Compressors and aircraft engines

Abstract

The present invention relates to a compressor and an aeroengine, wherein the compressor comprises a first blade (10) and a first edge plate (20), wherein the first edge plate (20) is connected to the root of the first blade (10), wherein the first edge plate (20) comprises a first edge plate front portion (21) extending from the leading edge of the first blade (10) in a direction away from the trailing edge of the first blade (10), wherein the first edge plate front portion (21) comprises a first top surface close to the first blade (10) in a radial direction, wherein the first top surface comprises a first curved surface section away from the first blade (10) and a first plane section close to the first blade (10). The aeroengine comprises a compressor. The present invention has a guiding and rectifying effect on airflow, can make the airflow flow more stable, reduce airflow disturbance, and reduce aerodynamic loss.

Description

Technical Field

[0001] The present invention relates to the technical field of aeroengines, and in particular to a compressor and an aeroengine. Background Art

[0002] An axial flow compressor is a compressor in which the flow direction of the airflow in the meridian plane is basically parallel to the rotor axis. The compressor includes a series of stators and rotors arranged alternately for gas transportation and compression. For the rotor blades in an axial flow compressor, the part connected to the shaft is the blade root. For the stator components, especially the stator components using the comb tooth sealing method, the part close to the rotating shaft sealing position is the blade root. In order to realize the shape of the flow channel, an edge plate extending along the flow channel is provided at the blade root. The rotor blades are mainly fixed in the circumferential direction by the edge plate at the blade root.

[0003] In order to avoid collision between the edge plate at the root of the stator blade and the edge plate at the root of the rotor blade, a certain axial clearance must be ensured between the edge plates of the rotor and the stator. This gap causes incompleteness of the flow channel at the hub, and it is impossible to meet the aerodynamic design requirements. In order to reduce the leakage loss caused by the root of the cantilever stator, a comb tooth seal is usually used in the structure to solve it. However, the comb tooth seal method will form a cavity structure, and there is a pressure difference before and after the cavity, and a cavity leakage vortex will be generated inside. For different edge plate shapes and comb tooth sealing methods, the cavity leakage amount is very different. An edge plate with an unreasonable structural design will cause the mainstream impact to enter the cavity, causing greater losses. Therefore, it is necessary to optimize the structure of the edge plate.

[0004] It should be noted that the information disclosed in the background technology section of the present invention is only intended to increase the understanding of the overall background of the present invention, and should not be regarded as acknowledging or suggesting in any form that the information constitutes prior art already known to those skilled in the art. Summary of the invention

[0005] The embodiments of the present invention provide a compressor and an aircraft engine, and the structure of the edge plate is optimized.

[0006] According to one aspect of the present invention, there is provided a compressor, comprising:

[0007] a first blade; and

[0008] A first edge plate connected to the root of the first blade;

[0009] Among them, the first edge plate includes a first edge plate front portion extending from the leading edge of the first blade in a direction away from the trailing edge of the first blade, the first edge plate front portion includes a first top surface close to the first blade in the radial direction, and the first top surface includes a first curved surface segment away from the first blade and a first plane segment close to the first blade.

[0010] In some embodiments, the first curved surface segment comprises an arcuate surface.

[0011] In some embodiments, the compressor also includes a second blade, which is arranged adjacent to the first blade and located upstream of the first blade. The line connecting the leading edge point A of the first blade and the trailing edge point B of the second blade is a straight line AB. On a cross section passing through the root chord of the first blade and cut along the radial direction, the first curved surface segment is cut into an arc and the arc is tangent to the straight line AB.

[0012] In some embodiments, the first planar segment gradually moves away from the rotation axis of the compressor in a direction approaching the first blade.

[0013] In some embodiments, the compressor also includes a second blade, which is arranged adjacent to the first blade and located upstream of the first blade. The line connecting the leading edge point A of the first blade and the trailing edge point B of the second blade is a straight line AB. On a cross section passing through the root chord of the first blade and cut along the radial direction, a straight line formed by connecting the endpoint E of the first plane segment close to the first curved surface segment and the leading edge point A of the first blade coincides with the straight line cut into the first plane segment.

[0014] In some embodiments, an axial length of the first curved surface segment is 6% to 10% of a root chord length of the first blade.

[0015] In some embodiments, an axial length of the first planar segment is no less than 2% of a root chord length of the first blade.

[0016] In some embodiments, the compressor also includes a second blade, which is arranged adjacent to the first blade and located upstream of the first blade. The line connecting the leading edge point A of the first blade and the trailing edge point B of the second blade is a straight line AB. On a cross section passing through the root chord of the first blade and cut along the radial direction, the angle between the line connecting the endpoint C of the curve cut into by the first curved surface segment away from the first plane segment and the trailing edge point B of the second blade and the straight line AB is 5° to 7°.

[0017] In some embodiments, the compressor also includes a second blade, which is arranged adjacent to the first blade and located upstream of the first blade. The line connecting the leading edge point A of the first blade and the trailing edge point B of the second blade is a straight line AB. On a cross section passing through the root chord of the first blade and cut along the radial direction, an extension line of a first side edge line cut from a first side surface adjacent to the first top surface and away from the first blade at the front of the first edge plate intersects with the straight line AB at a point D, and a length between an endpoint C away from the first plane segment and point D of the curve cut from the first curved surface segment is not less than 1.5% of the root chord length of the first blade.

[0018] In some embodiments, the compressor further includes a casing, a rotor shaft, a second blade and a second edge plate, the first blade is connected to the casing, the second edge plate is connected to the rotor shaft, and the root of the second blade is connected to the second edge plate.

[0019] In some embodiments, the second edge plate includes a second edge plate front portion extending from the leading edge of the second blade in a direction away from the trailing edge of the second blade, the second edge plate front portion includes a second top surface close to the second blade in a radial direction, the second top surface includes a second curved surface segment away from the second blade and a second planar segment close to the second blade.

[0020] According to another aspect of the present invention, there is provided an aircraft engine comprising the above-mentioned compressor.

[0021] Based on the above technical scheme, the first top surface in the embodiment of the present invention includes a first curved surface section away from the first blade and a first plane section close to the first blade. When the airflow reaches the front of the first edge plate, it can be guided by the first curved surface section to avoid the mainstream entering the cavity formed between the edge plates to cause aerodynamic losses. It can also reduce the vortex entering the cavity, reduce the leakage of the cavity, and reduce flow losses. Moreover, a first plane section is also provided downstream of the first curved surface section. Through the first plane section, the airflow can move smoothly along the plane after passing through the first curved surface section until it reaches the first blade. The first plane section has a rectifying effect on the airflow before entering the first blade, which can make the airflow entering the first blade smoother and reduce airflow disturbance. BRIEF DESCRIPTION OF THE DRAWINGS

[0022] The drawings described herein are used to provide a further understanding of the present invention and constitute a part of this application. The exemplary embodiments of the present invention and their descriptions are used to explain the present invention and do not constitute an improper limitation of the present invention. In the drawings:

[0023] Figure 1 A sectional view of a partial structure of an embodiment of a compressor of the present invention.

[0024] Figure 2 A partial cross-sectional view of an embodiment of a compressor of the present invention.

[0025] Figure 3 It is a schematic diagram of the gas flow inside the compressor in the related technology.

[0026] Figure 4 The figure is a schematic diagram of the gas flow inside an embodiment of the compressor of the present invention.

[0027] In the figure:

[0028] 10. First blade; 20. First edge plate; 21. Front portion of first edge plate; 30. Second blade; 40. Second edge plate; 41. Front portion of second edge plate; 50. Casing; 60. Rotor shaft; 70. Cavity. DETAILED DESCRIPTION

[0029] The technical solutions in the embodiments will be described clearly and completely below in conjunction with the accompanying drawings 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.

[0030] In the description of the present invention, it should be understood that the terms "center", "lateral", "longitudinal", "front", "back", "left", "right", "up", "down", "vertical", "horizontal", "top", "bottom", "inside", "outside" and the like indicate orientations or positional relationships based on the orientations or positional relationships shown in the accompanying drawings, and are only for the convenience of describing the present invention and simplifying the description, rather than indicating or implying that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and therefore should not be understood as limiting the scope of protection of the present invention.

[0031] like Figure 1 As shown, in some embodiments of the compressor provided by the present invention, the compressor includes a first blade 10 and a first edge plate 20, wherein the first edge plate 20 is connected to the root of the first blade 10, wherein the first edge plate 20 includes a first edge plate front portion 21 extending from the leading edge of the first blade 10 in a direction away from the trailing edge of the first blade 10, and the first edge plate front portion 21 includes a first top surface close to the first blade 10 in the radial direction, and the first top surface includes a first curved surface segment away from the first blade 10 and a first plane segment close to the first blade 10. The first curved surface segment is farther away from the first blade 10 than the first plane segment. The first plane segment is located downstream of the first curved surface segment.

[0032] In the above embodiment, the first top surface includes a first curved surface section away from the first blade 10 and a first plane section close to the first blade 10. When the airflow reaches the front portion 21 of the first edge plate, it can be guided through the first curved surface section to avoid the mainstream entering the cavity formed between the edge plates to cause aerodynamic losses. It can also reduce the vortex entering the cavity, reduce the leakage of the cavity, and reduce flow losses. Moreover, a first plane section is also provided downstream of the first curved surface section. Through the first plane section, the airflow can move smoothly along the plane after passing through the first curved surface section until it reaches the first blade 10. The first plane section has a rectifying effect on the airflow before entering the first blade 10, which can make the airflow entering the first blade 10 smoother and reduce airflow disturbances.

[0033] In some embodiments, the first planar section is connected to the leading edge of the root of the first blade 10 .

[0034] In some embodiments, the first curved surface segment includes an arc-shaped surface. The arc-shaped surface is smoother and can make the airflow flow more smoothly when guiding the airflow, reduce the generation of vortices, and reduce the impact on aerodynamic losses.

[0035] like Figure 2 As shown, in some embodiments, the compressor also includes a second blade 30, which is arranged adjacent to the first blade 10 and is located upstream of the first blade 10, and a line connecting a leading edge point A of the first blade 10 and a trailing edge point B of the second blade 30 is a straight line AB, and on a cross section passing through the root chord of the first blade 10 and cut along the radial direction, the first curved surface segment is cut into an arc and the arc is tangent to the straight line AB.

[0036] The mainstream direction of the airflow from the trailing edge of the second blade 30 is roughly the same as the direction of the straight line AB. Therefore, setting the arc to be tangent to the straight line AB allows the airflow to continue to flow smoothly downstream along the arc surface when it reaches the front portion 21 of the first edge plate, thereby reducing the generation of vortices and reducing airflow disturbances.

[0037] In some embodiments, the first plane segment gradually moves away from the rotation axis of the compressor in a direction close to the first blade 10. The first plane segment is tilted relative to the rotation axis of the compressor.

[0038] like Figure 2 As shown, in the direction approaching the first blade 10 , the first plane segment is inclined upward.

[0039] In some embodiments, the compressor further includes a second blade 30, which is arranged adjacent to the first blade 10 and is located upstream of the first blade 10. The line connecting the leading edge point A of the first blade 10 and the trailing edge point B of the second blade 30 is a straight line AB. On a cross section passing through the root chord of the first blade 10 and cut along the radial direction, the straight line formed by connecting the end point E of the curve cut into the first curved surface segment close to the first plane segment and the leading edge point A of the first blade 10 coincides with the straight line cut into the first plane segment. This arrangement enables the mainstream airflow to flow toward the first blade 10 along the first plane segment after being guided by the first curved surface segment. In the first plane segment, the airflow can be rectified to make the flow more uniform and stable.

[0040] In some embodiments, the axial length of the first curved surface segment is 6% to 10% of the root chord length of the first blade 10 , such as 6%, 7%, 8%, 9%, and 10%.

[0041] In some embodiments, the axial length of the first planar segment is not less than 2% of the root chord length of the first blade 10 , such as 2%, 2.5%, 3%, 4%, etc.

[0042] In some embodiments, the compressor also includes a second blade 30, which is arranged adjacent to the first blade 10 and is located upstream of the first blade 10, and a line connecting a leading edge point A of the first blade 10 and a trailing edge point B of the second blade 30 is a straight line AB, and on a cross section passing through the root chord of the first blade 10 and cut along a radial direction, an angle between a line connecting an endpoint C of the curve cut into by the first curved surface segment away from the first plane segment and the trailing edge point B of the second blade 30 and the straight line AB is 5° to 7°, for example, 5°, 6° and 7°.

[0043] In some embodiments, the compressor also includes a second blade 30, which is arranged adjacent to the first blade 10 and is located upstream of the first blade 10, and the line connecting the leading edge point A of the first blade 10 and the trailing edge point B of the second blade 30 is a straight line AB. On a cross section passing through the root chord of the first blade 10 and cut along the radial direction, an extension line of the first side edge line of the first edge plate front portion 21 adjacent to the first top surface and away from the first blade 10 is cut and intersects with the straight line AB at point D, and the length between the endpoint C of the curve cut into the first curved surface segment away from the first plane segment and point D is not less than 1.5% of the root chord length of the first blade 10, such as 1.5%, 2%, 2.5% and 3%, etc.

[0044] In some embodiments, the compressor further includes a casing 50, a rotor shaft 60, a second blade 30, and a second edge plate 40. The first blade 10 is connected to the casing 50, the second edge plate 40 is connected to the rotor shaft 60, and the root of the second blade 30 is connected to the second edge plate 40. In this embodiment, the first blade 10 is a stator blade, the second blade 30 is a rotor blade, the front end of the first edge plate 20 connected to the root of the stator blade is configured to include a first curved surface segment and a first plane segment, and the front end of the second edge plate 40 connected to the root of the rotor blade can be configured to have the same structure as the front end of the first edge plate 20, or can be configured to have a different structure.

[0045] In some embodiments, the second edge plate 40 includes a second edge plate front portion 41 extending from the leading edge of the second blade 30 in a direction away from the trailing edge of the second blade 30, the second edge plate front portion 41 includes a second top surface close to the second blade 30 in the radial direction, and the second top surface includes a second curved surface segment away from the second blade 30 and a second flat surface segment close to the second blade 30. In this embodiment, the front end structure of the second edge plate 40 is the same as the front end structure of the first edge plate 20, and other setting dimensions can also refer to the settings of the first edge plate 20 in the above-mentioned various embodiments.

[0046] In some embodiments, the second edge plate 40 includes a second edge plate rear portion extending from the trailing edge of the second blade 30 in a direction away from the leading edge of the second blade 30, the second edge plate rear portion includes a second bottom surface away from the second blade 30 in the radial direction, the first edge plate front portion 21 includes a first bottom surface away from the first blade 10 in the radial direction, and the first bottom surface and the second bottom surface are located at the same radial height, that is, the distance between the first bottom surface and the second bottom surface and the rotation axis of the compressor is the same. This arrangement can eliminate the step difference between the first bottom surface and the second bottom surface, increase the difficulty of the mainstream entering the cavity 70, reduce the gas entering the cavity 70, thereby reducing the cavity leakage and reducing the aerodynamic loss caused by the step difference.

[0047] In some embodiments, the first edge plate 20 includes a first edge plate rear portion extending from the trailing edge of the first blade 10 in a direction away from the leading edge of the first blade 10, and the first edge plate rear portion includes a first bottom surface away from the first blade 10 in the radial direction, and the first bottom surface is located at the same radial height as the second bottom surface of the second blade 30 located downstream of the first blade 10. This arrangement can increase the difficulty of the airflow in the rear row of the cavity 70 to flow back to the front row of the cavity 70 and the difficulty of the airflow inside the cavity 70 to flow into the main flow channel, reduce boundary layer mixing, and reduce mixing loss.

[0048] The structural optimization process of an embodiment of the compressor of the present invention is described below:

[0049] like Figure 1 As shown, the compressor includes a casing 50, a rotor shaft 60, a plurality of first blades 10 and a plurality of second blades 30, wherein the first blades 10 and the second blades 30 can be arranged alternately, wherein the first blades 10 are stator blades mounted on the casing 50, and the second blades 30 are rotor blades connected to the rotor shaft 60.

[0050] A first edge plate 20 is provided at the root of the first blade 10 close to the rotor shaft 60 , and the first edge plate 20 is sealed with the outer cylinder wall of the rotor shaft 60 by means of comb teeth. A second edge plate 40 is connected between the second blade 30 and the rotor shaft 60 .

[0051] Taking the adjacent first blade 10 and second blade 30 as an example, the first blade 10 is located downstream of the second blade 30, there is a preset distance between the first blade 10 and the second blade 30, and there is a preset distance between the first edge plate 20 and the second edge plate 40. A cavity 70 with an opening is formed between the rotor shaft 60, the first edge plate 20 and the second edge plate 40, and there is a pressure difference at the opening of the cavity 70, driving the fluid in the cavity 70 to flow.

[0052] like Figure 2 As shown, when optimizing the first top surface shape of the first edge plate 20, the specific operation steps include:

[0053] First, the root chord line of the first blade 10 is longitudinally cut along the radial direction to the first blade 10 and the first edge plate 20 to obtain a first cross section, which includes the leading edge point A of the first blade 10 and the first side line of the first edge plate 20 away from the first blade 10; the root chord line of the second blade 30 is longitudinally cut along the radial direction to the second blade 30 and the second edge plate 40 to obtain a second cross section, which includes the trailing edge point B of the second blade 30;

[0054] Then, the trailing edge point B of the second blade 30 and the leading edge point A of the first blade 10 are connected to obtain a straight line AB;

[0055] With point B as the center, rotate straight line AB clockwise. After rotating by a preset angle (5° to 7°), the intersection of straight line AB and the first side line is point C;

[0056] A first straight line parallel to the first side line is drawn on the side of the first side line close to the first blade 10, the axial length between the first straight line and the first side line is L1, L1 is 6% to 10% of the root chord length of the first blade 10, and the intersection of the first straight line and the straight line AB is point E;

[0057] Draw a circle based on point C, point E and straight line AB, which passes through point C and point E and is tangent to straight line AB, to obtain the curve formed by the first curved surface segment on the first section (specifically, draw a second straight line perpendicular to straight line AB through point E, connect point C and point E and draw a third straight line passing through the center point of line segment CE and perpendicular to line segment CE, the intersection of the second straight line and the third straight line is the center of the circle, and after finding the center of the circle, draw an arc passing through point C and point E, which is the curve formed by the first curved surface segment on the first section);

[0058] At this point, the optimization of the first top surface of the first edge plate 20 is completed, wherein the arc CE is a curve formed by the first curved surface segment on the first cross section, and the line segment EA is a line segment formed by the first plane segment on the first cross section.

[0059] The optimization method of the second top surface of the second edge plate 40 is the same as the optimization method of the first top surface of the first edge plate 20 , and will not be repeated here.

[0060] like Figure 3The figure is a schematic diagram of the compressor structure before optimization. The compressor includes a plurality of first blades 10' and a plurality of second blades 30'. The first blades 10' are mounted on the casing 50', and the second blades 30' are mounted on the rotor shaft 60'. A first edge plate 20' is provided at the root of the first blade 10', and a second edge plate 40' is provided between the second blade 30' and the rotor shaft 60'. A cavity 70' is formed between the rotor shaft 60', the first edge plate 20' and the second edge plate 40'. Before optimization, the first top surface of the first edge plate 20' and the second top surface of the second edge plate 40' are both straight inclined surfaces inclined upward. When the airflow flows from the trailing edge of the second blade 30' to the first top surface, a large airflow disturbance will occur. There are many vortices in the cavity 70', and the flow mixing of the airflow in the radial direction is relatively intense, and the mixing loss is large. The airflow in the cavity is always in an unstable state, and the aerodynamic loss is large.

[0061] like Figure 4 As shown, after the compressor edge plate structure is optimized, the front end of the first top surface of the first edge plate 20 is a curved surface segment, and the rear end is a flat surface segment. Under the drainage effect of the curved surface segment, the airflow from the upstream flows more to the downstream blades, effectively reducing the amount of air entering the cavity 70, and the airflow field in the cavity 70 is more stable, significantly reducing aerodynamic losses and improving the margin of the compressor.

[0062] Through the description of multiple embodiments of the compressor of the present invention, it can be seen that the leading edge structure of the blade edge plate in the compressor of the present invention is optimized, which makes up for the deficiencies in the aerodynamic flow channel design process and meets the requirements of aerodynamic performance. The influence of fluid expansion during the flow process is taken into account between the leading and trailing edge surfaces, thereby minimizing the pressure difference in the cavity and reducing cavity leakage losses.

[0063] In various embodiments of the present invention, the compressor may be an axial flow compressor.

[0064] Based on the above-mentioned compressor, the present invention also proposes an aircraft engine, which includes the above-mentioned compressor.

[0065] The positive technical effects of the compressor in the above-mentioned embodiments are also applicable to aircraft engines and will not be described in detail here.

[0066] Finally, it should be noted that the above embodiments are only used to illustrate the technical solution of the present invention rather than to limit it. Although the present invention has been described in detail with reference to the preferred embodiments, ordinary technicians in the field should understand that without departing from the principles of the present invention, the specific implementation methods of the present invention can still be modified or some technical features can be replaced by equivalents, and these modifications and equivalent replacements should be included in the scope of the technical solution for protection of the present invention.

Claims

1. A compressor, characterized in that: include: A first blade (10); and A first edge plate (20) connected to the root of the first blade (10); The first edge plate (20) includes a first edge plate front portion (21) extending from the leading edge of the first blade (10) in a direction away from the trailing edge of the first blade (10), the first edge plate front portion (21) includes a first top surface close to the first blade (10) in a radial direction, and the first top surface includes a first curved surface segment away from the first blade (10) and a first plane segment close to the first blade (10).

2. The compressor according to claim 1, characterized in that: The first curved surface segment includes an arc-shaped surface.

3. The compressor according to claim 1, characterized in that: The invention also comprises a second blade (30), wherein the second blade (30) is arranged adjacent to the first blade (10) and is located upstream of the first blade (10), a line connecting a leading edge point A of the first blade (10) and a trailing edge point B of the second blade (30) is a straight line AB, and on a cross section passing through a root chord of the first blade (10) and cut along a radial direction, the first curved surface segment is cut into a circular arc and the circular arc is tangent to the straight line AB.

4. The compressor according to claim 1, characterized in that: The first plane section gradually moves away from the rotation axis of the compressor in a direction approaching the first blade (10).

5. The compressor according to claim 1, characterized in that: The invention also comprises a second blade (30), wherein the second blade (30) is arranged adjacent to the first blade (10) and the second blade (30) is located upstream of the first blade (10), a line connecting a leading edge point A of the first blade (10) and a trailing edge point B of the second blade (30) is a straight line AB, and on a cross section passing through a root chord of the first blade (10) and cut along a radial direction, a straight line formed by connecting an end point E of the first curved surface segment close to the first plane segment and the leading edge point A of the first blade (10) coincides with a straight line formed by connecting the first plane segment.

6. The compressor according to claim 1, characterized in that: The axial length of the first curved surface segment is 6% to 10% of the root chord length of the first blade (10).

7. The compressor according to claim 1, characterized in that: The axial length of the first plane section is not less than 2% of the root chord length of the first blade (10).

8. The compressor according to claim 1, characterized in that: The invention also comprises a second blade (30), wherein the second blade (30) is arranged adjacent to the first blade (10) and the second blade (30) is located upstream of the first blade (10), a line connecting a leading edge point A of the first blade (10) and a trailing edge point B of the second blade (30) is a straight line AB, and on a cross section passing through a root chord of the first blade (10) and cut along a radial direction, an angle between a line connecting an end point C of the curve cut into by the first curved surface segment, which is away from the first plane segment, and the trailing edge point B of the second blade (30) and the straight line AB is 5° to 7°.

9. The compressor according to claim 1, characterized in that: The invention also comprises a second blade (30), wherein the second blade (30) is arranged adjacent to the first blade (10) and the second blade (30) is located upstream of the first blade (10); a line connecting a leading edge point A of the first blade (10) and a trailing edge point B of the second blade (30) is a straight line AB; on a cross section passing through the root chord of the first blade (10) and cut along a radial direction, an extension line of a first side edge line cut from a first side surface of a front portion (21) of the first edge plate adjacent to the first top surface and away from the first blade (10) intersects with the straight line AB at a point D; and a length between an end point C of the curve cut from the first curved surface segment away from the first plane segment and the point D is not less than 1.5% of the root chord length of the first blade (10).

10. The compressor according to any one of claims 1 to 9, characterized in that: The invention also comprises a casing (50), a rotor shaft (60), a second blade (30) and a second edge plate (40), wherein the first blade (10) is connected to the casing (50), the second edge plate (40) is connected to the rotor shaft (60), and the root of the second blade (30) is connected to the second edge plate (40).

11. The compressor according to claim 10, characterized in that: The second edge plate (40) includes a second edge plate front portion (41) extending from the leading edge of the second blade (30) in a direction away from the trailing edge of the second blade (30), the second edge plate front portion (41) includes a second top surface close to the second blade (30) in a radial direction, and the second top surface includes a second curved surface segment away from the second blade (30) and a second flat surface segment close to the second blade (30).

12. An aircraft engine, characterized in that: It comprises a compressor as claimed in any one of claims 1 to 11.

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