, and the throttling element 2 with the second preset shape can expand to the first preset shape when the temperature decreases.

[0041] The throttling element 2 is located in the cooling channel 12, and / or the throttling element 2 is provided at the inlet of the cooling channel 12 and includes:

[0042] a. The throttling element 2 is located in the cooling channel 12, so that the cooling gas enters the cooling channel 2 and exchanges heat with the throttling element 2, so that the shape of the throttling element 2 changes, thereby changing the flow cross-section of the cooling channel 2.

[0043] b. The throttling element 2 is disposed at the inlet of the cooling channel 12. Specifically, the inlet of the cooling channel 12 is opened on the first end surface 121 of the blade body 1. The throttling element 2 is attached to the first end surface 121 of the blade body 1. When the throttling element 2 is in a first preset shape, at least a portion of the inlet of the cooling channel 12 is blocked, thereby minimizing the flow cross-section of the cooling channel 12. When the cooling gas is blown toward the first end surface 121, the shape of the throttling element 2 changes, thereby changing the flow cross-section of the cooling channel 2.

[0044] c. There are multiple throttling elements 2, some of which are located in the cooling channel 12, and others of which are located at the inlet of the cooling channel 12. Thus, the multiple throttling elements 2 can change the flow cross-sections of multiple locations in the cooling channel 2, thereby changing the flow rate of the cooling gas entering the cooling channel 2.

[0045] d. The first portion of the throttle element 2 extends into the cooling channel 12, while the second portion of the throttle element 2 extends out of the cooling channel 12 and is located at the inlet of the cooling channel 12. Thus, when the cooling gas blows toward the first end surface 121, the shape of the throttle element 2 changes, allowing the throttle element 2 to change the flow cross-section of the cooling channel 2.

[0046] When the temperature of the cooling gas entering the cooling channel 12 rises from a first preset temperature to a second preset temperature (under high operating conditions), the throttle element 2 contracts and deforms from the first preset shape to the second preset shape. When the throttle element 2 contracts and deforms from the first preset shape to the second preset shape, the flow cross-section of the cooling channel 12 increases, thereby increasing the flow rate of the cooling gas flowing into the cooling channel 12. In other words, when the temperature of the cooling gas entering the cooling channel 12 rises, the cooling gas exchanges heat with the throttle element 2, causing the throttle element 2 to contract and deform from the first preset shape to the second preset shape. The throttle element 2 contracts, thereby reducing obstruction to the flow cross-section of the cooling channel 12, thereby increasing the flow cross-section of the cooling channel 12 and increasing the flow rate of the cooling gas flowing into the cooling channel 12. This ensures that the blade body 1 has a sufficient amount of cooling gas. Conversely, when the temperature of the cooling gas entering the cooling channel 12 drops from the second preset temperature to the first preset temperature, the throttle element 2 expands and deforms from the second preset shape to the first preset shape. This is so that the flow cross section of the cooling channel 12 is reduced and the flow rate of the cooling gas flowing into the cooling channel 12 is reduced, thereby preventing the blade body 1 from being overcooled.

[0047] In some embodiments, the first preset temperature is less than or equal to 100° C., and the second preset temperature is greater than or equal to 600° C. Specifically, when the temperature of the cooling gas increases from 100° C. to 600° C., the throttle element 2 contracts and deforms from the first preset shape to the second preset shape. When the temperature of the cooling gas decreases from 600° C. to 100° C., the throttle element 2 expands and deforms from the second preset shape to the first preset shape.

[0048] In some embodiments, when the throttle element 2 is in the first preset shape, the ratio of the flow cross-section of the cooling channel 12 to the total flow cross-section of the cooling channel 12 is (0.5-0.8):1. For example, when the throttle element 2 is in the first preset shape, the ratio of the flow cross-section of the cooling channel 12 to the total flow cross-section of the cooling channel 12 is 0.6:1. The (minimum) flow cross-section of the cooling channel 12 is 0.6 of its total flow cross-section, thereby reducing the flow rate of the cooling gas entering.

[0049] In some embodiments, the thickness of the throttling element 2 coincides with the extension direction of the cooling channel 12. In a cross-section perpendicular to the thickness of the throttling element 2, the projected area of ​​the throttling element 2 decreases when the throttling element 2 contracts and deforms from the first preset shape to the second preset shape. The first section of the cooling channel 12 is adjacent to the inlet of the cooling channel 12, and the extension direction of the first section of the cooling channel 12 coincides with the thickness direction of the sheet-like or mesh-like throttling element. For example, in a cross-section perpendicular to and in the vertical direction, the projected area of ​​the throttling element 2 decreases when the throttling element 2 contracts and deforms from the first preset shape to the second preset shape.

[0050] like Figures 1 to 3As shown, in some embodiments, the blade body 1 includes a body portion and a throttle orifice plate 3 .

[0051] The cooling channel 12 includes a connected air intake channel and a connecting channel 122. The throttle orifice plate 3 has an air intake channel 31, and the main body has the connecting channel 122 and the cooling chamber 11. The throttle orifice plate 3 is located at the entrance of the connecting channel 122 of the main body. The air intake channel 31 is connected to the connecting channel 122, and the shape of the air intake channel 31 matches the shape of the connecting channel 122. Specifically, the throttle orifice plate 3 is located on the first end surface 121 of the main body. The shape of the air intake channel 31 is the same as that of the connecting channel 122, and the inner wall surface of the air intake channel 31 is coplanar and connected to the inner wall surface of the first section of the connecting channel 122 (near its entrance). This allows cooling gas to flow unimpeded from the air intake channel 31 into the connecting channel 122 and then into the cooling chamber 11. The thickness of the throttle orifice plate 31 is consistent with the thickness of the throttling element 2 and is less than or equal to a preset value. The thickness of the throttling element 2 is greater than or equal to 0.5 mm and less than or equal to 1.5 mm, and the thickness of the throttling orifice 3 is less than or equal to 6 mm. For example, the thickness of the throttling element 2 is 1 mm, and the thickness of the throttling orifice 3 is 2 mm.

[0052] The throttle element 2 is disposed on the throttle orifice plate 3. Specifically, the throttle element 2 is disposed on at least one of a sidewall of the throttle orifice plate 3 in the thickness direction and an inner wall surface of the intake passage 31. In a cross section perpendicular to the thickness direction of the throttle element 2, at least a portion of the projection of the throttle element 2 in the first predetermined shape overlaps at least a portion of the projection of the cooling passage 12. As a result, the throttle element 2 located on the throttle orifice plate 3 can change the (minimum) flow cross-section of the cooling passage 12.

[0053] In some embodiments, the throttling element 2 is sheet-shaped or mesh-shaped. Specifically, both sheet-shaped and mesh-shaped throttling elements 2 can be circumferentially extended to increase the blocking area. For example, a frame is provided around the mesh-shaped throttling element 2, which is connected to the throttling orifice plate 3. Cooling gas can pass through the holes in the mesh-shaped throttling element 2. The expanded and contracted mesh-shaped throttling element 2 increases the holes in the throttling element 2, thereby increasing the flow rate of cooling gas flowing into the cooling channel 12.

[0054] In some embodiments, the throttle element 2 is located on the side of the throttle orifice plate 3 facing away from the main body. Specifically, the throttle element 2 is located on the side wall of the throttle orifice plate 3 facing away from the main body in the thickness direction. This allows the throttle element 2 to quickly exchange heat with the cooling gas when it blows toward the blade body 1, thereby deforming in shape and changing the (minimum) flow cross-section of the cooling channel 12.

[0055] In some embodiments, the throttle element 2 is located in the intake passage 31 and connected to the inner wall surface of the intake passage 31. As a result, the throttle element 2 can exchange heat with the cooling gas entering the intake passage 31 and about to enter the cooling passage 12, thereby deforming in shape.

[0056] In some embodiments, there are multiple throttling elements 2 and cooling channels 12, and the multiple throttling elements 2 are matched with the multiple cooling channels 12 in a one-to-one correspondence. Specifically, there are multiple throttling elements 2, intake channels 31, and connecting channels 122, and the multiple intake channels 31 are connected with the multiple connecting channels 122 in a one-to-one correspondence. The multiple throttling elements 2 are matched with the multiple connecting channels 122 in a one-to-one correspondence.

[0057] like Figure 2 and Figure 3 As shown, there are three throttling elements 2, three air inlet channels 31 and three connecting channels 122. The three throttling elements 2 are attached to the side wall of the throttling orifice plate 3 in the thickness direction facing away from the main body. The throttling element 2 is sheet-shaped, as shown in FIG. Figure 2 As shown, the throttle element 2 in the second preset shape does not block the cooling gas from entering the intake passage; Figure 3 As shown, the throttle element 2 in the first preset shape blocks the cooling gas from entering the intake passage.

[0058] In the description of the present invention, it should be understood that the terms "center", "longitudinal", "lateral", "length", "width", "thickness", "up", "down", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inside", "outside", "clockwise", "counterclockwise", "axial", "radial", "circumferential" and the like to indicate orientations or positional relationships 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, rather than indicating or implying 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 limiting the present invention.

[0059] Furthermore, the terms "first" and "second" are used for descriptive purposes only and should not be construed as indicating or implying relative importance or implicitly specifying the number of the technical features being referred to. Thus, a feature defined as "first" or "second" may explicitly or implicitly include at least one such feature. In the description of the present invention, "plurality" means at least two, such as two, three, etc., unless otherwise specifically defined.

[0060] In the present invention, unless otherwise specified or limited, the terms "installed," "connected," "connect," "fixed," etc. should be understood in a broad sense. For example, they can refer to fixed connection, detachable connection, or integration; mechanical connection, electrical connection, or communication; direct connection or indirect connection through an intermediate medium; internal communication between two elements or interaction between two elements, unless otherwise specified. Those skilled in the art will understand the specific meanings of the above terms in the present invention based on specific circumstances.

[0061] In the present invention, unless otherwise expressly specified or limited, when a first feature is "above" or "below" a second feature, it may mean that the first and second features are in direct contact, or that the first and second features are in indirect contact through an intermediary. Furthermore, when a first feature is "above," "above," or "above" a second feature, it may mean that the first feature is directly above or diagonally above the second feature, or simply means that the first feature is at a higher level than the second feature. When a first feature is "below," "below," or "below" a second feature, it may mean that the first feature is directly below or diagonally below the second feature, or simply means that the first feature is at a lower level than the second feature.

[0062] In the present invention, the terms "one embodiment," "some embodiments," "example," "specific example," or "some examples" mean that the specific features, structures, materials, or characteristics described in conjunction with the embodiment or example are included in at least one embodiment or example of the present invention. In this specification, the schematic representations of the above terms do not necessarily refer to the same embodiment or example. Moreover, the specific features, structures, materials, or characteristics described can be combined in any appropriate manner in any one or more embodiments or examples. In addition, those skilled in the art can combine and combine different embodiments or examples described in this specification, as well as features of different embodiments or examples, unless they are mutually inconsistent.

[0063] Although the above embodiments have been shown and described, it is understood that the above embodiments are illustrative and are not to be construed as limitations on the present invention. Changes, modifications, substitutions and variations of the above embodiments by those skilled in the art are all within the scope of protection of the present invention.

Claims

1. A gas turbine blade, characterized in that: include: a blade body, the blade body having a cooling cavity and a cooling channel communicating with the cooling cavity, the cooling channel being adapted to allow cooling gas to pass through; A throttling element, wherein the throttling element is located in the cooling channel, and / or the throttling element is arranged at the inlet of the cooling channel, the throttling element is made of shape memory alloy material, the throttling element has different shapes corresponding to different temperatures so that the throttling element has a first preset shape and a second preset shape, when the temperature of the cooling gas entering the cooling channel rises from the first preset temperature to the second preset temperature, the throttling element shrinks and deforms from the first preset shape to the second preset shape, when the throttling element shrinks and deforms from the first preset shape to the second preset shape, the flow cross-section of the cooling channel increases so as to increase the flow rate of the cooling gas flowing into the cooling channel, the thickness direction of the throttling element is consistent with the extension direction of the cooling channel, and on the cross section perpendicular to the thickness direction of the throttling element, the projected area of ​​the throttling element decreases when the throttling element shrinks and deforms from the first preset shape to the second preset shape.

2. The gas turbine blade according to claim 1, wherein: The blade body includes a main body and a throttle orifice plate, the cooling channel includes a connected air inlet channel and a connecting channel, the throttle orifice plate has the air inlet channel, the main body has the connecting channel and the cooling cavity, the throttle orifice plate is arranged at the inlet of the connecting channel of the main body, the shape of the air inlet channel is adapted to the shape of the connecting channel, the throttle element is arranged on the throttle orifice plate, and on a cross section perpendicular to the thickness direction of the throttle element, at least part of the projection of the throttle element in the first preset shape coincides with at least part of the projection of the cooling channel.

3. The gas turbine blade according to claim 2, wherein: The throttling element is located on a side of the throttling orifice plate facing away from the main body.

4. The gas turbine blade according to claim 2, wherein: The throttling element is located in the intake passage and is connected to the inner wall surface of the intake passage.

5. The gas turbine blade according to claim 2, wherein: There are multiple throttling elements and multiple cooling channels, and the multiple throttling elements are matched with the multiple cooling channels in a one-to-one correspondence.

6. The gas turbine blade according to claim 2, wherein: The throttling element is in sheet or net shape.

7. The gas turbine blade according to claim 1, wherein: When the throttling element is in the first preset shape, the ratio of the flow cross-section of the cooling channel to the total flow cross-section of the cooling channel is (0.5-0.8):

1.

8. The gas turbine blade according to claim 1, wherein: The first preset temperature is less than or equal to 100° C., and the second preset temperature is greater than or equal to 600° C.

9. A gas turbine, characterized in that: The invention comprises a gas turbine blade according to any one of claims 1 to 8.

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