A turbine internal cooling air nozzle structure

Abstract

The present application belongs to the field of aero-engine cooling design and is a turbine internal cooling air nozzle structure, including a cooling air nozzle, an air collecting box, a front plate inner ring, and a rear inner ring. A certain gap is reserved between the upper edge clamp ring and the cup holder, and between the lower edge clamp ring and the support ring, allowing for free movement. However, the positions of the upper edge clamp ring and the lower edge clamp ring limit the relative movement. During operation, the cooling air nozzle will move toward the side away from the cup holder until the lower edge clamp ring is completely overlapped on the support ring, increasing the overlap of the cooling air nozzle. Even considering the incompatibility between the extreme tolerance and thermal deformation, the cooling air nozzle will not be affected by the rear half boss, and will not be dislocated or dislodged, achieving reliable overlap. Since the position of the cooling air nozzle is stable, it can also stably cooperate with the cup holder, ensuring that the cooling air flow path is unobstructed, so that the air flow pressure in the front cavity of the turbine disc is sufficient, and ensuring that the front cavity of the turbine disc meets the design requirements for cooling the turbine rotor blades and the chamber sealing.

Description

Technical Field

[0001] The present application relates to the field of aero-engine cooling design, and in particular to a turbine internal cooling air nozzle structure. Background Art

[0002] As aircraft engines evolve toward higher thrust-to-weight ratios and higher turbine inlet temperatures, the operating temperatures of engine hot-end components are rising. Components like turbine blades are being subjected to increasingly harsh operating environments characterized by high temperatures, high pressures, and high rotational speeds. While turbine blade materials limit their temperature tolerance, advanced turbine cooling technologies can improve turbine performance and blade life. A widely adopted cooling method, both domestically and internationally, utilizes cooling air drawn from the compressor to cool the turbine guide vanes and rotor blades before discharging into the turbine duct to mix with the combustion gas. The cooling air nozzle, a crucial component of the cooling airflow path, is commonly used to connect the turbine guide vanes to the inner ring of the guide vanes.

[0003] Figure 1 It is an existing cold air nozzle structure. The upper spherical surface of the cold air nozzle 1 is inserted into the cup holder 2, and the lower spherical surface is inserted into the support ring 9 of the front half inner ring 3. The lower edge corner 6 of the cold air nozzle 1 is overlapped on the rear half boss 7 of the rear half inner ring 4. The cooling air flows out from the air outlet 8 on the air collecting box 5 and is introduced into the chamber formed by the front half inner ring 3 and the rear half inner ring 4 through the cup holder 2 and the cold air nozzle 1. Then the airflow is introduced into the front cavity of the turbine disk to supply air for cooling the turbine rotor blades and seal the cavity.

[0004] The main disadvantages of the existing air conditioning nozzle structure are:

[0005] 1) The lower spherical surface of the cold air nozzle is inserted into the support ring hole of the front inner ring. Positioning is achieved by partially overlapping the lower edge corner with the rear boss in the axial direction. This overlap is small, approximately 1 / 8 the arc length of the lower edge corner. Considering the extreme tolerances and the mismatch between the axial thermal deformation of the front inner ring and the rear boss, the overlapped portion of the lower edge corner of the cold air nozzle is at risk of dislocation from the rear boss, making the overlap unreliable.

[0006] 2) When the cooling air nozzle is disconnected, the flow area is blocked, the cooling air flow path is blocked, and the air pressure introduced into the front cavity of the turbine disc is insufficient. On the one hand, this will lead to insufficient cooling air supply for the turbine rotor blades, causing the blades to overheat. On the other hand, insufficient chamber sealing pressure will cause the risk of gas backflow.

[0007] 3) After the air conditioning nozzle is disconnected, it will vibrate irregularly in the inner ring due to the airflow, which is not conducive to the vibration of the whole machine.

[0008] Therefore, how to ensure the reliable overlap of the air conditioning nozzle is a problem that needs to be solved. Summary of the Invention

[0009] The purpose of this application is to provide a turbine internal cooling air nozzle structure to solve the problems of small overlap, easy detachment and insufficient sealing of the cooling air nozzle in the prior art.

[0010] The technical solution of the present application is: a turbine internal cooling air nozzle structure, comprising a cooling air nozzle, an air collecting box, a front half inner ring and a rear half inner ring; the cooling air nozzle is provided with a coaxially arranged annular lower edge clamp ring and an upper edge clamp ring, the support ring of the front half inner ring is provided with a mounting hole for the lower spherical surface of the cooling air nozzle, the lower edge clamp ring can be completely overlapped on the support ring of the front half inner ring, a cup holder is welded on the air collecting box, and the cup holder is sleeved on the upper spherical surface of the cooling air nozzle.

[0011] Preferably, an annular upper edge clamp ring is coaxially provided on the cold air nozzle, and the upper edge clamp ring can overlap and cooperate with the cup holder.

[0012] Preferably, an annular support ring is coaxially arranged on the side of the front half inner ring close to the rear half inner ring, a mounting hole is opened on the support ring, the cold air nozzle is inserted into the mounting hole, and the front half boss is integrally connected to the side of the support ring close to the rear half boss.

[0013] Preferably, the front half boss is overlapped with the rear half inner ring.

[0014] Preferably, an annular rear half boss is provided on the rear half inner ring, and the rear half boss is overlapped with the front half boss.

[0015] The present invention discloses a turbine internal cooling air nozzle structure comprising a cooling air nozzle, an air collecting box, a front inner ring, and a rear inner ring. A certain gap is reserved between the upper edge clamp ring and the cup holder, and between the lower edge clamp ring and the support ring, allowing for free floating. However, the position of the upper and lower edge clamp rings limits the relative movement of the cooling air nozzle therewith. During operation, the cooling air nozzle moves toward the side away from the cup holder until the lower edge clamp ring completely overlaps the support ring, increasing the overlap of the cooling air nozzle. Even considering the incompatibility between the extreme tolerance and thermal deformation, the cooling air nozzle is not affected by the rear inner ring and will not be dislocated or dislodged, achieving a reliable overlap. Because the cooling air nozzle is in a stable position, it can also stably cooperate with the cup holder, ensuring an unobstructed cooling air flow path, sufficient airflow pressure in the front cavity of the turbine disc, and ensuring that the front cavity of the turbine disc meets the design requirements for cooling the turbine rotor blades and the chamber seal. With the support of the lower edge clamp ring and the support ring, the cooling air nozzle is reliably overlapped and reliably positioned under the action of airflow. BRIEF DESCRIPTION OF THE DRAWINGS

[0016] In order to more clearly illustrate the technical solutions provided by this application, the following is a brief introduction to the accompanying drawings. Obviously, the accompanying drawings described below are only some embodiments of this application.

[0017] Figure 1It is a schematic diagram of the overlapping structure of the air conditioning nozzle in the background technology;

[0018] Figure 2 This is a schematic diagram of the overlapping structure of the air conditioning nozzle in this application.

[0019] 1. Air conditioning nozzle; 2. Cup holder; 3. Front inner ring; 4. Rear inner ring; 5. Air collecting box; 6. Lower edge clamping angle; 7. Rear boss; 8. Air outlet; 9. Support ring; 10. Front boss; 11. Lower edge clamping ring; 12. Upper edge clamping ring; 13. Turbine guide blades. DETAILED DESCRIPTION

[0020] In order to make the purpose, technical solutions and advantages of the implementation of this application clearer, the technical solutions in the embodiments of this application will be described in more detail below in conjunction with the drawings in the embodiments of this application.

[0021] A turbine internal cooling air nozzle structure, such as Figure 2 As shown, it includes a cooling air nozzle 1, an air collecting box 5, a front inner ring half 3, and a rear inner ring half 4. The air collecting box 5 is welded to the turbine guide blade 13. The air collecting box 5 has a hollow interior and communicates with the cooling channels inside the turbine guide blade 13. The air collecting box 5 has an air outlet 8 and is welded to a cup holder 2. The cup holder 2 is a cylindrical hollow structure and communicates with the interior of the air collecting box 5 through the air outlet 8.

[0022] In the working state, the turbine guide blades 13 and the front and rear inner rings 3 and 4 have different deformations due to different temperatures and stress conditions. A certain gap needs to be reserved to offset the thermal deformation, so the cold air nozzle 1 needs to have a certain sliding amount.

[0023] The air conditioning nozzle 1 is coaxially arranged on the inner side of the cup holder 2. A coaxially arranged annular lower edge clamp ring 11 is provided on the air conditioning nozzle 1. The front half inner ring 3 and the rear half inner ring 4 are coaxially arranged with the turbine disk. The front half inner ring 3 is provided with an annular support ring 9 coaxially arranged with the turbine disk. The lower edge clamp ring 11 can be overlapped on the support ring 9. The cup holder 2 is welded on the air collecting box 5, and the cup holder 2 is sleeved on the upper spherical surface of the air conditioning nozzle 1.

[0024] The cooling air first enters the air collecting box 5 from the turbine guide vanes 13, then enters the cup holder 2 and the cooling air nozzle 1 through the air outlet 8, and then enters the chamber formed by the front half inner ring 3 and the rear half inner ring 4 through the cooling air nozzle 1. The air flow is then introduced into the front cavity of the turbine disk to supply air for cooling the turbine rotor blades and to seal the chamber.

[0025] A certain gap is reserved between the upper edge clamp ring 12 of the cold air nozzle and the cup holder 2, and between the lower edge clamp ring 11 and the support ring 9, allowing for free movement. However, the position of the upper and lower edge clamp rings limits the relative movement. During operation, the cold air nozzle will move toward the side away from the cup holder 2 until the lower edge clamp ring 11 completely overlaps the support ring 9, increasing the overlap of the cold air nozzle. Even considering the incompatibility between the extreme tolerance and thermal deformation, the cold air nozzle will not be affected by the rear half boss 7 and will not be dislocated or dislodged, achieving a reliable overlap. Because the position of the cold air nozzle is stable, it can also stably cooperate with the cup holder 2, ensuring that the cooling air flow path is unobstructed, so that the airflow pressure in the front cavity of the turbine disk is sufficient, and the front cavity of the turbine disk meets the design requirements for cooling the turbine rotor blades and the chamber sealing. Under the support and positioning of the lower edge clamp ring 11 and the support ring 9, the cold air nozzle is reliably overlapped and reliably positioned under the action of airflow.

[0026] Preferably, an annular upper edge clamp ring 12 is coaxially provided on the air conditioning nozzle 1, and the upper edge clamp ring 12 can overlap with the cup holder 2 to prevent the upper spherical surface of the air conditioning nozzle 1 from moving into the air collecting box 5. In conjunction with the lower edge clamp ring 11, the travel on both sides of the air conditioning nozzle 1 is limited to ensure that the air conditioning nozzle 1 works within a suitable position range.

[0027] Preferably, an annular support ring 9 is coaxially disposed on the side of the front inner ring 3 near the rear inner ring 4. The support ring 9 has a mounting hole, into which the air conditioning nozzle 1 is inserted. The front boss 10 is integrally connected to the side of the support ring 9 near the rear boss 7. With the support ring 9, the air conditioning nozzle 1 is now limited only by the support ring 9 and the cup holder 2, rather than by the support ring 9, the rear boss 7, and the cup holder 2. This makes assembly and positioning of the air conditioning nozzle 1 more convenient and precise.

[0028] Preferably, the front half boss 10 overlaps with the rear half inner ring boss 7 , and the cold air nozzle 1 has no contact with the rear half inner ring 4 .

[0029] Preferably, an annular rear half boss 7 is provided on the rear half inner ring 4 , and the rear half boss 7 and the front half boss 10 are stably supported.

[0030] The above description is merely a specific embodiment of the present application, but the scope of protection of the present application is not limited thereto. Any changes or substitutions that can be easily conceived by a person skilled in the art within the technical scope disclosed in this application should be included in the scope of protection of the present application. Therefore, the scope of protection of the present application should be based on the scope of protection of the claims.

Claims

1. A turbine internal cooling air nozzle structure, characterized in that: It comprises an air-conditioning nozzle (1), an air collecting box (5), a front inner ring (3) and a rear inner ring (4); the air-conditioning nozzle (1) is provided with a coaxially arranged annular lower edge clamp (11) and an upper edge clamp (12); the support ring (9) of the front inner ring (3) is provided with a mounting hole for the air-conditioning nozzle (1); the lower edge clamp (11) can be overlapped on the support ring (9); a cup seat (2) is welded on the air collecting box (5), and the cup seat (2) is sleeved on the upper spherical surface of the air-conditioning nozzle (1); the air-conditioning nozzle (1) is coaxially provided with an annular upper edge clamp (12), the upper edge clamp (12) can overlap with the cup seat (2) to prevent the upper spherical surface of the air-conditioning nozzle (1) from moving and extending into the air collecting box (5), and cooperates with the lower edge clamp (11) to limit the travel of both the inner and outer sides of the air-conditioning nozzle (1); A certain gap is reserved between the clamping ring (12) on the upper edge of the air conditioner nozzle and the cup holder (2).

2. The turbine internal cooling air nozzle structure according to claim 1, characterized in that: An annular support ring (9) is coaxially arranged on one side of the front inner ring (3) close to the rear inner ring (4), and a mounting hole is provided on the support ring (9), and the air conditioning nozzle (1) is inserted into the mounting hole. An annular rear half boss (7) is provided on the rear inner ring (4), and the rear half boss (7) overlaps and cooperates with the front half boss (10); the front half boss (10) is integrally connected to the side of the support ring (9) close to the rear half boss (7).

3. The turbine internal cooling air nozzle structure according to claim 2, wherein: The front half boss (10) is overlapped with the rear half inner ring (4).

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