A gas turbine nozzle-fin compound bleed air structure

Abstract

The application discloses a gas turbine nozzle-fin combined air bleeding structure and belongs to the technical field of aero-engines. The gas turbine nozzle-fin combined air bleeding structure comprises a first-stage disc, a second-stage disc, a first disc cavity and a second disc cavity. A first cavity is arranged below the first disc cavity. A plurality of fins are fixedly arranged in the first cavity. The plurality of fins are uniformly arranged around the central shaft of the first-stage disc. A plurality of nozzle holes are arranged on the inner wall of the first disc cavity. The two ends of the nozzle holes are respectively communicated with the first disc cavity and the first cavity. A communication groove is arranged on the inner wall of the first cavity. The communication groove is used for connecting the first cavity and the second disc cavity. The application has the effects of reducing the wind resistance loss in the compressor, increasing the air flow vortex reduction effect and improving the efficiency of the unit.

Description

Technical Field

[0001] This application relates to the field of aero-engine technology, and in particular to a gas turbine nozzle-fin composite air intake structure. Background Technology

[0002] From a gas turbine design perspective, multi-stage axial-flow compressors, combustion chambers, and multi-stage cooling turbines are key components of heavy-duty gas turbines. The key technologies for axial-flow compressors mainly involve blade aerodynamic design and research; the key technologies for combustion chambers mainly involve the design of combustion characteristics, cooling, and sealing; and the key technologies for multi-stage cooling turbines are comprehensive cooling technologies.

[0003] The compressor includes a first-stage disk and a second-stage disk. The centerlines of the first-stage disk and the second-stage disk are collinear, and an air inlet is provided at the connection between the two disks. Grooves are formed on the opposite sidewalls of the connection between the first-stage disk and the second-stage disk, creating a first disk cavity. A second disk cavity is formed within the second-stage disk. Multiple anti-vortex holes are evenly distributed on the inner wall of the first disk cavity, extending obliquely into the second disk cavity. An air outlet is provided on the inner wall of the second disk cavity near the central axis.

[0004] Regarding the aforementioned technologies, the expansion and contraction of the airflow channels at both ends caused by the anti-vortex orifice to lead to viscous dissipation of the airflow and a small flow area, resulting in increased wind resistance loss and hindering the anti-vortex effect of airflow. Summary of the Invention

[0005] In order to reduce the air resistance loss in the compressor and increase the airflow vortex reduction effect, thereby improving the unit efficiency, this application provides a gas turbine nozzle-fin composite air intake structure.

[0006] The technical solution for the gas turbine nozzle-fin composite air induced draft structure provided in this application is as follows: A gas turbine nozzle-fin composite air intake structure includes a first-stage disk, a second-stage disk, a first disk cavity, and a second disk cavity. A first chamber is formed below the first disk cavity. Multiple fins are fixedly arranged in the first chamber, and the multiple fins are evenly arranged around the central axis of the first-stage disk. Multiple nozzle holes are formed on the inner wall of the first disk cavity, and the two ends of the nozzle holes are respectively connected to the first disk cavity and the first chamber. A connecting groove is formed on the inner wall of the first chamber, and the connecting groove connects the first chamber and the second disk cavity.

[0007] By adopting the above technical solution, the airflow enters the first disc cavity from the air inlet. The airflow in the first disc cavity enters the top space of the first chamber through the nozzle hole. Then, the airflow converges at the connecting slot through the channel between two adjacent fins and flows to the outlet pipe from the connecting slot. During the airflow process, the fins can limit the circumferential velocity of the airflow, suppress the development of free vortices, and reduce flow resistance. At the same time, the fins have a larger flow area than the anti-vortex hole, avoiding sudden widening and narrowing of the flow channel during the air intake process. This reduces viscous dissipation caused by airflow mixing, reduces wind resistance loss, and thus increases the anti-vortex effect of the airflow and improves the unit efficiency.

[0008] Preferably, the nozzle orifice is tilted in the opposite direction.

[0009] By adopting the above technical solution, the inclined setting of the nozzle orifice can increase airflow loss and reduce airflow velocity.

[0010] Preferably, a groove is formed at the end of the fin away from the center of the first-stage disk, and a slider slides in the groove. The opposite side walls of the slider are slidably connected to the opposite inner walls of the first-stage disk, and a driving mechanism for driving the slider to slide is provided in the first-stage disk.

[0011] By adopting the above technical solution, the operator can adjust the position of the slider through the drive mechanism, thereby adjusting the distance between the fins and the nozzle orifice. By adjusting the distance between the fins and the nozzle orifice, the operator can adjust the airflow speed at the fin inlet, and thus adjust the swirl ratio.

[0012] Preferably, the drive mechanism includes multiple ropes and multiple springs, with each rope corresponding to one of the multiple fins. One end of each rope is fixedly connected to the slider. The two ends of each spring are fixedly connected to the slider and the inner wall of the groove, respectively. The drive mechanism also includes a drive assembly for simultaneously tightening or releasing the multiple ropes.

[0013] By adopting the above technical solution, when the slider is completely in the groove, the rope tightens and pulls the slider into the groove to compress the spring. When it is necessary to extend the fin length, the operator releases the tension of multiple ropes at the same time through the drive component. At this time, the slider in each fin moves away from the groove under the elastic force of the spring, thereby extending the length of all fins in the first chamber.

[0014] Preferably, the first-stage disk has a placement slot, and the drive assembly is disposed in the placement slot. The drive assembly includes a ring disk, multiple rotating rods, multiple first gears, a second gear, and a rotating cylinder. The ring disk is fixedly connected to the inner wall of the placement slot. Multiple rope holes are evenly provided on the end face of the ring disk. Multiple ropes correspond one-to-one with multiple rope holes, and the ropes pass through the side wall of the fin and then through the rope holes. The number of rotating rods, rope holes, and first gears are equal. The rotating rods are rotatably connected to the end face of the ring disk. The first gears are fixedly sleeved on the end of the rotating rod away from the ring disk. The rope is wound around the rotating rod. One end of the rotating cylinder is rotatably connected to the end face of the ring disk. The other end of the rotating cylinder rotates and passes through the end face of the first-stage disk. The second gear is fixedly sleeved on the end of the rotating cylinder near the ring disk. The second gear meshes with the multiple first gears. The drive mechanism also includes a fixing component for fixing the rotating cylinder.

[0015] By adopting the above technical solution, when the worker needs to tighten or release the rope, the worker first releases the fixed restriction of the rotating drum, and then the worker rotates the rotating drum. The rotation of the rotating drum drives the second gear to rotate, the rotation of the second gear drives multiple first gears to rotate simultaneously, the rotation of the first gears drives the rotating rod to rotate, and the rotation of the rotating rod drives the rope to wind or release.

[0016] Preferably, the fixing assembly includes a first ratchet, a second ratchet, a first pawl, and a second pawl. A placement groove is provided on the outer side of the first stage disc. The first ratchet and the second ratchet rotate within the placement groove. The first ratchet and the second ratchet are fixedly sleeved on the peripheral side wall of the rotating cylinder at the end away from the second gear. Connecting rods are fixedly connected to the inner walls on both sides of the rotating cylinder within the placement groove. The first pawl and the second pawl are respectively sleeved on the connecting rods on both sides and rotate on them. A torsion spring is sleeved on each of the two connecting rods. The two ends of the torsion spring are fixedly connected to the connecting rod and the first pawl, respectively. The first pawl engages with the first ratchet, and the second pawl engages with the second ratchet; a first abutting block is fixedly connected to the side wall of the first pawl, and the first abutting block abuts against the inner wall of the placement groove; a second abutting block is fixedly connected to the side wall of the second pawl, and the second abutting block abuts against the placement groove; two sets of control components are provided on the first stage disk, and the two sets of control components can respectively control the engagement state of the first pawl and the second pawl.

[0017] By adopting the above technical solution, when the worker needs to rotate the drum to drive the rope release, the worker releases the control component of the first pawl, causing the first pawl to engage with the first ratchet. Under the action of the control component, the second pawl moves away from the second ratchet. Then, the worker rotates the drum, which drives the rotating rod to rotate and release the rope, while reducing the possibility of the drum reversing. When the worker needs to tighten the rope, the worker uses the control component to move the first pawl away from the first ratchet, and the second pawl engages with the second ratchet. At this time, the worker rotates the drum to drive the rotating rod to rotate and wind more rope, tightening the rope, while reducing the possibility of the drum reversing. After the worker adjusts the length of the fins, the worker releases both sets of control components, causing the first pawl to engage with the first ratchet and the second pawl to engage with the second ratchet. At this time, the position of the drum is limited, thereby reducing the possibility of changes in rope tension.

[0018] Preferably, the control component includes a fixed rod and a loop, the fixed rod is fixedly connected to the first stage disc, one end of the loop is fixedly connected to the first pawl, and the other end of the loop is provided with a loop, which is fitted onto the fixed rod.

[0019] By adopting the above technical solution, when the worker needs to move the first pawl away from the first ratchet, the worker pulls the loop and puts the loop on the loop onto the fixed rod. When the loop is pulled, the first pawl moves with the loop, thus moving away from the first ratchet. When the first pawl needs to engage with the first ratchet, the worker removes the loop from the fixed rod, and the first pawl resets under the action of the torsion spring inside.

[0020] Preferably, the inner wall of the chute is provided with a storage groove, and a fixed pulley is fixedly connected in the storage groove, with the rope wound around the fixed pulley.

[0021] By adopting the above technical solution, the fixed pulley can change the direction of the rope and the direction of the force on the rope, which makes it easier for the rope to drive the slider to move.

[0022] Preferably, the rope is fitted with a protective sleeve.

[0023] By adopting the above technical solution, the protective sleeve can reduce the friction force on the rope during movement, thereby reducing the wear and tear of the rope.

[0024] Preferably, the spring is fitted with a telescopic rod, and the two ends of the telescopic rod are respectively fixedly connected to the slider and the inner wall of the groove.

[0025] By adopting the above technical solution, when the spring is compressed, the telescopic rod is compressed accordingly, which can reduce the possibility of the spring bending and being damaged.

[0026] In summary, this application includes at least one of the following beneficial technical effects: 1. Airflow enters the first disc cavity through the air inlet. The airflow in the first disc cavity enters the top space of the first chamber through the nozzle orifice. Then, the airflow converges at the connecting slot through the channel between two adjacent fins and flows to the outlet pipe from the connecting slot. During the airflow process, the fins can limit the circumferential velocity of the airflow, suppress the development of free vortices, and reduce flow resistance. At the same time, the fins have a larger flow area than the anti-vortex orifice, which avoids the sudden widening and narrowing of the flow channel during the air intake process, thereby reducing viscous dissipation caused by airflow mixing, reducing wind resistance loss, and thus increasing the anti-vortex effect of the airflow and improving the unit efficiency. 2. Tilting the nozzle orifice increases airflow loss and reduces airflow velocity; 3. The operator can adjust the position of the slider through the drive mechanism, thereby adjusting the distance between the fins and the nozzle orifice. By adjusting the distance between the fins and the nozzle orifice, the operator can adjust the airflow speed at the fin inlet, and thus adjust the swirl ratio. Attached Figure Description

[0027] Figure 1 This is a schematic diagram of a gas turbine nozzle-fin composite air intake structure.

[0028] Figure 2 These are cross-sectional views of the first-level disk and the second-level disk in Embodiment 1 of this application.

[0029] Figure 3 This is a schematic diagram of the protruding nozzle hole structure in Embodiment 1 of this application.

[0030] Figure 4 These are cross-sectional views of the first-level disk and the second-level disk in Embodiment 2 of this application.

[0031] Figure 5 This is a structural schematic diagram of the prominent fixing component in Embodiment 2 of this application.

[0032] Explanation of reference numerals in the attached figures: 1. First-stage disc; 2. Second-stage disc; 3. First disc cavity; 4. Second disc cavity; 5. Air inlet; 6. Air outlet; 7. First chamber; 8. Fin; 9. Nozzle orifice; 10. Connecting groove; 11. Slide groove; 12. Slider; 13. Drive mechanism; 14. Rope; 15. Spring; 16. Drive assembly; 17. Placement groove; 18. Ring disc; 19. Rotating rod; 20. First gear; 21. Second gear; 22. 23. Rotary drum; 24. Rope threading hole; 25. Fixing component; 26. First ratchet; 27. First pawl; 28. Second pawl; 29. ​​Placement slot; 30. Control component; 31. Connecting rod; 32. Torsion spring; 33. Fixing rod; 34. Rope loop; 35. Storage slot; 36. Fixed pulley; 37. Protective sleeve; 38. Telescopic rod; 39. Second ratchet; 40. First stop block; 41. Second stop block. Detailed Implementation

[0033] The following is in conjunction with the appendix Figure 1-5 This application will be described in further detail.

[0034] This application discloses a gas turbine nozzle-fin composite air intake structure.

[0035] Implementation 1 like Figure 1 and Figure 2 As shown, it includes a first-stage disk 1, a second-stage disk 2, a first disk cavity 3, and a second disk cavity 4. The first disk cavity 3 is annular in shape, and a first chamber 7 is opened downstream of the first disk cavity 3. The first chamber 7 is circular in shape, and multiple fins 8 are fixedly arranged inside the first chamber 7. The multiple fins 8 have the same structure and are all cuboid in shape. The multiple fins 8 are evenly arranged around the central axis of the first-stage disk 1, and the two side walls of the fins 8 are fixedly welded to the opposite inner walls of the first chamber 7.

[0036] like Figure 2 and Figure 3 As shown, a plurality of nozzle holes 9 are evenly distributed on the inner wall of the annular bottom of the first disk cavity 3. The nozzle holes 9 extend radially along the first disk cavity 3, and the plurality of nozzle holes 9 correspond to a plurality of fins 8. The nozzle holes 9 are inclined in the opposite direction, with the upper end of the nozzle hole 9 connected to the first disk cavity 3 and the lower end of the nozzle hole 9 connected to the first chamber 7. The inverted arrangement of the nozzle holes 9 can increase airflow loss and reduce airflow velocity. A connecting groove 10 is provided in the second stage disk 2. The connecting groove 10 is located near the central axis of the second stage disk 2 and extends along the central axis. The two ends of the connecting groove 10 are connected to the air outlet 6 and the first chamber 7, respectively.

[0037] The implementation principle of Embodiment 1 of this application is as follows: When the compressor rotates, the airflow enters the first disc cavity 3 from the air inlet 5. The airflow in the first disc cavity 3 enters the top space of the first chamber 7 from the nozzle hole 9. Then, the airflow converges towards the central axis through the channel between two adjacent fins 8, and finally flows to the outlet pipe from the connecting groove 10. During the airflow process, the fins 8 can limit the circumferential velocity of the airflow, suppress the development of free vortices, and reduce flow resistance. At the same time, the fins 8 have a larger flow area than the anti-vortex hole, which avoids the sudden widening and contraction of the flow channel during the air intake process, thereby reducing the viscous dissipation caused by airflow mixing, reducing wind resistance loss, and thus increasing the anti-vortex effect of the airflow and improving the unit efficiency.

[0038] Example 2 like Figure 4 As shown, a groove 11 is provided at the end of the fin 8 away from the center of the first-stage disk 1. The groove 11 extends along the length of the fin 8. A slider 12 slides within the groove 11. The slider 12 is cuboid in shape, and its left and right opposite sidewalls are slidably connected to the opposite inner walls of the first-stage disk 1. A drive mechanism 13 is provided within the first-stage disk 1 to drive the slider 12 to slide. The operator can adjust the position of the slider 12 through the drive mechanism 13, thereby adjusting the distance between the fin 8 and the nozzle orifice 9. By adjusting the distance between the fin 8 and the nozzle orifice 9, the operator can adjust the airflow velocity at the inlet of the fin 8, and thus adjust the swirl ratio. Furthermore, the maximum extent to which the slider 12 is completely within the groove 11 is such that the top of the slider 12 is flush with the top of the fin 8, thereby preventing airflow from entering the groove 11; when the slider 12 moves into the groove 11 and extends the length of the fin 8, the two side walls of the slider 12 slide against the relative inner walls of the first chamber 7, thereby reducing the possibility of airflow flowing between the slider 12 and the inner wall of the first chamber 7.

[0039] like Figure 4 As shown, the drive mechanism 13 includes multiple ropes 14 and multiple springs 15. The number of ropes 14 is the same as the number of fins 8, and one rope 14 is connected to each fin 8. The ropes 14 are non-elastic, and one end of each rope 14 is fixedly embedded in the end of the slider 12 near the center of the first chamber 7. A storage groove 35 is vertically formed on the inner wall of the bottom of the slide groove 11. A fixed pulley 36 is installed in the storage groove 35. The ropes 14 are wound around the side wall of the fixed pulley 36. The fixed pulley 36 can change the direction of the ropes 14 and the direction of the force on the ropes 14, thereby making it easier for the ropes 14 to drive the slider 12 to move. In this embodiment, two springs 15 are installed in each slide groove 11. The two ends of the springs 15 are fixedly welded to the slider 12 and the inner wall of the slide groove 11, respectively. A telescopic rod 38 is sleeved inside the springs 15. The two ends of the telescopic rod 38 are fixedly welded to the lower end face of the slider 12 and the inner wall of the bottom of the slide groove 11, respectively. When the springs 15 are compressed, the telescopic rod 38 is compressed accordingly, which can reduce the possibility of the springs 15 bending and being damaged.

[0040] like Figure 4 As shown, a placement groove 17 is provided at the end of the first-stage disk 1 away from the second-stage disk 2. The placement groove 17 is annular. The drive mechanism 13 also includes a drive assembly 16 that drives multiple ropes 14 to tighten or release simultaneously. The drive assembly 16 is disposed in the placement groove 17. The drive assembly 16 includes a ring disk 18, multiple rotating rods 19, multiple first gears 20, a second gear 21, and a rotating cylinder 22. The ring disk 18 is annular, and the center of the ring disk 18 is on the same axis as the center of the first-stage disk 1. One end face of the ring disk 18 is fixedly welded to the inner wall of the placement groove 17. Multiple rope holes 23 are evenly provided on the end face of the ring disk 18. The multiple rope holes 23 form a circle. The number of multiple ropes 14 is the same as the number of rope holes 23, and the multiple ropes 14 are threaded through the multiple rope holes 23 in a one-to-one correspondence. The portion of the rope 14 that passes through the fin 8 is fitted with a protective cover 37. The protective cover 37 can reduce the friction force on the rope 14 during movement, thereby reducing the wear and tear of the rope 14.

[0041] like Figure 4 As shown, there are an equal number of rotating rods 19, multiple rope holes 23, and multiple first gears 20. The rotating rods 19 are cylindrical and their axis is set in the horizontal direction. The rotating rods 19 are rotatably connected to the end face of the ring disk 18 and are located next to the corresponding rope holes 23. The first gears 20 are fixedly sleeved on the end of the rotating rod 19 away from the ring disk 18. The rope 14 is wrapped around the side wall of the rotating rod 19. The left end of the rotating cylinder 22 is rotatably connected to the right end face of the ring disk 18. The right end of the rotating cylinder 22 rotates and passes through the end face of the first stage disk 1. The second gear 21 is fixedly sleeved on the end of the rotating cylinder 22 near the ring disk 18. The second gear 21 meshes with multiple first gears 20. The drive mechanism 13 also includes a fixing component 24 for fixing the rotating cylinder 22.

[0042] like Figure 4 and Figure 5 As shown, the fixing component 24 includes a first ratchet 25, a second ratchet 39, a first pawl 26, and a second pawl 27. A placement groove 28 is provided on the outer wall of the first stage disc 1 in the horizontal direction. The first ratchet 25 and the second ratchet 39 both rotate in the placement groove 28, and the teeth of the first ratchet 25 and the second ratchet 39 are in opposite directions. The first ratchet 25 and the second ratchet 39 are both fixedly sleeved on the side wall of the rotating cylinder 22 away from the ring disc 18. The first pawl 26 and the second pawl 27 are distributed on both sides of the rotating cylinder 22. The first ratchet 25 meshes with the first pawl 26, and the second ratchet 39 meshes with the second pawl 27. Two sets of control components 29 are provided on the outer wall of the first stage disc 1. The two sets of control components 29 can control the meshing state of the first pawl 26 and the second pawl 27 respectively.

[0043] like Figure 5As shown, two connecting rods 30 are fixedly welded to the inner wall of the placement groove 28. The connecting rods 30 are cylindrical, and their axes extend horizontally. A first pawl 26 and a second pawl 27 are respectively fitted and rotated on the two connecting rods 30. A torsion spring 31 is fitted on each of the two connecting rods 30, and the two ends of the torsion spring 31 are fixedly welded to the connecting rod 30 and the first pawl 26, respectively. The control component 29 includes a fixed rod 32 and a loop 33. The fixed rod 32 is fixedly welded to the side wall of the first stage disc 1. One end of the loop 33 is fixedly embedded in the first pawl 26, and the other end of the loop 33 is provided with a collar 34, which is fitted onto the fixed rod 32.

[0044] like Figure 4 and Figure 5 As shown, when the fin 8 is at its shortest length, the slider 12 is completely within the groove 11, with the top of the slider 12 flush with the top of the fin 8. Simultaneously, the rope 14 is tightened, pulling the slider 12 into the groove 11 to compress the spring 15, which is then compressed. When adjusting the distance between the fin 8 and the nozzle hole 9 to extend the fin 8 length, the operator first releases the bidirectional locking restriction of the rotating drum 22. The operator then pulls the loop 33 on the second pawl 27, placing the loop 34 onto the fixing rod 32 beside the second pawl 27, thus moving the second pawl 27 away from the second ratchet 39. At this time, the first pawl 26 engages with the first ratchet 25, and a first stop block 40 is fixedly welded to the side wall of the first pawl 26. The first stop block 40 can abut against the inner wall of the placement groove 28, thereby limiting the unidirectional rotation of the first ratchet 25. The operator rotates the drum 22 clockwise. The rotation of the drum 22 drives the second gear 21 to rotate clockwise. The rotation of the second gear 21 drives multiple first gears 20 to rotate. The rotation of the first gears 20 drives the rotating rod 19 to rotate and releases the rope 14. The slider 12 moves out of the slide groove 11 under the elastic force of the spring 15, thereby increasing the length of the fin 8.

[0045] like Figure 4 and Figure 5As shown, when the operator needs to shorten the length of the fin 8, the operator removes the rope 33 from the fixed rod 32 on the second pawl 27 and places the rope 33 on the fixed rod 32 next to the first pawl 26, so that the first pawl 26 is away from the first ratchet 25, and the second pawl 27 engages with the second ratchet 39. Then, the operator rotates the drum 22 counterclockwise, which drives the second gear 21 to rotate counterclockwise. The second gear 21 drives multiple first gears 20 to rotate, causing the rotating rod 19 to wind and tighten the rope 14. The rope 14 pulls the slider 12 into the groove 11, thereby reducing the length of the fin 8. A second stop block 41 is fixedly welded to the side wall of the second pawl 27. The second stop block 41 can abut against the inner wall of the placement groove 28, thus preventing the operator from reversing the rotation when rotating the drum 22. After the staff adjusts the length of the fin 8, they release the ropes 33 on the two fixing rods 32, so that the first pawl 26 engages with the first ratchet 25 and the second pawl 27 engages with the second ratchet 39, thereby limiting the position of the rotating drum 22 and reducing the possibility of changes in the tension of the rope 14.

[0046] The implementation principle of Embodiment 2 of this application is as follows: A sliding groove 11 is provided on the fin 8, and a slider 12 slides in the sliding groove 11. The slider 12 slides on the inner wall of the first chamber 7. The operator can adjust the position of the slider 12 through the drive mechanism 13, thereby adjusting the distance between the fin 8 and the nozzle hole 9. The operator can adjust the airflow speed at the inlet of the fin 8 by adjusting the distance between the fin 8 and the nozzle hole 9, thereby adjusting the swirl ratio.

[0047] The above are all preferred embodiments of this application, and are not intended to limit the scope of protection of this application. Therefore, all equivalent changes made in accordance with the structure, shape and principle of this application should be covered within the scope of protection of this application.

Claims

1. A gas turbine nozzle-fin composite air intake structure, comprising a first-stage disk (1), a second-stage disk (2), a first disk cavity (3), and a second disk cavity (4), characterized in that: A first chamber (7) is provided below the first disk cavity (3), and a plurality of fins (8) are fixedly arranged in the first chamber (7). The plurality of fins (8) are evenly arranged around the central axis of the first disk (1). A plurality of nozzle holes (9) are provided on the inner wall of the first disk cavity (3), and the two ends of the nozzle holes (9) are respectively connected to the first disk cavity (3) and the first chamber (7). A connecting groove (10) is provided on the inner wall of the first chamber (7), and the connecting groove (10) connects the first chamber (7) with the second disk cavity (4). The fin (8) has a groove (11) at one end away from the center of the first stage disk (1). A slider (12) slides in the groove (11). The opposite side walls of the slider (12) are slidably connected to the opposite inner walls of the first stage disk (1). A driving mechanism (13) for driving the slider (12) to slide is provided in the first stage disk (1). The drive mechanism (13) includes multiple ropes (14) and multiple springs (15). The multiple ropes (14) are arranged in a one-to-one correspondence with the multiple fins (8). One end of each rope (14) is fixedly connected to the slider (12). The two ends of each spring (15) are fixedly connected to the inner wall of the slider (12) and the groove (11), respectively. The drive mechanism (13) also includes a drive assembly (16) for simultaneously tightening or releasing the multiple ropes (14).

2. The gas turbine nozzle-fin composite air intake structure according to claim 1, characterized in that: The nozzle orifice (9) is tilted in the opposite direction.

3. The gas turbine nozzle-fin composite air intake structure according to claim 1, characterized in that: The first-stage disk (1) has a placement slot (17) and the drive assembly (16) is disposed in the placement slot (17). The drive assembly (16) includes a ring disk (18), multiple rotating rods (19), multiple first gears (20), a second gear (21), and a rotating cylinder (22). The ring disk (18) is fixedly connected to the inner wall of the placement slot (17). Multiple rope holes (23) are evenly provided on the end face of the ring disk (18). Multiple ropes (14) correspond one-to-one with multiple rope holes (23). The ropes (14) pass through the side wall of the fin (8) and then through the rope holes (23). The number of the plurality of rotating rods (19), the plurality of rope holes (23), and the plurality of first gears (20) are equal. The rotating rods (19) are rotatably connected to the end face of the ring disk (18). The first gears (20) are fixedly sleeved on the end of the rotating rods (19) away from the ring disk (18). The rope (14) is wound around the rotating rods (19). One end of the rotating cylinder (22) is rotatably connected to the end face of the ring disk (18). The other end of the rotating cylinder (22) rotates and passes through the end face of the first stage disk (1). The second gear (21) is fixedly sleeved on the end of the rotating cylinder (22) near the ring disk (18). The second gear (21) meshes with the plurality of first gears (20). The drive mechanism (13) also includes a fixing component (24) for fixing the rotating cylinder (22).

4. The gas turbine nozzle-fin composite air intake structure according to claim 3, characterized in that: The fixing component (24) includes a first ratchet (25), a second ratchet (39), a first pawl (26), and a second pawl (27). A placement groove (28) is provided on the outer side of the first stage disc (1). The first ratchet (25) and the second ratchet (39) both rotate within the placement groove (28). The first ratchet (25) and the second ratchet (39) are both fixedly sleeved on the peripheral side wall of the rotating cylinder (22) away from the second gear (21). Connecting rods (30) are fixedly connected to the inner walls on both sides of the rotating cylinder (22) within the placement groove (28). The first pawl (26) and the second pawl (27) are respectively sleeved and rotated on the connecting rods (30) on both sides. A torsion spring (31) is sleeved on each of the two connecting rods (30). The two ends of the torsion spring (31) are fixedly connected to the connecting rod (30) and the first pawl (26) respectively. The first pawl (26) engages with the first ratchet (25), and the second pawl (27) engages with the second ratchet (39); a first stop block (40) is fixedly connected to the side wall of the first pawl (26), and the first stop block (40) abuts against the inner wall of the placement groove (28); a second stop block (41) is fixedly connected to the side wall of the second pawl (27), and the second stop block (41) abuts against the placement groove (28); two sets of control components (29) are provided on the first stage disc (1), and the two sets of control components (29) can respectively control the engagement state of the first pawl (26) and the second pawl (27).

5. The gas turbine nozzle-fin composite air intake structure according to claim 4, characterized in that: The control component (29) includes a fixed rod (32) and a loop (33). The fixed rod (32) is fixedly connected to the first stage disc (1). One end of the loop (33) is fixedly connected to the first pawl (26). The other end of the loop (33) is provided with a collar (34), which is fitted onto the fixed rod (32).

6. The gas turbine nozzle-fin composite air intake structure according to claim 1, characterized in that: The inner wall of the chute (11) is provided with a storage groove (35), and a fixed pulley (36) is fixedly connected in the storage groove (35). The rope (14) is wound around the fixed pulley (36).

7. The gas turbine nozzle-fin composite air intake structure according to claim 1, characterized in that: The rope (14) is fitted with a protective sleeve (37).

8. The gas turbine nozzle-fin composite air intake structure according to claim 1, characterized in that: The spring (15) is fitted with a telescopic rod (38), and the two ends of the telescopic rod (38) are respectively fixedly connected to the slider (12) and the inner wall of the groove (11).

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