A compressor with a bleed air structure and an aeroengine

Abstract

The application provides a compressor with a bleed air structure and an aero-engine, and relates to the technical field of aero-engines. The compressor with the bleed air structure is formed with a first air path and a second air path which are connected with a main flow channel and a bleed air hole, and is provided with a rotor blade in the first air path and a stator blade in the second air path, so that a bleed air structure for guiding the airflow in the main flow channel to the bleed air hole is formed. The bleed air amount can be improved without increasing the opening area of the bleed air hole, and then the strength of the rotor disc is ensured on the basis of meeting the demand of the bleed air amount, and the problem of safety hidden danger is avoided.

Description

Technical Field

[0001] This invention relates to the field of aero-engine technology, and more specifically, to a compressor and aero-engine with an air bleed structure. Background Technology

[0002] The compressor is one of the main components of an aero-engine. In an aero-engine, the gas temperature in the main flow channel of the compressor is relatively low and the pressure is relatively high compared to other components. The turbine rotor and stator components, which have relatively high operating temperatures, often need to draw gas from the main flow channel of the compressor to cool the turbine rotor and stator components.

[0003] Generally, compressors have bleed-in ports on the rotor drum wall to draw cooling gas from the compressor's mains flow into the drum cavity, and then to the turbine end for cooling. To ensure the cooling gas reaches the turbine end, a certain flow rate is required. Currently, bleed-in ports are typically located in the high-pressure region of the later stages of the compressor to increase the bleed-in pressure. While this increases the bleed-in pressure, the gas temperature in the high-pressure region is also relatively high, affecting the cooling effect, thus requiring a larger bleed-in volume. As the bleed-in volume increases, the area of ​​the bleed-in ports needs to be larger, leading to a decrease in the strength of the compressor rotor drum and increasing the risk of safety hazards. Summary of the Invention

[0004] The following provides a brief overview of one or more aspects to offer a basic understanding of them. This overview is not an exhaustive summary of all conceived aspects, nor is it intended to identify key or decisive elements of all aspects, nor to define the scope of any or all aspects. Its sole purpose is to present some concepts of one or more aspects in a simplified form to prepare for the more detailed descriptions that follow.

[0005] The purpose of this invention is to provide a compressor with an air intake structure, which can improve the technical problems of reduced rotor drum strength and potential safety hazards caused by increasing the air intake volume by increasing the air intake hole area in existing compressors.

[0006] The present invention also aims to provide an aero engine that can improve the technical problems of reduced rotor drum strength and potential safety hazards caused by increasing the bleed air volume by increasing the bleed air port area in existing technologies.

[0007] Embodiments of the present invention can be implemented in the following ways:

[0008] A compressor with an air bleed structure includes a casing, a rectifying structure, a rotor disk, and a first blade and a second blade. The casing is fitted over the rotor disk. The first blade and the second blade are spaced apart and mounted on the rotor disk, and are used to rotate under the drive of the rotor disk. The rectifying structure is fixedly mounted on the casing and is located between the first blade and the second blade. An air bleed hole is provided on the rotor disk.

[0009] The rotor disk has a first wall and a second wall, and the rectifying structure has a third wall and a fourth wall; the first wall faces the third wall and forms a first air passage extending radially along the rotor disk between the first wall and the third wall; the second wall faces the fourth wall and forms a second air passage extending axially along the rotor disk between the second wall and the fourth wall, the first air passage and the second air passage are connected and used to guide the airflow to the air intake hole;

[0010] The first wall surface is provided with a plurality of rotor blades distributed circumferentially along the rotor disk, the rotor blades being used to draw airflow from the main flow channel into the first air passage; the fourth wall surface is provided with a plurality of stator blades distributed circumferentially along the rotor disk, the stator blades being used to adjust the airflow angle from the first air passage and guide the airflow into the air intake hole.

[0011] Optionally, the second wall surface is further provided with grating teeth, and the fourth wall surface is further provided with a honeycomb structure, the grating teeth and the honeycomb structure cooperate to form a seal; the air vent is provided on the second wall surface and is located between the stator blade and the grating teeth.

[0012] Optionally, the air vent is located downstream of the comb teeth.

[0013] Optionally, the rotor disk includes a first-stage disk and a second-stage disk, with one axial end of the first-stage disk fixedly connected to the second-stage disk; the grating teeth and the air vents are both disposed on the second-stage disk.

[0014] Optionally, the third wall surface is provided with a first wear-resistant coating that faces the rotor blades; and / or,

[0015] The second wall surface is provided with a second wear-resistant coating that is directly opposite the stator blade.

[0016] Optionally, the first wear-resistant coating is spaced apart from the rotor blades, and the distance between the first wear-resistant coating and the rotor blades is 0.6 mm to 0.8 mm; and / or,

[0017] The second wear-resistant coating is spaced apart from the stator blade, and the distance between the second wear-resistant coating and the stator blade is 0.6mm to 0.8mm.

[0018] Optionally, the rectification structure includes rectification blades and an inner ring, the inner ring being sleeved outside the rotor disk and located between the first blade and the second blade; one end of the rectification blade is mounted on the inner ring, and the other end of the rectification blade is mounted on the casing.

[0019] Optionally, the two ends of the rectifier blade are respectively provided with a first T-shaped connecting part and a second T-shaped connecting part, the inner ring is provided with a first T-shaped groove, the first T-shaped groove is engaged with the first T-shaped connecting part, and the casing is provided with a second T-shaped groove, the second T-shaped groove is engaged with the second T-shaped connecting part.

[0020] Optionally, the first blade and the second blade are blades of the intermediate stage of the compressor with the bleed air structure.

[0021] An aircraft engine comprising the compressor having the bleed air structure described above.

[0022] The beneficial effects of the compressor and aero-engine with bleed air structure provided by the embodiments of the present invention include:

[0023] An embodiment of the present invention provides a compressor with an air bleed structure, comprising a casing, a rectifying structure, a rotor disk, and first and second blades. The casing is fitted over the rotor disk, thus forming a main flow channel between the casing and the rotor disk. The first and second blades are spaced apart on the rotor disk and can rotate under the drive of the rotor disk, thereby pressurizing the airflow in the main flow channel. Simultaneously, an air bleed hole is provided on the rotor disk to draw the gas out of the main flow channel. The rectifying structure is fixedly mounted on the casing and is located between the first and second blades. The rotor disk has a first wall and a second wall, and the rectifying structure has a third wall and a fourth wall. The first and third walls face each other and form a first air passage extending radially along the rotor disk. The second and fourth walls face each other and form a second air passage extending axially along the rotor disk. The first and second air passages communicate with each other and are used to guide the airflow to the air bleed hole. Multiple rotor blades extending circumferentially along the rotor disk are arranged on the first wall surface. These rotor blades are used to draw airflow from the main flow channel into the first air passage. Multiple stator blades extending axially along the rotor disk are arranged on the fourth wall surface. These stator blades are used to adjust the airflow angle from the first air passage and guide the airflow into the air intake hole. By setting rotor blades and stator blades in the first and second air passages respectively, an air intake structure is formed that guides the airflow in the main flow channel to the air intake hole. This increases the air intake volume without increasing the opening area of ​​the air intake hole, thereby ensuring the strength of the rotor disk while meeting the air intake volume requirements and avoiding potential safety hazards.

[0024] Embodiments of the present invention also provide an aero-engine comprising the aforementioned compressor with a bleed air structure. Since this aero-engine includes the aforementioned compressor with an aero-structure, it also has the beneficial effect of increasing the bleed air volume without increasing the opening area of ​​the bleed air vents, thereby ensuring the strength of the rotor disk while meeting the bleed air volume requirements and avoiding potential safety hazards. Attached Figure Description

[0025] The above-described features and advantages of the present invention will be better understood after reading the following detailed description of embodiments of the present disclosure in conjunction with the accompanying drawings. In the drawings, components are not necessarily drawn to scale, and components having similar related characteristics or features may have the same or similar reference numerals.

[0026] Figure 1 A compressor with an air intake structure according to one aspect of the present invention is shown.

[0027] Figure label:

[0028] 100 - Compressor; 110 - Rotor disc; 111 - First stage disc; 112 - First drum; 113 - First impeller disc; 114 - First mounting platform; 115 - Second stage disc; 116 - Second drum; 117 - Second impeller disc; 118 - Second mounting platform; 119 - First wall surface; 121 - Second wall surface; 122 - Second wear-resistant coating; 123 - Air intake port; 124 - Grate teeth; 131 - First blade; 132 - Second blade; 133 - Main flow channel; 140 - Complete unit Flow structure; 141-Inner ring; 142-Third wall surface; 143-Fourth wall surface; 144-Honeycomb structure; 145-First wear-resistant coating; 147-First T-groove; 148-Rectifying blade; 149-First T-shaped connection; 151-Second T-shaped connection; 160-Casing; 161-First casing section; 162-Second casing section; 163-Second T-groove; 171-First air passage; 172-Second air passage; 173-Rotor blade; 174-Stator blade. Detailed Implementation

[0029] The present invention will now be described in detail with reference to the accompanying drawings and specific embodiments. It should be noted that the aspects described below with reference to the accompanying drawings and specific embodiments are merely exemplary and should not be construed as limiting the scope of protection of the present invention in any way.

[0030] In the description of this invention, it should be noted that if terms such as "upper," "lower," "inner," "outer," or "vertical" appear, the orientation or positional relationship indicated is based on the orientation or positional relationship shown in the accompanying drawings, or the orientation or positional relationship in which the product of this invention is usually placed when in use, and does not indicate or imply that the device or element referred to must have a specific orientation or be constructed and operated in a specific orientation, and therefore should not be construed as a limitation of this invention.

[0031] At the same time, it should be noted that the terms "first" and "second" are used only for distinguishing descriptions and should not be interpreted as indicating or implying relative importance.

[0032] In the description of this invention, it should also be noted that, unless otherwise explicitly specified or limited, the terms "installation," "connection," and "linking" should be interpreted broadly. For example, they can refer to a fixed connection, an integral connection, or a detachable connection; they can refer to a mechanical connection or an electrical connection; they can refer to a direct connection or an indirect connection through an intermediate medium, or a connection within two components, etc. Those skilled in the art can understand the specific meaning of the above terms in this invention according to the specific circumstances.

[0033] Figure 1 This is a partial structural schematic diagram of the compressor 100 with an air bleed structure provided in this embodiment. Please refer to... Figure 1This embodiment provides a compressor 100 with an air bleed structure, hereinafter referred to as compressor 100. An aero-engine (not shown in the figure) is also provided.

[0034] The aero engine includes a compressor 100, as well as other components such as a turbine. The compressor 100 is connected to the turbine, thereby cooling the stationary rotor components of the turbine by bleed air in the main flow channel 133 of the compressor 100.

[0035] The compressor 100 includes a casing 160, a rectifying structure 140, a rotor disk 110, and first blades 131 and second blades 132. The casing 160 is fitted over the rotor disk 110, thus forming a main flow channel 133 between the casing 160 and the rotor disk 110. The first blades 131 and second blades 132 are spaced apart and mounted on the rotor disk 110, and can rotate under the drive of the rotor disk 110, thereby pressurizing the airflow in the main flow channel 133. At the same time, the rotor disk 110 has an air duct 123 to draw the gas out of the main flow channel 133. The rectifying structure 140 is fixedly mounted on the casing 160 and is located between the first blades 131 and second blades 132. The rotor disk 110 has a first wall 119 and a second wall 121, and the rectifying structure 140 has a third wall 142 and a fourth wall 143. The first wall 119 and the third wall 142 face each other and form a first air passage 171 extending radially along the rotor disk 110. The second wall 121 and the fourth wall 143 face each other and form a second air passage 172 extending axially along the rotor disk 110. The first air passage 171 and the second air passage 172 communicate with each other and are used to guide the airflow to the air intake hole 123. A plurality of rotor blades 173 extending circumferentially along the rotor disk 110 are provided on the first wall 119. The rotor blades 173 are used to draw the airflow from the main flow channel 133 into the first air passage 171. A plurality of stator blades 174 extending axially along the rotor disk 110 are provided on the fourth wall 143. The stator blades 174 are used to adjust the airflow angle from the first air passage 171 and guide the airflow to flow into the air intake hole 123. By setting rotor blades 173 and stator blades 174 in the first air passage 171 and the second air passage 172 respectively, an air intake structure is formed to guide the airflow in the main flow channel 133 to the air intake hole 123. This can increase the air intake volume without increasing the opening area of ​​the air intake hole 123, thereby ensuring the strength of the rotor disk 110 while meeting the air intake volume requirements and avoiding potential safety hazards.

[0036] The compressor 100 with an air bleed structure provided in this embodiment will be further described below:

[0037] Please continue to refer to Figure 1In this embodiment, the rotor disk 110 includes a first-stage disk 111 and a second-stage disk 115, with one axial end of the first-stage disk 111 fixedly connected to the second-stage disk 115. Specifically, both the first-stage disk 111 and the second-stage disk 115 are cylindrical structures, coaxially connected and fixed. In other words, the first-stage disk 111 and the second-stage disk 115 are coaxially arranged, the axial direction of the first-stage disk 111 and the second-stage disk 115 is the axial direction of the rotor disk 110, and the radial direction of the first-stage disk 111 and the second-stage disk 115 is the radial direction of the rotor disk 110.

[0038] The first-stage disk 111 includes a first wheel disk and a first drum 112 connected to each other. The first drum 112 has a cylindrical structure. The first wheel disk has a first mounting platform 114 protruding radially outward from the first drum 112. A first blade 131 is mounted on the first mounting platform 114. When the rotor disk 110 rotates, the first blade 131 rotates synchronously with the first-stage disk 111. Similarly, the second-stage disk 115 includes a second wheel disk 117113 and a second drum 116 connected to each other. The second drum 116 has a cylindrical structure. The first drum 112 and the second drum 116 are coaxially connected and fixed, thereby realizing the coaxial connection between the first-stage disk 111 and the second-stage disk 115. The second wheel disk 117113 has a second mounting platform 118 that protrudes radially outward from the second drum 116. The second blade 132 is mounted on the second mounting platform 118. When the rotor disk 110 rotates, the second blade 132 rotates synchronously with the second stage disk 115.

[0039] It should be noted that since the main flow channel 133 in the compressor 100 is formed between the casing 160 and the rotor disk 110, the main flow channel 133 is the interior of the compressor 100. In other words, the interior of the compressor 100 is located on the outside of the rotor disk 110 and the inside of the casing 160.

[0040] In this embodiment, the second wall surface 121 is further provided with grating teeth 124, and the fourth wall surface 143 is further provided with a honeycomb structure 144. The grating teeth 124 and the honeycomb structure 144 cooperate to form a seal. The air duct 123 is provided on the second wall surface 121 and is located between the stator blade 174 and the grating teeth 124. In this way, the airflow introduced from the first air passage 171 into the second air passage 172 is blocked by the sealing structure and can flow more into the air duct 123, thereby increasing the air intake of the air duct 123.

[0041] Furthermore, the air intake hole 123 is located downstream of the comb teeth 124. The air pressure upstream of the comb teeth 124 is lower than the air pressure downstream of the comb teeth 124. Therefore, by setting the air intake hole 123 downstream of the comb teeth 124, the first air passage 171 and the second air passage 172 are located downstream of the comb teeth 124, which helps to increase the air intake pressure of the air intake hole 123 and increase the air intake volume.

[0042] Specifically, the first blade 131 is located upstream of the second blade 132; in other words, the first blade 131 is closer to the air inlet of the compressor 100 than the second blade 132. The bleed-out port 123 is located downstream of the grate 124, meaning the bleed-out port 123 is located on the side of the grate 124 closest to the second impeller 117113. In this embodiment, the first wall surface 119 is the wall surface of the second mounting platform 118 near the rectifier structure 140; in other words, the rotor blade 173 is fixedly connected to the second mounting platform 118, and the second wall surface 121 is the wall surface of the second drum 116 located upstream of the second mounting platform 118. Thus, the first air passage 171 formed between the first wall 119 and the rectifier structure 140 is located downstream of the rectifier structure 140 and extends radially along the compressor 100. The second air passage 172 formed between the second wall 121 and the rectifier structure 140 guides the airflow in the first air passage 171 toward the air intake 123 in the direction from the outlet end to the inlet end of the compressor 100. In other words, the airflow direction in the second air passage 172 is opposite to the airflow direction in the main flow channel 133.

[0043] Optionally, the rotor blades 173 are fixedly connected to the second-stage disk 115 by welding. It is understood that in some other embodiments, the rotor blades 173 and the second-stage disk 115 may also be configured as an integrally formed structure.

[0044] During operation, the rotor blades 173 rotate with the rotor disk 110, thereby drawing in the airflow from the main flow channel 133 and pressurizing it. The blade profile of the rotor blades 173 can be that of a pressurizing blade, with specific dimensions determined by the distance between the rectifying structure 140 and the second mounting platform 118. The stator blades 174 are mounted on the rectifying structure 140 and therefore do not rotate with the rotor disk 110. The stator blades 174 decelerate and pressurize the airflow drawn from the first air passage 171. They also adjust the airflow angle, reduce circumferential movement, guide the airflow into the intake port 123, and suppress overflow near the intake port. Optionally, the stator blades 174 can adopt the blade profile of a conventional compressor stator blade.

[0045] In this embodiment, both the grating teeth 124 and the air vents 123 are disposed on the second stage disk 115. Specifically, the second wall surface 121 is the outer peripheral surface of the second drum 116, the grating teeth 124 are disposed at one end of the second drum 116 near the first stage disk 111, and the air vents 123 are disposed on the side of the grating teeth 124 near the second mounting platform 118.

[0046] The rectifying structure 140 includes rectifying blades 148 and an inner ring 141. The inner ring 141 is sleeved outside the rotor disk 110 and is located between the first blade 131 and the second blade 132. One end of the rectifying blade 148 is mounted on the inner ring 141, and the other end of the rectifying blade 148 is mounted on the casing 160. The rectifying blade 148 is fixedly mounted on the casing 160, so during the operation of the compressor 100, the rectifying blade 148 is fixed relative to the casing 160, and correspondingly, the inner ring 141 is also fixed relative to the casing 160. The third wall surface 142 of the rectifying structure 140 is the axial side wall surface of the inner ring 141 located downstream, and the fourth wall surface 143 of the rectifying structure 140 is the inner circumferential surface of the inner ring 141. A stator blade 174 is provided at one downstream end of the fourth wall surface 143. A honeycomb structure 144 is provided on the fourth wall surface 143 closer to the upstream of the stator blade 174. The honeycomb structure 144 cooperates with the grating teeth 124 to seal the structure. Optionally, the stator blade 174 can be fixed to the inner ring 141 by welding. It is understood that in some other embodiments, the inner ring 141 and the stator blade 174 can be integrally formed.

[0047] Optionally, the two ends of the rectifier blade 148 are respectively provided with a first T-shaped connecting portion 149 and a second T-shaped connecting portion 151. A first T-shaped groove 147 is provided on the inner ring 141, and the first T-shaped connecting portion 149 engages with the first T-shaped groove 147 to connect the inner ring 141 and the rectifier blade 148. A second T-shaped groove 163 is provided on the casing 160, and the second T-shaped groove 163 engages with the second T-shaped connecting portion 151 to connect the rectifier blade 148 and the casing 160.

[0048] Specifically, there are multiple rectifier blades 148. The inner ring 141 is an annular component surrounding the rotor disk 110. Multiple rectifier blades 148 are circumferentially distributed and installed on the inner ring 141. The radial outer ends of the multiple rectifier blades 148 are connected to the casing 160. Thus, the multiple rectifier blades 148 are circumferentially distributed in the main flow channel 133 and located between the first blade 131 and the second blade 132, rectifying the airflow between the first blade 131 and the second blade 132.

[0049] The casing 160 includes multiple casing sections, which are distributed sequentially along the axial direction of the compressor 100. The casing sections located outside the first stage disk 111 and the second stage disk 115 are the first casing section 161 and the second casing section 162, respectively. A second T-shaped groove 163 is formed at the connection between the first casing section 161 and the second casing section 162.

[0050] Optionally, in this embodiment, the rotor disk 110 is provided with a plurality of air vents 123, which are distributed circumferentially along the rotor disk 110. Specifically, the number of air vents 123, the number of rotor blades 173, and the number of stator blades 174 can be set to be the same.

[0051] In this embodiment, to improve operational safety and stability, a first wear-resistant coating 145 is also provided on the third wall surface 142, facing the rotor blade 173. Similarly, a second wear-resistant coating 122 is also provided on the second wall surface 121, facing the stator blade 174. By providing wear-resistant coatings, wear on the third wall surface 142 can be effectively avoided when the rotor blade 173 rotates relative to the third wall surface 142, and wear on the second wall surface 121 when it rotates relative to the rotor blade 173. It should be noted that in this embodiment, the compressor 100 is provided with both the first wear-resistant coating 145 and the second wear-resistant coating 122. It is understood that in some other embodiments, only the first wear-resistant coating 145 or the second wear-resistant coating 122 may be provided.

[0052] Further, the first wear-resistant coating 145 is spaced apart from the rotor blade 173, and the distance between the first wear-resistant coating 145 and the rotor blade 173 is 0.6mm to 0.8mm. Optionally, the distance between the first wear-resistant coating 145 and the rotor blade 173 can be set to 0.6mm, 0.7mm, or 0.8mm. Further, the second wear-resistant coating 122 is spaced apart from the stator blade 174, and the distance between the second wear-resistant coating 122 and the stator blade 174 is 0.6mm to 0.8mm. Optionally, the distance between the second wear-resistant coating 122 and the stator blade 174 can be set to 0.6mm, 0.7mm, or 0.8mm.

[0053] It should be noted that, due to the thermal expansion and contraction caused by temperature during the operation of the compressor 100, the gap will decrease as the temperature rises, because the gap mentioned above in this application is the distance in the cold state.

[0054] Because the compressor 100 provided in this embodiment has an air bleed structure, the air bleed volume can be increased. Therefore, compared with the existing compressor 100, the position of the air bleed port 123 can be advanced. Optionally, the air bleed port 123 can be set in an intermediate stage of the compressor 100. In other words, the first blade 131 and the second blade 132 can be blades of an intermediate stage of the compressor 100. Taking a 10-stage compressor 100 as an example, the first blade 131 and the second blade 132 can be the fifth and sixth stage blades of the compressor 100, while in the existing compressor 100, the air bleed port 123 is generally set between the seventh and eighth stages. The advanced position of the air bleed port 123 means that the airflow temperature in the main flow channel 133 is lower, and the cooling effect of the low-temperature gas is better.

[0055] Embodiments of the present invention provide a compressor 100 and an aero-engine with an bleed air structure. By providing an bleed air structure formed by rotor blades 173 and stator blades 174 in the compressor 100, the bleed air volume of the bleed air orifice 123 is increased, improving bleed air efficiency and reducing the area of ​​the bleed air orifice 123, thereby enhancing the strength of the rotor disk 110. Moreover, by advancing the bleed air position in the casing, the bleed air flow temperature is lower, thereby improving the cooling effect.

[0056] The above description is merely a specific embodiment of the present invention, but the scope of protection of the present invention is not limited thereto. Any variations or substitutions that can be easily conceived by those skilled in the art within the scope of the technology disclosed in the present invention should be included within the scope of protection of the present invention.

Claims

1. A compressor with an air bleed structure, the compressor comprising a casing, a rectifying structure, a rotor disk, and a first blade and a second blade, the casing being fitted over the rotor disk; the first blade and the second blade being spaced apart and mounted on the rotor disk, and used to rotate under the drive of the rotor disk; the rectifying structure being fixedly mounted on the casing, and the rectifying structure being located between the first blade and the second blade; the rotor disk having air bleed holes; characterized in that, The rotor disk has a first wall and a second wall, and the rectifying structure has a third wall and a fourth wall; the first wall faces the third wall and forms a first air passage extending radially along the rotor disk between the first wall and the third wall; the second wall faces the fourth wall and forms a second air passage extending axially along the rotor disk between the second wall and the fourth wall, the first air passage and the second air passage are connected and used to guide the airflow to the air intake hole; The first wall surface is provided with a plurality of rotor blades distributed circumferentially along the rotor disk, the rotor blades being used to draw airflow from the main flow channel into the first air passage; the fourth wall surface is provided with a plurality of stator blades distributed circumferentially along the rotor disk, the stator blades being used to adjust the airflow angle from the first air passage and guide the airflow into the air intake hole.

2. The compressor with an air bleed structure according to claim 1, characterized in that, The second wall surface is also provided with grating teeth, and the fourth wall surface is also provided with a honeycomb structure. The grating teeth and the honeycomb structure cooperate to form a seal. The air vent is provided on the second wall surface and is located between the stator blade and the grating teeth.

3. The compressor with an air bleed structure according to claim 2, characterized in that, The air intake hole is located downstream of the comb teeth.

4. The compressor with an air induced draft structure according to claim 2, characterized in that, The rotor disk includes a first-stage disk and a second-stage disk, with one axial end of the first-stage disk fixedly connected to the second-stage disk; the grating teeth and the air vents are both disposed on the second-stage disk.

5. The compressor with an air bleed structure according to claim 1, characterized in that, The third wall surface is provided with a first wear-resistant coating that is directly opposite the rotor blade; and / or, The second wall surface is provided with a second wear-resistant coating that is directly opposite the stator blade.

6. The compressor with an air bleed structure according to claim 5, characterized in that, The first wear-resistant coating is spaced apart from the rotor blades, and the distance between the first wear-resistant coating and the rotor blades is 0.6 mm to 0.8 mm; and / or, The second wear-resistant coating is spaced apart from the stator blade, and the distance between the second wear-resistant coating and the stator blade is 0.6mm to 0.8mm.

7. The compressor with an air bleed structure according to claim 1, characterized in that, The rectification structure includes rectification blades and an inner ring. The inner ring is sleeved outside the rotor disk and is located between the first blade and the second blade. One end of the rectification blade is mounted on the inner ring, and the other end of the rectification blade is mounted on the casing.

8. The compressor with an air bleed structure according to claim 7, characterized in that, The rectifier blade is provided with a first T-shaped connecting part and a second T-shaped connecting part at both ends, and a first T-shaped groove is provided on the inner ring. The first T-shaped groove is engaged with the first T-shaped connecting part. The casing is provided with a second T-shaped groove, and the second T-shaped groove is engaged with the second T-shaped connecting part.

9. The compressor with an air bleed structure according to claim 1, characterized in that, The first blade and the second blade are blades of the intermediate stage of the compressor with the bleed air structure.

10. An aircraft engine, characterized in that, The aero-engine includes a compressor with an air bleed structure as described in any one of claims 1-9.

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