Water intake estimation and flow control method for aircraft engine during wing washing

Abstract

The application discloses an aero-engine in-wing cleaning water intake estimation and flow control method. Including: in the process of cleaning the aero-engine, the total jet flow of the nozzle, the average axial flow velocity of the jet flow and the actual speed of the aero-engine in the cleaning state are filtered and denoised in each control cycle, and the target control parameter is obtained; according to the target control parameter and the key geometric parameter of the aero-engine, the static shielding of the blade and the rotating dynamic sweeping shielding effect are combined, and the effective jet flow that can be sprayed into the aero-engine channel under the target total jet flow of the nozzle is calculated in real time; according to the difference value between the effective jet flow and the preset target cleaning water flow, the output frequency of the frequency conversion water pump in the aero-engine cleaning system is controlled based on the embedded control algorithm. The embodiment improves the water intake estimation accuracy and cleaning quality.

Description

TECHNICAL FIELD

[0001] The present application relates to the field of aero-engine maintenance and cleaning, and particularly relates to a water intake estimation and flow control method for aero-engine in-flight cleaning. BACKGROUND

[0002] As the core power device of an aircraft, an aero-engine is operated under complex and variable working conditions for a long time, and a large amount of inclusions, oil stains and marine salt in the air can be sucked into the engine, which can cause the aerodynamic performance of the engine compressor blade surface to deteriorate, further cause the compressor surge margin to decrease and the exhaust temperature to abnormally increase, and cause the exhaust gas temperature margin (EGTM) to decrease and the overall thermal efficiency to significantly decrease. Therefore, regular in-flight cleaning or chemical cleaning has become a key conventional maintenance method for removing dirt and prolonging in-flight operation life.

[0003] In the research of in-flight cleaning technology, the existing technology includes water washing time decision and hardware static structure improvement. On the one hand, the decision mode is changed from the traditional fixed time or regular water washing mode to the dynamic adjustment of the water washing time based on the performance monitoring state of the aircraft, which can prolong the engine disassembly interval and reduce the operation and maintenance cost of the airline. On the other hand, by improving the hardware structure of the cleaning system or researching the influence of the structure parameters (such as aperture and jet angle) of the in-flight water washing nozzle on the jet flow pattern, the cleaning efficiency can be improved.

[0004] However, the existing in-flight cleaning technology only monitors the total jet flow of the nozzle by the flow meter of the air inlet, and does not consider the effective water intake into the engine, and lacks an effective and accurate water intake estimation method. Most of the existing methods are based on the idealized assumption of a static flow field, and do not fully consider the actual influence of the geometric blocking and dynamic cutting effect of the high-speed rotating fan blade on the water flow during the cleaning process, so it is difficult to accurately obtain the actual water intake. At the same time, the existing technology lacks a mathematical model describing the dynamic cutting effect of the blade rotation on the water flow, and the maintenance personnel can only estimate the water intake based on experience, which can cause the cleaning effect to be less than expected, affect the dirt removal effect and performance recovery determination, and if the water pump power is blindly increased, it can also cause waste of cleaning liquid, and even cause the risk of engine case overflow and corrosion. SUMMARY

[0005] The embodiments of the present application provide a water intake estimation and flow control method for aero-engine in-flight cleaning, which can accurately estimate the effective water intake during the cleaning process, reduce the loss of cleaning liquid and improve the cleaning quality.

[0006] According to an aspect of the embodiments of the present application, a water intake estimation and flow control method for aero-engine in-flight cleaning is provided, and the method comprises: In the process of in-flight cleaning of an aero-engine, the following operations are performed in each regulation cycle: The nozzle total jet flow, jet average axial flow rate of a cleaning nozzle in an aero-engine cleaning system and actual rotating speed of the aero-engine in a cleaning state are filtered and denoised to obtain target regulation parameters; The target regulation parameters include the target nozzle total jet flow, target jet average axial flow rate and target actual rotating speed obtained after filtering. According to the target regulation parameters and key geometric parameters of the aero-engine, the effective jet flow that can be sprayed into the inner channel of the aero-engine under the target nozzle total jet flow is calculated in real time in combination with the effects of blade static shielding and rotating dynamic sweeping shielding. The key geometric parameters include the inner channel hub radius, inner channel effective opening height, blade number, blade static shielding thickness and blade axial chord length of the aero-engine. According to the difference value between the effective jet flow and a preset target cleaning required water flow, the output frequency of the variable frequency water pump in the aero-engine cleaning system is regulated based on an embedded control algorithm.

[0007] According to another aspect of the embodiment of the present application, an in-flight cleaning water intake estimation and flow control device for an aero-engine is provided, which comprises: A target regulation parameter real-time acquisition module is configured to filter and denoise the nozzle total jet flow, jet average axial flow rate of a cleaning nozzle in an aero-engine cleaning system and actual rotating speed of the aero-engine in a cleaning state to obtain target regulation parameters. An effective jet flow real-time calculation module is configured to calculate the effective jet flow that can be sprayed into the inner channel of the aero-engine under the target nozzle total jet flow in real time according to the target regulation parameters and key geometric parameters of the aero-engine in combination with the effects of blade static shielding and rotating dynamic sweeping shielding. A variable frequency water pump output frequency regulation module is configured to regulate the output frequency of the variable frequency water pump in the aero-engine cleaning system according to the difference value between the effective jet flow and a preset target cleaning required water flow based on an embedded control algorithm.

[0008] According to another aspect of the embodiment of the present application, an electronic device is provided, which comprises: At least one processor; and a memory connected in communication with the at least one processor; wherein, The memory stores a computer program that can be executed by the at least one processor, which enables the at least one processor to perform the method for estimating and controlling the amount of water entering the aircraft engine during wing cleaning, as described in any embodiment of the present invention.

[0009] According to another aspect of the present invention, a computer-readable storage medium is provided, the computer-readable storage medium storing computer instructions, the computer instructions being configured to cause a processor to execute and implement the method for estimating and controlling the water inflow during wing cleaning of an aero-engine as described in any embodiment of the present invention.

[0010] According to another aspect of the present invention, a computer program product is also provided, including a computer program that, when executed by a processor, implements the steps of the method for estimating and controlling the water inflow during wing cleaning of an aero-engine as described in any embodiment of the present invention.

[0011] The technical solution of this invention obtains the target control parameters by real-time acquisition of the total jet flow rate, average axial velocity of the jet, and actual rotational speed of the aero-engine during cleaning, from the cleaning nozzles in the aero-engine cleaning system. This effectively filters out the influence of electromagnetic interference and mechanical vibration on the rotational speed and flow rate signals. By combining the static shielding and dynamic sweeping shielding effects of the blades, the effective jet flow rate of the aero-engine inner duct is calculated in real time, improving the accuracy of the effective water intake estimation. Based on the embedded control algorithm, the output frequency of the variable frequency water pump in the aero-engine cleaning system is adjusted, avoiding cleaning quality problems caused by insufficient water intake and reducing cleaning agent waste and casing overflow.

[0012] It should be understood that the description in this section is not intended to identify key or essential features of the embodiments of the present invention, nor is it intended to limit the scope of the invention. Other features of the invention will become readily apparent from the following description. Attached Figure Description

[0013] To more clearly illustrate the technical solutions in the embodiments of the present invention, the accompanying drawings used in the description of the embodiments will be briefly introduced below. Obviously, the accompanying drawings described below are only some embodiments of the present invention. For those skilled in the art, other drawings can be obtained based on these drawings without creative effort.

[0014] Figure 1 This is a flowchart of a method for estimating and controlling the water inflow during wing cleaning of an aero-engine according to Embodiment 1 of the present invention; Figure 2This is a flowchart of a method for estimating and controlling the water inflow during wing cleaning of an aircraft engine according to Embodiment 2 of the present invention; Figure 3 This is a derivation diagram of an engine cleaning jet water inlet estimation model based on polar coordinates, applicable to an embodiment of the present invention. Figure 4 This is a flowchart of a precise estimation and control system for jet water inlet volume of an aero-engine, applicable to an embodiment of the present invention. Figure 5 This is a schematic diagram of a device for estimating and controlling the amount of water entering an aircraft engine during wing cleaning, according to Embodiment 3 of the present invention. Figure 6 This is a schematic diagram of the electronic device used to implement the method for estimating and controlling the water inflow during wing cleaning of an aircraft engine according to an embodiment of the present invention. Detailed Implementation

[0015] To enable those skilled in the art to better understand the present invention, the technical solutions of the present invention will be clearly and completely described below with reference to the accompanying drawings of the embodiments of the present invention. Obviously, the described embodiments are only some embodiments of the present invention, and not all embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those skilled in the art without creative effort should fall within the scope of protection of the present invention.

[0016] It should be noted that the terms "first," "second," etc., in the specification, claims, and accompanying drawings of this invention are used to distinguish similar objects and are not necessarily used to describe a specific order or sequence. It should be understood that such data can be interchanged where appropriate so that the embodiments of the invention described herein can be implemented in orders other than those illustrated or described herein. Furthermore, the terms "comprising" and "having," and any variations thereof, are intended to cover non-exclusive inclusion; for example, a process, method, system, product, or apparatus that comprises a series of steps or units is not necessarily limited to those steps or units explicitly listed, but may include other steps or units not explicitly listed or inherent to such processes, methods, products, or apparatus.

[0017] Example 1 Figure 1This is a flowchart illustrating a method for estimating and controlling the water inflow during wing cleaning of an aero-engine, as provided in Embodiment 1 of the present invention. This embodiment is applicable to situations where, during wing cleaning of an aero-engine, the effective water inflow into the engine's internal ducts is accurately estimated by fully considering the effects of geometric obstruction and dynamic truncation caused by fan blade rotation. This method can be executed by a device for estimating and controlling the water inflow during wing cleaning of an aero-engine. This device can be implemented in hardware and / or software and is generally configured in the controller of the aero-engine cleaning system. This controller can, for example, be an industrial-grade microprocessor equipped with an ARM / DSP architecture.

[0018] In the process of the aircraft engine cleaning system performing wing cleaning on the set aircraft engine, the controller will periodically adjust the output frequency of the variable frequency water pump in the cleaning system at a preset adjustment frequency to ensure that the cleaning fluid that actually enters the internal channels of the aircraft engine can achieve the expected target cleaning water flow rate.

[0019] Correspondingly, such as Figure 1 As shown, the method includes: During on-wing cleaning of an aircraft engine, the following operations are performed in each control cycle: S110. The total nozzle jet flow rate, average axial velocity of the jet, and actual rotational speed of the aero-engine under cleaning conditions of the cleaning nozzles in the real-time acquisition aero-engine cleaning system are filtered and denoised to obtain the target control parameters.

[0020] The target control parameters include the total jet flow rate of the target nozzle, the average axial velocity of the target jet, and the actual rotational speed of the target, obtained after filtering.

[0021] Specifically, Kalman filtering can be used to filter the real-time collected nozzle total jet flow rate, average axial velocity of the jet, and actual rotation speed to remove sensor noise and signal fluctuations. The filtered results can then be used as target control parameters for subsequent water inflow estimation.

[0022] The total jet flow rate of the nozzle is the total volume of cleaning fluid ejected from the cleaning nozzle per unit time. It is collected in real time by a Coriolis flow meter or a high-precision electromagnetic flow meter built into the cleaning system, and its typical range is 0.0005. 0.005 The average axial velocity of the jet refers to the average speed of the cleaning fluid ejected from the cleaning nozzle along the engine's axial direction. It can be obtained through physical calculation based on pressure data collected by a high-frequency pressure sensor in the pipeline, combined with the nozzle orifice diameter and relevant calibration parameters. The range is generally 20. 100 The actual engine speed during cleaning is acquired by an engine speed sensor (such as an N1-axis photoelectric speed sensor or a magnetoelectric speed sensor) and fed back to the cleaning system via a bus. Under cold start or idle conditions, the actual engine speed typically ranges from 5 rpm. 50 rad / s.

[0023] In an optional embodiment of this invention, the total nozzle jet flow rate, average axial velocity of the jet, and actual rotational speed of the aircraft engine under cleaning conditions, which are collected in real time from the cleaning nozzles in the aircraft engine cleaning system, are filtered and denoised to obtain the target control parameters. This can include: If the current control cycle is the first control cycle, then based on the preset initial state parameters, the real-time collected nozzle total jet flow rate, jet average axial velocity and actual rotation speed are processed by Kalman filtering to obtain the target control parameters; If the current control cycle is not the first control cycle, the Kalman filter is applied to the real-time collected nozzle total jet flow rate, average axial velocity of the jet, and actual rotation speed based on the state estimate of the previous historical control cycle to obtain the target control parameters.

[0024] Considering the pump vibration and electromagnetic interference present in industrial environments, the raw sampled data output by the sensors collecting the above parameters often contains high-frequency noise. The controller incorporates a Kalman filter module at this stage. When the Kalman filter module performs filtering using the Kalman filter algorithm, the initial state parameters, including the initial state estimate, initial covariance matrix, process noise covariance matrix, and measurement noise covariance matrix, are all preset based on system characteristics and sensor parameters.

[0025] Specifically, in the first control cycle, the Kalman filter uses the preset initial state estimate and initial covariance matrix as the starting values ​​for the filter recursion, and executes the prediction step and update step in sequence to obtain the target control parameters after filtering in the first control cycle.

[0026] The prediction step specifically includes: based on the state estimation at the previous moment, combined with the system model, obtaining prior state estimates and prior covariance for the total nozzle jet flow rate, average jet axial velocity, and actual rotational speed under the current control cycle. The update step includes: using the total nozzle jet flow rate, average jet axial velocity, and actual rotational speed collected by the sensor in real time as the input observation values, combining the prior state estimation to complete the state correction, and outputting the denoised posterior state, which is the target control parameter for the current cycle.

[0027] Furthermore, when the control period k is a positive integer greater than or equal to 2, the state estimate of the previous control period needs to be used as a priori value for prediction and updating, and the filtering process is implemented according to the following filtering state equation.

[0028] in, This is the multidimensional state vector of the current control cycle (i.e., the target control parameter). , This is the state estimate of the total jet flow rate of the nozzle under the current control cycle (i.e., the target total jet flow rate of the nozzle). This is the state estimate of the average axial velocity of the jet under the current control cycle (i.e., the average axial velocity of the target jet). This is the estimated value of the actual rotational speed under the current control cycle; This is the multidimensional state vector of the previous control cycle, that is, the posterior state output by the update step of the previous control cycle, or the target control parameter of the previous control cycle.

[0029] This is the control input for the current control cycle; The process noise of the current control cycle follows a Gaussian distribution with zero mean and covariance Q, where Q is the process noise covariance matrix; A is the state transition matrix; B is the control input matrix; and H is the measurement matrix. The sensor measurements for the current control cycle (i.e., the total nozzle jet flow rate, average axial velocity of the jet, and actual rotational speed of the aircraft engine under cleaning conditions, which are collected in real time from the cleaning nozzles in the aircraft engine cleaning system). The measurement noise of the current control cycle follows a Gaussian distribution with zero mean and covariance R, where R is the measurement noise covariance matrix; the state transition matrix A, control input matrix B, and measurement matrix H are system matrices pre-calibrated based on the hardware characteristics of the cleaning system and remain unchanged during the filtering process.

[0030] Kalman filtering eliminates abrupt spikes through a "prediction-update" iterative calculation, and uses the smoothed and denoised data as effective parameters to input into subsequent calculation stages, thus ensuring the stability of the operation.

[0031] S120. Based on the target control parameters and the key geometric parameters of the aero-engine, and combined with the static shielding and dynamic sweeping shielding effects of the blades, the effective jet flow rate that can be injected into the inner duct of the aero-engine under the total jet flow rate of the target nozzle is calculated in real time.

[0032] Key geometric parameters include the hub radius of the inductor, the effective opening height of the inductor, the number of blades, the static shielding thickness of the blades, and the axial chord length of the blades.

[0033] The inner duct hub radius is the distance from the root of the aero-engine fan blade to the axis of rotation; the effective opening height of the inner duct is the distance from the hub surface to the blade tip, i.e., the radial height of the fan blade; the number of blades refers to the total number of fan blades; the static shielding thickness of the blade refers to the physical thickness of the fan blade along the circumference. The thicker the blade, the stronger the static shielding effect; the axial chord length of the blade refers to the projected length of the blade along the engine axis. The larger the chord length, the longer the time required for the cleaning jet to pass through the axial chord length of the blade, the greater the dynamic sweeping distance generated by the blade during this time, and the more significant the dynamic truncation effect.

[0034] Specifically, the static shielding effect of the blades depends on the number of blades and the thickness of the static shielding, reflecting the degree of geometric obstruction of the water flow by the blade body; the rotating dynamic sweep shielding effect depends on the actual rotational speed, the axial chord length of the blades, and the number of blades, reflecting the degree of dynamic interception of the water flow by the blade rotation. Both together determine the effective jet flow rate that can be injected into the inner duct of the aero-engine under the total jet flow rate of the target nozzle.

[0035] The effective jet flow rate refers to the actual effective medium (i.e., cleaning fluid) flow rate that can successfully penetrate the fan and stably enter the engine's internal duct to participate in the cleaning of compressor deposits in the total jet ejected through the cleaning nozzle during the on-wing cleaning process of the aero-engine, after excluding the static physical blockage loss of the fan blades and the dynamic sweeping and cutting loss of the high-speed rotation of the blades.

[0036] It is important to emphasize that the effective jet flow rate is different from the total jet flow rate at the nozzle outlet. The total jet flow rate is the total flow rate of the medium ejected from the cleaning nozzle, without considering the obstruction and shearing losses of the fan blades. In contrast, the effective jet flow rate fully characterizes the actual water intake capacity under the coupling effect of blade geometric obstruction and dynamic sweeping. It is the core physical quantity for determining the actual cleaning water volume of the engine and ensuring the descaling effect and performance recovery accuracy.

[0037] S130. Based on the difference between the effective jet flow rate and the preset target cleaning water flow rate, the output frequency of the variable frequency water pump in the aircraft engine cleaning system is adjusted according to the embedded control algorithm.

[0038] The variable frequency water pump is used to supply cleaning fluid to the cleaning nozzle, and the control quantity is calculated according to the control algorithm to adjust the output frequency of the variable frequency water pump to change the total jet flow rate of the target nozzle, so that the effective jet flow rate approaches the target cleaning water flow rate in each control cycle.

[0039] In this embodiment, the difference between the effective jet flow rate and the preset target cleaning water flow rate is input to a preset controller, which has a built-in control algorithm. The control algorithm includes any one of the following: standard PID control algorithm, fuzzy PID control algorithm, sliding mode variable structure control algorithm, or model predictive control algorithm. It is used to calculate the control quantity based on the difference value to adjust the output frequency of the variable frequency water pump.

[0040] In practical applications, at the beginning of each control cycle, the total nozzle jet flow rate, average axial velocity of the jet, and actual engine speed during cleaning can be collected from the cleaning nozzles in the aero-engine cleaning system. Using these three collected values ​​as input, the effective jet flow rate for each control cycle can be calculated. Furthermore, based on the difference between the effective jet flow rate and the preset target cleaning water demand, the output frequency of the variable frequency pump can be adaptively controlled in a closed-loop manner within each control cycle, achieving dynamic and precise matching of the cleaning jet flow rate to the target cleaning water demand.

[0041] The technical solution of this invention obtains the target control parameters by real-time acquisition of the total jet flow rate, average axial velocity of the jet, and actual rotational speed of the aero-engine during cleaning, from the cleaning nozzles in the aero-engine cleaning system. This effectively filters out the influence of electromagnetic interference and mechanical vibration on the rotational speed and flow rate signals. By combining the static shielding and dynamic sweeping shielding effects of the blades, the effective jet flow rate of the aero-engine inner duct is calculated in real time, improving the accuracy of the effective water intake estimation. Based on the embedded control algorithm, the output frequency of the variable frequency water pump in the aero-engine cleaning system is effectively controlled, avoiding cleaning quality problems caused by insufficient water intake and reducing cleaning agent waste and casing overflow.

[0042] Example 2 Figure 2 This is a flowchart illustrating another method for estimating and controlling the inlet water volume during wing cleaning of an aero-engine, provided in Embodiment 2 of the present invention. This embodiment is a specific implementation based on the above embodiment. Specifically, this embodiment specifies the operation of "calculating in real time the effective jet flow rate that can be injected into the inner duct of the aero-engine under the total jet flow rate of the target nozzle, based on the target control parameters and the key geometric parameters of the aero-engine, combined with the static shielding and rotating dynamic sweeping shielding effects of the blades." Correspondingly, as... Figure 2 As shown, the method includes: During on-wing cleaning of an aircraft engine, the following operations are performed in each control cycle: S210. The total nozzle jet flow rate, average axial velocity of the jet, and actual rotational speed of the aero-engine under cleaning conditions of the cleaning nozzles in the real-time acquisition aero-engine cleaning system are filtered and denoised to obtain the target control parameters.

[0043] The target control parameters include the total jet flow rate of the target nozzle, the average axial velocity of the target jet, and the actual rotational speed of the target, obtained after filtering.

[0044] S220. Determine whether the jet ejected by the cleaning nozzle meets the preset uniform spraying condition in the radial direction of the effective opening height of the inner channel: if yes, then execute S230; otherwise, execute S240.

[0045] In this embodiment, the effective jet flow rate can be calculated using different methods depending on whether the jet ejected from the cleaning nozzle is uniform in the radial direction within the effective opening height of the inner channel. The uniform spray condition refers to the jet flow rate being approximately uniformly distributed radially within the radial range of the effective opening height of the inner channel.

[0046] The determination of uniform spray conditions can be achieved in any of the following ways: receiving user input through a preset control button to select a uniform or non-uniform jet mode; dynamically determining whether the jet meets the uniform spray conditions through real-time image acquisition in each control cycle; and conducting calibration experiments on the cleaning system in advance to determine the jet uniformity state corresponding to different spray parameters.

[0047] S230. Calculate the effective jet flow rate according to the pre-constructed formula for the inner channel: The effective jet flow rate that can be injected into the inner duct of the aero-engine under the total jet flow rate Q of the target nozzle is calculated. Execute S280.

[0048] in, The average axial velocity of the target jet. Let L be the target actual rotational speed, L be the axial chord length of the blade, and Z be the number of blades. Where h is the static shielding thickness of the blade, and h is the effective opening height of the inner channel. The radius of the inner channel hub is given. The formula for calculating the effective jet flow rate of the inner channel is obtained by definite integral over a preset jet element along the effective opening height range of the inner channel, based on the equivalent interference relationship constructed by the static blocking and rotating dynamic sweeping blocking effects of the blades.

[0049] For example, the static shielding thickness of the blade is 0.005. The axial chord length of the blade is 0.05m. The inner diameter is 0.3m, and the radius of the inner diameter wheel hub is 0.2m. The effective opening height of the inner channel is 1.0m, and the value of 0.05 is also specified. 0.3m, the number of blades is 20. 60 pieces.

[0050] The equivalent interference relationship refers to combining the two physical effects of static geometric obstruction and rotational dynamic sweeping obstruction of the blade into an equivalent total obstruction ratio, which is directly used to calculate the effective jet flow rate. The preset jet micro-element refers to the effective opening height range of the inner duct. Inner, radial width is The thin annular band (also called a thin annular infinitesimal element, or simply an infinitesimal element) is the basic unit of calculation for definite integrals. The total effective jet flow rate is obtained by summing the results of all infinitesimal elements along the radial interval.

[0051] Specifically, in this embodiment, when the jet is uniformly distributed at the opening height of the inner channel, the effective opening height range of the inner channel is divided radially. Discretize into an infinite number of thin circular rings, each with a radius of... Width is Since the jet flow rate density remains consistent at each thin annular micro-element under uniform spray conditions, the total jet flow rate Q of the target nozzle is multiplied by the penetration ratio of the corresponding annular micro-element, and within the effective opening range... The total effective jet flow rate can be obtained by internal integration. .

[0052] At any radius p At that location, the tangential linear velocity of the fan blades is High-pressure jet droplets move at an axial velocity The time required to traverse the axial chord length of the blade is: .

[0053] During the travel time t, the additional arc length formed by a single blade sweeping in the tangential direction due to rotational motion is: This sweeping arc length increases the effective shielding width of the blade. By superimposing this sweeping arc length with the original static shielding thickness of the blade, the dynamic equivalent interference arc length can be obtained: Therefore, the dynamic equivalent total shading arc length formed by the Z blades is: Z.

[0054] For each thin annular band, the total circumference of the entire annulus is... Then the shading ratio of the Z blades is: Therefore, the actual effective permeability coefficient corresponding to the annular micro-element... for: .

[0055] The dynamic equivalent interference arc length Substituting the expression into the calculation, we get The actual effective permeability coefficient is used to characterize the proportion of cleaning fluid that can pass through the fan blade gaps and enter the internal ducts of the aero-engine. The value range is [0,1].

[0056] For radius The radial width is The area of ​​the thin annular band accounts for a proportion of the effective opening area. Under uniform injection conditions, the jet flow rate density is the same on each thin annular band. The total jet flow rate Q of the target nozzle is distributed across one thin annular band as follows: .

[0057] Furthermore, the jet flow rate that can penetrate the blade chord and enter the inner duct of this thin annular band is: The micro-element flow rate is measured along the effective opening height range of the inner channel. By performing definite integrals, we can obtain: Substituting the upper and lower limits of the definite integral and performing integration, we obtain the final analytical expression, which is the effective jet flow rate actually passing through the blades and entering the inner duct. The calculation expression is: .

[0058] After obtaining the target control parameters for a control cycle, and combining them with the key geometric parameters of the aero-engine, the controller can directly calculate the above-mentioned parameters based on the above expression. .

[0059] S240, For those located in polar coordinates A radius within the range is Width is The thin circular band, expressed as: The actual effective permeability coefficient of the thin annular belt was determined. And execute S250.

[0060] Specifically, when the jet does not meet the uniform spray condition in the radial direction of the effective opening height of the duct, that is, when the intensity distribution of the jet is uneven in the radial direction of the effective opening height of the duct, it is necessary to calculate the actual effective permeability coefficient at different radial positions point by point along the radial direction. .

[0061] The uneven intensity distribution of the jet in the radial direction of the effective opening height of the inner channel means that, in actual working conditions, the jet ejected by the cleaning nozzle is usually unevenly distributed in the radial direction of the opening height of the inner channel. Typically, the jet density is high in the central region and low in the edge region.

[0062] As can be seen from the formula derivation of S230, for the polar coordinates located at A radius within the range is Width is The thin circular band, and the actual effective permeability coefficient corresponding to the thin circular band. , The value range is [0,1]. After determining the actual effective permeability coefficient of the thin annular belt, it is necessary to further construct the jet spatial distribution function of the cleaning nozzle.

[0063] S250. Based on the total jet flow rate and average axial velocity of the target jet under the current control cycle, the jet spatial distribution function of the cleaning nozzle is constructed. Execute S260.

[0064] In an optional implementation of this embodiment, the jet spatial distribution function of the cleaning nozzle is constructed based on the total jet flow rate of the target nozzle and the average axial velocity of the target jet under the current control cycle, which may include: S2501. Query the experience data table that matches the aero-engine, and obtain the distribution standard deviation corresponding to the total jet flow rate of the target nozzle and the average axial velocity of the target jet. .

[0065] Specifically, using the combination of the target nozzle's total jet flow rate and the target jet's average axial velocity as an index, the corresponding distribution standard deviation is queried from a pre-established empirical matching table. Among them, the standard deviation of the distribution Used to characterize the radial divergence of the jet from the cleaning nozzle.

[0066] Optionally, the empirical data table used in this embodiment is pre-calibrated. During calibration, a test platform can be built, and jet intensity data at different radial positions can be collected by changing the total jet flow rate and the average axial velocity of the jet. Then, Gaussian fitting can be performed on the test data for each set of working conditions to obtain the ideal distribution standard deviation for the corresponding working condition. The total jet flow rate, average axial velocity of the jet, and the ideal distribution standard deviation are stored one-to-one to form an empirical data table, which is pre-stored in the controller for querying and recall during real-time control. When changing the nozzle model, the empirical data table needs to be recalibrated and updated.

[0067] S2502, According to the formula: The expected value of the target center is calculated. .

[0068] Where h is the effective opening height of the inner channel. The radius of the inner wheel hub. Target center expectation value. The center position of the jet in the radial direction of the effective opening height of the inner channel is the target radial position where the cleaning fluid jet should be concentrated.

[0069] S2503, The expression: , is determined as the jet spatial distribution function of the cleaning nozzle, used to describe the relative intensity of the jet at different radial positions.

[0070] Preferably, the jet is assumed to follow a Gaussian distribution in the radial direction, and a Gaussian distribution function is used to describe the relative intensity distribution of the jet in the radial direction: in, for The relative intensity of the jet at the target center is given by exp(.), which is a natural exponential function with the natural constant e as its base; this function is expressed as the expected value at the target center. The peak position is represented by the standard deviation of the distribution. The degree of jet dispersion is controlled, and the relative intensity of the jet at different radial positions is characterized, exhibiting a distribution pattern of dense distribution at the center and sparse distribution at the edges. The jet intensity is... It is largest at the point of origin and gradually decreases towards both sides. It should be noted that... The relative intensity weighting function of the jet needs to be normalized during subsequent integration to ensure the conservation of the total jet flow rate.

[0071] S260, Based on the actual effective permeability coefficient and jet spatial distribution function Construct the calculus flow field truncation formula: .

[0072] Specifically, when the jet is non-uniformly distributed in the radial direction of the effective opening height of the inner duct, the effective opening height range of the inner duct is divided along the radial direction. Discretize into an infinite number of thin circular rings, each with a radius of... Width is Within each thin annular zone, the jet flow rate density is non-uniform, according to the jet spatial distribution function. Calculate the relative intensity of the jet from the thin annular belt.

[0073] On each thin annular band, the corresponding infinitesimal jet flow rate is the total jet flow rate Q of the target nozzle multiplied by the relative jet intensity at that location. With the width of the thin annular band The product of, i.e. The actual effective flow rate that this infinitesimal element can enter the inner channel is: .

[0074] The effective flow rate of all infinitesimal elements is along the radial interval By accumulating these formulas, we obtain the calculus formula for the flow field cutoff: The actual effective permeability coefficient and jet spatial distribution function Substituting the specific expression and expanding it, we get: Among them, here The effective jet flow rate is defined as the jet flow rate in the radial direction of the effective opening height of the inner channel, where the uniform jetting condition is not met.

[0075] It should be noted that the integrand of the above integral relationship includes The product of the term and the Gaussian function does not have an elementary analytic closed-form solution; therefore, it cannot be directly calculated using a fixed expression similar to S230. The analytical solution of the definite integral.

[0076] Therefore, the controller needs to use a preset integral algorithm to obtain the effective jet flow rate in real time by integrating the parameters according to the target control parameters. The specific value.

[0077] S270. The differential integral flow field truncation formula is solved in real time using a preset numerical integration method to obtain the effective jet flow rate that can be injected into the inner duct of the aero-engine under the total jet flow rate Q of the target nozzle. Execute S280.

[0078] In this embodiment, the differential integral flow field truncation formula can be solved in real time using a numerical integration method. The numerical integration method includes the trapezoidal integration method or the Simpson integration method. This numerical integration solution method can adapt to the condition of non-uniform radial distribution of the nozzle jet, further eliminating theoretical errors caused by uneven physical atomization of the nozzle, and improving the estimation accuracy of the effective jet flow rate under extreme conditions.

[0079] S280. Based on the difference between the effective jet flow rate and the preset target cleaning water flow rate, the output frequency of the variable frequency water pump in the aircraft engine cleaning system is adjusted according to the embedded control algorithm.

[0080] Specifically, the target cleaning water flow rate can be read from the preset parameters of the cleaning process. The difference between the target cleaning water flow rate and the effective jet flow rate is calculated to generate a continuous deviation signal. The deviation signal is then fed into any one of the embedded standard PID control algorithm, fuzzy PID control algorithm, sliding mode variable structure control algorithm, or model predictive control algorithm. The controller outputs a control quantity to adjust the output frequency of the variable frequency water pump, so that the effective jet flow rate approaches the target cleaning water flow rate, thereby realizing closed-loop control of the inlet water flow rate.

[0081] This embodiment preferably employs a standard PID control algorithm based on an embedded system. The control law of this algorithm is as follows: in, The value of u represents the deviation between the target cleaning water flow rate and the effective jet flow rate at the current time t. The control quantity output by the controller is used to adjust the output frequency of the variable frequency water pump; This is the proportionality coefficient. The integral time constant is... The above parameters are all preset based on the hardware characteristics of the cleaning system, and are the differential time constants.

[0082] Proportional Term Used for immediate and substantial compensation of the base fluid volume in response to current cut-off losses; integral term Used to eliminate long-term accumulated steady-state errors caused by minute fluctuations in water pressure; differential term It is used to provide advance suppression of the rate of change of deviation caused by sudden changes in engine speed, and to prevent water pressure overshoot.

[0083] It should be noted that the control quantity u output by the controller After amplitude limiting, it is mapped to an adjustment command for the output frequency of the variable frequency water pump, which drives the variable frequency water pump to adjust the output flow rate, thereby achieving closed-loop precise control of the effective jet flow rate.

[0084] The technical solution of this invention determines the uniformity of the jet flow in the radial direction of the effective opening height of the inner duct, constructs formulas for uniform jet conditions and jet spatial distribution functions for non-uniform jet conditions, and combines the static shielding and rotating dynamic sweeping shielding effects of the blades to construct a formula for calculating the effective jet flow rate of the inner duct, thus achieving accurate estimation of the effective water intake under different operating conditions. By controlling the output frequency of the variable frequency water pump through a control algorithm, the effective jet flow rate is made close to the target cleaning water flow rate, avoiding cleaning quality problems caused by insufficient water intake, reducing cleaning agent waste, and lowering the cleaning cost of aero engines.

[0085] Based on the above embodiments, after filtering and denoising the total nozzle jet flow rate, average axial velocity of the jet, and actual rotational speed of the aero-engine under cleaning conditions in the real-time acquired data of the aero-engine cleaning system to obtain the target control parameters, the method may further include: Determine whether the target's actual rotational speed and the target jet's average axial velocity satisfy the preset loss rate constraint formula: ; If not, the system determines that the current on-wing cleaning process is in an extremely abnormal condition and controls the aircraft engine cleaning system to perform a shutdown alarm operation.

[0086] Specifically, Characterizing the flow loss caused by the dynamic sweeping and blocking effect of blade rotation. This represents the flow loss caused by static obstruction of the blades. When the loss rate is less than 1, it indicates that the effective jet flow rate is positive, and the cleaning system is in normal operating condition. Otherwise, when the loss rate is greater than or equal to 1, i.e., the constraint condition is not met, it indicates that the effective jet flow rate is zero or negative, meaning that the jet cannot pass through the blades and enter the inner duct under the current operating condition. If the current on-wing cleaning process is determined to be in an extreme abnormal operating condition, the cleaning system will be controlled to execute a shutdown alarm operation to prevent the cleaning fluid from being thrown by the blades into the outer duct, causing casing overflow and corrosion risks.

[0087] Based on the above embodiments, the method may further include: When the aircraft engine cleaning system is started to perform the cleaning operation on the aircraft engine, the initial rotational speed of the aircraft engine is collected.

[0088] Based on the initial rotational speed and the loss rate constraint formula, the initial total jet flow rate of the cleaning nozzles in the aero-engine cleaning system is set.

[0089] Specifically, the initial rotational speed is substituted into the loss rate constraint formula. Under the premise of satisfying the constraint condition, the lower limit of the average axial velocity of the jet can be calculated. Combining the lower limit of the average axial velocity of the jet with the pre-built flow rate and velocity calibration relationship of the cleaning nozzle in the aero-engine cleaning system, the lower limit of the total jet flow rate of the nozzle can be calculated. Based on the lower limit of the total jet flow rate of the nozzle, the initial total jet flow rate of the cleaning nozzle can be set accordingly to ensure that the initial total jet flow rate of the nozzle meets the loss rate constraint condition at the beginning of the cleaning stage.

[0090] If, after substituting the initial rotational speed, it is detected that there is no average axial velocity of the jet that can satisfy the above loss rate constraint, then it is determined that the current initial rotational speed condition cannot safely carry out cleaning, an alarm signal is output, and the cleaning process is prohibited from starting.

[0091] Figure 3 This is a derivation diagram of a model for estimating the influent flow rate of an engine cleaning jet based on polar coordinates, applicable to embodiments of the present invention. Figure 3 As shown, the derivation diagram establishes a polar coordinate system centered on the engine rotation axis to characterize the radial spatial distribution of the jet at the inlet of the inner duct and the obstruction relationship of the fan blades on the cleaning jet.

[0092] Specifically, the fan blades move at an angular velocity (Unit: rad / s) Rotation about the engine's axis of rotation. in, Figure 3 The radial lines a, b, and c represent the cleaning jets ejected from the cleaning nozzles. The three jets shown in the diagram are for illustrative purposes only and do not constitute a limitation on the actual number of nozzles. This solution is applicable to both single-nozzle and multi-nozzle applications. (Unit: rad / s) represents the angular velocity of the fan blades. h is the radius of the inner channel hub; h is the effective radial height of the inner channel opening. L represents the radial width of a certain radial thin circular ring micro-element within the effective opening height range of the inner channel; L is the axial chord length of the fan blade, which extends along the direction of the engine rotation axis and is perpendicular to the drawing plane of this polar coordinate schematic diagram. This represents the infinitesimal area of ​​the fan blade at the corresponding radial position, and is a geometrical representation in the derivation process.

[0093] The cleaning jet is sprayed from each cleaning nozzle along the engine axis toward the fan blades, discretizing the radial range of the effective opening height of the inner duct into several radial widths. A thin circular annular element. For any radial position... In the thin circular ring element at the point, during the process of the cleaning jet passing through the axial chord length L of the fan blade along the axis, the high-speed rotating fan blade will tangentially sweep out a dynamic arc length in a very short time during the passage of the jet; this dynamic sweeping arc length is superimposed with the static physical thickness of the blade to form a dynamic equivalent interference arc length, which is used to characterize the total blocking effect of the fan blade on the cleaning jet at this radial position.

[0094] This model uses the total jet flow rate Q of all nozzles as the input parameter, and performs integral calculations on all radial thin annular micro-elements of the inner duct in sequence. By combining the blade blocking effect at each radial position, the effective jet flow rate that can pass through the fan blades and actually enter the inner duct can be obtained.

[0095] Figure 4 This is a flowchart illustrating the overall process of a precise estimation and closed-loop control system for jet water inlet volume in an aero-engine, applicable to embodiments of the present invention. Figure 4As shown, the system includes an input terminal, a preprocessing layer, a core computing layer, a closed-loop control layer, and an output layer. The input terminal acquires sensor data in real time and obtains key geometric parameters of the aero-engine. The sensor data includes the total nozzle jet flow rate, the average axial velocity of the jet, and the actual engine speed. The key geometric parameters include the inner duct hub radius, the effective inner duct opening height, the number of fan blades, the fan static shielding thickness, and the fan axial chord length. The preprocessing layer uses Kalman filtering to denoise the sensor data and obtain the target control parameters. The core computing layer calculates the effective jet flow rate based on the target control parameters and geometric parameters, combined with the effects of blade static shielding and rotating dynamic sweep shielding. The closed-loop control layer compares the effective jet flow rate with the target cleaning water flow rate. Based on the difference, it adjusts the output frequency of the variable frequency pump through the controller to change the total nozzle jet flow rate and feeds the adjusted total nozzle jet flow rate back to the input terminal to enter the next control cycle, forming a closed-loop control. The output layer outputs the effective jet flow rate for the current control cycle for quantitative evaluation of the cleaning effect.

[0096] In a specific example, taking the cold start operation of a narrow-body passenger aircraft as an example, the total jet flow rate of the target nozzle is... Q =0.002 ; Target jet mean axial velocity Target actual speed w =10 rad / s; blade static shielding thickness ; Blade axial chord length L =0.1m; Number of blades Z =30; Inner wheel hub radius The effective opening height of the internal channel is h = 0.1m. The system uses numerical integration to calculate the effective jet flow rate. Under the current rotational speed and geometric parameters, approximately 20.2% of the total flow rate ejected from the nozzle is blocked or intercepted by the fan blades, resulting in only 79.8% of the effective flow rate actually entering the inner duct. Comparing the calculated effective jet flow rate with the preset target cleaning water flow rate, the current effective jet flow rate is found to be lower than the target cleaning water flow rate. Therefore, the controller outputs a control signal to increase the output frequency of the variable frequency pump, thereby increasing the total jet flow rate of the nozzle and compensating for the liquid volume.

[0097] In another specific example, taking the high-thrust idle operation of a wide-body passenger aircraft as an example, the total jet flow rate of the target nozzle... Q =0.004 ; Target jet mean axial velocity Target actual speed w =30 rad / s; blade static shielding thickness =0.02m; Blade axial chord length L =0.2m; Number of blades Z=40; Inner wheel hub radius The effective opening height of the internal channel is h = 0.15m. Due to the combined effect of the large chord length and high rotational speed of the wide-body aircraft, the large chord length extends the axial distance of the water droplet passing through the blade, while the high rotational speed significantly increases the tangential sweep velocity of the blade. The combined effect of these two factors enhances the dynamic sweeping blocking effect of the blade rotation. Numerical integration is used internally to calculate the effective jet flow rate. Under the current rotational speed and geometric parameters, approximately 66.7% of the total flow rate ejected from the nozzle is blocked or intercepted by the fan blades and cannot enter the inner cavity. The actual effective flow rate entering the inner cavity is only 33.3% of the total flow rate. After calculation, the controller determines that the current effective jet flow rate is lower than the preset target cleaning water flow rate. It then increases the output frequency of the variable frequency water pump to increase the total jet flow rate of the nozzle, ensuring that the cleaning water volume entering the inner cavity meets the standard.

[0098] The technical solutions of the embodiments of the present invention can achieve the following beneficial effects: 1. Improved estimation accuracy and provision of a quantitative evaluation basis: This invention superimposes the sweeping effect caused by fan blade rotation with the static physical thickness, and uses polar coordinate calculus analytical expressions to mathematically quantify the fluid shear loss estimation, which was originally in the empirical blind zone. This provides reliable, interference-free pre-entry physical data for the quantitative evaluation of the water washing effect of civil aircraft engines (such as accurately assessing the objective contribution of water washing to extending on-wing time and EGTM recovery).

[0099] 2. Achieving Dynamic Closed-Loop Compensation for Cleaning Flow and Supporting Energy Conservation and Emission Reduction: Based on the calculus model and closed-loop feedback mechanism of this invention, the cleaning system can estimate in real time the water flow cut-off rate caused by different cold start / idle operating speeds and cleaning equipment jet parameters, and automatically adjust the output frequency of the variable frequency water pump. This avoids the waste of cleaning agent and casing overflow caused by blindly increasing the spray volume, avoids cleaning quality problems caused by insufficient water intake, and is in line with the development trend of energy conservation and emission reduction technology in civil aviation and green aviation.

[0100] 3. Suppresses industrial site interference and has strong engineering robustness: By introducing Kalman filtering or moving average filtering algorithms in the parameter acquisition stage, the influence of electromagnetic interference and mechanical vibration on speed and flow signals is effectively filtered out, ensuring the robustness of the calculus model calculation results and the smoothness of closed-loop regulation.

[0101] 4. Multi-aircraft adaptability and low computational cost: The technical solution of this invention extracts the pure physical geometry and kinematic parameters of the aero-engine and the cleaning equipment. When dealing with different aircraft models, only the key geometric parameters and real-time operating parameters that match the target engine need to be updated, and the controller can perform the corresponding effective jet flow calculation, which has good cross-aircraft applicability.

[0102] Example 3 Figure 5 This is a schematic diagram of a device for estimating and controlling the water inflow during wing cleaning of an aircraft engine, provided in Embodiment 3 of the present invention. This device is configured in the controller of the aircraft engine cleaning system. Figure 5 As shown, the device includes: a target control parameter real-time acquisition module 510, an effective jet flow rate real-time calculation module 520, and a variable frequency pump output frequency control module 530.

[0103] In the process of on-wing cleaning of aircraft engines, the above modules work together in each control cycle to achieve the functions of estimating the water inflow and controlling the flow rate during on-wing cleaning. Specifically: The target control parameter real-time acquisition module 510 is used to filter and denoise the total nozzle jet flow rate, average axial velocity of the jet, and actual speed of the aero-engine under cleaning conditions in the real-time acquisition of the cleaning nozzle in the aero-engine cleaning system to obtain the target control parameters. The target control parameters include the total jet flow rate of the target nozzle, the average axial velocity of the target jet, and the actual rotational speed of the target, obtained after filtering. The effective jet flow rate real-time calculation module 520 is used to calculate the effective jet flow rate that can be injected into the inner duct of the aero-engine under the total jet flow rate of the target nozzle, based on the target control parameters and the key geometric parameters of the aero-engine, combined with the static shielding and rotating dynamic sweeping shielding effects of the blades. Among them, key geometric parameters include the hub radius of the inductor of the aero-engine, the effective opening height of the inductor, the number of blades, the static shielding thickness of the blades, and the axial chord length of the blades. The variable frequency water pump output frequency control module 530 is used to control the output frequency of the variable frequency water pump in the aircraft engine cleaning system based on the difference between the effective jet flow rate and the preset target cleaning water flow rate, using an embedded control algorithm.

[0104] The technical solution of this invention obtains the target control parameters by real-time acquisition of the total jet flow rate, average axial velocity of the jet, and actual rotational speed of the aero-engine during cleaning, from the cleaning nozzles in the aero-engine cleaning system. This effectively filters out the influence of electromagnetic interference and mechanical vibration on the rotational speed and flow rate signals. By combining the static shielding and dynamic sweeping shielding effects of the blades, the effective jet flow rate of the aero-engine inner duct is calculated in real time, improving the accuracy of the effective water intake estimation. Based on the embedded control algorithm, the output frequency of the variable frequency water pump in the aero-engine cleaning system is adjusted, avoiding cleaning quality problems caused by insufficient water intake and reducing cleaning agent waste and casing overflow.

[0105] Based on the above embodiments, the effective jet flow rate real-time calculation module 520 can be used for: When it is determined that the jet ejected by the cleaning nozzle meets the preset uniform spraying condition in the radial direction of the effective opening height of the inner channel, the effective jet flow rate of the inner channel is calculated according to the pre-constructed formula: The effective jet flow rate that can be injected into the inner duct of the aero-engine under the total jet flow rate Q of the target nozzle is calculated. ; in, The average axial velocity of the target jet. Let L be the target actual rotational speed, L be the axial chord length of the blade, and Z be the number of blades. Where h is the static shielding thickness of the blade, and h is the effective opening height of the inner channel. The radius of the inner channel hub is given. The formula for calculating the effective jet flow rate of the inner channel is obtained by definite integral over a preset jet element along the effective opening height range of the inner channel, based on the equivalent interference relationship constructed by the static blocking and rotating dynamic sweeping blocking effects of the blades.

[0106] Based on the above embodiments, the effective jet flow rate real-time calculation module 520 may further include: The actual effective permeability coefficient determination unit is used to determine the actual effective permeability coefficient when the jet ejected by the cleaning nozzle does not meet the preset uniform spraying condition in the radial direction of the effective opening height of the inner channel, specifically for the case where the actual effective permeability coefficient is located in polar coordinates. A radius within the range is Width is The thin circular band, expressed as: The actual effective permeability coefficient of the thin annular belt was determined. ; The jet spatial distribution function construction unit is used to construct the jet spatial distribution function of the cleaning nozzle based on the total jet flow rate and the average axial velocity of the target jet under the current control cycle. ; The calculus flow field truncation formula construction unit is used to construct the actual effective permeability coefficient. and jet spatial distribution function Construct the calculus flow field truncation formula: ; The effective jet flow rate calculation unit is used to solve the differential integral flow field truncation formula in real time using a preset numerical integration method to obtain the effective jet flow rate that can be injected into the inner duct of the aero-engine under the total jet flow rate Q of the target nozzle. ; in, The average axial velocity of the target jet. Let L be the target actual rotational speed, L be the axial chord length of the blade, and Z be the number of blades. Where h is the static shielding thickness of the blade, and h is the effective opening height of the inner channel. The radius of the inner wheel hub.

[0107] Based on the above embodiments, the jet spatial distribution function construction unit can be specifically used for: Query the empirical data table matching the aero-engine to obtain the distribution standard deviation corresponding to the total jet flow rate of the target nozzle and the average axial velocity of the target jet. ; According to the formula: The expected value of the target center is calculated. ; The expression: , is determined as the jet spatial distribution function of the cleaning nozzle.

[0108] Based on the above embodiments, it may further include an abnormal operating condition determination module, used for: Determine whether the target's actual rotational speed and the target jet's average axial velocity satisfy the preset loss rate constraint formula: ; If not, the system determines that the current on-wing cleaning process is in an extremely abnormal condition and controls the aircraft engine cleaning system to perform a shutdown alarm operation.

[0109] Based on the above embodiments, a total jet flow initialization module may also be included, used for: When the aircraft engine cleaning system is started to perform the cleaning operation on the aircraft engine, the initial rotational speed of the aircraft engine is collected; Based on the initial rotational speed and the loss rate constraint formula, the initial total jet flow rate of the cleaning nozzles in the aero-engine cleaning system is set.

[0110] Based on the above embodiments, the target control parameter real-time acquisition module 510 can be used for: If the current control cycle is the first control cycle, then based on the preset initial state parameters, the real-time collected nozzle total jet flow rate, jet average axial velocity and actual rotation speed are processed by Kalman filtering to obtain the target control parameters; If the current control cycle is not the first control cycle, the Kalman filter is applied to the real-time collected nozzle total jet flow rate, average axial velocity of the jet, and actual rotation speed based on the state estimate of the previous historical control cycle to obtain the target control parameters. Based on the above embodiments, the variable frequency pump output frequency control module 530 can be used for: Based on the difference between the effective jet flow rate and the preset target cleaning water flow rate, the output frequency of the variable frequency water pump in the aero-engine cleaning system is adjusted according to any one of the embedded standard PID control algorithm, fuzzy PID control algorithm, sliding mode variable structure control algorithm, or model predictive control algorithm.

[0111] The water inlet volume estimation and flow control device for wing cleaning of aero engines provided in this embodiment of the invention can execute the water inlet volume estimation and flow control method for wing cleaning of aero engines provided in any embodiment of the invention, and has the corresponding functional modules and beneficial effects of the method.

[0112] The collection, storage, use, processing, transmission, provision, and disclosure of user personal information involved in the technical solution disclosed herein comply with the provisions of relevant laws and regulations and do not violate public order and good morals.

[0113] Example 4 Figure 6 A schematic diagram of an electronic device 10 that can be used to implement embodiments of the present invention is shown. The electronic device is intended to represent various forms of digital computers, such as laptop computers, desktop computers, workstations, personal digital assistants, servers, blade servers, mainframe computers, and other suitable computers. The electronic device can also represent various forms of mobile devices, such as personal digital assistants, cellular phones, smartphones, wearable devices (e.g., helmets, glasses, watches, etc.), and other similar computing devices. The components shown herein, their connections and relationships, and their functions are merely illustrative and are not intended to limit the implementation of the invention described and / or claimed herein.

[0114] like Figure 6 As shown, the electronic device 10 includes at least one processor 11 and a memory, such as a read-only memory 12 or a random access memory 13, communicatively connected to the at least one processor 11. The memory stores computer programs executable by the at least one processor. The processor 11 can perform various appropriate actions and processes based on the computer program stored in the read-only memory 12 or loaded from storage unit 18 into the random access memory 13. The random access memory 13 may also store various programs and data required for the operation of the electronic device 10. The processor 11, read-only memory 12, and random access memory 13 are interconnected via a bus 14. An input / output interface 15 is also connected to the bus 14.

[0115] Multiple components in electronic device 10 are connected to input / output interface 15, including: input unit 16, such as keyboard, mouse, etc.; output unit 17, such as various types of monitors, speakers, etc.; storage unit 18, such as disk, optical disk, etc.; and communication unit 19, such as network card, modem, wireless transceiver, etc. Communication unit 19 allows electronic device 10 to exchange information / data with other devices through computer networks such as the Internet and / or various telecommunications networks.

[0116] Processor 11 can be various general-purpose and / or special-purpose processing components with processing and computing capabilities. Some examples of processor 11 include, but are not limited to, central processing unit (CPU), graphics processing unit (GPU), various special-purpose artificial intelligence (AI) computing chips, various processors running machine learning model algorithms, digital signal processors (DSPs), and any suitable processor, controller, microcontroller, etc. Processor 11 performs the various methods and processes described above, such as performing the water inflow estimation and flow control method during wing cleaning of an aircraft engine as described in any embodiment of the present invention. That is: During on-wing cleaning of an aircraft engine, the following operations are performed in each control cycle: The total jet flow rate, average axial velocity of the jet, and actual rotational speed of the aero-engine under cleaning conditions in the real-time collected data of the cleaning nozzles in the aero-engine cleaning system are filtered and denoised to obtain the target control parameters. The target control parameters include the total jet flow rate of the target nozzle, the average axial velocity of the target jet, and the actual rotational speed of the target, obtained after filtering. Based on the target control parameters and the key geometric parameters of the aero-engine, and combined with the static shielding and dynamic sweeping shielding effects of the blades, the effective jet flow rate that can be injected into the inner duct of the aero-engine under the total jet flow rate of the target nozzle is calculated in real time. Among them, key geometric parameters include the hub radius of the inductor of the aero-engine, the effective opening height of the inductor, the number of blades, the static shielding thickness of the blades, and the axial chord length of the blades. Based on the difference between the effective jet flow rate and the preset target cleaning water flow rate, the output frequency of the variable frequency water pump in the aero-engine cleaning system is adjusted according to the embedded control algorithm.

[0117] In some embodiments, the method for estimating and controlling the water ingress volume during wing cleaning of an aircraft engine, as described in any embodiment of the present invention, can be implemented as a computer program tangibly contained in a computer-readable storage medium, such as storage unit 18. In some embodiments, part or all of the computer program can be loaded and / or installed on electronic device 10 via read-only memory 12 and / or communication unit 19. When the computer program is loaded into random access memory 13 and executed by processor 11, one or more steps of the method for estimating and controlling the water ingress volume during wing cleaning of an aircraft engine, as described above in any embodiment of the present invention, can be performed. Alternatively, in other embodiments, processor 11 can be configured by any other suitable means (e.g., by means of firmware) to perform the method for estimating and controlling the water ingress volume during wing cleaning of an aircraft engine, as described in any embodiment of the present invention.

[0118] Various embodiments of the systems and techniques described above herein can be implemented in digital electronic circuit systems, integrated circuit systems, field-programmable gate arrays (FPGAs), application-specific integrated circuits (ASICs), application-specific standard products (ASSPs), systems-on-a-chip (SoCs), complex programmable logic devices (CPLDs), computer hardware, firmware, software, and / or combinations thereof. These various embodiments may include implementations in a computer program product comprising one or more computer programs that can be executed and / or interpreted on a programmable system including at least one programmable processor, which may be a dedicated or general-purpose programmable processor capable of receiving data and instructions from a storage system, at least one input device, and at least one output device, and transmitting data and instructions to the storage system, the at least one input device, and the at least one output device.

[0119] The computer programs included in the computer program product for implementing the methods of the present invention may be written in any combination of one or more programming languages. These computer programs may be provided to a processor of a general-purpose computer, a special-purpose computer, or other programmable data processing device, such that when executed by the processor, the computer programs cause the functions / operations specified in the flowcharts and / or block diagrams to be performed. The computer programs may be executed entirely on a machine, partially on a machine, partially on a remote machine as a standalone software package, or entirely on a remote machine or server.

[0120] In the context of this invention, a computer-readable storage medium can be a tangible medium that may contain or store a computer program for use by or in conjunction with an instruction execution system, apparatus, or device. A computer-readable storage medium may include, but is not limited to, electronic, magnetic, optical, electromagnetic, infrared, or semiconductor systems, apparatus, or devices, or any suitable combination of the foregoing. More specific examples of machine-readable storage media include electrical connections based on one or more wires, portable computer disks, hard disks, random access memory (RAM), read-only memory (ROM), erasable programmable read-only memory (EPROM or flash memory), optical fibers, portable compact disk read-only memory (CD-ROM), optical storage devices, magnetic storage devices, or any suitable combination of the foregoing.

[0121] To provide interaction with a user, the systems and techniques described herein can be implemented on an electronic device having: a display device for displaying information to the user (e.g., a CRT (cathode ray tube) or LCD (liquid crystal display) monitor); and a keyboard and pointing device (e.g., a mouse or trackball) through which the user provides input to the electronic device. Other types of devices can also be used to provide interaction with the user; for example, feedback provided to the user can be any form of sensory feedback (e.g., visual feedback, auditory feedback, or tactile feedback); and input from the user can be received in any form (including sound input, voice input, or tactile input).

[0122] The systems and technologies described herein can be implemented in computing systems that include backend components (e.g., as data servers), or middleware components (e.g., application servers), or frontend components (e.g., user computers with graphical user interfaces or web browsers through which users can interact with implementations of the systems and technologies described herein), or any combination of such backend, middleware, or frontend components. The components of the system can be interconnected via digital data communication of any form or medium (e.g., communication networks). Examples of communication networks include local area networks (LANs), wide area networks (WANs), blockchain networks, and the Internet.

[0123] A computing system can include clients and servers. Clients and servers are generally located far apart and typically interact via a communication network. The client-server relationship is created by computer programs running on the respective computers and having a client-server relationship with each other. The server can be a cloud server, also known as a cloud computing server or cloud host, used to address the problems of high management difficulty and weak business scalability inherent in traditional physical hosting and VPS services.

[0124] It should be understood that the various forms of processes shown above can be used, with steps reordered, added, or deleted. For example, the steps described in this invention can be executed in parallel, sequentially, or in different orders, as long as the desired result of the technical solution of this invention can be achieved, and this is not limited herein.

[0125] The specific embodiments described above do not constitute a limitation on the scope of protection of this invention. Those skilled in the art should understand that various modifications, combinations, sub-combinations, and substitutions can be made according to design requirements and other factors. Any modifications, equivalent substitutions, and improvements made within the spirit and principles of this invention should be included within the scope of protection of this invention.

Claims

1. A method for estimating and controlling the water inflow during wing cleaning of an aero-engine, characterized in that, The method, executed by a controller in an aircraft engine cleaning system, includes: During on-wing cleaning of an aircraft engine, the following operations are performed in each control cycle: The total jet flow rate, average axial velocity of the jet, and actual rotational speed of the aero-engine under cleaning conditions in the real-time collected data of the cleaning nozzles in the aero-engine cleaning system are filtered and denoised to obtain the target control parameters. The target control parameters include the total jet flow rate of the target nozzle, the average axial velocity of the target jet, and the actual rotational speed of the target, obtained after filtering. Based on the target control parameters and the key geometric parameters of the aero-engine, and combined with the static shielding and dynamic sweeping shielding effects of the blades, the effective jet flow rate that can be injected into the inner duct of the aero-engine under the total jet flow rate of the target nozzle is calculated in real time. Among them, key geometric parameters include the hub radius of the inductor of the aero-engine, the effective opening height of the inductor, the number of blades, the static shielding thickness of the blades, and the axial chord length of the blades. Based on the difference between the effective jet flow rate and the preset target cleaning water flow rate, the output frequency of the variable frequency water pump in the aero-engine cleaning system is adjusted according to the embedded control algorithm.

2. The method according to claim 1, characterized in that, Based on the target control parameters and key geometric parameters of the aero-engine, and combining the effects of static blade shielding and dynamic sweeping shielding, the effective jet flow rate that can be injected into the aero-engine's inner duct under the total jet flow rate of the target nozzle is calculated in real time, including: When it is determined that the jet ejected by the cleaning nozzle meets the preset uniform spraying condition in the radial direction of the effective opening height of the inner channel, the effective jet flow rate of the inner channel is calculated according to the pre-constructed formula: The effective jet flow rate that can be injected into the inner duct of the aero-engine under the total jet flow rate Q of the target nozzle is calculated. ; in, The average axial velocity of the target jet. Let L be the target actual rotational speed, L be the axial chord length of the blade, and Z be the number of blades. Where h is the static shielding thickness of the blade, and h is the effective opening height of the inner channel. The radius of the inner channel hub is given. The formula for calculating the effective jet flow rate of the inner channel is obtained by definite integral over a preset jet element along the effective opening height range of the inner channel, based on the equivalent interference relationship constructed by the static blocking and rotating dynamic sweeping blocking effects of the blades.

3. The method according to claim 1, characterized in that, Based on the target control parameters and key geometric parameters of the aero-engine, and combining the effects of static blade shielding and dynamic sweeping shielding, the effective jet flow rate that can be injected into the aero-engine's inner duct under the total jet flow rate of the target nozzle is calculated in real time, including: When it is determined that the jet ejected by the cleaning nozzle does not meet the preset uniform spraying condition in the radial direction of the effective opening height of the inner channel, for the case located in polar coordinates A radius within the range is Width is The thin circular band, expressed as: The actual effective permeability coefficient of the thin annular belt was determined. ; Based on the total jet flow rate and average axial velocity of the target jet under the current control cycle, the jet spatial distribution function of the cleaning nozzle is constructed. ; Based on the actual effective permeability coefficient and jet spatial distribution function Construct the calculus flow field truncation formula: ; The differential integral flow field truncation formula is solved in real time using a preset numerical integration method to obtain the effective jet flow rate that can be injected into the inner duct of the aero-engine under the total jet flow rate Q of the target nozzle. ; in, The average axial velocity of the target jet. Let L be the target actual rotational speed, L be the axial chord length of the blade, and Z be the number of blades. Where h is the static shielding thickness of the blade, and h is the effective opening height of the inner channel. The radius of the inner wheel hub.

4. The method according to claim 3, characterized in that, Based on the total jet flow rate and average axial velocity of the target jet under the current control cycle, the jet spatial distribution function of the cleaning nozzle is constructed, including: Query the empirical data table matching the aero-engine to obtain the distribution standard deviation corresponding to the total jet flow rate of the target nozzle and the average axial velocity of the target jet. ; According to the formula: The expected value of the target center is calculated. ; The expression: , is determined as the jet spatial distribution function of the cleaning nozzle.

5. The method according to any one of claims 2-4, characterized in that, After filtering and denoising the total nozzle jet flow rate, average axial velocity of the jet, and actual engine speed under cleaning conditions of the cleaning nozzles in the real-time acquired data of the aero-engine cleaning system to obtain the target control parameters, the method further includes: Determine whether the target's actual rotational speed and the target jet's average axial velocity satisfy the preset loss rate constraint formula: ; If not, the system determines that the current on-wing cleaning process is in an extremely abnormal condition and controls the aircraft engine cleaning system to perform a shutdown alarm operation.

6. The method according to claim 5, characterized in that, The method further includes: When the aircraft engine cleaning system is started to perform the cleaning operation on the aircraft engine, the initial rotational speed of the aircraft engine is collected; Based on the initial rotational speed and the loss rate constraint formula, the initial total jet flow rate of the cleaning nozzles in the aero-engine cleaning system is set.

7. The method according to claim 1, characterized in that, The total nozzle jet flow rate, average axial velocity of the jet, and actual engine speed under cleaning conditions in the real-time data collected from the cleaning nozzles of the aero-engine cleaning system are filtered and denoised to obtain the target control parameters, including: If the current control cycle is the first control cycle, then based on the preset initial state parameters, the real-time collected nozzle total jet flow rate, jet average axial velocity and actual rotation speed are processed by Kalman filtering to obtain the target control parameters; If the current control cycle is not the first control cycle, the Kalman filter is applied to the real-time collected nozzle total jet flow rate, average axial velocity of the jet, and actual rotation speed based on the state estimate of the previous historical control cycle to obtain the target control parameters. Based on the difference between the effective jet flow rate and the preset target cleaning water flow rate, the output frequency of the variable frequency water pump in the aircraft engine cleaning system is adjusted according to the embedded control algorithm, including: Based on the difference between the effective jet flow rate and the preset target cleaning water flow rate, the output frequency of the variable frequency water pump in the aero-engine cleaning system is adjusted according to any one of the embedded standard PID control algorithm, fuzzy PID control algorithm, sliding mode variable structure control algorithm, or model predictive control algorithm.

8. An electronic device, characterized in that, The electronic device includes: At least one processor; and a memory communicatively connected to said at least one processor; wherein, The memory stores a computer program that can be executed by the at least one processor, the computer program being executed by the at least one processor to enable the at least one processor to perform the method for estimating and controlling the amount of water entering the aircraft engine during wing cleaning as described in any one of claims 1-7.

9. A computer-readable storage medium, characterized in that, The computer-readable storage medium stores computer instructions that, when executed by a processor, implement the method for estimating and controlling the water inflow during wing cleaning of an aircraft engine as described in any one of claims 1-7.

10. A computer program product, characterized in that, The computer program product includes a computer program that, when executed by a processor, implements the method for estimating and controlling the water inflow during wing cleaning of an aero-engine according to any one of claims 1-7.

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