Environmentally responsive aeroengine flexible blade and method of controlling the same

Abstract

This invention belongs to the aerospace field, specifically disclosing an environmentally responsive flexible blade for aero-engines and its control method, aiming to solve the problem of inflection points easily occurring during the bending process of existing flexible blades. The flexible blade is connected and supported by a first and second wave rope to the blade skin, and simultaneously connected to the apex of their respective first and second arched rope segments by a first and second linear rope, respectively. A drive mechanism controls the tension and slack of the first and second linear ropes, allowing the flexible blade to bend smoothly upwards or downwards. This flexible blade and its control method can quickly respond to the blade's operating environment, ensuring the flexible blade is always in a safe operating state, which is beneficial for effectively improving the working efficiency of aero-engines.

Description

Technical Field

[0001] This invention belongs to the field of aerospace, specifically relating to an environmentally responsive flexible blade for aero-engines and its control method. Background Technology

[0002] Flexible blades for aero-engines possess superior strength and stability compared to traditional rigid blades. They can eliminate resonance and instability through deformation and vibration, improving the efficiency, performance, lifespan, stability, and reliability of aero-engines while reducing noise and vibration. In the aerospace field, flexible blades offer significant advantages for aero-engines. However, most current flexible blades exhibit inflection points during bending, specifically abrupt turns or discontinuous changes, which significantly reduce their lifespan and efficiency. Furthermore, existing flexible blades also suffer from slow response and incomplete bending in terms of controllable bending. Summary of the Invention

[0003] This invention provides an environmentally responsive flexible blade for aero-engines, aiming to solve the problem that existing flexible blades are prone to inflection points during bending.

[0004] The technical solution adopted by the present invention to solve its technical problem is: an environmentally responsive flexible blade for aero-engines, including blade skin, blade truss and drive mechanism;

[0005] The blade skin is an airfoil structure, which includes a first skin and a second skin that are smoothly connected at their front ends; a blade cavity is formed between the first skin and the second skin.

[0006] The blade truss is disposed in the blade cavity;

[0007] The blade truss includes a fixing rod and a rope frame mechanism;

[0008] The fixing rod is hinged to the front end of the blade cavity;

[0009] The rope frame mechanism includes a first wave rope, a first linear rope, a second wave rope, and a second linear rope, all of which are rigid ropes with reversible deformation capabilities.

[0010] The first wave rope is composed of at least two first arched rope segments connected in sequence, with the first arched rope segments protruding toward the second skin; the front end of the first wave rope is connected to a fixed rod, and the connection points of each first arched rope segment and the rear end of the first wave rope are movably connected to the first skin through a first support rod.

[0011] The first linear rope is connected to the top of each first arched rope segment, and the front end of the first linear rope is connected to the front end of the first wave rope and / or the fixed rod.

[0012] The second wave rope is composed of at least two second arched rope segments connected in sequence, with the second arched rope segments protruding towards the first skin; the front end of the second wave rope is connected to a fixed rod, and the connection points of each second arched rope segment and the rear end of the second wave rope are movably connected to the second skin through a second support rod.

[0013] The second linear rope corresponds to the first linear rope and is connected to the top of each second arched rope segment, and the front end of the second linear rope is connected to the front end of the second wave rope and / or the fixed rod.

[0014] The drive mechanism is connected to the rear end of the first linear rope and the rear end of the second linear rope respectively; the drive mechanism can pull the first linear rope and relax the second linear rope to make the flexible blade change to an upward bending state, and can pull the second linear rope and relax the first linear rope to make the flexible blade change to a downward bending state.

[0015] Furthermore, a clamping member is provided at the front end of the blade cavity, and the fixing rod is hinged to the clamping member.

[0016] Furthermore, there are at least two rope frame mechanisms, which are spaced apart along the width direction of the blade cavity.

[0017] Furthermore, the drive mechanism includes a rotating rod and a servo motor;

[0018] The rotating rod is rotatably disposed at the rear end of the blade cavity, and has a swingable first connecting part and a second connecting part, wherein the first connecting part and the second connecting part swing in opposite directions during the rotation of the rotating rod;

[0019] The rear end of the first linear rope is movably connected to the first connecting part via a first connecting rod;

[0020] The rear end of the second linear rope is movably connected to the second connecting part via a second connecting rod;

[0021] The servo motor is connected to the rotating rod and can drive the rotating rod to rotate back and forth.

[0022] Furthermore, the first connecting part is a perforated boss located on the upper side of the rotating rod;

[0023] The second connecting part is a perforated boss located on the underside of the rotating rod;

[0024] The rear end of the first link is hinged to the first connecting part via a link pin;

[0025] The rear end of the second link is hinged to the second connecting part via a link pin.

[0026] The present invention also provides a control method for an environmentally responsive aero-engine flexible blade, wherein the flexible blade is controlled by a control system, and the flexible blade is the aforementioned environmentally responsive aero-engine flexible blade.

[0027] The control method includes:

[0028] Preset the initial values ​​for duct wind speed and rotor speed;

[0029] Preset the initial blade angle value for the flexible blades;

[0030] The main data of the duct is monitored in real time and transmitted back to the control system to calculate the most suitable blade angle and direction.

[0031] Determine whether the difference between the initial blade angle value and the optimal blade angle value is within the allowable range of blade angle difference;

[0032] If not, the difference is converted into the angle and direction that the servo needs to rotate, and then used to generate commands to control the servo.

[0033] Furthermore, the control method also includes:

[0034] Real-time monitoring of relevant parameters of the flexible blades and transmission of data back to the control system;

[0035] Determine whether the relevant parameters of the monitored flexible blades exceed the preset safety range;

[0036] If the limit is exceeded, an alarm will be triggered, and the servo motor will be controlled to operate via a preset safety adjustment command.

[0037] Furthermore, the blade angle values ​​must include those for the aero-engine in at least three states: takeoff, constant speed, and landing.

[0038] The relevant parameters of flexible blades include at least one of the following: blade temperature, stress, amplitude, and frequency during operation.

[0039] Furthermore, the relationship between the rotation angle required by the servo motor and the bending deformation angle of the flexible blade is controlled according to the following formula;

[0040]

[0041] In the formula, γ represents the bending deformation angle of the flexible blade, r represents the radius of the circular trajectory drawn by the rotating rod when it rotates, θ represents the angle of rotation of the rotating rod driven by the servo motor, d represents the maximum distance between the first linear rope and the second linear rope, and l represents the distance from the front end of the first linear rope to the part where it connects with the last side first arched rope segment.

[0042] Furthermore, the control system includes a computer control module, a servo control module, a blade sensor, a duct sensor, and an alarm module;

[0043] The computer control module is used to receive and process data acquired by the blade sensor and the duct sensor, and also to control the servo control module and the alarm module.

[0044] The servo control module is used to control the rotation direction and rotation angle of the servo, thereby controlling the bending deformation direction and bending deformation angle of the flexible blade.

[0045] The blade sensor is used to acquire real-time parameters of temperature, stress, and vibration of the flexible blade during operation.

[0046] The duct sensor is used to acquire real-time parameters of the duct wind speed and rotor speed of the aero-engine under operating conditions.

[0047] The alarm module is used to receive instructions from the computer control module to issue an alarm signal when the real-time parameters of temperature, stress and vibration of the flexible blade exceed the preset safety range.

[0048] The beneficial effects of this invention are as follows:

[0049] 1) The flexible blade is connected and supported by a first wave rope consisting of at least two first arched rope segments connected in sequence and a second wave rope consisting of at least two second arched rope segments connected in sequence. This allows the flexible blade to maintain a streamlined shape during bending, avoiding abrupt turns or discontinuous changes. Simultaneously, by connecting the first and second linear ropes to the arches of their respective first and second arched rope segments, the deformation of each arched rope segment can be coordinated during the bending process, ensuring the continuity of the shape change of the flexible blade as a whole. Furthermore, by controlling the tension and slack of the first and second linear ropes through a drive mechanism, the flexible blade can bend smoothly upwards or downwards. Additionally, the rope frame mechanism is movably connected to the blade skin via a fixed rod, a first support rod, and a second support rod. This ensures the overall structural rigidity of the flexible blade while providing necessary deformation freedom to better adapt to force changes caused by environmental conditions and facilitates smooth bending of the flexible blade.

[0050] 2) This control method can more accurately adjust the bending state of the flexible blades through the control system, thereby improving the response speed and control accuracy of the flexible blades.

[0051] 3) By presetting environmental parameters and initial blade angle values ​​and performing real-time monitoring, the most suitable blade angle value and direction can be calculated; when the blade angle difference is outside the allowable range, the difference can be converted into the angle and direction that the servo needs to rotate, and commands can be generated to control the servo, thus ensuring the efficiency and stability of the aero engine.

[0052] 4) By monitoring the relevant parameters of the flexible blades in real time during operation and performing safety checks, we can detect any dangerous situations and take different actions for each specific situation. This ensures that when the relevant parameters of the flexible blades exceed the safe range, we can deal with them in a timely manner and avoid safety accidents.

[0053] 5) The flexible blade and its control method can respond quickly to the working environment of the blade, ensuring that the flexible blade is always in a safe operating state, which is conducive to effectively improving the working efficiency of the aero-engine. Attached Figure Description

[0054] Figure 1 This is a three-dimensional structural schematic diagram of the environmentally responsive flexible blade for aero-engines in this invention.

[0055] Figure 2 This is a side view of the flexible blade of an aero-engine based on environmental response in the present invention in a split state.

[0056] Figure 3 This is a schematic diagram illustrating the flexible blade of an aero-engine based on environmental response in a bent state, as described in this invention.

[0057] Figure 4 This is a schematic diagram of the control system for the environmentally responsive flexible blades of an aero-engine in this invention.

[0058] Figure 5 This is a flowchart of the control method for flexible blades of aero-engines based on environmental response in this invention;

[0059] The components are labeled as follows: First skin 110, Second skin 120, Blade cavity 130, Clamping member 131, Fixing rod 210, First wave rope 220, First arched rope segment 221, First linear rope 230, First support rod 240, Second wave rope 250, Second arched rope segment 251, Second linear rope 260, Second support rod 270, Rotating rod 310, First connecting part 311, Second connecting part 312, Servo motor 320, First connecting rod 330, Second connecting rod 340, Computer control module 410, Servo motor control module 420, Flexible blade 440, Blade sensor 450, Duct sensor 460, Alarm module 470. Detailed Implementation

[0060] The present invention will be further described below with reference to the accompanying drawings and embodiments. The same reference numerals in the drawings denote components with the same or similar functions. Although various aspects of the embodiments are shown in the drawings, they are not necessarily drawn to scale unless specifically indicated otherwise.

[0061] The environmentally responsive flexible blade for aero-engines and its control method provided by this invention can be applied to each blade of the rotor and stator of an aero-engine. Although only the structure, working process and control process of a single flexible blade are described in order to fully describe the exemplary embodiments of this invention, this invention is not limited thereto.

[0062] In the description of this invention, it should be understood that the terms "center," "longitudinal," "lateral," "length," "width," "thickness," "upper," "lower," "front," "rear," "left," "right," "vertical," "horizontal," "top," "bottom," "inner," "outer," "clockwise," "counterclockwise," "axial," "radial," and "circumferential," indicating orientation or position and dimensional relationships, are based on the orientation or positional relationships shown in the accompanying drawings and are only for ease of description, not indicating or implying that the device or component referred to must have a specific orientation, or be constructed and operated in a specific orientation, and therefore should not be construed as a limitation of this invention; the term "multiple" refers to three or more; the expression "mainly composed of or constituted by" is interpreted as also including structural components not mentioned in the sentence; the term "and / or" is merely a description of the relationship between related objects, indicating that three relationships can exist, for example: A and / or B, which can represent: A alone, A and B simultaneously, and B alone. Furthermore, the terms "first" and "second" are used for descriptive purposes only and should not be construed as indicating or implying relative importance.

[0063] Combination Figure 1 and Figure 2 As shown, an environmentally responsive flexible blade for an aero-engine includes a blade skin, a blade truss, and a drive mechanism.

[0064] The blade skin is one of the main components of the flexible blade, primarily used to cover or wrap other parts of the flexible blade. The blade skin is usually made of composite materials with properties such as lightweight, high strength, high temperature resistance, and fatigue resistance. The blade skin has an airfoil structure, which has good aerodynamic characteristics and low wind resistance during operation. The blade skin includes a first skin 110 and a second skin 120 that are smoothly connected at their leading edges. A blade cavity 130 is formed between the first skin 110 and the second skin 120. Other corresponding edges of the first skin 110 and the second skin 120 can also be smoothly connected as needed.

[0065] The blade truss is one of the main components of the flexible blade. The blade truss is set in the blade cavity 130. Its main function is to provide the structural support required by the flexible blade, while maintaining the shape and stability of the flexible blade, so that the flexible blade can remain stable in high-speed rotation and high-temperature environment, and can withstand various loads during the operation of the aero-engine.

[0066] The blade truss includes a fixed rod 210 and a rope frame mechanism;

[0067] The fixing rod 210 is hinged at the front end of the blade cavity 130 and is used to movably connect the front end of the rope frame mechanism with the front end of the blade skin.

[0068] The rope frame mechanism includes a first wave rope 220, a first linear rope 230, a second wave rope 250, and a second linear rope 260. All three ropes—220, 230, 250, and 260—are rigid ropes with reversible deformation capability. Reversible deformation capability refers to the ability of a material to undergo reversible deformation under external force and to return to its original shape after the external force is removed. A rigid rope is a rope or rope-like component with a certain degree of rigidity, made of a material with reversible deformation capability, enabling it to absorb energy under external force and return to its original shape after the external force is removed. Materials with reversible deformation capability typically possess good elasticity and plasticity, maintaining a certain elastic deformation after deformation without permanent deformation or breakage.

[0069] The first wave rope 220 is composed of at least two first arched rope segments 221 connected in sequence, with the first arched rope segments 221 protruding towards the second skin 120. The front end of the first wave rope 220 is connected to the fixed rod 210, and the connection points of each first arched rope segment 221 and the rear end of the first wave rope 220 are movably connected to the first skin 110 through the first support rod 240. The arc of the arch of each first arched rope segment 221 that makes up the first wave rope 220 usually increases from front to back. By connecting and supporting the first skin 110 with the first wave rope 220, the flexible blade can maintain a streamlined shape during bending. Usually, multiple first lug groups are provided on the first skin 110. Each first lug group consists of two lugs spaced apart on the left and right. The two ends of the first support rod 240 are rotatably connected to the two lugs of the same first lug group, respectively.

[0070] The first linear rope 230 is connected to the top of each first arched rope segment 221, and the front end of the first linear rope 230 is connected to the front end of the first wave rope 220 and / or the fixing rod 210. In this way, the deformation of each first arched rope segment 221 can be coordinated during the bending process of the flexible blade driven by the first linear rope 230, and the continuity of the shape change when the flexible blade is bent as a whole can be further guaranteed.

[0071] The second wave rope 250 is composed of at least two second arched rope segments 251 connected in sequence, with the second arched rope segments 251 protruding towards the first skin 110. The front end of the second wave rope 250 is connected to the fixed rod 210, and the connection points of each second arched rope segment 251 and the rear end of the second wave rope 250 are movably connected to the second skin 120 through the second support rod 270. The arc of each second arched rope segment 251 that makes up the second wave rope 250 usually increases from front to back. By connecting and supporting the second skin 120 with the second wave rope 250, the flexible blade can maintain a streamlined shape during bending. The second wave rope 250 and the first wave rope 220 in the same rope frame mechanism are usually arranged symmetrically to each other (when the flexible blade is in a non-bending state). Usually, multiple second lug groups are provided on the second skin 120. The second lug groups have the same structure as the first lug groups, and the two ends of the second support rod 270 are rotatably connected to the two lugs of the same second lug group, respectively.

[0072] The second linear rope 260 corresponds to the first linear rope 230 and is connected to the top of each second arched rope segment 251. The front end of the second linear rope 260 is connected to the front end of the second wave rope 250 and / or the fixing rod 210. In this way, the deformation of each second arched rope segment 251 can be coordinated during the bending process of the flexible blade driven by the second linear rope 260, further ensuring the continuity of the shape change when the flexible blade is bent as a whole. The second linear rope 260 and the first linear rope 230 in the same rope frame mechanism are usually arranged symmetrically to each other (when the flexible blade is in a non-bending state).

[0073] The drive mechanism is connected to the rear end of the first linear rope 230 and the rear end of the second linear rope 260, respectively, and is used to drive the flexible blade to switch between three states: an upward bending state, an unbending state, and a downward bending state. The drive mechanism can pull the first linear rope 230 and loosen the second linear rope 260 to make the flexible blade change to an upward bending state, and can pull the second linear rope 260 and loosen the first linear rope 230 to make the flexible blade change to a downward bending state. The drive mechanism can be of various types, such as: a motor and its accessories, a servo motor 320 and its accessories, an electric push rod and its accessories, a cylinder or hydraulic cylinder and its accessories, etc.

[0074] The flexible blade is connected and supported by a blade truss mainly composed of a fixed rod 210 and a rope frame mechanism. The tension and relaxation of the first linear rope 230 and the second linear rope 260 are controlled by a drive mechanism, allowing the flexible blade to smoothly bend upwards or downwards, thus solving the problem of inflection points easily occurring during the bending process of existing flexible blades. Furthermore, the fixed rod 210, the first support rod 240, and the second support rod 270 enable the rope frame mechanism to be movably connected to the blade skin. This ensures the overall structural rigidity of the flexible blade while providing it with the necessary degrees of freedom for deformation, better adapting to force changes caused by environmental conditions and facilitating smooth bending of the flexible blade.

[0075] The principle behind the bending of this flexible blade is as follows:

[0076] After receiving the instruction to drive the flexible blade to bend upward, the drive mechanism pulls the first linear rope 230 and releases the second linear rope 260. The tension is transmitted through the first linear rope 230 to the first arched rope segment 221 and the fixing rod 210. The fixing rod 210 located at the front end of the blade cavity 130 pulls the head of the flexible blade to make it tilt upward. Each of the first arched rope segments 221 undergoes elastic deformation simultaneously and applies a downward force to the first skin 110, thereby driving the flexible blade to bend and deform upward.

[0077] After receiving the instruction to drive the flexible blade to bend downward, the drive mechanism pulls the second linear rope 260 and releases the first linear rope 230. The tension is transmitted through the second linear rope 260 to the second arched rope segment 251 and the fixing rod 210. The fixing rod 210 located at the front end of the blade cavity 130 pulls the head of the flexible blade to tilt downward. Each second arched rope segment 251 undergoes elastic deformation simultaneously and applies an upward force to the second skin 120, thereby causing the flexible blade to bend and deform downward.

[0078] The bending process described above achieves a smooth bending from the root to the tip of the flexible blade, avoiding the formation of inflection points.

[0079] For example Figure 2 As shown, in some preferred embodiments of the present invention, a clamping member 131 is provided at the front end of the blade cavity 130, and the fixing rod 210 is hinged to the clamping member 131. Two or more clamping members 131 may be provided depending on the width dimension of the flexible blade, structural strength requirements, etc.; the structure of the clamping member 131 can be various, preferably a U-shaped member with the opening facing backward, so as to facilitate the fixing rod 210 to be hinged to the clamping member 131 through the hinge shaft.

[0080] For example Figure 1As shown, in some preferred embodiments of the present invention, there are at least two rope frame mechanisms, which are spaced apart along the width direction of the blade cavity 130. By providing two or more rope frame mechanisms, the structural strength, stability, and service life of the flexible blade can be enhanced.

[0081] Combined Figure 1 and Figure 2 As shown, in some preferred embodiments of the present invention, the drive mechanism includes a rotating rod 310 and a servo motor 320. The rotating rod 310 is rotatably disposed at the rear end of the blade cavity 130, and has a swingable first connecting portion 311 and a second connecting portion 312, wherein the first connecting portion 311 and the second connecting portion 312 swing in opposite directions during the rotation of the rotating rod 310. The rear end of the first linear rope 230 is movably connected to the first connecting portion 311 via a first connecting rod 330. The rear end of the second linear rope 260 is movably connected to the second connecting portion 312 via a second connecting rod 340. The servo motor 320 is drively connected to the rotating rod 310 and can drive the rotating rod 310 to reciprocate, thereby causing the flexible blade to bend and deform. The servo motor 320 typically drives the rotating rod 310 to rotate around its own axis, and the servo motor 320 and the rotating rod 310 are generally mounted together as the root of the flexible blade on the hub of the aero engine. The drive mechanism consists of a small number of parts, has a relatively simple structure, and is easy to install and maintain. Moreover, the combination of the servo motor 320, the rotating rod 310, the connecting rod, and the linear rope can achieve efficient drive, enabling the flexible blade to respond quickly and perform the required bending action.

[0082] The working principle of the aforementioned drive mechanism is as follows: When the servo motor 320 receives an excitation signal, it drives the rotating rod 310 to rotate around its own axis. The rotation of the rotating rod 310 causes the first connecting rod 330 and the second connecting rod 340 connected to it to change position, that is, to achieve oscillation in opposite directions. One connecting rod pulls the linear rope connected to it, while the other connecting rod releases the linear rope connected to it. Figure 3 As shown.

[0083] Combined Figure 1 and Figure 2 As shown, in some preferred embodiments of the present invention, the first connecting part 311 is a perforated boss located on the upper side of the rotating rod 310; the second connecting part 312 is a perforated boss located on the lower side of the rotating rod 310; the rear end of the first connecting rod 330 is hinged to the first connecting part 311 via a connecting pin; the rear end of the second connecting rod 340 is hinged to the second connecting part 312 via a connecting pin. The perforated boss type connecting part facilitates hinged connection with the connecting rod, and the vertical distribution of the first connecting part 311 and the second connecting part 312 has advantages such as simple structure and stable and reliable transmission.

[0084] The present invention also provides a control method for an environmentally responsive aero-engine flexible blade, wherein the control method controls the flexible blade 440 through a control system, the flexible blade 440 being the aforementioned environmentally responsive aero-engine flexible blade.

[0085] like Figure 4 As shown, the control system includes a computer control module 410, a servo control module 420, a blade sensor 450, a duct sensor 460, and an alarm module 470.

[0086] The computer control module 410 is used to receive and process the data acquired by the blade sensor 450 and the duct sensor 460, and also to control the servo control module 420 and the alarm module 470.

[0087] The servo control module 420 is used to control the rotation direction and rotation angle of the servo 320, thereby realizing the control of the bending deformation direction and bending deformation angle of the flexible blade 440.

[0088] The blade sensor 450 is used to acquire real-time parameters of temperature, stress and vibration of the flexible blade 440 under working conditions;

[0089] The duct sensor 460 is used to acquire real-time parameters of the duct wind speed and rotor speed of the aero-engine during operation.

[0090] The alarm module 470 is used to receive instructions from the computer control module 410 to issue an alarm signal when the real-time parameters of temperature, stress and vibration of the flexible blade 440 exceed the preset safety range.

[0091] This control method allows for more precise adjustment of the bending state of the flexible blade 440 through the control system, improving the response speed and control accuracy of the flexible blade 440. The blade sensor 450 and its related circuitry are typically installed within the blade cavity 130. The various modules of the control system can be integrated together, or each module, sensor, and servo motor 320 can be individually connected for communication. Communication connection refers to the exchange of signals between connected devices, and can be divided into wired and wireless connections. Wired connections are typically cable or fiber optic connections; wireless connections are typically radio communication, Bluetooth, infrared, or NFC connections.

[0092] The computer control module 410 typically includes a processor and memory.

[0093] The processor of the computer control module 410 is a single processing unit or multiple processing units for executing different actions of the method flow according to embodiments of the present invention. Specifically, the processor of the computer control module 410 typically includes a general-purpose microprocessor, an instruction set processor and / or an associated chipset and / or a special-purpose microprocessor (e.g., an application-specific integrated circuit (ASIC)), etc. The processor may also include onboard memory for caching purposes.

[0094] The memory of the computer control module 410 stores a computer-executable program that, when executed by the processor, causes the processor to perform the operations described above. For example, it can be any medium capable of containing, storing, transmitting, propagating, or transmitting instructions. For example, a readable storage medium can include, but is not limited to, electrical, magnetic, optical, electromagnetic, infrared, or semiconductor systems, devices, instruments, or propagation media. Specific examples of readable storage media include: magnetic storage devices, such as magnetic tape or hard disk drives (HDDs); optical storage devices, such as optical discs (CD-ROMs); memories, such as random access memory (RAM) or flash memory; and / or wired / wireless communication links.

[0095] The servo control module 420, typically coupled to the servo 320, is configured to drive the servo 320 and control the rotation direction and rotation angle of the servo 320, thereby controlling the bending deformation direction and bending deformation angle of the flexible blade 440.

[0096] The blade sensor 450, typically installed in the blade cavity 130 of the flexible blade 440, is configured to acquire real-time parameters related to temperature, stress, and vibration of the flexible blade 440 during operation. The blade sensor 450 typically includes a temperature sensor, a stress sensor, and a vibration sensor.

[0097] Duct sensor 460, typically installed inside the duct of an aircraft engine, is configured to acquire real-time parameters of airflow velocity and rotor speed within the duct during operation. Duct sensor 460 typically includes an airflow velocity sensor and a rotor speed sensor.

[0098] The alarm module 470 is configured to receive instructions from the computer control module 410 and issue an alarm signal when the real-time parameters related to temperature, stress, and vibration of the flexible blade 440 exceed the preset safety range.

[0099] In practical applications, the computer control module 410, servo control module 420, servo motor 320, and alarm module 470 can be integrated together. For example, they can be integrated onto a single circuit board.

[0100] In some preferred embodiments of the present invention, the control method includes:

[0101] Preset initial values ​​for duct wind speed and rotor speed; duct wind speed refers to the airflow speed entering the duct of the aero-engine, and rotor speed refers to the rotational speed of the aero-engine rotor;

[0102] The initial blade angle value of the flexible blade 440 is preset; the blade angle refers to the angle of bending deformation of the flexible blade 440; usually, the blade angle value includes at least the values ​​of the aero engine in three states: takeoff, constant speed, and landing.

[0103] The main data of the duct is monitored in real time and transmitted back to the control system to calculate the most suitable blade angle and direction. The main data of the duct usually includes at least the duct wind speed and rotor speed. The blade angle and direction that enable the aero-engine to achieve the highest working efficiency are usually taken as the most suitable indicators.

[0104] Determine whether the difference between the initial blade angle value and the optimal blade angle value is within the allowable range of blade angle difference;

[0105] If not, the difference is converted into the angle and direction that the servo motor 320 needs to rotate, and commands are generated to control the servo motor 320 to work.

[0106] By presetting environmental parameters and initial blade angle values ​​and conducting real-time monitoring, the most suitable blade angle value and direction can be calculated. If the blade angle difference is outside the allowable range, the difference can be converted into the angle and direction that the servo motor 320 needs to rotate, and commands can be generated to control the servo motor 320 to work, thus ensuring the efficiency and stability of the aero engine.

[0107] In some preferred embodiments of the present invention, the control method further includes:

[0108] The relevant parameters of the flexible blade 440 are monitored in real time and the data is transmitted back to the control system. The relevant parameters of the flexible blade 440 typically include at least one of the blade's temperature, stress, amplitude, and frequency under operating conditions.

[0109] Determine whether the relevant parameters of the monitored flexible blade 440 exceed the preset safety range;

[0110] If the error exceeds the limit, an alarm will be triggered, and the servo motor 320 will be controlled to operate via a preset safety adjustment command.

[0111] By monitoring the relevant parameters of the flexible blade 440 in real time during operation and performing safety checks, detecting any dangerous situations, and taking different actions for different situations, it can be ensured that the relevant parameters of the flexible blade 440 are dealt with in a timely manner when they exceed the safe range, thus avoiding safety accidents.

[0112] Combination Figure 5As shown, in some preferred embodiments of the present invention, the control method includes:

[0113] Step S301: Based on the existing aero-engine test data, summarize and obtain the initial value of the preset duct wind speed and the corresponding initial value of the preset rotor speed.

[0114] Step S302: Calculate the angle value of the flexible blade 440 when the aero-engine has the highest efficiency based on the initial value preset in step S301, and set it as the initial blade angle value, which is recorded in the computer control module 410; wherein, the angle value includes at least three initial blade angle values ​​when the aero-engine is in the three normal states of takeoff, constant speed and landing.

[0115] In step S303, during the operation of the aero-engine, the duct sensor 460 located in the aero-engine duct monitors the duct wind speed and rotor speed in real time, and immediately transmits the monitoring results to the computer control module 410 for updating and recording.

[0116] In step S304, the computer control module 410 calculates the most suitable blade angle value based on the real-time updated monitoring data, and sets an allowable range for the blade angle difference (e.g., ±3°).

[0117] Step S305: Based on the initial blade angle value calculated in step S302 and the most suitable blade angle value calculated in step S304, determine whether the difference between the two exceeds the allowable range of blade angle difference. If the difference between the blade angles calculated in the previous two steps is within the allowable range of difference, the computer control module 410 will not send the control command for servo rotation and will continue to repeat the previous step.

[0118] Step S306: When the difference between the two calculated blade angles is outside the allowable range of the above difference, the computer control module 410 converts the difference between the two calculated blade angles into the rotation direction and rotation angle of the servo motor 320, and sends the servo motor rotation command to the servo motor control module 420.

[0119] In step S307, after receiving the command, the servo control module 420 sends a pulse excitation signal to the servo 320 located at the root of the flexible blade 440, so that it rotates in the specified direction and angle according to the command. According to the previous flexible blade bending principle, the servo 320 drives the rotating rod 310 to rotate, thereby driving the flexible blade 440 to bend, so that the working efficiency of the aero engine approaches or reaches its maximum.

[0120] In step S308, the blade sensor 450 located inside the flexible blade 440 monitors the temperature, stress and vibration data of the flexible blade 440 in real time and transmits the monitoring data back to the computer control module 410.

[0121] In step S309, the computer control module 410 organizes and compares the monitoring data transmitted back by the blade sensor 450 to determine whether the real-time working data of the flexible blade 440 exceeds the preset safety range. The preset safety range includes, but is not limited to, the blade's limit temperature, limit stress, limit amplitude, and limit vibration frequency.

[0122] In step S310, if the comparison result of the computer control module 410 exceeds the preset safety range, the computer control module 410 sends a control command to the alarm module 470 to issue an alarm, notifying relevant personnel to perform maintenance operations or related emergency safety measures. At the same time, the computer control module 410 sends a preset safety adjustment command to the servo control module 420, such as controlling the flexible blade 440 to stop the bending adjustment of the angle and restore it to its initial shape. If the comparison result of the computer control module 410 does not exceed the preset safety range, then step S303 is repeated.

[0123] The flexible blade and its control method can respond quickly to the working environment of the blade, ensuring that the flexible blade is always in a safe operating state, which is conducive to effectively improving the working efficiency of aero-engines.

[0124] Combination Figure 1 , Figure 2 and Figure 3 As shown, in some preferred embodiments of the present invention, the relationship between the angle at which the servo motor 320 needs to rotate and the bending deformation angle of the flexible blade 440 is controlled according to the following formula;

[0125]

[0126] In the formula, γ represents the bending deformation angle of the flexible blade 440, r represents the radius of the circular trajectory drawn by the rotating rod 310 when it rotates, θ represents the angle by which the servo motor 320 drives the rotating rod 310 to rotate, d represents the maximum distance between the first linear rope 230 and the second linear rope 260, and l represents the distance between the front end of the first linear rope 230 and the part where it connects with the last side first arched rope segment 221, or the distance between the front end of the second linear rope 260 and the part where it connects with the last side second arched rope segment 251, or the average of the two distances mentioned above.

[0127] The computer control module 410 typically converts the difference between the blade angles calculated in the previous two calculations into the rotation direction and rotation angle of the servo motor 320 according to the above formula, so as to improve the accuracy and effectiveness of control.

Claims

1. Environmentally responsive flexible blades for aero-engines, including blade skin, blade truss, and drive mechanism; The blade skin is an airfoil structure, which includes a first skin (110) and a second skin (120) that are smoothly connected at their front ends; a blade cavity (130) is formed between the first skin (110) and the second skin (120); The blade truss is disposed in the blade cavity (130); Its features are: The blade truss includes a fixed rod (210) and a rope frame mechanism; The fixing rod (210) is hinged to the front end of the blade cavity (130); The rope frame mechanism includes a first wave rope (220), a first linear rope (230), a second wave rope (250), and a second linear rope (260), wherein the first wave rope (220), the first linear rope (230), the second wave rope (250), and the second linear rope (260) are all rigid ropes with reversible deformation capability. The first wave rope (220) is composed of at least two first arched rope segments (221) connected in sequence, and the first arched rope segments (221) protrude toward the second skin (120); the front end of the first wave rope (220) is connected to the fixed rod (210), and the connection points of each first arched rope segment (221) and the rear end of the first wave rope (220) are movably connected to the first skin (110) through the first support rod (240); The first linear rope (230) is connected to the top of each first arched rope segment (221), and the front end of the first linear rope (230) is connected to the front end of the first wave rope (220) and / or the fixed rod (210). The second wave rope (250) is composed of at least two second arched rope segments (251) connected in sequence, and the second arched rope segments (251) protrude toward the first skin (110); the front end of the second wave rope (250) is connected to the fixed rod (210), and the connection points of each second arched rope segment (251) and the rear end of the second wave rope (250) are movably connected to the second skin (120) through the second support rod (270); The second linear rope (260) corresponds to the first linear rope (230) and is connected to the top of each second arched rope segment (251), and the front end of the second linear rope (260) is connected to the front end of the second wave rope (250) and / or the fixed rod (210). The drive mechanism is connected to the rear end of the first linear rope (230) and the rear end of the second linear rope (260) respectively; the drive mechanism can pull the first linear rope (230) and relax the second linear rope (260) to make the flexible blade change to an upward bending state, and can pull the second linear rope (260) and relax the first linear rope (230) to make the flexible blade change to a downward bending state.

2. The environmentally responsive flexible blade for aero-engines according to claim 1, characterized in that: The front end of the blade cavity (130) is provided with a clamping member (131), and the fixing rod (210) is hinged to the clamping member (131).

3. The environmentally responsive flexible blade for aero-engines according to claim 1, characterized in that: The rope frame mechanism is at least two and is distributed at intervals along the width direction of the blade cavity (130).

4. The environmentally responsive flexible blade for aero-engines according to any one of claims 1 to 3, characterized in that: The drive mechanism includes a rotating rod (310) and a servo motor (320); The rotating rod (310) is rotatably disposed at the rear end of the blade cavity (130), and has a swingable first connecting part (311) and a second connecting part (312), and the first connecting part (311) and the second connecting part (312) swing in opposite directions during the rotation of the rotating rod (310). The rear end of the first linear rope (230) is movably connected to the first connecting part (311) via the first connecting rod (330); The rear end of the second linear rope (260) is movably connected to the second connecting part (312) via the second connecting rod (340); The servo motor (320) is connected to the rotating rod (310) and can drive the rotating rod (310) to rotate back and forth.

5. The environmentally responsive flexible blade for aero-engines according to claim 4, characterized in that: The first connecting part (311) is a perforated boss located on the upper side of the rotating rod (310); The second connecting part (312) is a perforated boss located on the lower side of the rotating rod (310); The rear end of the first connecting rod (330) is hinged to the first connecting part (311) by a connecting rod pin; The rear end of the second link (340) is hinged to the second connecting part (312) via a link pin.

6. A control method for flexible blades of aero-engines based on environmental response, characterized in that: The flexible blade (440) is controlled by a control system, wherein the flexible blade (440) is the environmentally responsive flexible blade for aero-engines as described in claim 4 or 5. The control method includes: Preset the initial values ​​for duct wind speed and rotor speed; Preset the initial blade angle value of the flexible blade (440); The main data of the duct is monitored in real time and transmitted back to the control system to calculate the most suitable blade angle and direction. Determine whether the difference between the initial blade angle value and the optimal blade angle value is within the allowable range of blade angle difference; If not, the difference is converted into the angle and direction that the servo motor (320) needs to rotate, and commands are generated to control the servo motor (320) to work.

7. The control method for flexible blades of aero-engines based on environmental response according to claim 6, characterized in that, The control method also includes: Real-time monitoring of relevant parameters of the flexible blade (440) and transmission of data back to the control system; Determine whether the relevant parameters of the monitored flexible blade (440) exceed the preset safety range; If the error exceeds the limit, an alarm will be triggered, and the servo motor (320) will be controlled to operate via a preset safety adjustment command.

8. The control method for flexible blades of aero-engines based on environmental response according to claim 7, characterized in that: The blade angle values ​​must include those for the aircraft engine in at least three states: takeoff, constant speed, and landing. The relevant parameters of the flexible blade (440) include at least one of the blade's temperature, stress, amplitude and frequency under operating conditions.

9. The control method for environmentally responsive flexible blades of aero-engines according to any one of claims 6 to 8, characterized in that: The relationship between the angle at which the servo motor (320) needs to rotate and the bending deformation angle of the flexible blade (440) is controlled by the following formula; In the formula, γ represents the bending deformation angle of the flexible blade (440), r represents the radius of the circular trajectory drawn by the rotating rod (310) when it rotates, θ represents the angle by which the servo motor (320) drives the rotating rod (310) to rotate, d represents the maximum distance between the first linear rope (230) and the second linear rope (260), and l represents the distance between the front end of the first linear rope (230) and the part where it connects with the last side first arched rope segment (221).

10. The control method for flexible blades of aero-engines based on environmental response according to claim 9, characterized in that: The control system includes a computer control module (410), a servo control module (420), a blade sensor (450), a duct sensor (460), and an alarm module (470). The computer control module (410) is used to receive and process data acquired by the blade sensor (450) and the duct sensor (460), and also to control the servo control module (420) and the alarm module (470). The servo control module (420) is used to control the rotation direction and rotation angle of the servo (320), thereby realizing the control of the bending deformation direction and bending deformation angle of the flexible blade (440). The blade sensor (450) is used to acquire real-time parameters of temperature, stress and vibration of the flexible blade (440) under working conditions; The duct sensor (460) is used to acquire real-time parameters of the duct wind speed and rotor speed of the aero-engine under operating conditions. The alarm module (470) is used to receive instructions from the computer control module (410) to issue an alarm signal when the real-time parameters of temperature, stress and vibration of the flexible blade (440) exceed the preset safety range.

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