A 60MW triple reheat exhaust air turbine

Abstract

A 60MW triple reheat axial exhaust air turbine belongs to the field of compressed air energy storage technology. The present invention aims to solve the problem of insufficient efficiency and unit economy of 60MW single reheat air turbine units. It includes a high-pressure cylinder and a low-pressure cylinder; a first bearing box, a high-pressure cylinder, a second bearing box, a low-pressure cylinder and an axial exhaust cylinder are connected in sequence from front to back, a high-pressure integral forging rotor is provided for rotation in the high-pressure cylinder, a low-pressure integral forging rotor is provided for rotation in the low-pressure cylinder, a third bearing box is provided inside the axial exhaust cylinder, the front end of the high-pressure integral forging rotor is sleeved with the No. 1 support bearing in the first bearing box, the rear end of the low-pressure integral forging rotor is sleeved with the No. 3 support bearing in the third bearing box, the front end of the low-pressure integral forging rotor is sleeved with the No. 2 support bearing in the second bearing box, and is connected to the rear end of the high-pressure integral forging rotor; the main gas of the present invention has been reheated three times, which effectively improves the efficiency and unit economy of the unit.

Description

Technical Field

[0001] The present invention belongs to the technical field of compressed air energy storage, and in particular relates to a 60MW triple reheat axial exhaust air turbine. Background Art

[0002] Compressed air energy storage (CAES) involves compressing air during periods of low grid load, releasing the compressed air to generate electricity through steam turbines during peak load periods. As a clean form of power generation, CAES offers advantages such as high efficiency, low cost, high cleanliness, and a compact structure, and holds promising application prospects.

[0003] At present, China's compressed air energy storage turbine power generation technology is developing extremely rapidly. For a 60MW compressed air energy storage system, the Chinese invention patent with publication number CN116537896A discloses a 60MW single-reheat reaction air turbine. However, the efficiency and economy of the single-reheat air turbine unit are insufficient. Summary of the Invention

[0004] The present invention aims to provide a 60MW triple reheat axial exhaust air turbine to address the problem of insufficient efficiency and unit economy of 60MW single reheat air turbine units. The technical solutions adopted by the present invention are as follows:

[0005] A 60MW triple-reheat axial exhaust air turbine comprises a first bearing housing, a high-pressure cylinder, a high-pressure integrally forged rotor, a second bearing housing, a low-pressure cylinder, a low-pressure integrally forged rotor, and an axial exhaust cylinder. The first bearing housing, high-pressure cylinder, second bearing housing, low-pressure cylinder, and axial exhaust cylinder are sequentially connected from front to back. A high-pressure integrally forged rotor rotates within the high-pressure cylinder, a low-pressure integrally forged rotor rotates within the low-pressure cylinder, and a third bearing housing is disposed within the axial exhaust cylinder. The front end of the high-pressure integrally forged rotor is sleeved and fitted with a No. 1 support bearing within the first bearing housing and is connected to the rotor of the generator. The rear end of the low-pressure integrally forged rotor is sleeved and fitted with a No. 3 support bearing within the third bearing housing. The front end of the low-pressure integrally forged rotor is sleeved and fitted with a No. 2 support bearing within the second bearing housing and is connected to the rear end of the high-pressure integrally forged rotor.

[0006] The inner wall of the high-pressure cylinder is sleeved with a high-pressure cylinder exhaust side balance ring, a high-pressure No. 1 partition sleeve, a high-pressure cylinder intake side balance ring and a high-pressure No. 2 partition sleeve in sequence from front to back. The inner periphery of the high-pressure cylinder exhaust side balance ring and the inner periphery of the high-pressure cylinder intake side balance ring are both provided with a high-pressure gas sealing ring. The inner periphery of the high-pressure No. 1 partition sleeve is provided with a No. 1 static blade assembly, and the inner periphery of the high-pressure No. 2 partition sleeve is provided with a No. 2 static blade assembly. The high-pressure integral forging rotor is sleeved with a No. 1 moving blade assembly and a No. 2 moving blade assembly. The No. 1 static blade assembly cooperates with the No. 1 moving blade assembly to form a primary throughflow, and the No. 2 static blade assembly cooperates with the No. 2 moving blade assembly to form a secondary throughflow. The high-pressure cylinder exhaust side balance ring and the high-pressure cylinder intake side balance ring are both cooperated with the outer periphery of the high-pressure integral forging rotor through the high-pressure gas sealing ring.

[0007] The inner wall of the low-pressure cylinder is sequentially sleeved with a low-pressure cylinder exhaust side balance ring, a low-pressure No. 1 partition sleeve, a low-pressure cylinder intake side balance ring and a low-pressure No. 2 partition sleeve from front to back. The inner periphery of the low-pressure cylinder exhaust side balance ring and the inner periphery of the low-pressure cylinder intake side balance ring are both provided with a low-pressure air sealing ring. The inner periphery of the low-pressure No. 1 partition sleeve is provided with a No. 3 static blade assembly, and the inner periphery of the low-pressure No. 2 partition sleeve is provided with a No. 4 static blade assembly. The No. 3 moving blade assembly and the No. 4 moving blade assembly are sleeved on the low-pressure forged rotor. The No. 3 static blade assembly and the No. 3 moving blade assembly cooperate to form a three-stage flow, the No. 4 static blade assembly and the No. 4 moving blade assembly cooperate to form a four-stage flow, and the low-pressure cylinder exhaust side balance ring and the low-pressure cylinder intake side balance ring are both cooperated with the outer periphery of the low-pressure forged rotor through the low-pressure air sealing ring.

[0008] Furthermore, both ends of the high-pressure cylinder are rotationally sealed with the high-pressure integral forging rotor through the high-pressure cylinder gas seal body.

[0009] Furthermore, the front end of the low-pressure cylinder is rotationally sealed with the low-pressure integral forging rotor through the low-pressure cylinder gas seal body.

[0010] Furthermore, the high-pressure cylinder is connected to the first bearing box through a cat's claw and a centering beam push-pull structure, and the high-pressure cylinder is connected to the second bearing box through a cat's claw and a centering beam push-pull structure.

[0011] Furthermore, the low-pressure cylinder is connected to the second bearing box through a cat's claw and a centering beam push-pull structure respectively.

[0012] Furthermore, it also includes a base, and the axial exhaust cylinder is supported on the base through a flexible plate.

[0013] Furthermore, the low-pressure cylinder is connected to the axial exhaust cylinder via a flange.

[0014] Furthermore, the third bearing box is fixed to the inner wall of the axial exhaust cylinder by welding through a plurality of supports.

[0015] Furthermore, the No. 1 moving blade assembly is composed of seven stages of blades, the No. 2 moving blade assembly is composed of five stages of blades, the No. 3 moving blade assembly is composed of three stages of blades, and the No. 4 moving blade assembly is composed of two stages of blades.

[0016] Furthermore, a shaft shoulder is provided at the front end of the low-pressure integral forging rotor, and a first thrust bearing and a second thrust bearing are provided in the second bearing box, and the first thrust bearing and the second thrust bearing are respectively against both sides of the shaft shoulder.

[0017] Compared with the prior art, the present invention has the following beneficial effects:

[0018] 1. The flow adopts a multi-stage small enthalpy drop reaction design, which fundamentally improves the flow efficiency.

[0019] 2. All stationary and moving blades adopt pre-twisted assembled structure. Compared with traditional welded partitions, the assembled structure has no welds, avoiding welding deformation and better ensuring flow accuracy.

[0020] 3. The main gas is reheated three times, which effectively improves the efficiency and economy of the unit of the present invention.

[0021] 4. The main air valve is directly connected to the high-pressure cylinder, eliminating the need for an air guide pipe. Both the high-pressure cylinder and the low-pressure cylinder use tangential volute intake, minimizing intake losses.

[0022] 5. The N+1 shafting design is adopted, with only one bearing used to support the high-pressure integrally forged rotor, which shortens the span of the unit and simplifies the structure.

[0023] 6. The axial exhaust cylinder is fixed to the axial exhaust cylinder base frame by bolts. The axial exhaust cylinder base frame is composed of three parallel flexible plates arranged in a bilaterally symmetrical manner. The three flexible plates absorb the expansion of the axial exhaust cylinder by deforming forward and backward.

[0024] 7. The present invention uses air as the working fluid, has a high safety factor, little environmental pollution, huge economic and social benefits, and can save a lot of resources.

[0025] 8. As can be seen from the slide pin system diagram of the present invention, the center plane of the second support bearing is used as the absolute dead point, and the first and second thrust bearings are installed in the second bearing box to ensure that the center plane of the low-pressure forged rotor's shoulder can remain stationary as the rotor's relative dead point. After heating, the high-pressure cylinder expands toward the generator with the absolute dead point as the reference, and the low-pressure cylinder expands toward the axial exhaust cylinder side with the absolute dead point as the reference. After heating, the high-pressure forged rotor expands toward the generator with the relative dead point as the reference, and the low-pressure forged rotor expands toward the axial exhaust cylinder side with the relative dead point as the reference. BRIEF DESCRIPTION OF THE DRAWINGS

[0026] Figure 1It is a front view of the present invention;

[0027] Figure 2 is a top view of the present invention;

[0028] Figure 3 It is a schematic diagram of tangential intake;

[0029] Figure 4 It is an axonometric view of the high-pressure cylinder;

[0030] Figure 5 It is an axonometric view of the low-pressure cylinder;

[0031] Figure 6 It is an axonometric view of the axial exhaust cylinder;

[0032] Figure 7 It is a diagram of the sliding pin system of the present invention;

[0033] Figure 8 is a schematic diagram of a reaction blade;

[0034] Figure 9 It is a schematic diagram of air seal.

[0035] In the figure, 1. the first bearing box, 2. the high-pressure cylinder gas seal, 3. the high-pressure cylinder exhaust side balance ring, 4. the high-pressure integral forging rotor, 5. the high-pressure No. 1 partition sleeve, 6. the high-pressure cylinder intake side balance ring, 7. the high-pressure No. 2 partition sleeve, 8. the high-pressure cylinder, 9. the second bearing box, 10. the low-pressure cylinder gas seal, 11. the low-pressure cylinder exhaust side balance ring, 12. the low-pressure integral forging rotor, 13. the low-pressure No. 1 partition sleeve, 14. the low-pressure cylinder intake side balance ring, 15. the low-pressure cylinder, 16. the low-pressure No. 2 partition sleeve, 17. the axial exhaust cylinder, 18. the No. 1 support bearing, 19. the No. 2 support bearing, 20. the shaft shoulder, 21. the No. 3 support bearing, 22. the cat's claw, 23. the absolute dead point, 24. the relative dead point, 25. the generator, 26. the centering beam push-pull structure, 27. the third bearing box. DETAILED DESCRIPTION

[0036] To make the objectives, technical solutions, and advantages of the present invention more clearly apparent, the present invention is described below using specific embodiments shown in the accompanying drawings. However, it should be understood that these descriptions are merely illustrative and are not intended to limit the scope of the present invention. In addition, in the following description, descriptions of well-known structures and technologies are omitted to avoid unnecessary confusion of the concepts of the present invention.

[0037] The connections mentioned in the present invention are divided into fixed connections and detachable connections. The fixed connection refers to a non-detachable connection, including but not limited to conventional fixed connection methods such as hem connection, rivet connection, adhesive connection, and welding connection. The detachable connection refers to but not limited to conventional detachable connection methods such as bolt connection, snap connection, pin connection, and hinge connection. When the specific connection method is not clearly specified, it is assumed that at least one connection method can be found among the existing connection methods to achieve the function. Those skilled in the art can choose according to their needs. For example, a welded connection is selected for a fixed connection, and a bolted connection is selected for a detachable connection.

[0038] The present invention will be further described in detail below with reference to the accompanying drawings. The following embodiments are provided to explain the present invention, but the present invention is not limited to the following embodiments.

[0039] Example: Figure 1-9 As shown, a 60MW triple reheat axial exhaust air turbine includes a first bearing box 1, a high-pressure cylinder 8, a high-pressure integral forged rotor 4, a second bearing box 9, a low-pressure cylinder 15, a low-pressure integral forged rotor 12 and an axial exhaust cylinder 17; the first bearing box 1, the high-pressure cylinder 8, the second bearing box 9, the low-pressure cylinder 15 and the axial exhaust cylinder 17 are connected in sequence from front to back, the high-pressure integral forged rotor 4 is rotatably arranged in the high-pressure cylinder 8, the low-pressure integral forged rotor 12 is rotatably arranged in the low-pressure cylinder 15, and a third bearing box 27 is provided inside the axial exhaust cylinder 17. The front end of the high-pressure integral forged rotor 4 is sleeved and matched with the No. 1 support bearing 18 in the first bearing box 1 and is connected to the rotor of the generator 25. The rear end of the low-pressure integral forged rotor 12 is sleeved and matched with the No. 3 support bearing 21 in the third bearing box 27. The front end of the low-pressure integral forged rotor 12 is sleeved and matched with the No. 2 support bearing 19 in the second bearing box 9 and is connected to the rear end of the high-pressure integral forged rotor 4;

[0040] The inner wall of the high-pressure cylinder 8 is sleeved with a high-pressure cylinder exhaust side balance ring 3, a high-pressure No. 1 partition sleeve 5, a high-pressure cylinder intake side balance ring 6 and a high-pressure No. 2 partition sleeve 7 in sequence from front to back. The inner periphery of the high-pressure cylinder exhaust side balance ring 3 and the inner periphery of the high-pressure cylinder intake side balance ring 6 are both provided with high-pressure gas sealing rings. The inner periphery of the high-pressure No. 1 partition sleeve 5 is provided with a No. 1 static blade assembly, and the inner periphery of the high-pressure No. 2 partition sleeve 7 is provided with a No. 2 static blade assembly. The high-pressure forged rotor 4 is sleeved with a No. 1 moving blade assembly and a No. 2 moving blade assembly. The No. 1 static blade assembly cooperates with the No. 1 moving blade assembly to form a primary throughflow, and the No. 2 static blade assembly cooperates with the No. 2 moving blade assembly to form a secondary throughflow. The high-pressure cylinder exhaust side balance ring 3 and the high-pressure cylinder intake side balance ring 6 are both matched with the outer periphery of the high-pressure forged rotor 4 through high-pressure gas sealing rings;

[0041] The inner wall of the low-pressure cylinder 15 is sequentially sleeved with a low-pressure cylinder exhaust side balance ring 11, a low-pressure No. 1 partition sleeve 13, a low-pressure cylinder intake side balance ring 14 and a low-pressure No. 2 partition sleeve 16 from front to back. The inner periphery of the low-pressure cylinder exhaust side balance ring 11 and the inner periphery of the low-pressure cylinder intake side balance ring 14 are both provided with low-pressure air sealing rings. The inner periphery of the low-pressure No. 1 partition sleeve 13 is provided with a No. 3 static blade assembly, and the inner periphery of the low-pressure No. 2 partition sleeve 16 is provided with a No. 4 static blade assembly. The No. 3 moving blade assembly and the No. 4 moving blade assembly are sleeved on the low-pressure forged rotor 12. The No. 3 static blade assembly and the No. 3 moving blade assembly cooperate to form a three-stage flow, and the No. 4 static blade assembly and the No. 4 moving blade assembly cooperate to form a four-stage flow. The low-pressure cylinder exhaust side balance ring 11 and the low-pressure cylinder intake side balance ring 14 are both cooperated with the outer periphery of the low-pressure forged rotor 12 through the low-pressure air sealing ring.

[0042] Both ends of the high-pressure cylinder 8 are rotationally sealed with the high-pressure integral forging rotor 4 through the high-pressure cylinder gas seal body 2.

[0043] The front end of the low-pressure cylinder 15 is rotatably sealed with the low-pressure integral forging rotor 12 through the low-pressure cylinder gas seal body 10.

[0044] The high-pressure cylinder 8 is connected to the first bearing box 1 through the cat claw 22 and the centering beam push-pull structure 26, and the high-pressure cylinder 8 is connected to the second bearing box 9 through the cat claw 22 and the centering beam push-pull structure 26.

[0045] The low-pressure cylinder 15 is connected to the second bearing box 9 through the cat claw 22 and the centering beam push-pull structure 26 respectively.

[0046] It also includes a base on which the axial exhaust cylinder 17 is supported by a flexible plate.

[0047] The low-pressure cylinder 15 is connected to the axial exhaust cylinder 17 via a flange.

[0048] The third bearing box 27 is fixed to the inner wall of the axial exhaust cylinder 17 by welding through a plurality of struts.

[0049] The No. 1 moving blade assembly is composed of seven stages of blades, the No. 2 moving blade assembly is composed of five stages of blades, the No. 3 moving blade assembly is composed of three stages of blades, and the No. 4 moving blade assembly is composed of two stages of blades.

[0050] A shaft shoulder 20 is provided at the front end of the low-pressure integral forging rotor 12 , and a first thrust bearing and a second thrust bearing are provided in the second bearing box 9 . The first thrust bearing and the second thrust bearing are respectively against both sides of the shaft shoulder 20 .

[0051] The present invention adopts a 3000 rpm rotation speed design and is designed with four flow sections, namely the first flow, the second flow, the third flow and the fourth flow in order of pressure reduction. It is designed with three reheating and is a double-cylinder axial arrangement air turbine unit with a high-pressure cylinder 8 and a low-pressure cylinder 15. The overall layout is in the form of a generator 25-high-pressure cylinder 8-low-pressure cylinder 15-axial exhaust cylinder 17, and the arrangement is a series coaxial drive. The high-pressure cylinder 8 is provided with two intake valves, one main and one adjustment. Both sides of the high-pressure cylinder 8 are connected to the first bearing box 1 and the second bearing box 9 by a cat's claw 22 and a fixed center beam push-pull structure 26; the low-pressure cylinder 15 is connected to the axial exhaust cylinder 17 by a vertically arranged flange, and the low-pressure cylinder 15 is connected to the second bearing box 9 by a cat's claw 22 and a fixed center beam push-pull structure 26. The axial exhaust cylinder 17 is supported on the base by a flexible plate. The back pressure of the unit of the present invention is 0.0724MPa, the main gas temperature is 177.5℃, and the working fluid is air. It has the advantages of high safety factor, low environmental pollution, and long service life. The main gas enters the high-pressure cylinder 8 tangentially through the main gas valve, first passes through the first-stage flow to do work, and then passes through the No. 1 reheater to heat the air to the main gas temperature. Then it enters the second-stage flow to do work, and passes through the No. 2 reheater to heat the air to the main gas temperature. Then it enters the third-stage flow to do work, and passes through the No. 3 reheater to heat the air to the main gas temperature. Finally, it enters the fourth-stage flow to do work. The air enters the exhaust pipe through the axial exhaust cylinder 17 and is discharged into the atmosphere after being silenced. The main gas has been reheated three times, which effectively improves the efficiency and economy of the unit. The pressure balancing pipe outside the high-pressure cylinder 8 and the low-pressure cylinder 15 and the balance hub gas seal arranged inside can balance the front and rear end pressures and axial thrusts in the high-pressure cylinder 8 and the low-pressure cylinder 15 respectively. Comb-shaped seals are designed at both ends of the high-pressure cylinder 8 and at the front end of the low-pressure cylinder 15. These seals provide a reasonable clearance, meeting both economical and safety requirements while also facilitating easy maintenance. Both the high-pressure cylinder 8 and the low-pressure cylinder 15 utilize a single-layer cylinder structure, offering flexible startup, lateral tangential intake, and axial exhaust, effectively minimizing air pressure loss.

[0052] The present invention adopts a comb-tooth-type high-pressure cylinder gas seal 2 and a low-pressure cylinder gas seal 10. The gas seal gap is reasonable, can meet the requirements of economy and safety, and is easy to maintain. The first-level flow, second-level flow, third-level flow and fourth-level flow of the present invention adopt a multi-stage small enthalpy drop reaction design to fundamentally improve the flow efficiency. The No. 1 static blade assembly, No. 2 static blade assembly, No. 3 static blade assembly, No. 4 static blade assembly, No. 1 moving blade assembly, No. 2 moving blade assembly, No. 3 moving blade and No. 4 moving blade assembly all adopt a pre-twisted assembled structure. Compared with the traditional welded partition, the assembled structure has no welds, avoids welding deformation, and better guarantees the flow accuracy; the tangential air intake can reduce the air intake loss. The present invention has excellent thermal performance and flow efficiency, high product reliability, and meets the requirements of flexible start and stop. It is safe and reliable in operation and easy to repair and maintain.

[0053] The present invention has the following advantages:

[0054] 1. The flow adopts a multi-stage small enthalpy drop reaction design, which fundamentally improves the flow efficiency.

[0055] 2. All stationary and moving blades adopt pre-twisted assembled structure. Compared with traditional welded partitions, the assembled structure has no welds, avoiding welding deformation and better ensuring flow accuracy.

[0056] 3. The main gas is reheated three times, which effectively improves the efficiency and economy of the unit of the present invention.

[0057] 4. The main air valve is directly connected to the high-pressure cylinder 8, eliminating the air guide pipe structure. Both the high-pressure cylinder 8 and the low-pressure cylinder 15 are tangentially volute-type, minimizing intake losses.

[0058] 5. The N+1 shafting design is adopted, with only one bearing used to support the high-pressure integrally forged rotor 4, which shortens the span of the unit and simplifies the structure.

[0059] 6. The axial exhaust cylinder 17 is fixed to the axial exhaust cylinder base frame by bolts. The axial exhaust cylinder base frame is composed of three parallel flexible plates arranged in a bilaterally symmetrical manner. The three flexible plates absorb the expansion of the axial exhaust cylinder 17 by deforming forward and backward.

[0060] 7. The present invention uses air as the working fluid, has a high safety factor, little environmental pollution, huge economic and social benefits, and can save a lot of resources.

[0061] 8. As can be seen from the slide pin system diagram of the present invention, the center plane of the second support bearing 19 is used as the absolute dead point 23, and the first and second thrust bearings are installed in the second bearing box 9 to ensure that the center plane of the shoulder 20 of the low-pressure forged rotor 12 can remain stationary as the rotor relative dead point 24. After heating, the high-pressure cylinder 8 expands toward the generator 25 with the absolute dead point 23 as the reference, and the low-pressure cylinder 15 expands toward the axial exhaust cylinder 17 with the absolute dead point 23 as the reference. After heating, the high-pressure forged rotor 4 expands toward the generator 25 with the relative dead point 24 as the reference, and the low-pressure forged rotor 12 expands toward the axial exhaust cylinder 17 with the relative dead point 24 as the reference.

[0062] The above embodiments are merely illustrative of the present invention and do not limit its scope of protection. Those skilled in the art may make partial changes thereto, which are within the scope of protection of the present invention as long as they do not exceed the spirit of the present invention.

Claims

1. A 60MW triple reheat exhaust air turbine, characterized by: The invention comprises a first bearing box (1), a high-pressure cylinder (8), a high-pressure integral forging rotor (4), a second bearing box (9), a low-pressure cylinder (15), a low-pressure integral forging rotor (12) and an axial exhaust cylinder (17); the first bearing box (1), the high-pressure cylinder (8), the second bearing box (9), the low-pressure cylinder (15) and the axial exhaust cylinder (17) are sequentially connected from front to back, the high-pressure cylinder (8) is provided with a high-pressure integral forging rotor (4) for rotation, the low-pressure cylinder (15) is provided with a low-pressure integral forging rotor (12) for rotation, and the axial exhaust cylinder (17) is provided with a low-pressure integral forging rotor (12) for rotation. A third bearing box (27) is provided inside the exhaust cylinder (17); the front end of the high-pressure forged rotor (4) is sleeved and matched with the No. 1 support bearing (18) in the first bearing box (1) and is connected to the rotor of the generator (25); the rear end of the low-pressure forged rotor (12) is sleeved and matched with the No. 3 support bearing (21) in the third bearing box (27); the front end of the low-pressure forged rotor (12) is sleeved and matched with the No. 2 support bearing (19) in the second bearing box (9) and is connected to the rear end of the high-pressure forged rotor (4); The inner wall of the high-pressure cylinder (8) is sleeved with a high-pressure cylinder exhaust side balance ring (3), a high-pressure No. 1 partition sleeve (5), a high-pressure cylinder intake side balance ring (6) and a high-pressure No. 2 partition sleeve (7) in sequence from front to back. The inner periphery of the high-pressure cylinder exhaust side balance ring (3) and the inner periphery of the high-pressure cylinder intake side balance ring (6) are both provided with a high-pressure gas sealing ring. The inner periphery of the high-pressure No. 1 partition sleeve (5) is provided with a No. 1 static blade assembly. The inner periphery of the high-pressure No. 2 partition sleeve (7) is provided with a No. 2 static blade assembly. The high-pressure integral forging rotor (4) is sleeved with a No. 1 moving blade assembly and a No. 2 moving blade assembly. The No. 1 static blade assembly and the No. 1 moving blade assembly cooperate to form a primary throughflow. The No. 2 static blade assembly and the No. 2 moving blade assembly cooperate to form a secondary throughflow. The high-pressure cylinder exhaust side balance ring (3) and the high-pressure cylinder intake side balance ring (6) are both cooperated with the outer periphery of the high-pressure integral forging rotor (4) through the high-pressure gas sealing ring. The inner wall of the low-pressure cylinder (15) is sleeved with a low-pressure cylinder exhaust side balance ring (11), a low-pressure No. 1 partition plate sleeve (13), a low-pressure cylinder intake side balance ring (14) and a low-pressure No. 2 partition plate sleeve (16) in sequence from front to back. The inner periphery of the low-pressure cylinder exhaust side balance ring (11) and the inner periphery of the low-pressure cylinder intake side balance ring (14) are both provided with a low-pressure gas seal ring. The inner periphery of the low-pressure No. 1 partition plate sleeve (13) is provided with a No. 3 static blade assembly. The inner periphery of the low-pressure No. 2 partition plate sleeve (16) is provided with a No. 3 static blade assembly. A fourth static blade assembly is arranged around the periphery, a third moving blade assembly and a fourth moving blade assembly are sleeved on the low-pressure integral forging rotor (12), the third static blade assembly and the third moving blade assembly cooperate to form a three-stage through-flow, the fourth static blade assembly and the fourth moving blade assembly cooperate to form a four-stage through-flow, and a low-pressure cylinder exhaust side balance ring (11) and a low-pressure cylinder intake side balance ring (14) are both cooperated with the outer periphery of the low-pressure integral forging rotor (12) through a low-pressure gas seal ring; The high-pressure cylinder (8) is connected to the first bearing box (1) through the cat's claw (22) and the fixed center beam push-pull structure (26), and the high-pressure cylinder (8) is connected to the second bearing box (9) through the cat's claw (22) and the fixed center beam push-pull structure (26); the low-pressure cylinder (15) is connected to the second bearing box (9) through the cat's claw (22) and the fixed center beam push-pull structure (26); the front end of the low-pressure forged rotor (12) is provided with a shaft shoulder (20), and the second bearing box (9) is provided with a first thrust bearing and a second thrust bearing, and the first thrust bearing and the second thrust bearing are respectively against the two sides of the shaft shoulder (20).

2. A 60MW triple reheat exhaust air turbine according to claim 1, characterized in that: Both ends of the high-pressure cylinder (8) are respectively rotatably sealed with the high-pressure integral forging rotor (4) through the high-pressure cylinder gas seal body (2).

3. A 60MW triple reheat exhaust air turbine according to claim 2, characterized in that: The front end of the low-pressure cylinder (15) is rotationally sealed with the low-pressure integral forging rotor (12) through the low-pressure cylinder gas seal body (10).

4. A 60MW triple reheat exhaust air turbine according to claim 1, characterized in that: It also comprises a base, on which the axial exhaust cylinder (17) is supported by a flexible plate.

5. The 60MW triple reheat exhaust air turbine according to claim 1, characterized in that: The low-pressure cylinder (15) is connected to the axial exhaust cylinder (17) via a flange.

6. A 60MW triple reheat exhaust air turbine according to claim 1, characterized in that: The third bearing box (27) is fixed to the inner wall of the axial exhaust cylinder (17) by welding through a plurality of struts.

7. The 60MW triple reheat exhaust air turbine according to claim 1, characterized in that: The No. 1 moving blade assembly is composed of seven stages of blades, the No. 2 moving blade assembly is composed of five stages of blades, the No. 3 moving blade assembly is composed of three stages of blades, and the No. 4 moving blade assembly is composed of two stages of blades.

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