Compressor stator vane adjustment method and compressor

Abstract

This disclosure provides a method for adjusting compressor stator blades and a compressor, relating to the field of compressor technology. The method for adjusting compressor stator blades includes: acquiring parameters of the distorted flow field of the compressor in the circumferential direction, establishing a flow field model, with parameters including velocity, pressure, and temperature; dividing multiple stator blades in the same stage of the compressor into N regions based on the flow field model; and using N adjusting devices to adjust the installation angle of the stator blades in each of the N regions, dynamically adjusting the installation angle according to the compressor's operating parameters to achieve aerodynamic matching between the stator blades and the distorted flow field. The installation angles of stator blades in any adjacent regions are different, while the installation angles of stator blades in the same region are the same. This adjustment method can achieve aerodynamic matching between the stator blades and the distorted flow field, reduce stator blade losses, improve the uniformity of the compressor outlet airflow, increase the stability margin of the downstream rotor, and ensure the efficient and stable operation of the compressor.

Description

Technical Field

[0001] This disclosure relates to the field of compressor technology, and in particular to a method for adjusting compressor stator blades and a compressor. Background Technology

[0002] An air compressor is a component that increases air pressure by using high-speed rotating blades to do work on the air. It is an important part of devices such as aircraft engines and gas turbines. To ensure stable operation of the air compressor, the airflow through it needs to be adjusted according to actual conditions. Therefore, the angles of the stator blades in the compressor are adjustable. By adjusting the synchronous rotation of each stator blade through a control mechanism, the rotation angle of each stator blade can be changed synchronously, thereby regulating the airflow through the compressor.

[0003] The prior art discloses a compressor and its multi-stage adjustable stationary vane adjustment device. The adjustment device includes a drive unit, transmission bars, a transmission gear system, and a linkage ring. The drive unit has a first toothed portion. The transmission bars are arranged in pairs on both sides of the first toothed portion and are movably supported on the outer periphery of the housing. The two transmission bars mesh with the first toothed portion on both sides. The transmission gear system includes an input end gear and an output end gear that rotates with the input end gear. The input end gear meshes with the two transmission racks. The second toothed portion of the linkage ring meshes with the transmission end and the output end gear of the adjustable stationary vane, respectively.

[0004] However, the above solution still has the following technical problems: when the compressor flow field is distorted, the stator blades of the same stage of the compressor have the same installation angle, which will not only affect the aerodynamic matching between the stator blades and the incoming flow, causing flow loss in the stator blades, but also lead to uneven airflow in the compressor, affecting the compressor's stable operating margin. Summary of the Invention

[0005] Based on the above problems, this disclosure provides a method for adjusting the stator blades of a compressor and a compressor, which can achieve aerodynamic matching between the stator blades and the flow field under the condition of compressor flow field distortion, reduce the flow loss of the stator blades, improve the airflow uniformity of the compressor, and thus improve the stable operation margin of the compressor.

[0006] On one hand, this disclosure provides a method for adjusting compressor stator blades, comprising: acquiring parameters of the distorted flow field of the compressor in the circumferential direction, and establishing a flow field model, wherein the parameters include velocity, pressure, and temperature; dividing multiple stator blades of the compressor located in the same stage into N regions according to the flow field model, wherein N is an integer greater than 1; adjusting the installation angle of the stator blades in the N regions respectively using N adjustment devices, and dynamically adjusting the installation angle according to the operating parameters of the compressor to achieve aerodynamic matching between the stator blades and the distorted flow field, wherein the installation angles of the stator blades in any adjacent regions are different, and the installation angles of the stator blades in the same region are the same.

[0007] In this embodiment of the disclosure, the operating parameters of the compressor are monitored by sensors to analyze and evaluate the performance of the compressor. The operating parameters include rotational speed and airflow.

[0008] In this embodiment of the disclosure, the performance and distorted flow field of the compressor are tested and analyzed by experimental measurement techniques or numerical simulation to evaluate the influence of different installation angles of the stator blades on the operating parameters of the compressor. The numerical simulation uses CFD tools.

[0009] In this embodiment of the disclosure, the method further includes: applying the optimized installation angle to the stator blades of the compressor, adjusting the stator blades of the compressor to conduct experimental verification of the compressor performance, and iteratively adjusting the installation angle based on the experimental verification results.

[0010] In this embodiment of the present disclosure, the installation angle of any of the stator blades of the same stage is individually adjusted by different adjustment devices. The adjustment devices are installed in the compressor casing, and the plurality of adjustment devices do not interfere with each other and can stably adjust the stator blades.

[0011] In this embodiment of the present disclosure, the stator blade includes an inlet guide vane, a stator blade, and an outlet guide vane. According to the flow field model, the installation angle of at least one of the inlet guide vane, the stator blade, and the outlet guide vane is adjusted using the adjustment device.

[0012] In this embodiment of the disclosure, several of the above-mentioned adjusting devices are communicatively connected to a control device, and the control device is capable of controlling the movement of the above-mentioned adjusting devices.

[0013] In this embodiment of the present disclosure, the adjustment device includes a drive member and an actuator. The drive member is mounted on the casing of the compressor and is connected to the actuator in a transmission manner. The actuator is used to connect with the stator blade.

[0014] On the other hand, this disclosure also provides a compressor in which the stator blades are adjusted by the compressor stator blade adjustment method described in any of the above embodiments. The compressor also includes a hub, a rotor, and a casing, with the rotor mounted on the hub and the stator blades mounted on the casing.

[0015] In this embodiment of the disclosure, based on the above-mentioned flow field model of the distorted flow field, at the same radial position of the compressor, along the circumferential direction of the compressor, the inlet geometric angle, outlet geometric angle, chord length and maximum thickness of each of the above-mentioned stator blades are different.

[0016] According to embodiments of this disclosure, the compressor stator blade adjustment method divides multiple stator blades of the same stage into N regions and uses N adjustment devices to adjust the installation angle of the stator blades in each of the N regions. This enables asymmetrical adjustment of the installation angle of multiple stator blades of the same stage, achieving asymmetrical setup of stator blades in the same stage. Under conditions of compressor flow field distortion, this method achieves aerodynamic matching between the stator blades and the distorted flow field, reducing stator blade losses, improving the uniformity of the compressor outlet airflow, and increasing the stability margin of the downstream rotor, thereby ensuring efficient and stable compressor operation. By dynamically adjusting the stator blades according to the compressor's operating parameters, the aerodynamic matching effect between the stator blades and the distorted flow field can be further improved, enhancing compressor performance. Attached Figure Description

[0017] The above and other objects, features and advantages of this disclosure will become clearer from the following description of embodiments with reference to the accompanying drawings, in which:

[0018] Figure 1 The diagram schematically illustrates the distribution of the distorted flow field of a compressor stator blade according to an embodiment of the present disclosure.

[0019] Figure 2 The diagram illustrates one embodiment of a method for adjusting the installation angle of compressor stator blades according to embodiments of the present disclosure.

[0020] Figure 3 for Figure 2 A schematic diagram showing the distribution of the stator blade mounting angle adjustment angle along the circumferential direction in the adjustment method shown.

[0021] Figure 4 The diagram illustrates a further embodiment of the distribution of the stator blade mounting angle adjustment angle along the circumferential position according to an embodiment of the present disclosure.

[0022] Figure 5 The diagram schematically illustrates the circumferential distribution of the inlet airflow angle of a compressor at different radial positions according to an embodiment of the present disclosure.

[0023] Figure 6 The diagram schematically illustrates the circumferential distribution of the inlet and outlet geometry angles of the stator blades according to an embodiment of the present disclosure.

[0024] The meanings of the reference numerals in the above figures are as follows:

[0025] 1-First adjusting device;

[0026] 2-Second adjusting device;

[0027] 3-Third adjustment device. Detailed Implementation

[0028] This disclosure provides a method for adjusting the stator blades of a compressor and a compressor, which can reduce the flow loss of the stator blades, improve the uniformity of the airflow at the compressor outlet, increase the stable operating margin of the downstream rotor, and ensure the efficient and stable operation of the compressor.

[0029] When the compressor flow field is distorted, if the stator blades of the same stage have the same installation angle, it will not only affect the aerodynamic matching between the stator blades and the incoming flow, causing flow losses in the stator blades, but also lead to uneven airflow within the compressor, affecting the compressor's stable operating margin. Therefore, it is necessary to perform non-axisymmetric adjustment of the compressor stator blades to achieve aerodynamic matching between the full-circumference stator blades and the distorted flow field, thereby reducing flow losses in the stator blades, improving the uniformity of the compressor outlet airflow, and ensuring the efficient and stable operation of the compressor.

[0030] See Figures 1 to 4The compressor stator blade adjustment method disclosed herein includes: acquiring parameters of the compressor distorted flow field in the circumferential direction and establishing a flow field model, the parameters including velocity, pressure and temperature; dividing multiple stator blades of the same stage of the compressor into N regions according to the flow field model, where N is an integer greater than 1; adjusting the installation angle of the stator blades in the N regions respectively using N adjustment devices, and dynamically adjusting the installation angle according to the operating parameters of the compressor to achieve aerodynamic matching between the stator blades and the distorted flow field, wherein the installation angles of the stator blades in any adjacent regions are different, and the installation angles of the stator blades in the same region are the same. Based on the established flow field model describing the variation law of the distorted flow field, multiple stator blades of the same stage are divided into N regions. N adjustment devices are used to adjust the installation angle of the stator blades in each of the N regions. This enables asymmetric adjustment of the installation angle of multiple stator blades of the same stage, achieving non-axisymmetric setup of the stator blades. Under the condition of flow field distortion in the compressor, this allows for aerodynamic matching of the stator blades with the distorted flow field in the full circumferential direction, reducing flow losses in the stator blades, improving the uniformity of the compressor outlet airflow, and increasing the stability margin of the downstream rotor, thus ensuring the efficient and stable operation of the compressor. Furthermore, dynamic adjustment of the stator blade installation angle based on the compressor's operating parameters can further improve the aerodynamic matching effect between the stator blades and the distorted flow field, thereby improving the compressor's performance.

[0031] In this embodiment, the compressor's operating parameters are monitored by sensors to analyze and evaluate its performance. These operating parameters include rotational speed and airflow rate. Rotational speed and airflow rate are two key indicators for compressor performance evaluation. By detecting these operating parameters through sensors, the compressor's operating status can be obtained in real time. This allows for the adjustment and optimization of the stator blade installation angle, improving the compressor's operating efficiency and reliability. Furthermore, it enhances the aerodynamic matching effect between the stator blades and the distorted flow field, ensuring the compressor's stable and efficient operation.

[0032] In this embodiment, the compressor's performance and distorted flow field are tested and analyzed using experimental measurement techniques or numerical simulations to evaluate the impact of different stator blade installation angles on the compressor's operating parameters. The numerical simulation employs CFD tools. Testing the compressor using experimental measurement techniques such as Particle Image Velocity (PIV) or numerical simulation techniques such as Computational Fluid Dynamics (CFD) allows for the analysis of compressor performance and distorted flow field, thereby assessing the impact of different stator blade installation angles on compressor performance. This leads to the optimization and iteration of the circumferential distribution of stator blade installation angles that aerodynamically matches the distorted flow field, ensuring stable and efficient compressor operation. Experimental measurement techniques can directly acquire actual operating data of the compressor at different stator blade installation angles, including key parameters such as rotational speed, airflow rate, pressure distribution, and temperature distribution. Experimental measurement techniques are intuitive and realistic, directly reflecting the actual operating state of the compressor. Numerical simulation techniques, especially those using CFD (Computational Fluid Dynamics) tools, can perform detailed simulations and analyses of the internal flow field of a compressor. By establishing a three-dimensional model of the compressor and setting different stator blade installation angles, the operating conditions of the compressor under various conditions can be simulated. CFD tools can calculate the distribution of parameters such as velocity, pressure, and temperature in the flow field, as well as the formation and evolution of the distorted flow field. By comparing and analyzing the simulation results under different installation angles, a deeper understanding of the impact of the stator blade installation angle on compressor performance can be gained.

[0033] The compressor stator blade adjustment method disclosed herein further includes: applying the optimized installation angle to the compressor stator blades, adjusting the compressor stator blades to conduct experimental verification of compressor performance, and iteratively adjusting the installation angle based on the experimental verification results. After a series of simulation optimizations of the installation angle, an installation angle scheme for the stator blades that aerodynamically matches the distorted flow field is obtained. The compressor is then subjected to actual testing, and the stator blades are adjusted according to the optimized installation angle scheme. Pressure, flow rate, and other parameter data of the compressor are collected and compared with the parameter data of the compressor before adjustment. Through continuous experimentation and adjustment, the optimal installation angle of the stator blades that aerodynamically matches the compressor is iteratively optimized to improve compressor performance.

[0034] Based on experimental measurement techniques or numerical simulation results, a set of preliminary optimized stator blade installation angles is determined. These angles should be designed to achieve aerodynamic matching between the stator blades and the distorted flow field in the full circumferential direction, reduce flow losses in the stator blades, improve the uniformity of the compressor outlet airflow, and increase the stability margin of the downstream rotor. The compressor stator blades are then practically adjusted, applying the optimized installation angles and ensuring precise adjustment. Finally, the compressor performance is experimentally verified, and experimental measurement techniques are used to obtain data on the compressor's performance after the adjustment. Actual operating data at the installation angle, including key parameters such as speed, airflow, and pressure distribution, will be used to evaluate whether the compressor performance has been improved. Based on the experimental results, the installation angle will be iteratively adjusted. If the experimental data shows that the performance has improved but has not reached the expected target, the installation angle can be further fine-tuned to find a better solution. If the experimental data shows that the performance has decreased or other problems have occurred, the cause needs to be analyzed and the installation angle adjusted to improve the performance. Through continuous experimental verification and iterative adjustment, the optimal stator blade installation angle will be found to optimize the compressor performance.

[0035] See Figure 4 In this compressor, the installation angle of each stator blade in the same stage is individually adjusted by different regulating devices mounted in the compressor casing. These devices operate independently and stably adjust the stator blades. By independently adjusting the installation angle of each stator blade, the airflow distribution and flow state within the compressor can be more precisely controlled, allowing for more accurate matching of changes in the distorted flow field. This reduces flow losses in the stator blades, improves the uniformity of the compressor outlet airflow, and increases the stability margin of the downstream rotor, ensuring efficient and stable compressor operation. Furthermore, it significantly improves the efficiency of troubleshooting and repair. The independent design of the different regulating devices ensures that the installation angle adjustment of each stator blade is performed independently and is not affected by the adjustments of other blades. This guarantees the accuracy and stability of the adjustment, avoiding performance fluctuations or malfunctions caused by mutual interference between the regulating devices.

[0036] As an alternative, the blades can be divided into several regions along the circumference, with the stator blades in each region having the same installation angle. This configuration simplifies the stator blade adjustment process and reduces adjustment costs.

[0037] Optionally, see Figures 1 to 3The stator blade installation angle was asymmetrically adjusted based on the compressor speed and flow rate. According to the non-uniform distribution characteristics of the airflow angle in the distorted flow field, the stator blade was divided into three regions, each adjusted by a separate adjusting device: adjusting device 1, adjusting device 2, and adjusting device 3. These devices adjusted the stator blade installation angles of the three regions to γ1, γ2, and γ3, respectively. Through sampling design and numerical simulation verification, it was found that under the compressor design speed and design flow rate conditions, the installation angles of the three regions were γ1 = 0°, γ2 = -8°, and γ3 = 6°, respectively. The stator blade loss at γ1 = 0° is 15.88% lower than the stator blade loss when the installation angle (axisymmetric adjustment) is 0° in all three regions. Under 90% design speed and design flow conditions, the stator blade loss is 23.72% lower when the installation angles of the three regions are γ1 = 0°, γ2 = -6° and γ3 = 24°, respectively, compared to the stator blade loss when the installation angle of the three regions is 0° (axisymmetric adjustment). Therefore, the optimal installation angle of the stator blades in the three regions under different distortion flow conditions and different operating conditions was studied and obtained.

[0038] The stator blades include inlet guide vanes, stationary blades, and outlet guide vanes. Based on the flow field model, the installation angle of at least one of these three blades is adjusted using an adjustment device. The compressor's distorted flow field includes inlet distorted flow field and interstage distorted flow field. Based on the distribution of the distorted flow field, the inlet guide vanes, stationary blades, or outlet guide vanes requiring installation angle adjustment are adjusted. This allows for precise asymmetric adjustment of the compressor stator blades, reducing stator blade adjustment costs and flow losses.

[0039] In this embodiment, several regulating devices are communicatively connected to a control device, which can control the movement of the regulating devices. The control device transmits regulating signals to the regulating devices based on the real-time operating parameters received from the compressor, thereby achieving real-time and accurate adjustment of the stator blades.

[0040] Optionally, the adjustment device includes a drive component and an actuator. The drive component is mounted in the compressor casing and is connected to the actuator via a transmission connection. The actuator is used to connect with the stator blades. Under the action of the drive component, the actuator can adjust the installation angle of the stator blades. The drive component can be driven by electric, hydraulic, or pneumatic means to ensure rapid response and accurate adjustment.

[0041] On the other hand, this disclosure also provides a compressor, the stator blades of which are adjusted by any of the above-described compressor stator blade adjustment methods. The compressor also includes a hub, a rotor, and a casing, with the rotor mounted on the hub and the stator blades mounted on the casing. After adjusting the installation angle of the stator blades, the flow losses of the stator blades can be reduced, ensuring high-efficiency operation of the compressor under varying operating conditions.

[0042] Based on the flow field model of the distorted flow field, at the same radial position of the compressor, the inlet geometry, outlet geometry, chord length, and maximum thickness of each stator blade are different along the circumferential direction of the compressor. Adjusting the geometric parameters such as the inlet geometry, outlet geometry, chord length, and maximum thickness of the stator blades can improve the aerodynamic matching effect between the stator blades and the distorted flow field, enabling the stator blades to maintain efficient aerodynamic performance under various flow field conditions.

[0043] Among them, at the radial positions of 10% and 70% of the compressor inlet, the circumferential distribution of the inlet airflow angle is as follows: Figure 5 As shown in the figure, after design optimization, the circumferential distribution of the stator blade's inlet and outlet geometric angles is obtained as follows: Figure 6 As shown, numerical simulations have verified that the two asymmetric stator blade distribution designs can reduce stator blade losses at the radial positions of 10% and 70% of the compressor inlet by 16.15% and 18.33%, respectively.

[0044] It should also be noted that the directional terms mentioned in the embodiments, such as "up," "down," "front," "back," "left," and "right," are only for reference to the directions in the accompanying drawings and are not intended to limit the scope of protection of this disclosure. Throughout the drawings, the same elements are represented by the same or similar reference numerals. Conventional structures or constructions will be omitted where they may cause confusion in understanding this disclosure.

[0045] Furthermore, the shapes and dimensions of the components in the figures do not reflect actual size and proportion, but are merely illustrative of embodiments of this disclosure. Additionally, any reference numerals placed between parentheses in the claims should not be construed as limiting the scope of the claims.

[0046] Furthermore, the word "comprising" does not exclude the presence of elements or steps not listed in the claims. The word "a" or "an" preceding an element does not exclude the presence of a plurality of such elements.

[0047] The use of ordinal numbers such as "first," "second," "third," etc., in the specification and claims to modify the corresponding elements does not imply that the element has any ordinal number, nor does it represent the order of one element with another element, or the order of manufacturing methods. The use of these ordinal numbers is only to enable a named element to be clearly distinguished from another element with the same name.

[0048] Furthermore, unless specifically described or required to occur in a specific order, the order of the above steps is not limited to those listed above and can be varied or rearranged according to the desired design. Moreover, the above embodiments can be used in combination with each other or with other embodiments based on design and reliability considerations; that is, technical features from different embodiments can be freely combined to form more embodiments.

[0049] Those skilled in the art will understand that modules in the device of the embodiments can be adaptively changed and placed in one or more devices different from that embodiment. Modules, units, or components in the embodiments can be combined into a single module, unit, or component, and further, they can be divided into multiple sub-modules, sub-units, or sub-components. Except where at least some of such features and / or processes or units are mutually exclusive, any combination can be used to combine all features disclosed in this specification (including the accompanying claims, abstract, and drawings) and all processes or units of any method or device so disclosed. Unless expressly stated otherwise, each feature disclosed in this specification (including the accompanying claims, abstract, and drawings) may be replaced by an alternative feature that serves the same, equivalent, or similar purpose. Furthermore, in the unit claims enumerating several means, several of these means may be embodied by the same hardware item.

[0050] The specific embodiments described above further illustrate the purpose, technical solutions, and beneficial effects of this disclosure. It should be understood that the above descriptions are merely specific embodiments of this disclosure and are not intended to limit this disclosure. Any modifications, equivalent substitutions, improvements, etc., made within the spirit and principles of this disclosure should be included within the protection scope of this disclosure.

Claims

1. A method of adjusting a compressor stator vane, characterized by, include: Obtain the parameters of the compressor distorted flow field in the circumferential direction and establish a flow field model. The parameters include velocity, pressure and temperature. Based on the flow field model, the multiple stator blades of the compressor located in the same stage are divided into N regions, where N is an integer greater than 1; The installation angles of the stator blades in N regions are adjusted by using N adjustment devices respectively. The installation angles are dynamically adjusted according to the operating parameters of the compressor to achieve aerodynamic matching between the stator blades and the distorted flow field. The installation angles of the stator blades in any adjacent regions are different, while the installation angles of the stator blades in the same region are the same. Based on the non-uniform distribution characteristics of the airflow angle in the distorted flow field, the stator blades are divided into three regions, and the installation angle of the stator blades is asymmetrically adjusted according to the compressor speed and flow rate.

2. The compressor stator blade adjustment method according to claim 1, characterized in that, The compressor's operating parameters, including speed and airflow, are monitored by sensors to analyze and evaluate its performance.

3. The compressor stator blade adjustment method according to claim 1, characterized in that, The performance and distorted flow field of the compressor are tested and analyzed by experimental measurement techniques or numerical simulation to evaluate the influence of different installation angles of the stator blades on the operating parameters of the compressor. The numerical simulation uses CFD tools.

4. The compressor stator blade adjustment method according to any one of claims 1-3, characterized in that, Also includes: The optimized installation angle is applied to the stator blades of the compressor to adjust the stator blades of the compressor for experimental verification of compressor performance. Based on the experimental verification results, the installation angle is iteratively adjusted.

5. The compressor stator blade adjustment method according to claim 4, characterized in that, The installation angle of any stator blade in the same stage is individually adjusted by different adjustment devices, which are installed in the compressor casing. The adjustment devices do not interfere with each other and can stably adjust the stator blade.

6. The compressor stator blade adjustment method according to claim 4, characterized in that, The stator blades include an inlet guide vane, a stator blade, and an outlet guide vane. Based on the flow field model, the installation angle of at least one of the inlet guide vane, the stator blade, and the outlet guide vane is adjusted using the adjustment device.

7. The compressor stator blade adjustment method according to claim 4, characterized in that, All of the aforementioned adjustment devices are communicatively connected to a control device, which is capable of controlling the movement of the adjustment devices.

8. The compressor stator blade adjustment method according to claim 7, characterized in that, The regulating device includes a drive component and an actuator. The drive component is installed in the compressor casing and is connected to the actuator in a transmission manner. The actuator is used to connect with the stator blade.

9. A compressor, characterized in that, The stator blades of the compressor are adjusted by the compressor stator blade adjustment method according to any one of claims 1-8. The compressor further includes a hub, a rotor, and a casing. The rotor is mounted on the hub, and the stator blades are mounted on the casing.

10. The compressor according to claim 9, characterized in that, Based on the flow field model of the distorted flow field, at the same radial position of the compressor, the inlet geometry, outlet geometry, chord length, and maximum thickness of each stator blade are different along the circumferential direction of the compressor.

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