Gas turbine blade with inner cavity structure capable of enhancing heat exchange

Abstract

The invention provides a gas turbine blade with an inner cavity structure capable of enhancing heat exchange, which comprises an inner cavity and a column, the inner cavity is in fluid communication with a cooling pipeline, the column is positioned inside the inner cavity, and the cooling pipeline is in fluid communication with the column. The circumferential face of the column does not make contact with the blade body wall face corresponding to the inner cavity in the radial direction of the gas turbine blade, and the volume of the column accounts for 5%-50% of the total volume of the inner cavity. The columnar object occupies part of space of part of the internal cavity, so that more cold air quantity cools the blade body wall surface corresponding to the internal cavity in a centralized manner, the cooling efficiency is improved, and meanwhile, the consumption of the cold air quantity is also reduced.

Description

Technical Field

[0001] The present invention relates to the technical field of gas turbines, and in particular to a gas turbine blade with an inner cavity structure capable of enhancing heat exchange. Background Art

[0002] With the development of gas turbine technology, the operating environment temperature of turbine blades continues to rise. In order to ensure that turbine blades operate within the allowable temperature range of high-temperature alloy materials and ensure blade life, higher requirements are placed on the design of blade cooling structures, bringing more challenges. Traditional cooling structures are increasingly unable to meet design requirements. There is an urgent need to propose more efficient cooling structures to improve heat exchange efficiency and extend turbine blade life. At the same time, because higher overall performance indicators will strictly limit the compressor air flow occupied by turbine cooling, innovative designs of high-efficiency turbine blade cooling structures are being carried out based on the principle of minimum air usage.

[0003] In the prior art, CN117536694A, for example, proposes a turbine blade and gas turbine. The turbine blade includes a blade body, wherein the inner cavity of the blade body has a first cavity and a second cavity sequentially arranged along the airflow direction of the blade body, the first cavity having a first target surface and a second target surface disposed opposite each other along the thickness direction of the blade body; a first plate is disposed within the first cavity to form a first chamber and a second chamber in the first cavity; a spoiler post, a first spoiler assembly, and a second spoiler assembly are disposed within the second cavity, wherein the spoiler posts are spaced apart within the second cavity, the first spoiler assembly and the second spoiler assembly are arranged along the airflow direction, the first spoiler assembly is disposed on the sidewalls of the second cavity and forms a plurality of spoiler chambers on the corresponding sidewalls, and the second spoiler assembly is disposed on the sidewalls of the second cavity and forms a flow channel on the corresponding sidewalls. The turbine blade disclosed in this technical solution can adopt different cooling structures in different sections, thereby improving the overall cooling effect. Another example is CN105649681A, which discloses staggered ribs for a gas turbine guide vane. The guide vane's inner cavity is divided into a front region and a rear region along the chord direction. The front region is provided with a short duct, and the staggered ribs are arranged in the rear region and include multiple cooling ribs. In the rear region, multiple rows of cooling ribs are arranged from the leading edge to the trailing edge of the guide vane. The ends of the multiple rows of cooling ribs are separated by partitions. The cooling ribs are staggered within the guide vane to form multiple cooling airflow secondary channels. Cooling air for the guide vane flows through the upper end surface of the short duct and into the duct interior. The cooling air is jet-pressurized within the short duct, passing through the holes on the leading edge of the short duct to cool the leading edge of the ribs. The cooling air then flows along the cooling airflow secondary channels through the trailing edge of the guide vane and into the turbine main channel. This technical solution has the beneficial effects of increasing the flow heat exchange area, improving the flow heat transfer coefficient, significantly enhancing heat exchange capacity, reducing cooling air usage, and improving the efficiency and power of the gas turbine.

[0004] However, the existing technologies cannot completely solve the above technical problems. Summary of the Invention

[0005] The purpose of the present invention is to solve the above-mentioned technical problems.

[0006] To achieve the above-mentioned objectives, the present invention proposes a gas turbine blade having an inner cavity structure capable of enhancing heat exchange, comprising an internal cavity and a columnar object. The internal cavity is fluidically connected to a cooling pipe, and the columnar object is located inside the internal cavity. Along the radial direction of the gas turbine blade, the circumferential surface of the columnar object does not contact the blade wall surface corresponding to the internal cavity, and the volume of the columnar object accounts for 5% to 50% of the total volume of the internal cavity.

[0007] Furthermore, the cross-sectional area of ​​the columnar object shows a trend of continuous or discontinuous reduction along the radial direction of the gas turbine blade.

[0008] Furthermore, the inner chamber and the column both extend in the radial direction of the gas turbine blade.

[0009] Furthermore, along the radial direction of the gas turbine blade, the centroid axis of the column coincides with the centroid axis of the internal cavity.

[0010] Furthermore, it also includes a plurality of heat-conducting arms, which connect the inner wall of the blade corresponding to the internal cavity and the columnar object.

[0011] Furthermore, the sum of the volumes of the columnar object and the heat conducting arm accounts for 10% to 60% of the total volume of the internal chamber.

[0012] Furthermore, the heat conducting arm is a plate-shaped structure, and the heat conducting arm extends along the radial direction of the gas turbine blade.

[0013] Furthermore, the thickness of the heat conducting arm decreases continuously or discontinuously along the radial direction of the gas turbine blade.

[0014] Furthermore, two edges of the heat conducting arm extending along the radial direction of the gas turbine blade are respectively connected to the blade wall surface corresponding to the internal cavity and the columnar object.

[0015] Furthermore, the heat conducting arm is made of a material having a thermal conductivity greater than 20 W / (mk).

[0016] Furthermore, it comprises a plurality of said internal chambers, and the plurality of said internal chambers are arranged in sequence from the leading edge to the trailing edge of the gas turbine blade.

[0017] Furthermore, the plurality of internal chambers are fluidically connected to each other.

[0018] Furthermore, the centroid of the internal cavity is located on the median camber line of the gas turbine blade.

[0019] Furthermore, it comprises three internal chambers, and the distances from the centroid of the internal chamber to the trailing edge of the gas turbine blade from the leading edge to the trailing edge of the gas turbine blade are respectively 3 / 4, 1 / 2 and 1 / 4 of the total length of the median arc line.

[0020] Furthermore, the proportion of the heat-conducting arm 3 in the internal chamber 1 close to the trailing edge of the gas turbine blade to the total volume of the internal chamber is greater than the proportion of the heat-conducting arm in the internal chamber away from the trailing edge of the gas turbine blade to the total volume of the internal chamber.

[0021] Furthermore, the internal chamber includes a plurality of sub-chambers, each of which extends radially along the gas turbine blade. The sub-chambers are respectively surrounded by the inner wall surface of the internal chamber, the peripheral surface of the columnar object, and the heat conducting arm.

[0022] Furthermore, the plurality of sub-chambers are fluidically connected to each other.

[0023] Furthermore, on a cross section perpendicular to the radial direction of the gas turbine blade and with the centroid of the column as the center of the circle, the minimum radius of the sub-chambers is the same.

[0024] Furthermore, the plurality of sub-chambers can be divided into at least a first-shaped cavity and a second-shaped cavity.

[0025] Furthermore, the internal chamber is a cylindrical structure, and the columnar object is a closed hollow structure.

[0026] By applying the above technical solution of the present invention, at least the following technical effects are achieved:

[0027] 1. In the present invention, the columnar object occupies part of the space of the internal cavity, so that more cold air is concentrated on cooling the blade wall corresponding to the internal cavity, thereby improving the cooling efficiency and reducing the consumption of cold air.

[0028] 2 In the present invention, the heat conducting arm is arranged between the column and the inner wall of the internal chamber, dividing the internal chamber into multiple sub-chambers, increasing the area in contact with the fluid, and improving the heat exchange efficiency by increasing the heat exchange area.

[0029] 3. In the present invention, the heat conducting arm conducts the heat from the blade wall to the internal cavity, and the heat is quickly conducted out through convection heat exchange between the cold air in the internal cavity and the heat conducting arm, thereby reducing the blade body temperature and improving the uniformity of the blade body temperature.

[0030] 4. In the present invention, the heat conducting arm connects the columnar object and the blade wall corresponding to the internal cavity, plays the role of supporting the wall, and can improve the rigidity of the gas turbine blade. At the same time, the heat conducting arm also occupies part of the space of the internal cavity, so that more cold air can be concentrated to cool the blade wall of the internal cavity, thereby improving the cooling efficiency.

[0031] 5. The present invention improves the flexibility of design and provides more adjustable parameters for cooling analysis and life analysis. The design requirements of cooling analysis and life analysis can be met by adjusting the wall thickness and number of the heat conducting arms and the size of the central column.

[0032] Additional aspects and advantages of the present invention will be set forth in part in the description which follows and, in part, will be obvious from the description which follows, or may be learned through practice of the present invention. BRIEF DESCRIPTION OF THE DRAWINGS

[0033] The accompanying drawings, which constitute part of the present invention, are intended to provide a further understanding of the present invention. The exemplary embodiments of the present invention and their descriptions are intended to explain the present invention and do not constitute an undue limitation of the present invention. In the accompanying drawings:

[0034] Figure 1 A schematic diagram of the internal chamber structure in one embodiment is shown;

[0035] Figure 2 A schematic cross-sectional view of an internal chamber in one embodiment is shown;

[0036] Figure 3 A schematic diagram of the structure of a gas turbine blade in one embodiment is shown;

[0037] Figure 4 A schematic cross-sectional view of a gas turbine blade body in one embodiment is shown;

[0038] Figure 5 A schematic diagram of the internal chamber structure in another embodiment is shown;

[0039] Figure 6 A schematic cross-sectional view of an internal chamber in another embodiment is shown;

[0040] Figure 7 A schematic diagram of the structure of a gas turbine blade in another embodiment is presented;

[0041] Figure 8 A schematic cross-sectional view of a gas turbine blade in another embodiment is shown;

[0042] Figure numerals: 1, internal chamber; 11, first shape cavity; 12, second shape cavity; 13, sub-chamber; 2, columnar object; 3, heat conducting arm. DETAILED DESCRIPTION

[0043] It should be noted that, in the absence of conflict, the embodiments and features of the embodiments of the present invention can be combined with each other. The present invention will be described in detail below with reference to the accompanying drawings and in combination with the embodiments.

[0044] The present invention is further described in detail below with reference to specific examples. These examples should not be construed as limiting the scope of protection claimed in the present invention.

[0045] Example 1

[0046] According to one aspect of the present invention, a gas turbine blade is proposed, comprising an internal chamber 1 and a columnar object 2, wherein the internal chamber 1 is fluidically connected to a cooling pipe, the columnar object 2 is located inside the internal chamber 1, and along the radial direction of the gas turbine blade, the circumferential surface of the columnar object 2 does not contact the corresponding blade wall surface of the internal chamber 1, and the volume of the columnar object 2 accounts for 5% to 50% of the total volume of the internal chamber 1.

[0047] In order to more accurately describe the relationship between the various components, the following definitions are made:

[0048] Fluid connectivity refers to the connection of different containers or devices through pipes, pipelines, etc., which can realize the transmission and distribution of fluids such as gases or liquids. In this connected system, fluids such as gases or liquids can flow from one container to another or from one device to another under the action of pressure differences.

[0049] The radial direction of the gas turbine blade refers to the direction from the root to the tip of the rotor blade or the direction from the inner end wall to the outer end wall of the stationary blade.

[0050] Specifically, if Figure 1-4 As shown, the heat of the gas turbine blades is transferred into the internal chamber 1 , and cold air flows in the internal chamber 1 . More cold air flows along the blade wall corresponding to the internal chamber 1 to remove the heat from the internal chamber 1 .

[0051] In this embodiment, the volume of the column 2 accounts for 30% of the total volume of the internal chamber 1. When the volume of the column 2 is less than 5% of the total volume of the internal chamber 1, on the one hand, it will affect its ability to support the wall surface, thereby weakening its role in improving the structural strength of the gas turbine blades. On the other hand, it will not achieve the beneficial effect of "allowing more cold air to concentrate on cooling the blade wall surface corresponding to the internal chamber, thereby improving cooling efficiency and reducing cold air consumption." When the volume of the column 2 is greater than 50% of the total volume of the internal chamber 1, it will restrict the flow of cold air. The increase in flow resistance will result in too little cold air, which will lead to an excessively high temperature field and fail to meet the cooling design requirements.

[0052] In other embodiments, the volume of the column 2 may account for 5%, 10%, 15%, 20%, 25%, 35%, 40%, 45%, 50%, etc. of the total volume of the internal chamber 1 .

[0053] The gas turbine blade further includes a plurality of heat-conducting arms 3, each connecting the corresponding inner wall of the blade body of the internal chamber 1 and the columnar member 2. Each heat-conducting arm 3 is a plate-like structure extending radially along the gas turbine blade. The thickness of each heat-conducting arm 3 decreases continuously along the radial direction of the gas turbine blade.

[0054] Specifically, the cross-sectional area of ​​the column 2 decreases continuously along the radial direction of the gas turbine blade. The heat conducting arm is arranged between the column and the inner wall of the internal chamber, which not only divides the internal chamber into multiple sub-chambers but also increases the contact area with the fluid, thereby improving the heat exchange efficiency.

[0055] In other embodiments, along the radial direction of the gas turbine blade, the cross-sectional area of ​​the columnar object 2 may be discontinuously reduced, or may be a cross-section with a constant area.

[0056] The internal chamber 1 and the column 2 both extend in the radial direction of the gas turbine blade. In the radial direction of the gas turbine blade, the centroid axis of the column 2 coincides with the centroid axis of the internal chamber 1. The internal chamber 1 is a cylindrical structure.

[0057] It should be noted that, in a cross section perpendicular to the radial direction of the gas turbine blade, the outer contour of the cross section of the columnar object 2 is streamlined, including but not limited to circular, elliptical, and teardrop-shaped. In this cross section, the radius of the columnar object 2 is not less than twice the thickness of the heat conducting arm 3.

[0058] Specifically, if Figure 1-4 As shown, the internal chamber 1 is a cylindrical structure, and the column 2 is a solid structure; the outer contour line of the cross section of the column 2 is streamlined, which can reduce flow loss.

[0059] In other embodiments, the columnar object 2 may be a closed hollow structure, which can reduce the mass of the gas turbine blade. The centroid axis of the columnar object 2 may not coincide with the centroid axis of the internal chamber 1.

[0060] The sum of the volumes of the column 2 and the heat-conducting arm 3 accounts for 10% to 60% of the total volume of the internal chamber 1. Specifically, in this embodiment, the sum of the volumes of the column 2 and the heat-conducting arm 3 accounts for 40% of the total volume of the internal chamber 1. The column 2 and the heat-conducting arm 3 occupy part of the space of the internal chamber, so that more cold air can be concentrated on cooling the blade wall corresponding to the internal chamber, thereby improving the cooling efficiency and reducing the consumption of cold air. If the sum of the volumes of the column 2 and the heat-conducting arm 3 is less than 10% of the total volume of the internal chamber 1, on the one hand, it will affect the effect of supporting the wall, thereby weakening its role in improving the structural strength of the gas turbine blades. On the other hand, it cannot achieve the beneficial effect of "concentrating more cold air on cooling the blade wall corresponding to the internal chamber, improving the cooling efficiency and reducing the consumption of cold air". When the sum of the volumes of the columnar object 2 and the heat conducting arm 3 is greater than 60% of the total volume of the internal chamber 1 , the flow of cold air will be restricted. The increase in flow resistance will result in too little cold air flow, which will cause the temperature field to be too high and fail to meet the cooling design requirements.

[0061] In other embodiments, the sum of the volumes of the column 2 and the heat-conducting arm 3 may account for 10%, 15%, 20%, 25%, 30%, 35%, 45%, 50%, 55%, 60%, etc. of the total volume of the internal chamber 1 .

[0062] The thickness of the heat conducting arm 3 decreases continuously along the radial direction of the gas turbine blade. The two edges of the heat conducting arm 3 extending along the radial direction of the gas turbine blade are connected to the inner wall surface of the internal chamber 1 and the columnar object 2 respectively. Figure 1-4 As shown, a plurality of plate-shaped heat-conducting arms 3 are distributed in a "radial" pattern with the centroid of the columnar object 2 as the center.

[0063] In other embodiments, along the radial direction of the gas turbine blade, the cross-sectional area of ​​the column 2 and the thickness of the heat conducting arm 3 may be discontinuously reduced or constant. The change adjustment of the cross-sectional area of ​​the column 2 is affected by the change of the cross-sectional area of ​​the internal chamber 1. For the moving blades, the cross-sectional area of ​​the internal chamber 1 generally becomes smaller in the radial direction of the blade, and the cross-sectional area of ​​the column 2 will be adaptively adjusted accordingly. For the stationary blades, the cross-sectional area of ​​the internal chamber 1 changes very little in the radial direction of the blade, and the cross-sectional area of ​​the column 2 may also remain unchanged. At the same time, the cross-sectional area size adjustment of the column 2 can also be adaptively adjusted according to the life assessment results. For the moving blades, when evaluating vibration problems, the size of the column 2 can be adjusted to meet the life requirements.

[0064] The heat conducting arm 3 is made of a material with a thermal conductivity greater than 20 W / (mk). Specifically, the gas turbine blade is manufactured by casting, and the heat conducting arm 3 and the blade body of the gas turbine blade are made of the same material.

[0065] The internal chamber 1 includes multiple sub-chambers 13 extending radially along the gas turbine blade. Each sub-chamber 13 is enclosed by the corresponding blade airfoil wall of the internal chamber 1, the circumference of the columnar object 2, and the heat transfer arm 3. The multiple sub-chambers 13 are fluidically connected to one another. On a cross section perpendicular to the radial direction of the gas turbine blade and centered at the centroid of the columnar object 2, the minimum radius of each sub-chamber 13 is the same.

[0066] In order to more accurately describe the structure of the internal chamber, the following definitions are made: the minimum radius of the sub-chamber refers to the minimum distance from the center of the column to the column wall corresponding to the sub-chamber on the radial section perpendicular to the gas turbine blade; the maximum radius of the sub-chamber refers to the distance from the center of the column to the inner wall of the blade corresponding to the sub-chamber on the radial section perpendicular to the gas turbine blade.

[0067] Specifically, if Figure 1-4 As shown, twelve heat-conducting arms 3 are provided in an internal chamber 1, dividing the internal chamber 1 into twelve sub-chambers 13. The twelve sub-chambers 13 are radially distributed around the centroid of the column 2. Through holes are provided on the heat-conducting arms 3 to connect adjacent sub-chambers 13.

[0068] In other embodiments, one internal chamber 1 may be provided with more than twelve sub-chambers 13, or less than twelve sub-chambers 13. The multiple sub-chambers 13 may also be disconnected from each other.

[0069] The gas turbine blade includes multiple internal chambers 1, which are sequentially arranged from the leading edge to the trailing edge of the gas turbine blade. The centroid of each internal chamber 1 is located on the mid-camber line of the gas turbine blade. Three internal chambers 1 are included, and the distances from the centroid of each internal chamber 1 to the trailing edge of the gas turbine blade to the trailing edge of the gas turbine blade are respectively 3 / 4, 1 / 2, and 1 / 4 of the total length of the mid-camber line. The multiple internal chambers 1 are fluidically connected to each other.

[0070] In other embodiments, the multiple internal chambers 1 may not be connected to each other.

[0071] The proportion of the heat conducting arm 3 in the internal chamber 1 close to the trailing edge of the gas turbine blade to the total volume of the internal chamber 1 is greater than the proportion of the heat conducting arm 3 in the internal chamber 1 far from the trailing edge of the gas turbine blade.

[0072] Specifically, if Figure 3-4As shown, the heat transfer arm 3 connects the columnar member 2 to the corresponding blade wall surface of the internal chamber 1, providing support for the wall surface. Especially in the internal chamber near the trailing edge of the gas turbine blade, the heat transfer arm 3 occupies a large proportion of the total volume of the internal chamber, strengthening the heat transfer arm 3's support for the blade wall surface and further improving the rigidity of the gas turbine blade.

[0073] By applying the above technical solution of the present invention, at least the following technical effects are achieved:

[0074] 1. In the present invention, the columnar object occupies part of the space of the internal cavity, so that more cold air is concentrated on cooling the blade wall corresponding to the internal cavity, thereby improving the cooling efficiency and reducing the consumption of cold air.

[0075] 2 In the present invention, the heat conducting arm is arranged between the column and the inner wall of the internal chamber, dividing the internal chamber into multiple sub-chambers, increasing the area in contact with the fluid, and improving the heat exchange efficiency by increasing the heat exchange area.

[0076] 3. In the present invention, the heat conducting arm conducts the heat from the blade wall to the internal cavity, and the heat is quickly conducted out through convection heat exchange between the cold air in the internal cavity and the heat conducting arm, thereby reducing the blade body temperature and improving the uniformity of the blade body temperature.

[0077] 4. In the present invention, the heat conducting arm connects the columnar object and the blade wall corresponding to the internal cavity, plays the role of supporting the wall, and can improve the rigidity of the gas turbine blade. At the same time, the heat conducting arm also occupies part of the space of the internal cavity, so that more cold air can be concentrated to cool the blade wall of the internal cavity, thereby improving the cooling efficiency.

[0078] 5. The present invention improves the flexibility of design and provides more adjustable parameters for cooling analysis and life analysis. The design requirements of cooling analysis and life analysis can be met by adjusting the wall thickness and number of the heat conducting arms and the size of the central column.

[0079] Example 2

[0080] This embodiment is similar to Figure 1-4 The first embodiment shown is substantially the same, except that the shapes of the multiple sub-cavities in the same internal chamber 1 are not identical. In this embodiment, the multiple sub-cavities 13 can be divided into at least a first-shaped cavity 11 and a second-shaped cavity 12.

[0081] Specifically, on a cross section perpendicular to the radial direction of the gas turbine blade and centered about the centroid of the columnar object 2, the maximum radius and minimum radius of the first-shaped cavity 11 are respectively smaller than the maximum radius and minimum radius of the second-shaped cavity 12. The first-shaped cavity 11 and the second-shaped cavity 12 cooperate with each other and can be adjusted in size and layout according to the shape of the blade. They can be applied to different positions of the gas turbine blade, improving the adaptability of the internal cavity.

[0082] More specifically, if Figure 5-8 As shown, the first cavity 11 is petal-shaped and serves as the primary sub-cavity, while the second cavity 12 is nearly triangular or other shaped and serves as the secondary sub-cavity. The secondary sub-cavity and the primary sub-cavity cooperate to form the entire internal chamber 1. The design of the secondary sub-cavity facilitates better adjustment of the wall thickness and ensures maximum uniformity.

[0083] In other implementations, the multiple sub-chambers 13 can be divided into more diverse shapes, including but not limited to cylindrical, triangular, and polygonal prism shapes, to better accommodate variations in blade shape. However, the multiple sub-chambers 13 should have relatively uniform volumes to ensure uniform cooling fluid flow and improve temperature uniformity across the blade.

[0084] By applying the above technical solution of the present invention, at least the following technical effects are achieved:

[0085] 1. In the present invention, the columnar object occupies part of the space of the internal cavity, so that more cold air is concentrated on cooling the blade wall corresponding to the internal cavity, thereby improving the cooling efficiency and reducing the consumption of cold air.

[0086] 2 In the present invention, the heat-conducting arm is arranged between the column and the inner wall of the internal chamber, dividing the internal chamber into multiple sub-chambers, increasing the area in contact with the fluid, and improving the heat exchange efficiency by increasing the heat exchange area.

[0087] 3. In the present invention, the heat conducting arm conducts the heat from the blade wall to the internal cavity, and the heat is quickly conducted out through convection heat exchange between the cold air in the internal cavity and the heat conducting arm, thereby reducing the blade body temperature and improving the uniformity of the blade body temperature.

[0088] 4. In the present invention, the heat conducting arm connects the columnar object and the blade wall corresponding to the internal cavity, plays the role of supporting the wall, and can improve the rigidity of the gas turbine blade. At the same time, the heat conducting arm also occupies part of the space of the internal cavity, so that more cold air can be concentrated to cool the blade wall of the internal cavity, thereby improving the cooling efficiency.

[0089] 5. The present invention improves the flexibility of design and provides more adjustable parameters for cooling analysis and life analysis. The design requirements of cooling analysis and life analysis can be met by adjusting the wall thickness and number of the heat conducting arms and the size of the central column.

[0090] Example 3

[0091] This embodiment is similar to Figure 1-4The first embodiment shown is substantially the same, differing only in that this embodiment does not include a heat transfer arm 3 and the internal chamber 1 does not include a sub-chamber. In this embodiment, the gas turbine blade includes an internal chamber 1 and a columnar object 2. The internal chamber 1 is fluidically connected to a cooling duct. The columnar object 2 is located within the internal chamber 1. Along the radial direction of the gas turbine blade, the circumferential surface of the columnar object 2 does not contact the inner wall surface of the internal chamber 1. The volume of the columnar object 2 accounts for 5% to 50% of the total volume of the internal chamber 1.

[0092] Specifically, the column 2 extends radially along the gas turbine blade, with both ends connected to the blade walls corresponding to the internal chamber 1. Heat from the gas turbine blade is transferred into the internal chamber 1, which is connected to the external cooling pipeline. The column 2 allows air to flow more along the blade walls corresponding to the internal chamber, dissipating heat from the internal chamber 1.

[0093] In this embodiment, the volume of the column 2 accounts for 30% of the total volume of the internal chamber 1. In other embodiments, the volume of the column 2 may account for 5%, 10%, 15%, 20%, 25%, 35%, 40%, 45%, 50%, etc. of the total volume of the internal chamber 1.

[0094] By applying the above technical solution of the present invention, at least the following technical effects are achieved:

[0095] In the present invention, the columnar object occupies part of the space of the internal cavity, so that more cold air is concentrated on cooling the blade wall surface corresponding to the internal cavity, thereby improving the cooling efficiency and reducing the consumption of cold air.

[0096] The above are only a number of specific embodiments of the present invention, but the scope of protection of the present invention is not limited thereto. Any technician familiar with the technical field, within the technical scope disclosed by the present invention, who makes equivalent replacements or changes based on the technical solutions and inventive concepts of the present invention, should be covered by the scope of protection of the present invention.

[0097] It should be noted that, in this document, relational terms such as first and second, etc., are used only to distinguish one entity or operation from another entity or operation, and do not necessarily require or imply any actual relationship or order between these entities or operations. Moreover, the terms "comprises," "comprising," or any other variations thereof are intended to cover non-exclusive inclusion, such that a process, method, article, or device comprising a series of elements includes not only those elements, but also other elements not explicitly listed, or elements inherent to such process, method, article, or device. In the absence of further limitations, an element defined by the phrase "comprising a ..." does not exclude the presence of other identical elements in the process, method, article, or device comprising the element.

[0098] It should be noted that, in the description of this specification, the reference 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 expressions 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 one or more embodiments or examples in a suitable manner. In addition, those skilled in the art can combine and combine different embodiments or examples described in this specification and the features of different embodiments or examples, unless they are contradictory.

Claims

1. A gas turbine blade having an inner cavity structure capable of enhancing heat exchange, characterized in that: The invention comprises an internal chamber (1) and a column (2), wherein the internal chamber (1) is fluidically connected to a cooling pipe, the column (2) is located inside the internal chamber (1), and along the radial direction of the gas turbine blade, the peripheral surface of the column (2) does not contact the blade wall surface corresponding to the internal chamber (1), and the volume of the column (2) accounts for at least 5% to 50% of the total volume of the internal chamber (1).

2. The gas turbine blade with an enhanced heat exchange inner cavity structure according to claim 1, characterized in that: The cross-sectional area of ​​the column (2) shows a trend of continuous or discontinuous reduction along the radial direction of the gas turbine blade.

3. The gas turbine blade with an enhanced heat exchange inner cavity structure according to claim 2, characterized in that: The inner chamber (1) and the column (2) both extend in the radial direction of the gas turbine blade.

4. The gas turbine blade with an enhanced heat exchange inner cavity structure according to claim 3, characterized in that: Along the radial direction of the gas turbine blade, the centroid axis of the column (2) coincides with the centroid axis of the internal chamber (1).

5. The gas turbine blade with an enhanced heat exchange inner cavity structure according to claim 4, characterized in that: It also includes a plurality of heat-conducting arms (3), wherein the heat-conducting arms (3) connect the inner wall of the blade corresponding to the internal cavity (1) and the columnar object (2).

6. The gas turbine blade with an enhanced heat exchange inner cavity structure according to claim 5, characterized in that: The sum of the volumes of the columnar object (2) and the heat-conducting arm (3) accounts for 10% to 60% of the total volume of the internal chamber (1).

7. The gas turbine blade with an enhanced heat exchange inner cavity structure according to claim 6, characterized in that: The heat conducting arm (3) is a plate-shaped structure, and the heat conducting arm (3) extends along the radial direction of the gas turbine blade.

8. The gas turbine blade with an enhanced heat exchange inner cavity structure according to claim 7, characterized in that: The thickness of the heat conducting arm (3) along the radial direction of the gas turbine blade shows a trend of continuous or discontinuous reduction.

9. The gas turbine blade with an enhanced heat exchange inner cavity structure according to claim 8, characterized in that: Two sides of the heat conducting arm (3) extending in the radial direction of the gas turbine blade are respectively connected to the blade wall surface corresponding to the internal chamber (1) and the columnar object (2).

10. The gas turbine blade with an enhanced heat exchange inner cavity structure according to claim 9, characterized in that: The heat-conducting arm (3) is made of a material with a thermal conductivity greater than 20 W / (mk).

11. The gas turbine blade with an enhanced heat exchange inner cavity structure according to claim 10, characterized in that: It comprises a plurality of internal chambers (1), and the plurality of internal chambers (1) are arranged in sequence from the leading edge to the trailing edge of the gas turbine blade.

12. The gas turbine blade with an enhanced heat exchange inner cavity structure according to claim 11, characterized in that: The plurality of internal chambers (1) are fluidically connected to each other.

13. The gas turbine blade with an enhanced heat exchange inner cavity structure according to claim 12, characterized in that: The centroid of the internal chamber (1) is located on the median camber line of the gas turbine blade.

14. The gas turbine blade with an inner cavity structure capable of enhancing heat exchange according to claim 13, characterized in that: The invention comprises three internal chambers (1), and the distances between the centroid of the internal chamber (1) and the trailing edge of the gas turbine blade along the leading edge to the trailing edge of the gas turbine blade account for 3 / 4, 1 / 2 and 1 / 4 of the total length of the median arc line respectively.

15. The gas turbine blade with an enhanced heat exchange inner cavity structure according to claim 14, characterized in that: The proportion of the heat-conducting arm (3) in the internal chamber (1) close to the trailing edge of the gas turbine blade to the total volume of the internal chamber (1) is greater than the proportion of the heat-conducting arm (3) in the internal chamber (1) away from the trailing edge of the gas turbine blade to the total volume of the internal chamber (1).

16. The gas turbine blade with an enhanced heat exchange inner cavity structure according to claim 15, characterized in that: The internal chamber (1) includes a plurality of sub-chambers (13), each of which extends radially along the gas turbine blade. The sub-chambers (13) are respectively surrounded by the inner wall surface of the internal chamber (1), the peripheral surface of the columnar object (2), and the heat-conducting arm (3).

17. The gas turbine blade with an enhanced heat exchange inner cavity structure according to claim 16, characterized in that: The plurality of sub-chambers (13) are fluidically connected to each other.

18. The gas turbine blade with an enhanced heat exchange inner cavity structure according to claim 17, characterized in that: On a cross section perpendicular to the radial direction of the gas turbine blade and with the centroid of the column (2) as the center of the circle, the minimum radius of the sub-chambers (13) is the same.

19. The gas turbine blade with an enhanced heat exchange inner cavity structure according to claim 17, characterized in that: The plurality of sub-chambers (13) can be divided into at least a first-shaped cavity (11) and a second-shaped cavity (12).

20. The gas turbine blade with an inner cavity structure capable of enhancing heat exchange according to any one of claims 1 to 19, characterized in that: The internal chamber (1) is a cylindrical structure, and the columnar object (2) is a closed hollow structure.

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