Control method, device and equipment for guide and static blade combined regulation and deflation coupled gas compressor

Abstract

The invention provides a gas compressor control method, device and equipment based on guide and static blade joint blending and deflation coupling, and can be applied to the technical field of aero-engines and gas turbine gas compressors. The method comprises the steps that according to the intersection point of a characteristic curve of the gas compressor at the preset rotating speed and a common working line of the gas compressor, the working point of the gas compressor at the preset rotating speed is determined, and the common working line is a steady-state working condition point track determined according to the whole engine matching relation; according to the difference between the blade geometric inlet angle and the inlet relative airflow angle of the pitch diameter section of the rotor blade of the gas compressor, the attack angle of the pitch diameter section of the rotor blade of the gas compressor corresponding to the working point is determined; and under the condition that it is determined that the attack angle does not meet the preset angle range, the adjusted attack angle meets the preset angle range and the stability margin at the preset rotating speed is larger than or equal to the preset margin by adjusting the installation angle of an adjustable guide vane and an adjustable static vane of the gas compressor and adjusting the gas bleeding amount.

Description

Technical Field

[0001] This disclosure relates to the field of aero-engine and gas turbine compressor technology, and specifically to a compressor control method, device and equipment for guide vane joint adjustment and venting coupling. Background Technology

[0002] The stability margin of a compressor is a core indicator for measuring its surge resistance and safe and stable operating range, affecting the performance and reliability of aero-engines or gas turbines. Sufficient stability margin is the fundamental guarantee to prevent the compressor from entering unstable operating states such as surge or stall, enabling the engine to operate efficiently and stably even when deviating from its design conditions. With the continuous improvement of compressor performance, multi-stage high-load compressors are facing the challenge of insufficient stability margin under low operating conditions.

[0003] Common methods for widening the stability margin include guide vane adjustment and interstage bleed. However, designing and controlling guide vane adjustment and interstage bleed independently has drawbacks, such as control redundancy and significant efficiency loss, mutual interference between actions, and limited overall stability enhancement. Summary of the Invention

[0004] In view of the above problems, this disclosure provides a compressor control method, device and equipment for guide vane adjustment and venting coupling.

[0005] According to the first aspect of this disclosure, a compressor control method based on guide vane and stator joint adjustment and venting coupling is provided, comprising: determining the operating point of the compressor at a predetermined speed based on the intersection of the characteristic curve of the compressor at a predetermined speed and the common operating line of the compressor, wherein the common operating line is the steady-state operating point trajectory determined by the matching relationship of the entire engine; determining the angle of attack of the rotor blade mid-diameter section of the compressor corresponding to the operating point based on the difference between the blade geometric inlet angle and the inlet relative airflow angle of the rotor blade mid-diameter section of the compressor; and, if the determined angle of attack does not meet the predetermined angle range, adjusting the installation angle of the adjustable guide vanes and adjustable stator vanes of the compressor, and adjusting the venting volume, so that the adjusted angle of attack meets the predetermined angle range, and the stability margin at the predetermined speed is greater than or equal to the predetermined margin.

[0006] According to embodiments of this disclosure, adjusting the installation angle of the adjustable guide vane and the adjustable stationary vane of the compressor, and adjusting the venting volume, includes: adjusting the installation angle of the adjustable guide vane and the adjustable stationary vane first, based on the deviation between the angle of attack and a predetermined angle range, to adjust the angle of attack; and adjusting the venting volume if it is determined that the angle of attack still does not meet the predetermined angle range after adjustment.

[0007] According to embodiments of this disclosure, adjusting the venting volume includes: determining the required angle-of-attack adjustment amount based on the deviation between the adjusted angle of attack and a predetermined angle range; determining the inlet relative airflow angle after pre-venting based on the angle-of-attack adjustment amount and the inlet relative airflow angle; determining the inlet axial velocity after pre-venting based on the compressor rotor blade inlet axial velocity corresponding to the operating point, the inlet relative airflow angle after pre-venting, and the inlet relative airflow angle; determining the pre-venting volume based on the compressor inlet flow rate corresponding to the operating point, the inlet axial velocity after pre-venting, and the inlet axial velocity; and performing a venting operation based on the pre-venting volume.

[0008] According to embodiments of this disclosure, the compressor control method based on guide vane coupling and venting coupling further includes: determining the stability margin at a predetermined speed based on the operating parameters of the near stall point and the operating point on the characteristic curve, provided that the angle of attack meets the predetermined angle range.

[0009] According to embodiments of this disclosure, the compressor control method based on guide vane and stator joint adjustment and venting coupling further includes: calculating characteristic curves using aerodynamic analysis tools when the compressor is at a predetermined speed, the guide vanes and stator vanes are not adjusted, and there is no venting.

[0010] According to embodiments of this disclosure, the engine includes at least: a compressor, a combustion chamber, a turbine, a turbine guide vane, and a nozzle; the compressor control method based on guide vane coupling and exhaust coupling further includes: determining a set of steady-state operating points that satisfy the conditions of continuous flow and power balance of the engine based on the characteristics and geometric parameters of the compressor, combustion chamber, turbine, turbine guide vane, and nozzle, wherein each of the multiple steady-state operating points in the set is a point on the characteristic curve of the compressor at the corresponding speed; and determining the connection trajectory of the points on the multiple characteristic curves corresponding to the steady-state operating points as a common operating line.

[0011] According to embodiments of this disclosure, the rotor blades include multiple rotor blades, and the method further includes: determining that the angle of attack meets the predetermined angle range when it is determined that the angles of attack of the mid-diameter sections of the multiple rotor blades all meet the predetermined angle range. According to embodiments of this disclosure, the compressor control method of guide vane co-adjustment and venting coupling further includes: when it is determined that the angle of attack of the mid-diameter section of at least one rotor blade among the multiple rotor blades does not meet the predetermined angle range, coordinating the installation angle of the adjustable guide vanes of the compressor and the adjustable stator vanes of the corresponding stage of at least one rotor blade, and adjusting the venting volume of the corresponding stage.

[0012] The second aspect of this disclosure provides a compressor control device based on guide vane-stationary vane coupling and venting coupling, comprising: a first determining module, configured to determine the operating point of the compressor at a predetermined speed based on the intersection of the compressor's characteristic curve at a predetermined speed and the common operating line of the compressor, wherein the common operating line is the steady-state operating point trajectory determined by the matching relationship of the entire engine; a second determining module, configured to determine the angle of attack of the compressor's rotor blade mid-diameter section corresponding to the operating point based on the difference between the blade geometric inlet angle and the inlet relative airflow angle of the compressor's rotor blade mid-diameter section; and a coordination adjustment module, configured to, when the determined angle of attack does not meet the predetermined angle range, adjust the installation angle of the compressor's adjustable guide vanes and adjustable stationary vanes, and adjust the venting volume, so that the adjusted angle of attack meets the predetermined angle range, and the stability margin at the predetermined speed is greater than or equal to the predetermined margin.

[0013] A third aspect of this disclosure provides an electronic device comprising: one or more processors; and a memory for storing one or more computer programs, wherein the one or more processors execute the one or more computer programs to implement the steps of the method described above.

[0014] A fourth aspect of this disclosure also provides a computer-readable storage medium having a computer program or instructions stored thereon, which, when executed by a processor, implement the steps of the above-described method.

[0015] The fifth aspect of this disclosure also provides a computer program product, including a computer program or instructions that, when executed by a processor, implement the steps of the above-described method.

[0016] According to embodiments of this disclosure, the intersection of the characteristic curve of the compressor operating at a predetermined speed and the common operating line is determined as the operating point, which determines the angle of attack distribution of the compressor rotor blades. The angle of attack is a parameter affecting flow stability. Therefore, by adjusting the installation angles of the adjustable guide vanes and adjustable stator vanes, and adjusting the bleed volume, the angle of attack can be made to meet a predetermined angle range, thereby controlling the stability margin to be greater than or equal to the predetermined margin. Because the guide vane and stator vane adjustment and bleed coupling can work synergistically, the compressor flow field is reconstructed from the inlet dimension (optimizing the inlet angle of attack) and the outlet dimension (adjusting the flow back pressure), achieving precise matching of the aerodynamic loads at the front and rear ends. This results in better suppression of flow separation and increased stability margin compared to a single control method. Furthermore, this synergistic mechanism follows the principle of minimum control cost, achieving the stability enhancement target with smaller guide vane and stator vane angles and less bleed volume. Thus, while ensuring high stability, it minimizes the efficiency loss caused by bleed, improving the overall efficiency of the compressor. Attached Figure Description

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

[0018] Figure 1 A flowchart of a compressor control method for guide vane coupling and venting coupling according to an embodiment of the present disclosure is shown;

[0019] Figure 2 A schematic diagram of the adjustable guide / stator blade angle of attack of a rotor blade according to an embodiment of the present disclosure is shown;

[0020] Figure 3 A schematic diagram showing the rotor intake angle change caused by interstage pre-bleeding according to an embodiment of the present disclosure is shown.

[0021] Figure 4 A flowchart of a compressor control method with guide vane coupling and venting coupling according to another embodiment of the present disclosure is shown;

[0022] Figure 5 A structural block diagram of a compressor control device with guide vane and venting coupling according to an embodiment of the present disclosure is shown; and

[0023] Figure 6 A block diagram of an electronic device suitable for implementing a compressor control method for guide vane coupling and venting coupling according to an embodiment of the present disclosure is shown. Detailed Implementation

[0024] The embodiments of the present disclosure will now be described with reference to the accompanying drawings. However, it should be understood that these descriptions are exemplary only and are not intended to limit the scope of the disclosure. In the following detailed description, numerous specific details are set forth to provide a thorough understanding of the embodiments of the present disclosure for ease of explanation. However, it will be apparent that one or more embodiments may be practiced without these specific details. Furthermore, descriptions of well-known structures and techniques are omitted in the following description to avoid unnecessarily obscuring the concepts of the present disclosure.

[0025] The terminology used herein is for the purpose of describing particular embodiments only and is not intended to limit this disclosure. The terms “comprising,” “including,” etc., as used herein indicate the presence of the stated features, steps, operations, and / or components, but do not exclude the presence or addition of one or more other features, steps, operations, or components.

[0026] All terms used herein (including technical and scientific terms) have the meanings commonly understood by those skilled in the art, unless otherwise defined. It should be noted that the terms used herein are to be interpreted in a manner consistent with the context of this specification, and not in an idealized or overly rigid way.

[0027] When using expressions such as "at least one of A, B and C", they should generally be interpreted in accordance with the meaning that is commonly understood by those skilled in the art (e.g., "a system having at least one of A, B and C" should include, but is not limited to, a system having A alone, a system having B alone, a system having C alone, a system having A and B, a system having A and C, a system having B and C, and / or a system having A, B and C, etc.).

[0028] In the technical solution disclosed herein, the user information (including but not limited to user personal information, user image information, user device information, such as location information) and data (including but not limited to data used for analysis, stored data, and displayed data) involved are all information and data authorized by the user or fully authorized by all parties. Furthermore, the collection, storage, use, processing, transmission, provision, disclosure, and application of related data all comply with relevant laws, regulations, and standards, necessary confidentiality measures have been taken, and they do not violate public order and good morals. Corresponding operation entry points are provided for users to choose to authorize or refuse.

[0029] Traditional compressor stabilization design typically treats guide vane adjustment and interstage venting as independent control methods. This approach has the following inherent drawbacks:

[0030] (1) Lack of synergy and limited effect: The adjustment of guide vanes and stator vanes mainly improves the aerodynamic matching of the front stage, but has limited effect on the adjustment of the back stage. The venting mainly alleviates the blockage of the back stage, but the discharge of high-pressure gas will cause significant energy waste and has a weak effect on the optimization of the front stage. The two lack synergy, and the overall stability enhancement effect is limited.

[0031] (2) Design redundancy and efficiency loss: To ensure stability under all operating conditions, the two systems are often designed independently according to the more severe operating conditions, resulting in control redundancy. Under most intermediate operating conditions, the guide vane angle and the venting volume are not optimal, causing unnecessary performance loss.

[0032] (3) Mutual interference: When the two systems are running independently, their control effects may cancel each other out or produce negative effects.

[0033] The embodiments of this disclosure provide a compressor control method with guide vane and stator joint adjustment and venting coupling, including: determining the operating point of the compressor at a predetermined speed based on the intersection of the characteristic curve of the compressor at a predetermined speed and the common operating line of the compressor, wherein the common operating line is the steady-state operating point trajectory determined by the matching relationship of the entire engine; determining the angle of attack of the rotor blade mid-diameter section of the compressor corresponding to the operating point based on the difference between the blade geometric inlet angle and the inlet relative airflow angle of the rotor blade mid-diameter section of the compressor; and, if the determined angle of attack does not meet the predetermined angle range, adjusting the installation angle of the adjustable guide vanes and adjustable stator vanes of the compressor, and adjusting the venting volume, so that the adjusted angle of attack meets the predetermined angle range, and the stability margin at the predetermined speed is greater than or equal to the predetermined margin.

[0034] The following is through Figures 2-4 The compressor control method of guide vane coupling and venting coupling according to the embodiments of this disclosure will be described in detail.

[0035] Figure 1 A flowchart of a compressor control method for guide vane coupling and venting coupling according to an embodiment of the present disclosure is shown.

[0036] like Figure 1 As shown, the compressor control method of guide vane coupling and venting coupling in this embodiment includes operations S110 to S130.

[0037] When operating S110, the operating point of the compressor at the predetermined speed is determined by the intersection of the characteristic curve of the compressor at the predetermined speed and the common operating line of the compressor. The common operating line is the steady-state operating point trajectory determined by the matching relationship of the entire engine.

[0038] The characteristic curves may include a flow-to-total-pressure ratio curve and a flow-to-efficiency curve. Flow rate is the x-axis of the characteristic curve, and total pressure ratio and efficiency are the y-axis of the two curves, respectively. Flow rate can be understood as the mass flow rate of gas in the compressor, with units of kg / s. Total pressure ratio can be understood as the ratio of the total pressure at the compressor outlet to the total pressure at the compressor inlet. Total temperature ratio can be understood as the ratio of the total temperature at the compressor outlet to the total temperature at the compressor inlet. Efficiency can be understood as the degree to which the compressor effectively converts input work into useful pressurization capacity, and can be calculated from the total temperature ratio and the total pressure ratio; this disclosure does not impose specific limitations on this.

[0039] The predetermined speed can be a key speed value that is pre-set based on the engine's overall design specifications, the compressor's aerodynamic performance requirements, and the actual operating conditions, covering the entire operating speed range of the compressor, including but not limited to the compressor's starting speed, idle speed, partial load speed, and rated load speed.

[0040] Operating points can include, but are not limited to, information such as flow rate, total pressure ratio, and efficiency.

[0041] This disclosure does not specify how to determine the intersection point between the characteristic curve and the common operating line. For example, a software-coupled iterative calculation method can be used: The compressor characteristic curve at a predetermined speed is generated using a flow calculation tool, imported into the overall system performance software, and the system matching constraints are input. The software iterates according to the coupling relationship to obtain the common operating line, and then uses a built-in numerical convergence algorithm to solve for the curve intersection point to determine the operating point parameters. A graphical analysis method involves plotting the compressor characteristic curve at the predetermined speed and the system's common operating line on the same two-dimensional coordinate system. The intersection point is determined using plotting software functions, manual interpolation, or geometric measurement. Combined with supplementary data, the parameters are completed to obtain the operating point. An analytical equation solution method involves establishing analytical equations for the compressor characteristics and the system's common operating line. After solving these equations simultaneously, the flow rate solution is obtained through algebraic elimination, numerical root solving, etc., and then substituted into the equations to complete the parameters and determine the operating point.

[0042] In operation S120, the angle of attack of the compressor rotor blade mid-diameter section corresponding to the operating point is determined based on the difference between the blade geometric inlet angle and the inlet relative airflow angle of the compressor rotor blade mid-diameter section.

[0043] For the operating point at the predetermined compressor speed, focusing on the cross section at the middle diameter position of the rotor blade, the angle of attack of the rotor blade's middle diameter section that matches the current operating point can be accurately determined by calculating the difference between the relative inlet airflow angle and the geometric inlet angle. This provides a core basis for subsequent judgment on whether the stability margin meets the conditions.

[0044] Figure 2 A schematic diagram of the angle of attack of an adjustable guide / stator rotor blade according to an embodiment of the present disclosure is shown.

[0045] like Figure 2 As shown, The inlet relative airflow angle is the angle between the airflow direction and the blade rotation direction when the airflow enters the rotating rotor blade. The inlet geometric angle is the mid-diameter section of the rotor blade. It is a fixed physical shape angle of the blade itself. It is the angle between the tangent direction of the mid-arc of the leading edge of the blade and the direction of the rotor's rotation circumference. The angle of attack of the mid-diameter section is the angle between the relative airflow direction and the tangent direction of the leading edge of the blade's mid-curve. It is also the difference between the relative airflow angle and the geometric inlet angle, as shown in equation (1) below:

[0046] (1).

[0047] When operating S130, if it is determined that the angle of attack does not meet the predetermined angle range, the installation angle of the adjustable guide vanes and adjustable stationary vanes of the compressor, as well as the venting volume, are adjusted to make the adjusted angle of attack meet the predetermined angle range, and the stability margin at the predetermined speed is greater than or equal to the predetermined margin.

[0048] The predetermined angle range can be set based on aerodynamic design theories and overall machine requirements. It is a reasonable range of the rotor blade mid-section angle of attack pre-set to ensure optimal aerodynamic performance of the compressor rotor blades and suppress flow separation. For example, the predetermined angle range can be -2°≤i≤2°, but it is not limited to this.

[0049] When the angle of attack of the rotor blade's mid-diameter section does not meet the predetermined angle range (i.e., -2°≤i≤2°), the airflow direction towards the rotor blades can be optimized by changing the installation angles of the compressor's adjustable guide vanes and adjustable stator vanes. Additionally, the airflow within the compressor can be adjusted by regulating the venting volume to discharge some of the compressed air. These two adjustment methods work together, complementing each other to ensure that the adjusted angle of attack meets the predetermined angle range and that the stability margin at the predetermined speed is greater than or equal to the predetermined margin, thus guaranteeing stable and efficient compressor operation.

[0050] According to embodiments of this disclosure, the intersection of the characteristic curve of the compressor operating at a predetermined speed and the common operating line is determined as the operating point, which determines the angle of attack distribution of the compressor rotor blades. The angle of attack is a parameter affecting flow stability. Therefore, by adjusting the installation angles of the adjustable guide vanes and adjustable stator vanes, and by adjusting the bleed volume, the angle of attack can be made to meet a predetermined angle range, thereby controlling the stability margin to be greater than or equal to the predetermined margin. Because the guide vane and stator vane adjustment and bleed coupling can work synergistically, the compressor flow field is reconstructed from the inlet dimension (optimizing the inlet angle of attack) and the outlet dimension (adjusting the flow back pressure), achieving precise matching of the aerodynamic loads at the front and rear ends. This results in better suppression of flow separation and increased stability margin compared to a single control method. Furthermore, this synergistic mechanism follows the principle of minimum control cost, achieving the stability enhancement target with smaller guide vane and stator vane angles and less bleed volume. Thus, while ensuring high stability, it minimizes the efficiency loss caused by bleed, improving the overall efficiency and economy of the compressor.

[0051] According to embodiments of this disclosure, when performing such Figure 1 Before operation S110, the compressor control method of guide vane and stator joint adjustment and venting coupling may also include the following operation: under the condition that the compressor guide vanes and stator vanes are not adjusted and there is no venting, the characteristic curve is calculated using aerodynamic analysis tools.

[0052] Under the basic operating conditions where the compressor is at a predetermined speed, and its guide vanes and stator vanes remain in their initial state without any angle adjustment, and no venting operation is performed to ensure complete airflow within the compressor, analysis tools conforming to industry aerodynamic calculation standards, such as compressor flow calculation programs and three-dimensional numerical models, can be used to accurately simulate the flow process of airflow within the compressor channel and calculate characteristic curves that reflect the changes in the compressor's core aerodynamic performance, such as flow rate, total pressure ratio, and efficiency, at that speed.

[0053] Under the basic operating conditions of predetermined speed, unadjusted guide vanes and stator vanes, and no venting, the characteristic curves obtained through aerodynamic analysis tools can accurately reflect the inherent aerodynamic performance of the compressor. This provides a unified and reliable benchmark for subsequent positioning of the operating point, calculation of the angle of attack, and implementation of coupled regulation, ensuring precise and effective control and avoiding the blindness of traditional regulation.

[0054] According to embodiments of this disclosure, the engine assembly may include at least: a compressor, a combustion chamber, a turbine, a turbine guide vane, and a nozzle. This disclosure does not specifically limit the specific arrangement or connection method between the compressor, combustion chamber, turbine, turbine guide vane, and nozzle in the engine assembly.

[0055] In execution such Figure 1 Before operation S110, the compressor control method of guide vane joint adjustment and exhaust coupling may also include the following operations: based on the characteristics and geometric parameters of the compressor, combustion chamber, turbine, turbine guide vane, and nozzle, determine a set of steady-state operating points that satisfy the conditions of continuous flow and power balance of the entire engine. Each of the multiple steady-state operating points in the set of steady-state operating points is a point on the characteristic curve of the compressor at the corresponding speed; the connection trajectory of the points on the multiple characteristic curves corresponding to the steady-state operating points is determined as a common working line.

[0056] The steady-state operating point can be a compressor operating state point that satisfies the constraints of continuous flow and power balance of the whole engine based on the characteristics and geometric parameters of the engine. Each steady-state operating point corresponds to a specific point on the characteristic curve of the compressor at a certain speed.

[0057] For example, for a certain aero-engine, the characteristics and geometric parameters of the compressor, combustion chamber, turbine, turbine guide vane and nozzle of this engine are input into the overall performance calculation software for analysis. Five operating state points that meet the two core constraints of continuous flow and power balance are selected. These five operating state points are on the characteristic curves at different speeds. Connecting these five points yields the common operating line.

[0058] To illustrate, overall performance calculation software can employ various methods for calculating steady-state operating points. For example, a simplified analytical calculation can be used, establishing a set of core algebraic equations describing flow continuity and power balance based on classical aerodynamic and thermodynamic formulas for each component of the engine. By directly solving these equations, a series of steady-state operating points can be quickly obtained. This method is fast and its principle is clear. Alternatively, a numerical simulation of the entire engine can be used, constructing physical models of each component and coupling them into a complete virtual engine within a digital environment. By adjusting the operating parameters of the virtual engine, the steady-state operating points can be directly read from the simulation results. This method more accurately reflects the complex internal flow and heat transfer processes.

[0059] The common operating line determined by the above method accurately reflects the compressor's actual operating path. This ensures that subsequent adjustments to the compressor's guide vanes and stator vanes, as well as interstage venting, are based on a realistic and reliable operating condition. This avoids problems such as poor matching with the overall engine, unattainable performance, or an excessively narrow stable operating range caused by designing the compressor in isolation, thus improving the compatibility and effectiveness of the compressor and the overall engine design.

[0060] According to embodiments of this disclosure, when performing such Figure 1 During operation S130, the compressor control method of guide vane and stator joint adjustment and venting coupling may also include the following operations: based on the deviation between the angle of attack and the predetermined angle range, the installation angle of the adjustable guide vane and the adjustable stator vane is adjusted first to adjust the angle of attack; if it is determined that the angle of attack still does not meet the predetermined angle range after adjustment, the venting volume is adjusted.

[0061] First, determine the specific deviation between the current rotor blade mid-diameter section angle of attack and the predetermined angle range. Prioritize adjusting the installation angles of the compressor's adjustable guide vanes and adjustable stator vanes. By changing their installation posture, optimize the airflow direction towards the rotor blades, thereby specifically correcting the angle of attack. After adjusting the guide vane and stator vane installation angles, recheck whether the angle of attack falls within the predetermined angle range. If the angle of attack still does not meet the requirements, supplementary control is performed by adjusting the venting volume, i.e., discharging a portion of the compressed air to adjust the airflow within the compressor, ensuring that the angle of attack ultimately reaches the predetermined standard.

[0062] According to embodiments of this disclosure, when adjusting the installation angles of the adjustable guide vanes and adjustable stator vanes, the adjustment method can be flexibly set according to the magnitude of the deviation between the angle of attack and the predetermined angle range, and the compressor operating conditions. If the angle of attack deviation is small (e.g., ±0.5°~±1°), a small-amplitude gradual adjustment is adopted to gradually correct the airflow injection direction and avoid sudden changes in the flow field; if the deviation is large (e.g., exceeding ±1°), a targeted large-amplitude adjustment can be performed to quickly pull the angle of attack back to a reasonable range.

[0063] The venting volume can also be adjusted through various precise control methods. For example, quantitative calculation-based adjustment determines the angle of attack adjustment amount based on the deviation between the adjusted angle of attack and the predetermined range. Combined with parameters such as the rotor blade inlet axial velocity and the inlet relative airflow angle, the inlet axial velocity and pre-venting volume are calculated, and the venting operation is performed according to the calculated value. Rapid query-based adjustment determines the correspondence between the angle of attack deviation and the venting volume through experiments. The appropriate venting volume is directly looked up in the table according to the actual angle of attack deviation, improving the adjustment response speed. Dynamic feedback-based adjustment continuously monitors the angle of attack change during the venting process and adjusts the venting volume in real time until the angle of attack meets the predetermined range.

[0064] The angle of attack is optimized by adjusting the installation angles of the adjustable guide vanes and adjustable stator vanes. This operation is direct and easy to control, so it is prioritized for adjustment. If the angle of attack still does not meet the predetermined angle range after adjustment, the venting volume is then adjusted. This allows the rotor blade angle of attack to be quickly adjusted to the predetermined angle range without wasting energy, balancing ease of operation with performance optimization.

[0065] The aforementioned adjustment of the venting volume includes: determining the required angle of attack adjustment amount based on the deviation between the adjusted angle of attack and the predetermined angle range; determining the inlet relative airflow angle after pre-venting based on the angle of attack adjustment amount and the inlet relative airflow angle; determining the inlet axial velocity after pre-venting based on the compressor rotor blade inlet axial velocity corresponding to the operating point, the inlet relative airflow angle after pre-venting, and the inlet relative airflow angle; determining the pre-venting volume based on the compressor inlet flow rate corresponding to the operating point, the inlet axial velocity after pre-venting, and the inlet axial velocity; and performing the venting operation based on the pre-venting volume.

[0066] Figure 3 A schematic diagram showing the rotor intake angle change caused by interstage pre-bleeding according to an embodiment of the present disclosure is shown.

[0067] like Figure 3 As shown, the air intake flow rate at the operating point without venting is known from the calculation results of the aerodynamic analysis tool. The axial velocity of the rotor blades during air intake is The relative airflow angle at the rotor blade inlet is Let the pre-venting volume be... After pre-venting, the axial velocity of the rotor blades is... After pre-venting, the relative airflow angle at the rotor blade inlet is The change in the relative airflow angle at the rotor blade inlet As shown in equation (2):

[0068] (2).

[0069] Based on the deviation between the angle of attack and the predetermined angle range that still exists after adjusting the installation angles of the guide vanes and stator vanes, the required angle of attack adjustment amount to achieve the target angle of attack is determined, i.e. Then, based on this angle of attack adjustment amount... relative airflow angle with the current rotor blade inlet Calculate and determine the inlet relative airflow angle of the rotor blades after pre-venting. As shown in equation (3):

[0070] (3).

[0071] Based on the axial velocity of the rotor blades during air intake , inlet relative airflow angle after pre-venting and the inlet relative airflow angle Determine the intake axial velocity after pre-bleeding. As shown in equation (4):

[0072] (4).

[0073] Then, based on the initial compressor inlet flow rate corresponding to the operating point... 1. Intake axial velocity after pre-bleeding and original intake axial velocity The required pre-venting volume is quantitatively determined by adapting the flow rate to the axial velocity. As shown in equation (5):

[0074] (5).

[0075] By setting The amount of gas released can achieve this. The angle of attack adjustment range.

[0076] Finally, a precise venting operation is performed according to the calculated pre-venting volume to achieve targeted control of the flow field inside the compressor.

[0077] This method overcomes the lag and blindness of traditional "trial and error" or "experience-based" venting, and achieves precise, rapid and minimally disturbed active intervention in compressor flow. Thus, while effectively suppressing stall and widening the stability margin, it minimizes unnecessary venting losses and optimizes the overall efficiency of the engine.

[0078] Given that the angle of attack meets the predetermined angle range, the stability margin at the predetermined speed is determined based on the operating parameters of the near stall point and the operating point on the characteristic curve.

[0079] Operating parameters may include, but are not limited to, parameters such as flow rate and total pressure ratio.

[0080] The near-stall point is the inherent critical operating point on the compressor characteristic curve. It refers to the limit point at which the compressor is about to enter an unstable state such as stall or surge, but still maintains stable operation.

[0081] The stability margin SM at each speed can be calculated based on the total pressure ratio and flow rate data contained at the operating point and near stall point, as shown in the following equation (6):

[0082] (6)

[0083] in, Near stall pressure ratio, The flow rate near the stall point. The operating point pressure ratio, For the working point flow rate.

[0084] Determine whether the stability margin SM meets the target value SM. obj If this condition is not met, i.e., SM < SM obj Then, readjust the guide vane and stator vane angles and the air release rate until the conditions are met. Target stability margin SM obj It is determined based on the design specifications of different engines and gas turbines. Generally, the target stability margin SM obj The value range is 10% to 15%.

[0085] By calculating the stability margin, the qualitative judgment of compressor stability is transformed into a quantifiable and precise real-time monitoring indicator, ensuring compressor stability while improving efficiency.

[0086] Figure 4 A flowchart of a compressor control method for guide vane coupling and venting coupling according to another embodiment of the present disclosure is shown.

[0087] like Figure 4 As shown, the compressor control method of guide vane joint adjustment and exhaust coupling includes: first, determining the initial characteristic curve of the compressor in the unadjusted state; obtaining the operating point at each speed based on the intersection of this characteristic curve and the common operating line of the entire engine; then calculating the angle of attack value i of the rotor blade mid-diameter section at the corresponding operating point, and determining whether it is within the predetermined optimal angle of attack range (-2°~2°); if the angle of attack meets the requirements, further calculating the stability margin SM at the current speed, and comparing it with the target stability margin SM. obj If the stability margin meets the requirements, the design process ends and the final coupled stability expansion scheme is output. If the angle of attack does not meet the requirements or the stability margin is insufficient, the process returns to the steps of coordinating and adjusting the installation angle of the guide vanes and stator vanes with the interstage venting volume, and the characteristic calculation and operating point acquisition are performed again until the angle of attack and stability margin both meet the set requirements.

[0088] According to an embodiment of this disclosure, when there are multiple rotor blades, if it is determined that the angle of attack of the mid-diameter sections of the multiple rotor blades all satisfy the predetermined angle range, then the angle of attack is determined to satisfy the predetermined angle range.

[0089] When there are multiple rotor blades in the compressor, the angle of attack of the mid-diameter section of each rotor blade is detected. If the detection confirms that the angle of attack of the mid-diameter section of each rotor blade meets the predetermined angle range, it can be determined that the angle of attack of the corresponding operating point of the current compressor meets the requirements of the predetermined angle range.

[0090] By requiring all rotor blades to meet the required angle of attack, the overall aerodynamic status of the compressor is monitored, ensuring the overall stability of the compressor more comprehensively and reliably.

[0091] According to embodiments of this disclosure, when there are multiple rotor blades, if it is determined that the angle of attack of at least one rotor blade's mid-diameter section does not meet a predetermined angle range, the installation angles of the compressor's adjustable guide vanes and the adjustable stator vanes of at least one rotor blade's corresponding stage, as well as the venting volume of the corresponding stage, are coordinated and adjusted.

[0092] When it is detected that the angle of attack of at least one rotor blade in a multi-rotor blade section does not meet the predetermined angle range, a targeted adjustment method is used for control. First, the adjustable guide vane installation angle of the compressor is adjusted to optimize the overall airflow direction. Then, the stage to which the rotor blade with the substandard angle of attack belongs is precisely located, and the adjustable stator installation angle of the corresponding stage is adjusted simultaneously. At the same time, the venting volume of the corresponding stage is adjusted for the substandard stage. By discharging part of the compressed air in that stage, the airflow rate within that stage is adjusted.

[0093] This strategy achieves a shift from a holistic to a localized approach, enabling the rapid and precise elimination of localized problems with minimal overall performance cost, thereby improving the compressor's stability recovery efficiency.

[0094] According to another embodiment of this disclosure, the installation angles of the adjustable guide vanes and adjustable stator vanes, and the interstage venting volume determined by the compressor control method of the above-described guide vane-stator joint adjustment and venting coupling, can be used as core design parameters for the compressor's structural and aerodynamic design. The adjustment mechanisms of the guide vanes and stator vanes, the blade installation reference, and the angle adjustment stroke are designed according to the determined installation angles. The position, flow area, and control valve structure of the interstage venting port are designed according to the precisely calculated venting volume requirements, ensuring that the compressor can achieve aerodynamic performance optimization under all operating conditions through preset joint adjustment and venting strategies.

[0095] The optimized compressor is integrated with engine components such as the combustion chamber, turbine, and intake / exhaust system to achieve efficient operation of the engine across all operating conditions, including start-up, idling, partial load, and rated load, relying on the coupling characteristics of the compressor. This ultimately improves the overall performance and reliability of aero engines or gas turbines and is applicable to the design and manufacture of various multi-stage axial flow compressors with adjustable inlet guide vanes.

[0096] Based on the compressor control method of guide vane-stationary vane coordination and venting coupling described above, this disclosure also provides a compressor design device of guide vane-stationary vane coordination and venting coupling. The following will be combined with... Figure 5 The device is described in detail.

[0097] Figure 5 A structural block diagram of a compressor design device with guide vane adjustment and venting coupling according to an embodiment of the present disclosure is shown.

[0098] like Figure 5 As shown, the compressor design device 500 of the guide vane coupling and venting coupling in this embodiment includes a first determining module 510, a second determining module 520 and a coordination and adjustment module 530.

[0099] The first determining module 510 is used to determine the operating point of the compressor at the predetermined speed based on the intersection of the characteristic curve of the compressor at the predetermined speed and the common operating line of the compressor. The common operating line is the steady-state operating point trajectory determined by the matching relationship of the engine as a whole.

[0100] The second determining module 520 is used to determine the angle of attack of the compressor rotor blade mid-diameter section corresponding to the operating point based on the difference between the blade geometric inlet angle and the inlet relative airflow angle of the compressor rotor blade mid-diameter section.

[0101] The coordination and adjustment module 530 is used to adjust the installation angle of the adjustable guide vanes and adjustable stator vanes of the compressor, as well as the venting volume, so that the adjusted angle of attack meets the predetermined angle range and the stability margin at the predetermined speed is greater than or equal to the predetermined margin when it is determined that the angle of attack does not meet the predetermined angle range.

[0102] According to embodiments of this disclosure, the first determining module 510 includes an acquisition submodule and a third determining submodule. The acquisition submodule is used to calculate characteristic curves using aerodynamic analysis tools under the conditions of a predetermined speed, with the compressor's guide vanes and stator vanes not adjusted and no bleed. The third determining submodule is used to determine a set of steady-state operating points that satisfy the conditions of continuous flow and power balance of the entire engine, based on the characteristics and geometric parameters of the compressor, combustion chamber, turbine, turbine guide vane, and nozzle. Each of the multiple steady-state operating points in the set is a point on the characteristic curve of the compressor at the corresponding speed; the connection trajectory of the points on the multiple characteristic curves corresponding to the steady-state operating points is determined as a common working line.

[0103] The coordination and adjustment module 530 includes a first adjustment submodule and a fourth determination submodule. The first adjustment submodule is used to adjust the installation angles of the adjustable guide vanes and adjustable stator vanes first, based on the deviation between the angle of attack and a predetermined angle range, to adjust the angle of attack; if the angle of attack still does not meet the predetermined angle range after adjustment, the venting volume is adjusted. The fourth determination submodule is used to determine the stability margin at a predetermined speed, based on the operating parameters of the near-stall point and the operating point on the characteristic curve, when the angle of attack meets the predetermined angle range.

[0104] The first adjustment submodule includes an execution unit. The execution unit is used to determine the required angle-of-attack adjustment amount based on the deviation between the adjusted angle of attack and a predetermined angle range; to determine the inlet relative airflow angle after pre-venting based on the angle-of-attack adjustment amount and the inlet relative airflow angle; to determine the inlet axial velocity after pre-venting based on the compressor rotor blade inlet axial velocity corresponding to the operating point, the inlet relative airflow angle after pre-venting, and the inlet relative airflow angle; to determine the pre-venting amount based on the compressor inlet flow rate corresponding to the operating point, the inlet axial velocity after pre-venting, and the inlet axial velocity; and to execute the venting operation based on the pre-venting amount.

[0105] When the rotor blades consist of multiple blades, the compressor design device for the coordinated adjustment and venting of guide vanes and stator blades includes a fifth determining module. This fifth determining module is used to determine the case where the angle of attack meets the predetermined angle range, provided that the angles of attack of the mid-diameter sections of the multiple rotor blades all meet the predetermined angle range.

[0106] The fifth determining module includes a second adjustment submodule. The second adjustment submodule is used to coordinate and adjust the installation angle of the adjustable guide vanes of the compressor and the adjustable stator vanes of the corresponding stage of at least one rotor blade when the angle of attack of the mean diameter section of at least one rotor blade does not meet the predetermined angle range, and to adjust the venting volume of the corresponding stage.

[0107] According to embodiments of this disclosure, any plurality of modules among the first determining module 510, the second determining module 520, and the coordination and adjustment module 530 can be combined into one module, or any one of these modules can be split into multiple modules. Alternatively, at least part of the functionality of one or more of these modules can be combined with at least part of the functionality of other modules and implemented in one module. According to embodiments of this disclosure, at least one of the first determining module 510, the second determining module 520, and the coordination and adjustment module 530 can be at least partially implemented as hardware circuitry, such as a field-programmable gate array (FPGA), a programmable logic array (PLA), a system-on-a-chip, a system-on-a-substrate, a system-on-package, an application-specific integrated circuit (ASIC), or implemented by any other reasonable means of integrating or packaging circuitry, or implemented in any one of software, hardware, and firmware methods, or in a suitable combination of any of these. Alternatively, at least one of the first determining module 510, the second determining module 520, and the coordination and adjustment module 530 can be at least partially implemented as a computer program module, which, when run, can perform corresponding functions.

[0108] Figure 6 A block diagram of an electronic device suitable for implementing a compressor control method for guide vane coupling and venting coupling according to an embodiment of the present disclosure is shown.

[0109] like Figure 6 As shown, an electronic device 600 according to an embodiment of the present disclosure includes a processor 601, which can perform various appropriate actions and processes according to a program stored in a read-only memory ROM 602 or a program loaded from a storage portion 608 into a random access memory RAM 603. The processor 601 may include, for example, a general-purpose microprocessor (e.g., a CPU), 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 601 may also include onboard memory for caching purposes. The processor 601 may include a single processing unit or multiple processing units for performing different actions of the method flow according to an embodiment of the present disclosure.

[0110] RAM 603 stores various programs and data required for the operation of electronic device 600. Processor 601, ROM 602, and RAM 603 are interconnected via bus 604. Processor 601 performs various operations of the method flow according to embodiments of the present disclosure by executing programs in ROM 602 and / or RAM 603. It should be noted that the programs may also be stored in one or more memories other than ROM 602 and RAM 603. Processor 601 may also perform various operations of the method flow according to embodiments of the present disclosure by executing programs stored in said one or more memories.

[0111] According to embodiments of this disclosure, the electronic device 600 may further include an input / output (I / O) interface 605, which is also connected to a bus 604. The electronic device 600 may also include one or more of the following components connected to the input / output (I / O) interface 605: an input section 606 including a keyboard, mouse, etc.; an output section 607 including a cathode ray tube (CRT), liquid crystal display (LCD), etc., and a speaker, etc.; a storage section 608 including a hard disk, etc.; and a communication section 609 including a network interface card such as a LAN card, modem, etc. The communication section 609 performs communication processing via a network such as the Internet. A drive 610 is also connected to the input / output (I / O) interface 605 as needed. A removable medium 611, such as a disk, optical disk, magneto-optical disk, semiconductor memory, etc., is installed on the drive 610 as needed so that computer programs read from it can be installed into the storage section 608 as needed.

[0112] This disclosure also provides a computer-readable storage medium, which may be included in the device / apparatus / system described in the above embodiments; or it may exist independently and not assembled into the device / apparatus / system. The computer-readable storage medium carries one or more programs that, when executed, implement the method according to the embodiments of this disclosure.

[0113] According to embodiments of this disclosure, the computer-readable storage medium may be a non-volatile computer-readable storage medium, such as including, but not limited to: portable computer disks, hard disks, random access memory (RAM), read-only memory (ROM), erasable programmable read-only memory (EPROM or flash memory), portable compact disk read-only memory (CD-ROM), optical storage devices, magnetic storage devices, or any suitable combination thereof. In this disclosure, the computer-readable storage medium may be any tangible medium that contains or stores a program that can be used by or in conjunction with an instruction execution system, apparatus, or device. For example, according to embodiments of this disclosure, the computer-readable storage medium may include ROM 602 and / or RAM 603 and / or one or more memories other than ROM 602 and RAM 603 described above.

[0114] Embodiments of this disclosure also include a computer program product comprising a computer program containing program code for performing the methods shown in the flowchart. When the computer program product is run on a computer system, the program code is used to cause the computer system to implement the methods provided in the embodiments of this disclosure.

[0115] When the computer program is executed by the processor 601, it performs the functions defined in the system / apparatus of this disclosure embodiments. According to embodiments of this disclosure, the systems, apparatuses, modules, units, etc., described above can be implemented by computer program modules.

[0116] In one embodiment, the computer program may rely on a tangible storage medium such as an optical storage device or a magnetic storage device. In another embodiment, the computer program may also be transmitted and distributed in the form of signals over a network medium, and downloaded and installed via the communication section 609, and / or installed from the removable medium 611. The program code contained in the computer program can be transmitted using any suitable network medium, including but not limited to: wireless, wired, etc., or any suitable combination thereof.

[0117] In such an embodiment, the computer program can be downloaded and installed from a network via the communication section 609, and / or installed from the removable medium 611. When the computer program is executed by the processor 601, it performs the functions defined in the system of this disclosure embodiment. According to embodiments of this disclosure, the systems, devices, apparatuses, modules, units, etc., described above can be implemented by computer program modules.

[0118] According to embodiments of this disclosure, program code for executing the computer programs provided in embodiments of this disclosure can be written in any combination of one or more programming languages. Specifically, these computational programs can be implemented using high-level procedural and / or object-oriented programming languages, and / or assembly / machine languages. Programming languages ​​include, but are not limited to, languages ​​such as Java, C++, Python, "C", or similar programming languages. The program code can execute entirely on a user's computing device, partially on a user's device, partially on a remote computing device, or entirely on a remote computing device or server. In cases involving remote computing devices, the remote computing device can be connected to the user's computing device via any type of network, including a local area network (LAN) or a wide area network (WAN), or it can be connected to an external computing device (e.g., via the Internet using an Internet service provider).

[0119] The flowcharts and block diagrams in the accompanying drawings illustrate the architecture, functionality, and operation of possible implementations of systems, methods, and computer program products according to various embodiments of this disclosure. In this regard, each block in a flowchart or block diagram may represent a module, segment, or portion of code containing one or more executable instructions for implementing a specified logical function. It should also be noted that in some alternative implementations, the functions indicated in the blocks may occur in a different order than those indicated in the drawings. For example, two consecutively indicated blocks may actually be executed substantially in parallel, and they may sometimes be executed in reverse order, depending on the functions involved. It should also be noted that each block in a block diagram or flowchart, and combinations of blocks in a block diagram or flowchart, may be implemented using a dedicated hardware-based system that performs the specified function or operation, or using a combination of dedicated hardware and computer instructions.

[0120] Those skilled in the art will understand that the features described in the various embodiments of this disclosure can be combined and / or combined in various ways, even if such combinations or combinations are not explicitly described in this disclosure. In particular, the features described in the various embodiments of this disclosure can be combined and / or combined in various ways without departing from the spirit and teachings of this disclosure. All such combinations and / or combinations fall within the scope of this disclosure.

[0121] The embodiments of this disclosure have been described above. However, these embodiments are for illustrative purposes only and are not intended to limit the scope of this disclosure. Although various embodiments have been described above, this does not mean that the measures in the various embodiments cannot be used advantageously in combination. Various substitutions and modifications can be made by those skilled in the art without departing from the scope of this disclosure, and all such substitutions and modifications should fall within the scope of this disclosure.

Claims

1. A compressor control method based on guide vane-stationary vane coupling and venting coupling, characterized in that, The method includes: The operating point of the compressor at the predetermined speed is determined by the intersection of the characteristic curve of the compressor at the predetermined speed and the common operating line of the compressor. The common operating line is the steady-state operating point trajectory determined by the matching relationship of the engine as a whole. The angle of attack of the compressor rotor blade mid-diameter section corresponding to the operating point is determined based on the difference between the blade geometric inlet angle and the inlet relative airflow angle of the compressor rotor blade mid-diameter section. If the angle of attack does not meet the predetermined angle range, the installation angles of the adjustable guide vanes and adjustable stator vanes of the compressor, as well as the venting volume, are adjusted to make the adjusted angle of attack meet the predetermined angle range, and the stability margin at the predetermined speed is greater than or equal to the predetermined margin.

2. The method according to claim 1, characterized in that, The adjustment of the installation angle of the adjustable guide vanes and adjustable stationary vanes of the compressor, and the adjustment of the venting volume include: Based on the deviation between the angle of attack and the predetermined angle range, the installation angles of the adjustable guide vane and the adjustable stator vane are adjusted first to adjust the angle of attack; If the angle of attack still does not meet the predetermined angle range after adjustment, adjust the venting volume.

3. The method according to claim 2, characterized in that, The adjustment of the venting volume includes: Based on the deviation between the adjusted angle of attack and the predetermined angle range, the required angle of attack adjustment amount is determined; Based on the angle of attack adjustment and the inlet relative airflow angle, determine the inlet relative airflow angle after pre-venting; The inlet axial velocity after pre-venting is determined based on the rotor blade inlet axial velocity of the compressor corresponding to the operating point, the inlet relative airflow angle after pre-venting, and the inlet relative airflow angle. The pre-venting amount is determined based on the compressor's inlet flow rate corresponding to the operating point, the inlet axial velocity after pre-venting, and the inlet axial velocity. Based on the pre-venting volume, perform the venting operation.

4. The method according to claim 1, characterized in that, The method further includes: Given that the angle of attack meets the predetermined angle range, the stability margin at the predetermined speed is determined based on the operating parameters of the near stall point and the operating point on the characteristic curve.

5. The method according to claim 1, characterized in that, The method further includes: Under the conditions of no adjustment of the compressor's guide vanes and stator vanes at the predetermined speed and no venting, the characteristic curve is calculated using aerodynamic analysis tools.

6. The method according to claim 1, characterized in that, The engine assembly includes at least: the compressor, combustion chamber, turbine, turbine guide vane, and nozzle; The method further includes: Based on the characteristics and geometric parameters of the compressor, the combustion chamber, the turbine, the turbine guide vane, and the nozzle, a set of steady-state operating points that satisfy the conditions of continuous flow and power balance of the engine are determined. Each of the multiple steady-state operating points in the set of steady-state operating points is a point on the characteristic curve of the compressor at the corresponding speed. The trajectory connecting the points on the multiple characteristic curves that correspond to the steady-state operating point is determined as the common working line.

7. The method according to any one of claims 1 to 6, characterized in that, The rotor blades comprise a plurality of blades, and the method further includes: If the angle of attack of the mean diameter sections of the multiple rotor blades all satisfy the predetermined angle range, then the angle of attack is determined to satisfy the predetermined angle range.

8. The method according to claim 7, characterized in that, The method further includes: If it is determined that the angle of attack of at least one rotor blade in the mean diameter section of the plurality of rotor blades does not meet the predetermined angle range, the installation angle of the adjustable guide vane of the compressor and the adjustable stationary vane of the corresponding stage of the at least one rotor blade, and the exhaust volume of the corresponding stage are adjusted in a coordinated manner.

9. A compressor control device based on guide vane-stationary vane coordination and venting coupling, characterized in that, The device includes: The first determining module is used to determine the operating point of the compressor at the predetermined speed based on the intersection of the characteristic curve of the compressor at the predetermined speed and the common operating line of the compressor, wherein the common operating line is the steady-state operating point trajectory determined by the matching relationship of the engine as a whole. The second determining module is used to determine the angle of attack of the rotor blade mid-diameter section of the compressor corresponding to the operating point based on the difference between the blade geometric inlet angle and the inlet relative airflow angle of the rotor blade mid-diameter section of the compressor. The coordination and adjustment module is used to adjust the installation angle of the adjustable guide vanes and adjustable stator vanes of the compressor, and adjust the venting volume, so that the adjusted angle of attack meets the predetermined angle range and the stability margin at the predetermined speed is greater than or equal to the predetermined margin, when it is determined that the angle of attack does not meet the predetermined angle range.

10. An electronic device, comprising: One or more processors; Memory, used to store one or more computer programs. The characteristic feature is that the one or more processors execute the one or more computer programs to implement the steps of the method according to any one of claims 1 to 8.

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