Online monitoring method and monitoring equipment for characteristics of aero-engine nozzle and readable storage medium

Abstract

The invention relates to an aero-engine nozzle characteristic online monitoring method, monitoring equipment and a readable storage medium. The online monitoring method for the characteristics of the aero-engine nozzle comprises the steps that S1, the flow characteristics of an auxiliary oil way fuel nozzle and the flow characteristics of a main oil way fuel nozzle are determined respectively; s2, on the basis of rated characteristic lines of the auxiliary oil way fuel nozzle and the main oil way fuel nozzle, a P% first range is selected to conduct auxiliary oil way fuel nozzle flow characteristic monitoring, a P% second range is selected to conduct main oil way fuel nozzle flow characteristic monitoring, and corresponding flow characteristic lines are generated; and S3, the flow characteristic line and the rated characteristic line are compared, and whether the main oil way fuel nozzle and / or the auxiliary oil way fuel nozzle corresponding to the flow characteristic line are / is abnormal or not is judged. The invention provides an aero-engine nozzle characteristic on-line monitoring method, monitoring equipment and a readable storage medium, which can effectively monitor the characteristic change of a fuel nozzle and further determine whether the characteristic of the fuel nozzle is abnormal or not.

Description

Technical Field

[0001] The present invention relates to the technical field of aircraft engine monitoring, and in particular to an aircraft engine nozzle characteristic online monitoring method, monitoring equipment and a readable storage medium. Background Art

[0002] Figure 1 The schematic diagram of the aircraft engine fuel system of the prior art is shown. As shown in the figure, the conventional aircraft engine fuel system 100 is mainly composed of a low-pressure pump 101, a high-pressure pump 102, a constant pressure valve 103, an actuating component 104, a high-pressure shut-off valve 105, a fuel grading valve 106, a secondary oil circuit fuel nozzle 107, a main oil circuit fuel nozzle 108, a metering valve 109, a pressure difference valve 110, an oil return valve 111, an overrun valve 112, etc. In order to perform necessary status monitoring and calculation, the aircraft engine fuel system 100 is usually provided with a fuel main pipe pressure sensor 113 and a combustion chamber back pressure sensor 114. After the aircraft fuel is pressurized by the low-pressure pump 101 and the high-pressure pump 102, it enters the fuel main pipe and the fuel nozzles 107 and 108 through the metering valve 109 and the high-pressure shut-off valve 105 and is supplied to the engine combustion chamber 115. The metering valve 109 is used to meter the amount of fuel to the engine combustion chamber 115; the high-pressure shut-off valve 105 is used to maintain the system with sufficient minimum servo pressure and cut off the fuel to the engine combustion chamber 115 after the engine stops; the differential pressure valve 110 is used to ensure that the pressure difference before and after the metering valve 109 is constant, so that the position of the metering valve 109 can control the amount of fuel to the combustion chamber 115; the return valve 111 is used to return the fuel provided by the high-pressure pump 102 that exceeds the engine demand to the low-pressure pump 101. The fuel grading valve 106 is used for fuel grading in order to improve the atomization effect of the fuel nozzle. When the flow rate of the combustion chamber 115 is small, the fuel is supplied to the auxiliary fuel nozzle 107 of the combustion chamber, and when the flow rate of the combustion chamber 115 is large, the fuel is supplied to the main fuel nozzle 108 of the combustion chamber 115. In order to meet the requirements of the main and auxiliary oil circuit control of the combustion chamber 115, a fuel grading control valve 106 is provided. The grading control valve can be electrically controlled or pressure controlled to achieve switch or continuous grading control. The fuel main pressure sensor 113 is usually used to determine whether the fuel is shut off. The combustion chamber back pressure sensor 114 is an important sensor of the aircraft engine 3 section and plays a vital role in the oil-gas ratio control law.

[0003] The main purpose of the fuel nozzles 107 and 108 is to achieve functions such as fuel atomization, stable oil-gas mixing, and stable combustion. Aircraft engines often have multiple nozzles. For a single nozzle, the nozzle diameter is very small. Since the main pipe may be involved in the fuel after parking or there is incomplete combustion of the fuel during the operation of the engine, it will cause carbon deposition and coking of the nozzle over time, change the characteristics, and even cause complete blockage, affecting the normal operation of the engine. The current engine fuel nozzle maintenance strategy mostly adopts a condition-based maintenance plan, which needs to determine whether to replace the nozzle based on the nozzle inspection results. Conventional nozzle inspection plans are mostly ground inspection plans such as endoscopes. This plan is weak for small-aperture nozzles and cannot determine whether coking occurs through visual inspection. At the same time, inspection plans such as endoscope borescopes need to be carried out on the ground, with a long inspection cycle and high consumption costs. Summary of the invention

[0004] In view of the above problems in the prior art, the present invention proposes an online monitoring method, monitoring equipment and readable storage medium for aircraft engine nozzle characteristics, which can effectively monitor changes in fuel nozzle characteristics and further determine whether there is any abnormality in the fuel nozzle characteristics.

[0005] Specifically, the present invention proposes an online monitoring method for nozzle characteristics of an aircraft engine. The fuel system of the aircraft engine includes a fuel grading valve, a main oil circuit fuel nozzle, a secondary oil circuit fuel nozzle and a combustion chamber. Metered oil enters the fuel grading valve through a fuel main pipe, is supplied to the main oil circuit fuel nozzle and the secondary oil circuit fuel nozzle under the control of the fuel grading valve, and then enters the combustion chamber for combustion. The online monitoring method includes the following steps:

[0006] S1, respectively determining the flow characteristics of the auxiliary oil circuit fuel nozzle and the flow characteristics of the main oil circuit fuel nozzle, the calculation formula of the flow characteristics of the auxiliary oil circuit fuel nozzle is: Wf*P% / (P22-Ps3), and the calculation formula of the flow characteristics of the main oil circuit fuel nozzle is: Wf*(1-P%) / (P22-Ps3);

[0007] Wherein Wf is the metered fuel entering the fuel grading valve through the fuel main pipe, P% is the fuel ratio of the main oil circuit, P% = main oil circuit fuel / metered fuel Wf, P22 is the pre-injection pressure of the fuel nozzle, and Ps3 is the back pressure of the combustion chamber;

[0008] S2, based on the rated characteristic lines of the auxiliary fuel line fuel nozzle and the main fuel line fuel nozzle, selecting a first range of P% to monitor the flow characteristic of the auxiliary fuel line fuel nozzle, selecting a second range of P% to monitor the flow characteristic of the main fuel line fuel nozzle, and generating corresponding flow characteristic lines;

[0009] S3, comparing the flow characteristic line with the rated characteristic line, and determining whether there is an abnormality in the main oil circuit fuel nozzle and / or the auxiliary oil circuit fuel nozzle corresponding to the flow characteristic line.

[0010] According to one embodiment of the present invention, step S3 includes:

[0011] Based on the rated characteristic line and the value range of P%, the early warning characteristic lines of the auxiliary oil circuit fuel nozzle and the main oil circuit fuel nozzle are set. If the flow characteristic line drifts toward the corresponding early warning characteristic line and touches the early warning characteristic line, it is determined that the main oil circuit fuel nozzle and / or the auxiliary oil circuit fuel nozzle corresponding to the flow characteristic line is abnormal.

[0012] According to an embodiment of the present invention, the first range of P% is selected to be 60% to 80%.

[0013] According to an embodiment of the present invention, the second range of P% is selected to be 20% to 40%.

[0014] According to an embodiment of the present invention, in step S3, it is set that under the same pressure, the flow rate ratio of the warning characteristic line to the rated characteristic line is 0.9:1.

[0015] According to one embodiment of the present invention, the fuel grading valve includes a grading valve with a movable window and a grading electro-hydraulic servo valve, the fuel main pipe is connected to the auxiliary oil circuit fuel nozzle and the main oil circuit fuel nozzle through the grading valve, and the grading electro-hydraulic servo valve connects the two ends of the grading valve to realize pressure switching, so as to control the movement of the movable window to adjust the fuel supply ratio of the auxiliary oil circuit fuel nozzle and the main oil circuit fuel nozzle.

[0016] According to one embodiment of the present invention, a first pressure sensor is provided on the fuel main pipe for obtaining the pre-injection pressure P22 of the fuel nozzle, and a second pressure sensor is provided in the combustion chamber for obtaining the back pressure Ps3 of the combustion chamber.

[0017] The present invention also provides an online monitoring device for aircraft engine nozzle characteristics, comprising a memory, a processor, and a computer program stored in the memory and executable on the processor, wherein the processor implements the steps of any of the aforementioned methods for online monitoring of aircraft engine nozzle characteristics when executing the computer program.

[0018] The present invention also provides a computer-readable storage medium having a computer program stored thereon, wherein when the computer program is executed by a processor, the steps of any of the aforementioned methods for online monitoring of nozzle characteristics of an aero-engine are implemented.

[0019] The present invention provides an online monitoring method, monitoring equipment and readable storage medium for aircraft engine nozzle characteristics. Based on the pressure changes before and after the fuel nozzle and the fuel grading ratio data, the nozzle characteristics of the main and auxiliary oil circuit fuel nozzles are monitored, and compared with the rated characteristic lines of the main and auxiliary oil circuit fuel nozzles to determine whether the fuel nozzle characteristics are abnormal.

[0020] It is to be understood that both the foregoing general description and the following detailed description of the present invention are exemplary and explanatory and are intended to provide further explanation of the invention as claimed. BRIEF DESCRIPTION OF THE DRAWINGS

[0021] The accompanying drawings are included to provide further explanation of the present invention, and are incorporated into and constitute a part of this application. The accompanying drawings illustrate embodiments of the present invention and together with the description serve to explain the principle of the present invention.

[0022] In the attached figure:

[0023] Figure 1 A schematic diagram of a prior art aircraft engine fuel system is shown.

[0024] Figure 2 A flowchart of an on-line monitoring method for nozzle characteristics of an aircraft engine according to an embodiment of the present invention is shown.

[0025] Figure 3 A partial schematic diagram of an aircraft engine fuel system according to an embodiment of the present invention is shown.

[0026] Figure 4 A schematic diagram showing online monitoring results of aero-engine nozzle characteristics according to an embodiment of the present invention.

[0027] The above drawings include the following reference numerals:

[0028] Engine fuel system 100

[0029] Low Pressure Pump 101

[0030] High pressure pump 102

[0031] Constant pressure valve 103

[0032] Actuating component 104

[0033] High pressure shut-off valve 105

[0034] Fuel staging valve 106

[0035] Auxiliary fuel line fuel nozzle 107

[0036] Main oil line fuel nozzle 108

[0037] Metering valve 109

[0038] Differential pressure valve 110

[0039] Oil return valve 111

[0040] Overdrive valve 112

[0041] Pressure sensor 113

[0042] Back pressure sensor 114

[0043] Combustion chamber 115

[0044] Sliding Window 301

[0045] Grading valve 302

[0046] Grading electro-hydraulic servo valve 303

[0047] Fuel main 304

[0048] First pressure sensor 305

[0049] Second pressure sensor 306

[0050] Auxiliary fuel line fuel nozzle rated characteristic line 401

[0051] Main fuel line fuel nozzle rated characteristic line 402

[0052] Auxiliary oil circuit fuel nozzle flow characteristic line 403

[0053] Main oil circuit fuel nozzle flow characteristic line 404

[0054] Auxiliary fuel line fuel nozzle warning characteristic line 405

[0055] Main oil circuit fuel nozzle warning characteristic line 406 DETAILED DESCRIPTION

[0056] It should be noted that, in the absence of conflict, the embodiments and features in the embodiments of the present application may be combined with each other.

[0057] The technical solutions in the embodiments of the present application will be described clearly and completely below in conjunction with the drawings in the embodiments of the present application. Obviously, the described embodiments are only a part of the embodiments of the present application, rather than all of the embodiments. The following description of at least one exemplary embodiment is actually only illustrative and is by no means intended to limit the present application and its application or use. Based on the embodiments in the present application, all other embodiments obtained by ordinary technicians in the field without creative work are within the scope of protection of the present application.

[0058] It should be noted that the terms used herein are only for describing specific embodiments and are not intended to limit the exemplary embodiments according to the present application. As used herein, unless the context clearly indicates otherwise, the singular form is also intended to include the plural form. In addition, it should be understood that when the terms "comprise" and / or "include" are used in this specification, it indicates the presence of features, steps, operations, devices, components and / or combinations thereof.

[0059] Unless otherwise specifically stated, the relative arrangement, numerical expressions and numerical values ​​of the parts and steps set forth in these embodiments do not limit the scope of the application. Meanwhile, it should be understood that, for ease of description, the sizes of the various parts shown in the accompanying drawings are not drawn according to actual proportional relationships. The technology, methods and equipment known to those of ordinary skill in the relevant art may not be discussed in detail, but in appropriate cases, the technology, methods and equipment should be considered as a part of the specification. In all examples shown and discussed here, any specific value should be interpreted as being merely exemplary, rather than as a limitation. Therefore, other examples of exemplary embodiments may have different values. It should be noted that similar reference numerals and letters represent similar items in the following drawings, and therefore, once a certain item is defined in an accompanying drawing, it does not need to be further discussed in subsequent drawings.

[0060] In the description of the present application, it should be understood that the directions or positional relationships indicated by directional words such as "front, back, up, down, left, right", "lateral, vertical, perpendicular, horizontal" and "top, bottom" are usually based on the directions or positional relationships shown in the drawings, and are only for the convenience of describing the present application and simplifying the description. Unless otherwise specified, these directional words do not indicate or imply that the device or element referred to must have a specific direction or be constructed and operated in a specific direction, and therefore cannot be understood as limiting the scope of protection of the present application; the directional words "inside and outside" refer to the inside and outside relative to the contours of each component itself.

[0061] In addition, it should be noted that the use of words such as "first" and "second" to define components is only for the convenience of distinguishing the corresponding components. If not otherwise stated, the above words have no special meaning and cannot be understood as limiting the scope of protection of this application. In addition, although the terms used in this application are selected from well-known and commonly used terms, some terms mentioned in the specification of this application may be selected by the applicant at his or her discretion, and their detailed meanings are explained in the relevant parts of the description of this article. In addition, it is required to understand this application not only by the actual terms used, but also by the meaning implied by each term.

[0062] refer to Figure 1After the aircraft fuel is pressurized by the low-pressure pump 101, the system low-pressure pressure Pb is formed. The fuel is then pressurized by the high-pressure pump 102 under the action of the load to form the high-pressure oil pressure Ps. One way of high-pressure oil is supplied to the constant-pressure valve 103 of the servo system to adjust the constant-pressure oil pressure Pc; the other way is supplied to the metering valve 109. The pressure before the metering valve 109 is P1, and the pressure after the metering valve is P2. The differential pressure valve 110 senses the pressure before and after the metering valve 109, and maintains the pressure difference before and after the metering valve 109 constant by controlling the return oil valve 111, so that the metering flow is only related to the metering valve opening. The fuel enters the high-pressure shut-off valve 105 through the metering valve 109. When the metering flow is small, the high-pressure shut-off valve 105 is closed to ensure that the fuel system 100 has sufficient high-pressure oil pressure Ps. When the metering flow increases, the high-pressure shut-off valve 105 opens, and the pressure after the high-pressure shut-off valve 105 is P22. The metering oil passes through the high-pressure shut-off valve 105 and enters the fuel grading valve 106, and is supplied to the main oil circuit fuel nozzle 108 and the auxiliary oil circuit fuel nozzle 107 under the control of the fuel grading valve 106. The back pressure of the combustion chamber behind the nozzle is Ps3.

[0063] In a typical aircraft engine fuel system 100, the pressure conditions of the metered fuel line are:

[0064] Ps>P1>P2>P22>Ps3;

[0065] The pressure conditions of the servo fuel line are as follows:

[0066] Ps>Pc>Pb; Pc-Pb=constant.

[0067] Figure 2 The flowchart of the method for online monitoring of nozzle characteristics of an aircraft engine according to one embodiment of the present invention is shown. As shown in the figure, the present invention provides a method for online monitoring of nozzle characteristics of an aircraft engine. The method is applicable to Figure 1 The existing aircraft engine fuel system 100 is provided. The aircraft engine fuel system 100 includes a fuel grading valve 106, a main oil line fuel nozzle 108, a secondary oil line fuel nozzle 107 and a combustion chamber 115. The metering oil enters the fuel grading valve 106 through the fuel main pipe, and is supplied to the main oil line fuel nozzle 108 and the secondary oil line fuel nozzle 107 under the control of the fuel grading valve 106, and then enters the combustion chamber 115 for combustion. The online monitoring method includes the following steps:

[0068] S1, respectively determine the flow characteristics of the auxiliary oil circuit fuel nozzle 107 and the flow characteristics of the main oil circuit fuel nozzle 108, the calculation formula of the flow characteristics of the auxiliary oil circuit fuel nozzle is: Wf*P% / (P22-Ps3); the calculation formula of the flow characteristics of the main oil circuit fuel nozzle is: Wf*(1-P%) / (P22-Ps3);

[0069] Where Wf is the metered fuel entering the fuel grading valve 106 through the fuel main pipe. The metered fuel Wf can be back-calculated according to the position of the metering valve 109. P% is the main fuel ratio, P% = main fuel / metered fuel Wf, P22 is the pre-injection pressure of the fuel nozzle, and Ps3 is the back pressure of the combustion chamber 115. It should be noted that the flow characteristic reflects the relationship between flow and pressure. The fuel grading valve 106 is used to control the fuel flow ratio entering the auxiliary fuel nozzle 107 and the main fuel nozzle 108. When the engine is in a small operating condition such as slow speed and cruising, the fuel grading valve 106 mainly supplies fuel to the auxiliary fuel nozzle 107. At this time, the fuel of the auxiliary fuel nozzle 107 accounts for a high proportion. When the engine is in a small operating condition such as takeoff and climbing, the fuel grading valve 106 mainly supplies fuel to the main fuel nozzle 108. At this time, the fuel of the main fuel nozzle 108 accounts for a high proportion.

[0070] S2, based on the rated characteristic lines of the auxiliary fuel nozzle 107 and the main fuel nozzle 108, in order to ensure that the pre-injection pressure P22 of the fuel nozzle is close to the actual pressure before the nozzle, and according to the data segment with higher actual calculation accuracy in the test data, the first range of P% is selected to monitor the flow characteristics of the auxiliary fuel nozzle 107, and the second range of P% is selected to monitor the flow characteristics of the main fuel nozzle 108, and the corresponding flow characteristic lines are generated. The characteristic lines reflect the characteristic change trends of the auxiliary fuel nozzle 107 and the main fuel nozzle 108.

[0071] S3, compare the flow characteristic line with the rated characteristic line, and determine whether there is any abnormality in the main oil circuit fuel nozzle 108 and / or the auxiliary oil circuit fuel nozzle 107 corresponding to the flow characteristic line. If there is any abnormality, it means that coking has intensified and the corresponding main oil circuit fuel nozzle 108 and / or the auxiliary oil circuit fuel nozzle 107 needs to be replaced.

[0072] Preferably, step S3 includes:

[0073] Based on the rated characteristic line and the value range of P%, the warning characteristic lines of the auxiliary oil circuit fuel nozzle 107 and the main oil circuit fuel nozzle 108 are set. If the flow characteristic line drifts toward the corresponding warning characteristic line and touches the warning characteristic line, it is determined that the main oil circuit fuel nozzle 108 and / or the auxiliary oil circuit fuel nozzle 107 corresponding to the flow characteristic line is abnormal. Specifically, as the coking of the nozzle intensifies, the characteristic lines of the auxiliary oil circuit fuel nozzle 107 and the main oil circuit fuel nozzle 108 will drift toward the warning characteristic line. If they reach the position of the warning characteristic line, it is determined that the coking cannot be used and needs to be replaced.

[0074] Preferably, the first range of P% is selected to be 60% to 80%. Under this working condition, fuel is mainly supplied to the auxiliary oil circuit fuel nozzle 107, and the pre-injection pressure P22 of the fuel nozzle is close to the actual pressure before the auxiliary oil circuit fuel nozzle 107.

[0075] Preferably, the second range of P% is selected to be 20% to 40%. Under this working condition, fuel is mainly supplied to the main oil circuit fuel nozzle 108, and the pre-injection pressure P22 of the fuel nozzle is close to the actual pressure before the main oil circuit fuel nozzle 108.

[0076] Preferably, in step S3, the flow rate ratio of the warning characteristic line to the rated characteristic line is set to 0.9:1 under the same pressure. That is, under the same pressure, the flow rate of the warning characteristic line is set to be 10% lower than the flow rate of the rated characteristic line. If the flow rate characteristic line drifts toward the corresponding warning characteristic line and touches the warning characteristic line, it is determined that the fuel nozzle is abnormal. As an example and not a limitation, the warning characteristic line can be set according to actual conditions.

[0077] Figure 3 A partial schematic diagram of an aircraft engine fuel system according to an embodiment of the present invention is shown. As shown in the figure, the fuel grading valve 106 of the engine fuel system 100 includes a grading valve 302 with a movable window 301 and a grading electro-hydraulic servo valve 303. The fuel main pipe 304 is connected to the auxiliary oil circuit fuel nozzle 107 and the main oil circuit fuel nozzle 108 through the grading valve 302. The grading electro-hydraulic servo valve 303 realizes the switching of the constant pressure Pc and the return oil pressure Pb at both ends connected to the grading valve 302 according to the electrical signal sent by the engine electronic controller, so as to realize the up and down movement of the movable window 301. The movable window 301 moves up and down to change the fuel supply oil circuit area of ​​the fuel nozzle, so as to adjust the fuel supply ratio of the auxiliary oil circuit fuel nozzle 107 and the main oil circuit fuel nozzle 108.

[0078] Preferably, a first pressure sensor 305 is provided on the fuel main pipe 304 for obtaining the pre-injection pressure P22 of the fuel nozzle, and a second pressure sensor 306 is provided in the combustion chamber 115 for obtaining the back pressure Ps3 of the combustion chamber 115.

[0079] Furthermore, when the movable window 301 moves upward and the graded valve 302 and the auxiliary oil circuit fuel nozzle 107 form a series flow path, the auxiliary oil circuit is mainly supplied with oil, and the throttling area of ​​the graded valve 302 is >> the auxiliary oil circuit nozzle. Therefore, the flow resistance of the auxiliary oil circuit nozzle is >> the flow resistance of the graded valve 302. At this time, the pre-injection pressure of the fuel nozzle P22 ≈ the pre-injection pressure of the auxiliary oil circuit fuel nozzle 107, and the flow characteristics of the auxiliary oil circuit fuel nozzle 107 can be characterized by Wf*P% / (P22-Ps3). When the main oil circuit is mainly supplied with oil, the movable window 301 moves downward, and the graded valve 302 and the main oil circuit fuel nozzle 108 form a series flow path. The throttling area of ​​the graded valve 302 is >> the main oil circuit fuel nozzle 108. Therefore, the flow resistance of the main oil circuit fuel nozzle 108 is >> the flow resistance of the graded valve 302. At this time, the pre-injection pressure of the fuel nozzle P22 ≈ the pre-injection pressure of the main oil circuit fuel nozzle 108. The flow characteristics of the main oil circuit fuel nozzle 108 can be characterized by Wf*(1-P%) / (P22-Ps3).

[0080] Figure 4 The schematic diagram of the online monitoring result of the nozzle characteristic of an aircraft engine according to an embodiment of the present invention is shown. As shown in the figure, the X-axis is used to represent the pressure (Mpa), and the Y-axis is used to represent the flow rate (kg / h). As mentioned above, based on the rated characteristic line 401 of the auxiliary oil circuit fuel nozzle and the rated characteristic line 402 of the main oil circuit fuel nozzle, in order to ensure that the pre-injection pressure P22 of the fuel nozzle is close to the actual pressure before the nozzle, and according to the data segment with higher actual calculation accuracy in the test data, P% is selected at 60% to 80% to monitor the flow characteristic of the auxiliary oil circuit fuel nozzle 107, and the corresponding pressure value range in the reference figure is about 1.2 to 3.3Mpa, and the auxiliary oil circuit fuel nozzle flow characteristic line 403 (indicated by dot-dash line) is generated. P% is selected at 20% to 40% to monitor the flow characteristic of the main oil circuit fuel nozzle 108, and the corresponding pressure value range in the reference figure is about 3.9 to 4Mpa, and the corresponding main oil circuit fuel nozzle flow characteristic line 404 (indicated by dot-dash line) is generated.

[0081] Based on the value range of the rated characteristic lines 401, 402 and P%, the auxiliary oil circuit fuel nozzle warning characteristic line 405 (indicated by the dashed line) and the main oil circuit fuel nozzle warning characteristic line 406 (indicated by the dashed line) are set. If the flow characteristic lines 403, 404 drift toward the corresponding warning characteristic lines 405, 406 and touch the warning characteristic lines 405, 406, it is determined that the main oil circuit fuel nozzle 108 and / or the auxiliary oil circuit fuel nozzle 107 corresponding to the flow characteristic lines 403, 404 are abnormal. The direction indicated by the arrow in the figure is the drift direction of the flow characteristic lines 403, 404. As the nozzle coking intensifies, the auxiliary oil circuit fuel nozzle flow characteristic line 403 and the main oil circuit fuel nozzle flow characteristic line 404 will drift toward the corresponding warning characteristic lines 405, 406. If they reach the position of the warning characteristic lines 405, 406, it is determined that the coking cannot be used and needs to be replaced.

[0082] Under the same pressure, the ratio of the flow rate (value) of the warning characteristic lines 405 and 406 to the flow rate (value) of the rated characteristic line is 0.9:1. Assuming that in the monitoring range of the main oil circuit fuel nozzle 108, when the pressure is 5Mpa, the actual flow value corresponding to the monitoring main oil circuit fuel nozzle flow characteristic line 404 is 6000kg / h, then this flow value exceeds the corresponding flow value of 5400kg / h of the main oil circuit fuel nozzle warning characteristic line 406, indicating that the main oil circuit fuel nozzle 108 is working normally. If the pressure is 5Mpa, the actual flow value corresponding to the monitoring main oil circuit fuel nozzle flow characteristic line 404 is 5200kg / h, then this flow value is lower than the corresponding flow value of 5400kg / h of the main oil circuit fuel nozzle warning characteristic line 406, indicating that the main oil circuit fuel nozzle 108 is coked and cannot be used and needs to be replaced immediately. Similarly, within the monitoring range of the auxiliary oil circuit fuel nozzle 107, if the monitored auxiliary oil circuit fuel nozzle flow characteristic line 403 drifts toward the corresponding warning characteristic line 405 and touches the warning characteristic line 405, it is determined that the auxiliary oil circuit fuel nozzle 107 is abnormal and needs to be replaced.

[0083] The present invention also provides an online monitoring device for aircraft engine nozzle characteristics, comprising a memory, a processor, and a computer program stored in the memory and executable on the processor. When the processor executes the computer program, the steps of any of the aforementioned methods for online monitoring of aircraft engine nozzle characteristics are implemented.

[0084] The present invention also provides a computer-readable storage medium having a computer program stored thereon, and when the computer program is executed by a processor, the steps of any of the aforementioned methods for online monitoring of nozzle characteristics of an aero-engine are implemented.

[0085] Among them, the specific implementation methods and technical effects of the aircraft engine nozzle characteristic online monitoring equipment and computer-readable storage medium can be referred to the embodiments of the aircraft engine nozzle characteristic online monitoring method provided by the present invention, which will not be repeated here.

[0086] The invention provides an on-line monitoring method, monitoring device and readable storage medium for aircraft engine nozzle characteristics, which have the following advantages:

[0087] The fuel nozzle characteristics can be monitored in real time during each flight cycle, and the nozzle characteristics can be monitored at any time;

[0088] Monitoring data can be accumulated to predict and estimate the degree of nozzle blockage, supporting situation-based maintenance;

[0089] No additional sensors or other hardware structures are added on the basis of the existing technology, and it is easy to implement.

[0090] Those skilled in the art will further appreciate that the various illustrative logic blocks, modules, circuits, and algorithm steps described in conjunction with the embodiments disclosed herein may be implemented as electronic hardware, computer software, or a combination of the two. To clearly illustrate this interchangeability of hardware and software, various illustrative components, blocks, modules, circuits, and steps are generally described above in terms of their functionality. Whether such functionality is implemented as hardware or software depends on the specific application and the design constraints imposed on the overall system. The technician may implement the described functionality in different ways for each specific application, but such implementation decisions should not be interpreted as resulting in a departure from the scope of the present invention.

[0091] The various illustrative logic modules and circuits described in conjunction with the embodiments disclosed herein may be implemented or executed with a general purpose processor, a digital signal processor (DSP), an application specific integrated circuit (ASIC), a field programmable gate array (FPGA) or other programmable logic device, discrete gate or transistor logic, discrete hardware components, or any combination thereof designed to perform the functions described herein. A general purpose processor may be a microprocessor, but in the alternative, the processor may be any conventional processor, controller, microcontroller, or state machine. The processor may also be implemented as a combination of computing devices, such as a combination of a DSP and a microprocessor, a plurality of microprocessors, one or more microprocessors in cooperation with a DSP core, or any other such configuration.

[0092] The steps of the method or algorithm described in conjunction with the embodiments disclosed herein may be embodied directly in hardware, in a software module executed by a processor, or in a combination of the two. The software module may reside in a RAM memory, a flash memory, a ROM memory, an EPROM memory, an EEPROM memory, a register, a hard disk, a removable disk, a CD-ROM, or any other form of storage medium known in the art. An exemplary storage medium is coupled to a processor so that the processor can read and write information from / to the storage medium. In an alternative, a storage medium may be integrated into a processor. The processor and the storage medium may reside in an ASIC. The ASIC may reside in a user terminal. In an alternative, the processor and the storage medium may reside in a user terminal as discrete components.

[0093] In one or more exemplary embodiments, the functions described may be implemented in hardware, software, firmware, or any combination thereof. If implemented as a computer program product in software, each function may be stored on or transmitted by a computer-readable medium as one or more instructions or codes. Computer-readable media include both computer storage media and communication media, including any medium that facilitates the transfer of a computer program from one place to another. Storage media may be any available medium that can be accessed by a computer. As an example and not limitation, such a computer-readable medium may include RAM, ROM, EEPROM, CD-ROM or other optical disk storage, disk storage or other magnetic storage device, or any other medium that can be used to carry or store the desired program code in the form of an instruction or data structure and can be accessed by a computer. Any connection is also properly referred to as a computer-readable medium. For example, if the software is transmitted from a website, a server, or other remote source using a coaxial cable, a fiber optic cable, a twisted pair, a digital subscriber line (DSL), or wireless technologies such as infrared, radio, and microwaves, the coaxial cable, fiber optic cable, twisted pair, DSL, or wireless technologies such as infrared, radio, and microwaves are included in the definition of the medium. Disk and disc as used herein include compact disc (CD), laser disc, optical disc, digital versatile disc (DVD), floppy disk and Blu-ray disc, wherein disk often reproduces data magnetically, while disc reproduces data optically with lasers. Combinations of the above should also be included within the scope of computer-readable media.

[0094] It will be apparent to those skilled in the art that various modifications and variations may be made to the above exemplary embodiments of the present invention without departing from the spirit and scope of the present invention. Therefore, it is intended that the present invention covers modifications and variations of the present invention that fall within the scope of the appended claims and their equivalent technical solutions.

Claims

1. An online monitoring method for nozzle characteristics of an aircraft engine, wherein the fuel system of the aircraft engine comprises a fuel grading valve, a main fuel line fuel nozzle, a secondary fuel line fuel nozzle and a combustion chamber, and the metering oil enters the fuel grading valve through a fuel main pipe, and is controlled by the fuel grading valve to be supplied to the main fuel line fuel nozzle and the secondary fuel line fuel nozzle, and then enters the combustion chamber for combustion, and the online monitoring method comprises the following steps: S1, respectively determining the flow characteristics of the auxiliary oil circuit fuel nozzle and the flow characteristics of the main oil circuit fuel nozzle, the calculation formula of the flow characteristics of the auxiliary oil circuit fuel nozzle is: Wf*P% / (P22-Ps3), and the calculation formula of the flow characteristics of the main oil circuit fuel nozzle is: Wf*(1-P%) / (P22-Ps3); Wherein Wf is the metered fuel entering the fuel grading valve through the fuel main pipe, P% is the fuel ratio of the main oil circuit, P% = main oil circuit fuel / metered fuel Wf, P22 is the pre-injection pressure of the fuel nozzle, and Ps3 is the back pressure of the combustion chamber; S2, based on the rated characteristic lines of the auxiliary fuel line fuel nozzle and the main fuel line fuel nozzle, selecting a first range of P% to monitor the flow characteristic of the auxiliary fuel line fuel nozzle, selecting a second range of P% to monitor the flow characteristic of the main fuel line fuel nozzle, and generating corresponding flow characteristic lines; S3, comparing the flow characteristic line with the rated characteristic line, and determining whether there is an abnormality in the main oil circuit fuel nozzle and / or the auxiliary oil circuit fuel nozzle corresponding to the flow characteristic line.

2. The method for online monitoring of nozzle characteristics of an aircraft engine according to claim 1, characterized in that: Step S3 includes: Based on the rated characteristic line and the value range of P%, the early warning characteristic lines of the auxiliary oil circuit fuel nozzle and the main oil circuit fuel nozzle are set. If the flow characteristic line drifts toward the corresponding early warning characteristic line and touches the early warning characteristic line, it is determined that the main oil circuit fuel nozzle and / or the auxiliary oil circuit fuel nozzle corresponding to the flow characteristic line is abnormal.

3. The method for online monitoring of nozzle characteristics of an aircraft engine according to claim 1, characterized in that: The first range of P% is selected to be 60% to 80%.

4. The method for online monitoring of nozzle characteristics of an aircraft engine according to claim 1, characterized in that: The second range of P% is selected to be 20% to 40%.

5. The method for online monitoring of nozzle characteristics of an aircraft engine according to claim 2, characterized in that: In step S3, it is set that under the same pressure, the flow rate ratio of the warning characteristic line to the rated characteristic line is 0.9:

1.

6. The method for online monitoring of nozzle characteristics of an aircraft engine according to claim 1, characterized in that: The fuel grading valve includes a grading valve with a movable window and a grading electro-hydraulic servo valve. The fuel main pipe is connected to the auxiliary oil circuit fuel nozzle and the main oil circuit fuel nozzle through the grading valve. The grading electro-hydraulic servo valve connects the two ends of the grading valve to realize pressure switching, so as to control the movement of the movable window to adjust the fuel supply ratio of the auxiliary oil circuit fuel nozzle and the main oil circuit fuel nozzle.

7. The method for online monitoring of nozzle characteristics of an aircraft engine according to claim 6, characterized in that: A first pressure sensor is provided on the fuel main pipe for obtaining the pre-injection pressure P22 of the fuel nozzle, and a second pressure sensor is provided in the combustion chamber for obtaining the back pressure Ps3 of the combustion chamber.

8. An on-line monitoring device for nozzle characteristics of an aircraft engine, comprising a memory, a processor, and a computer program stored in the memory and executable on the processor, characterized in that: When the processor executes the computer program, the steps of the method for online monitoring of nozzle characteristics of an aero-engine as claimed in any one of claims 1 to 5 are implemented.

9. A computer-readable storage medium having a computer program stored thereon, characterized in that: When the computer program is executed by a processor, the steps of the method for online monitoring of nozzle characteristics of an aero-engine as claimed in any one of claims 1 to 5 are implemented.

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