A gas turbine blade cooling device

Abstract

The application discloses a gas turbine blade cooling device, which comprises an air inlet end, a fixed blade cooling mechanism and a moving blade cooling mechanism, wherein the moving blade cooling mechanism comprises an air inlet wheel which is fixedly installed on the outside of a main shaft, one side of the air inlet wheel is provided with a gas guide cover, the circumferential direction of the air inlet wheel is provided with a vortex mechanism, the surface of the air inlet wheel is provided with an air inlet, and the air inlet is communicated with the vortex mechanism; the vortex mechanism comprises an air inlet seat; compressed air is guided through the gas guide cover, introduced through the air inlet, transported through a gas guide pipe, tangentially enters the air inlet seat through a tangential air port, cooperates with a gas guide inner seat to form a high-speed vortex, and automatically separates a central low-temperature gas flow and a peripheral high-temperature gas flow through energy exchange; the low-temperature gas flow is introduced into a moving blade through a cold gas pipe and an internal channel of the main shaft and is specially used for blade cooling; compared with a traditional cooling mode of directly introducing compressed air, the cooling temperature is lower and the cooling efficiency is higher, and the problem that the traditional air cooling effect is poor is improved from the root.

Description

Technical Field

[0001] This invention belongs to the field of gas turbine technology, and specifically relates to a gas turbine blade cooling device. Background Technology

[0002] A gas turbine blade cooling system is a complex airflow channel, cavity, and structural design integrated inside and on the surface of the gas turbine blade. Its core function is to forcibly cool the blade metal, enabling it to operate safely for extended periods in high-temperature combustion gases far exceeding the material's melting point. Cooling gas flows inside the blade, carrying away heat (internal cooling), and is ejected from small holes on the blade surface to form a heat-insulating film (external cooling), reducing the blade metal temperature to within the material's safe operating range.

[0003] Currently, conventional gas turbine blades generally use compressed air as the cooling medium for forced cooling during actual operation. This cooling method typically uses an air compressor to provide the cooling air source, which is then transported through pipelines into the internal flow channels of the blade. Heat is removed from the blade surface and interior through convection heat transfer and film insulation. However, under actual operating conditions, due to factors such as the relatively weak heat exchange capacity of air itself, uneven distribution of cooling air flow, and flow field disturbances at high temperatures, the heat exchange efficiency of existing air cooling systems is low. The overall cooling effect is insufficient to meet the increasing demands of turbine inlet gas temperatures, and the blades still face high thermal loads and the risk of thermal fatigue. Therefore, a gas turbine blade cooling device needs to be designed to address these problems. Summary of the Invention

[0004] The purpose of this invention is to provide a gas turbine blade cooling device to solve the problems mentioned in the background art.

[0005] To achieve the above objectives, the present invention provides the following technical solution: a gas turbine blade cooling device, comprising: At the intake end, a compressor, a combustion chamber, and a turbine chamber are sequentially installed at one end of the intake end. A main shaft is installed in the middle of the compressor, combustion chamber, and turbine chamber. Stationary blades are installed on the inner wall of the turbine chamber. Moving blades are installed at one end of the main shaft. A fixed-blade cooling mechanism includes a steam pump installed inside the compressor and connected to the stationary blades via a pipe assembly. The blade cooling mechanism includes an air intake wheel, which is fixedly installed on the outside of the main shaft. An air guide shroud is installed on one side of the air intake wheel. A vortex mechanism is installed around the air intake wheel. An air inlet is provided on the surface of the air intake wheel, and the air inlet is connected to the vortex mechanism. The vortex mechanism includes an air intake seat, which is fixedly installed inside the air intake wheel. An air guide pipe is provided on one side of the air intake seat, and one end of the air guide pipe is connected to the air intake port. A hot air pipe and a cold air pipe are respectively installed at both ends of the air intake seat. An air guide head is installed at one end of the hot air pipe, and the orientation of the air guide head corresponds to the interior of the combustion chamber. An air guide plug is installed inside the air guide head. One end of the cold air pipe is connected to the internal channel of the main shaft, and the internal channel of the main shaft is connected to the interior of the moving blade.

[0006] Preferably, the air intake wheel is located at one end of the compressor, and the air guide shroud is connected to the interior of the compressor.

[0007] Preferably, the inner wall of the air inlet seat is provided with a tangential air port, which is connected to the air guide pipe.

[0008] Preferably, one end of the air guide plug is fixedly installed with an air-blocking protrusion, the outer surface of the air-blocking protrusion is provided with an air guide hole, and the other end of the air guide plug is internally connected to the air guide hole.

[0009] Preferably, the air intake seat is equipped with an air guide inner seat, and a spiral guide groove is provided between the air guide inner seat and the air intake seat. The interior of the air guide inner seat is connected to the interior of the cold air pipe.

[0010] Preferably, the moving blade includes a moving blade body and a trapezoidal connecting seat. The moving blade body is mounted on one end of the main shaft via the trapezoidal connecting seat. A cooling air passage is provided inside the moving blade body. An air intake passage is provided inside the trapezoidal connecting seat. One end of the air intake passage is connected to an internal passage of the main shaft. One end of the cooling air passage is connected to the other end of the air intake passage. A top air film hole is provided at the end of the moving blade body. The other end of the cooling air passage is connected to the top air film hole.

[0011] Preferably, the front end face of the moving blade body is provided with an end air film hole, the side cross face of the moving blade body is provided with a tangential air film hole, the end air film hole and the tangential air film hole are both connected to the cooling air passage, and a ceramic film is provided on the surface of the moving blade body.

[0012] Preferably, the piping assembly includes a heat-absorbing pipe, an external pipe, a heat-conducting pipe, and a heat-dissipating pipe. The heat-absorbing pipe is installed on the inner wall of the combustion chamber, the external pipe is installed on the outer wall of the combustion chamber, the heat-dissipating pipe is installed on the inner wall of the compressor, and the heat-conducting pipe is installed on the outer side of the compressor. One end of the heat-absorbing pipe is connected to the stationary blade, and one end of the heat-conducting pipe is connected to the other end of the heat-absorbing pipe via a steam pump. The other end of the heat-conducting pipe is connected to one end of the heat-dissipating pipe, and the other end of the heat-dissipating pipe is connected to one end of the external pipe. The other end of the external pipe is connected to the stationary blade, and a heat-conducting fin is fixedly installed between the heat-conducting pipe and the heat-dissipating pipe.

[0013] Preferably, the stationary blade includes a stationary blade body, one end of which is fixedly mounted with a mounting base. The stationary blade body is mounted on the inner wall of the turbine chamber via the mounting base. An inlet and an outlet are provided on the inner side of the mounting base. A flow-guiding heat absorption cavity is provided inside the stationary blade body, and the two ends of the flow-guiding heat absorption cavity are respectively connected to the inlet and the outlet.

[0014] Preferably, the steam inlet is connected to one end of the external pipe, the heat-absorbing chamber is connected to one end of the heat-absorbing pipe, and the surface of the stationary blade body is provided with a heat-insulating film.

[0015] Compared with the prior art, the beneficial effects of the present invention are: 1. Compressed air is guided by the air guide shroud, introduced through the air inlet, and transported through the air guide pipe. It enters the air inlet tangentially along the tangential air inlet and forms a high-speed vortex with the inner air guide seat. Through energy exchange, the central low-temperature airflow and the peripheral high-temperature airflow are automatically separated. The low-temperature airflow is introduced into the moving blades through the cooling pipe and the internal channel of the main shaft, which is specifically used for blade cooling. Compared with the traditional cooling method of directly introducing compressed air, the cooling temperature is lower and the cooling efficiency is higher, which fundamentally improves the problem of poor traditional air cooling effect.

[0016] 2. The high-temperature hot air generated by eddy separation is introduced into the combustion chamber through the hot air pipe, the air guide hole of the air guide head, and the air guide plug to participate in secondary combustion, realizing the recovery and utilization of waste heat. While enhancing cooling, it reduces energy loss and improves the overall thermal efficiency of the gas turbine.

[0017] 3. The cooling airflow enters the moving blade body through the internal channel of the main shaft and the air intake channel of the trapezoidal connecting seat. It fully exchanges heat in the cooling air passage and then exits through the end air film hole, tangential air film hole and top air film hole, forming a complete and continuous low temperature air film on the surface of the moving blade body. This effectively isolates the blade from the scouring of high temperature combustion gases. Combined with the ceramic film on the surface of the moving blade body, this significantly reduces the heat load on the blade and improves its high temperature resistance and thermal fatigue resistance.

[0018] 4. The stationary blades adopt a closed-loop cooling system driven by a steam pump of the fixed blade cooling mechanism. The steam flows continuously in the heat absorption chamber inside the stationary blade body, which has strong heat exchange capacity and uniform cooling. This avoids the defects of traditional air cooling flow fluctuation and uneven cooling, and ensures the long-term stable operation of the stationary blades.

[0019] 5. After absorbing the heat from the main body of the stationary blades, the steam flows into the heat absorption pipe through the steam outlet, further absorbing the residual heat from the combustion chamber wall. Then, it is pressurized by the steam pump and enters the heat conduction pipe. The heat is transferred to the heat dissipation pipe through the heat conduction fins. The airflow in the compressor is guided by the airflow groove to sweep across the surface of the heat dissipation pipe, achieving forced air cooling. The cooled steam flows back to the heat absorption chamber through the external pipe and steam inlet, realizing multi-stage heat recovery and reuse. Attached Figure Description

[0020] Figure 1This is a schematic diagram of the gas turbine structure of the present invention; Figure 2 This is a schematic diagram of the gas turbine cross-sectional structure of the present invention; Figure 3 For the present invention Figure 2 Schematic diagram of the structure at point A in the middle; Figure 4 This is a schematic diagram of the external heat absorption tube structure of the present invention; Figure 5 This is a schematic diagram of the stationary blade structure of the present invention; Figure 6 This is a schematic diagram of the intake wheel structure of the present invention; Figure 7 This is a schematic diagram of the eddy current mechanism structure of the present invention; Figure 8 This is a schematic diagram of the moving blade structure of the present invention; In the diagram: 1. Inlet; 11. Compressor; 12. Combustion chamber; 13. Turbine chamber; 14. Main shaft; 2. Fixed blade cooling mechanism; 21. Heat dissipation pipe; 22. Heat conduction pipe; 23. Heat absorption pipe; 24. External pipe; 25. Steam pump; 26. Heat conduction fin; 27. Airflow channel; 3. Moving blade cooling mechanism; 31. Inlet impeller; 32. Air guide shroud; 33. Inlet port; 4. Swirl mechanism; 41. Inlet seat; 42. Air guide pipe; 43. Tangential air inlet; 44. Inner air guide seat; 45. Heat... 46. ​​Air pipe; 47. Air guide head; 48. Air guide plug; 481. Air guide hole; 482. Air baffle protrusion; 5. Moving blade; 51. Moving blade body; 52. Trapezoidal connecting seat; 53. Air inlet channel; 54. Cooling air channel; 55. End film air hole; 56. Tangential film air hole; 57. Top film air hole; 58. Ceramic film; 6. Stationary blade; 61. Stationary blade body; 62. Mounting seat; 63. Steam inlet; 64. Guide heat absorption chamber; 65. Steam outlet; 66. Heat insulation film. Detailed Implementation

[0021] The technical solutions of the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some embodiments of the present invention, and not all embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of the present invention.

[0022] Example 1: Please see Figures 1 to 3This invention provides a technical solution: a gas turbine blade cooling device, comprising an inlet end 1, a fixed blade cooling mechanism 2, and a moving blade cooling mechanism 3; a compressor 11, a combustion chamber 12, and a turbine chamber 13 are sequentially arranged along the airflow direction at one end of the inlet end 1, the compressor 11, the combustion chamber 12, and the turbine chamber 13 are arranged coaxially, and a main shaft 14 is provided through the middle of the turbine chamber 13; stationary blades 6 are fixedly installed on the inner wall of the turbine chamber 13, and moving blades 5 are fixedly installed at one end of the main shaft 14 near the turbine chamber 13, the main shaft 14 drives the moving blades 5 to rotate synchronously under the drive of high-temperature gas, thereby realizing energy conversion; The moving blade cooling mechanism 3 includes an air inlet wheel 31, which is fixedly sleeved on the outside of the main shaft 14 and can rotate synchronously with the main shaft 14. An air guide shroud 32 is provided on one side of the air inlet wheel 31, and vortex mechanisms 4 are evenly arranged around the circumference of the air inlet wheel 31. An air inlet 33 is opened on the surface of the air inlet wheel 31 and is connected to the vortex mechanism 4 to guide the cooling airflow from the compressor 11 into the vortex mechanism 4. The air inlet wheel 31 is arranged at one end of the compressor 11, and the air guide shroud 32 is connected to the inside of the compressor 11 to guide and converge the compressed air output by the compressor 11. The vortex mechanism 4 includes an intake seat 41, which is fixedly installed inside the intake wheel 31. An air guide pipe 42 is provided on one side of the intake seat 41, with one end connected to the intake port 33. A hot air pipe 45 and a cold air pipe 46 are respectively connected to both ends of the intake seat 41. An air guide head 47 is installed at one end of the hot air pipe 45, facing the interior of the combustion chamber 12, and an air guide plug 48 is installed inside the air guide head 47. One end of the cold air pipe 46 is connected to the internal channel of the main shaft 14, which is further connected to the internal cooling channel of the moving blade 5, thus supplying air to cool the moving blade 5. However; a tangential air inlet 43 is provided on the inner wall of the air inlet seat 41, which is connected to the air guide pipe 42, so that the cooling airflow enters the air inlet seat 41 tangentially to form a vortex; one end of the air guide plug 48 is fixedly provided with an air-blocking protrusion 482, and an air guide hole 481 is provided on the outer surface of the air-blocking protrusion 482; the other end of the air guide plug 48 is connected to the air guide hole 481 to realize the diversion and guidance of the airflow; an air guide inner seat 44 is installed inside the air inlet seat 41, and a spiral guide groove is provided between the air guide inner seat 44 and the air inlet seat 41; the interior of the air guide inner seat 44 is connected to the interior of the cold air pipe 46 to enhance the heat exchange effect of the airflow rotation. As can be seen from the above description, the present invention has the following beneficial effects: Compressed air is guided by the air guide shroud 32, introduced by the air inlet 33, and transported by the air guide pipe 42. It enters the air inlet seat 41 tangentially along the tangential air inlet 43 and cooperates with the inner air guide seat 44 to form a high-speed vortex. Through energy exchange, the central low-temperature airflow and the peripheral high-temperature airflow are automatically separated. The low-temperature airflow is introduced into the moving blade 5 through the cooling pipe 46 and the internal channel of the main shaft 14, which is specifically used for blade cooling. Compared with the traditional cooling method of directly introducing compressed air, the cooling temperature is lower and the cooling efficiency is higher, which fundamentally improves the problem of poor traditional air cooling effect.

[0023] Further reading is available. Figure 1-8 The moving blade 5 includes a moving blade body 51 and a trapezoidal connecting seat 52. The moving blade body 51 is fixedly installed at the end of the main shaft 14 through the trapezoidal connecting seat 52. A cooling air passage 54 is opened inside the moving blade body 51, and an air intake passage 53 is opened inside the trapezoidal connecting seat 52. One end of the air intake passage 53 is connected to the internal passage of the main shaft 14, and one end of the cooling air passage 54 is connected to the other end of the air intake passage 53. A top air film hole 57 is opened at the end of the moving blade body 51, and the other end of the cooling air passage 54 is connected to the top air film hole 57. An end air film hole 55 is opened on the front end face of the moving blade body 51, and a tangential air film hole 56 is opened on the side cut surface. Both the end air film hole 55 and the tangential air film hole 56 are connected to the cooling air passage 54. A ceramic film 58 is provided on the surface of the moving blade body 51 to improve heat insulation and high-temperature oxidation resistance.

[0024] Using the above technical solution, the cooling airflow enters the moving blade body 51 through the internal channel of the main shaft 14 and the air intake channel 53 of the trapezoidal connecting seat 52. It fully exchanges heat in the cooling air passage 54 and then exits through the end air film hole 55, the tangential air film hole 56 and the top air film hole 57, forming a complete and continuous low temperature air film on the surface of the moving blade body 51. This effectively isolates the high temperature combustion gas from scouring. Combined with the ceramic film 58 on the surface of the moving blade body 51, it significantly reduces the heat load on the blade and improves its high temperature resistance and thermal fatigue resistance.

[0025] Example 2: Please see Figures 1 to 3As shown, based on Embodiment 1, the present invention provides a technical solution: the fixed blade cooling mechanism 2 includes a steam pump 25, which is installed inside the compressor 11 to drive the cooling medium to circulate. The steam pump 25 is connected to the stationary blade 6 through a pipe assembly to form a closed-loop cooling circuit, thereby achieving continuous and efficient cooling of the stationary blade 6. The pipe assembly includes a heat absorption pipe 23, an external pipe 24, a heat conduction pipe 22, and a heat dissipation pipe 21. The heat absorption pipe 23 is arranged on the inner wall of the combustion chamber 12, and the external pipe 24 is arranged on the inner wall of the combustion chamber 12. The heat dissipation pipe 21 is arranged on the inner wall of the compressor 11, and the heat conduction pipe 22 is arranged on the outer side of the compressor 11. One end of the heat absorption pipe 23 is connected to the stationary blade 6, and one end of the heat conduction pipe 22 is connected to the other end of the heat absorption pipe 23 via the steam pump 25. The other end of the heat conduction pipe 22 is connected to one end of the heat dissipation pipe 21, and the other end of the heat dissipation pipe 21 is connected to one end of the external pipe 24. The other end of the external pipe 24 is connected to the stationary blade 6. A heat conduction plate 26 is fixedly installed between the heat conduction pipe 22 and the heat dissipation pipe 21 to enhance the heat dissipation efficiency. Further reading is available. Figure 1-5 The stationary blade 6 includes a stationary blade body 61, with a mounting base 62 fixedly installed at one end of the stationary blade body 61. The stationary blade body 61 is fixedly installed on the inner wall of the turbine chamber 13 through the mounting base 62. An inlet 63 and an outlet 65 are provided on the inner side of the mounting base 62. A flow-guiding heat absorption cavity 64 is provided inside the stationary blade body 61. The two ends of the flow-guiding heat absorption cavity 64 are connected to the inlet 63 and the outlet 65, respectively. The inlet 63 is connected to one end of the external pipe 24, and the flow-guiding heat absorption cavity 64 is connected to one end of the heat absorption pipe 23. A heat insulation film 66 is provided on the surface of the stationary blade body 61 to further reduce the thermal impact of high-temperature combustion gas on the blade body.

[0026] Using the above technical solution, the stationary blade 6 is driven by the steam pump 25 of the fixed blade cooling mechanism 2 for closed-loop cooling. The steam flows continuously in the heat absorption chamber 64 inside the stationary blade body 61, which has strong heat exchange capacity and uniform cooling. This avoids the defects of traditional air cooling flow fluctuation and uneven cooling, ensuring the long-term stable operation of the stationary blade 6. After absorbing the heat of the stationary blade body 61, the steam flows into the heat absorption pipe 23 through the steam outlet 65, further absorbing the residual heat of the combustion chamber 12 wall. Then, it is pressurized by the steam pump 25 and enters the heat conduction pipe 22. The heat is transferred to the heat dissipation pipe 21 through the heat conduction plate 26. The airflow in the compressor 11 is guided by the airflow groove 27 to sweep across the surface of the heat dissipation pipe 21 to achieve forced air cooling. The cooled steam flows back to the heat absorption chamber 64 through the external pipe 24 and the steam inlet 63, realizing multi-stage heat recovery and reuse. The overall energy consumption is lower and the economy is stronger.

[0027] The working principle and usage process of this invention: During the operation of the gas turbine, the moving blades 5 and stationary blades 6 will rapidly accumulate a large amount of heat under the continuous scouring of high-temperature gas. It is necessary to achieve efficient heat dissipation through a matching cooling device in order to ensure the structural strength and service life of the blades. The cooling process of the moving blade 5: When the moving blade 5 is cooled, the compressed air output from the compressor 11 is gathered and guided by the air guide shroud 32. The airflow enters the air guide pipe 42 through the air inlet 33 on the surface of the air inlet impeller 31, and then enters the interior of the air inlet seat 41 tangentially through the tangential air inlet 43. The airflow in the air inlet seat 41 cooperates with the inner air guide seat 44 to form a high-speed rotating vortex, and flows along the spiral path to the hot air pipe 45, forming a high-speed rotating airflow on the inner wall of the hot air pipe 45. Under the obstruction of the air baffle protrusion 482, the rotating airflow is deflected and flows back to the cold air pipe 46 along the central area of ​​the hot air pipe 45. During this process, the vortex attached to the inner wall of the hot air pipe 45 forms a relatively high-temperature airflow, which is discharged into the combustion chamber 12 through the air guide hole 481 and the air guide plug 48 to participate in combustion. The low-temperature airflow returning to the central cooling pipe 46 enters the internal channel of the main shaft 14 as an effective cooling airflow. The principle is that by compressing air rotating at high speed inside the pipe, the central airflow is cooled down and the peripheral airflow is heated by the conservation of angular momentum and energy exchange, thereby separating the cold air and the hot air. The cooling airflow then enters the moving blade body 51 through the internal channel of the main shaft 14 and the air intake channel 53 in the trapezoidal connecting seat 52. It flows in the cooling air passage 54 and fully absorbs the heat inside the moving blade body 51 to achieve convective cooling. The airflow after absorbing heat is discharged through the end air film hole 55, the tangential air film hole 56 and the top air film hole 57, forming a continuous and stable low-temperature air film on the surface of the moving blade body 51, which isolates the direct impact of high-temperature combustion gas. Combined with the surface ceramic film 58, it further improves the heat insulation and cooling effect. Cooling process of the stationary blades: The stationary blades 6 adopt a closed-loop steam cooling system, with the steam pump 25 providing circulation power to drive the cooling steam to continuously circulate within the pipe assembly and the stationary blades 6. When the steam flows in the heat absorption chamber 64 inside the stationary blade body 61, it absorbs the heat from the stationary blade body 61 and flows into the heat absorption pipe 23 through the steam outlet 65. In the heat absorption pipe 23, it further absorbs the residual heat from the inner wall of the combustion chamber 12, thus achieving heat collection. After absorbing heat and increasing its temperature, the steam is pressurized by the steam pump 25 and enters the heat conduction pipe 22. The heat is then transferred through the heat conduction fins 26 on the heat conduction pipe 22. The airflow is transferred to the heat dissipation pipe 21; the airflow in the compressor 11 is guided by the airflow groove 27 to sweep across the surface of the heat dissipation pipe 21, quickly carrying away the heat on the heat dissipation pipe 21 and the heat conduction plate 26, thereby cooling the circulating steam; the cooled steam flows back to the heat absorption chamber 64 of the stationary blade body 61 through the external pipe 24 and the steam inlet 63, and absorbs the heat of the stationary blade body 61 again to complete the next cycle; the heat insulation film 66 on the surface of the stationary blade body 61 can further block the heat radiation and heat convection of the high-temperature gas, and in conjunction with the steam circulation cooling, achieve stable and efficient cooling of the stationary blade 6.

[0028] It should be noted that, in this document, relational terms such as "first" and "second" are used only to distinguish one entity or operation from another, and do not necessarily require or imply any such actual relationship or order between these entities or operations. Furthermore, the terms "comprising," "including," or any other variations thereof are intended to cover non-exclusive inclusion, such that a process, method, article, or apparatus that comprises a list of elements includes not only those elements but also other elements not expressly listed, or elements inherent to such a process, method, article, or apparatus. Without further limitations, an element defined by the phrase "comprising one..." does not exclude the presence of other identical elements in the process, method, article, or apparatus that includes said element.

[0029] The above description is only used to illustrate the technical solution of the present invention and is not intended to limit it. Any other modifications or equivalent substitutions made by those skilled in the art to the technical solution of the present invention, as long as they do not depart from the spirit and scope of the technical solution of the present invention, should be covered within the scope of the claims of the present invention.

Claims

1. A gas turbine blade cooling device, characterized in that: include: An air intake end (1) is provided with a compressor (11), a combustion chamber (12) and a turbine chamber (13) in sequence at one end of the air intake end (1). A main shaft (14) is provided in the middle of the compressor (11), the combustion chamber (12) and the turbine chamber (13). A stationary blade (6) is provided on the inner wall of the turbine chamber (13). A moving blade (5) is provided at one end of the main shaft (14). The fixed blade cooling mechanism (2) includes a steam pump (25) installed inside the compressor (11) and connected to the stationary blade (6) via a pipe assembly. The moving blade cooling mechanism (3) includes an air intake wheel (31), which is fixedly installed on the outside of the main shaft (14). An air guide shroud (32) is installed on one side of the air intake wheel (31). A vortex mechanism (4) is installed around the air intake wheel (31). An air inlet (33) is provided on the surface of the air intake wheel (31). The air inlet (33) is connected to the vortex mechanism (4). The vortex mechanism (4) includes an air intake seat (41), which is fixedly installed inside the air intake wheel (31). A guide pipe (42) is provided on one side of the air intake seat (41). One end of the guide pipe (42) is connected to the air intake port (33). A hot air pipe (45) and a cold air pipe (46) are respectively installed at both ends of the air intake seat (41). A guide head (47) is installed at one end of the hot air pipe (45). The orientation of the guide head (47) corresponds to the interior of the combustion chamber (12). A guide plug (48) is installed inside the guide head (47). One end of the cold air pipe (46) is connected to the internal channel of the main shaft (14). The internal channel of the main shaft (14) is connected to the interior of the moving blade (5).

2. The gas turbine blade cooling device according to claim 1, characterized in that: The intake wheel (31) is located at one end of the compressor (11), and the air guide shroud (32) is connected to the interior of the compressor (11).

3. The gas turbine blade cooling device according to claim 1, characterized in that: The inner wall of the air inlet seat (41) is provided with a tangential air port (43), which is connected to the air guide pipe (42).

4. The gas turbine blade cooling device according to claim 1, characterized in that: One end of the air guide plug (48) is fixedly installed with an air-blocking protrusion (482), and an air guide hole (481) is opened on the outer surface of the air-blocking protrusion (482). The other end of the air guide plug (48) is connected to the air guide hole (481).

5. A gas turbine blade cooling device according to claim 1, characterized in that: The air inlet seat (41) is equipped with an air guide seat (44), and a spiral guide groove is provided between the air guide seat (44) and the air inlet seat (41). The interior of the air guide seat (44) is connected to the interior of the cold air pipe (46).

6. A gas turbine blade cooling device according to claim 1, characterized in that: The moving blade (5) includes a moving blade body (51) and a trapezoidal connecting seat (52). The moving blade body (51) is installed at one end of the main shaft (14) through the trapezoidal connecting seat (52). A cooling air passage (54) is provided inside the moving blade body (51). An air intake passage (53) is provided inside the trapezoidal connecting seat (52). One end of the air intake passage (53) is connected to the internal passage of the main shaft (14). One end of the cooling air passage (54) is connected to the other end of the air intake passage (53). A top air film hole (57) is provided at the end of the moving blade body (51). The other end of the cooling air passage (54) is connected to the top air film hole (57).

7. A gas turbine blade cooling device according to claim 6, characterized in that: The front end face of the moving blade body (51) is provided with an end air film hole (55), and the side cut surface of the moving blade body (51) is provided with a tangential air film hole (56). The end air film hole (55) and the tangential air film hole (56) are both connected to the cooling air passage (54). The surface of the moving blade body (51) is provided with a ceramic film (58).

8. A gas turbine blade cooling device according to claim 1, characterized in that: The piping assembly includes a heat-absorbing pipe (23), an external pipe (24), a heat-conducting pipe (22), and a heat-dissipating pipe (21). The heat-absorbing pipe (23) is installed on the inner wall of the combustion chamber (12), the external pipe (24) is installed on the outer wall of the combustion chamber (12), the heat-dissipating pipe (21) is installed on the inner wall of the compressor (11), and the heat-conducting pipe (22) is installed on the outer side of the compressor (11). One end of the heat-absorbing pipe (23) is connected to the stationary blade (6), one end of the heat-conducting pipe (22) is connected to the other end of the heat-absorbing pipe (23) through a steam pump (25), the other end of the heat-conducting pipe (22) is connected to one end of the heat-dissipating pipe (21), the other end of the heat-dissipating pipe (21) is connected to one end of the external pipe (24), and the other end of the external pipe (24) is connected to the stationary blade (6). A heat-conducting plate (26) is fixedly installed between the heat-conducting pipe (22) and the heat-dissipating pipe (21).

9. A gas turbine blade cooling device according to claim 8, characterized in that: The stationary blade (6) includes a stationary blade body (61), one end of which is fixedly mounted with a mounting base (62). The stationary blade body (61) is mounted on the inner wall of the turbine chamber (13) via the mounting base (62). The mounting base (62) has an inlet (63) and an outlet (65) on its inner side. The stationary blade body (61) has a flow-guiding heat absorption cavity (64) inside, and the two ends of the flow-guiding heat absorption cavity (64) are connected to the inlet (63) and the outlet (65) respectively.

10. A gas turbine blade cooling device according to claim 9, characterized in that: The steam inlet (63) is connected to one end of the external pipe (24), the heat absorption chamber (64) is connected to one end of the heat absorption pipe (23), and the surface of the stationary blade body (61) is provided with a heat insulation film (66).

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