A structure for suppressing wind resistance and temperature rise of turntable cavity of aircraft engine

Abstract

The present invention relates to the technical field of aircraft engines, and specifically to an aircraft engine structure for suppressing wind resistance and temperature rise of a turntable cavity, comprising: a cylinder, an annular partition and a pre-swirl air supply pipe, wherein the cylinder is sleeved on a high-pressure turbine shaft and a low-pressure turbine shaft between a high-pressure turbine disk and a low-pressure turbine disk; two annular partitions are sleeved and fixed in the radial direction of the end of the cylinder, and the axial direction of the outer peripheral end of the annular partition is connected to the engine casing, a gap is formed between each annular partition and the corresponding turbine disk, and an air flow outlet is formed between the outer peripheral end of the annular partition and the outer peripheral end of the corresponding turbine disk; an air supply cavity is formed between the cylinder, the engine casing and the two annular partitions; a plurality of pre-swirl air supply pipes are obliquely arranged on the opposite surfaces of the two annular partitions, wherein the outlet direction of the pre-swirl air supply pipe on the annular partition close to the corresponding turbine disk is the same as the rotation direction of the turbine disk. The device reduces the relative movement speed between the airflow and the turbine disk, thereby reducing the wind resistance and temperature rise.

Description

Technical Field

[0001] The invention relates to the technical field of aeroengines, and in particular to a structure for suppressing wind resistance and temperature rise of a turntable cavity of an aeroengine. Background Art

[0002] The turbine disk is a key component in an aircraft engine. Its working environment is very harsh. It not only has to withstand high temperature and pressure, but also has to experience high-speed rotation and vibration. Controlling the temperature of the turbine disk to keep it within the long-term allowable range of the material is a very important design indicator.

[0003] The counter-rotating disc cavity refers to the cavity between the high-pressure turbine disc and the low-pressure turbine disc. The three-dimensional diagram of the fluid domain of the typical counter-rotating disc cavity is shown in the figure below: Figure 5 As shown, for the convenience of display, a circumferential 1 / 72 sector is selected. The high-pressure turbine disc shaft and the low-pressure turbine disc shaft assembly rotate in opposite directions at high speeds, and the maximum relative speed can reach 25,000 rpm in the ground takeoff state. Windage temperature rise refers to the temperature rise caused by the friction between the high-speed rotating turbine disc and the airflow inside the disc cavity. When the inlet flow rate is small, the windage temperature rise will reach a very high level, affecting the temperature control and safety of the high-pressure turbine disc. Suppressing the windage temperature rise is an important guarantee to ensure that the turbine disc works in an appropriate temperature range.

[0004] Due to the high relative speed of the turntable cavity, the wind resistance temperature rise of the turntable cavity is often higher, and the need to suppress the wind resistance temperature rise is more urgent. The airflow inside the turntable cavity is very complex. The typical turntable cavity meridian streamline diagram is as follows: Figure 5 As shown, due to the higher rotation speed of the high-pressure disc, the centrifugal force exerted on the airflow is greater. Therefore, a large clockwise vortex is usually formed in the meridian plane at a high radius, and the vortex system at other positions is squeezed to form a counter-vortex structure. The closed vortex system inside the turntable cavity will cause the airflow to stay in the disk cavity for a long time, thereby generating a large amount of wind resistance heat, resulting in a high temperature in the disk cavity. This will be more severe when the inlet flow rate of the turntable cavity is small. At this time, the existing typical turntable cavity structure is difficult to avoid the wind resistance temperature rise of the turntable cavity. How to reduce the wind resistance temperature rise is an urgent problem that needs to be solved.

[0005] Therefore, it is necessary to provide an aircraft engine turntable cavity wind resistance temperature rise suppression structure to solve the above problems. Summary of the invention

[0006] The present invention provides an aircraft engine turntable cavity wind resistance temperature rise suppression structure to solve the problem that with the continuous improvement of aircraft engine design indicators, the incoming flow temperature is higher and the inlet flow is smaller, and the existing typical turntable cavity structure is difficult to avoid excessive wind resistance temperature rise of the turntable cavity.

[0007] An aircraft engine of the present invention adopts the following technical solution for the wind resistance temperature rise suppression structure of the turntable cavity, including:

[0008] The cylinder is sleeved on the high-pressure turbine shaft and the low-pressure turbine shaft between the high-pressure turbine disk and the low-pressure turbine disk;

[0009] Two annular baffles are respectively mounted and fixed on the radial direction of the end of the cylinder body, and the axial direction of the outer peripheral end of the annular baffle is connected to the engine casing, a gap is formed between each annular baffle and the corresponding turbine disk, and an air flow outlet is formed between the outer peripheral end of the annular baffle and the outer peripheral end of the corresponding turbine disk; an air supply cavity is formed between the cylinder body, the engine casing and the two annular baffles;

[0010] And a plurality of pre-swirl air supply pipes, which are obliquely arranged on the opposite surfaces of the two annular partitions, and are used to connect the gap with the air supply cavity; wherein the outlet direction of the pre-swirl air supply pipe on the annular partition close to the high-pressure turbine disk is the same as the rotation direction of the high-pressure turbine disk; the outlet direction of the pre-swirl air supply pipe on the annular partition close to the low-pressure turbine disk is the same as the rotation direction of the low-pressure turbine disk.

[0011] Preferably, all pre-swirl air supply pipes are arranged between the outer circumference of the annular partition and the target radial annular surface of the annular partition, wherein the target radial annular surface is the annular surface located at a position halfway between the outer circumference and the center of the annular partition.

[0012] Preferably, the number of pre-swirl air supply pipes decreases from the outer peripheral surface of the annular partition to the target radial annular surface.

[0013] Preferably, a limiting annular baffle is radially arranged at the outer peripheral end of the annular baffle facing away from the engine casing, and an annular first airflow outlet is formed between the limiting annular baffle and the radial direction of the outer peripheral end of the corresponding high-pressure turbine disk, and the outlet direction of the first airflow outlet is perpendicular to the high-pressure turbine shaft; an annular second airflow outlet is formed between the limiting annular baffle and the outer peripheral surface of the corresponding low-pressure turbine disk, and the outlet direction of the second airflow outlet is parallel to the high-pressure turbine shaft.

[0014] Preferably, the aperture of the pre-swirl air supply tube is 1 mm.

[0015] Preferably, the inclination angle of the pre-swirl air supply pipe is the angle between the pre-swirl air supply pipe and the axial direction, and the angle is 75°.

[0016] Preferably, the axial distance between the annular partition plate and the corresponding turbine disk is 15 mm.

[0017] Preferably, the distance between the inner wall of the cylinder and the high-pressure turbine shaft is 15 mm; the distance between the inner wall of the cylinder and the low-pressure turbine shaft is 13 mm.

[0018] Preferably, connecting ears are provided on opposite sides of the outer circumferential surfaces of the two annular partitions, and the connecting ears are connected to the engine casing by screws.

[0019] Preferably, the ends of the high-pressure turbine shaft and the low-pressure turbine shaft are staggered to form a third airflow outlet.

[0020] The beneficial effects of the present invention are:

[0021] By setting a cylinder and two annular baffles, the cylinder and the engine casing are connected by the annular baffles, so that an air supply cavity is formed between the annular baffles, the cylinder and the inner wall of the engine casing, and pre-swirl air supply pipes connecting the cavity and the gap formed between the turbine disk and the corresponding annular baffles are set on the opposite sides of the two annular baffles. After the air flow enters the air supply cavity from the total air inlet on the engine casing, it enters the gap between the annular baffle and the turbine disk through the pre-swirl air supply pipe, and then flows out from the air flow outlet formed between the outer peripheral end of the annular baffle and the outer peripheral end of the corresponding turbine disk. In this process, the pre-swirl air supply pipe is set on the annular baffle to make the vortex system between the turbine disks disappear, thereby reducing momentum mixing and reducing wind resistance and temperature rise. Moreover, since the outlet direction of the inclined pre-swirl air supply pipe is the same as the rotation direction of the corresponding turbine disk, the fluid flows more smoothly, thereby reducing the relative movement speed between the air flow and the turbine disk, and further reducing wind resistance and temperature rise. BRIEF DESCRIPTION OF THE DRAWINGS

[0022] In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings required for use in the embodiments or the description of the prior art will be briefly introduced below. Obviously, the drawings described below are only some embodiments of the present invention. For ordinary technicians in this field, other drawings can be obtained based on these drawings without paying creative work.

[0023] Figure 1 A cross-sectional view of a structure for suppressing wind resistance and temperature rise of a turntable cavity of an aircraft engine of the present invention;

[0024] Figure 2 It is a schematic diagram of a 1 / 72 sector of a fluid domain of a structure for suppressing wind resistance and temperature rise of a turntable cavity of an aircraft engine in an embodiment of the present invention;

[0025] Figure 3 It is a schematic diagram of the arrangement of a single pre-swirl air supply pipe in a top view of a structure for suppressing windage and temperature rise of a turntable cavity of an aircraft engine in an embodiment of the present invention;

[0026] Figure 4 It is a schematic diagram of a 1 / 72 sector of an existing structural fluid domain in an embodiment of the present invention;

[0027] Figure 5 This is a typical streamline diagram of the fluid domain in the rotating disk cavity;

[0028] Figure 6 for Figure 4 Streamline diagram of the fluid domain of the existing structure;

[0029] Figure 7 for Figure 2 Streamline diagram of the fluid domain of the suppression structure of the present invention;

[0030] Figure 8 for Figure 4 Schematic diagram of high pressure swirl ratio in the fluid domain of the existing structure;

[0031] Fig. 9 for Figure 2 A schematic diagram of the high pressure swirl ratio of the fluid domain of the suppression structure of the present invention;

[0032] Fig.10 for Figure 4 Schematic diagram of low-pressure swirl ratio of the fluid domain in the existing structure;

[0033] Fig.11 for Figure 2 A schematic diagram of the low-pressure swirl ratio of the fluid domain of the suppression structure of the present invention;

[0034] Fig.12 for Figure 4 Schematic diagram of absolute total temperature of the meridian surface of the rotating disk cavity of the existing structure;

[0035] Fig.13 for Figure 2 A schematic diagram of the absolute total temperature of the meridian plane of the rotating disk cavity of the suppression structure of the present invention;

[0036] Fig.14 for Figure 4 Schematic diagram of solid wall temperature of the existing structure;

[0037] Fig.15 for Figure 2 Schematic diagram of the solid wall temperature of the suppression structure of the present invention.

[0038] In the figure: 1. engine casing; 2. high-pressure side annular partition; 3. high-pressure turbine disk; 4. high-pressure turbine shaft; 5. cylinder; 6. low-pressure turbine shaft; 7. low-pressure turbine disk; 8. low-pressure side annular partition; 9. pre-swirl air supply pipe; 10. main air inlet; 101. first air flow outlet; 102. second air flow outlet; 103. third air flow outlet. DETAILED DESCRIPTION

[0039] The following will be combined with the drawings in the embodiments of the present invention to clearly and completely describe the technical solutions in the embodiments of the present invention. Obviously, the described embodiments are only part of the embodiments of the present invention, not all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without creative work are within the scope of protection of the present invention.

[0040] An embodiment of a structure for suppressing wind resistance and temperature rise of a turntable cavity of an aircraft engine of the present invention is as follows: Figure 1 As shown, it includes: a barrel 5, two annular partitions and a plurality of pre-swirl air supply pipes 9. The barrel 5 is sleeved on the high-pressure turbine shaft 4 and the low-pressure turbine shaft 6 between the high-pressure turbine disk 3 and the low-pressure turbine disk 7. It should be noted that there are gaps between the inner wall of the barrel 5 and the high-pressure turbine disk 3, and between the inner wall of the barrel 5 and the low-pressure turbine disk 7; the two annular partitions are the high-pressure side annular partition 2 and the low-pressure side annular partition 8. The high-pressure side annular partition 2 is sleeved and fixed on the radial direction of the barrel 5 near the end of the high-pressure turbine disk 3, and the low-pressure side annular partition 8 is sleeved and fixed on the radial direction of the barrel 5 near the end of the high-pressure turbine disk 3. The annular baffle is fixed to the radial direction of the end of the cylinder 5 near the low-pressure turbine disk 7, and the outer peripheral end of the annular baffle is axially connected to the engine casing 1. A gap (i.e., a fluid domain) is formed between each annular baffle and the corresponding turbine disk, and an air flow outlet is formed between the outer peripheral end of the annular baffle and the outer peripheral end of the corresponding turbine disk; an air supply cavity is formed between the cylinder 5, the engine casing 1 and the two annular baffles; a plurality of pre-swirl air supply pipes 9 are obliquely arranged on the opposite surfaces of the two annular baffles, and the pre-swirl air supply pipes 9 are used to connect the gap and the air supply cavity; wherein, as Figure 3 As shown, the outlet direction of the pre-swirl air supply pipe 9 on the annular partition (high-pressure side annular partition 2) close to the high-pressure turbine disk 3 is the same as the rotation direction of the high-pressure turbine disk 3; the outlet direction of the pre-swirl air supply pipe 9 on the annular partition (low-pressure side annular partition 8) close to the low-pressure turbine disk 7 is the same as the rotation direction of the low-pressure turbine disk 7, and a limiting annular partition is arranged radially away from the outer peripheral end of the annular partition of the engine casing 1, and an annular first airflow outlet 101 is formed between the limiting annular partition and the radial direction of the outer peripheral end of the corresponding high-pressure turbine disk 3, and the outlet of the first airflow outlet 101 The outlet direction is perpendicular to the high-pressure turbine shaft 4; an annular second airflow outlet 102 is formed between the limiting annular partition and the outer peripheral surface of the corresponding low-pressure turbine disk 7, and the outlet direction of the second airflow outlet 102 is parallel to the high-pressure turbine shaft 4, and the ends of the high-pressure turbine shaft 4 and the low-pressure turbine shaft 6 are staggered to form a third airflow outlet 103; so that the airflow has a greater circumferential motion speed when it flows out, and the motion direction of the airflow flowing out of the airflow outlet of the pre-swirl air supply pipe 9 is the same as the rotation direction of the corresponding turbine disk, thereby reducing the relative motion speed between the airflow and the turbine disk. It should be noted that Figure 1 A half cross-sectional view of the suppression structure is shown, wherein the dashed line indicates the symmetry line of the suppression structure, which is the central axis of the high-pressure turbine disk 3 .

[0041] like Figure 2As shown, in an exemplary embodiment, since the rotation linear velocity of the turbine disc corresponding to the low radius (between the target radial annular surface and the outer circumference of the cylinder 5) is low and the wind resistance temperature rise effect is small, the wind resistance temperature rise effect at the low radius is small, so all pre-swirl air supply pipes 9 are arranged between the outer circumference of the annular partition and the target radial annular surface of the annular partition, wherein the target radial annular surface is the annular surface located at the half position from the outer circumference to the center of the annular partition; and the number of pre-swirl air supply pipes 9 decreases from the outer circumference of the annular partition to the target radial annular surface. In this embodiment, there are a total of six rows of air supply holes, and the ratio of the number of air supply holes from the outer circumference of the annular partition to the target radial annular surface of the annular partition is 3:3:2:2:1:1. Since the linear velocity of the turntable at the high radius of the turbine (between the outer circumference of the annular partition and the target radial annular surface) is the highest, a larger number of pre-swirl air supply pipes 9 are arranged on the side close to the outer circumference of the annular partition, which is conducive to increasing the inertial force of the airflow, thereby reducing the relative speed between the turntable and the airflow. The reason why no air supply holes are arranged from the target radial annular surface to the center of the annular partition is that the radial inward flow of the airflow is affected by the conservation of angular momentum and will be accelerated in the circumferential direction, and the linear velocity of the rotor is decreasing. Therefore, it is not necessary to provide additional rotating airflow to maintain a high relative rotation speed. That is, a pre-swirl air supply pipe 9 is arranged between the outer peripheral surface of the annular partition and the target radial annular surface of the annular partition to make the vortex system between the turbine disks disappear, thereby reducing momentum mixing and reducing wind resistance temperature rise.

[0042] In an exemplary embodiment, the aperture of the pre-swirl air supply pipe 9 is 1 mm. It should be noted that the use of small and dense air supply holes is conducive to forming a sliding wall similar to an air film on the annular partition, thereby reducing the stagnation effect of the stationary wall on the rotating airflow and helping to maintain the circumferential motion speed of the airflow.

[0043] In an exemplary embodiment, the inclination angle of the pre-swirl air supply pipe 9 is, in principle, as large as possible while meeting the processing requirements, but is usually limited to between 60° and 75°. Figure 3 Further increase in the pre-swirl angle brings limited benefits, and the total pressure loss increases rapidly. The inclination angle of the pre-swirl air supply pipe 9 is the angle between the pre-swirl air supply pipe 9 and the axial direction, which is 75°.

[0044] In an exemplary embodiment, the axial distance between the annular partition plate and the corresponding turbine disk is 15 mm.

[0045] Specifically, the distance between the inner wall of the cylinder 5 and the high-pressure turbine shaft 4 is 15 mm; the distance between the inner wall of the cylinder 5 and the low-pressure turbine shaft 6 is 13 mm.

[0046] In an exemplary embodiment, connecting ears are provided on opposite sides of the outer circumferences of the two annular partitions, and the connecting ears are connected to the engine casing 1 by screws.

[0047] The following is combined with Figure 6 - Fig.15 And specific simulation data illustrate the present invention:

[0048] This simulation process is to Figure 4 The 1 / 72 sector of the fluid domain of the existing structure shown and Figure 2 The numerical simulation of flow and heat transfer in the fluid domain (i.e., the gap formed between the annular partition and the corresponding turbine disk) of the suppression structure of the embodiment shown in the figure is performed to obtain the following result: Figures 6 to 15 The simulation results show that the aperture of the pre-swirl air supply pipe 9 is 1 mm; the inclination angle of the pre-swirl air supply pipe 9 is 75°; and the axial distance between the annular partition and the corresponding turbine disk is 15 mm.

[0049] 1. Comparison results of fluid domain streamlines:

[0050] like Figure 6 As shown in the fluid domain streamline diagram of the existing structure, there is a meridian vortex system, and as Figure 7 The meridian vortex system of the suppression structure formed by the cylinder and two annular partitions of the present invention basically disappears, and the high-pressure and low-pressure airflow momentum cannot be mixed, that is, the structure of the present invention has smoother fluid flow than the existing structure.

[0051] 2. Comparison results of fluid domain swirl ratio:

[0052] The high-pressure swirl ratio of the fluid domain is defined as the ratio of the circumferential velocity of the airflow to the linear velocity of the high-pressure turbine disk at the same radius; the low-pressure swirl ratio is defined as the ratio of the circumferential velocity of the airflow to the linear velocity of the low-pressure turbine disk at the same radius, where the same direction is positive and the reverse direction is negative. Figure 8 As shown, the high pressure vortex in the fluid domain of the suppression structure of the present invention is as follows Fig. 9 As shown; the low-pressure swirl flow in the fluid domain of the existing structure is Fig.10 As shown, the low-pressure swirl in the fluid domain of the suppression structure of the present invention is as follows Fig.11 As shown. Figure 8 and Fig.10 As shown in the figure, the swirl ratio of the fluid domain of the existing structure is relatively small as a whole, which is basically below 0.2 relative to the high-pressure rotor and basically negative relative to the low-pressure rotor, which indicates that the wind resistance friction between the airflow and the high- and low-pressure turbine discs is relatively strong. Fig. 9 and Fig.11 As shown, the swirl ratio of the fluid domain is relatively high as a whole, basically above 0.6 relative to the high-pressure rotor, close to 1 between the target radial annular surface and the outer peripheral surface of the annular partition, and basically above 0.9 relative to the low-pressure rotor, and locally greater than 1. This shows that the airflow of the suppression structure implemented in this embodiment and the wind resistance friction effect of the high and low-pressure turbine disks are greatly reduced.

[0053] 3. Fluid domain temperature comparison results:

[0054] Under the condition that the inlet temperature and the total gas consumption of the disc cavity are the same, the absolute total temperature of the meridian surface of the existing counter-rotating disc cavity structure is as follows: Fig.12 As shown, the suppression structure of this embodiment has an effect on the absolute total temperature of the meridian surface of the rotating disk cavity. Fig.13 As shown, when the import is 800K, Fig.12 As shown in Figure 2, the average absolute total temperature of the meridian surface of the existing structure is 833K. Fig.13 As shown, the average absolute total temperature of the meridian surface of the suppression structure of this embodiment is 806K, that is, compared with the existing structure, the wind resistance temperature rise of the suppression structure of this embodiment is reduced from 33K to 6K, with a relative reduction of 82%, which is obvious.

[0055] 4. Comparison results of solid wall temperature:

[0056] When the inlet is 800K, the solid wall temperature of the existing structure is as follows: Fig.14 As shown, the solid wall temperature of the suppression structure of this embodiment is as follows: Fig.15 As shown, Fig.14 As shown, the average wall temperature of the high-pressure turbine disk of the existing structure is 872K, and the average wall temperature of the low-pressure turbine disk is 861K; Fig.15 As shown, the average wall temperature of the high-pressure turbine disk of the suppression structure of this embodiment is 816K, and the average wall temperature of the low-pressure turbine disk is 796K, that is, compared with the existing structure, the solid wall temperature of the suppression structure of this embodiment is significantly reduced.

[0057] In summary, the wind resistance temperature rise suppression structure of the turntable cavity of an aircraft engine provided by the embodiment of the present invention can effectively organize the flow field inside the turntable cavity and reduce the magnitude of wind resistance temperature rise. Compared with the existing wind resistance temperature rise suppression structure of the turntable cavity, the wind resistance temperature rise of the present invention is lower and more conducive to the temperature control of the turbine disk.

[0058] The above description is only a preferred embodiment of the present invention and is not intended to limit the present invention. Any modifications, equivalent substitutions, improvements, etc. made within the spirit and principle of the present invention should be included in the protection scope of the present invention.

Claims

1. An aircraft engine structure for suppressing wind resistance and temperature rise of a turntable cavity, characterized in that: include: A cylinder (5) is sleeved on the high-pressure turbine shaft (4) and the low-pressure turbine shaft (6) between the high-pressure turbine disk (3) and the low-pressure turbine disk (7); Two annular baffles are respectively mounted and fixed in the radial direction of the end of the cylinder (5); the outer peripheral ends of the annular baffles are axially connected to the engine casing (1); a gap is formed between each annular baffle and the corresponding turbine disk; and an air flow outlet is formed between the outer peripheral end of the annular baffle and the outer peripheral end of the corresponding turbine disk; an air supply cavity is formed between the cylinder (5), the engine casing (1) and the two annular baffles; and a plurality of pre-swirl air supply pipes (9) which are obliquely arranged on opposite surfaces of the two annular partitions and are used to connect the gap with the air supply cavity; wherein the outlet direction of the pre-swirl air supply pipe (9) on the annular partition close to the high-pressure turbine disk (3) is along the rotation direction of the high-pressure turbine disk (3); and the outlet direction of the pre-swirl air supply pipe (9) on the annular partition close to the low-pressure turbine disk (7) is along the rotation direction of the low-pressure turbine disk (7); Wherein, connecting ears are arranged on opposite sides of the outer circumferences of the two annular partitions, and the connecting ears are connected to the engine casing (1) through screws; the ends of the high-pressure turbine shaft (4) and the low-pressure turbine shaft (6) are staggered to form a third airflow outlet (103).

2. The structure for suppressing wind resistance and temperature rise of a turntable cavity of an aircraft engine according to claim 1, characterized in that: All pre-swirl air supply pipes (9) are arranged between the outer circumferential surface of the annular partition and the target radial annular surface of the annular partition, wherein the target radial annular surface is an annular surface located at a position halfway between the outer circumference of the annular partition and the center.

3. The structure for suppressing wind resistance and temperature rise of the turntable cavity of an aircraft engine according to claim 2, characterized in that: The number of pre-swirl air supply pipes (9) decreases from the outer peripheral surface of the annular partition to the target radial annular surface.

4. The structure for suppressing wind resistance and temperature rise of a turntable cavity of an aircraft engine according to claim 1, characterized in that: A limiting annular baffle is provided radially at the outer peripheral end of the annular baffle away from the engine casing (1), and an annular first airflow outlet (101) is formed between the limiting annular baffle and the radial direction of the outer peripheral end of the corresponding high-pressure turbine disk (3), and the outlet direction of the first airflow outlet (101) is perpendicular to the high-pressure turbine shaft (4); an annular second airflow outlet (102) is formed between the limiting annular baffle and the outer peripheral surface of the corresponding low-pressure turbine disk (7), and the outlet direction of the second airflow outlet (102) is parallel to the high-pressure turbine shaft (4).

5. The structure for suppressing wind resistance and temperature rise of a turntable cavity of an aircraft engine according to claim 1, characterized in that: The aperture of the pre-swirl air supply pipe (9) is 0.5 mm to 1 mm.

6. The structure for suppressing wind resistance and temperature rise of a turntable cavity of an aircraft engine according to claim 1, characterized in that: The inclination angle of the pre-swirl air supply pipe (9) is the angle between the pre-swirl air supply pipe (9) and the axial direction, and the angle is 60°-75°.

7. The structure for suppressing wind resistance and temperature rise of a turntable cavity of an aircraft engine according to claim 1, characterized in that: The axial distance between the annular partition and the corresponding turbine disc is 10 mm to 20 mm.

8. The structure for suppressing wind resistance and temperature rise of a turntable cavity of an aircraft engine according to claim 1, characterized in that: The distance between the inner wall of the cylinder (5) and the high-pressure turbine shaft (4) is 10 mm to 20 mm; the distance between the inner wall of the cylinder (5) and the low-pressure turbine shaft (6) is 8 mm to 18 mm.

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