Air system for power turbine rotor of small and medium-sized gas turbine

Abstract

A small and medium-sized gas turbine power turbine rotor air system relates to the technical field of gas turbines. The problems that an existing gas turbine with a power turbine needs to bleed air from different positions of an air compressor, so that the using amount of cooling air is large, and the cooling efficiency is low are solved. The gas turbine comprises a front wall, a main flow gas channel, a first-stage turbine wheel disc, a rear wall and a shaft cavity, a first cavity is formed between the first-stage turbine wheel disc and the front wall, the first cavity and the shaft cavity communicate with a gas compressor at the same time, and the first cavity communicates with the main flow gas channel through a first gas outlet, a second gas outlet and a third gas outlet; only one strand of compressed air is led out from a certain part of the air compressor, one part of the compressed air flows into the first cavity, the other part of the compressed air flows into the shaft cavity and converges into the mainstream fuel gas channel after passing through the multi-stage blades, and the compressed air is shunted, so that the effects of cooling the wheel disc, sealing the disc cavity and sealing and pressurizing the bearing cavity can be completed, and the cold air consumption can be saved; the gas turbine unit efficiency is improved.

Description

Technical Field

[0001] The present invention relates to the technical field of gas turbines, and particularly to an air system for a power turbine rotor of a medium and small-sized gas turbine. Background Art

[0002] For a gas turbine with a power turbine, the disk of the power turbine rotor needs to be cooled. At the same time, it is necessary to seal between the power turbine disk and the stationary parts to prevent the backflow of gas, and it is necessary to seal and pressurize the air in the front cavity of the bearing to prevent the leakage of lubricating oil.

[0003] To achieve the above functions, the internal air system of the power turbine rotor, especially for a multi-stage power turbine, generally needs to bleed air from different positions of the compressor, resulting in a complex structure of the internal air system of the rotor, a large amount of cooling air consumption, and low cooling efficiency.

[0004] In summary, the existing gas turbines with power turbines have the problem that they need to bleed air from different positions of the compressor, resulting in a large amount of cooling air consumption and low cooling efficiency. Summary of the Invention

[0005] The purpose of the present invention is to solve the problem that the existing gas turbines with power turbines need to bleed air from different positions of the compressor, resulting in a large amount of cooling air consumption and low cooling efficiency. Furthermore, an air system for a power turbine rotor of a medium and small-sized gas turbine is provided.

[0006] The technical solution of the present invention is: an air system for a power turbine rotor of a medium and small-sized gas turbine, including: a front wall, a mainstream gas passage, a first-stage turbine disk, a rear wall, and a shaft cavity. A first chamber is formed between the first-stage turbine disk and the front wall;

[0007] The first chamber and the shaft cavity are both connected to the compressor;

[0008] The first chamber is connected to the mainstream gas passage through a first air outlet, a second air outlet, and a third air outlet. The first air outlet is arranged between the first-stage moving blade and the first flange, the second air outlet is arranged between the first-stage moving blade and the first partition, and the third air outlet is arranged between the second-stage moving blade and the second flange;

[0009] The shaft cavity is connected to the mainstream gas passage through a fourth air outlet, a fifth air outlet, a sixth air outlet, a seventh air outlet, and an eighth air outlet. The fourth air outlet is arranged between the second-stage moving blade and the second partition, the fifth air outlet is arranged between the third flange and the third-stage moving blade, the sixth air outlet is arranged between the third-stage moving blade and the third partition, the seventh air outlet is arranged between the fourth-stage moving blade and the fourth flange, and the eighth air outlet is arranged between the fourth-stage moving blade and the rear wall.

[0010] Further, a second chamber is formed between the first-stage turbine disk and the first flange. One end of the second chamber communicates with the first chamber through a first-stage gap channel, and the other end of the second chamber communicates with the mainstream gas channel through the first gas outlet.

[0011] Further, a third chamber is formed among the first-stage turbine disk, the second-stage turbine disk and the spacer. The third chamber communicates with the first chamber through the disk holes on the first-stage turbine disk;

[0012] A fourth chamber is formed among the first-stage turbine disk, the first partition plate and the spacer. One end of the fourth chamber communicates with the third chamber through the radial holes on the spacer, and the other end of the fourth chamber communicates with the mainstream gas channel through the second gas outlet.

[0013] Further, a fifth chamber is formed among the first partition plate, the second flange, the second-stage turbine disk and the spacer. One end of the fifth chamber communicates with the fourth chamber through a first-stage sealing structure, and the other end of the fifth chamber communicates with the mainstream gas channel through the third gas outlet. The first-stage sealing structure is located between the first partition plate and the first labyrinth insert.

[0014] Further, a sixth chamber is formed between the second-stage turbine disk and the shaft rod. One end of the sixth chamber communicates with the shaft cavity through the left-side holes on the shaft rod, and the other end of the sixth chamber communicates with a seventh chamber through the gap between the shaft rod and the second-stage turbine disk;

[0015] A seventh chamber is formed between the second partition plate and the second-stage turbine disk. The seventh chamber communicates with the mainstream gas channel through the fourth gas outlet.

[0016] Further, an eighth chamber is formed in front of the third-stage turbine disk. One end of the eighth chamber communicates with the seventh chamber through a second sealing structure, and the other end of the eighth chamber communicates with the mainstream gas channel through the fifth gas outlet. The second sealing structure is located between the second partition plate and the first gas seal.

[0017] Further, a ninth chamber is formed between the lower part of the third-stage turbine disk and the fourth-stage turbine disk. One end of the ninth chamber communicates with the eighth chamber through the lower holes on the third-stage turbine disk, and the other end of the ninth chamber communicates with a tenth chamber through the upper holes on the third-stage turbine disk;

[0018] A tenth chamber is formed between the third-stage turbine disk and the third partition plate. The tenth chamber communicates with the mainstream gas channel through the sixth gas outlet.

[0019] Further, an eleventh chamber is formed between the four-stage turbine disk and the third partition. One end of the eleventh chamber communicates with the tenth chamber through a third sealing structure, and the other end of the eleventh chamber communicates with the mainstream gas passage through a seventh air outlet.

[0020] Further, a twelfth chamber is formed among the four-stage turbine disk, the rear wall, the ear seat, the baffle plate and the disk shaft coupling ring. One end of the twelfth chamber communicates with the shaft chamber through a right-side hole on the shaft rod, and the other end of the twelfth chamber communicates with a thirteenth chamber through a gap between the disk and the rear wall;

[0021] A thirteenth chamber is formed between the upper part of the four-stage turbine disk and the rear wall, and the thirteenth chamber communicates with the mainstream gas passage through an eighth air outlet.

[0022] The present invention has the following effects compared with the prior art:

[0023] 1. The small and medium-sized gas turbine power turbine rotor air system provided by the present invention only draws a single stream of compressed air from a certain part of the compressor. Part of the compressed air flows into the first chamber, and the other part flows into the shaft chamber. After passing through multiple stages of blades, it converges into the mainstream gas passage. Through the diversion of the compressed air, it can not only complete the functions of cooling the disk, sealing the disk cavity and pressurizing the bearing cavity seal, but also save the consumption of cold air and improve the efficiency of the gas turbine unit. Description of the Drawings

[0024] Figure 1 is the overall structural schematic diagram of the small and medium-sized gas turbine power turbine rotor air system of the present invention;

[0025] Figure 2 is Figure 1 the enlarged view of area A in

[0026] Figure 3 is Figure 1 the enlarged view of area B in

[0027] Figure 4 is Figure 1 the enlarged view of area C in

[0028] Figure 5 is Figure 1 the enlarged view of area D in

[0029] Figure 6 is Figure 1 the enlarged view of area E in

[0030] In the figure: 1. Front wall; 2. Mainstream gas passage; 3. First-stage turbine disk; 4. Rear wall; 5. Shaft cavity; 6. First chamber; 7. First air outlet; 8. Second air outlet; 9. Third air outlet; 10. First-stage moving blade; 11. First flange; 12. Second partition; 13. First partition; 14. Second-stage moving blade; 15. Second flange; 16. Fourth air outlet; 17. Fifth air outlet; 18. Sixth air outlet; 19. Seventh air outlet; 20. Eighth air outlet; 21. Third flange; 22. Third-stage moving blade; 23. Third partition; 24. Fourth-stage moving blade; 25. Fourth flange; 26. Second chamber; 27. First-stage clearance passage; 28. Second-stage turbine disk; 29. Isolation member; 30. Third chamber; 31. Disk hole; 32. Fourth chamber; 33. Radial hole; 34. Fifth chamber; 35. First-stage sealing structure; 36. First labyrinth insert; 37. Shaft rod; 38. Sixth chamber; 39. Left hole; 40. Seventh chamber; 41. Third-stage turbine disk; 42. Eighth chamber; 43. Second sealing structure; 44. First air seal; 45. Fourth-stage turbine disk; 46. Ninth chamber; 47. Upper hole; 48. Tenth chamber; 49. Eleventh chamber; 50. Third sealing structure; 51. Ear seat; 52. Baffle; 53. Disk-shaft coupling ring; 54. Twelfth chamber; 55. Right hole; 56. Thirteenth chamber; 57. Lower hole. Detailed implementation mode

[0031] Detailed implementation mode one: Combining Figures 1 to 6 To illustrate this implementation mode, this implementation mode includes a front wall 1, a mainstream gas passage 2, a first-stage turbine disk 3, a rear wall 4 and a shaft cavity 5. A first chamber 6 is formed between the first-stage turbine disk 3 and the front wall 1. The first chamber 6 and the shaft cavity 5 are both connected to the compressor. The first chamber 6 is connected to the mainstream gas passage 2 through a first air outlet 7, a second air outlet 8 and a third air outlet 9. The first air outlet 7 is arranged between the first-stage moving blade 10 and the first flange 11. The second air outlet 8 is arranged between the first-stage moving blade 10 and the first partition 13. The third air outlet 9 is arranged between the second-stage moving blade 14 and the second flange 15. The shaft cavity 5 is connected to the mainstream gas passage 2 through a fourth air outlet 16, a fifth air outlet 17, a sixth air outlet 18, a seventh air outlet 19 and an eighth air outlet 20. The fourth air outlet 16 is arranged between the second-stage moving blade 14 and the second partition 12. The fifth air outlet 17 is arranged between the third flange 21 and the third-stage moving blade 22. The sixth air outlet 18 is arranged between the third-stage moving blade 22 and the third partition 23. The seventh air outlet 19 is arranged between the fourth-stage moving blade 24 and the fourth flange 25. The eighth air outlet 20 is arranged between the fourth-stage moving blade 24 and the rear wall 4. The cooling gas cools the components along the way and simultaneously functions as a seal between the rotating and stationary parts and prevents the main gas flow from flowing back.

[0032] For the air system of the power turbine rotor of a medium and small gas turbine in this embodiment, only one stream of compressed air is led out from a certain part of the compressor. Part of the compressed air flows into the first chamber 6, and the other part flows into the shaft cavity 5. After passing through multiple stages of blades, it converges into the mainstream gas passage 2. By diverting the compressed air, it can not only complete the functions of cooling the disk, sealing the disk cavity, and pressurizing the bearing cavity seal, but also save the consumption of cold air and improve the efficiency of the gas turbine unit.

[0033] Specific Embodiment 2: In combination with Figure 1 、 Figure 2 to illustrate this embodiment. The difference between this embodiment and Specific Embodiment 1 is that a second chamber 26 is formed between the first-stage turbine disk 3 and the first flange 11. One end of the second chamber 26 is communicated with the first chamber 6 through a first-stage gap passage 27, and the other end of the second chamber 26 is communicated with the mainstream gas passage 2 through a first air outlet 7. After the cooling air flows through the second chamber 26, it enters the mainstream gas passage 2. The flow range of the cooling air is wide and the cooling effect is better. Other components and connection relationships are the same as those in Specific Embodiment 1.

[0034] Specific Embodiment 3: In combination with Figure 1 、 Figure 2 to illustrate this embodiment. The difference between this embodiment and Specific Embodiment 1 is that a third chamber 30 is formed between the first-stage turbine disk 3, the second-stage turbine disk 28, and the spacer 29. The third chamber 30 is communicated with the first chamber 6 through a disk hole 31 on the first-stage turbine disk 3. A fourth chamber 32 is formed between the first-stage turbine disk 3, the first partition 13, and the spacer 29. One end of the fourth chamber 32 is communicated with the third chamber 30 through a radial hole 33 on the spacer 29, and the other end of the fourth chamber 32 is communicated with the mainstream gas passage 2 through a second air outlet 8. The cooling air flows through the third chamber 30 and the fourth chamber 32 in sequence, and then enters the mainstream gas passage 2. The cooling air can cool the components along the way. Other components and connection relationships are the same as those in Specific Embodiment 1.

[0035] Specific Embodiment 4: In combination with Figure 1 、 Figure 2 to illustrate this embodiment. The difference between this embodiment and Specific Embodiment 3 is that a fifth chamber 34 is formed between the first partition 13, the second flange 15, the second-stage turbine disk 28, and the spacer 29. One end of the fifth chamber 34 is communicated with the fourth chamber 32 through a first-stage sealing structure 35, and the other end of the fifth chamber 34 is communicated with the mainstream gas passage 2 through a third air outlet 9. The first-stage sealing structure 35 is located between the first partition 13 and the first labyrinth insert 36. Part of the cooling air in the fourth chamber 32 will enter the fifth chamber 34 to cool the components along the way, and then enter the mainstream gas passage 2. Other components and connection relationships are the same as those in Specific Embodiment 3.

[0036] Embodiment V: In combination with Figure 1 and Figure 3 describe this embodiment. The difference between this embodiment and Embodiment I is that a sixth chamber 38 is formed between the secondary turbine disk 28 and the shaft rod 37. One end of the sixth chamber 38 communicates with the shaft cavity 5 through the left hole 39 on the shaft rod 37, and the other end of the sixth chamber 38 communicates with the seventh chamber 40 through the gap between the shaft rod 37 and the secondary turbine disk 28. A seventh chamber 40 is formed between the second partition 12 and the secondary turbine disk 28. The seventh chamber 40 communicates with the main gas flow channel 2 through the fourth gas outlet 16. The cooling gas in the shaft cavity 5 flows through the sixth chamber 38 and the seventh chamber 40 in sequence to cool the components along the way, and then enters the main gas flow channel 2. Other compositions and connection relationships are the same as those in Embodiment I.

[0037] Embodiment VI: In combination with Figure 1 and Figure 3 describe this embodiment. The difference between this embodiment and Embodiment V is that an eighth chamber 42 is formed in front of the tertiary turbine disk 41. One end of the eighth chamber 42 communicates with the seventh chamber 40 through the second sealing structure 43, and the other end of the eighth chamber 42 communicates with the main gas flow channel 2 through the fifth gas outlet 17. The second sealing structure 43 is located between the second partition 12 and the first gas seal 44. A part of the cooling gas in the seventh chamber 40 will enter the eighth chamber 42, cool the components along the way, and then enter the main gas flow channel 2. Other compositions and connection relationships are the same as those in Embodiment V.

[0038] Embodiment VII: In combination with Figure 1 and Figure 3 describe this embodiment. The difference between this embodiment and Embodiment VI is that a ninth chamber 46 is formed between the lower part of the tertiary turbine disk 41 and the quaternary turbine disk 45. One end of the ninth chamber 46 communicates with the eighth chamber 42 through the lower hole 57 on the tertiary turbine disk 41, and the other end of the ninth chamber 46 communicates with the tenth chamber 48 through the upper hole 47 on the tertiary turbine disk 41. A tenth chamber 48 is formed between the tertiary turbine disk 41 and the third partition 23. The tenth chamber 48 communicates with the main gas flow channel 2 through the sixth gas outlet 18. A part of the cooling gas in the eighth chamber 42 will enter the ninth chamber 46, then pass through the tenth chamber 48 and enter the main gas flow channel 2. This process can cool the components along the way. Other compositions and connection relationships are the same as those in Embodiment VI.

[0039] Embodiment VIII: In combination with Figure 1 and Figure 4To describe this embodiment, the difference between this embodiment and the seventh specific embodiment is that an eleventh chamber 49 is formed between the four-stage turbine disk 45 and the third partition 23. One end of the eleventh chamber 49 communicates with the tenth chamber 48 through a third sealing structure 50, and the other end of the eleventh chamber 49 communicates with the main gas flow channel 2 through a seventh gas outlet 19. A part of the cooling gas in the tenth chamber 48 will enter the eleventh chamber 49, cool the components along the way and then enter the main gas flow channel 2. Other compositions and connection relationships are the same as those in the seventh specific embodiment.

[0040] Specific embodiment nine: Combining Figures 1 to 6 To describe this embodiment, the difference between this embodiment and the first specific embodiment is that a twelfth chamber 54 is formed between the four-stage turbine disk 45, the rear wall 4, the ear seat 51, the baffle 52 and the disk shaft coupling ring 53. One end of the twelfth chamber 54 communicates with the shaft cavity 5 through a right hole 55 on the shaft rod 37, and the other end of the twelfth chamber 54 communicates with a thirteenth chamber 56 through the gap between the four-stage turbine disk 45 and the rear wall 4. A thirteenth chamber 56 is formed between the upper part of the four-stage turbine disk 45 and the rear wall 4, and the thirteenth chamber 56 communicates with the main gas flow channel 2 through an eighth gas outlet 20. Other compositions and connection relationships are the same as any one of the first to eighth specific embodiments.

[0041] The working principle of this embodiment:

[0042] A stream of cooling gas is introduced from a certain part of the compressor. The cooling gas enters the first chamber 6 and the shaft cavity 5 at the same time. After the cooling gas entering the first chamber 6 is shunted, it enters the main gas flow channel 2 from the first gas outlet 7, the second gas outlet 8, and the third gas outlet 9 respectively. After the cooling gas entering the shaft cavity 5 is shunted, it enters the main gas flow channel 2 from the fourth gas outlet 16, the fifth gas outlet 17, the sixth gas outlet 18, the seventh gas outlet 19, and the eighth gas outlet 20 respectively. The components along the way can be cooled during the flow of the cooling gas.

[0043] The content of the present invention is not limited to the content of the above embodiments. The combination of one or several specific embodiments can also achieve the purpose of the invention.

Claims

1. A small to medium-sized gas turbine power turbine rotor air system, comprising: A front wall (1), a mainstream gas channel (2), a first-stage turbine wheel (3), a rear wall (4) and an axial cavity (5), wherein a first chamber (6) is formed between the first-stage turbine wheel (3) and the front wall (1); Characterized in that the first chamber (6) and the shaft chamber (5) are simultaneously connected to the compressor; The first chamber (6) is connected to the mainstream gas channel (2) through a first gas outlet (7), a second gas outlet (8), and a third gas outlet (9), wherein the first gas outlet (7) is arranged between the first-stage moving blade (10) and the first flange (11), the second gas outlet (8) is arranged between the first-stage moving blade (10) and the first partition plate (13), and the third gas outlet (9) is arranged between the second-stage moving blade (14) and the second flange (15); The axial cavity (5) is connected to the mainstream gas channel (2) through a fourth gas outlet (16), a fifth gas outlet (17), a sixth gas outlet (18), a seventh gas outlet (19), and an eighth gas outlet (20); the fourth gas outlet (16) is arranged between the second-stage moving blade (14) and the second partition plate (12); the fifth gas outlet (17) is arranged between the third flange (21) and the third-stage moving blade (22); the sixth gas outlet (18) is arranged between the third-stage moving blade (22) and the third partition plate (23); the seventh gas outlet (19) is arranged between the fourth-stage moving blade (24) and the fourth flange (25); and the eighth gas outlet (20) is arranged between the fourth-stage moving blade (24) and the rear wall (4).

2. A small and medium-sized gas turbine power turbine rotor air system according to claim 1, characterized in that: A second chamber (26) is formed between the first-stage turbine wheel (3) and the first flange (11); one end of the second chamber (26) is connected to the first chamber (6) through a first-stage gap channel (27); and the other end of the second chamber (26) is connected to the mainstream fuel gas channel (2) through the first gas outlet (7).

3. A small and medium-sized gas turbine power turbine rotor air system according to claim 1, characterized in that: A third chamber (30) is formed between the first-stage turbine wheel disc (3), the second-stage turbine wheel disc (28) and the isolation member (29), and the third chamber (30) is communicated with the first chamber (6) through a wheel disc hole (31) on the first-stage turbine wheel disc (3); A fourth chamber (32) is formed between the first-stage turbine wheel (3), the first partition plate (13) and the isolation member (29); one end of the fourth chamber (32) is connected to the third chamber (30) via a radial hole (33) on the isolation member (29); and the other end of the fourth chamber (32) is connected to the mainstream fuel gas channel (2) via the second gas outlet (8).

4. A small and medium-sized gas turbine power turbine rotor air system according to claim 3, characterized in that: A fifth chamber (34) is formed between the first baffle (13), the second flange (15), the second-stage turbine wheel (28) and the isolation member (29); one end of the fifth chamber (34) is connected to the fourth chamber (32) via a first-stage sealing structure (35); the other end of the fifth chamber (34) is connected to the mainstream fuel gas channel (2) via the third gas outlet (9); and the first-stage sealing structure (35) is located between the first baffle (13) and the first labyrinth insert (36).

5. A small and medium-sized gas turbine power turbine rotor air system according to claim 1, characterized in that: A sixth chamber (38) is formed between the second-stage turbine wheel disc (28) and the shaft (37); one end of the sixth chamber (38) is communicated with the shaft cavity (5) through a left hole (39) on the shaft (37); and the other end of the sixth chamber (38) is communicated with the seventh chamber (40) through a gap between the shaft (37) and the second-stage turbine wheel disc (28); A seventh chamber (40) is formed between the second partition plate (12) and the second-stage turbine wheel (28), and the seventh chamber (40) is connected to the mainstream fuel gas channel (2) through a fourth gas outlet (16).

6. A small and medium-sized gas turbine power turbine rotor air system according to claim 5, characterized in that: An eighth chamber (42) is formed in front of the third-stage turbine wheel (41), one end of the eighth chamber (42) is connected to the seventh chamber (40) via a second sealing structure (43), and the other end of the eighth chamber (42) is connected to the mainstream fuel gas channel (2) via a fifth gas outlet (17), and the second sealing structure (43) is located between the second partition plate (12) and the first gas seal (44).

7. A small and medium-sized gas turbine power turbine rotor air system according to claim 6, characterized in that: A ninth chamber (46) is formed between the lower portion of the third-stage turbine wheel disc (41) and the fourth-stage turbine wheel disc (45); one end of the ninth chamber (46) is communicated with the eighth chamber (42) through a lower hole (57) on the third-stage turbine wheel disc (41); and the other end of the ninth chamber (46) is communicated with the tenth chamber (48) through an upper hole (47) on the third-stage turbine wheel disc (41); A tenth chamber (48) is formed between the third-stage turbine wheel (41) and the third partition plate (23), and the tenth chamber (48) is connected to the mainstream fuel gas channel (2) through a sixth gas outlet (18).

8. A small and medium-sized gas turbine power turbine rotor air system according to claim 7, characterized in that: An eleventh chamber (49) is formed between the fourth-stage turbine wheel (45) and the third partition plate (23), one end of the eleventh chamber (49) is connected to the tenth chamber (48) through the third sealing structure (50), and the other end of the eleventh chamber (49) is connected to the mainstream fuel gas channel (2) through the seventh gas outlet (19).

9. A small and medium-sized gas turbine power turbine rotor air system according to any one of claims 1 to 8, characterized in that: A twelfth chamber (54) is formed between the fourth-stage turbine wheel disc (45), the rear wall (4), the ear seat (51), the baffle plate (52) and the disc shaft connecting ring (53); one end of the twelfth chamber (54) is communicated with the shaft cavity (5) through the right hole (55) on the shaft rod (37); and the other end of the twelfth chamber (54) is communicated with the thirteenth chamber (56) through the gap between the fourth-stage turbine wheel disc (45) and the rear wall (4); A thirteenth chamber (56) is formed between the upper portion of the four-stage turbine wheel (45) and the rear wall (4), and the thirteenth chamber (56) is connected to the mainstream fuel gas channel (2) through the eighth gas outlet (20).

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