Rectifying device and aero-engine with same

Abstract

The invention relates to the technical field of aero-engines, and discloses a rectifying device and an aero-engine with the same. The rectifying device is suitable for being arranged between an air inlet channel and an engine and comprises a casing, the air inlet end of the casing is connected with the air outlet end of the air inlet channel, and the air outlet end of the casing is connected with the air inlet end of the engine; and the blade assemblies are arranged on the surface of the inner wall of the casing and distributed in the circumferential direction of the surface of the inner wall of the casing. The blade assembly arranged between the air inlet channel and the engine is used for rectification, the pneumatic loss is small, the rectification effect is good, on the premise that the structure of the engine and the structure of the air inlet channel are not changed, the pneumatic stability of the engine after the S-shaped air inlet channel is installed can be improved, and the rectification device serves as an independent part and is convenient to use. The original structures of the air inlet channel and the engine are not damaged, the use safety is high, and meanwhile the installation mode is simple and convenient.

Description

Technical Field

[0001] The present invention relates to the technical field of aeroengines, and particularly relates to a rectifying device and an aeroengine having the same. Background Art

[0002] In modern high-performance stealth unmanned aerial vehicles, in order to improve the stealth performance, S-shaped and other special-shaped air intakes are widely adopted, making the problem of engine intake distortion more prominent.

[0003] In the prior art, by adding flow control inside the air intake, for example, by using vortex generators or blowing / suction inside the air intake to forcibly mix the vortices inside the air intake, and then destroying the counter-rotating vortex structure to achieve rectification. However, the method of forced mixing will bring large aerodynamic losses inside the air intake, reducing the performance and stability of the engine.

[0004] Alternatively, guide vanes are arranged inside the air intake to improve the outlet flow field of the air intake. However, for high-performance air intakes made of composite materials, there are potential safety hazards caused by stress concentration when opening holes in the air intake to install guide vanes, and it is also difficult to fix the guide vanes. Summary of the Invention

[0005] In view of this, the present invention provides a rectifying device and an aeroengine having the same to solve the problems of large aerodynamic losses inside the air intake and reduced engine performance caused by the existing rectifying measures of adding flow control inside the air intake, as well as the potential safety hazards and installation difficulties existing in the rectifying measures of arranging guide vanes inside the air intake.

[0006] In a first aspect, the present invention provides a rectifying device adapted to be arranged between an air intake and an engine. The rectifying device includes:

[0007] A casing, the intake end of the casing is connected to the outlet end of the air intake, and the outlet end of the casing is connected to the intake end of the engine;

[0008] A blade assembly arranged on the inner wall surface of the casing and circumferentially arranged along the inner wall surface of the casing.

[0009] Advantageous Effects: The present invention does not set, for example, vortex generators or blowing / suction inside the air intake to forcibly mix the vortices inside the air intake, but rectifies through the blade assembly arranged between the air intake and the engine. It has small aerodynamic losses and good rectifying effects. Without changing the structures of the engine and the air intake, the aerodynamic stability of the engine after installing an S-shaped air intake can be improved.

[0010] Compared with the existing method of installing flow guiding vanes in the intake duct to improve the outlet flow field of the intake duct, the rectifying device in the present invention is installed between the intake duct and the engine. As an independent part, the rectifying device does not damage the original structures of the intake duct and the engine, and has high safety in use while the installation method is simple and convenient.

[0011] Optionally, the casing is annular, the blade assembly includes a first blade group, a second blade group and a third blade group arranged at intervals, and the second blade group and the third blade group are symmetrically distributed with the first blade group as the mirror plane.

[0012] Beneficial effects: The casing is set to be annular, and different first blade groups, second blade groups and third blade groups are arranged on the inner wall surface of the annular casing, so that the rectifying device formed by the casing and the blade assembly is applicable to the counter-rotating vortex structure of the air flow at the outlet end of the S-shaped intake duct. The second blade group and the third blade group are symmetrically arranged with the first blade group as the mirror plane, which can balance the distribution of the air flow in the annular casing, reduce flow separation, thereby reducing aerodynamic losses and improving the energy transfer efficiency. At the same time, the second blade group and the third blade group are symmetrically arranged, so that loads such as aerodynamic forces are evenly distributed in the axial direction of the casing, reducing local stress concentration and prolonging the fatigue life of the rectifying device.

[0013] Optionally, a first region and a second region are provided on the inner wall of the casing, and the line connecting the center points of the first region and the second region is the central symmetry axis of the casing;

[0014] Wherein, the first blade group is provided in the first region and the second region respectively, the second blade group and the third blade group are provided outside the first region and the second region, and the second blade group and the third blade group are symmetrically distributed with the central symmetry axis as the mirror plane.

[0015] Beneficial effects: The first blade groups in the first region and the second region separate the second blade group and the third blade group. When the air flow generates an asymmetric disturbance due to distortion, the flow guiding effects of the mirror-symmetric second blade group and third blade group correct the flow field and prevent the disturbance from spreading to the first region and the second region, realizing effective rectification of the rectifying device.

[0016] Optionally, the first blade group includes at least two first blades, and the multiple first blades are symmetrically distributed with the central symmetry axis as the mirror plane, and the first blades are straight blades without twist angle.

[0017] Beneficial effects: The first blades are straight blades without twist angle, and the multiple first blades are symmetrically distributed with the central symmetry axis as the mirror plane, which can form a highly symmetric main flow channel in the casing, forcing the air flow to be evenly distributed along the central symmetry axis, thereby realizing the rectification effect.

[0018] Optionally, the second blade group includes a plurality of second blades arranged at intervals, the third blade group includes a plurality of third blades arranged at intervals, both the second blades and the third blades are twisted blades, and the second blades and the third blades have opposite helix directions.

[0019] Beneficial effects: The opposite helix directions of the second blades and the third blades can generate a reverse correction force on the circumferential secondary flow, forcing the air flow discharged from the intake duct to move axially, thereby achieving a rectifying effect.

[0020] Optionally, the second blade includes a first flow guiding area and a second flow guiding area, the first flow guiding area and the second flow guiding area are arranged in sequence along the upstream to downstream direction of the casing, and the first flow guiding area is curved relative to the second flow guiding area;

[0021] The third blade includes a third flow guiding area and a fourth flow guiding area, the third flow guiding area and the fourth flow guiding area are arranged in sequence along the upstream to downstream direction of the casing, and the third flow guiding area is curved relative to the fourth flow guiding area;

[0022] Wherein, the bending directions of the first flow guiding area and the third flow guiding area are opposite.

[0023] Beneficial effects: The first flow guiding area located upstream in the second blade is bent in a specific direction to apply an initial flow guiding force to the air flow, thereby suppressing flow separation. The second flow guiding area located downstream in the second blade continues to guide the flow with a smaller curvature, further smoothing the flow guiding turning, avoiding flow separation caused by a single large - amplitude bending, ensuring that the mainstream direction of the air flow is close to the axial direction, thereby achieving a rectifying effect. The third flow guiding area located upstream in the third blade is bent in a specific direction to apply an initial flow guiding force to the air flow, thereby suppressing flow separation. The fourth flow guiding area located downstream in the third blade continues to guide the flow with a smaller curvature, further smoothing the flow guiding turning, avoiding flow separation caused by a single large - amplitude bending, ensuring that the mainstream direction of the air flow is close to the axial direction, thereby achieving a rectifying effect. The opposite bending directions of the first flow guiding area and the third flow guiding area form a mirror flow guiding effect on both sides of the central symmetry axis, thereby forcing the air flow to move axially.

[0024] Optionally, the first area corresponds to the top of the exhaust end of the intake duct, and the second area corresponds to the bottom of the exhaust end of the intake duct.

[0025] Beneficial effects: The first area corresponds to the top of the exhaust end of the intake duct, and the second area corresponds to the top of the exhaust end of the intake duct, so that the first blade group corresponds to the top and the bottom of the exhaust end of the intake duct. The first blade adopts a non - twisted straight blade, which can guide the air flow discharged from the intake duct to the engine more smoothly and uniformly, reducing aerodynamic losses.

[0026] Optionally, a positioning portion is provided on the casing, and the positioning portion is adapted to limit the position of the casing relative to the air inlet duct.

[0027] Advantageous effects: By positioning the installation position of the casing through the positioning portion, when installing the casing, the operator can conveniently and accurately align the first area of the casing with the top of the exhaust end of the air inlet duct, and align the second area of the casing with the bottom of the exhaust end of the air inlet duct, avoiding inaccurate installation positions of the casing and the air inlet duct, thereby improving the rectifying effect of the rectifying device.

[0028] Optionally, the casing includes:

[0029] An installation ring, on the inner wall surface of which the blade assembly is provided;

[0030] A connecting portion, provided on the outer wall of the installation ring, and the connecting portion is respectively connected to the air inlet duct and the engine.

[0031] Advantageous effects: The installation ring is fixed to the air inlet duct and the engine through the connecting portion, and the blade assembly is arranged inside the installation ring. The connection between the blade assembly and the installation ring is fixed. On the basis of not damaging the internal structure of the air inlet duct, the rectification of the exhaust end of the air inlet duct is realized, and the connection method between the installation ring and the air inlet duct and the engine is simple and convenient, improving the work efficiency and reducing the use cost.

[0032] In a second aspect, the present invention provides an aeroengine, including the rectifying device according to any one of the above.

[0033] Advantageous effects: The aeroengine has the above rectifying device, and uses the rectifying device to rectify the swirling distorted air flow discharged from the exhaust end of the S-shaped air inlet duct, so that the aeroengine can work normally. Description of the Drawings

[0034] In order to more clearly illustrate the specific embodiments of the present invention or the technical solutions in the prior art, the following will briefly introduce the drawings required for use in the description of the specific embodiments or the prior art. Obviously, the following drawings are some embodiments of the present invention. For those of ordinary skill in the art, other drawings can be obtained based on these drawings without creative efforts.

[0035] Figure 1 Schematic diagram of the position relationship of the casing in the embodiment of the present invention;

[0036] Figure 2 Schematic diagram of the position relationship of the first blade group, the second blade group and the third blade group in the embodiment of the present invention;

[0037] Figure 3Schematic diagram of a specific setting mode of the blade assembly according to an embodiment of the present invention;

[0038] Figure 4 Schematic diagram of another specific setting mode of the blade assembly according to an embodiment of the present invention;

[0039] Figure 5 Schematic diagram of the rectification principle of the first blade;

[0040] Figure 6 Schematic diagram of the rectification principle of the second blade;

[0041] Figure 7 Schematic diagram of the rectification principle of the third blade;

[0042] Figure 8 Schematic diagram of the twist direction of the second blade and the third blade.

[0043] Explanation of reference numerals:

[0044] 1, intake duct; 2, engine; 201, engine inlet blade;

[0045] 3, casing; 301, mounting ring; 302, connecting part; 303, bolt hole; 304, inner ring

[0046] 4, blade assembly; 41, first blade group; 411, first blade; 42, second blade group; 421, second blade; 4211, first flow guiding area; 4212, second flow guiding area; 43, third blade group; 431, third blade; 4311, third flow guiding area; 4312, fourth flow guiding area;

[0047] 5, central axis of symmetry; 6, positioning part; 7, first area; 8, second area. Detailed implementation manners

[0048] To make the objectives, technical solutions and advantages of the embodiments of the present invention clearer, the technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings in the embodiments of the present invention. Obviously, the described embodiments are some, but not all, of the embodiments of the present invention. Based on the embodiments of the present invention, all other embodiments obtained by those skilled in the art without creative efforts shall fall within the protection scope of the present invention.

[0049] In order to improve the stealth performance, modern high-performance stealth unmanned aerial vehicles widely adopt special-shaped air inlets such as S-bends, making the problem of engine inlet distortion more prominent. Such inlet distortion is somewhat different from that of conventional combat aircraft. Generally, there are two types of distortion forms: pressure distortion and swirl coupling. Both types of distortion have a great impact on the aerodynamic stability of the engine, which may cause problems with the engine's aerodynamic stability and engine vibration caused by unstable flow excitation, seriously endangering the safe use of the engine.

[0050] At present, in response to the problem of the severe impact of swirl distortion in the stealth air inlet on the engine, the countermeasures are mainly divided into two categories. The first category is to increase flow control inside the air inlet. For example, the internal vortices of the air inlet are forcibly mixed through vortex generators or blowing / suction inside the air inlet, thereby destroying the counter-rotating vortex structure and achieving rectification. However, through the scheme of forced vortex mixing, the forced mixing will bring large aerodynamic losses inside the air inlet, reducing the engine performance and stability. It is difficult to control the improvement of swirl distortion through the internal vortex mixing of the air flow.

[0051] Or, guide vanes are arranged inside the air inlet to improve the outlet flow field by controlling the secondary flow inside the air inlet. However, adding guide vanes inside the air inlet, the rectification of the outlet flow field belongs to upstream indirect rectification, and it is difficult to ensure the quality of the outlet flow field. At the same time, this type of technical means can only be achieved by opening holes in the air inlet or fixing guide vanes inside the air inlet. For aircraft pursuing high thrust-to-weight ratio, their air inlets usually use composite materials. Due to the material characteristics of composite materials, opening holes in the air inlet may bring potential safety hazards caused by stress concentration. At the same time, it is also difficult to fix the guide vanes.

[0052] Regarding the above problems, please refer to Figures 1-8 First, an embodiment of the present invention provides a rectifying device adapted to be arranged between the air inlet 1 and the engine 2. The rectifying device includes: a casing 3, the inlet end of the casing 3 is connected to the outlet end of the air inlet 1, and the outlet end of the casing 3 is connected to the inlet end of the engine 2; a blade assembly 4, arranged on the inner wall surface of the casing 3 and circumferentially arranged along the inner wall surface of the casing 3.

[0053] In this embodiment, a rectifying device is arranged between the air inlet duct 1 and the engine 2. The rectifying device includes a casing 3 and a blade assembly 4. The casing 3 is used to connect the air inlet duct 1 and the engine 2, so that the discharged air flow of the air inlet duct 1 enters the engine inlet blade 201 of the engine 2 through the casing 3. When the air flow passes through the casing 3, it is rectified by the blade assembly 4 on the inner wall of the casing 3. After the distorted air flow generated by the S-shaped air inlet duct 1 passes through the blade assembly 4, the air flow vortices are broken up and rectified, improving the quality of the air flow field entering the engine 2, eliminating or weakening the unstable flow caused by the swirl distortion of the engine 2 and the air flow excitation energy generated by the unstable flow, and improving the mechanical stability and aerodynamic stability of the engine 2.

[0054] Preferably, the rectifying device is applicable to the S-shaped air inlet duct 1 of a stealth unmanned aerial vehicle.

[0055] In this embodiment, no vortex generator or in-duct blowing / suction is provided inside the air inlet duct 1 to forcibly mix the vortices inside the air inlet duct 1. Instead, the rectification is carried out by the blade assembly 4 arranged between the air inlet duct 1 and the engine 2, which has relatively small aerodynamic losses, good rectification effect, less influence on the performance of the engine 2 and improves the aerodynamic stability of the engine.

[0056] In this embodiment, no guide vane is provided inside the air inlet duct 1 to improve the outlet flow field of the air inlet duct 1. The rectifying device in the present invention is installed between the air inlet duct 1 and the engine 2. As an independent part, the rectifying device does not damage the original structures of the air inlet duct 1 and the engine 2, and has high use safety while the installation method is simple and convenient.

[0057] Optionally, referring to Figure 2 , the casing 3 is annular, and the blade assembly 4 includes a first blade group 41, a second blade group 42 and a third blade group 43 which are arranged at intervals. The second blade group 42 and the third blade group 43 are symmetrically distributed with the first blade group 41 as the mirror plane.

[0058] In this embodiment, the casing 3 is arranged to be annular, and the central axis of the air outlet end of the air inlet duct 1, the central axis of the air inlet end of the engine 2 and the central axis of the casing 3 preferably coincide. After the air flow passes through the air inlet duct 1, swirl distortion occurs. When the swirling distorted air flow passes through the first blade group 41, the second blade group 42 and the third blade group 43, the first blade group 41, the second blade group 42 and the third blade group 43 correct the air flow deflection angle caused by the swirl at the air outlet end of the air inlet duct 1, ensuring that the air flow angle at the air inlet end of the engine 2 enters axially, reducing the excessive positive / negative pre-swirl angle at the fan or compressor inlet stage of the engine 2, enabling the engine inlet blade 201 to work in a better working state, and avoiding vibration problems and aerodynamic stability problems caused by swirl distortion.

[0059] In this embodiment, the casing 3 is set to be annular, and different first blade groups 41, second blade groups 42, and third blade groups 43 are arranged on the inner wall surface of the annular casing 3, so that the rectifying device formed by the casing 3 and the blade assembly 4 is applicable to the counter-rotating vortex structure of the air flow at the outlet end of the S-shaped inlet duct 1. The second blade group 42 and the third blade group 43 are symmetrically arranged with the first blade group 41 as the mirror plane, which can balance the distribution of the air flow in the annular casing 3, reduce flow separation, thereby reducing aerodynamic losses and improving the energy transfer efficiency. At the same time, the second blade group 42 and the third blade group 43 are symmetrically arranged, so that loads such as aerodynamic forces are evenly distributed axially on the casing 3, reducing local stress concentration and prolonging the fatigue life of the rectifying device.

[0060] Optionally, referring to Figure 2 , the inner wall of the casing 3 is provided with a first region 7 and a second region 8, and the line connecting the center points of the first region 7 and the second region 8 is the central symmetry axis 5 of the casing 3; wherein, the first blade group 41 is respectively arranged in the first region 7 and the second region 8, and the second blade group 42 and the third blade group 43 are arranged outside the first region 7 and the second region 8, and the second blade group 42 and the third blade group 43 are symmetrically distributed with the central symmetry axis 5 as the mirror plane.

[0061] In this embodiment, the inside of the casing 3 is divided into four regions, and gaps are respectively arranged between the two sides of the first region 7 and the second region 8, and the two gaps are respectively used to accommodate the second blade group 42 and the third blade group 43. In this way, the second blade group 42 and the third blade group 43 are respectively arranged on both sides of the first blade group 41, and the first blade group 41 in the first region 7 and the second region 8 separates the second blade group 42 from the third blade group 43. When the air flow generates an asymmetric disturbance due to distortion, the flow guiding effects of the mirror-symmetric second blade group 42 and third blade group 43 correct the flow field and prevent the disturbance from spreading to the first region 7 and the second region 8, realizing effective rectification of the rectifying device.

[0062] Optionally, referring to Figure 2 、 Figure 5 , the first blade group 41 includes at least two first blades 411, and the multiple first blades 411 are symmetrically distributed with the central symmetry axis 5 as the mirror plane, and the first blade 411 is a straight blade without twist angle.

[0063] In this embodiment, at least two first blades 411 are provided, and the number thereof is an even number. In this way, the multiple first blades 411 are arranged along the annular inner wall of the casing 3, which can ensure the symmetric arrangement of the multiple first blades 411. The first blade 411 is a straight blade without twist angle, and the multiple first blades 411 are symmetrically distributed with the central symmetry axis 5 as the mirror plane, which can form a highly symmetric main flow path in the casing 3 and force the air flow to be evenly distributed along the central symmetry axis 5, thereby realizing the rectification effect.

[0064] Optionally, referring toFigure 2 , Figure 8 , the second vane group 42 includes a plurality of second vanes 421 arranged at intervals, the third vane group 43 includes a plurality of third vanes 431 arranged at intervals, both the second vanes 421 and the third vanes 431 are twisted vanes, and the rotation directions of the second vanes 421 and the third vanes 431 are opposite.

[0065] In this embodiment, the second vanes 421 and the third vanes 431 are arranged along the annular inner wall of the casing 3. At the same time, the opposite rotation directions of the second vanes 421 and the third vanes 431 can generate a reverse correction force on the circumferential secondary flow, forcing the air flow discharged from the intake passage 1 to move axially, thereby achieving a rectifying effect.

[0066] In a specific embodiment, referring to Figure 2 , the rotation directions of the second vanes 421 and the third vanes 531 are opposite. Taking the second vane group 42 located on the left side of the central symmetry axis 5 and the third vane group 43 located on the right side of the central symmetry axis 5 as an example, the second vanes 421 among them are twisted vanes with a reverse deflection angle, and the third vanes 431 are twisted vanes with a forward deflection angle.

[0067] In a specific embodiment, referring to Figure 2 , the number of the first vanes 411 arranged in the first region 7 is two, and the two first vanes 411 are symmetrically distributed with the central symmetry axis 5 as the mirror plane. The number of the first vanes 411 arranged in the second region 8 is four, and the four first vanes 411 are symmetrically distributed in pairs with the central symmetry axis 5 as the mirror plane. The number of the second vanes 421 and the number of the third vanes 431 are both 12, and the multiple second vanes 421 and the multiple third vanes 431 are symmetrically distributed one by one with the central symmetry axis 5 as the mirror plane. Of course, the specific numbers of the first vanes 411, the second vanes 421, and the third vanes 431 can also be adaptively adjusted according to actual needs.

[0068] Optionally, referring to Figure 6 , Figure 7 , the second vane 421 includes a first flow guiding area 4211 and a second flow guiding area 4212, the first flow guiding area 4211 and the second flow guiding area 4212 are arranged in sequence along the upstream to downstream direction of the casing 3, and the first flow guiding area 4211 is bent relative to the second flow guiding area 4212; the third vane 431 includes a third flow guiding area 4311 and a fourth flow guiding area 4312, the third flow guiding area 4311 and the fourth flow guiding area 4312 are arranged in sequence along the upstream to downstream direction of the casing 3, and the third flow guiding area 4311 is bent relative to the fourth flow guiding area 4312; wherein, the bending directions of the first flow guiding area 4211 and the third flow guiding area 4311 are opposite.

[0069] In this embodiment, the first flow guiding region 4211 located upstream in the second blade 421 is bent in a specific direction to apply an initial flow guiding force to the air flow, thereby suppressing flow separation. The second flow guiding region 4212 located downstream in the second blade 421 continues to guide the flow with a smaller curvature, further smoothing the flow guiding turn, avoiding flow separation caused by a single large - amplitude bend, ensuring that the mainstream direction of the air flow is close to the axial direction, and thus achieving a flow rectification effect. The third flow guiding region 4311 located upstream in the third blade 431 is bent in a specific direction to apply an initial flow guiding force to the air flow, thereby suppressing flow separation. The fourth flow guiding region 4312 located downstream in the third blade 431 continues to guide the flow with a smaller curvature, further smoothing the flow guiding turn, avoiding flow separation caused by a single large - amplitude bend, ensuring that the mainstream direction of the air flow is close to the axial direction, and thus achieving a flow rectification effect. The opposite bending directions of the first flow guiding region 4211 and the third flow guiding region 4311 form a mirror flow guiding effect on both sides of the central symmetry axis 5, thereby forcing the air flow to move along the axial direction.

[0070] Optionally, referring to Figure 3 , the first region 7 and the top of the exhaust end of the intake passage 1 are correspondingly arranged, and the second region 8 and the bottom of the exhaust end of the intake passage 1 are correspondingly arranged.

[0071] In this embodiment, the first region 7 corresponds to the top of the exhaust end of the intake passage 1, and the second region 8 corresponds to the top of the exhaust end of the intake passage 1, so that the first blade group 41 corresponds to the top and the bottom of the exhaust end of the intake passage 1. The first blade 411 adopts a non - twisted straight blade, which can guide the exhaust air flow of the intake passage 1 to the engine 2 more smoothly and evenly, reducing the aerodynamic loss.

[0072] Optionally, referring to Figure 3 , a positioning portion 6 is provided on the casing 3, and the positioning portion 6 is adapted to limit the position of the casing 3 relative to the intake passage 1.

[0073] In this embodiment, the installation position of the casing 3 is positioned by the positioning portion 6. When installing the casing 3, the operator can conveniently and accurately align the first region 7 of the casing 3 with the top of the exhaust end of the intake passage 1 and align the second region 8 of the casing 3 with the bottom of the exhaust end of the intake passage 1, avoiding inaccurate installation positions of the casing 3 and the intake passage 1, thereby improving the flow rectification effect of the flow rectifying device.

[0074] Optionally, referring to Figure 3 , the casing 3 includes: an installation ring 301, on the inner wall surface of which a blade assembly 4 is provided; a connecting portion 302, provided on the outer wall of the installation ring 301, and the connecting portion 302 is respectively connected to the intake passage 1 and the engine 2.

[0075] In this embodiment, the connecting portion 302 preferably adopts two annular casing mounting edges. The casing mounting edges are sleeved and fixed on the outer peripheral wall of the mounting ring 301, and a plurality of bolt holes 303 are arranged at intervals on the casing mounting edges. Bolts passing through the bolt holes 303 on the casing mounting edges are used to fixedly connect the two casing mounting edges to the air outlet end of the air inlet passage 1 and the air inlet end of the engine 2 respectively, so as to realize the connection and fixation of the casing 3 with the air inlet passage 1 and the engine 2. Of course, in addition to the above setting method, the connecting portion 302 can also be a plurality of connecting plates. Bolt holes 303 are arranged on the connecting plates. The plurality of connecting plates are divided into two groups, and each group of connecting plates is arranged at intervals circumferentially along the outer peripheral wall of the mounting ring 301. One group of connecting plates is used to connect with the air inlet passage 1, and the other group of connecting plates is used to connect with the engine 2.

[0076] In this way, the mounting ring 301 is fixed to the air inlet passage 1 and the engine 2 through the connecting portion 302. The blade assembly 4 is arranged in the mounting ring 301. The connection and fixation of the blade assembly 4 with the mounting ring 301 realize the rectification of the exhaust end of the air inlet passage 1 without damaging the internal structure of the air inlet passage 1. Moreover, the connection method of the mounting ring 301 with the air inlet passage 1 and the engine 2 is simple and convenient, improving the working efficiency and reducing the use cost.

[0077] In a specific embodiment, referring to Figure 3 , the positioning portion 6 is an anti-misalignment bolt hole arranged on the casing mounting edge. This anti-misalignment bolt hole is different in structure from other bolt holes 303. On the air outlet end of the air inlet passage 1 and / or the air inlet end of the engine 2, anti-misalignment bolt holes matching the anti-misalignment bolt holes on the casing mounting edge are provided. When installing the casing 3, the operator can align the anti-misalignment bolt holes with the top and bottom of the air inlet passage 1 and / or the engine, thereby preventing the casing 3 from being misaligned relative to the air inlet passage 1.

[0078] Alternatively, the positioning portion 6 is an indication line coated on the casing mounting edge. When installing the casing 3, the operator can determine the installation position of the casing 3 through the mark of the indication line, and can also prevent the casing 3 from being misaligned relative to the air inlet passage 1.

[0079] In an alternative embodiment, referring to Figure 3, the inner cavity of the mounting ring 301 serves as an air flow channel. One ends of the first blade 411, the second blade 421, and the third blade 431 are fixed to the inner wall of the mounting ring 301, and the other ends of the first blade 411, the second blade 421, and the third blade 431 are suspended. In this way, the other ends of the first blade 411, the second blade 421, and the third blade 431 are suspended, which can avoid abrupt obstruction to the air flow, reduce flow separation and turbulence generation, and improve the rectification efficiency. At the same time, the first blade 411, the second blade 421, and the third blade 431 only need to be fixed on one side, simplifying the installation process of the first blade 411, the second blade 421, and the third blade 431 and shortening the assembly cycle.

[0080] In another alternative embodiment, referring to Figure 4 , the inner cavity of the mounting ring 301 serves as an air flow channel. An inner ring 304 is further provided inside the mounting ring 301. One ends of the first blade 411, the second blade 421, and the third blade 431 are fixed to the inner wall of the mounting ring 301, and the other ends of the first blade 411, the second blade 421, and the third blade 431 are fixed to the outer wall of the inner ring 304. In this way, the inner ring 304 is used to connect the first blade 411, the second blade 421, and the third blade 431 to form an integral structure, enhancing the installation firmness of the first blade 411, the second blade 421, and the third blade 431.

[0081] In a second aspect, the present invention provides an aeroengine 2, including the rectifying device of any one of the above. The aeroengine 2 has the above rectifying device, and the rectifying device is used to rectify the exhaust gas flow at the exhaust end of the intake duct 1, so that the aeroengine 2 can work normally.

[0082] Although the embodiments of the present invention have been described in conjunction with the accompanying drawings, those skilled in the art can make various modifications and variations without departing from the spirit and scope of the present invention, and such modifications and variations all fall within the scope defined by the appended claims.

Claims

1. A rectifying device, characterized in that, Suitable for being arranged between an air inlet duct (1) and an engine (2), the rectifying device includes: A casing (3), the air inlet end of the casing (3) is connected to the air outlet end of the air inlet duct (1), and the air outlet end of the casing (3) is connected to the air inlet end of the engine (2); A blade assembly (4), arranged on the inner wall surface of the casing (3) and circumferentially arranged along the inner wall surface of the casing (3).

2. The rectifying device according to claim 1, characterized in that, The casing (3) is annular, the blade assembly (4) includes a first blade group (41), a second blade group (42) and a third blade group (43) arranged at intervals, and the second blade group (42) and the third blade group (43) are symmetrically distributed with the first blade group (41) as the mirror plane.

3. The rectifying device according to claim 2, characterized in that, The inner wall of the casing (3) is provided with a first region (7) and a second region (8), and the connection line between the center points of the first region (7) and the second region (8) is the central symmetry axis (5) of the casing (3); Wherein, the first blade group (41) is respectively arranged in the first region (7) and the second region (8), the second blade group (42) and the third blade group (43) are arranged outside the first region (7) and the second region (8), and the second blade group (42) and the third blade group (43) are symmetrically distributed with the central symmetry axis (5) as the mirror plane.

4. The rectifying device according to claim 3, characterized in that, The first blade group (41) includes at least two first blades (411), and the plurality of first blades (411) are symmetrically distributed with the central symmetry axis (5) as the mirror plane, and the first blade (411) is a straight blade without twist angle.

5. The rectifying device according to claim 3, characterized in that, The second blade group (42) includes a plurality of second blades (421) arranged at intervals, the third blade group (43) includes a plurality of third blades (431) arranged at intervals, the second blades (421) and the third blades (431) are both twisted blades, and the rotation directions of the second blades (421) and the third blades (431) are opposite.

6. The rectifying device according to claim 5, characterized in that, The second blade (421) includes a first flow guiding area (4211) and a second flow guiding area (4212), the first flow guiding area (4211) and the second flow guiding area (4212) are arranged in sequence along the upstream to downstream direction of the casing (3), and the first flow guiding area (4211) is bent relative to the second flow guiding area (4212); The third blade (431) includes a third flow guiding area (4311) and a fourth flow guiding area (4312), the third flow guiding area (4311) and the fourth flow guiding area (4312) are arranged in sequence along the upstream to downstream direction of the casing (3), and the third flow guiding area (4311) is bent relative to the fourth flow guiding area (4312); Wherein, the bending directions of the first flow guiding area (4211) and the third flow guiding area (4311) are opposite.

7. The rectifying device according to any one of claims 3 to 6, characterized in that, The first region (7) corresponds to the top of the exhaust end of the air inlet duct (1), and the second region (8) corresponds to the bottom of the exhaust end of the air inlet duct (1).

8. The rectifying device according to claim 7, characterized in that, A positioning portion (6) is provided on the casing (3), and the positioning portion (6) is adapted to limit the position of the casing (3) relative to the intake passage (1).

9. The rectifying device according to any one of claims 3-6, characterized in that, The casing (3) includes: a mounting ring (301) having the blade assembly (4) provided on an inner wall surface thereof; a connecting portion (302) provided on an outer wall of the mounting ring (301), and the connecting portion (302) is respectively connected to the intake passage (1) and the engine (2).

10. An aeroengine, characterized in that, It includes the rectifying device according to any one of claims 1-9.

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