Thermal insulation structure of aircraft engine and its bearing seat

Abstract

The present invention discloses an aircraft engine and a bearing seat heat insulation structure thereof, wherein the bearing seat heat insulation structure includes a bearing seat and a heat insulation cover, the inner cavity of the bearing seat is used to install bearings, the outer wall of the bearing seat is provided with a first air flow channel extending along the axial direction of the bearing seat, the heat insulation cover is installed on the outer periphery of the bearing seat with a gap relative to the first air flow channel, and the side of the heat insulation cover away from the bearing seat is used to enclose a second air flow channel together with the turbine disk. The bearing seat heat insulation structure provided by the present invention forms a double-layer air flow channel on the outer periphery of the bearing seat through the cooperation of the heat insulation cover and the bearing seat, forming a complete air flow circuit. Since the double-layer air flow channel completely surrounds the outer periphery of the bearing seat, the cooling gas flows rapidly in the double-layer air flow channel respectively, which can enhance convective heat exchange, achieve sufficient cooling and heat insulation effects in a limited radial space, and effectively prevent the high temperature of the turbine disk from being transferred to the interior of the bearing seat.

Description

Technical Field

[0001] The present invention relates to the technical field of bearing seats of aircraft engines, and in particular to a bearing seat heat insulation structure and an aircraft engine using the bearing seat heat insulation structure. Background Art

[0002] In a gas turbine engine, the interior of the bearing seat is used to install bearings. Lubricating oil usually needs to be introduced into the bearing seat through an external pipeline to lubricate and cool the bearings. Due to the limitation of the lubricating oil operating temperature, the lubricating oil temperature rise often needs to be controlled within 30°C. Therefore, the cooling of the bearing seat needs to be considered to prevent the high temperature of the turbine disk flow path gas from heating the bearing seat through heat conduction, heat radiation, etc., which may cause the lubricating oil temperature to be too high.

[0003] Traditional bearing seat insulation methods generally involve adding a heat shield around the outer periphery of the bearing seat. This shield reduces the heat radiation from the high-temperature wall of the transition section to the outer wall of the bearing seat, thereby reducing the heat load on the lubricating oil within the bearing seat. However, because the heat shield requires a relatively thick structure (insulating material must be filled inside the heat shield) to provide sufficient insulation, this structure increases the weight and radial dimensions of the bearing seat, adversely affecting the lightweight and miniaturized design of aircraft engines. Summary of the Invention

[0004] The present invention primarily provides a bearing seat heat insulation structure to solve the technical problems of the existing aircraft engine bearing seat heat insulation structure being heavy and occupying a large space.

[0005] The present invention also provides an aero-engine, which adopts the above-mentioned bearing seat heat insulation structure.

[0006] According to a first aspect of the present invention, there is provided a bearing seat thermal insulation structure for installation between a bearing and a turbine disk of an aircraft engine. The bearing seat thermal insulation structure comprises a bearing seat and a heat shield. The inner cavity of the bearing seat is used to mount the bearing. The outer wall of the bearing seat is provided with a first airflow channel extending axially along the bearing seat. The heat shield is mounted on the outer periphery of the bearing seat with a gap relative to the first airflow channel. A surface of the heat shield, remote from the bearing seat, is used to enclose a second airflow channel together with the turbine disk.

[0007] The first end of the bearing seat is used to be arranged in the turbine disk, and the second end of the bearing seat extends axially to the outside of the turbine disk. The first air flow channel is provided with an air inlet at the second end of the bearing seat, and the first air flow channel is connected with the second air flow channel at the first end of the bearing seat. The air inlet is used to allow cooling gas to flow along the first air flow channel to the first end of the bearing seat, and then allow the cooling gas to enter the second air flow channel from the first air flow channel and flow along the second air flow channel toward the second end of the bearing seat.

[0008] Preferably, a plurality of air film holes are provided on the heat insulation cover, and the air film holes penetrate the heat insulation cover to connect the first air flow channel and the second air flow channel. The air film holes are used to introduce part of the cooling gas in the first air flow channel into the side of the heat insulation cover away from the bearing seat and adhere to the surface of the heat insulation cover to form an air film.

[0009] More preferably, the heat shield is provided with multiple air film hole groups along its axial direction, wherein the air film hole groups include multiple air film holes spaced apart along the circumference of the heat shield, and the air film holes in two adjacent air film hole groups are staggered along the axial direction of the heat shield.

[0010] Preferably, the heat insulation cover is provided with air guide blades, and the air guide blades are arranged in a ring spiral shape around the wall surface of the heat insulation cover.

[0011] Preferably, the heat shield is provided with a corrugated structure for compensating for expansion when heated.

[0012] Furthermore, a positioning boss is provided on a side of the heat shield facing the bearing seat and / or a side of the bearing seat facing the heat shield, and the heat shield is mounted on the bearing seat via the positioning boss.

[0013] Furthermore, the bearing seat insulation structure also includes a carbon sealing assembly, which is arranged at the first end of the bearing seat and is used to abut the rotating shaft. A diverter port is provided at the position where the first air flow channel is connected to the second air flow channel, and the diverter port is used to divert part of the cooling gas in the first air flow channel to the carbon sealing assembly.

[0014] Preferably, an outer wall of the bearing seat is provided with an oil groove, and the bearing seat heat insulation structure further comprises a cover plate which is provided on the oil groove and which together with the oil groove forms an oil channel.

[0015] More preferably, the lubricating oil channel includes an oil inlet channel provided above the bearing seat and an oil outlet channel provided below the bearing seat. An oil outlet hole is also provided below the bearing seat. The first end of the oil outlet hole is communicated with the inner cavity of the bearing seat, and the second end of the oil outlet hole is communicated with the oil outlet channel. The oil outlet hole is arranged at an angle so that the second end of the oil outlet hole is inclined toward the oil outlet direction of the oil outlet channel.

[0016] According to a second aspect of the present invention, there is also provided an aircraft engine comprising a bearing and a turbine disc, the aircraft engine further comprising the above-mentioned bearing seat insulation structure, the bearing seat insulation structure being arranged between the turbine disc and the bearing and supporting and fixing the bearing.

[0017] The present invention has the following beneficial effects:

[0018] The bearing seat thermal insulation structure provided by the present invention forms a double-layer airflow channel around the outer periphery of the bearing seat through the cooperation of the heat shield and the bearing seat. This allows cooling gas to enter the inner side of the turbine disk along the first airflow channel and then flow out in the opposite direction along the second airflow channel, forming a complete airflow circuit. Furthermore, because the double-layer airflow channel completely surrounds the outer periphery of the bearing seat, the cooling gas flows rapidly around the outer periphery of the bearing seat within the double-layer airflow channel, thereby enhancing convective heat transfer and achieving sufficient cooling and thermal insulation within a limited radial space. This effectively prevents the high temperature of the turbine disk from being transferred to the interior of the bearing seat, thereby maintaining an optimal temperature environment for the bearings and lubricating oil within the bearing seat and ensuring performance. Furthermore, because the double-layer airflow channel formed around the outer periphery of the bearing seat can achieve sufficient cooling and thermal insulation, the thermal insulation performance requirements of the heat shield itself are not high. A thin-walled structure can meet the thermal insulation requirements, thereby reducing weight and radial dimensions, further facilitating lightweight and miniaturized aircraft engine designs.

[0019] 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

[0020] 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:

[0021] Figure 1 A three-dimensional diagram of a bearing seat heat insulation structure provided by an embodiment of the present invention;

[0022] Figure 2 for Figure 1 Exploded view of the bearing housing insulation structure shown;

[0023] Figure 3for Figure 1 The cross-sectional structure diagram of the heat insulation structure of the bearing seat is shown, wherein the single arrow is used to indicate the flow direction of the cooling gas, and the straight line with an arrow is used to indicate the flow direction of the lubricating oil;

[0024] Figure 4 A planar expansion diagram of a heat shield provided in another embodiment of the present invention;

[0025] Figure 5 for Figure 4 Referring to the figure showing the heat shield in use, arrows indicate the flow direction of the cooling gas.

[0026] Figure 6 A schematic cross-sectional view of a heat shield according to another embodiment of the present invention;

[0027] Figure 7 This is a schematic cross-sectional structural diagram of a heat shield provided in yet another embodiment of the present invention.

[0028] Legend:

[0029] 1. Bearing seat insulation structure; 11. Bearing seat; 111. Positioning boss; 112. Oil groove; 113. Oil outlet hole; 12. Heat shield; 121. Air film hole; 122. Corrugated structure; 13. Carbon sealing assembly; 14. Cover plate; 15. Nozzle; 100. First air flow channel; 101. Air inlet; 200. Second air flow channel; 300. Oil channel; 301; Oil inlet channel; 302. Oil outlet channel; 2. Bearing; 3. Turbine disk. DETAILED DESCRIPTION

[0030] The embodiments of the present invention are 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.

[0031] Figures 1 to 5 The figures together show the heat-insulating structure of the bearing seat provided by an embodiment of the present invention, which is used to be arranged between the bearing and the turbine disk of an aircraft engine and to support and fix the bearing. The relatively light and thin structure can better cool and insulate the bearing and lubricating oil inside the bearing seat, preventing the high temperature of the flow path gas of the turbine disk from heating the bearing and lubricating oil through heat conduction, heat radiation, etc., thereby ensuring the performance of the bearing and lubricating oil.

[0032] Please combine Figure 1 and Figure 2 The bearing seat heat insulation structure 1 includes a bearing seat 11 and a heat insulation cover 12. The heat insulation cover 12 is sleeved on the outer periphery of the bearing seat 11 to provide a certain heat insulation protection for the bearing seat 11.

[0033] like Figure 3As shown, the inner cavity of the bearing seat 11 is used to install the bearing 2, and the outer wall of the bearing seat 11 is provided with a first air flow channel 100 extending along the axial direction of the bearing seat 11. The heat shield 12 is installed on the outer periphery of the bearing seat 11 with a gap relative to the first air flow channel 100. The side of the heat shield 12 away from the bearing seat 11 is used to enclose a second air flow channel 200 together with the turbine disk 3. The first air flow channel 100 and the second air flow channel 200 both completely cover the gap between the bearing seat 11 and the turbine disk 3.

[0034] Specifically, the first end of the bearing seat 11 is used to be arranged in the turbine disk 3, and the second end of the bearing seat 11 extends axially to the outside of the turbine disk 3. The first air flow channel 100 is provided with an air inlet 101 at the second end of the bearing seat 11. The first air flow channel 100 is connected to the second air flow channel 200 at the first end of the bearing seat 11. The air inlet 101 is used to introduce cooling gas so that the cooling gas flows along the first air flow channel 100 to the first end of the bearing seat 11, and then the cooling gas enters the second air flow channel 200 from the first air flow channel 100 and flows along the second air flow channel 200 toward the second end of the bearing seat 11.

[0035] The bearing seat insulation structure 1 can form a double-layer airflow channel on the periphery of the bearing seat 11 through the mutual nesting of the heat insulation cover 12 and the bearing seat 11, so that the cooling gas can enter the inner side of the turbine disk 3 along the first airflow channel 100 and then flow out in the opposite direction along the second airflow channel 200, forming a complete airflow circuit. Moreover, since the double-layer airflow channels completely surround the periphery of the bearing seat 11, the cooling gas flows rapidly around the periphery of the bearing seat 11 in the double-layer airflow channels, which can enhance convective heat exchange and achieve sufficient cooling and heat insulation effects in a limited radial space, thereby effectively preventing the high temperature of the turbine disk 3 from being transferred to the inside of the bearing seat 11, and thus the bearing 2 and lubricating oil inside the bearing seat 11 can be in a better temperature environment, ensuring the performance of use. Secondly, since the double-layer air flow channel formed on the outer periphery of the bearing seat 11 can achieve sufficient cooling and heat insulation, the heat insulation performance of the heat insulation cover 12 itself is not required to be high. The heat insulation cover 12 can meet the heat insulation requirements by adopting a thin-walled structure, thereby reducing weight and radial dimensions, which is more conducive to the lightweight design and miniaturization design of the aircraft engine.

[0036] Preferably, the radial width of the first airflow channel 100 is 0.5-1.5 mm, the radial width of the second airflow channel 200 is 1-2 mm, and the radial width of the first airflow channel 100 is smaller than the radial width of the second airflow channel 200. Controlling the radial widths of both the first airflow channel 100 and the second airflow channel 200 within a relatively small size range not only reduces the radial size of the bearing seat thermal insulation structure 1, but also accelerates the flow rate of the cooling gas, improves the convective heat transfer coefficient, and reduces the thermal effect of the turbine disk 3 on the outer wall of the bearing seat 11. Moreover, because the radial width of the first airflow channel 100 is smaller than the radial width of the second airflow channel 200, the flow rate of the cooling gas in the first airflow channel 100 is greater than the flow rate of the cooling gas in the second airflow channel 200, so that the first airflow channel 100 can replenish the cooling gas for the second airflow channel 200 more quickly, fully ensuring the cooling and heat insulation effect of the second airflow channel 200, and further enhancing the convective heat transfer effect.

[0037] It is worth noting that when the radial width of the first airflow channel 100 is less than 0.5 mm or the radial width of the second airflow channel 200 is less than 1 mm, the cooling gas will flow at high speed in an overly narrow space, resulting in an excessively fast flow rate, making it impossible for the cooling gas to fully cover the bearing seat 11 or the heat shield 12, thereby reducing the cooling and heat insulation effects. When the radial width of the first airflow channel 100 is greater than 1.5 mm or the radial width of the second airflow channel 200 is greater than 2 mm, the cooling gas flow space will be too large and the flow rate will be too slow. Under the continuous heating of the high temperature of the flow channel gas of the turbine disk 3, the cooling effect will be affected and the radial size of the bearing seat heat insulation structure 1 will be increased.

[0038] Preferably, the thickness of the heat shield 12 is 0.5-1 mm. Since the double-layer airflow channel formed on the periphery of the bearing seat 11 can achieve sufficient cooling and heat insulation, the heat shield 12 itself does not require high heat insulation performance. The heat shield 12 only needs to separate the first airflow channel 100 and the second airflow channel 200 and have a certain structural strength. Compared with existing heat shields, it does not require filling with insulation material, is thinner, and has lower cost. In addition, the double-layer airflow channel formed by the heat shield 12 has better cooling and heat insulation effects.

[0039] Please combine Figure 4 and Figure 5Preferably, a plurality of air film holes 121 are arranged on the heat insulation cover 12, and the air film holes 121 pass through the two opposite sides of the heat insulation cover 12 to connect the first air flow channel 100 and the second air flow channel 200. The air film holes 121 are used to introduce part of the cooling gas in the first air flow channel 100 into the side of the heat insulation cover 12 away from the bearing seat 11 and adhere to the surface of the heat insulation cover 12 to form an air film.

[0040] Specifically, the air film holes 121 have a diameter of 0.05-0.1 mm. These holes direct a small portion of the cooling gas within the first airflow channel 100 to the side of the heat shield 12 facing away from the bearing seat 11. Driven by the airflow in the second airflow channel 200, this portion of cooling gas forms an air film against the surface of the heat shield 12, providing enhanced cooling and insulation on the side of the heat shield 12 facing the turbine disk 3. In this embodiment, the air film holes 121 are configured as straight holes to facilitate machining, reduce processing difficulty, and lower costs.

[0041] like Figure 6 and Figure 7 As shown, in other embodiments, the air film hole 121 can also adopt an arc-shaped hole or a V-shaped hole, so that the air film hole 121 is inclined toward one end of the first air flow channel 100 toward the air flow of the first air flow channel 100, and the air film hole 121 is inclined toward one end of the second air flow channel 200 toward the air flow direction of the second air flow channel 200, so that the air film hole 121 can better introduce the cooling gas, and the cooling gas in the air film hole 121 can be ejected along the air flow direction of the second air flow channel 200, and the direction of the cooling gas is converted by the internal structure of the air film hole 121, so that the cooling gas can more stably cover the surface of the heat insulation cover 12 to form an air film, reduce the aerodynamic mixing loss, and further improve the cooling effect.

[0042] exist Figure 4 As shown in the figure, the heat shield 12 is provided with multiple air film hole groups along its axial direction. These air film hole groups include multiple air film holes 121 spaced apart along the circumference of the heat shield 12. The air film holes 121 in two adjacent air film hole groups are staggered along the axial direction of the heat shield 12. This prevents the cooling gas from being concentrated on a single line in the heat shield 12 and unable to fully disperse. It also prevents the multiple air film holes 121 on the heat shield 12 from being concentrated along a single line and affecting the airflow stability of the first and second air flow channels 100, 200, thereby ensuring the cooling and heat insulation effect of the cooling gas.

[0043] Preferably, the heat insulation cover 12 is provided with air guide blades (not shown in the figure, the same below), and the air guide blades are arranged in a ring spiral shape around the inner wall surface and / or outer wall surface of the heat insulation cover 12. The air guide blades change the direction of the air flow, so that the cooling gas flows in a ring spiral shape around the bearing seat 11 or around the heat insulation cover 12 at high speed, thereby fully covering different positions of the bearing seat 11 and / or the heat insulation cover 12, thereby enhancing the convective heat exchange effect.

[0044] exist Figure 1 and Figure 2 As shown in the figure, the heat shield 12 is further provided with a corrugated structure 122. When the heat shield 12 is deformed due to uneven heating, the corrugated structure 122 can be used for expansion and contraction compensation, so that the heat shield 12 remains positioned and fixed relative to the bearing seat 11, thereby preventing the first air flow channel 100 and the second air flow channel 200 from being deformed and affecting the air flow stability.

[0045] Furthermore, a positioning boss 111 is provided on one side of the heat insulation cover 12 facing the bearing seat 11 and / or on one side of the bearing seat 11 facing the heat insulation cover 12. The heat insulation cover 12 is mounted on the bearing seat 11 via the positioning boss 111. The supporting and positioning function of the positioning boss 111 can effectively suppress thermal deformation of the heat insulation cover 12, so that the heat insulation cover 12 maintains a fixed gap relative to the outer wall of the bearing seat 11, thereby ensuring that the first air flow channel 100 is evenly distributed.

[0046] Furthermore, the heat shield 12 and the bearing seat 11 are fixed by welding to ensure connection strength and stability.

[0047] exist Figure 3 As shown in the figure, the bearing seat thermal insulation structure 1 further includes a carbon seal assembly 13, which is disposed at the first end of the bearing seat 11 and is configured to abut the rotating shaft. A diverter is provided at the location where the first airflow channel 100 and the second airflow channel 200 communicate. The diverter is configured to divert a portion of the cooling gas within the first airflow channel 100 to the carbon seal assembly 13. The cooling gas cools the carbon seal assembly 13 and also creates a pressure differential between the cooling gas and the inner cavity of the bearing seat 11. This pressure differential enhances the sealing effect of the carbon seal assembly 13 and prevents lubricating oil leakage.

[0048] Preferably, an oil groove 112 is formed on the outer wall of the bearing seat 11. The bearing seat thermal insulation structure 1 further includes a cover plate 14, which covers the oil groove 112 and, together with the oil groove 112, encloses an oil passage 300 for the flow of lubricating oil. The oil groove 112 is first designed on the bearing seat 11 and then sealed with the cover plate 14 to form an internal oil passage. This ensures smooth oil inflow and outflow. Compared to casting or machining internal through-holes in the bearing seat 11, the structure has better manufacturability and is more convenient to process and form. It also enables axial oil inflow and outflow, reduces the thickness requirements of the bearing seat 11, and can further reduce the thickness of the bearing seat 11, achieving a miniaturized design.

[0049] Preferably, the lubricating oil passage 300 includes an oil inlet passage 301 located above the bearing seat 11 and an oil outlet passage 302 located below the bearing seat 11. An oil outlet hole 113 is also provided below the bearing seat 11. A first end of the oil outlet hole 113 communicates with the inner cavity of the bearing seat 11, and a second end of the oil outlet hole 113 communicates with the oil outlet passage 302. The oil outlet hole 113 is tilted so that the second end of the oil outlet hole 113 is inclined toward the oil outlet direction of the oil outlet passage 302. Compared to a straight hole structure, the oil outlet hole 113 does not require two vertical through-holes to be machined on the bearing seat 11, thus reducing the number of machining steps. Furthermore, there is no right-angle bend in the flow channel, resulting in better and smoother oil return.

[0050] Furthermore, the bearing seat thermal insulation structure 1 also includes a nozzle 15 disposed in the inner cavity of the bearing seat 11 and connected to the oil inlet passage 301. The nozzle 15 is used to spray lubricating oil in the oil inlet passage 301 into the inner cavity of the bearing seat 11. The nozzle 15 is provided with one or more oil spray holes, so that the direction of oil spraying can be flexibly adjusted by varying the number and position of the oil spray holes. For example, when the nozzle 15 is disposed between the carbon seal assembly 13 and the bearing 2, lubricating oil is sprayed toward the carbon seal assembly 13 through at least one oil spray hole, thereby cooling the carbon seal assembly 13. Lubricating oil is then sprayed toward the bearing 2 through at least one oil spray hole, thereby ensuring cooling and lubrication of the bearing 2.

[0051] According to a second aspect of the present invention, there is also provided an aircraft engine, comprising a bearing 2 and a turbine disk 3, and the above-mentioned bearing seat insulation structure 1, wherein the bearing seat insulation structure 1 is arranged between the turbine disk 3 and the bearing 2 and supports and fixes the bearing 2. Since the bearing seat insulation structure 1 adopts a relatively light and thin structure, it can better cool and insulate the bearing 2 and the lubricating oil, while ensuring the performance, it can reduce the weight and reduce the radial size, which is more conducive to the lightweight design and miniaturization design of the aircraft engine.

[0052] The foregoing description is merely a preferred embodiment of the present invention and is 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 bearing seat heat insulation structure, used for being arranged between a bearing (2) and a turbine disk (3) of an aircraft engine, characterized in that: The bearing seat heat insulation structure comprises a bearing seat (11) and a heat shield (12), the inner cavity of the bearing seat (11) is used to install the bearing (2), the outer wall of the bearing seat (11) is provided with a first air flow channel (100) extending along the axial direction of the bearing seat (11), the heat shield (12) is installed on the outer periphery of the bearing seat (11) with a gap relative to the first air flow channel (100), and the surface of the heat shield (12) away from the bearing seat (11) is used to enclose a second air flow channel (200) together with the turbine disk (3); The first end of the bearing seat (11) is used to be arranged in the turbine disk (3), and the second end of the bearing seat (11) extends axially to the outside of the turbine disk (3); the first air flow channel (100) is provided with an air inlet (101) at the second end of the bearing seat (11); the first air flow channel (100) is communicated with the second air flow channel (200) at the first end of the bearing seat (11); the air inlet (101) is used to allow cooling gas to flow along the first air flow channel (100) to the first end of the bearing seat (11), and then the cooling gas enters the second air flow channel (200) from the first air flow channel (100) and flows along the second air flow channel (200) toward the second end of the bearing seat (11); The heat shield (12) is provided with a plurality of air film holes (121), and the air film holes (121) penetrate the heat shield (12) to connect the first air flow channel (100) and the second air flow channel (200). The air film holes (121) are used to introduce part of the cooling gas in the first air flow channel (100) into the side of the heat shield (12) away from the bearing seat (11) and adhere to the surface of the heat shield (12) to form an air film.

2. The heat-insulating structure of the bearing seat according to claim 1, characterized in that: The heat shield (12) is provided with a plurality of exhaust film hole groups along its axial direction, wherein the exhaust film hole groups include a plurality of exhaust film holes (121) arranged at intervals along the circumference of the heat shield (12), and the exhaust film holes (121) in two adjacent exhaust film hole groups are staggered along the axial direction of the heat shield (12).

3. The heat-insulating structure of the bearing seat according to claim 1, characterized in that: The heat insulation cover (12) is provided with air guide blades, and the air guide blades are arranged in a ring spiral shape around the wall surface of the heat insulation cover (12).

4. The heat-insulating structure of the bearing seat according to claim 1, characterized in that: The heat-insulating cover (12) is provided with a corrugated structure (122) for performing expansion and contraction compensation when thermally expanded.

5. The heat-insulating structure of the bearing seat according to claim 1, characterized in that: A positioning boss (111) is provided on one side of the heat shield (12) facing the bearing seat (11) and / or a side of the bearing seat (11) facing the heat shield (12), and the heat shield (12) is mounted on the bearing seat (11) via the positioning boss (111).

6. The heat-insulating structure of the bearing seat according to claim 1, characterized in that: The bearing seat heat insulation structure also includes a carbon sealing component (13), which is arranged at the first end of the bearing seat (11) and is used to abut the rotating shaft. A diversion port is provided at the position where the first air flow channel (100) and the second air flow channel (200) are connected, and the diversion port is used to divert part of the cooling gas in the first air flow channel (100) to the carbon sealing component (13).

7. The heat-insulating structure of the bearing seat according to claim 1, characterized in that: An outer wall of the bearing seat (11) is provided with an oil groove (112), and the bearing seat heat insulation structure further includes a cover plate (14) which is covered on the oil groove (112) and together with the oil groove (112) forms an oil channel (300).

8. The heat-insulating structure of the bearing seat according to claim 7, characterized in that: The lubricating oil channel (300) comprises an oil inlet channel (301) provided above the bearing seat (11) and an oil outlet channel (302) provided below the bearing seat (11); an oil outlet hole (113) is further provided below the bearing seat (11); a first end of the oil outlet hole (113) is communicated with the inner cavity of the bearing seat (11); a second end of the oil outlet hole (113) is communicated with the oil outlet channel (302); and the oil outlet hole (113) is tilted so that the second end of the oil outlet hole (113) is tilted toward the oil outlet direction of the oil outlet channel (302).

9. An aircraft engine comprising a bearing (2) and a turbine disk (3), characterized in that: It also includes a bearing seat heat insulation structure according to any one of claims 1 to 8, wherein the bearing seat heat insulation structure is provided between the turbine disk (3) and the bearing (2) and supports and fixes the bearing (2).

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