A multi-stage cascade guide vane device, design method and guide vane adjusting method

Abstract

This invention discloses a multi-stage adjustable guide vane device, its design method, and its adjustment method. The device includes a drive mechanism and at least three stages of adjustable guide vane assemblies. Each stage of the adjustable guide vane assembly includes multiple guide vanes. The drive mechanism is connected to each stage of the adjustable guide vane assembly for simultaneous adjustment of the guide vane angles of each stage, maintaining the compressor surge boundary within a preset threshold range during low-speed operation. This invention improves upon the existing two-stage adjustable guide vane design for aero-engines by incorporating at least three stages of adjustable guide vane assemblies. It redesigns the guide vane adjustment rules and aims to expand the compressor's operating margin at low speeds by adjusting the blade angles of each stage of the adjustable guide vane assembly. This ensures that the compressor surge boundary remains essentially unchanged at low speeds, thereby eliminating the need for a bleed valve, improving fuel economy, reducing weight, size, and cost.

Description

Technical Field

[0001] This invention relates to the field of aero-engine technology, specifically to a multi-stage guide vane adjustment device, its design method, and its adjustment method. Background Technology

[0002] After an aircraft engine is converted into a ground-based gas turbine, it typically needs to operate in a low-speed range below 85% of its relative equivalent speed for extended periods. However, at low speeds, the compressor is prone to surge. Existing gas turbines generally employ a structural design combining adjustable guide vane assemblies and bleed valves. Under low-speed conditions, opening the bleed valves to discharge excess air reduces the amount of air flowing to subsequent stages while increasing the airflow through the preceding stages for stable operation. This prevents compressor surge and improves operating margin.

[0003] However, this structure has obvious drawbacks when applied to ground-based gas turbines: long-term opening of the bleed valve under low operating conditions leads to a large waste of compressed air and poor fuel economy; the bleed valve itself has a complex structure and high cost, which is not conducive to cost reduction; at the same time, it requires additional external pipelines, which significantly increases the overall weight, size and maintenance cost of the engine. Summary of the Invention

[0004] In view of this, the present invention provides a multi-stage guide vane device, a design method, and a guide vane adjustment method to solve the problem that existing aero-engine designs do not meet the requirements for long-term low-speed operation of ground gas turbines.

[0005] In a first aspect, the present invention provides a multi-stage guide vane device, applied in an aero-engine compressor, comprising: At least three levels of adjustable guide vane assemblies, each level of which includes multiple guide vanes; The drive mechanism is connected to each stage of the adjustable guide vane assembly for transmission. The drive mechanism is used to simultaneously adjust the guide vane angle of each stage of the adjustable guide vane assembly so that the surge boundary of the compressor in the low operating condition range is maintained within a preset threshold range.

[0006] The beneficial effects of the aforementioned multi-stage adjustable guide vane device are as follows: it improves the original two-stage adjustable guide vane of the aero-engine to at least three-stage adjustable guide vane assembly, redesigns the guide vane adjustment law, and aims to expand the working margin of the compressor at low speed by adjusting the blade angle of each stage of the adjustable guide vane assembly, ensuring that the compressor surge boundary remains basically unchanged at low speed, thereby achieving the purpose of eliminating the bleed valve, improving fuel economy, reducing weight, reducing size, and reducing cost.

[0007] In one optional implementation, the drive mechanism includes: The drive linkage connects to the drive source. The control lever is hinged to the drive linkage via a first connecting structure. The control lever is parallel to the engine axis, and the end of the control lever is rotatably mounted on the compressor housing. At least three-stage linkage ring assemblies are provided, with each stage of the linkage ring assemblies arranged linearly at intervals along the engine axis. Each stage of the linkage ring assemblies is hinged to the control lever via a connecting rod assembly, and each stage of the linkage ring assemblies is provided with multiple rocker arm assemblies at circumferential intervals. The rocker arm assemblies are connected to the guide vanes.

[0008] In one alternative embodiment, each of the guide vanes is disposed inside the compressor housing, the drive mechanism is disposed outside the compressor housing, and the guide vanes are rotatably mounted on the rocker arm assembly via a shaft passing through the compressor housing.

[0009] The beneficial effects of the above technical solution are as follows: The drive mechanism is located outside the compressor housing, avoiding direct contact with the internal high-temperature, high-pressure airflow, effectively reducing the heat load and corrosion risk of the drive mechanism and extending its service life. Simultaneously, the external arrangement facilitates the inspection and maintenance of the drive mechanism, eliminating the need to disassemble the compressor flow path components, significantly improving operational convenience. A reliable sealing structure is used where the shaft passes through the compressor housing to prevent internal airflow leakage and maintain the stability of the internal aerodynamic environment of the compressor. Furthermore, this separate internal and external layout design does not occupy the internal flow path space of the compressor and provides ample operating space for the installation and commissioning of the adjustable guide vane components, adapting to the compact structural requirements of aero-derivative gas turbines.

[0010] In one optional embodiment, the linkage assembly includes a second connecting structure, a connecting rod, and a linkage lug. One end of the second connecting structure is connected to a control lever, and the other end of the second connecting structure is hinged to the connecting rod. The end of the connecting rod away from the second connecting structure is hinged to the linkage lug, and the linkage lug is disposed on the linkage assembly.

[0011] In one optional embodiment, the adjustable guide vane assembly is provided with three levels: a zero-level adjustable guide vane assembly, a first-level adjustable guide vane assembly, and a second-level adjustable guide vane assembly. The zero-level adjustable guide vane assembly includes multiple zero-level guide vanes, the first-level adjustable guide vane assembly includes multiple first-level guide vanes, and the second-level adjustable guide vane assembly includes multiple second-level guide vanes. The linkage ring assembly is configured with three levels: a zero-level linkage ring assembly, a first-level linkage ring assembly, and a second-level linkage ring assembly. The rocker arm assembly is provided with three levels: a zero-level rocker arm, a first-level rocker arm, and a second-level rocker arm. The zero-stage guide vane is rotatably mounted on the zero-stage rocker arm, which is hinged to the zero-stage linkage ring assembly. The first-stage guide vane is rotatably mounted on the first-stage rocker arm, which is hinged to the first-stage linkage ring assembly. The second-stage guide vane is rotatably mounted on the second-stage rocker arm, which is hinged to the second-stage linkage ring assembly.

[0012] The beneficial effects of the above technical solution are as follows: This invention improves upon the original two-stage adjustable guide vanes by creating a three-stage adjustable guide vane system. The guide vane adjustment mechanism is redesigned, and by adjusting the blade angles of the zero-stage, first-stage, and second-stage guide vanes, the compressor surge boundary is kept essentially unchanged. This achieves the elimination of the bleed valve, ultimately improving fuel economy, reducing weight, decreasing size, and lowering costs. This invention has a compact structure, high reliability, and can simultaneously adjust all three stages of guide vanes, satisfying different adjustment angle ranges for each stage.

[0013] In one optional implementation, the angle adjustment range of each level of the adjustable guide vane assembly is configured independently, and the adjustable angle range of each level of the adjustable guide vane assembly is set by the parameters of the drive mechanism.

[0014] Secondly, the present invention provides a design method for a multi-stage coordinated guide vane device, comprising the following steps: S1. To meet the usage requirements of gas turbines in the low operating range, the compressor guide vanes are configured as at least three-stage adjustable guide vane assemblies; S2. Determine the target angle adjustment range for each stage of the adjustable guide vane assembly, taking the constraint that the compressor's low-condition surge boundary does not decrease; S3. Design the motion transmission path of the drive mechanism and calculate the maximum angle adjustment range that the drive mechanism can drive at each stage of adjustable guide vane assembly; S4. Compare the maximum angle adjustment range with the target angle adjustment range; when the maximum angle adjustment range is different from the target angle adjustment range, optimize the design parameters of the drive mechanism to make the maximum angle adjustment range the same as the target angle adjustment range.

[0015] The beneficial effects of the above technical solution are as follows: This invention can effectively adapt to the usage requirements of aero-derivative gas turbines in low operating conditions. Through the coordinated adjustment of at least three stages of adjustable guide vane assemblies, and with the target angle adjustment range determined by the constraint that the surge boundary does not decrease, it ensures that the compressor maintains stable aerodynamic performance at low loads and avoids increased surge risk due to guide vane adjustment. At the same time, by optimizing the design parameters of the drive mechanism, the maximum angle adjustment range of the drive mechanism is precisely matched with the target angle adjustment range, realizing precise joint adjustment of each stage of guide vanes and improving the reliability and effectiveness of guide vane adjustment.

[0016] In an optional implementation, step S3 involves calculating the maximum angle adjustment range that the drive mechanism can drive at each stage of the adjustable guide vane assembly, including the following steps: With the engine axis as the X-axis, a coordinate system is constructed according to the right-hand rule. The length of the drive link, the length of the first connecting structure, the included angle of the control lever, the length of the second connecting structure, the length of the link of this stage, the radial position of the linkage lug, the radial position of the rocker arm mounting center, the initial angular position of the linkage lug, and the rocker arm length parameters are determined in sequence. The limit adjustment angles of the guide vane in two opposite directions are calculated respectively, and the sum of the two is the maximum angle adjustment range of the guide vane.

[0017] In one alternative implementation, in step S4, the design parameters of the drive mechanism are optimized, specifically including: optimizing the position and / or size parameters of at least one of the drive linkage, control lever, linkage assembly at each stage, linkage ring assembly, or rocker arm assembly.

[0018] Thirdly, the present invention provides a guide vane adjustment method, the method being based on the aforementioned multi-stage coordinated guide vane device, comprising the following steps: At least three stages of adjustable guide vane assemblies are installed in the compressor. The guide vane angle of each stage of the adjustable guide vane assembly is adjusted simultaneously by the drive mechanism to match the airflow angle of attack at different speeds of the compressor, so that the airflow enters the corresponding next stage rotor at a preset angle; and the flow capacity and work capacity of each stage of the compressor are matched to widen the surge margin in the low operating condition range.

[0019] In one optional implementation, the guide vane angles of each stage of the adjustable guide vane assembly are simultaneously adjusted via a drive mechanism, specifically including the following steps: The drive source outputs power to drive the control lever to rotate via the drive linkage. The control lever drives the corresponding linkage ring assembly to move circumferentially via each level of linkage assembly. Each level of linkage ring assembly drives the corresponding rocker arm assembly to swing, and finally drives the guide vane of the corresponding level to rotate around its own axis, thus completing the angle adjustment. Attached Figure Description

[0020] To more clearly illustrate the specific embodiments of the present invention or the technical solutions in the prior art, the drawings used in the description of the specific embodiments or the prior art will be briefly introduced below. Obviously, the drawings described below are some embodiments of the present invention. For those skilled in the art, other drawings can be obtained from these drawings without creative effort.

[0021] Figure 1 A schematic diagram of the structure of a multi-stage coordinated guide vane device provided by the present invention; Figure 2 A side view of a multi-stage guide vane device provided by the present invention; Figure 3 A force and motion transmission route diagram for a multi-stage coordinated guide vane device provided by the present invention; Figure 4 A schematic diagram of the zero-stage guide vane adjustment law of a multi-stage coordinated guide vane device provided by the present invention; Figure 5 A schematic diagram of the relevant dimensions of the drive linkage of a multi-stage coordinated guide vane device provided by the present invention; Figure 6 A schematic diagram showing the relevant dimensions of the control lever of a multi-stage coordinated guide vane device provided by the present invention; Figure 7 A schematic diagram of the relevant dimensions of the zero-stage connecting rod of a multi-stage coordinated guide vane device provided by the present invention; Figure 8 A schematic diagram showing the relevant dimensions of the zero-stage linkage ring assembly and the zero-stage rocker arm of a multi-stage coordinated guide vane device provided by the present invention; Figure 9 A schematic diagram of the relevant dimensions of the zero-stage rocker arm of a multi-stage coordinated guide vane device provided by the present invention; Figure 10 This is a schematic diagram of the current venting valve device.

[0022] Explanation of reference numerals in the attached figures: 1. Drive linkage; 2. Control lever; 3. Zero-stage linkage; 4. First-stage linkage; 5. Second-stage linkage; 6. Zero-stage linkage ring assembly; 7. Zero-stage rocker arm; 8. First-stage linkage ring assembly; 9. First-stage rocker arm; 10. Second-stage linkage ring assembly; 11. Second-stage rocker arm; 12. Guide vane; 13. Compressor housing; 14. Rotary shaft; 15. First connecting structure; 16. Second connecting structure; 17. Linkage ring lug. Detailed Implementation

[0023] To make the objectives, technical solutions, and advantages of the embodiments of the present invention clearer, the technical solutions of the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some embodiments of the present invention, not all embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of the present invention.

[0024] After an aircraft engine is converted into a ground-based gas turbine, it typically needs to operate for extended periods in a low-speed range below 85% of its relative equivalent speed. However, at low speeds, the compressor is prone to surge. Existing gas turbines generally employ a structural design combining adjustable guide vane assemblies and bleed valves, such as... Figure 10As shown, under low-speed operating conditions, opening the bleed valve to discharge excess air reduces the amount of air flowing to the subsequent stages and increases the airflow through the preceding stages that operates stably, thereby preventing compressor surge and improving operating margin. However, existing aero-engine designs do not meet the requirements for long-term low-speed operation of ground-based gas turbines, and this structure has significant drawbacks when applied to ground-based gas turbines: Prolonged opening of the bleed valve under low operating conditions will result in a large waste of compressed air and poor fuel economy. The venting valve itself has a complex structure and high cost, which is not conducive to cost reduction; It also requires additional external piping, which significantly increases the overall weight, size, and maintenance costs of the engine.

[0025] Based on this, the present invention provides a multi-stage adjustable guide vane device, a design method, and a guide vane adjustment method. By designing a multi-stage adjustable guide vane device, the vent valve can be eliminated, thereby ensuring working margin and ultimately achieving the goals of improving fuel economy, reducing weight, reducing size, and lowering cost.

[0026] Combination Figures 1 to 9 As shown, the specific embodiments of the present invention will be described in detail below with reference to the multi-stage coordinated guide vane device of the first aspect, the design method of the multi-stage coordinated guide vane device of the second aspect, and the guide vane adjustment method of the third aspect.

[0027] According to an embodiment of the present invention, in a first aspect, a multi-stage coordinated guide vane device is provided, combined with... Figure 1 and Figure 2 As shown, this device, used in aero-engine compressors, includes an adjustable guide vane assembly and a drive mechanism. The adjustable guide vane assembly has at least three stages, each stage comprising multiple guide vanes 12. The drive mechanism is connected to each stage of the adjustable guide vane assembly and simultaneously adjusts the angle of the guide vanes 12 at each stage, maintaining the surge boundary of the compressor within a preset threshold range during low-operational-condition periods. The drive mechanism can simultaneously adjust each stage of the adjustable guide vane assembly to meet the different angle adjustment requirements of each stage of the guide vane.

[0028] It should be noted that the surge boundary refers to the critical limit between a stable operating state and the occurrence of surge phenomena during the operation of a gas turbine compressor. When the compressor's intake airflow decreases to a certain critical value, the airflow will experience periodic backflow and oscillation, leading to a sharp decline in compressor performance and even damage to the equipment. The surge boundary is the marker line that defines this critical state, ensuring that the compressor can avoid the surge region and maintain stable operation under various operating conditions.

[0029] In this embodiment, at least three stages of adjustable guide vane assemblies are arranged in the compressor, and a multi-stage coordinated adjustment drive mechanism is designed to achieve synchronous adjustment of each stage of the guide vanes. By adjusting the guide vane angle, the surge margin of the compressor in the low operating condition range is widened, and the bleed valve structure is completely eliminated while ensuring that the compressor surge boundary remains basically unchanged. The adjustment accuracy and operating condition matching degree of the three-stage guide vane coordinated adjustment are much higher than the original two-stage guide vane + bleed valve scheme. The surge margin fluctuation of the compressor is smaller under low operating conditions, and there is no operating condition disturbance caused by the opening and closing of the bleed valve, resulting in more stable compressor operation.

[0030] This embodiment improves upon the existing two-stage adjustable guide vanes of an aero-engine by replacing them with at least a three-stage adjustable guide vane assembly. The guide vane adjustment mechanism is redesigned, and the aim is to expand the compressor's operating margin at low speeds by adjusting the blade angles of each stage of the adjustable guide vane assembly. This ensures that the compressor surge boundary remains essentially unchanged at low speeds, thereby eliminating the need for a bleed valve, improving fuel economy, reducing weight, size, and cost. Specifically, expanding the compressor's operating margin at low speeds means that, through the coordinated angle adjustment of the multi-stage adjustable guide vane assembly, a sufficient safety distance is maintained between the compressor's actual operating point and the surge boundary during low-speed operation. This allows the compressor to operate stably in lower flow ranges or more complex low-operation conditions without relying on the bleed valve's bleed action to mitigate surge risks, thus achieving the design objective of eliminating the bleed valve and optimizing the overall compressor performance.

[0031] The core principles of designing at least three-stage adjustable guide vane assemblies can be summarized in the following two points: 1) Matching speed and controlling angle of attack: This ensures that the airflow enters the rotor blades at the optimal angle (angle of attack) at the compressor's design speed. At low speeds, by adjusting the guide vanes at each stage, the airflow direction is pre-twisted, allowing it to enter the next stage rotor at a near-ideal angle. This prevents airflow separation and surge caused by excessive angle of attack. 2) Change the flow and work capacity: At low speed, by adjusting the guide vanes of each stage, the flow and energy between each stage can be matched, avoiding the compressor inlet flow being too large and causing stall, and the compressor outlet flow being too dense and causing blockage, thereby widening the surge margin at low speed.

[0032] This embodiment replaces the bleed valve with a multi-stage adjustable guide vane assembly, avoiding the waste of compressed air caused by the bleed valve being open for a long time under low-speed conditions, thereby improving fuel economy.

[0033] This embodiment eliminates the complex and expensive venting valve and its associated external piping, reducing component costs and system complexity.

[0034] This embodiment eliminates the bleed valve and related pipelines, significantly reducing the overall weight and size of the engine and optimizing the structural layout.

[0035] This embodiment can be adapted to ground-based gas turbines and other aircraft, and can be applied to different aircraft models without major modifications.

[0036] In some embodiments, the drive mechanism includes a drive linkage 1, a control lever 2, and at least a three-stage linkage assembly.

[0037] Drive link 1 is connected to the drive source, which is a device that provides power.

[0038] The control lever 2 is hinged to the drive link 1 via a first connecting structure 15. The first connecting structure 15 is a rod structure disposed between the drive link 1 and the control lever 2. One end of the first connecting structure 15 is hinged to the drive link 1, and the other end of the first connecting structure 15 is connected to the control lever 2. The control lever 2 is parallel to the engine axis. The end of the control lever 2 is rotatably mounted on the compressor housing 13.

[0039] The linkage ring assembly has at least three levels. The center of the linkage ring assembly coincides with the engine axis. Each level of the linkage ring assembly is arranged linearly at intervals along the engine axis. Each level of the linkage ring assembly is hinged to the control lever 2 through a connecting rod assembly. Each level of the linkage ring assembly is provided with multiple rocker arm assemblies at intervals along the circumference. The rocker arm assemblies are connected to the guide vane 12.

[0040] The working process of this embodiment is as follows: After the drive source is started, the drive source connecting part drives the drive linkage 1 to move. The drive linkage 1 pushes the first connecting structure 15 hinged to it, thereby driving the control lever 2 to rotate. When the control lever 2 rotates, it synchronously drives the linkage ring assemblies of each stage to rotate around the engine axis through the linkage assembly hinged to it. During the rotation of each linkage ring assembly, the rocker arm assembly arranged circumferentially swings accordingly. The rocker arm assembly drives the guide vane 12 connected to it to rotate around its own mounting axis, thereby realizing the synchronous angle adjustment of at least three stages of guide vanes. When the drive source moves in the opposite direction, the above transmission path runs in the reverse direction, and the guide vane angle is adjusted accordingly in the reverse direction to adapt to the compressor operation requirements under different operating conditions.

[0041] This embodiment uses a drive mechanism to drive at least three stages of linkage ring assemblies to rotate simultaneously, achieving coordinated adjustment of the 12-degree angle of each stage of the guide vanes. This effectively optimizes the flow characteristics of the airflow inside the compressor, improves the compressor's compression efficiency and pressure ratio, and enhances the adaptability of the aero-derivative gas turbine under different operating conditions. The linkage ring assemblies are arranged linearly along the engine axis, with a compact structure and reasonable layout, adapting to the space constraints of the aero-derivative gas turbine. The hinged transmission structure of the drive linkage and the control lever is reliable and responsive, able to quickly follow the drive source's actions to adjust the 12-degree angle of the guide vanes, ensuring a smooth transition of the gas turbine when switching operating conditions.

[0042] It should be noted that the initial angle of the guide vanes 12 in each stage of the adjustable guide vane assembly is set differently based on the optimal airflow characteristics and interstage matching requirements under the design conditions of the aero-derivative gas turbine. The initial angle value is reserved with sufficient adjustment margin to ensure that the guide vanes can cover the airflow adjustment requirements under different operating conditions (such as start-up, low load, and high load) when the angle is increased in the forward direction or decreased in the reverse direction, thus laying the foundation for the efficient and stable operation of the compressor across the entire operating range.

[0043] In some embodiments, each guide vane 12 is disposed inside the compressor housing 13, the drive mechanism is disposed outside the compressor housing 13, and the guide vane 12 is rotatably disposed on the rocker arm assembly via a rotating shaft 14 passing through the compressor housing 13.

[0044] In this embodiment, the drive mechanism is located outside the compressor housing 13, avoiding direct contact with the internal high-temperature, high-pressure airflow. This effectively reduces the heat load and corrosion risk of the drive mechanism, extending its service life. Simultaneously, the external arrangement facilitates maintenance and repair of the drive mechanism, eliminating the need to disassemble the compressor flow path components and significantly improving operational convenience. The shaft 14, passing through the compressor housing 13, employs a reliable sealing structure to prevent internal airflow leakage and maintain the stability of the internal aerodynamic environment of the compressor. Furthermore, this separate internal and external layout design does not occupy internal flow path space within the compressor and provides ample operating space for the installation and commissioning of the adjustable guide vane components, adapting to the compact structural requirements of aero-derivative gas turbines.

[0045] Furthermore, since the rotating shaft 14 passes through the compressor housing 13, when the linkage ring assembly drives the rocker arm assembly to move, one end of the rocker arm assembly is limited by the rotating shaft 14, so that the rocker arm assembly can only swing, and then drive the rotating shaft 14 to rotate. When the rotating shaft 14 rotates, it drives the guide vane 12 to rotate around its axis.

[0046] In some embodiments, the linkage assembly includes a second connecting structure 16, a connecting rod, and a linkage lug 17. The second connecting structure 16 is a rod structure disposed between the connecting rod and the control lever 2. One end of the second connecting structure 16 is connected to the control lever 2, and the other end of the second connecting structure 16 is hinged to the connecting rod. The end of the connecting rod away from the second connecting structure 16 is hinged to the linkage lug 17, and the linkage lug 17 is disposed on the linkage assembly.

[0047] In some embodiments, the angle adjustment range of each stage of the adjustable guide vane assembly is configured independently, and the adjustable angle range of each stage of the adjustable guide vane assembly is set by the parameters of the drive mechanism. This embodiment can simultaneously adjust three stages of guide vanes and meet the different adjustment angle ranges of each stage of guide vane.

[0048] In an optional embodiment, the adjustable guide vane assembly has three levels: a zero-level adjustable guide vane assembly, a first-level adjustable guide vane assembly, and a second-level adjustable guide vane assembly. The zero-level adjustable guide vane assembly includes multiple zero-level guide vanes, the first-level adjustable guide vane assembly includes multiple first-level guide vanes, and the second-level adjustable guide vane assembly includes multiple second-level guide vanes. The linkage ring assembly has three levels: a zero-level linkage ring assembly 6, a first-level linkage ring assembly 8, and a second-level linkage ring assembly 10. The rocker arm assembly has three levels: a zero-level rocker arm 7, a first-level rocker arm 9, and a second-level rocker arm 11. The zero-stage guide vane is rotatably mounted on the zero-stage rocker arm 7, which is hinged to the zero-stage linkage ring assembly 6. The zero-stage linkage ring assembly 6 is hinged to the second connecting structure via the zero-stage connecting rod 3. The first-stage guide vane is rotatably mounted on the first-stage rocker arm 9, which is hinged to the first-stage linkage ring assembly 8. The first-stage linkage ring assembly 8 is hinged to another second connecting structure via the first-stage connecting rod 4. The second-stage guide vane is rotatably mounted on the second-stage rocker arm 11, which is hinged to the second-stage linkage ring assembly 10. The second-stage linkage ring assembly 10 is hinged to another second connecting structure via the second-stage connecting rod 5.

[0049] The working process is as follows: The drive mechanism applies driving forces to the zero-stage linkage ring assembly 6, the first-stage linkage ring assembly 8, and the second-stage linkage ring assembly 10 respectively, based on the real-time operating parameters of the aero-derivative gas turbine. When the zero-stage linkage ring assembly 6 displaces circumferentially along the compressor casing, the zero-stage rocker arm 7, hinged to it, is pulled and swings around the pivot shaft 14, thereby causing the zero-stage guide vane to rotate around its own axis to a preset angle. Similarly, the displacement of the first-stage linkage ring assembly 8 is transmitted to the first-stage guide vane through the first-stage rocker arm 9, enabling the first-stage guide vane to complete the corresponding angle adjustment. The second-stage linkage ring assembly 10 drives the second-stage guide vane to rotate through the second-stage rocker arm 11. The transmission path of force and motion is as follows: Figure 3 As shown, because the angle adjustment range of each adjustable guide vane assembly is independently configured, the drive mechanism can precisely control the deflection amplitude of each guide vane, realizing the coordinated linkage of multiple guide vanes. This adapts to the aerodynamic requirements of the gas turbine under different loads, optimizes the airflow organization inside the compressor, and improves the operating efficiency and stability of the gas turbine.

[0050] This embodiment improves upon the original two-stage adjustable guide vanes by creating a three-stage adjustable guide vane system. The guide vane adjustment mechanism is redesigned, and by adjusting the blade angles of the zero-stage, first-stage, and second-stage guide vanes, the compressor surge boundary is kept essentially unchanged. This achieves the goal of eliminating the bleed valve, ultimately improving fuel economy, reducing weight, size, and cost. This embodiment features a compact structure, high reliability, and can simultaneously adjust all three stages of guide vanes, satisfying different adjustment angle ranges for each stage.

[0051] According to an embodiment of the present invention, in a second aspect, a design method for a multi-stage guide vane device is provided, comprising the following steps: S1. To meet the usage requirements of gas turbines in the low operating range, the compressor guide vanes are configured as at least three-stage adjustable guide vane assemblies.

[0052] S2. Using the constraint that the compressor's low-condition surge boundary does not decrease, determine the target angle adjustment range for each stage of the adjustable guide vane assembly.

[0053] The "compressor surge boundary not decreasing under low operating conditions" means that, under low operating conditions of the gas turbine, the critical operating boundary at which the compressor surges will not shift in a direction unfavorable to stable operation due to the angle adjustment of each stage of the adjustable guide vane assembly. This ensures that the compressor can maintain stable aerodynamic performance in the low-load range and avoids increased surge risk due to guide vane adjustment. Under low operating conditions, the compressor flow rate is more likely to approach the surge boundary. Therefore, using the non-decreasing surge boundary as a constraint condition can effectively ensure that the compressor maintains stable aerodynamic performance at low loads, providing a key basis for the angle configuration of multi-stage adjustable guide vanes.

[0054] S3. Design the motion transmission path of the drive mechanism and calculate the maximum angle adjustment range that the drive mechanism can drive at each stage of adjustable guide vane assembly.

[0055] S4. Compare the maximum angle adjustment range with the target angle adjustment range; when the maximum angle adjustment range is different from the target angle adjustment range, optimize the design parameters of the drive mechanism to make the maximum angle adjustment range the same as the target angle adjustment range.

[0056] This embodiment effectively adapts to the usage requirements of aero-derivative gas turbines in low operating conditions. Through the coordinated adjustment of at least three stages of adjustable guide vane assemblies, and with the target angle adjustment range determined by the constraint of not lowering the surge boundary, it ensures that the compressor maintains stable aerodynamic performance at low loads, avoiding increased surge risk due to guide vane adjustment. At the same time, by optimizing the design parameters of the drive mechanism, the maximum angle adjustment range of the drive mechanism is precisely matched with the target angle adjustment range, realizing precise joint adjustment of each stage of guide vanes, and improving the reliability and effectiveness of guide vane adjustment.

[0057] In step S3, the maximum angle adjustment range of the adjustable guide vane assembly at each stage that the drive mechanism can drive is calculated, including the following steps: with the engine axis as the X-axis, a coordinate system is constructed according to the right-hand rule, and the length of the drive link 1, the length of the first connecting structure 15, the included angle of the control lever 2, the length of the second connecting structure 16, the length of the link of this stage, the radial position of the linkage ring lug 17, the radial position of the rocker arm mounting center of this stage, the initial angular position of the linkage ring lug 17, and the length parameters of the rocker arm of this stage are determined in sequence. The limit adjustment angles of the guide vane of this stage along two opposite directions are calculated respectively, and the sum of the two is the maximum angle adjustment range of the guide vane of this stage.

[0058] Taking the zero-stage guide vane as an example, in comparison Figure 4A brief explanation of each parameter is provided. A coordinate system is constructed using the engine axis as the X-axis and the right-hand rule. Figure 4 Point A is the initial position of the driving link, and α1 is the length of the driving link (see details). Figure 5 Point C is the center position of the joystick (see details). Figure 6 α2 is the length of the connection structure between the joystick and the drive linkage (see details). Figure 6 ), β1 is the joystick angle (see details) Figure 6 α3 is the length of the connection structure between the joystick and the zero-level linkage (see details). Figure 6 ), α4 is the length of the zero-order link (see details) Figure 7 ), α5 is the radial position of the linkage ring lug (see details) Figure 8 R1 is the radial position of the zero-level rocker arm mounting center (see details). Figure 8 ), β2 is the initial angular position of the linkage ring lug (see details) Figure 8 ), α6 is the length of the zero-level rocker arm (see details) Figure 9 Therefore, the adjustable angle of the zero-stage guide vane in one direction is β3°. Similarly, point B in the diagram represents the limit position of the drive linkage in a specific direction. According to the motion law, the adjustable angle of the zero-stage guide vane in another direction is β4°. In summary, the adjustable angle range of the zero-stage guide vane is (β3° + β4°). By adjusting the relevant dimensions of the control lever and the zero-stage linkage, different angle adjustment ranges of the zero-stage guide vane can be achieved.

[0059] In step S4, the design parameters of the drive mechanism are optimized, specifically including: optimizing the position and / or size parameters of at least one of the drive linkage 1, control lever 2, each stage of linkage assembly, linkage ring assembly or rocker arm assembly.

[0060] According to an embodiment of the present invention, in a third aspect, a guide vane adjustment method is provided, the method being based on a multi-stage coordinated guide vane device, comprising the following steps: At least three stages of adjustable guide vane assemblies are installed in the compressor. The guide vane angle of each stage of the adjustable guide vane assembly is adjusted simultaneously by the drive mechanism to match the airflow angle of attack at different speeds of the compressor, so that the airflow enters the corresponding next stage rotor at a preset angle; and the flow capacity and work capacity of each stage of the compressor are matched to widen the surge margin in the low operating condition range.

[0061] In some embodiments, the guide vane angle of each level of adjustable guide vane assembly is adjusted simultaneously by the drive mechanism, specifically including the following steps: the drive source outputs power to drive the control lever 2 to rotate through the drive linkage 1, the control lever 2 drives the corresponding linkage ring assembly to move circumferentially through the linkage assembly of each level, the linkage ring assembly of each level drives the corresponding rocker arm assembly to swing, and finally drives the guide vane 12 of the corresponding level to rotate around its own axis, thereby completing the angle adjustment.

[0062] Although embodiments of the 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 invention, and such modifications and variations all fall within the scope defined by the appended claims.

Claims

1. A multi-stage guide vane device, applied in an aero-engine compressor, characterized in that, include: At least three levels of adjustable guide vane assembly, each level of the adjustable guide vane assembly includes multiple guide vanes (12). The drive mechanism is connected to the adjustable guide vane assemblies of each stage for transmission. The drive mechanism is used to simultaneously adjust the guide vane (12) angle of each stage of the adjustable guide vane assemblies so that the surge boundary of the compressor in the low operating condition range is maintained within the preset threshold range.

2. The multi-stage coordinated guide vane device according to claim 1, characterized in that, The drive mechanism includes: The drive link (1) is connected to the drive source; The control lever (2) is hinged to the drive linkage (1) through the first connecting structure (15). The control lever (2) is parallel to the engine axis, and the end of the control lever (2) is rotatably mounted on the compressor housing (13). At least three-stage linkage ring assemblies are arranged linearly at intervals along the engine axis. Each stage of the linkage ring assemblies is hinged to the control lever (2) via a connecting rod assembly. Each stage of the linkage ring assemblies is provided with multiple rocker arm assemblies at intervals along the circumference. The rocker arm assemblies are connected to the guide vane (12).

3. The multi-stage coordinated guide vane device according to claim 2, characterized in that, Each of the guide vanes (12) is disposed inside the compressor housing (13), the drive mechanism is disposed outside the compressor housing (13), and the guide vanes (12) are rotatably disposed on the rocker arm assembly via a rotating shaft (14) passing through the compressor housing (13).

4. The multi-stage guide vane device according to claim 2, characterized in that, The linkage assembly includes a second connecting structure (16), a connecting rod, and a linkage lug (17). One end of the second connecting structure (16) is connected to the control lever (2), and the other end of the second connecting structure (16) is hinged to the connecting rod. The end of the connecting rod away from the second connecting structure (16) is hinged to the linkage lug (17), and the linkage lug (17) is disposed on the linkage assembly.

5. The multi-stage guide vane device according to claim 2, characterized in that, The adjustable guide vane assembly is provided with three levels: a zero-level adjustable guide vane assembly, a first-level adjustable guide vane assembly, and a second-level adjustable guide vane assembly. The zero-level adjustable guide vane assembly includes multiple zero-level guide vanes, the first-level adjustable guide vane assembly includes multiple first-level guide vanes, and the second-level adjustable guide vane assembly includes multiple second-level guide vanes. The linkage ring assembly is configured with three levels, namely the zero-level linkage ring assembly (6), the first-level linkage ring assembly (8), and the second-level linkage ring assembly (10). The rocker arm assembly is provided with three levels, namely the zero-level rocker arm (7), the first-level rocker arm (9) and the second-level rocker arm (11). The zero-stage guide vane is rotatably mounted on the zero-stage rocker arm (7), which is hinged to the zero-stage linkage ring assembly (6). The first-stage guide vane is rotatably mounted on the first-stage rocker arm (9), which is hinged to the first-stage linkage ring assembly (8). The second-stage guide vane is rotatably mounted on the second-stage rocker arm (11), which is hinged to the second-stage linkage ring assembly (10).

6. A design method for a multi-stage coordinated guide vane device, characterized in that, The method described is a design method for the multi-stage coordinated guide vane device according to any one of claims 1-5, comprising the following steps: S1. To meet the usage requirements of gas turbines in the low operating range, the compressor guide vanes are configured as at least three-stage adjustable guide vane assemblies; S2. Determine the target angle adjustment range for each stage of the adjustable guide vane assembly, taking the constraint that the compressor's low-condition surge boundary does not decrease; S3. Design the motion transmission path of the drive mechanism and calculate the maximum angle adjustment range that the drive mechanism can drive at each stage of adjustable guide vane assembly; S4. Compare the maximum angle adjustment range with the target angle adjustment range; when the maximum angle adjustment range is different from the target angle adjustment range, optimize the design parameters of the drive mechanism to make the maximum angle adjustment range the same as the target angle adjustment range.

7. The design method of the multi-stage coordinated guide vane device according to claim 6, characterized in that, In step S3, the maximum angle adjustment range that the drive mechanism can drive at each stage of the adjustable guide vane assembly is calculated, including the following steps: Using the engine axis as the X-axis, a coordinate system is constructed according to the right-hand rule. The length of the drive link (1), the length of the first connecting structure (15), the control lever angle, the length of the second connecting structure (16), the length of the link in this stage, the radial position of the linkage lug (17), the radial position of the rocker arm mounting center, the initial angular position of the linkage lug (17), and the rocker arm length parameters are determined in sequence. The limit adjustment angles of the guide vane in two opposite directions are calculated respectively, and the sum of the two is the maximum angle adjustment range of the guide vane.

8. The design method of the multi-stage coordinated guide vane device according to claim 6, characterized in that, In step S4, the design parameters of the drive mechanism are optimized, specifically including: optimizing the position and / or size parameters of at least one of the drive linkage (1), control lever (2), linkage assembly at each stage, linkage ring assembly or rocker arm assembly.

9. A guide vane adjustment method, characterized in that, The method is based on the multi-stage coordinated guide vane device according to any one of claims 1-5, and includes the following steps: At least three stages of adjustable guide vane assemblies are installed in the compressor. The guide vane angle of each stage of the adjustable guide vane assembly is adjusted simultaneously by the drive mechanism to match the airflow angle of attack at different speeds of the compressor, so that the airflow enters the corresponding next stage rotor at a preset angle; and the flow capacity and work capacity of each stage of the compressor are matched to widen the surge margin in the low operating condition range.

10. The guide vane adjustment method according to claim 9, characterized in that, The guide vane angles of each adjustable guide vane assembly are adjusted simultaneously via a drive mechanism, specifically including the following steps: The power output from the drive source drives the control lever (2) to rotate through the drive linkage (1). The control lever (2) drives the corresponding linkage ring assembly to move circumferentially through the linkage assembly at each level. The linkage ring assembly at each level drives the corresponding rocker arm assembly to swing, and finally drives the guide vane (12) of the corresponding level to rotate around its own axis to complete the angle adjustment.

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