Heat regenerator and gas turbine thereof

Abstract

The invention relates to a heat regenerator and a gas turbine with the same. The heat regenerator comprises a buffer part and a heat exchanger, the multiple blades are fixedly arranged on the outer side of the buffer part in the circumferential direction, the blades are arranged at intervals in the circumferential direction, cold channels and hot channels are arranged between the blades in a surrounding mode, and the cold channels and the hot channels are alternately arranged; the blade comprises a primary heat exchange part, the primary heat exchange part extends in the involute direction, compressed air flow injected into the cold channel is tangent to the primary heat exchange part, the blade is arranged on the periphery of the buffer piece in a surrounding mode, the blade comprises a primary heat exchange part, and the primary heat exchange part extends in the involute direction. When the compressed air flow passes through the buffer piece and then is injected into the cold channel, the compressed air flow is tangent to the primary heat exchange part, so that the pressure loss of the compressed air flow is greatly reduced, and the heat exchange performance of the heat regenerator is improved.

Description

Technical Field

[0001] The present invention relates to the field of heat exchange equipment, in particular to a regenerator and a gas turbine thereof. Background Art

[0002] A gas turbine is an internal combustion power machine that uses a continuously flowing gas as a working fluid to drive the impeller to rotate at high speed, converting the energy of the fuel into useful work. In existing gas turbines, air is compressed by the compressor and then flows into the diffuser, where a high-speed jet is usually formed at the diffuser outlet. However, this high-speed airflow has a large velocity gradient and an unstable flow field. The existing method usually converts the high-speed jet into a stable airflow to adapt to the layout requirements of the existing regenerator. However, this also results in the failure to fully utilize the excellent heat transfer performance of the high-speed jet itself, resulting in a large pressure loss, thereby affecting the heat transfer performance of the regenerator. Summary of the Invention

[0003] The object of the present invention is to provide a regenerator having the characteristics of good heat exchange performance and good applicability.

[0004] To achieve the above object, the present invention adopts the following technical solutions:

[0005] A regenerator comprises: a buffer member; a plurality of blades fixedly arranged on the circumferential outer side of the buffer member, and the blades are spaced apart in the circumferential direction, a cold channel and a hot channel are arranged between the blades, and the cold channels and the hot channels are arranged alternately; the blades include a primary heat exchange portion, the primary heat exchange portion extends in an involute direction, and a compressed airflow injected into the cold channel is tangent to the primary heat exchange portion.

[0006] Preferably, the buffer member includes an upper fixing plate, a lower fixing plate, and a connecting plate fixed to both the upper fixing plate and the lower fixing plate, the upper fixing plate and the lower fixing plate are both fixed to the primary heat exchange part, and the connecting plate is spaced apart from the primary heat exchange part;

[0007] A buffer cavity is arranged between the buffer component and the primary heat exchange portion.

[0008] Preferably, the connecting plate has an opening, and along the axial direction of the regenerator, the opening is located on the lower side of the horizontal center line of the connecting plate.

[0009] Preferably, the opening is an annular opening, and the opening is located 7-9 mm below the horizontal center line of the connecting plate.

[0010] Preferably, the blade further includes a secondary heat exchange portion integrally formed with the primary heat exchange portion, and the secondary heat exchange portion is located radially outward of the primary heat exchange portion;

[0011] A cold channel inlet is formed at one end of the primary heat exchange part away from the secondary heat exchange part, and the cold channel inlet is spaced apart from the opening; a cold channel outlet is formed at one end of the secondary heat exchange part away from the primary heat exchange part.

[0012] Preferably, the regenerator further comprises an upper sealing plate and a lower sealing plate, wherein along the axial direction of the regenerator, the lower sealing plate is sealingly arranged on the lower end surface of the blade, and the lower sealing plate forms a heat channel inlet, and the upper sealing plate is sealingly arranged on the upper end surface of the blade, and the upper sealing plate forms a heat channel outlet;

[0013] Along the radial direction of the regenerator, the hot channel inlet is located radially outside the hot channel outlet.

[0014] Preferably, along the axial direction of the regenerator, the height of the primary heat exchange part is smaller than the height of the secondary heat exchange part, and the height of the primary heat exchange part gradually decreases in a direction away from the secondary heat exchange part.

[0015] Preferably, the secondary heat exchange portion extends along an involute direction or a straight line direction.

[0016] A gas turbine comprises a regenerator and a diffuser, wherein the diffuser is located in a buffer component, and an outlet of the diffuser is communicated with an opening of the buffer component.

[0017] Preferably, the diffuser includes a main body and a plurality of guide plates arranged on the main body, the guide plates are arranged at intervals in the circumferential direction, the compressed airflow flows between adjacent guide plates, and the angle between the compressed airflow and the tangent of the outer circle of the main body is 19.6°, the compressed airflow enters the buffer cavity through the opening, and then the compressed airflow enters the cold channel in a direction tangent to the primary heat exchange part.

[0018] Compared with the prior art, the present invention has the following beneficial effects:

[0019] The above technical solution provides a regenerator, which is surrounded by blades arranged on the outer periphery of the buffer, and the blades include a primary heat exchange part, which extends along the involute direction. When the compressed air flow passes through the buffer and is injected into the cold channel, the compressed air flow is tangent to the primary heat exchange part, thereby greatly reducing the pressure loss of the compressed air flow and improving the heat exchange performance of the regenerator. BRIEF DESCRIPTION OF THE DRAWINGS

[0020] Figure 1 A schematic diagram of a heat regenerator provided by an embodiment of the present invention from one perspective;

[0021] Figure 2 A schematic diagram of a regenerator provided by an embodiment of the present invention from another perspective;

[0022] Figure 3 for Figure 2 A magnified schematic diagram of point A in the middle;

[0023] Figure 4 A schematic diagram of the assembly of a buffer member and a blade provided in an embodiment of the present invention;

[0024] Figure 5 A schematic diagram of a buffer provided in an embodiment of the present invention;

[0025] Figure 6 A schematic diagram of the assembly of a blade provided in an embodiment of the present invention;

[0026] Figure 7 A schematic diagram of a regenerator and a diffuser provided in an embodiment of the present invention;

[0027] Figure 8 A schematic diagram of a diffuser provided in an embodiment of the present invention;

[0028] Figure 9 A schematic cross-sectional view of a regenerator and a diffuser provided in an embodiment of the present invention;

[0029] Figure 10 for Figure 9 A magnified schematic diagram of point B in the middle;

[0030] Figure 11 A schematic diagram of the flow directions of cold fluid and hot fluid in a regenerator provided in an embodiment of the present invention;

[0031] Figure 12 A schematic diagram of the flow direction of the cooling fluid of a gas turbine provided in an embodiment of the present invention.

[0032] 1. Buffer; 11. Upper fixing plate; 12. Lower fixing plate; 13. Connecting plate; 14. Buffer chamber; 15. Opening; 2. Blades; 21. Primary heat exchange section; 22. Secondary heat exchange section; 3. Cold channel; 31. Cold channel inlet; 32. Cold channel outlet; 4. Hot channel; 41. Hot channel inlet; 42. Hot channel outlet; 5. Upper sealing plate; 6. Lower sealing plate; 7. Diffuser; 71. Main body; 72. Guide plate. DETAILED DESCRIPTION

[0033] The present invention will be described in more detail below with reference to the accompanying drawings. It should be noted that the description of the present invention with reference to the accompanying drawings is merely illustrative and non-limiting. Different embodiments can be combined with each other to form other embodiments not shown in the following description.

[0034] See also Figures 1 to 12The present invention provides a regenerator, which includes a buffer 1, blades 2, a cold channel 3, a hot channel 4, an upper sealing plate 5, and a lower sealing plate 6. The present invention also provides a gas turbine, which includes a regenerator and a diffuser 7.

[0035] Specifically, a plurality of blades 2 are fixedly arranged on the circumferential outer side of the buffer member 1, and the blades 2 are arranged at intervals in the circumferential direction. A cold channel 3 and a hot channel 4 are arranged between the blades 2, and the cold channels 3 and the hot channels 4 are arranged alternately; the blades 2 include a primary heat exchange portion 21, the primary heat exchange portion 21 extends along the involute direction, and the compressed airflow injected into the cold channel 3 is tangent to the primary heat exchange portion 21.

[0036] The present invention provides a regenerator, which is surrounded by blades 2 and arranged on the outer periphery of a buffer member 1. The blades 2 include a primary heat exchange portion 21, which extends along the involute direction. When the compressed airflow passes through the buffer member 1 and is injected into the cold channel 3, the compressed airflow is tangent to the primary heat exchange portion 21, thereby greatly reducing the pressure loss of the compressed airflow and improving the heat exchange performance of the regenerator.

[0037] What you need to know is that the working principle of a gas turbine is to compress the air through a compressor to increase its pressure to form a compressed airflow, and then heat the compressed airflow in the combustion chamber to generate high-temperature and high-pressure gas to drive the turbine to do work. The compressed airflow expands and works in the turbine and is discharged as exhaust gas. Since the temperature of the exhaust gas discharged from the turbine is still very high, the regenerator can use the heat energy of the exhaust gas to preheat the compressed airflow after the compressor, thereby improving the overall thermal efficiency of the system.

[0038] A regenerator typically consists of two channels: a cold channel 3 and a hot channel 4. High-temperature exhaust gas flows through the hot channel 4, while the compressed air flows through the cold channel 3. In the regenerator, the compressed air in the cold channel 3 absorbs heat from the high-temperature exhaust gas and is heated before entering the combustion chamber for further heating, effectively reducing fuel consumption. By incorporating a regenerator, the thermal efficiency of the gas turbine can be significantly improved, effectively reducing fuel consumption.

[0039] To reduce the pressure loss of the compressed air in the regenerator, the gas turbine is equipped with a diffuser 7 at the compressor outlet. The diffuser 7 converts the kinetic energy of the compressed air into static pressure, increasing the static pressure and reducing the dynamic pressure of the compressed air. This effectively reduces the pressure loss of the compressed air before it enters the regenerator.

[0040] More specifically, the total number of blades 2 is 316. The cold channels 3 and hot channels 4 formed between each blade 2 are alternately distributed, and the width of each cold channel 3 and hot channel 4 is 0.9 mm. That is, the spacing between the cold channels 3 and hot channels 4 remains consistent along the flow direction, avoiding pressure loss caused by local expansion or contraction, thereby achieving both efficient heat exchange and low flow resistance. The maximum height of the blade 2 is 158 mm, the expanded length of the blade 2 is 497.13 mm, and the overall outer diameter of the regenerator is 500 mm. The blades 2 and buffer 1 can be made of SS321 stainless steel.

[0041] In addition, since the regenerator is cylindrical as a whole, the axial direction of the regenerator is defined as the axial direction, and the diameter direction of the regenerator is defined as the radial direction.

[0042] The buffer member 1 includes an upper fixing plate 11, a lower fixing plate 12, and a connecting plate 13 fixed to both the upper fixing plate 11 and the lower fixing plate 12. The upper fixing plate 11 and the lower fixing plate 12 are fixed to the primary heat exchange part 21, specifically by welding. The connecting plate 13 is spaced apart from the primary heat exchange part 21; a buffer cavity 14 is enclosed between the buffer member 1 and the primary heat exchange part 21.

[0043] Specifically, the connecting plate 13 is annular, and the upper fixing plate 11 and the lower fixing plate 12 can be integrally formed at the two axial ends of the connecting plate 13, and along the radial direction of the heat regenerator, the upper fixing plate 11 and the lower fixing plate 12 protrude outward from the outer surface of the connecting plate 13. When the upper fixing plate 11 and the lower fixing plate 12 are fixed to the primary heat exchange part 21, the connecting plate 13 is still spaced apart from the primary heat exchange part 21, so a partial buffer cavity 14 can be enclosed between the connecting plate 13 and the primary heat exchange part 21.

[0044] It should be understood that after exiting the diffuser 7, the compressed airflow enters the cold channel inlet 31. If the distance between the blades 2 and the diffuser 7 is too small, the compressed airflow will directly impact the surface of the blades 2, resulting in pressure loss of the compressed airflow. To avoid this, the present invention provides a buffer member 1 between the blades 2 and the diffuser 7, with a buffer cavity 14 enclosed between the buffer member 1 and the blades 2. Therefore, after exiting the diffuser 7, the compressed airflow first enters the buffer cavity 14 for buffering before entering the cold channel inlet 31. This prevents the compressed airflow from directly impacting the surface of the blades 2, thereby significantly preserving the compressed airflow's own pressure.

[0045] See also Figures 4 and 5 The connecting plate 13 has an opening 15, and along the axial direction of the regenerator, the opening 15 is located below the horizontal center line of the connecting plate 13. Specifically, the opening 15 is an annular opening, and the opening 15 is located 7-9 mm below the horizontal center line of the connecting plate 13.

[0046] It can be seen that the horizontal center line of the connecting plate 13 is Figure 5 The dotted line indicates that the axial lengths of the connecting plate 13 above and below the dotted line are the same. By positioning the opening 15 below the horizontal centerline of the connecting plate 13, the present invention fully utilizes the jet heat exchange mechanism, creating strong turbulent flow at the cold channel inlet 31, thereby further improving the overall heat exchange performance of the regenerator.

[0047] More specifically, because opening 15 is located 7-9 mm (preferably 8 mm) below the horizontal centerline of connecting plate 13, the compressed airflow forms a strong turbulent disturbance after entering the cold channel inlet 31 in the form of a jet. Furthermore, because hot channel inlet 41 is located axially below blade 2, the temperature on the underside of blade 2 is higher. Based on this, the present invention lowers the position of opening 15, thereby fully utilizing the turbulent characteristics of the jet and further improving heat exchange performance. Of course, if the position of opening 15 is too low, it will affect the heat exchange effect of the compressed airflow in the rear part of the regenerator. Therefore, through optimization calculations, locating opening 15 7-9 mm below the horizontal centerline of connecting plate 13 achieves maximum heat exchange performance.

[0048] It should be clear that after the compressed airflow passes through the opening 15 and the buffer cavity 14, it will enter the cold channel inlet 31. Since the opening 15 is located below the horizontal centerline of the connecting plate 13, the compressed airflow is also injected into the cold channel inlet 31 at a position below the horizontal centerline of the cold channel inlet 31.

[0049] See also Figure 6 The blade 2 further includes a secondary heat exchange portion 22 integrally formed with the primary heat exchange portion 21 , and the secondary heat exchange portion 22 is located radially outward of the primary heat exchange portion 21 .

[0050] A cold channel inlet 31 is formed at one end of the primary heat exchange part 21 away from the secondary heat exchange part 22 , and the cold channel inlet 31 is spaced apart from the opening 15 ; a cold channel outlet 32 ​​is formed at one end of the secondary heat exchange part 22 away from the primary heat exchange part 21 .

[0051] Along the axial direction of the regenerator, the lower sealing plate 6 is sealed on the lower end surface of the blade 2, and the lower sealing plate 6 forms a hot channel inlet 41. The upper sealing plate 5 is sealed on the upper end surface of the blade 2, and the upper sealing plate 5 forms a hot channel outlet 42. Along the radial direction of the regenerator, the hot channel inlet 41 is located radially outside the hot channel outlet 42.

[0052] See also Figures 1 to 3 、 Figures 10 to 12It can be seen that during the heat exchange process, the compressed air flow, that is, the cold fluid, first enters the cold channel 3 through the cold channel inlet 31 and then is ejected through the cold channel outlet 32. The overall path basically flows outward along the radial direction of the regenerator. The high-temperature exhaust gas, that is, the hot fluid, first enters the hot channel 4 through the hot channel inlet 41 and then is ejected through the hot channel outlet 42. The overall path flows inward along the radial direction of the regenerator and simultaneously flows from bottom to top along the axial direction of the regenerator. In other words, the present invention realizes the countercurrent flow of the cold fluid and the hot fluid, and can ensure a large average temperature difference during the heat exchange process. Compared with the existing parallel flow or cross flow heat exchange mode, the heat exchange efficiency is significantly improved, thereby enhancing the overall thermal efficiency of the gas turbine.

[0053] See also Figure 6 Along the axial direction of the regenerator, the height of the primary heat exchange portion 21 is less than the height of the secondary heat exchange portion 22, and the height of the primary heat exchange portion 21 gradually decreases in a direction away from the secondary heat exchange portion 22. The secondary heat exchange portion 22 extends in an involute direction or a straight line direction.

[0054] It can be known that the compressed airflow enters the cold channel inlet 31 in the form of a jet, which causes the compressed airflow to hardly participate in the heat exchange in the upper and lower axial parts of the primary heat exchange part 21. Therefore, the present invention removes the part of the primary heat exchange part 21 that does not participate in the heat exchange in a streamlined manner, thereby forming a shape in which the height of the primary heat exchange part 21 gradually decreases in the direction away from the secondary heat exchange part 22. The blades 2 of this shape can greatly reduce the overall mass of the heat exchanger without affecting the overall heat exchange performance of the heat exchanger, greatly reduce the cost of the heat exchanger, and improve practicality.

[0055] More specifically, when the compressed airflow enters the cold channel 3 in the form of a jet, the high-speed main jet area near the cold channel inlet 31 is the primary heat exchange zone, and the primary heat exchange zone corresponds to the primary heat exchange part 21. The compressed airflow in the primary heat exchange zone has a high flow rate and a high turbulence intensity, and the heat transfer capacity is significantly enhanced. As the compressed airflow flows along the cold channel 3 and gradually diffuses, the flow field tends to be uniform and enters the secondary heat exchange zone. The secondary heat exchange zone corresponds to the secondary heat exchange part 22. The secondary heat exchange zone mainly transfers heat in the form of stable convection. Structurally, the primary heat exchange part 21 extends along an involute shape, corresponding to the high jet path of the compressed airflow, which is conducive to maintaining the high-speed flow characteristics of the compressed airflow; and the secondary heat exchange part 22 can extend in the involute direction or in a straight line direction, corresponding to the uniform flow path of the compressed airflow, mainly to enhance the overall heat exchange area and efficiency.

[0056] See also Figures 7 to 12 The gas turbine provided by the present invention includes the above-mentioned regenerator and also includes a diffuser 7. The diffuser 7 is located in the buffer 1, and the outlet of the diffuser 7 is connected to the opening 15 of the buffer 1.

[0057] The diffuser 7 includes a main body 71 and a plurality of guide plates 72 arranged on the main body 71. The guide plates 72 are arranged at intervals along the circumferential direction. The compressed air flows between adjacent guide plates 72, and the angle between the compressed air and the tangent of the outer circle of the main body 71 is 19.6°. The compressed air enters the buffer cavity 14 through the opening 15, and then enters the cold channel 3 in a direction tangential to the primary heat exchange part 21.

[0058] Specifically, the main body 71 is cylindrical and can abut against the connecting plate 13. Along the axial direction of the regenerator, the upper surface of the main body 71 can be aligned with the lower side of the opening 15. Therefore, the compressed airflow flowing out of the diffuser 7 can directly pass through the opening 15 and flow into the buffer chamber 14. A plurality of guide plates 72 are provided on the upper surface of the main body 71. The extension direction of the guide plates 72 is arranged at an angle to the radial direction of the main body 71. Therefore, when the compressed airflow is ejected from adjacent guide plates 72, the angle between the compressed airflow and the tangent line of the outer circle of the main body 71 is 19.6°. On this basis, the present invention adjusts the position and angle of the blades 2 so that the compressed airflow can be injected into the cold channel 3 along the tangent line of the primary heat exchange portion 21, thereby greatly reducing the pressure of the compressed airflow itself and thereby improving the heat exchange efficiency of the regenerator.

[0059] The present invention also provides the following examples to verify the excellent heat exchange efficiency of the present invention:

[0060] Example:

[0061] Taking a 30kW micro gas turbine as an example, this invention can be applied to heat recovery and improve system thermal efficiency. For a 30kW micro gas turbine with a compressor pressure ratio of 3.6 and a turbine inlet temperature of 1100K, the system thermal efficiency is 0.17 without adding a regenerator. The specific algorithm is as follows:

[0062]

[0063] Where η is the thermal efficiency of the gas turbine, and h1, h2, h4, and h5 represent the enthalpy values ​​of the air before the compressor, after the compressor, before the turbine, and after the turbine, respectively. Adding the regenerator provided by this invention to the micro-gas turbine can double the system's thermal efficiency to 0.34. The specific algorithm is as follows:

[0064]

[0065] Where h3 represents the enthalpy value of the cold outlet of the regenerator.

[0066] In summary, the present invention has the following beneficial effects:

[0067] 1. Design of Cold Aisle 3

[0068] The present invention utilizes the characteristics of the compressed airflow at the outlet of diffuser 7 to allow the compressed airflow to enter the cold channel 3 of the regenerator in the form of a jet. In the present invention, a high-speed, directional compressed airflow is formed at the outlet of diffuser 7, and passes through a buffer chamber 14 to prevent the compressed airflow from directly impacting the surface of blades 2. This compressed airflow significantly improves the local heat transfer coefficient of cold channel 3 and enhances the cold-side convective heat transfer capacity. The strong turbulence and shear layer disturbances stimulated by the compressed airflow facilitate boundary layer regeneration and temperature gradient reconstruction, thereby improving overall heat transfer performance without significantly increasing the pressure drop at the cold end.

[0069] 2. Regenerator blade 2 adopts involute structure arrangement

[0070] Because the involute structure features continuously changing curvature and essentially constant channel spacing, it maintains a stable flow of hot and cold fluids within the channel, effectively reducing flow non-uniformity and localized turbulence concentration, minimizing pressure loss, and improving heat transfer uniformity. Furthermore, the counterflow design maintains a large average temperature difference throughout the heat transfer process, significantly improving heat recovery efficiency compared to parallel or cross-flow heat transfer modes, thereby effectively increasing the overall thermal efficiency of the micro gas turbine.

[0071] 3. The compressed airflow enters the cold channel 3 at the middle and lower part of the blade 2

[0072] Through detailed calculation and optimization, the present invention determined the optimal cold fluid channel entrance location. The cold fluid enters the cold channel 3 from the center of the regenerator approximately 8 mm below the horizontal centerline of blade 2. By placing the jet inlet in the lower middle portion of the cold channel 3, the present invention fully utilizes the high kinetic energy and strong heat transfer characteristics of the jet in its initial phase, forming a highly efficient primary heat exchange zone. Simultaneously, as the cold fluid naturally diffuses, a secondary heat exchange zone is established, maximizing overall heat transfer performance from inlet to outlet.

[0073] 4. Optimization of hot and cold fluid inlet and outlet partitions

[0074] The present invention clearly zons the inlets and outlets of the cold and hot fluids. By clearly dividing the inlet and outlet areas of the cold and hot fluid channels, the mixing and backflow of the fluids during the heat exchange process are reduced, the risk of decreased heat transfer efficiency is reduced, and the working stability and overall heat exchange performance of the regenerator are further improved.

[0075] The above embodiments are only preferred embodiments of the present invention and cannot be used to limit the scope of protection of the present invention. Any non-substantial changes and replacements made by technicians in this field on the basis of the present invention fall within the scope of protection required by the present invention.

Claims

1. A regenerator, characterized in that: include: Buffer (1); A plurality of blades (2) are fixedly arranged on the circumferential outer side of the buffer member (1), and the blades (2) are spaced apart in the circumferential direction. A cold channel (3) and a hot channel (4) are arranged between the blades (2), and the cold channel (3) and the hot channel (4) are arranged alternately. The blades (2) include a primary heat exchange portion (21), the primary heat exchange portion (21) extends in an involute direction, and a compressed airflow injected into the cold channel (3) is tangent to the primary heat exchange portion (21).

2. The regenerator according to claim 1, wherein: The buffer member (1) comprises an upper fixing plate (11), a lower fixing plate (12), and a connecting plate (13) fixed to both the upper fixing plate (11) and the lower fixing plate (12); the upper fixing plate (11) and the lower fixing plate (12) are both fixed to the primary heat exchange portion (21); and the connecting plate (13) is spaced apart from the primary heat exchange portion (21); A buffer chamber (14) is provided between the buffer component (1) and the primary heat exchange portion (21).

3. The regenerator according to claim 2, wherein: The connecting plate (13) has an opening (15), and along the axial direction of the regenerator, the opening (15) is located on the lower side of the horizontal center line of the connecting plate (13).

4. The regenerator according to claim 3, wherein: The opening (15) is an annular opening, and the opening (15) is located 7-9 mm below the horizontal center line of the connecting plate (13).

5. The regenerator according to claim 3, wherein: The blade (2) further includes a secondary heat exchange portion (22) integrally formed with the primary heat exchange portion (21), wherein the secondary heat exchange portion (22) is located radially outside the primary heat exchange portion (21); A cold channel inlet (31) is formed at one end of the primary heat exchange portion (21) away from the secondary heat exchange portion (22), and the cold channel inlet (31) is spaced apart from the opening (15); a cold channel outlet (32) is formed at one end of the secondary heat exchange portion (22) away from the primary heat exchange portion (21).

6. The regenerator according to claim 5, wherein: The regenerator further comprises an upper sealing plate (5) and a lower sealing plate (6); along the axial direction of the regenerator, the lower sealing plate (6) is sealingly arranged on the lower end surface of the blade (2), and the lower sealing plate (6) is formed with a heat channel inlet (41); the upper sealing plate (5) is sealingly arranged on the upper end surface of the blade (2), and the upper sealing plate (5) is formed with a heat channel outlet (42); Along the radial direction of the regenerator, the hot channel inlet (41) is located radially outside the hot channel outlet (42).

7. The regenerator according to claim 5, wherein: Along the axial direction of the regenerator, the height of the primary heat exchange part (21) is smaller than the height of the secondary heat exchange part (22), and the height of the primary heat exchange part (21) gradually decreases in a direction away from the secondary heat exchange part (22).

8. The regenerator according to claim 5, wherein: The secondary heat exchange portion (22) extends along an involute direction or a straight line direction.

9. A gas turbine, characterized in that: The regenerator comprises the regenerator according to any one of claims 1 to 8, and further comprises a diffuser (7), wherein the diffuser (7) is located in the buffer (1), and the outlet of the diffuser (7) is connected to the opening (15) of the buffer (1).

10. The gas turbine according to claim 9, wherein The diffuser (7) includes a main body (71) and a plurality of guide plates (72) arranged on the main body (71), wherein the guide plates (72) are arranged at intervals along the circumferential direction, and the compressed air flows between adjacent guide plates (72), and the angle between the compressed air and the tangent line of the outer circle of the main body (71) is 19.6°. The compressed air enters the buffer cavity (14) through the opening (15), and then enters the cold channel (3) in a direction tangential to the primary heat exchange part (21).

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