Low aspect ratio industrial axial compressor

Abstract

The utility model discloses a kind of small chord ratio industrial axial flow compressor, it is related to axial flow compressor technical field, solve the low single-stage pressure ratio of existing industrial compressor, technical problems such as inefficiency, insufficient reliability, comprising welded casing, static vane inner casing, static vane linkage adjusting mechanism, rotor assembly, import convergent casing, outlet diffuser casing and the structure such as;According to actual working condition requirement compressor series 6~12, blade uses the controllable diffusion blade profile of small chord ratio, uses the combination flow channel of equal outer diameter plus equal inner diameter, static vane linkage adjusting mechanism can realize the angle proportion adjustment of adjustable guide vane and 1~3 stage static vane.

Description

Technical Field

[0001] This utility model relates to the field of axial flow compressor technology, and more specifically to the field of industrial axial flow compressor technology with a small aspect ratio. Background Technology

[0002] An axial flow compressor is a turbine-type mechanical device that provides compressed gas. It is an important power source for large-scale air supply and gas compression in industries such as metallurgy, petroleum, chemical, fermentation, environmental protection, and air separation. Existing patents disclose the following technologies: Patent publication number CN102562665A, entitled "Axial Flow Compressor," discloses the following: When operating an IGV (Inlet Gas Vault) with partial load, such as through a gas turbine, a decrease in aerodynamic performance and / or reliability may occur due to increased load on the blades on the downstream side of the compressor. The purpose of this invention is to suppress this decrease in aerodynamic performance and / or reliability of the axial flow compressor. The axial flow compressor of this invention comprises: a rotor assembly; multiple rotor blade rows disposed on the rotor assembly; a cover located outside the rotor blade rows; multiple stationary blade rows disposed on the cover; and an outlet guide vane disposed downstream of the final stage stationary blade row in the stationary blade rows. The characteristic of this axial flow compressor is that the airflow inlet angle of the final stage stationary blade row is below the boundary line of the operating area.

[0003] The patent with publication number CN110173441A and patent title "Axial-Centrifugal Compressor" discloses the following: A turbine engine includes: a compressor section including a compressor, the compressor including an axial compressor stage, a variable outlet guide vane and a centrifugal compressor stage, the variable outlet guide vane being positioned between the axial compressor stage and the centrifugal compressor stage; a venting assembly including a venting airflow pipe communicating with the compressor airflow and a venting valve operable together with the venting airflow pipe, the venting valve including a venting valve actuator; and a connecting rod assembly connecting the venting valve actuator and the variable outlet guide vane, such that the variable outlet guide vane can move together with the venting valve.

[0004] The axial compressors mentioned above and in the prior art use an equal inner diameter design for their airflow channels and non-customized blade profiles based on the NACA65 airfoil. The blades have a large aspect ratio, resulting in problems such as low compression efficiency, low single-stage pressure ratio, and low strength margin of core components such as blades. Utility Model Content

[0005] The purpose of this invention is to solve the technical problems of low single-stage pressure ratio, low efficiency and insufficient reliability of existing industrial compressors. This invention provides a small aspect ratio industrial axial flow compressor.

[0006] To achieve the above objectives, this utility model specifically adopts the following technical solution: One aspect of this utility model provides a small aspect ratio industrial axial flow compressor, including a base, a housing mounted on the base, an inlet converging casing disposed at the front end of the housing, an outlet diffuser casing disposed at the rear end of the housing, a stator inner casing rotatably mounted in the housing along the axial direction, a rotor assembly rotatably mounted in the stator inner casing along the axial direction, a bearing for supporting the rotor assembly mounted in the housing, and a stator linkage adjustment mechanism. The cavity formed by the outer hub surface of the rotor assembly and the inner surface of the stator inner casing is the compressor flow channel. The rotor assembly is mounted in the stator inner casing through a support bearing assembly, which includes an intake support bearing and an exhaust support bearing located on both sides. The housing includes an intake housing, an intermediate housing, and an exhaust volute, which are welded together in sequence. The housing introduces the fluid to be compressed into the compressor axially, provides the installation positions for the various components of the compressor, and discharges the compressed fluid from the compressor radially. The rotor assembly includes a main shaft and multi-stage rotor blades mounted circumferentially in the middle part of the main shaft. The number of stages of the rotor blades can be any one of 6 to 12 stages. The diameter of the rotor assembly hub surface of the rotor blade part gradually increases from the installation position of the 1st stage rotor blade to the installation position of the 5th stage rotor blade. The rotor assembly hub surface after the installation position of the 5th stage rotor blade is a cylindrical surface. Specifically, the flow channel formed with the stator inner casing has an approximately equal outer diameter at the front and an equal inner diameter at the rear. The linear velocity of the first few stages of rotor blades is relatively high, which can achieve a higher power output. The equal inner diameter of the later stages results in a relatively larger rotor blade height, and the blade tip clearance has a smaller impact on efficiency, which is conducive to improving the overall efficiency of the unit.

[0007] The inner casing of the stationary vanes is the outer flow channel that constitutes the compressor. Adjustable guide vanes and multi-stage stationary vanes are provided on the inner wall of the inner casing of the stationary vanes. The number of stages of the stationary vanes is 6 to 12. The stationary blade linkage adjustment structure enables the linkage adjustment of the adjustable guide vanes and the 1st to 3rd stage stationary blades.

[0008] Bearings are classified into radial bearings and thrust bearings.

[0009] In one embodiment, the front external flow channel is a rotating surface composed of spline curves. The tangent of the generatrix of the rotating surface of the stationary blades from stage 0 to stage 5 makes an angle of 0.93 to 0.97° with the axis of the main shaft. The tangent of the generatrix of the rotating surface of the stationary blades from stage 5 onwards makes an angle of 1.5 to 2° with the axis of the main shaft. The range of the angle between the tangent of this generatrix and the compressor axis is as follows:

[0010] In one embodiment, the inner flow channel is a surface of revolution formed by spline curves from the first-stage rotor blade to the fifth-stage rotor blade, and the surface of revolution of the sixth-stage rotor blade and subsequent rotor blades is a cylindrical surface.

[0011] In one embodiment, the blade profile of each rotor stage is a controllable diffusion blade profile with a small aspect ratio, and the blade profile of each rotor stage is swept forward at a blade span percentage of more than 30%; the moving blade adopts a bent-twisted structure, with the root section as the reference, the maximum thickness position is at 40%-50% of the blade chord length, the aspect ratio range is 1.8-2.5, and the blade aspect ratio is in the range of 0.6-1.5.

[0012] In one embodiment, the stationary blade has a custom blade shape with a swept-back composite shape for its blade spread. The adjustable guide blade and the first to third stage stationary blades are all adjustable-angle blades, while the remaining stage stationary blades are fixed-angle blades. The stationary blades adopt an arc-shaped structure with the maximum thickness located at 30%-40% of the blade chord length. Both the leading and trailing edges adopt an elliptical structure with an aspect ratio ranging from 1.8 to 2.5 and an aspect ratio ranging from 0.6 to 1.6.

[0013] In one embodiment, the rotor blades, specifically the first to fourth stage rotor blades, employ axial dovetail tenons, with the angle between the plane of symmetry of the tenon and the axis of the rotor assembly being 20° to 28° (this angle is chosen to avoid excessive stress concentration at the blade tenon due to an excessively large angle, which could cause blade damage); the fifth to twelfth stage rotor blades employ low-stress T-shaped tenons.

[0014] In one embodiment, the stationary blade linkage adjustment mechanism includes linkage rings of various stages, blade cranks, proportional linkage rods, and pull rods, with each stage of linkage rotating around the compressor axis.

[0015] In one embodiment, the rotor blades are made of precipitation-hardened martensitic stainless steel 05Cr17Ni4Cu4Nb, and an inorganic phosphate anti-corrosion coating is sprayed onto the first to third stage rotor blades. The thickness of the inorganic phosphate anti-corrosion coating is ≥35~80μm.

[0016] In one embodiment, the adjustable guide vanes and stationary vanes are coated with an inorganic phosphate anti-corrosion coating, the thickness of which is ≥35~80μm.

[0017] The beneficial effects of this utility model are as follows: 1. Depending on the actual working conditions, the rotor assembly is arranged with a total of 6 to 12 levels of rotor blades. The inner casing of the stationary blades is arranged with adjustable guide blades and 6 to 12 levels of stationary blades corresponding to the rotor blades. The stationary blade linkage adjustment mechanism can realize the angle ratio adjustment of the adjustable guide blades and 1 to 3 levels of stationary blades.

[0018] 2. With this flow channel design, the front section can achieve a relatively higher tip linear velocity of the rotor blades under the same flow and compression capacity, which can maximize the working capacity of a single-stage blade; the rear section with a constant inner diameter can ensure the spanwise length of the rotor blades, thereby reducing the efficiency loss caused by the tip clearance.

[0019] 3. Both the moving and stationary blades employ a controlled diffuser airfoil with optimally distributed thickness and curvature. The airfoil features bending, twisting, and sweeping motions, and a non-repeating stage design, thus eliminating boundary layer separation and improving blade efficiency. The blades have a higher aspect ratio, allowing for a longer axial work distance per stage and greater pressure lift. The wide-chord controlled diffuser airfoil has a larger section modulus than existing blades, significantly reducing aerodynamic loads on the blade body.

[0020] 4. Compared to existing blade materials such as 20Cr13 or 13Cr11Ni2W2MoV, precipitation-hardening martensitic stainless steel 05Cr17Ni4Cu4Nb exhibits superior overall mechanical properties. Furthermore, compared to existing blade materials, 05Cr17Ni4Cu4Nb demonstrates better corrosion resistance. Applying an anti-corrosion coating to the blade surface effectively reduces corrosion during service.

[0021] 5. The linkage adjustment mechanism uses rolling, not axial movement. 1) Existing technology uses axial movement, requiring a large axial length for axial guidance in the linkage adjustment cylinder. This patent has fewer adjustable levels and a shorter adjustment structure. Using the original structure would result in insufficient axial guidance length, causing the adjustment mechanism to jam. 2) In the original structure, each level of stator vane relies on cranks of different lengths to achieve different levels of proportional adjustment. The crank length varies for each level, resulting in more types of parts. The rolling scheme can use the same crank length in different levels, relying on the change in crank length driving each level of adjustment ring to achieve different levels of proportional adjustment. This results in a simpler structure, lighter weight, greater flexibility, and simpler production organization. Attached Figure Description

[0022] To more clearly illustrate the technical solutions of the embodiments of this utility model, the accompanying drawings used in the embodiments will be briefly introduced below. It should be understood that the following drawings only show some embodiments of this utility model and should not be regarded as a limitation on the scope. For those skilled in the art, other related drawings can be obtained from these drawings without creative effort.

[0023] Figure 1 This is a schematic diagram showing the overall structure of an axial compressor; Figure 2 This is a schematic diagram of the flow channel structure of an axial compressor; Figure 3 This is a schematic diagram of the axial dovetail rotor blades of an axial compressor. Figure 4 This is a schematic diagram of the circumferential T-shaped tenon rotor blades of an axial compressor; Figure 5 This is a schematic diagram of the adjustable-angle stationary blades of an axial compressor. Figure 6 This is a schematic diagram of the fixed-angle stationary blades of an axial compressor; Reference numerals: 1. Base; 2. Housing; 3. Stator vane inner casing; 5. Rotor assembly; 6. Support bearing assembly; 2.1 Intake housing; 2.2 Exhaust housing; 3.1. Stationary blades; 5.1 Rotor blades; 6.1 Intake support bearing; 6.2 Exhaust support bearing. Detailed Implementation

[0024] To make the technical problems, technical solutions, and technical effects of this utility model clearer, the technical solutions of this utility model will be clearly and completely described below with reference to the accompanying drawings of the embodiments of this utility model. Obviously, the described embodiments are only some embodiments of this utility model, and not all embodiments. The components of the embodiments of this utility model described and shown in the accompanying drawings can generally be arranged and designed in various different configurations.

[0025] Therefore, the following detailed description of the embodiments of the present invention provided in the accompanying drawings is not intended to limit the scope of the claimed invention, but merely to illustrate selected embodiments of the invention. All other embodiments obtained by those skilled in the art based on the embodiments of the present invention without inventive effort are within the scope of protection of the present invention.

[0026] It should be noted that similar reference numerals and letters in the following figures indicate similar items; therefore, once an item is defined in one figure, it does not need to be further defined and explained in subsequent figures. Furthermore, the terms "first," "second," etc., are used only to distinguish descriptions and should not be construed as indicating or implying relative importance.

[0027] In the description of the embodiments of this utility model, it should be noted that the terms "inner", "outer", "upper", etc., indicate the orientation or positional relationship based on the orientation or positional relationship shown in the drawings, or the orientation or positional relationship in which the utility model product is usually placed when in use. They are only for the convenience of describing this utility model and simplifying the description, and do 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. Therefore, they should not be construed as limitations on this utility model.

[0028] Example 1 like Figures 1 to 6 As shown, this embodiment provides a small aspect ratio industrial axial flow compressor, including a base 1, a housing 2 mounted on the base 1, an inlet converging casing located at the front end of the housing 2, an outlet diffuser casing located at the rear end of the housing 2, a stator inner casing 3 rotatably mounted in the housing 2, a rotor assembly 5 rotatably mounted in the stator inner casing 3, a bearing mounted in the housing 2 to support the rotor assembly 5, and a stator linkage adjustment mechanism. The cavity formed by the outer hub surface of the rotor assembly 5 and the inner surface of the stator inner casing 3 is the compressor flow channel. The rotor assembly 5 is mounted in the stator inner casing 3 through a support bearing assembly 6, which includes an intake support bearing 6.1 and an exhaust support bearing 6.2 located on both sides. An intake housing 2.1 and an exhaust housing 2.2 are welded to both sides of the housing 2, respectively.

[0029] The housing 2 includes an intake housing 2.1, an intermediate housing, and an exhaust volute, which are welded in sequence. The housing 2 introduces the fluid to be compressed into the compressor axially, provides the installation position for each component of the compressor, and discharges the compressed fluid from the compressor radially. The rotor assembly 5 includes a main shaft and multi-stage rotor blades 5.1 circumferentially mounted in the middle part of the main shaft. The number of stages of the rotor blades 5.1 is any one of 6 to 12 stages. The diameter of the hub surface of the rotor assembly 5 in the rotor blades 5.1 section gradually increases from the installation position of the first stage rotor blade 5.1 to the installation position of the fifth stage rotor blade 5.1. The hub surface of the rotor assembly 5 after the installation position of the fifth stage rotor blade 5.1 is a cylindrical surface. The inner casing 3 is the outer flow channel of the compressor. Adjustable guide vanes and multi-stage stationary vanes 3.1 are provided on the inner wall of the inner casing 3. The number of stages of the stationary vanes 3.1 is 6 to 12. The stationary blade linkage adjustment structure enables the linkage adjustment of the adjustable guide vanes and the 1st to 3rd stage stationary blades 3.1.

[0030] Bearings are classified into radial bearings and thrust bearings.

[0031] In this embodiment, the stationary blade 3.1 adopts an arc-shaped structure, with the maximum thickness located at 30%-40% of the blade chord length. Both the leading and trailing edges adopt an elliptical structure, with an aspect ratio ranging from 1.8 to 2.5. The aspect ratio of the stationary blade 3.1 is in the range of 0.6 to 1.6.

[0032] The rotor blade 5.1 adopts a bending and twisting structure. Based on the root section, the bending and twisting range is within a certain range. The maximum thickness is located at 40%-50% of the blade chord length. The aspect ratio ranges from 1.8 to 2.5, and the aspect ratio of the rotor blade 5.1 is in the range of 0.6-1.5.

[0033] Example 2 This embodiment is a further optimization based on Embodiment 1, as detailed below: The front external flow channel is a rotating surface composed of spline curves. The angle between the tangent of the generatrix of the rotating surface of the stationary blades 3.1 from stage 0 to 5 and the axis of the main shaft is 0.93 to 0.97°. The angle between the tangent of the generatrix of the rotating surface of the stationary blades 3.1 from stage 5 onwards and the axis of the main shaft is 1.5 to 2°.

[0034] Example 3 This embodiment is a further optimization based on Embodiment 1, as detailed below: The internal flow channel, from stage 1 to 5, has a surface of revolution formed by spline curves at rotor blade 5.1. The surface of revolution for stage 6 and subsequent stage rotor blades 5.1 is cylindrical. The angle between the tangent of the generatrix of the rotor blades 5.1 at the intersection of the accumulation line of stages 1 to 12 and the generatrix of the internal flow channel's surface of revolution and the compressor axis is shown in the table below:

[0035] With this flow channel design, the tip linear velocity of rotor blade 5.1 can be relatively higher in the front section under the same flow and compression capacity, which can maximize the working capacity of a single-stage blade; the same inner diameter in the rear section can ensure the spanwise length of rotor blade 5.1, so as to reduce the efficiency loss caused by tip clearance.

[0036] After the compressor rotor blades 5.1, an expansion section is set. By increasing the axial dimension, the exhaust airflow generates a thrust pointing towards the exhaust side, balancing part of the aerodynamic axial force and reducing the load on the thrust bearing.

[0037] Example 4 This embodiment is a further optimization based on embodiment 3, as detailed below: The blade profile of rotor blade 5.1 at each stage is a controllable diffusion blade profile with a small aspect ratio, and the blade profile of rotor blade 5.1 at each stage has a forward sweep of more than 30% of the blade span.

[0038] The blade shape of stationary blade 3.1 is a custom blade shape, and the blade spread forming line of this custom blade shape is a swept composite shape; the adjustable guide blade and the first to third stage stationary blades 3.1 are all blades, while the other stage stationary blades 3.1 are fixed angle stationary blades 3.1.

[0039] Specifically, both the moving blade and the stationary blade 3.1 are controlled diffusion airfoils, no longer using the standard airfoil based on the NACA65 airfoil. This airfoil can better match the flow characteristics of the airflow and avoid uncontrolled separation and diffusion on the blade, especially near the tail.

[0040] Example 5 This embodiment is a further optimization based on embodiment 4, as detailed below: The rotor blades of stages 1 to 4 use axial dovetail tenons, with the angle between the plane of symmetry of the tenon and the axis of rotor assembly 5 being 20° to 28°; the rotor blades of stages 5 to 12 use low-stress T-shaped tenons.

[0041] Specifically, rotor blades 5.1 of stages 1-4 employ axial dovetail tenons, with the angle between the plane of symmetry of the tenon and the axis of rotor assembly 5 being 20°-28°. Rotor blades 5.1 of stages 5-12 employ low-stress T-shaped tenons. The use of axial dovetail tenons (as in patents CN219139459U and CN202223410447.5) for the earlier stages of rotor blades (such as those in patents CN219139459U and CN202223410447.5) increases the contact area between the blade tenon and the mortise of rotor assembly 5, and increases the load-bearing area of ​​the tenon, thereby reducing the stress level of the blade and improving its service life. The tenon profile is symmetrical, facilitating machining. The later stage blades are smaller and employ circumferential T-shaped tenons. The rotor blades 5.1, stages 1 to 4, use axial dovetail tenons. The angle between the plane of symmetry of the tenon and the axis of rotor assembly 5 is 20° to 28°. This can avoid the problem of stress concentration at the sharp corner of the blade tenon due to the excessive angle between the tenon and the axis of rotor assembly 5.

[0042] Example 6 This embodiment is a further optimization based on embodiment 5, as detailed below: The stationary blade linkage adjustment mechanism includes linkage rings at various levels, blade cranks, proportional linkage rods, and tie rods, with each linkage level rotating around the compressor axis.

[0043] In this embodiment, compared to the existing regulating cylinder structure, the linkage and rotation around the axis can avoid problems such as jamming and seizing caused by the guiding structure of the regulating cylinder structure. For the axial compressor of this technology, if a regulating cylinder structure is used, there are fewer adjustable blades, making jamming more likely.

[0044] Example 7 This embodiment is a further optimization based on embodiment 6, as detailed below: The rotor blade 5.1 is made of precipitation hardening martensitic stainless steel 05Cr17Ni4Cu4Nb. An inorganic phosphate anti-corrosion coating is sprayed on the rotor blades 5.1 of stages 1 to 3. The thickness of the inorganic phosphate anti-corrosion coating is ≥35~80μm.

[0045] The adjustable guide vanes and stationary blades are coated with an inorganic phosphate anti-corrosion coating with a thickness of ≥35~80μm.

[0046] In this embodiment, compared to the existing blade materials 20Cr13 and 13Cr11Ni2W2MoV, the precipitation-hardening martensitic stainless steel 05Cr17Ni4Cu4Nb exhibits superior overall performance. Furthermore, the existing blade materials 13Cr11Ni2W2MoV and 05Cr17Ni4Cu4Nb demonstrate better corrosion resistance. Applying an anti-corrosion coating to the blade surface effectively reduces corrosion during blade service.

Claims

1. A low aspect ratio industrial axial compressor, characterized in that, The compressor includes a base, a housing mounted on the base, an inlet convergent casing located at the front end of the housing, an outlet diffuser casing located at the rear end of the housing, a stator inner casing rotatably mounted in the housing along the axial direction, a rotor assembly (5) rotatably mounted in the stator inner casing along the axial direction, a bearing mounted in the housing to support the rotor assembly (5), and a stator linkage adjustment mechanism. The cavity formed by the outer hub surface of the rotor assembly (5) and the inner surface of the stator inner casing is the compressor flow channel. The rotor assembly (5) is mounted in the stator inner casing through a support bearing assembly, which includes an intake support bearing and an exhaust support bearing located on both sides. The housing consists of an intake housing, an intermediate housing, and an exhaust volute, which are welded together in sequence. The rotor assembly (5) includes a main shaft and multi-stage rotor blades (5.1) circumferentially mounted in the middle part of the main shaft. The number of stages of the rotor blades (5.1) is 6 to 12. The diameter of the hub surface of the rotor assembly (5) in the rotor blade (5.1) section gradually increases from the installation position of the first stage rotor blade (5.1) to the installation position of the fifth stage rotor blade (5.1). The hub surface of the rotor assembly (5) after the installation position of the fifth stage rotor blade (5.1) is a cylindrical surface. The inner casing of the stationary vanes is the outer flow channel of the compressor. The inner wall of the inner casing of the stationary vanes is provided with an adjustable inlet guide vane and a multi-stage stationary vane (3.1). The stationary vane (3.1) has 6 to 12 stages, which is the same as the number of stages of the rotor vane (5.1). The stationary blade linkage adjustment structure realizes the linkage adjustment of the adjustable guide blade and the 1st to 3rd stage stationary blades (3.1).

2. The low aspect ratio industrial axial compressor according to claim 1, characterized in that, The front external flow channel is a rotating surface composed of spline curves. The angle between the tangent of the generatrix of the rotating surface of the stationary blades (3.1) from stage 0 to 5 and the axis of the main shaft is 0.93 to 0.97°. The angle between the tangent of the generatrix of the rotating surface of the stationary blades (3.1) from stage 5 onwards and the axis of the main shaft is 1.5 to 2°.

3. A small aspect ratio industrial axial compressor according to claim 1, characterized in that, The internal flow channel, from the first-stage rotor blade (5.1) to the fifth-stage rotor blade (5.1), is a surface of revolution formed by spline curves. The surface of revolution of the sixth-stage rotor blade (5.1) and subsequent rotor blades (5.1) is a cylindrical surface. At the intersection of the accumulation line of the moving blades from the first to the twelfth stages and the generatrix of the surface of revolution of the internal flow channel, the angle between the tangent of the generatrix and the compressor axis is within the range of: 。 4. A small aspect ratio industrial axial compressor according to claim 1, characterized in that, The blade profile of each rotor blade (5.1) is a controllable diffusion blade profile with a small aspect ratio. The blade profile of each rotor blade (5.1) has a forward sweep of more than 30% of the blade span. The moving blade adopts a bent-twisted structure. Based on the root section, the maximum thickness is located at 40%-50% of the blade chord length. The aspect ratio ranges from 1.8 to 2.5, and the aspect ratio of the blade is in the range of 0.6 to 1.

5.

5. A small aspect ratio industrial axial compressor according to claim 1, characterized in that, The stationary blade (3.1) has a custom blade shape, and the blade spread line of the custom blade shape is a swept composite shape; the inlet adjustable guide blade and the first to third stage stationary blades (3.1) are all adjustable angle stationary blades, and the remaining stage stationary blades (3.1) are fixed angle stationary blades (3.1); the stationary blade adopts an arc-shaped structure, the maximum thickness is located at 30%-40% of the blade chord length, the leading and trailing edges adopt an elliptical structure, the length-to-width ratio is in the range of 1.8-2.5, and the aspect ratio of the blade is in the range of 0.6-1.

6.

6. A small aspect ratio industrial axial compressor according to claim 1, characterized in that, The rotor blades (5.1) of the first to fourth stages adopt axial dovetail tenons, and the angle between the plane of the tenon symmetry and the axis of the rotor assembly (5) is 20° to 28°; the rotor blades (5.1) of the fifth to twelfth stages adopt low-stress T-shaped tenons.

7. A small aspect ratio industrial axial compressor according to claim 1, characterized in that, The stationary blade linkage adjustment mechanism includes linkage rings at various levels, blade cranks, proportional linkage rods, and pull rods, with each linkage ring rotating around the compressor axis.

8. A small aspect ratio industrial axial compressor according to claim 1, characterized in that, The rotor blades (5.1) are made of precipitation-hardening martensitic stainless steel 05Cr17Ni4Cu4Nb.

9. A small aspect ratio industrial axial compressor according to claim 8, characterized in that, An inorganic phosphate anti-corrosion coating is sprayed on the rotor blades (5.1) of stages 1 to 3, and the thickness of the inorganic phosphate anti-corrosion coating is ≥35~80μm.

10. A small aspect ratio industrial axial compressor according to claim 1, characterized in that, The adjustable guide vane and the stationary vane are coated with an inorganic phosphate anti-corrosion coating, the thickness of which is ≥35~80μm.

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