Heat exchange rib, turbine blade and gas turbine with variable cross-sectional shape

Abstract

This invention discloses a heat exchange rib with a variable cross-section, turbine blades, and a gas turbine. The first and second ends of the heat exchange rib are both circular. The heat exchange rib includes a pressure-reducing section located between the first and second ends. The pressure-reducing section has an elliptical cross-section, with its major axis parallel to the direction of the cooling airflow. Alternatively, the pressure-reducing section has an airfoil cross-section, with its chord parallel to the direction of the cooling airflow. The pressure-reducing section has a wide leading edge and a narrow trailing edge, with its leading edge facing the direction of the cooling airflow. This invention uses a variable cross-section shape for the heat exchange rib, combining the advantages of cylindrical, elliptical, or airfoil-shaped heat exchange ribs. The two ends of the heat exchange rib connected to the two side walls of the cooling channel are circular. At least a portion of the structure of the heat exchange rib in the main flow region is elliptical or airfoil-shaped, ensuring heat exchange capacity while significantly reducing pressure loss in the cooling channel.

Description

Technical Field

[0001] This invention relates to the field of gas turbine technology, and in particular to a heat exchange rib, turbine blade and gas turbine with a variable cross-section shape. Background Technology

[0002] Gas turbines have important applications in many fields such as aviation propulsion, marine propulsion, and power generation. Currently, the turbine inlet temperature of gas turbines is far higher than the heat resistance limit of high-temperature alloys, so corresponding measures must be taken to reduce the blade operating temperature. Therefore, blade cooling has become one of the major key technologies for gas turbines to ensure the safe and reliable operation of blades.

[0003] High-temperature turbine blades generally employ a hollow structure, using high-pressure gas drawn from the compressor to cool the blade interior. Heat exchange ribs are commonly used for cooling in both traditional blade trailing edge channels and the internal channels of novel double-walled blades. These ribs enhance heat transfer on the channel's inner wall surface and also strengthen the structure, hence their widespread use in blade internal cooling design. However, traditional cylindrical heat exchange ribs result in significant pressure losses within the cooling channels, leading to low efficiency in cooling gas utilization. Summary of the Invention

[0004] This invention is based on the inventor's discoveries and understanding of the following facts and problems:

[0005] The inventors discovered that in the cooling channel of a turbine blade with heat exchange ribs, the primary location of the cooling heat transfer effect is near the side walls of the cooling channel. This is because the outer sides of the side walls of the cooling channel are the outer walls of the turbine blades, which are in contact with high-temperature combustion gases and therefore require efficient cooling. The heat exchange ribs generate turbulence within the cooling channel, causing strong airflow disturbances near the cooling channel walls, thus significantly enhancing the local heat transfer intensity. Based on this discovery, it can be concluded that the heat transfer capacity of the central column portion of the heat exchange ribs is significantly less than that of the portion near the cooling channel walls. Furthermore, because the column portion occupies a larger space, it causes the main pressure loss in the cooling channel. Therefore, it is necessary to optimize and improve the traditional heat exchange rib structure to enhance the heat transfer capacity and cooling efficiency of the turbine blade's internal structure.

[0006] The inventors conducted simulation tests on heat exchange rib structures with different cross-sectional shapes. Figure 1 The curves showing the friction coefficient as a function of Reynolds number are presented for three types of heat transfer fin arrays (cylindrical heat transfer fin array, symmetrical airfoil heat transfer fin array, and elliptical heat transfer fin array). Figure 1 The results show that the pressure loss generated by elliptical heat exchange fins and airfoil heat exchange fins is significantly lower than that of traditional circular heat exchange fins.

[0007] The present invention aims to at least partially solve one of the technical problems in related art, and desires to obtain a heat exchange rib structure with lower pressure loss. To this end, embodiments of the present invention propose a heat exchange rib with a variable cross-sectional shape, resulting in lower pressure loss.

[0008] Embodiments of the present invention also propose turbine blades having heat exchange ribs as described in the embodiments of the present invention.

[0009] Embodiments of the present invention also propose a gas turbine having the aforementioned turbine blades.

[0010] The present invention provides a heat exchange rib with a variable cross-sectional shape. The heat exchange rib has a first end and a second end opposite to each other in its axial direction. The first end and the second end of the heat exchange rib are respectively supported on two side walls of the cooling channel. The first end and the second end of the heat exchange rib are both circular in shape. The heat exchange rib includes a pressure relief part, which is located between the first end and the second end.

[0011] Wherein, the cross-section of the pressure-reducing part is elliptical, and the major axis of the pressure-reducing part is parallel to the incoming direction of the cooling airflow; or, the cross-section of the pressure-reducing part is airfoil, and the chord of the pressure-reducing part is parallel to the incoming direction of the cooling airflow. The pressure-reducing part has a wide leading edge and a narrow trailing edge, and the leading edge of the pressure-reducing part faces the incoming direction of the cooling airflow.

[0012] The heat exchange ribs of this embodiment of the invention are supported in the cooling channel of the turbine blade, which improves the structural strength of the turbine blade to a certain extent. Cooling airflow is introduced into the cooling channel, and the cooling airflow impacts the heat exchange ribs to generate turbulence, causing airflow disturbance. The airflow disturbance can significantly enhance the local heat exchange intensity and achieve efficient cooling.

[0013] Because the main cooling and heat exchange occurs in the cooling channel, which is near the two side walls of the cooling channel, that is, near the two ends of the heat exchange ribs, the heat exchange efficiency in the mainstream area far away from the wall is low, and the main pressure loss occurs in the mainstream area, caused by the column part of the heat exchange ribs.

[0014] Elliptical and airfoil heat transfer ribs cause less flow loss compared to circular heat transfer ribs (e.g., Figure 1 (As shown). Therefore, the heat exchange ribs in this embodiment of the invention adopt a variable cross-sectional shape, combining the advantages of cylindrical heat exchange ribs with elliptical or airfoil heat exchange ribs, so that the two ends of the heat exchange ribs connected to the two side walls of the cooling channel are circular, and at least part of the structure of the heat exchange ribs in the mainstream area is elliptical or airfoil-shaped, which ensures the heat exchange capacity of the heat exchange ribs while significantly reducing the pressure loss in the cooling channel.

[0015] In some embodiments, the first end smoothly transitions to the pressure-reducing portion; and / or, the second end smoothly transitions to the pressure-reducing portion.

[0016] In some embodiments, the cross-section of the pressure-reducing portion is elliptical, wherein the central axis of the first end coincides with the central axis of the pressure-reducing portion, and the diameter of the first end is equal in length to the minor axis of the pressure-reducing portion; and / or, the central axis of the second end coincides with the central axis of the pressure-reducing portion, and the diameter of the second end is equal in length to the minor axis of the pressure-reducing portion.

[0017] In some embodiments, the heat exchange rib includes a first segment and a second segment, wherein the first segment has a circular and an elliptical shape at its two ends in the axial direction, and the second segment has a circular and an elliptical shape at its two ends in the axial direction, wherein one end of the elliptical shape of the first segment is adapted to and connected to one end of the elliptical shape of the second segment; or, the heat exchange rib includes a first segment and a second segment, wherein the first segment has a circular and an airfoil shape at its two ends in the axial direction, and the second segment has a circular and an airfoil shape at its two ends in the axial direction, wherein one end of the airfoil shape of the first segment is adapted to and connected to one end of the airfoil shape of the second segment.

[0018] In some embodiments, the first end and the second end are symmetrical with respect to the structure of the pressure-reducing part; and / or, the cross-section of the pressure-reducing part is elliptical, and the ratio of the major axis to the minor axis of the pressure-reducing part is 1.5:1-3:1.

[0019] In some embodiments, the heat exchange rib includes: a first circular portion and a second circular portion, wherein the first circular portion is disposed adjacent to a first end of the heat exchange rib such that the first end of the heat exchange rib is circular, and the second circular portion is disposed adjacent to a second end of the heat exchange rib such that the second end of the heat exchange rib is circular.

[0020] In some embodiments, the heat exchange rib includes: a first transition section located between the first circular portion and the pressure reducing portion, for smooth transition between the first circular portion and the pressure reducing portion; and a second transition section located between the second circular portion and the pressure reducing portion, for smooth transition between the second circular portion and the pressure reducing portion.

[0021] In some embodiments, the first circular portion is a straight prism structure, the second circular portion is a straight prism structure, the pressure-reducing portion is a straight column structure, and the first circular portion and the second circular portion are respectively connected to the two ends of the pressure-reducing portion in its axial direction.

[0022] A turbine blade in another embodiment of the present invention includes: a housing defining a cooling channel; and a heat exchange rib array located within the cooling channel, the heat exchange rib array comprising a plurality of heat exchange ribs arranged at array intervals, the heat exchange ribs being heat exchange ribs with variable cross-sectional shapes as described in any of the preceding embodiments.

[0023] The gas turbine in another embodiment of the present invention includes turbine blades as described in the embodiments of the present invention. Attached Figure Description

[0024] Figure 1 These are curves showing the friction coefficient as a function of Reynolds number for three different shapes of heat exchange fin arrays.

[0025] Figure 2 This is a schematic diagram of the structure of a heat exchange rib for enhanced heat exchange according to an embodiment of the present invention.

[0026] Figure 3 yes Figure 2 Front view of the heat exchange fin.

[0027] Figure 4 yes Figure 2 Side view of the heat exchange fin.

[0028] Figure 5 yes Figure 2 Top view of the heat exchange fin.

[0029] Figure 6 This is a top view of a heat exchange rib for enhanced heat exchange according to another embodiment of the present invention.

[0030] Figure 7 This is a front view of a heat exchange rib for enhanced heat exchange according to another embodiment of the present invention.

[0031] Figure 8 This is a front view of a heat exchange rib for enhanced heat exchange according to another embodiment of the present invention.

[0032] Figure 9 This is a front view of a heat exchange rib for enhanced heat exchange according to another embodiment of the present invention.

[0033] Figure label:

[0034] Heat exchanger 100

[0035] First end 11, second end 12, pressure relief section 13, leading edge 131, trailing edge 132, first segment 101, second segment 102, first circular portion 103, second circular portion 104, first transition segment 105, second transition segment 106. Detailed Implementation

[0036] 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.

[0037] The following is based on Figures 3-9 The present invention describes a heat exchange rib 100 with a variable cross-sectional shape as an example, a turbine blade with the heat exchange rib 100, and a gas turbine having the aforementioned turbine blade. The turbine blade in this embodiment includes a shell and a heat exchange rib array. A cooling channel is defined within the shell, and the heat exchange rib array is located within the cooling channel. The heat exchange rib array includes a plurality of heat exchange ribs arranged at array intervals. These heat exchange ribs are the heat exchange ribs 100 for enhanced heat exchange in this embodiment, and the cooling airflow flows through the intervals formed between the plurality of heat exchange ribs 100.

[0038] In this embodiment of the invention, the heat exchange rib 100 has a first end 11 and a second end 12 opposite to each other in its axial direction. The first end 11 and the second end 12 are respectively used to support the two side walls of the cooling channel. The heat exchange rib 100 generates a heat exchange rib turbulence effect on the cooling airflow in the cooling channel to enhance the cooling intensity and cooling efficiency of the cooling airflow. Figure 3 As shown, the first end 11 and the second end 12 of the heat exchange rib 100 are both circular in shape. The heat exchange rib 100 includes a pressure reducing part 13, which is located between the first end 11 and the second end 12 of the heat exchange rib 100.

[0039] In some embodiments, such as Figures 3-5 As shown, the cross-section of the pressure-reducing section 13 is elliptical, and the major axis of the pressure-reducing section 13 is parallel to the incoming direction of the cooling airflow. At least one location of the heat exchange fin 100 in the main flow zone has an elliptical cross-section.

[0040] In other embodiments, such as Figure 6 As shown, the pressure-reducing section 13 has an airfoil-shaped cross-section. The chord of the pressure-reducing section 13 is parallel to the incoming direction of the cooling airflow. The pressure-reducing section 13 has a wider leading edge 131 and a narrower trailing edge 132. The leading edge 131 of the pressure-reducing section 13 faces the incoming direction of the cooling airflow. The heat exchange rib 100 has an airfoil-shaped cross-section at least at one location in the main flow area.

[0041] The heat exchange ribs of this embodiment of the invention are supported in the cooling channel of the turbine blade, which improves the structural strength of the turbine blade to a certain extent. Cooling airflow is introduced into the cooling channel, and the cooling airflow impacts the heat exchange ribs to generate turbulence, causing airflow disturbance. The airflow disturbance can significantly enhance the local heat exchange intensity and achieve efficient cooling.

[0042] Because the main cooling and heat exchange occurs in the cooling channel, which is near the two side walls of the cooling channel, that is, near the two ends of the heat exchange ribs, the heat exchange efficiency in the mainstream area far away from the wall is low, and the main pressure loss occurs in the mainstream area, caused by the column part of the heat exchange ribs.

[0043] Elliptical and airfoil heat transfer ribs cause less flow loss compared to circular heat transfer ribs (e.g., Figure 1 (As shown). Therefore, the heat exchange ribs in this embodiment of the invention adopt a variable cross-sectional shape, combining the advantages of cylindrical heat exchange ribs with elliptical or airfoil heat exchange ribs, so that the two ends of the heat exchange ribs connected to the two side walls of the cooling channel are circular, and at least part of the structure of the heat exchange ribs in the mainstream area is elliptical or airfoil-shaped, which ensures the heat exchange capacity of the heat exchange ribs while significantly reducing the pressure loss in the cooling channel.

[0044] In some embodiments, the first end 11 of the heat exchange rib 100 smoothly transitions to the pressure reduction section 13; and / or, the second end 12 smoothly transitions to the pressure reduction section 13. In other words, the heat exchange rib 100 smoothly transitions from a near-wall circular shape to an elliptical or airfoil-shaped cross-section in the middle. The smooth outer peripheral surface of the heat exchange rib 100 further reduces the flow loss caused by the heat exchange rib 100 in the cooling channel, while making the demolding process of the heat exchange rib 100 easier and reducing the manufacturing difficulty of the heat exchange rib 100.

[0045] As an example, such as Figures 3-5 As shown, the first end 11 of the heat exchange rib 100 smoothly transitions to the pressure reduction section 13, and the second end 12 smoothly transitions to the pressure reduction section 13. The heat exchange rib 100 smoothly transitions from a near-wall circular shape to an elliptical cross-section in the middle.

[0046] In some embodiments, such as Figures 3-5 As shown, the heat exchange rib 100 includes a first section 101 and a second section 102. The first section 101 has a circular shape at one end and an ellipse at the other end in the axial direction. The second section 102 has a circular shape at one end and an ellipse at the other end in the axial direction. The elliptical end of the first section 101 is adapted to and connected to the elliptical end of the second section 102.

[0047] In some other embodiments, the heat exchange rib 100 includes a first section 101 and a second section 102. The first section 101 has a circular shape and an airfoil at its two ends in the axial direction, respectively. The second section 102 has a circular shape and an airfoil at its two ends in the axial direction, respectively. One end of the airfoil of the first section 101 is adapted to and connected to one end of the airfoil of the second section 102.

[0048] Optionally, such as Figures 3-5As shown, the first segment 101 and the second segment 102 of the heat exchange rib 100 are directly connected, and the elliptical end of the first segment 101 matches the elliptical end of the second segment 102 to make the transition between the first segment 101 and the second segment 102 more natural and the structure of the heat exchange rib 100 more reasonable. The connection between the first segment 101 and the second segment 102 forms the pressure-reducing part 13 of the heat exchange rib 100. The end of the first segment 101 away from the second segment 102 is the first end 11 of the heat exchange rib 100, and the end of the second segment 102 away from the first segment 101 is the second end 12 of the heat exchange rib 100.

[0049] Optionally, the first section 101 and the second section 102 are integrally formed, that is, by designing a mold, the first section 101 and the second section 102 are cast together to form the heat exchange rib 100.

[0050] Alternatively, the first segment 101 and the second segment 102 can be separate structures. After the first segment 101 and the second segment 102 are cast separately, they can be fixed together by bonding or other means. Alternatively, the first segment 101 and the second segment 102 can be detachably connected, for example, through a threaded connection. This invention does not limit the connection method when the first segment 101 and the second segment 102 are separate structures.

[0051] Optionally, the first segment 101 and the second segment 102 are separate structures, and the first segment 101 and the second segment 102 have the same structure. The first segment 101 and the second segment 102 can be prepared using the same mold, which reduces the number of molds and lowers the manufacturing cost of the heat exchange rib 100.

[0052] In other embodiments, such as Figure 7 As shown, the pressure-reducing part 13 of the heat exchange rib 100 has a certain length in the axial direction of the heat exchange rib 100. The pressure-reducing part 13 is an elliptical column or an airfoil column. One end of the pressure-reducing part 13 is connected to the first section 101 and is adapted to the end shape of the first section 101. The other end of the pressure-reducing part 13 is connected to the second section 102 and is adapted to the end shape of the second section 102.

[0053] As an example, such as Figure 7 As shown, the pressure-reducing section 13 has a straight column structure, meaning that the cross-sectional area and shape of the pressure-reducing section 13 are the same at all points along its axial direction. The elliptical cross-section of the pressure-reducing section 13 is located in the main flow area of ​​the cooling channel, which helps to further reduce the pressure loss caused by the heat exchange fins 100 in the cooling channel. The straight column structure of the pressure-reducing section 13 is easier to manufacture, provides uniform stress, and has strong structural stability.

[0054] In other embodiments, the pressure-reducing section 13 can be a variable cross-section column, that is, the shape of the cross-section of the pressure-reducing section 13 varies along its axial direction. Optionally, the cross-sectional area of ​​the pressure-reducing section 13 gradually decreases from its two ends to the middle. While ensuring the basic support strength requirements of the pressure-reducing section 13, making the cross-sectional area of ​​the pressure-reducing section 13 gradually decrease from its two ends to the middle can further reduce the pressure loss caused by the heat exchange rib 100 in the cooling channel.

[0055] Optionally, the first section 101, the second section 102, and the pressure-reducing part 13 are integrally formed.

[0056] Alternatively, the first segment 101, the second segment 102, and the pressure-reducing part 13 may be separate structures, with the first segment 102 fixedly or detachably connected to one end of the pressure-reducing part 13, and the second segment 102 fixedly or detachably connected to one end of the pressure-reducing part 13.

[0057] In some embodiments, the cross-sectional area of ​​the heat exchange rib 100 gradually increases from the first end 11 toward the pressure reduction section 13, that is, the cross-sectional area of ​​the first section 101 gradually increases toward the direction closer to the second section 102, and / or, the cross-sectional area of ​​the heat exchange rib 100 gradually increases from the second end 12 toward the pressure reduction section 13, that is, the cross-sectional area of ​​the second section 102 gradually increases toward the direction closer to the first section 101.

[0058] As an example, such as Figures 3-5 As shown, the cross-sectional area of ​​the heat exchange rib 100 gradually increases from the first end 11 to the pressure reduction section 13, and the cross-sectional area of ​​the heat exchange rib 100 gradually increases from the second end 12 to the pressure reduction section 13. In other words, the cross-sectional area of ​​the heat exchange rib 100 gradually increases from its two ends to the middle, presenting a structure that is narrow at both ends and thick in the middle. This arrangement gives the heat exchange rib 100 a more suitable draft angle, which is suitable for manufacturing using traditional casting technology.

[0059] In some embodiments, the cross-section of the pressure-reducing part 13 is elliptical, the central axis of the first end 11 of the heat exchange rib 100 coincides with the central axis of the pressure-reducing part 13, and the diameter of the first end 11 is equal to the minor axis of the pressure-reducing part 13; and / or, the central axis of the second end 12 of the heat exchange rib 100 coincides with the central axis of the pressure-reducing part 13, and the diameter of the second end 12 is equal to the minor axis of the pressure-reducing part 13. This arrangement allows the heat exchange rib 100 to have a more suitable draft angle, which is suitable for manufacturing using conventional casting technology.

[0060] As an example, such as Figures 3-5As shown, the cross-section of the pressure-reducing section 13 is elliptical. The central axis of the first end 11 of the heat exchange rib 100 coincides with the central axis of the pressure-reducing section 13, and the central axis of the second end 12 of the heat exchange rib 100 also coincides with the central axis of the pressure-reducing section 13. In other words, the straight line containing the central axis of the first segment 101 coincides with the straight line containing the central axis of the second segment 102, meaning that the first segment 101 and the second segment 102 are coaxially arranged. This makes the structure of the heat exchange rib 100 more reasonable and stable, and also makes it easier to manufacture the molds required for producing the heat exchange rib 100. The diameter of the first end 11 is equal to the minor axis of the pressure-reducing section 13, and the diameter of the second end 12 is equal to the minor axis of the pressure-reducing section 13, giving the heat exchange rib 100 a more suitable draft angle, making it suitable for manufacturing using traditional casting techniques.

[0061] exist Figure 7 In the example shown, the straight line containing the central axis of the pressure relief section 13, the straight line containing the central axis of the first segment 101, and the straight line containing the central axis of the second segment 102 coincide, that is, the pressure relief section 13, the first segment 101, and the second segment 102 are coaxially arranged.

[0062] In some embodiments, such as Figures 3-7 As shown, the first end 11 and the second end 12 of the heat exchange rib 100 are structurally symmetrical with respect to the pressure reducing section 13, ensuring that the turbulence intensity generated by the first end 11 and the second end 12 is equal, resulting in a uniform turbulence effect. This balances the heat exchange capacity of the two sidewalls of the cooling channel, thereby ensuring uniform cooling on both sides of the turbine blades. Furthermore, the first section 101 and the second section 102 are structurally symmetrical with respect to the pressure reducing section 13, meaning that the first section 101 and the second section 102 have the same structural shape, resulting in balanced pressure losses caused by the first section 101 and the second section 102.

[0063] In some embodiments, such as Figures 3-5 As shown, the cross-section of the pressure reducing section 13 is elliptical, and the ratio of the major axis to the minor axis of the pressure reducing section 13 is 1.5:1-3:1. This effectively reduces the pressure loss of the heat exchange rib 100 while keeping the structural strength and manufacturing cost of the heat exchange rib 100 within an ideal range.

[0064] In other embodiments, such as Figure 6 As shown, the cross-section of the pressure-reducing section 13 is a symmetrical airfoil to avoid asymmetrical turbulence in the airflow caused by the pressure-reducing section 13, which would lead to irregular vortices in the airflow and result in uneven cooling in some areas of the cooling channel. Therefore, making the pressure-reducing section 13 a symmetrical airfoil is beneficial to promoting uniform cooling in the cooling channel.

[0065] In some embodiments, such as Figure 8 and Figure 9As shown, the heat exchange rib 100 includes a first circular portion 103 and a second circular portion 104. The first circular portion 103 is disposed adjacent to the first end 11 of the heat exchange rib 100 so that the first end 11 of the heat exchange rib 100 is circular in shape. The second circular portion 104 is disposed adjacent to the second end 12 of the heat exchange rib 100 so that the second end 12 of the heat exchange rib 100 is circular in shape. Both the first circular portion 103 and the second circular portion 104 are cylindrical, and the pressure reducing portion 13 is located between the first circular portion 103 and the second circular portion 104.

[0066] In some embodiments, such as Figure 8 As shown, the heat exchange rib 100 includes a first transition section 105 and a second transition section 106. The first transition section 105 is located between the first circular portion 103 and the pressure-reducing portion 13, and is used for a smooth transition between the first circular portion 103 and the pressure-reducing portion 13. The second transition section 106 is located between the second circular portion 104 and the pressure-reducing portion 13, and is used for a smooth transition between the second circular portion 104 and the pressure-reducing portion 13. The heat exchange rib 100 has a suitable draft angle and is suitable for manufacturing using conventional casting technology.

[0067] In other embodiments, such as Figure 9 As shown, the first circular portion 103 is a straight prism structure, the second circular portion 104 is a straight prism structure, and the pressure-reducing portion 13 is a straight column structure. The first circular portion 103 and the second circular portion 104 are respectively connected to the two ends of the pressure-reducing portion 13 in its axial direction.

[0068] As an example, the first circular portion 103 and the second circular portion 104 are symmetrical to the pressure relief portion 13. The cross-sectional areas of the first circular portion 103 and the second circular portion 104 are both larger than the cross-sectional area of ​​the pressure relief portion 13. The cross-sectional area of ​​the pressure relief portion 13 is smaller, and the pressure loss caused by the pressure relief portion 13 is lower.

[0069] The heat exchange rib 100 of the present invention combines the advantages of cylindrical heat exchange ribs with those of elliptical or airfoil heat exchange ribs. Compared with circular heat exchange ribs, it has a smaller pressure loss. After testing, the pressure loss of the heat exchange rib 100 provided in the present invention is reduced by at least 33% compared with cylindrical heat exchange ribs.

[0070] It should be noted that, as Figure 1 As shown, the pressure loss caused by the elliptical heat exchange rib is relatively large compared with that of the airfoil heat exchange rib. However, the manufacturing difficulty of the pressure relief part 13 with an elliptical cross section is lower than that of the pressure relief part 13 with an airfoil cross section. Therefore, in actual production, the cross section of the pressure relief part 13 can be designed to be elliptical or airfoil according to the requirements.

[0071] In the description of this invention, it should be understood that the terms "center," "longitudinal," "lateral," "length," "width," "thickness," "upper," "lower," "front," "rear," "left," "right," "vertical," "horizontal," "top," "bottom," "inner," "outer," "clockwise," "counterclockwise," "axial," "radial," and "circumferential" indicate the orientation or positional relationship based on the orientation or positional relationship shown in the accompanying drawings. They are used only for the convenience of describing this invention and simplifying the description, and are not intended to indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation. Therefore, they should not be construed as limitations on this invention.

[0072] 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 technical features indicated. Thus, a feature defined as "first" or "second" may explicitly or implicitly include at least one of that feature. In the description of this invention, "a plurality of" means at least two, such as two, three, etc., unless otherwise explicitly specified.

[0073] In this invention, unless otherwise explicitly specified and limited, the terms "installation," "connection," "linking," and "fixing," etc., should be interpreted broadly. For example, they can refer to a fixed connection, a detachable connection, or an integral part; they can refer to a mechanical connection, an electrical connection, or a connection that allows communication between them; they can refer to a direct connection or an indirect connection through an intermediate medium; they can refer to the internal communication of two components or the interaction between two components, unless otherwise explicitly limited. Those skilled in the art can understand the specific meaning of the above terms in this invention according to the specific circumstances.

[0074] In this invention, unless otherwise explicitly specified and limited, "above" or "below" the second feature can mean that the first feature is in direct contact with the second feature, or that the first feature is in indirect contact with the second feature through an intermediate medium. Furthermore, "above," "over," and "on top" of the second feature can mean that the first feature is directly above or diagonally above the second feature, or simply that the first feature is at a higher horizontal level than the second feature. "Below," "below," and "under" the second feature can mean that the first feature is directly below or diagonally below the second feature, or simply that the first feature is at a lower horizontal level than the second feature.

[0075] In this invention, the terms "one embodiment," "some embodiments," "example," "specific example," or "some examples," etc., refer to a specific feature, structure, material, or characteristic described in connection with that embodiment or example, which is included in at least one embodiment or example of the invention. In this specification, the illustrative expressions of the above terms do not necessarily refer to the same embodiment or example. Furthermore, the specific features, structures, materials, or characteristics described may be combined in any suitable manner in one or more embodiments or examples. Moreover, without contradiction, those skilled in the art can combine and integrate the different embodiments or examples described in this specification, as well as the features of different embodiments or examples.

[0076] Although embodiments of the present invention have been shown and described above, it is understood that the above embodiments are exemplary and should not be construed as limiting the present invention. Those skilled in the art can make changes, modifications, substitutions and variations to the above embodiments within the scope of the present invention.

Claims

1. A heat exchange rib with a variable cross-sectional shape, characterized in that, The heat exchange rib has a first end and a second end opposite to each other in its axial direction. The first end and the second end of the heat exchange rib are respectively supported on the two side walls of the cooling channel. The first end and the second end of the heat exchange rib are both circular in shape. The heat exchange rib includes a pressure relief part, which is located between the first end and the second end. The cross-section of the pressure-reducing section is elliptical, and the major axis of the pressure-reducing section is parallel to the direction of the incoming cooling airflow. Alternatively, the cross-section of the pressure-reducing section is an airfoil, the chord of the pressure-reducing section is parallel to the direction of the incoming cooling airflow, the pressure-reducing section has a wider leading edge and a narrower trailing edge, and the leading edge of the pressure-reducing section faces the direction of the incoming cooling airflow. The cross-section of the pressure-reducing section is elliptical. Wherein, the central axis of the first end coincides with the central axis of the pressure reducing part, and the diameter of the first end is the same length as the minor axis of the pressure reducing part; And / or, the central axis of the second end coincides with the central axis of the pressure-reducing part, and the diameter of the second end is equal in length to the minor axis of the pressure-reducing part.

2. The heat exchange rib with variable cross-sectional shape according to claim 1, characterized in that, The first end transitions smoothly to the pressure-reducing section; And / or, the second end smoothly transitions to the pressure-reducing section.

3. The heat exchange rib with a variable cross-sectional shape according to any one of claims 1-2, characterized in that, The heat exchange rib includes a first section and a second section. The first section has a circular shape at one end and an ellipse at the other end in the axial direction. The second section has a circular shape at one end and an ellipse at the other end in the axial direction. The elliptical end of the first section is adapted to and connected to the elliptical end of the second section. Alternatively, the heat exchange rib includes a first section and a second section, the first section having a circular shape and an airfoil at its two ends in the axial direction, and the second section having a circular shape and an airfoil at its two ends in the axial direction, with one end of the airfoil of the first section being adapted to and connected to one end of the airfoil of the second section.

4. The heat exchange rib with a variable cross-sectional shape according to any one of claims 1-2, characterized in that, The first end and the second end are symmetrical with respect to the pressure-reducing part structure; And / or, the cross-section of the pressure-reducing part is elliptical, and the ratio of the major axis to the minor axis of the pressure-reducing part is 1.5:1-3:

1.

5. The heat exchange rib with variable cross-sectional shape according to claim 1, characterized in that, include: A first circular portion and a second circular portion are provided, wherein the first circular portion is disposed adjacent to the first end of the heat exchange rib so that the first end of the heat exchange rib is circular, and the second circular portion is disposed adjacent to the second end of the heat exchange rib so that the second end of the heat exchange rib is circular.

6. The heat exchange rib with variable cross-sectional shape according to claim 5, characterized in that, include: A first transition section is located between the first circular portion and the pressure-reducing portion, and is used to smoothly transition between the first circular portion and the pressure-reducing portion; The second transition section is located between the second circular portion and the pressure-reducing portion, and is used to smoothly transition between the second circular portion and the pressure-reducing portion.

7. The heat exchange rib with variable cross-sectional shape according to claim 5, characterized in that, The first circular portion is a straight prism structure, the second circular portion is a straight prism structure, and the pressure-reducing portion is a straight column structure. The first circular portion and the second circular portion are respectively connected to the two ends of the pressure-reducing portion in their axial direction.

8. A turbine blade, characterized in that, include: A housing, wherein a cooling channel is defined within the housing; A heat exchange rib array, the heat exchange rib array being located within the cooling channel, the heat exchange rib array comprising a plurality of heat exchange ribs arranged at array intervals, the heat exchange ribs being heat exchange ribs with variable cross-sectional shapes according to any one of claims 1-7.

9. A gas turbine, characterized in that, The gas turbine includes the turbine blades as described in claim 8.

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