Variable geometry turbine guide vane with adjustable vane thickness and design method and application thereof

Abstract

The invention relates to a variable geometry turbine guide vane with adjustable blade thickness and a design method and application thereof, the variable geometry turbine guide vane comprises an adjustable guide vane and a fixed impeller matched with the adjustable guide vane, the adjustable guide vane comprises a guide vane body with an adjustable suction surface, and the guide vane body is composed of a fixed pressure surface and a sectional suction surface. And the sectional suction surface is divided into an upstream adjustable suction surface and a downstream fixed suction surface. According to the variable-thickness guide vane, by finely adjusting the thickness of the guide vane, the flow characteristic of airflow can be more accurately controlled, the performance of an engine is optimized, the variable-thickness guide vane adapts to different flight states and load changes, and the fuel efficiency and thrust are improved. In addition, the variable-thickness guide vane can reduce airflow loss, and efficient airflow flowing is kept.

Description

Technical Field

[0001] The present invention belongs to the technical field of aero-engine turbine propulsion, and in particular relates to a variable-geometry turbine guide vane with adjustable blade thickness, a design method thereof, and an application thereof. Background Art

[0002] Adaptive cycle engines are widely considered the next major advancement in jet engine technology. This innovative technology aims to dynamically adjust the engine's operating mode based on flight conditions and mission requirements to achieve greater fuel efficiency and performance. The research and development of adaptive cycle engines is particularly important given the increasing pressure on the aviation industry from increasingly stringent environmental regulations and fuel costs.

[0003] With the continuous advancement of aviation engine technology, improving engine performance, efficiency and adaptability has become a research focus. Especially in turbine engines, how to accurately control the flow and distribution of airflow is the key to ensuring efficient operation of the engine. Although traditional fixed geometry guide vanes can effectively control airflow under certain working conditions, their adjustment capabilities are limited under high load, variable working conditions and different flight conditions. In order to solve this problem, designers have developed variable geometry guide vane technology. Figure 1 As shown, it demonstrates the variable geometry guide vane technology in the prior art, which controls the airflow regulation by changing the throat area and the angle of attack through the overall rotation of the guide vane around the axis.

[0004] Even so, the adjustable guide vane technology still has limited adjustment capabilities. To address this issue, variable thickness guide vane technology has emerged. By varying the thickness of turbine engine guide vanes, the dynamic characteristics of the airflow can be more flexibly controlled. Variable thickness guide vanes not only optimize the airflow velocity, pressure distribution, and flow rate, but also adjust the airflow path in real time as the engine load changes, thereby improving the engine's thrust, fuel efficiency, and operating stability.

[0005] In addition, with the application of computational fluid dynamics (CFD) technology and advanced materials, the control method of guide vane thickness changes has become more precise and efficient, further enhancing the application prospects of variable thickness guide vanes. Compared with traditional variable geometry guide vane technology, thickness variation can provide more precise flow regulation. Therefore, in the design of modern high-performance turbine engines, it has become an important technical solution for improving the overall performance and adaptability of the engine. However, the existing thickness variation design control method is complex and unreliable. In addition, the overall change of the suction surface leads to imprecise airflow control and cannot adapt to various operating conditions. Summary of the Invention

[0006] In order to overcome the above-mentioned deficiencies of the prior art, the present invention provides a variable geometry turbine guide vane with adjustable blade thickness, and a design method and application thereof.

[0007] The technical solution adopted by the present invention to solve its technical problems is: A variable geometry turbine guide vane with adjustable blade thickness, comprising a guide vane body with an adjustable suction surface, wherein the guide vane body is composed of a fixed pressure surface and a segmented suction surface, wherein the segmented suction surface is divided into an upstream adjustable suction surface and a downstream fixed suction surface; The tail end of the adjustable suction surface is hinged to the guide vane body through a hinged rotation axis, and the hinged rotation axis is parallel to the span direction of the guide vane; the front end of the adjustable suction surface is plugged into the front end of the fixed pressure surface through a mortise and tenon structure; A guide vane cavity is provided inside the guide vane, and a thickness adjustment mechanism is provided in the guide vane cavity; the thickness adjustment mechanism includes an actuator, a transmission assembly, a rotating drive shaft, a connecting rod mechanism, and a rotating support shaft; wherein the rotating drive shaft extends along the span of the guide vane and is provided on the inner wall of the cavity corresponding to the fixed pressure surface via a hinge seat; the rotating drive shaft is hinged to the rotating support shaft via the connecting rod mechanism; and the rotating support shaft is provided on the inner wall of the cavity corresponding to the adjustable suction surface via a hinge seat; The rotating drive shaft is connected to the actuator through a transmission assembly; the rotating drive shaft is arranged parallel to the articulated rotating shaft; the actuator drives the rotating drive shaft to rotate according to the engine operating condition control signal, and the rotating drive shaft is linked with the connecting rod mechanism through the guide vane, so that the angle of the adjustable suction surface is adjusted around the articulated rotating shaft; during the adjustment process, the mortise and tenon structure at the front end of the adjustable suction surface is displaced along the fixed pressure surface, and at the same time, the tail end of the adjustable suction surface maintains cooperation with the downstream fixed suction surface; when the adjustable suction surface is deflected to the set angle, its leading edge forms an aerodynamic seal with the sealing structure of the fixed impeller.

[0008] In addition, the present invention also provides a design method for variable geometry turbine guide vanes with adjustable blade thickness, which uses the above-mentioned adjustable guide vanes to control the thickness and installation angle of the adjustable guide vanes according to different stages.

[0009] In addition, the present invention also provides a variable geometry turbine for a variable cycle aircraft engine, comprising the above-mentioned adjustable guide vanes and a fixed impeller coordinated therewith.

[0010] In addition, the present invention also provides an adaptive variable cycle engine, including the variable geometry turbine.

[0011] The advantages of the present invention compared with the prior art are: (1) Compared with the whole blade adjustable technology, variable thickness guide vane technology has significant advantages in airflow control accuracy, adaptability and efficiency. By finely adjusting the thickness of the guide vane, the variable thickness guide vane can more accurately control the flow characteristics of the airflow, optimize engine performance, adapt to different flight conditions and load changes, and improve fuel efficiency and thrust. In addition, variable thickness guide vanes can reduce airflow losses and maintain efficient airflow, while the adjustment of the whole blade angle may cause local airflow losses. Therefore, variable thickness guide vanes are more suitable for situations where high engine performance requirements are required.

[0012] (2) The present invention can significantly improve the efficiency, adaptability, and stability of aircraft engines, optimize fuel use, increase thrust output, and have a positive impact on the long-term reliability of the engine. It enables the engine to maintain optimal operating conditions under various flight conditions while reducing fuel consumption, noise, and emissions, thus providing significant economic benefits and environmental advantages.

[0013] (3) The design method of the adjustable guide vane of the present invention realizes the dynamic coupling control of the guide vane thickness and the installation angle through a multi-modal collaborative adjustment strategy. Based on the parameter adaptive algorithm of flight phase identification, a closed-loop control system is constructed in combination with real-time deformation feedback. It can complete the three-dimensional thickness gradient distribution optimization and aerodynamic attack angle matching within a millisecond response cycle, so that the guide vane geometric parameters are dynamically adapted to the real-time flow field. This control mechanism effectively reduces the fluctuation amplitude of turbine efficiency by suppressing the shock wave-boundary layer interference effect, breaking through the phase lag bottleneck of traditional mechanical adjustment, and realizing aeroelastic stability control under full-envelope flight conditions. BRIEF DESCRIPTION OF THE DRAWINGS

[0014] Figure 1 Schematic diagram of adjustment of an existing aircraft engine turbine with adjustable guide vanes, where (a) is before adjustment and (b) is after adjustment; Figure 2 A top view of a variable geometry turbine guide vane with adjustable blade thickness according to the present invention; Figure 3 Schematic diagram of the transmission mechanism of the variable geometry turbine guide vane with adjustable blade thickness of the present invention; Figure 4 This is a schematic diagram of the slot structure of the variable geometry turbine guide vane with adjustable blade thickness according to the present invention; Figure 5 This is a comparison diagram of the variable-geometry turbine guide vane with adjustable blade thickness of the present invention in its initial state and after thickness is changed.

[0015] Description of reference numerals: 1: Adjustable suction surface; 2: Rotating support shaft; 3: Fixed pressure surface; 4: Articulated shaft; 5: Connecting rod mechanism; 6: Blade cavity; 7: Articulated rotating shaft; 8: Rotating active shaft; 9: Insert block, 10: Slot. DETAILED DESCRIPTION

[0016] In order to make the purpose, technical solutions and advantages of the implementation of the present invention clearer, the technical solutions in the embodiments of the present invention will be described in more detail below in conjunction with the drawings in the embodiments of the present invention. In the drawings, the same or similar reference numerals throughout represent the same or similar elements or elements with the same or similar functions. The described embodiments are part of the embodiments of the present invention, not all of the embodiments. The embodiments described below with reference to the drawings are exemplary and are intended to be used to explain the present invention, and should not be understood as limiting the present invention. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without creative work are within the scope of protection of the present invention. The structure and technical solutions of the present invention are further described in detail below in conjunction with the drawings, and an embodiment of the present invention is given.

[0017] Example 1: Adjustable guide vanes like Figures 2 to 5 As shown, the variable geometry turbine guide vane with adjustable blade thickness provided in an embodiment of the present invention includes a guide vane body with an adjustable suction surface, wherein the guide vane body is composed of a fixed pressure surface 3 and a segmented suction surface, and the segmented suction surface is divided into an upstream adjustable suction surface 1 and a downstream fixed suction surface; the tail end of the adjustable suction surface 1 is hinged to the guide vane body through an articulated rotation axis 7, and the articulated rotation axis is parallel to the span direction of the guide vane; the front end of the adjustable suction surface 1 is plugged into the front end of the fixed pressure surface 3 through a mortise and tenon structure.

[0018] A guide vane cavity 6 is provided inside the guide vane, and a thickness adjustment mechanism is provided in the guide vane cavity 6; the thickness adjustment mechanism includes an actuator, a transmission assembly, a rotary drive shaft 8, a connecting rod mechanism, and a rotary support shaft 2; wherein the rotary drive shaft 8 extends along the span direction of the guide vane and is arranged on the inner wall of the cavity corresponding to the fixed pressure surface via a hinge seat; the rotary drive shaft 8 is hinged to the rotary support shaft 2 via a connecting rod mechanism 5; the rotary support shaft 2 is arranged on the inner wall of the cavity corresponding to the adjustable suction surface 1 via a hinge seat; the rotary drive shaft 8 is connected to the actuator via a transmission assembly; The rotating active shaft 8 is arranged parallel to the articulated rotating shaft 7; the actuator drives the rotating active shaft 8 to rotate according to the engine operating condition control signal, and the angle of the adjustable suction surface 1 is adjusted around the articulated rotating shaft 7 through the linkage of the guide vane rotating active shaft 2 and the connecting rod mechanism 5; during the adjustment process, the mortise and tenon structure at the front end of the adjustable suction surface 1 is displaced along the fixed pressure surface 3, and at the same time, the tail end of the adjustable suction surface maintains cooperation with the downstream fixed suction surface; when the adjustable suction surface is deflected to the set angle, its leading edge forms an aerodynamic seal with the sealing structure of the fixed impeller.

[0019] In a preferred embodiment, the adjustment area of the adjustable suction surface 1 covers the area from the leading edge of the guide vane to 50%-70% of the chord length, and its rotation axis is located in the guide vane cavity 6 at a position 1 / 3 of the chord length from the trailing edge. The transmission assembly is preferably a worm gear assembly, the actuator drives the worm to rotate, the worm drives the worm wheel to rotate, the worm wheel shaft is provided with an active bevel gear, the active bevel gear is engaged with the passive bevel gear of the rotating active shaft 8, thereby driving the rotation of the rotating active shaft 8. The connecting rod mechanism 5 preferably includes a pressure surface connecting rod and a suction surface connecting rod hinged to each other through a hinge shaft 4, wherein the pressure surface connecting rod is hinged to the rotating support shaft 2, and the suction surface connecting rod is hinged to the rotating active shaft 8. The front end of the adjustable suction surface 1 is provided with an insert 9, and the front end of the fixed pressure surface 3 is provided with a slot 10, and the insert 9 and the slot 10 form a mortise and tenon structure.

[0020] In a preferred embodiment, the contact surface between the insert 9 and the slot 10 is coated with a molybdenum disulfide solid lubricant coating, and the inner wall of the slot 10 is arranged with a honeycomb damping structure. A piezoelectric ceramic sensor array is embedded in the inner wall of the adjustable suction surface 1. This sensor array is connected to a closed-loop control module via a signal line, providing real-time feedback on the suction surface deformation and correcting the deflection angle.

[0021] There is a cavity in the middle of the guide vane, the suction surface is a partially adjustable structure, and the downstream of the guide vane suction surface and the pressure surface are fixed structures. The adjustable part of the suction surface has a hinge structure, which is connected to the rotating shaft in the middle. The adjustable suction surface and the fixed part are connected by a structure similar to a mortise and tenon. The rotation of the suction surface is achieved by the main shaft 7 driving the central rotating shaft 5 of the guide vane, and then pushing the adjustable suction surface through the connecting rod 4 and the hinge structure. That is, the thickness adjustment of the guide vane is achieved by rotating the variable suction surface at a small angle around the rotating shaft 7. After the maximum thickness of the guide vane changes, the aerodynamic characteristics near the blade can be more accurately controlled.

[0022] The guide vanes adopt a cavity design, which effectively reduces the weight of the guide vanes and the overall weight of the engine while ensuring sufficient structural strength and rigidity. At the same time, it provides space for the arrangement of components such as the drive mechanism inside the cavity, making the design more compact and reasonable. At the same time, the partially adjustable design of the suction surface allows the guide vanes to adjust their thickness in specific areas (such as 50%-70% of the chord length from the leading edge). This local adjustment method is more precise than the overall blade angle adjustment and can more accurately control the flow characteristics of the airflow, such as speed and pressure distribution, thereby optimizing the engine's performance under different operating conditions and better adapting to changes in flight conditions and loads.

[0023] In addition, the downstream and pressure surfaces of the suction surface utilize a fixed structure, providing stable support and a reference for the adjustable suction surface. This ensures the overall stability of the guide vane during adjustment, avoids problems such as excessive deformation or vibration that would result from an adjustable entire guide vane structure, and improves the reliability and service life of the guide vane. Furthermore, the adjustable suction surface and the fixed portion are connected via a mortise and tenon-like structure. This simple and reliable mechanical connection maintains a tight fit between the two during adjustment, effectively preventing airflow leakage and ensuring a tight seal in the airflow channel, thereby maintaining efficient engine operation. Furthermore, the front-end insert and slot, along with the molybdenum disulfide solid lubricant coating and honeycomb damping structure, further enhance the reliability and wear resistance of the connection and reduce the adverse effects of friction and vibration. Finally, a hinge structure is connected to the central rotating shaft, allowing the adjustable suction surface to rotate and adjust within a certain angle around the rotating axis. The rotating axis is located one-third of the chord length from the trailing edge. This layout and adjustment method achieves a suitable adjustment range, allowing the guide vane thickness to vary to meet the precise airflow control requirements of the engine in different operating modes, enhancing the engine's adaptability and flexibility.

[0024] The adjustable guide vanes in this embodiment help reduce the load on the turbine and improve the overall working balance of the engine, thereby improving efficiency by precisely controlling the pressure, velocity, and temperature distribution of the airflow. In addition, in high-temperature, high-pressure working environments, adjustment of the guide vane thickness can also effectively avoid airflow separation and vortex formation, thereby improving the stability and long-term operating performance of the engine.

[0025] Example 2: Design method Based on Example 1, the present invention further provides a design method for the variable-geometry turbine guide vanes with adjustable blade thickness, wherein the thickness and installation angle of the adjustable guide vanes are controlled according to different stages. The implementation of the design method mainly includes the following steps: (1) During takeoff, when the engine enters a high-thrust, high-load operating condition, the thickness of the turbine guide vanes is increased and their installation angle is adjusted so that the thickened blades can enhance the airflow capture capability. At the same time, the angle adjustment is used to maintain stable turbine operation. (2) During the cruise phase, when the engine is under medium thrust and low load conditions, the thickness of the turbine guide vanes is reduced and their installation angle is optimized so that the thinned blades can reduce aerodynamic drag and the angle is adjusted to adapt to a stable airflow environment. (3) During the descent phase, when the engine enters a low-thrust, low-load operating condition, the thickness of the turbine guide vanes is further reduced and their installation angle is adjusted simultaneously so that the thinned blades match the reduced airflow pressure and maintain fuel economy; (4) During the acceleration phase, when the engine thrust demand increases, the thickness of the turbine guide vanes is dynamically increased and their installation angle is corrected so that the thickened blades can withstand the increased airflow pressure. At the same time, the high-load operating efficiency is maintained through angle correction. (5) During high-speed flight, when the aircraft enters a high Mach number state, the thin design of the turbine guide vanes is maintained and their installation angle is optimized so that the thin blades can reduce interference with high-speed airflow and improve energy conversion efficiency; (6) During stall and extreme operating conditions, the abnormal airflow state is detected through the real-time monitoring system, and the thickness gradient distribution and three-dimensional installation angle of the turbine guide vanes are automatically adjusted to suppress airflow separation and maintain the structural integrity of the blades.

[0026] For the high-thrust, high-load environment during takeoff: During takeoff, the aircraft demands maximum engine thrust, placing a high load on the engine. Airflow and pressure are high, forcing the engine to cope with a heavy workload. During this phase, the thickness of the variable-geometry turbine is increased to cope with the high load and pressure. The thickened blades enhance the efficiency of airflow capture and conversion, thereby increasing thrust output. The blade angle may also be adjusted to ensure stable turbine operation.

[0027] For moderate thrust and low-load operating conditions during cruise: During cruise, the aircraft's thrust demand is low, engine load is reduced, and airflow is high and stable. During this phase, the thickness of the variable-geometry turbine is reduced to reduce aerodynamic drag and improve fuel efficiency. The blade angle is also adjusted to better suit the lower load environment. By reducing the thickness and adjusting the angle, the turbine minimizes energy loss and improves efficiency.

[0028] Designed for low-thrust, low-load environments during descent: During descent, engine load and airflow pressure are lower, further reducing thrust demand. During this phase, the thickness of the variable-geometry turbine continues to decrease to optimize fuel economy and reduce unnecessary power consumption. The blade angle is also adjusted accordingly to better cope with lower loads and airflow, maintaining stability and efficiency.

[0029] To increase thrust during acceleration and operate in higher-load environments: During acceleration, the engine demands greater thrust, increasing load and airflow pressure. During this period, the thickness of the variable-geometry turbine blades is increased to cope with these high-load operating conditions. Thicker turbine blades better withstand airflow pressure and increased load, increasing thrust output. The angle of the variable-geometry turbine blades is adjusted accordingly to ensure efficient operation under higher loads.

[0030] Designed for high thrust and high-speed operating environments during high-speed flight: At high speeds, the aircraft's speed is extremely high, and the airflow through the turbine is also very fast, creating a more complex operating environment. During this phase, the variable geometry turbine is reduced and maintained to a thinner size to reduce aerodynamic drag and improve efficiency. Thinner blades help minimize airflow disturbances, maximizing the turbine's energy conversion efficiency.

[0031] Designed for stall and extreme operating conditions: During stall and extreme operating conditions, the turbine faces high loads and complex airflow conditions. During these conditions, the variable-geometry turbine adjusts its thickness and angle to prevent airflow separation or stall. Through an automated control system, the turbine blade geometry can be adjusted in real time to ensure stable engine operation under extreme loads.

[0032] Example 3: Variable Cycle Aeroengine and Variable Geometry Turbine The present invention further provides a variable geometry turbine for a variable cycle aircraft engine, comprising the above-mentioned adjustable guide vanes and a fixed impeller matched therewith. Furthermore, the present invention provides an adaptive variable cycle engine, comprising a variable geometry turbine.

[0033] In an embodiment of the present invention, the coordination of adjustable guide vanes and fixed impellers enables precise control of the airflow. Adjustable guide vanes alter the flow state of the airflow within the guide vane channel by adjusting their thickness, directly affecting the velocity, pressure, and temperature distribution of the airflow. The fixed impeller provides a stable outlet for the airflow, optimally directing the airflow adjusted by the adjustable guide vanes to the next-stage turbine impeller. This coordination makes the airflow within the turbine smoother and more efficient, reducing airflow turbulence and losses. For example, under high-load conditions, the adjustable guide vanes reduce their thickness, increase the airflow channel area, reduce airflow velocity, and reduce impact on the turbine impeller; under low-load conditions, the adjustable guide vanes increase their thickness, reduce the airflow channel area, increase airflow velocity, and increase pressure energy. Through this precise airflow control, the engine achieves optimal performance under different operating conditions, improving fuel efficiency, reducing emissions, and increasing thrust output.

[0034] Furthermore, the coordination of the adjustable guide vanes and the fixed impeller enhances engine operational stability and reliability. The fixed impeller provides stable support for the adjustable guide vanes, preventing excessive deformation or vibration during adjustment. Adjustment of the adjustable guide vane thickness is performed in conjunction with the fixed impeller, with the adjustment range and angle limited and guided by the fixed impeller, ensuring smooth and accurate operation. This coordination significantly improves the engine's fuel efficiency and thrust output. Precise control of the adjustable guide vane thickness optimizes the flow characteristics within the turbine and enhances turbine efficiency. Under high-load conditions, the adjustable guide vanes are adjusted to the appropriate position, increasing the pressure energy of the airflow, enabling the turbine to extract more energy, boosting output power, and increasing thrust. Under low-load conditions, the adjustable guide vanes are reduced in thickness, reducing air velocity and impact on the turbine impeller, improving isentropic efficiency, and reducing fuel consumption. The fixed impeller ensures stable transmission of the adjusted airflow, ensuring optimal airflow into the next-stage turbine impeller, further enhancing turbine system efficiency.

[0035] The above embodiments fully and effectively achieve the objectives of the present invention. Those skilled in the art will appreciate that the present invention includes, but is not limited to, the contents described in the accompanying drawings and the above specific embodiments. Although the present invention has been described with reference to the embodiments currently considered to be the most practical and preferred, it should be understood that the present invention is not limited to the disclosed embodiments, and any modifications that do not deviate from the functional and structural principles of the present invention are intended to be included within the scope of the claims.

Claims

1. A variable geometry turbine guide vane with adjustable blade thickness, characterized in that: It comprises a guide vane body with an adjustable suction surface, wherein the guide vane body is composed of a fixed pressure surface (3) and a segmented suction surface, wherein the segmented suction surface is divided into an upstream adjustable suction surface (1) and a downstream fixed suction surface; The tail end of the adjustable suction surface (1) is hinged to the guide vane body via a hinged rotation axis (7), and the hinged rotation axis is parallel to the guide vane span direction; the front end of the adjustable suction surface (1) is plugged into the front end of the fixed pressure surface (3) via a mortise and tenon structure; A guide vane cavity (6) is provided inside the guide vane, and a thickness adjustment mechanism is provided in the guide vane cavity (6); the thickness adjustment mechanism comprises an actuator, a transmission assembly, a rotating driving shaft (8), a connecting rod mechanism (5), and a rotating support shaft (2); wherein the rotating driving shaft (8) extends along the span direction of the guide vane and is arranged on the inner wall of the cavity corresponding to the fixed pressure surface through a hinge seat, the rotating driving shaft (8) is hinged to the rotating support shaft (2) through the connecting rod mechanism (5), and the rotating support shaft (2) is arranged on the inner wall of the cavity corresponding to the adjustable suction surface (1) through a hinge seat; The rotating driving shaft (8) is connected to the actuator through a transmission assembly; the rotating driving shaft (8) is arranged parallel to the articulated rotating shaft (7); the actuator drives the rotating driving shaft (8) to rotate according to the engine working condition control signal, and the rotating driving shaft (8) is linked with the connecting rod mechanism (5) through the guide vane, so that the adjustable suction surface (1) is adjusted in angle around the articulated rotating shaft (7); during the adjustment process, the mortise and tenon structure at the front end of the adjustable suction surface (1) is displaced along the fixed pressure surface (3), and at the same time, the tail end of the adjustable suction surface is kept in cooperation with the downstream fixed suction surface; when the adjustable suction surface is deflected to a set angle, its leading edge forms an aerodynamic seal with the sealing structure of the fixed impeller.

2. The variable geometry turbine guide vane with adjustable blade thickness according to claim 1, characterized in that: The adjustable suction surface (1) has an adjustment area covering the guide vane leading edge to 50%-70% of the chord length, and its rotation axis is located in the guide vane cavity (6) at a position 1 / 3 of the chord length from the trailing edge.

3. The variable geometry turbine guide vane with adjustable blade thickness according to claim 1, characterized in that: The front end of the adjustable suction surface (1) is provided with an insert block (9), and the front end of the fixed pressure surface (3) is provided with a slot (10), and the insert block (9) and the slot (10) form the mortise and tenon structure.

4. The variable geometry turbine guide vane with adjustable blade thickness according to claim 3, characterized in that: The contact surface between the insert (9) and the slot (10) is provided with a molybdenum disulfide solid lubricating coating, and the inner wall of the slot (10) is arranged with a honeycomb damping structure.

5. The variable geometry turbine guide vane with adjustable blade thickness according to claim 1, characterized in that: The inner wall of the adjustable suction surface (1) is embedded with a piezoelectric ceramic sensor array, which is connected to a closed-loop control module via a signal line, and provides real-time feedback on the deformation of the suction surface and corrects the deflection angle.

6. The variable geometry turbine guide vane with adjustable blade thickness according to claim 1, characterized in that: The transmission assembly is a worm gear assembly, the actuator drives the worm to rotate, the worm drives the worm wheel to rotate, the worm wheel shaft is provided with an active bevel gear, the active bevel gear is engaged with the passive bevel gear of the rotating active shaft (8), thereby driving the rotation of the rotating active shaft (8).

7. The variable geometry turbine guide vane with adjustable blade thickness according to claim 1, characterized in that: The connecting rod mechanism (5) comprises a pressure surface connecting rod and a suction surface connecting rod hinged to each other via a hinge shaft (4), wherein the pressure surface connecting rod is hinged to the rotation support shaft (2), and the suction surface connecting rod is hinged to the rotation drive shaft (8).

8. A method for designing variable geometry turbine guide vanes with adjustable blade thickness, characterized in that: Based on the variable geometry turbine guide vane with adjustable blade thickness according to any one of claims 1 to 7, the thickness and installation angle of the adjustable guide vane are controlled according to different stages, and the method includes: (1) During takeoff, when the engine enters a high-thrust, high-load operating condition, the thickness of the turbine guide vanes is increased and their installation angle is adjusted so that the thickened blades can enhance the airflow capture capability. At the same time, the angle adjustment is used to maintain stable turbine operation. (2) During the cruise phase, when the engine is under medium thrust and low load conditions, the thickness of the turbine guide vanes is reduced and their installation angle is optimized so that the thinned blades can reduce aerodynamic drag and the angle is adjusted to adapt to a stable airflow environment. (3) During the descent phase, when the engine enters a low-thrust, low-load operating condition, the thickness of the turbine guide vanes is further reduced and their installation angle is adjusted simultaneously so that the thinned blades match the reduced airflow pressure and maintain fuel economy; (4) During the acceleration phase, when the engine thrust demand increases, the thickness of the turbine guide vanes is dynamically increased and their installation angle is corrected so that the thickened blades can withstand the increased airflow pressure. At the same time, the high-load operating efficiency is maintained through angle correction. (5) During high-speed flight, when the aircraft enters a high Mach number state, the thin design of the turbine guide vanes is maintained and their installation angle is optimized so that the thin blades can reduce interference with high-speed airflow and improve energy conversion efficiency; (6) During stall and extreme operating conditions, the abnormal airflow state is detected through the real-time monitoring system, and the thickness gradient distribution and three-dimensional installation angle of the turbine guide vanes are automatically adjusted to suppress airflow separation and maintain the structural integrity of the blades.

9. A variable geometry turbine for a variable cycle aircraft engine, characterized in that: The invention comprises a variable-geometry turbine guide vane with adjustable blade thickness as claimed in any one of claims 1 to 7, and a fixed impeller matched therewith.

10. An adaptive variable cycle engine, characterized in that: Including the variable geometry turbine of the variable cycle aircraft engine as described in claim 9.

Images