A two-stage gas turbine rotor cooling structure

Abstract

The present invention discloses a two-stage gas turbine rotor cooling structure in the field of turbine rotor cooling technology. By inserting a first sealing ring and a second sealing ring into a first-stage rotor and a second-stage rotor, a second chamber for supplying a second cooling gas is formed in the first rotor, and a first chamber for supplying a first cooling gas is formed in the second rotor. The first chamber and the second chamber are used to cool the second rotor and the first rotor respectively, and the first chamber and the second chamber are separated by the second sealing ring. The cooling gases in the first chamber and the second chamber can be controlled separately, which can be used to finely regulate the wheel center temperature of the first-stage rotor and the second-stage rotor, weaken the thermal stress of the wheel disk, refine the sealing and cooling design, and significantly improve the environmental adaptability, acceleration and deceleration working condition capability, etc. of the gas turbine rotor system and even the aircraft engine.

Description

Technical Field

[0001] The present invention relates to the technical field of turbine rotor cooling, in particular to a two-stage gas turbine rotor cooling structure. Background Art

[0002] Existing gas turbine engines are high-temperature, high-pressure, and high-speed rotating machines. As engine operating temperatures rise and centrifugal loads increase, the temperatures and centrifugal loads on the turbine rotor further increase. Furthermore, the operating environment of gas turbine engines is becoming increasingly complex, with transient operating conditions such as acceleration and deceleration becoming increasingly common. This requires more efficient and sophisticated cooling and sealing of the turbine rotor to improve the reliability and robustness of the cooling and sealing systems.

[0003] Existing gas turbine engines generally have turbine components in two configurations: single-stage and two-stage. In two-stage gas turbines, the disc seals and rotor cooling air for the two rotor stages often share a common flow path, drawn from the same upstream cooling air. The cooling seal flow paths of the two rotors are uninterrupted, resulting in coupling and influence between them. This leads to the following major disadvantages:

[0004] First, the two-stage gas turbine rotors share a cooling air path and are coupled in series. This makes the cooling design of the gas turbine rotors inadequate for the different temperatures and centrifugal loads of the two stages, increases cooling air usage, and reduces the overall efficiency of the gas turbine and even the engine.

[0005] Second, the two-stage gas turbine rotors are subject to different thermal loads. The upstream rotor is subject to a greater flow path heat load, while the downstream rotor is subject to a smaller flow path heat load. Using the same seal cooling air stream, it is difficult to achieve a uniform and reasonable temperature distribution from the disk rim to the disk center of the two-stage gas turbine. This results in an unreasonable and difficult to balance thermal stress distribution, shortening the service life of the turbine disk.

[0006] Third, the working environment of modern gas turbine engines is becoming more and more complex, and transitional operating conditions such as acceleration and deceleration are becoming more and more harsh. When the two-stage gas turbine rotors share a cooling air channel, the cooling air distribution affects each other. Under severe sudden operating conditions, it is difficult to reliably meet the sealing and cooling requirements of multiple positions of each stage of turbine rotors at the same time, reducing the engine's full range and acceleration and deceleration capabilities.

[0007] Based on this, the present invention designs a two-stage gas turbine rotor cooling structure to solve the above problems. Summary of the Invention

[0008] To achieve the above-mentioned objectives, the present invention provides the following technical solutions: a two-stage gas turbine rotor cooling structure, comprising a first-stage rotor and a second-stage rotor, wherein the first-stage rotor and the second-stage rotor are both rotating bodies, and the first-stage rotor and the second-stage rotor are coaxially arranged along a first direction, and are characterized in that: a first sealing ring is commonly inserted through the first-stage rotor and the second-stage rotor, and the outer diameter of the first sealing ring is smaller than the inner diameter of the first-stage rotor and the second-stage rotor; a second sealing ring is inserted into the gap between the first-stage rotor and the first sealing ring, and the outer diameter of the second sealing ring is smaller than the inner diameter of the first-stage rotor and larger than the outer diameter of the first sealing ring, and at the same time, one end of the second sealing ring located in the first-stage rotor abuts against the side surface of the second rotor for sealing; the first sealing ring, the second sealing ring and the second-stage rotor form a first chamber for the flow of a first cooling gas, and a second chamber for the flow of a second cooling gas is formed between the second sealing ring and the first-stage rotor.

[0009] As a further solution of the present invention, the first-stage rotor includes a first side surface and a second side surface opposite to each other along a first direction, and the second-stage rotor includes a first side surface and a second side surface opposite to each other along the first direction; the first side surface of the first-stage rotor is opposite to the first side surface of the second-stage rotor and a third chamber connected to the second chamber is formed therebetween.

[0010] As a further solution of the present invention, a first shaft neck is provided on the first side of the first-stage rotor, and a second shaft neck is provided on the first side of the second-stage rotor. The first shaft neck and the second shaft neck abut against each other to close the side of the third chamber away from the second chamber, and a first air hole for discharging the cooling gas in the third chamber is opened on the first shaft neck or the second shaft neck.

[0011] As a further solution of the present invention, a third shaft neck is provided on the second side surface of the secondary rotor, and a third sealing ring is clamped on the outer ring surface of the third shaft neck through a step groove. The end of the third sealing ring away from the third shaft neck extends along the second side surface of the secondary rotor and does not exceed the outer ring surface of the secondary rotor. A fourth chamber is formed between the third sealing ring and the second side surface of the secondary rotor. The end of the inner ring surface of the third shaft neck away from the secondary rotor protrudes from the inner ring surface of the third shaft neck and is tightly attached to the outer ring surface of the first sealing ring. A second air hole connecting the first chamber and the fourth chamber is opened at the position where the third shaft neck is adjacent to the first chamber and the fourth chamber.

[0012] As a further solution of the present invention, a groove is provided at a position where the first side surface of the secondary rotor is adjacent to the inner ring surface of the secondary rotor, and the outer ring surface of one end of the second sealing ring extending into the primary rotor abuts against the inner ring surface of the groove.

[0013] As a further solution of the present invention, a mounting groove is formed on one end of the outer ring surface of the second sealing ring close to the groove, and a sealing expansion ring is installed in the mounting groove.

[0014] As a further solution of the present invention, a boss is provided on the outer ring surface of the first sealing ring, the position of the boss coincides with the position of the groove in the first direction and abuts against the inner ring surface of the second sealing ring, for supporting one end of the second sealing ring extending into the groove.

[0015] As a further solution of the present invention, a third air hole is provided on the boss to connect two opposite sides of the boss in the first direction.

[0016] As a further solution of the present invention, a ventilation hole is opened on the surface of the second sealing ring, and the ventilation hole connects the inner ring surface and the outer ring surface of the second sealing ring, so that the first chamber and the second chamber are connected.

[0017] As a further solution of the present invention, a thickened area is provided on the first side surface of the secondary rotor, and the inner diameter of the thickened area is larger than the inner diameter of the secondary rotor, so that the inner annular surface of the thickened area and the inner annular surface of the secondary rotor are offset to form a groove.

[0018] The present invention has the following beneficial effects:

[0019] This device forms a second chamber for supplying the second cooling gas in the first rotor and a first chamber for supplying the first cooling gas in the second rotor by arranging a first sealing ring and a second sealing ring in the first rotor and the second rotor, the first chamber and the second chamber are used to cool the second rotor and the first rotor respectively, and the first chamber and the second chamber are separated by the second sealing ring. The cooling gases in the first chamber and the second chamber can be controlled separately, which can be used to finely regulate the wheel center temperature of the first rotor and the second rotor, weaken the thermal stress of the wheel disc, refine the sealing and cooling design, and significantly improve the environmental adaptability, acceleration and deceleration working condition capability, etc. of the gas turbine rotor system and even the aircraft engine.

[0020] In addition to the above-described objects, features and advantages, the present invention has other objects, features and advantages. The present invention will be further described in detail below with reference to the accompanying drawings. BRIEF DESCRIPTION OF THE DRAWINGS

[0021] The accompanying drawings, which constitute part of this application, are intended to provide a further understanding of the present invention. The exemplary embodiments of the present invention and their descriptions are intended to explain the present invention and do not constitute an undue limitation of the present invention. In the accompanying drawings:

[0022] Figure 1 It is a schematic diagram of the overall structure of the present invention.

[0023] Figure 2 Schematic diagram of cooling gas flow in the present invention.

[0024] Figure 3 It is a structural schematic diagram of the boss in the present invention.

[0025] Figure 4 Schematic diagram of the structure of the ventilation hole in the present invention.

[0026] Figure 5 It is a structural schematic diagram of the thickened area in the present invention.

[0027] Legend:

[0028] 1. First-stage rotor; 2. Second-stage rotor; 3. First sealing ring; 4. Second sealing ring; 5. First chamber; 6. Second chamber; 7. Third chamber; 8. First journal; 9. Second journal; 10. First air hole; 11. Third journal; 12. Third sealing ring; 13. Fourth chamber; 14. Second air hole; 15. Groove; 16. Mounting groove; 17. Sealing ring; 18. Boss; 19. Third air hole; 20. Ventilation hole; 21. Thickened area. DETAILED DESCRIPTION

[0029] The embodiments of the present invention will be described in detail below with reference to the accompanying drawings. However, the present invention can be implemented in many different ways as defined and covered below.

[0030] See also Figure 1-5 The present invention provides a two-stage gas turbine rotor cooling structure, comprising a first-stage rotor 1 and a second-stage rotor 2. The first-stage rotor 1 and the second-stage rotor 2 are both rotating bodies, and the first-stage rotor 1 and the second-stage rotor 2 are coaxially arranged along a first direction. A second chamber 6 for the flow of a second cooling gas and a first chamber 5 for the flow of a first cooling gas are respectively formed in the first-stage rotor 1 and the second-stage rotor 2. The second cooling gas is fed into the second chamber 6 to cool the wheel center of the first-stage rotor 1, and the first cooling gas is fed into the first chamber 5 to cool the wheel center of the second-stage rotor 2. The flow rates of the first cooling gas and the second cooling gas can be controlled respectively according to different temperatures and centrifugal loads of the first-stage rotor 1 and the second-stage rotor 2, thereby preventing excessive introduction of cooling gas and making the flow rate of cooling gas more reasonable. The temperature distribution from the disk rim to the disk center of the two-stage gas turbine can be more precisely controlled, thereby improving the service life of the turbine disk. Under severe sudden working conditions, the sealing and cooling requirements of the first-stage rotor 1 and the second-stage rotor 2 can be simultaneously met, thereby improving the full range and acceleration and deceleration capabilities of the engine.

[0031] Specifically, the first direction is the X direction.

[0032] Optionally, the first-stage sealing ring 3 is a pull rod, which is used to axially tighten the entire gas turbine and even the engine core.

[0033] Specifically, a first sealing ring 3 is inserted into both the first-stage rotor 1 and the second-stage rotor 2. The outer diameter of the first sealing ring 3 is smaller than the inner diameter of the first-stage rotor 1 and the second-stage rotor 2. A second sealing ring 4 is inserted into the gap between the first-stage rotor 1 and the first sealing ring 3. The outer diameter of the second sealing ring 4 is smaller than the inner diameter of the first-stage rotor 1 and larger than the outer diameter of the first sealing ring 3. At the same time, one end of the second sealing ring 4 located in the first-stage rotor 1 abuts against the side of the second-stage rotor 2 for sealing. The first sealing ring 3, the second sealing ring 4 and the second-stage rotor 2 form a first chamber 5. The second sealing ring 4 is inserted into the gap between the first-stage rotor 1 and the first sealing ring 3. A second chamber 6 is formed between the ring 4 and the first-stage rotor 1. As a result, the first cooling gas in the first chamber 5 can directly contact the inner annular surface of the second-stage rotor 2 to exchange heat with the second-stage rotor 2, so as to achieve the effect of cooling the wheel center of the second-stage rotor 2, while the second cooling gas in the second chamber 6 can directly contact the inner annular surface of the first-stage rotor 1 to exchange heat with the first-stage rotor 1, so as to achieve the effect of cooling the wheel center of the first-stage rotor 1, realizing independent temperature control of the wheel centers of the first-stage rotor 1 and the second-stage rotor 2, effectively reducing the thermal stress of the turbine disk and improving the life of the disk.

[0034] Specifically, such as Figure 1-2 As shown, the first-stage rotor 1 includes a first side surface and a second side surface that are opposite to each other along a first direction, and the second-stage rotor 2 includes a first side surface and a second side surface that are opposite to each other along the first direction;

[0035] The first side surface of the first-stage rotor 1 is opposite to the first side surface of the second-stage rotor 2, and there is a certain gap between the two. The area between the first side surface of the first-stage rotor 1 and the first side surface of the second-stage rotor 2 is the third chamber 7. The third chamber 7 is connected to the second chamber 6. The second cooling gas in the second chamber 6 flows from the left side to the right side of the second chamber 6 to cool the wheel center of the first rotor, and then enters the third chamber 7 from the junction of the second chamber 6 and the third chamber 7 to exchange heat with the first side surface of the first-stage rotor 1 and the first side surface of the first and second-stage rotors 2, thereby increasing the contact area between the second cooling gas and the first and second-stage rotors 1 and 2, improving the cooling effect, and making full use of the second cooling gas to cool the first and second-stage rotors 1 and 2.

[0036] Specifically, such as Figure 1-2As shown, a first journal 8 is provided on the first side of the first-stage rotor 1, and a second journal 9 is provided on the first side of the second-stage rotor 2, and the first journal 8 and the second journal 9 abut against each other to close the side of the third chamber 7 away from the second chamber 6, and a first air hole 10 for discharging the second cooling gas in the third chamber 7 is opened on the first journal 8 or the second journal 9. The second cooling gas entering the third chamber 7 from the second chamber 6 can only leave from the first air hole 10, so that the second cooling gas can fill the entire third chamber 7, fully contact and exchange heat with the first side of the first-stage rotor 1 and the first side of the second-stage rotor 2, thereby improving the cooling effect. At the same time, the second cooling gas passing through the second chamber 6 and the third chamber 7 is led out through the first air hole 10 to between the outer ring surfaces of the first-stage rotor 1 and the second-stage rotor 2, and exchanges heat with the outer ring surfaces of the first-stage rotor 1 and the second-stage rotor 2.

[0037] like Figure 1-2 As shown, a third journal 11 is provided on the second side surface of the secondary rotor 2. A third sealing ring 12 is clamped on the outer ring surface of the third journal 11 through a step groove. The end of the third sealing ring 12 away from the third journal 11 extends along the second side surface of the secondary rotor 2 and does not exceed the outer ring surface of the secondary rotor 2. A fourth chamber 13 is formed between the third sealing ring 12 and the second side surface of the secondary rotor 2. The end of the inner ring surface of the third journal 11 away from the secondary rotor 2 protrudes from the inner ring surface of the third journal 11 and is tightly attached to the outer ring surface of the first sealing ring 3. A channel connecting the first chamber 5 and the fourth chamber 13 is opened at the position where the third journal 11 is adjacent to the first chamber 5 and the fourth chamber 13. The second air hole 14 of the fourth chamber 13 forms the fourth chamber 13 on the second side surface of the secondary rotor 2 through the cooperation between the third sealing ring 12 and the second side surface of the secondary rotor 2. At the same time, the outer annular surface of the first sealing ring 3 abuts the inner annular surface of the third shaft neck 11, so that after the first cooling gas enters the first chamber 5, it can only be introduced into the fourth chamber 13 through the second air hole 14 defined in the third shaft neck 11. The first cooling gas will exchange heat with the second side surface of the secondary rotor 2 in the fourth chamber 13, thereby cooling the second side surface of the secondary rotor 2, improving the utilization rate of the second cooling gas, and enhancing the cooling effect on the secondary rotor 2.

[0038] Figure 3FIG2 shows an installation example of the second sealing ring 4. In this example, a groove 15 is provided at a position where the first side surface of the secondary rotor 2 and the inner ring surface of the secondary rotor 2 are adjacent. The outer ring surface of the end of the second sealing ring 4 extending into the primary rotor 1 abuts against the inner ring surface of the groove 15. During operation, the first sealing ring 3 and the second sealing ring 4 will rotate around their own axes following the first rotor and the secondary rotor 2. At this time, the first sealing ring 3 and the second sealing ring 4 will be subjected to the centrifugal force generated by the rotation. The outer ring surface of the end of the first sealing ring 3 extending into the secondary rotor 2 abuts against the inner ring surface of the third journal 11. The annular surfaces abut against each other to prevent the first sealing ring 3 from being deformed under the action of centrifugal force. Similarly, a groove 15 is provided at a position where the first side surface of the secondary rotor 2 and the inner annular surface are adjacent. One end of the second sealing ring 4 extending into the first rotor 1 abuts against the inner annular surface of the groove 15, supporting the suspended end of the second sealing ring 4 from the radial direction to prevent the second sealing ring 4 from being deformed during high-speed rotation and to prevent air leakage. At the same time, under the action of the centrifugal force generated by the high-speed rotation, the contact between the second sealing ring 4 and the groove 15 can be made closer, thereby improving the sealing effect.

[0039] Specifically, a thickened area 21 is provided on the first side surface of the secondary rotor 2. The inner diameter of the thickened area 21 is larger than the inner diameter of the secondary rotor 2, so that the inner annular surface of the thickened area 21 and the inner annular surface of the secondary rotor 2 are misaligned in the radial direction, thereby forming a groove 15 for contacting the second sealing rotor. Figure 5 As shown, the contact between the second sealing ring 4 and the secondary rotor 2 will cause a certain centrifugal load on the wheel center. Generally speaking, the wheel center is the location with the greatest stress on the turbine disk and the greatest impact on failure and damage. Therefore, during the disk design process, the stress of the wheel center must be strictly controlled, and the location with the greatest stress is optimally located at the rotor stacking center. In this solution, the thickened area 21 of the secondary rotor 2 does not affect the center position of the wheel center, which is located at the rotor stacking center. That is, the main load-bearing area of ​​the wheel center is nearly symmetrically distributed with respect to the rotor stacking center, with L1 and L2 of similar size. The thickened area 21 serves as an additional "auxiliary" load-bearing area.

[0040] like Figure 3As shown, in some examples, a mounting groove 16 is provided at one end of the outer ring surface of the second sealing ring 4 close to the groove 15, and a sealing ring 17 is installed in the mounting groove 16. A seal is formed by the sealing ring 17 abutting against the inner ring surface of the groove 15. Under harsh working conditions, the second sealing ring 4 and the groove 15 provided in the secondary rotor 2 may vibrate, which may cause harmful wear on the surface of the second sealing ring 4 or the secondary rotor 2. The sealing ring 17 has circumferential elasticity and elastic cooperation with the mounting groove 16 and the groove 15, which can reduce the wear of the key contact parts of the wheel center of the secondary rotor 2 to a certain extent. During operation, the sealing ring 17 will rotate synchronously with the second sealing ring 4. Under the action of centrifugal force, the sealing ring 17 will be tightly attached to the inner ring surface of the groove 15, thereby improving the radial sealing effect. At the same time, there will be a pressure difference between the cooling gas in the first chamber 5 and the second chamber 6. The pressure difference can press the sealing ring 17 against the side of the mounting groove 16 to improve the axial sealing effect of the sealing ring 17.

[0041] Furthermore, a number of deformation grooves are provided on the surface of the sealing ring 17. When the sealing ring 17 is in a high-temperature environment during operation, the deformation grooves can provide a certain space for the deformation of the sealing ring 17 when it expands due to heat, thereby preventing the sealing ring 17 from cracking due to thermal expansion and contraction, and improving the service life of the sealing ring 17.

[0042] like Figure 3-4 As shown, in some examples, the outer ring surface of the first sealing ring 3 is provided with a boss 18, and the position of the boss 18 in the first direction coincides with the position of the groove 15 in the first direction, so that the boss 18 can abut against the inner ring surface of the second sealing ring 4, and is used to support the end of the second sealing ring 4 extending into the groove 15 to suppress the vibration of the end of the second sealing ring 4 extending into the groove 15.

[0043] like Figure 4 As shown, when the boss 18 goes around the outer ring surface of the first sealing ring 3, the boss 18 will divide the first chamber 5 into two left and right areas. Therefore, it is necessary to open a third air hole 19 on the boss 18 and pass through the boss 18 along the axis of the boss 18. The third air hole connects the areas on the left and right sides of the boss 18 to ensure that the cooling gas flows normally in the first chamber 5.

[0044] like Figure 2As shown, the outer ring surface of the first journal 8 and the second journal 9 is chamber B, and the cooling gas in the third chamber 7 will be introduced into the B chamber from the first air hole 10. The cooling gas cools the right side of the outer ring surface of the first-stage rotor 1 and the left side of the outer ring surface of the second-stage rotor 2 in chamber B, and then leaves chamber B and enters the subsequent cooling structure. Chamber C is formed between the farthest end of the third sealing ring 12 away from the axis and the right side of the outer ring surface of the second-stage rotor 2, and the cooling gas in the fourth chamber 13 will finally directly enter chamber C to perform heat exchange on the right side of the outer ring surface of the second-stage rotor 2, cool the second-stage rotor 2, and be used for cooling the downstream disc cavity seal and rotor. Chamber B and chamber C are relatively independent and not interconnected. Therefore, the pressure distribution of chamber B and chamber C during operation will significantly affect the axial force of the first-stage rotor 1 and the second-stage rotor 2. Therefore, as shown in FIG. Figure 3 As shown, ventilation holes 20 are provided on the surface of the second sealing ring 4, and the ventilation holes connect the inner ring surface and the outer ring surface of the second sealing ring 4 to connect the first chamber 5 and the second chamber 6. The cooling gas with a higher pressure in the first chamber 5 and the second chamber 6 will be mixed with the cooling gas with a lower pressure through the ventilation holes 20. By adjusting the opening area and number of the ventilation holes, the mixing amount of the cooling gas in the first chamber 5 and the second chamber 6 can be controlled, and the temperature, pressure and air flow rate of the B and C air chambers can be adjusted to match the axial force of the rotor.

[0045] The above are merely preferred embodiments of the present invention and are not intended to limit the present invention. Those skilled in the art will readily appreciate that various modifications and variations of the present invention are possible. Any modifications, equivalent substitutions, or improvements made within the spirit and principles of the present invention shall be included within the scope of protection of the present invention.

Claims

1. A two-stage gas turbine rotor cooling structure, comprising a first-stage rotor (1) and a second-stage rotor (2), wherein the first-stage rotor (1) and the second-stage rotor (2) are both rotating bodies, and the first-stage rotor (1) and the second-stage rotor (2) are coaxially arranged along a first direction, characterized in that: A first sealing ring (3) is provided in both the first-stage rotor (1) and the second-stage rotor (2), and the outer diameter of the first sealing ring (3) is smaller than the inner diameter of the first-stage rotor (1) and the second-stage rotor (2); A second sealing ring (4) is inserted into the gap between the first-stage rotor (1) and the first sealing ring (3); the outer diameter of the second sealing ring (4) is smaller than the inner diameter of the first-stage rotor (1) and larger than the outer diameter of the first sealing ring (3); and one end of the second sealing ring (4) located inside the first-stage rotor (1) abuts against the side surface of the second-stage rotor (2) for sealing. The first sealing ring (3), the second sealing ring (4) and the secondary rotor (2) form a first chamber (5) for the flow of the first cooling gas, and a second chamber (6) for the flow of the second cooling gas is formed between the second sealing ring (4) and the primary rotor (1); The second side surface of the secondary rotor (2) is provided with a third journal (11), and the outer ring surface of the third journal (11) is clamped with a third sealing ring (12) through a step groove. The end of the third sealing ring (12) away from the third journal (11) extends along the second side surface of the secondary rotor (2) and does not exceed the outer ring surface of the secondary rotor (2). A fourth chamber (13) is formed between the third sealing ring (12) and the second side surface of the secondary rotor (2). The end of the inner ring surface of the third journal (11) away from the secondary rotor (2) protrudes from the inner ring surface of the third journal (11) and is in close contact with the outer ring surface of the first sealing ring (3). A second air hole (14) for communicating with the first chamber (5) and the fourth chamber (13) is provided at a position of the third journal (11) adjacent to the first chamber (5) and the fourth chamber (13).

2. A two-stage gas turbine rotor cooling structure according to claim 1, characterized in that: The primary rotor (1) comprises a first side surface and a second side surface that are opposite to each other along a first direction, and the secondary rotor (2) comprises a first side surface and a second side surface that are opposite to each other along the first direction; The first side surface of the primary rotor (1) is opposite to the first side surface of the secondary rotor (2), and a third chamber (7) communicating with the second chamber (6) is formed therebetween.

3. The two-stage gas turbine rotor cooling structure according to claim 2, characterized in that: A first journal (8) is provided on the first side of the first-stage rotor (1), and a second journal (9) is provided on the first side of the second-stage rotor (2). The first journal (8) and the second journal (9) abut against each other to close the side of the third chamber (7) away from the second chamber (6), and a first air hole (10) for discharging cooling gas in the third chamber (7) is provided on the first journal (8) or the second journal (9).

4. The two-stage gas turbine rotor cooling structure according to claim 1, characterized in that: A groove (15) is provided at a position where the first side surface of the secondary rotor (2) is adjacent to the inner ring surface of the secondary rotor (2), and the outer ring surface of one end of the second sealing ring (4) extending into the first rotor (1) abuts against the inner ring surface of the groove (15).

5. The two-stage gas turbine rotor cooling structure according to claim 4, characterized in that: An installation groove (16) is provided at one end of the outer ring surface of the second sealing ring (4) close to the groove (15), and a sealing expansion ring (17) is installed in the installation groove (16).

6. A two-stage gas turbine rotor cooling structure according to claim 5, characterized in that: The outer ring surface of the first sealing ring (3) is provided with a boss (18), the position of the boss (18) in the first direction coincides with the position of the groove (15) and abuts against the inner ring surface of the second sealing ring (4), and is used to support one end of the second sealing ring (4) extending into the groove (15).

7. A two-stage gas turbine rotor cooling structure according to claim 6, characterized in that: A third air hole (19) is provided on the boss (18) to connect two opposite sides of the boss (18) in the first direction.

8. The two-stage gas turbine rotor cooling structure according to claim 1, characterized in that: A ventilation hole (20) is provided on the surface of the second sealing ring (4), and the ventilation hole communicates with the inner ring surface and the outer ring surface of the second sealing ring (4), so that the first chamber (5) and the second chamber (6) are in communication.

9. The two-stage gas turbine rotor cooling structure according to claim 5, characterized in that: A thickened area (21) is provided on the first side surface of the secondary rotor (2), and the inner diameter of the thickened area (21) is larger than the inner diameter of the secondary rotor (2), so that the inner annular surface of the thickened area (21) and the inner annular surface of the secondary rotor (2) are misaligned to form a groove (15).

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