A pre-rotation pressurization integrated turbine rim seal cavity air supply optimization structure

Abstract

The application discloses a pre-rotation pressurization integrated turbine rim seal cavity air supply optimization structure and particularly relates to the field of aeroengines. The structure comprises oppositely arranged a moving disc and a stationary disc, and an axial sealing structure is arranged between the rim of the moving disc and the rim of the stationary disc. The stationary disc is provided with stationary vanes, and the sidewall of the moving disc is provided with moving vanes. A plurality of first impellers are arranged on the wall surface of the stationary disc. A plurality of pre-rotation inclined holes are arranged at the low radius position of the stationary disc. A second impeller is arranged on the wall surface of the moving disc, and the second impeller is located between the pre-rotation inclined hole and the first impeller. The inclination direction of the pre-rotation inclined hole and the bending direction of the second impeller are the same as the rotating direction of the moving disc, the bending direction of the first impeller is opposite to the bending direction of the second impeller, the second impeller and the first impeller are arranged alternately, and the initial end inclination angle of the second impeller is determined according to the inclination angle of the pre-rotation inclined hole. Based on the above structure, the sealing efficiency can be improved.

Description

Technical Field

[0001] This invention relates to the field of aero-engines, and in particular to an optimized structure for air supply to the pre-swirl supercharging integrated turbine rim sealing disk cavity. Background Technology

[0002] The rim seal is a crucial structure in aero-engine turbines, typically used to prevent high-temperature combustion gases from flowing back into the turbine cavity during engine operation. With the development of aero-engines, the temperature of the mainstream combustion gases has gradually increased, far exceeding the temperature resistance limits of materials. Therefore, efficient cooling technology is of great significance for promoting the development of aero-engines and ensuring their safe and stable operation. Current research indicates that increasing the pressure of the cooling gas is beneficial in preventing combustion gas intrusion. The commonly used method is to provide cooling gas through pre-swirl nozzles. After acceleration by the pre-swirl nozzles, the cooling gas has a higher circumferential velocity, resulting in a higher total circumferential pressure. This reduces the pressure difference between the mainstream and the turbine cavity, thereby reducing combustion gas intrusion. However, the total pressure increase achievable through pre-swirl nozzles is limited, and in some cases, its inhibitory effect on combustion gas intrusion is insufficient, leading to low sealing efficiency. Summary of the Invention

[0003] The main purpose of this application is to provide an optimized air supply structure for the pre-swirl booster integrated turbine rim sealing disk cavity, which aims to solve the problem of low sealing efficiency of existing turbine rim sealing structures.

[0004] To achieve the above objectives, this application provides an optimized air supply structure for a pre-swirl booster integrated turbine rim sealing disk cavity, comprising a moving disk and a stationary disk arranged opposite to each other, with an axial sealing structure between the rims of the moving disk and the stationary disk; stationary blades are provided on the stationary disk, and moving blades are provided on the sidewall of the moving disk; multiple first impellers are provided on the wall surface of the stationary disk, located inside the axial sealing structure and distributed sequentially along the circumference; multiple pre-swirl oblique holes are opened at the low radius position of the stationary disk, the inclination direction of the pre-swirl oblique holes being the same as the rotation direction of the moving disk; the moving disk's... A second impeller is installed on the wall surface, located between the pre-rotating inclined hole and the first impeller; the bending direction of the second impeller is the same as the rotation direction of the moving disk, while the bending direction of the first impeller is opposite to that of the second impeller; the lowest radius position of the first impeller is higher than the highest radius position of the second impeller, and the lowest radius position of the second impeller is higher than the radius position of the pre-rotating inclined hole; the distance between the first impeller and the wall surface of the moving disk is less than the axial height of the second impeller; the initial inclination angle of the second impeller is determined according to the inclination angle of the pre-rotating inclined hole.

[0005] Optionally, the second impeller includes a first straight segment, an arc segment, and a second straight segment connected in sequence. The first straight segment is tangent to the arc segment and is close to the pre-rotation inclined hole. The angle between the second straight segment and the circumferential direction is 0. The angle between the first straight segment and the circumferential direction is the initial inclination angle of the second impeller.

[0006] Optionally, the method for determining the initial tilt angle of the second impeller is as follows: obtain the pressure ratio of the pre-swirling inclined hole, determine the Mach number of the cold air at the outlet position of the pre-swirling inclined hole based on the pressure ratio of the pre-swirling inclined hole; determine the cold air velocity based on the cold air Mach number at the outlet position of the pre-swirling inclined hole, and determine the circumferential velocity of the cold air in combination with the tilt angle of the pre-swirling inclined hole; determine the relative circumferential velocity of the cold air based on the circumferential velocity of the cold air, the rotational angular velocity of the moving disk, and the radius position of the moving disk where the first straight segment is located; determine the radial velocity of the cold air, and determine the angle between the relative velocity of the airflow and the radial velocity based on the circumferential velocity of the cold air and the radial velocity of the cold air; determine the initial tilt angle of the second impeller based on the angle between the relative velocity of the airflow and the radial velocity.

[0007] Optionally, the difference between the relative velocity of the airflow and the radial angle and the initial tilt angle of the second impeller is ±5°.

[0008] Optionally, the first impeller is arc-shaped, and the initial inclination angle of the first impeller is 5~15°.

[0009] Optionally, the equation for determining the pressure surface profile of the first impeller is: ; The equation for determining the suction surface profile of the first impeller is: ; In the formula, ( x , y () represents the coordinates of the profile.

[0010] Optionally, the pre-rotated inclined hole has an inclination angle of 50-70° relative to the axial direction.

[0011] Optionally, the pre-rotated oblique hole includes an inlet section, a transition section, and an outlet section, with the diameter of the inlet section being larger than that of the outlet section.

[0012] Optionally, the axial sealing structure includes a first sealing ring disposed on the outer edge of the stationary plate, a second sealing ring disposed on the wall of the stationary plate, the second sealing ring being located inside the first sealing ring, and a gap being formed between the second sealing ring and the first sealing ring; a third sealing ring disposed on the wall of the moving plate, the third sealing ring extending into the gap.

[0013] Optionally, the number of the second impeller is a multiple of the number of moving blades.

[0014] Compared with the prior art, the beneficial effects of this application are as follows: The pre-swirl booster integrated turbine rim sealing disc cavity air supply optimization structure of the present invention features a pre-swirl inclined hole on the stationary disc, with the inclination direction of the pre-swirl inclined hole being the same as the rotation direction of the moving disc. The inclination angle increases the circumferential velocity of the incoming cold air. A first impeller is mounted on the stationary disc, and a second impeller is mounted on the moving disc, located between the pre-swirl inclined hole and the first impeller. When the cold air entering the disc cavity flows radially outward along the rotating wall, it will be worked by the second impeller, increasing the total pressure of the cold air. Then, the first impeller converts part of the circumferential total pressure into static pressure. This reduces the total pressure difference between the mainstream and the cavity, enhances the cold air outflow, and reduces the static pressure difference between the mainstream and the cavity, reducing gas intrusion and thus improving sealing efficiency. Attached Figure Description

[0015] Figure 1 This is a schematic diagram of the optimized air supply structure for the pre-swirl booster integrated turbine rim sealing disc cavity according to this application; Figure 2 for Figure 1 Schematic diagram of the central moving plate; Figure 3 for Figure 1 Schematic diagram of the structure of the second impeller; Figure 4 for Figure 1 Schematic diagram of the structure of the middle static plate; Figure 5 for Figure 1 A schematic diagram of the structure of the first impeller in the middle; Figure 6 This is a flowchart illustrating the method for determining the initial tilt angle of the second impeller in the pre-swirl booster integrated turbine rim sealing disk cavity air supply optimization structure of this application; Figure 7 for Figure 1 Schematic diagram of the pre-rotated inclined hole; Figure 8 for Figure 1 Cross-sectional view of the middle stationary plate; Figure 9 This is a graph showing the variation of sealing efficiency within the disk cavity with dimensionless radius position under the same working conditions for three models in this application embodiment; Figure 10 This diagram illustrates the variation of dimensionless static pressure of airflow within the disk cavity with the dimensionless radius position under the same operating conditions for three models in this application embodiment.

[0016] In the diagram, 1. stationary blade, 2. moving blade, 3. stationary disk, 4. moving disk, 5. first impeller, 6. second impeller, 7. pre-rotation oblique hole, 8. first sealing ring, 9. second sealing ring, 10. third sealing ring.

[0017] The realization of the purpose, functional features and advantages of this application will be further explained in conjunction with the embodiments and with reference to the accompanying drawings. Detailed Implementation

[0018] To make the objectives, technical solutions, and advantages of this application clearer, the technical solutions of this application will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some embodiments of this application, not all embodiments. Based on the embodiments of this application, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of this application.

[0019] Embodiments of the present invention provide an optimized air supply structure for a pre-swirl supercharging integrated turbine rim sealing disc cavity, such as... Figure 1 As shown, the device includes a moving disk 4 and a stationary disk 3 arranged opposite to each other. An axial sealing structure is provided between the rims of the moving disk 4 and the stationary disk 3. A stationary blade 1 is provided on the stationary disk 3, and a moving blade 2 is provided on the side wall of the moving disk 4. Multiple first impellers 5 are provided on the wall surface of the stationary disk 3, located inside the axial sealing structure and distributed sequentially along the circumference of the stationary disk 3. Multiple pre-rotation inclined holes 7 are opened at the low radius position of the stationary disk 3, and the inclination direction of the pre-rotation inclined holes 7 is the same as the rotation direction of the moving disk 4. A second impeller 6 is provided on the wall surface of the moving disk 4. Wheel 6 is located between the pre-rotating inclined hole 7 and the first impeller 5; the bending direction of the second impeller 6 is the same as the rotation direction of the moving disk 4, the bending direction of the first impeller 5 is opposite to the bending direction of the second impeller 6, the distance between the first impeller 5 and the wall of the moving disk 4 is less than the axial height of the second impeller 6; the lowest radius position of the first impeller 5 is higher than the highest radius position of the second impeller 6, and the lowest radius position of the second impeller 6 is higher than the radius position of the pre-rotating inclined hole 7; the initial inclination angle of the second impeller 6 is determined according to the inclination angle of the pre-rotating inclined hole 7.

[0020] In this embodiment, during turbine operation, the axially flowing cold air enters the disk cavity between the moving disk 4 and the stationary disk 3 with a high circumferential velocity after passing through the pre-swirling oblique hole 7, and impacts the wall of the moving disk 4. Under the action of the rotor pump effect, the cold air flows radially outward along the wall of the moving disk 4 and enters the region of the second impeller 6. Since the second impeller 6 does work on the cold air, the circumferential velocity and total pressure of the cold air are further increased. Then the cold air enters the first impeller 5, which converts the dynamic pressure head of the cold air with high circumferential velocity into static pressure. The airflow decelerates and increases pressure in the flow channel of the first impeller 5, thereby increasing the pressure at the high radius position in the disk cavity, thereby reducing the pressure difference between the disk cavity and the mainstream, weakening the driving force of gas intrusion, and improving sealing efficiency. Since the existing method increases the total pressure by enhancing the swirling flow, the static pressure in the cavity will actually decrease, which often leads to a lower-than-expected increase in total pressure and less improvement in sealing efficiency. Therefore, this invention increases the static pressure by using the first impeller 5.

[0021] The axial sealing structure includes a first sealing ring 8 disposed on the outer edge of the stationary plate 3, a second sealing ring 9 disposed on the wall surface of the stationary plate 3, the second sealing ring 9 being located inside the first sealing ring 8, and a gap being formed between the second sealing ring 9 and the first sealing ring 8; and a third sealing ring 10 disposed on the wall surface of the moving plate 4, the third sealing ring 10 extending into the gap.

[0022] Furthermore, such as Figure 2-3 As shown, the second impeller 6 includes a first straight segment, an arc segment, and a second straight segment connected in sequence. The first straight segment is tangent to the arc segment and is close to the pre-rotation oblique hole 7. The angle between the first straight segment and the circumferential direction is the initial inclination angle b of the second impeller 6. During operation, the cold air flows along the first straight segment, the arc segment, and the second straight segment. The first impeller 5 is arc-shaped. Because the tail of the second impeller 6 (the second straight segment) is shaped as a straight line in the radial direction, the rotational ratio of the airflow after being worked on by the second impeller 6 remains approximately 1. This means that after the airflow exits the second impeller 6, the velocity direction is approximately close to the circumferential direction. Therefore, as... Figure 4-5 As shown, in this embodiment, the initial inclination angle c of the first impeller 5 is set to 5~15°, which ensures that a large separation angle will not be generated when the airflow flows into the area of ​​the first impeller 5. The distance between the first impeller 5 and the wall of the moving disk 4 is less than the axial height of the second impeller 6, so that the second impeller 6 and the first impeller 5 are axially staggered, which facilitates the better transition of cold air from the second impeller 6 to the flow channel of the first impeller 5.

[0023] In one exemplary embodiment, such as Figure 6 As shown, the method for determining the initial inclination angle of the second impeller 6 is as follows: Step 1: Obtain the pre-swirl orifice pressure ratio. Based on the pre-swirl orifice pressure ratio, determine the Mach number of the cold gas at the outlet position of the pre-swirl orifice 7, i.e., the cold gas outlet Mach number. The expression is as follows: ; In the formula, The adiabatic index, This refers to the Mach number at the cold air outlet. The pressure ratio for the pre-rotated inclined hole.

[0024] Step 2: Determine the cold air flow rate based on the Mach number of the cold air outlet, and determine the circumferential velocity of the cold air by combining it with the tilt angle of the pre-swirl orifice 7, as shown in the following expression: ; ; In the formula, The airflow velocity is the cold air velocity. The gas constant is... The temperature is 3 for the static plate. The tilt angle of the pre-rotated inclined hole 7. This represents the circumferential velocity of the cold air.

[0025] Step 3: Based on the circumferential velocity of the cold air, the rotational angular velocity of the moving disk 4, and the radius position of the moving disk where the first straight segment is located, determine the relative circumferential velocity of the cold air, as expressed below: ; In the formula, The relative circumferential velocity of the cold air. This represents the radius of the moving disk where the first straight line segment is located, i.e., the perpendicular distance between the first straight line segment and the center of the moving disk. ω is the rotational angular velocity of the moving disk 4.

[0026] Step 4: Determine the radial velocity of the cold air, and based on the relative circumferential velocity and radial velocity of the cold air, determine the angle between the relative velocity and radial velocity of the airflow, as shown in the following expression: ; ; In the formula, The angle between the relative velocity of the airflow and the radial direction. For airflow, Let be the cross-sectional area of ​​the disk cavity. This represents the radial velocity of the cold air.

[0027] Step 5: Determine the initial tilt angle of the second impeller 6 (moving disc impeller) based on the relative velocity of the airflow and the radial angle; For example, the difference between the relative velocity of the airflow and the radial angle and the initial tilt angle of the second impeller 6 is ±5°.

[0028] In another exemplary embodiment, the equation for determining the pressure surface profile of the first impeller 5 is: ; The equation for determining the suction surface profile of the first impeller 5 is: ; In the formula, ( x , y () represents the coordinates of the profile.

[0029] For example, such as Figure 7-8As shown, the inclination angle α of the pre-swirling oblique orifice 7 relative to the axial direction is 50-70°. The pre-swirling oblique orifice 7 includes an inlet section, a transition section, and an outlet section, with the diameter of the inlet section being larger than that of the outlet section. The transition section is conical in shape with a cone angle of 30°. Preferably, the diameter of the inlet section is greater than or equal to twice the diameter of the outlet section, and the length of the outlet section is less than or equal to three times the diameter of the outlet section. The outlet end of the pre-swirling oblique orifice 7 has a rounded corner with a radius of 0.2-0.4 mm to improve the flow coefficient of the oblique orifice. The height of the second impeller 6 is less than or equal to half the width of the disk cavity, the thickness is 0.5-1 mm, and the outer edge has a rounded corner of 0.2-0.5 mm. The height of the first impeller 5 is less than or equal to 4 / 5 of the width of the disk cavity, and its thickness is 0.4-2mm. Its outer edge has a 0.2-0.5mm rounded corner. The axial height of the overlap between the first impeller 5 and the second impeller 6 (the difference between the distance between the first impeller 5 and the wall of the moving disk 4 and the axial height of the second impeller 6) is 1 / 4-2 / 5 of the width of the disk cavity. The radial distance between the beginning of the first impeller 5 and the end of the second impeller 6 is 1.5-3mm. The number of first impellers 5 is a multiple of the number of stationary blades 1, specifically determined by the size of the disk cavity. The number of second impellers 6 is a multiple of the number of moving blades 2, specifically determined by the size of the disk cavity. The number of first impellers 5 and the number of second impellers 6 should not be multiples of each other to avoid resonance. The number of second impellers 6 and the number of pre-rotating oblique holes 7 should not have a common divisor to avoid resonance.

[0030] The method for determining the number of pre-rotated inclined holes 7 is as follows: Since the airflow rate and supply pressure of the cold air used for a certain structure in an aero-engine are relatively fixed, the airflow rate and supply pressure must be matched when designing the pre-swirling oblique orifice 7. Specifically, the total pre-swirling flow area is calculated based on the flow coefficient, airflow rate, and supply pressure of the pre-swirling oblique orifice 7; the diameter and number of pre-swirling oblique orifices 7 are initially determined based on the total pre-swirling flow area to obtain a preliminary pre-swirling oblique orifice 7 structure; then, the airflow rate and pressure of this structure are obtained through numerical calculation, and the process is iteratively modified until the airflow rate and supply pressure are matched.

[0031] Example Detailed 3D modeling and numerical simulation verification were performed on the turbine structure of this invention and two comparative structures. In the 3D model of this invention, there are 17 pre-swirling oblique holes 7 with an inclination angle of 60° (towards the axial direction). The inlet diameter of the pre-swirling oblique hole 7 is 3.2 mm, and the outlet diameter is 1.6 mm. There are 120 second impellers 6 and 72 first impellers 5. The radial distance between the beginning of the first impeller 5 and the end of the second impeller 6 is 1.8 mm. The difference between comparative structure 1 (basic type) and this invention (improved type) is that the inclination angle of the pre-swirling holes is 0, and the first impeller 5 and the second impeller 6 are not set; the difference between comparative structure 2 (single-acting impeller) and this invention is that the first impeller 5 is not set. In the numerical simulation, the mainstream flow conditions are kept consistent with the cold air intake flow rate, the rotation speed is set to 18000 rpm, and the sealing cold air flow rate is 150 g / s. The simulation results are shown in […]. Figure 9-10 .

[0032] The sealing efficiency of the disk cavity calculated by the three models under the same working conditions (Sealing efficiency is between 0 and 1; the closer to 0, the more severe the gas intrusion, and vice versa.) This varies with the dimensionless radius. r The variation law of position (dimensionless radius refers to the ratio of the local radius to the maximum radius of the moving disk 4, used to characterize the relative radial position within the disk cavity), such as... Figure 9 As can be seen from the figure, the sealing efficiency of the model cavity of the present invention is improved compared with the other two models. The sealing efficiency is significantly improved at the high radius position (close to the sealing ring seam), with the sealing efficiency increasing from 0.8 to more than 0.95, while the sealing efficiency of the single-acting impeller is the lowest. Figure 10 The dimensionless static pressure Cp law shown is consistent with the sealing efficiency, where the dimensionless static pressure is the static pressure of the airflow inside the cavity. P Static pressure at the circumferential seam outlet of the wheel rim P OUT The ratio. Since the mainstream conditions remain unchanged, the hydrostatic pressure at the rim circumferential gap exit... P OUT It can be considered unchanged. (From) Figure 10 It can be seen that the dimensionless static pressure inside the cavity of the improved model is greater than that of the basic model and the single-acting impeller model. This indicates that under the same cold air conditions, the static pressure inside the cavity of the improved model is greater and the pressure difference with the mainstream is smaller. Therefore, the driving force for gas intrusion is smaller and the sealing efficiency is greater.

[0033] The reason for this situation is that during operation, the axially flowing cold air enters the disk cavity with a high circumferential velocity after passing through the pre-swirling oblique hole 7, and impacts the wall of the moving disk 4. Under the action of the rotor pump effect, the cold air flows radially outward along the wall of the moving disk 4 and enters the region of the second impeller 6. Since the second impeller 6 does work on the cold air, the circumferential velocity and total pressure of the cold air are further increased. The function of the first impeller 5 is to convert the dynamic pressure head of the cold air with high circumferential velocity into static pressure. The airflow decelerates and increases in pressure within the flow channel of the first impeller 5, thereby increasing the pressure at the high radius position within the disk cavity. However, with only the second impeller 6, the circumferential velocity of the airflow increases while the static pressure decreases, which leads to an increase in the pressure difference between the cavity and the mainstream, thus reducing the sealing performance. Figure 10 This also reflects that the static pressure inside the cavity of the improved model with the first impeller 5 and the second impeller 6 is greater than that of the basic model and the single-acting impeller model.

[0034] The above are merely preferred embodiments of this application and do not limit the patent scope of this application. Any equivalent structural or procedural transformations made using the content of this application's specification and drawings, or direct or indirect applications in other related technical fields, are similarly included within the patent protection scope of this application.

Claims

1. An optimized air supply structure for a pre-swirl supercharging integrated turbine rim sealing disc cavity, characterized in that, It includes a moving plate and a stationary plate that are arranged opposite to each other, and an axial sealing structure is provided between the rims of the moving plate and the rims of the stationary plate; The stationary plate is equipped with stationary blades, and the moving plate is equipped with moving blades on its side wall; Multiple first impellers are provided on the wall of the stationary disc. The multiple first impellers are located inside the axial sealing structure and are distributed sequentially along the circumference. Multiple pre-rotation inclined holes are provided at the low radius position of the stationary disk, and the inclination direction of the pre-rotation inclined holes is the same as the rotation direction of the moving disk. A second impeller is provided on the wall of the moving disk, and the second impeller is located between the pre-rotation inclined hole and the first impeller; The bending direction of the second impeller is the same as the rotation direction of the moving disk, while the bending direction of the first impeller is opposite to the bending direction of the second impeller. The lowest radius position of the first impeller is higher than the highest radius position of the second impeller, and the distance between the first impeller and the wall of the moving disk is less than the axial height of the second impeller; The lowest radius position of the second impeller is higher than the radius position of the pre-rotation inclined hole; The initial inclination angle of the second impeller is determined based on the inclination angle of the pre-rotating inclined hole.

2. The pre-swirl booster integrated turbine rim sealing disk cavity air supply optimization structure according to claim 1, characterized in that, The second impeller includes a first straight segment, an arc segment, and a second straight segment connected in sequence. The first straight segment is tangent to the arc segment and is close to the pre-rotation inclined hole. The second straight segment has an angle of 0 with the circumferential direction. The angle between the first straight segment and the circumferential direction is the initial inclination angle of the second impeller.

3. The pre-swirl booster integrated turbine rim sealing disk cavity air supply optimization structure according to claim 2, characterized in that, The method for determining the initial inclination angle of the second impeller is as follows: Obtain the pressure ratio of the pre-swirling inclined hole, and determine the Mach number of the cold gas at the outlet position of the pre-swirling inclined hole based on the pressure ratio of the pre-swirling inclined hole; The cold air velocity is determined by the cold air Mach number at the outlet position of the pre-swirling orifice, and the circumferential velocity of the cold air is determined by combining the inclination angle of the pre-swirling orifice. The relative circumferential velocity of the cold air is determined based on the circumferential velocity of the cold air, the rotational angular velocity of the moving disk, and the radius position of the moving disk where the first straight segment is located. Determine the radial velocity of the cold air, and determine the relative velocity of the airflow and the radial angle based on the circumferential velocity and radial velocity of the cold air; The initial tilt angle of the second impeller is determined based on the relative velocity of the airflow and the radial angle.

4. The pre-swirl booster integrated turbine rim sealing disk cavity air supply optimization structure according to claim 3, characterized in that, The difference between the relative velocity of the airflow and the radial angle and the initial tilt angle of the second impeller is ±5°.

5. The pre-swirl booster integrated turbine rim sealing disk cavity air supply optimization structure according to claim 2, characterized in that, The first impeller has an arc shape, and the initial inclination angle of the first impeller is 5~15°.

6. The pre-swirl booster integrated turbine rim sealing disk cavity air supply optimization structure according to claim 1, characterized in that, The equation for determining the pressure surface profile of the first impeller is: ； The equation for determining the suction surface profile of the first impeller is: ； In the formula, ( x , y () represents the coordinates of the profile.

7. The pre-swirl booster integrated turbine rim sealing disk cavity air supply optimization structure according to claim 1, characterized in that, The pre-rotated inclined hole has an inclination angle of 50-70° relative to the axial direction.

8. The pre-swirl booster integrated turbine rim sealing disk cavity air supply optimization structure according to claim 1, characterized in that, The pre-rotated inclined hole includes an inlet section, a transition section, and an outlet section, with the diameter of the inlet section being larger than that of the outlet section.

9. The optimized air supply structure for the pre-swirl supercharging integrated turbine rim sealing disk cavity as described in claim 1, characterized in that, The axial sealing structure includes a first sealing ring disposed on the outer edge of the stationary plate, a second sealing ring disposed on the wall of the stationary plate, the second sealing ring being located inside the first sealing ring, and a gap being formed between the second sealing ring and the first sealing ring; a third sealing ring disposed on the wall of the moving plate, the third sealing ring extending into the gap.

10. The pre-swirl booster integrated turbine rim sealing disk cavity air supply optimization structure according to claim 1, characterized in that, The number of the second impeller is a multiple of the number of moving blades.

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