On-wing adjusting method and device for aero-engine

Abstract

The invention discloses an on-wing adjusting method and device for an aero-engine, and the method comprises the steps: carrying out the flow field simulation of a combustion chamber of the aero-engine, and obtaining the distribution characteristics of a flow field in the combustion chamber; microcosmic changes of the floating tile component are analyzed, and sediment distribution characteristics are obtained; according to the flow field distribution characteristics and the sediment distribution characteristics, the damage process of the combustion chamber of the aero-engine to be adjusted is reproduced; according to the flow field distribution characteristics, carrying out life analysis on the floating tile part; generating an on-wing adjustment scheme according to the damage process and the life analysis result; and according to the on-wing adjustment scheme, the aero-engine to be adjusted is adjusted. By adopting the embodiment of the invention, the fuel nozzle of the damaged combustion chamber lining plate can be accurately positioned, the replacement opportunity is determined, on-wing adjustment of the aero-engine is realized, the service life of the aero-engine is prolonged, and the disassembly and maintenance frequency and cost are reduced.

Description

Technical Field

[0001] The present invention relates to the technical field of on-wing engine maintenance, and in particular to an on-wing adjustment method and device for an aero-engine. Background Art

[0002] At present, damage to the combustion chamber liner of an aircraft engine is a common reason for the engine to be dispatched for replacement.

[0003] Currently, maintenance teams can only monitor the progression of combustor liner damage on-wing using borescopes. When damage reaches the required manual standards, the aircraft is dismantled and sent for repair. This high cost of repair can reach $7 million per aircraft, placing a heavy burden on airlines. Summary of the Invention

[0004] The technical problem to be solved by the present invention is to provide a method and device for on-wing adjustment of an aircraft engine. By accurately locating the fuel nozzle that damages the combustion chamber liner and determining the replacement time, the on-wing adjustment of the aircraft engine is achieved, thereby extending the service life of the aircraft engine and reducing the maintenance frequency and cost.

[0005] To solve the above technical problems, an embodiment of the present invention provides an on-wing adjustment method for an aircraft engine, comprising:

[0006] Performing flow field simulation on a combustion chamber of an aircraft engine to obtain flow field distribution characteristics in the combustion chamber; the flow field at least includes a temperature field;

[0007] Obtaining a floating tile component with ablation damage of an aircraft engine to be adjusted, and obtaining a deposit distribution characteristic by analyzing microscopic changes in the floating tile component;

[0008] applying a load to a floating tile sample component based on the flow field distribution characteristics and the deposit distribution characteristics so as to make the load consistent with the floating tile component, thereby reproducing the damage process of the combustion chamber of the aircraft engine to be adjusted; the floating tile sample component is consistent with the floating tile component of the aircraft engine to be adjusted before use;

[0009] performing a life analysis on the floating tile component according to the flow field distribution characteristics;

[0010] According to the damage process and the results of the life analysis, the location and replacement timing of the fuel nozzle of the damaged combustion chamber liner are obtained, and an on-wing adjustment plan is generated;

[0011] The aircraft engine to be adjusted is adjusted according to the on-wing adjustment plan.

[0012] As an improvement to the above solution, the flow field simulation of the combustion chamber of the aircraft engine is performed to obtain the flow field distribution characteristics in the combustion chamber, including:

[0013] Calculate the temperature field distribution under typical engine operating conditions and obtain the first flow field distribution characteristics;

[0014] Calculate the temperature field distribution when using different fuel nozzles and obtain the second flow field distribution characteristics;

[0015] The flow field distribution characteristics in the combustion chamber are obtained by combining the first flow field distribution characteristics and the second flow field distribution characteristics.

[0016] As an improvement to the above solution, obtaining the ablation-damaged floating tile component of the aircraft engine to be adjusted and analyzing the microscopic changes of the floating tile component to obtain the deposit distribution characteristics includes:

[0017] Obtaining a floating tile component with ablation damage of an aircraft engine to be adjusted;

[0018] The floating tile component is subjected to SEM testing, nanoindentation testing, and XRD testing to obtain changes in the thermal barrier coating on the surface of the combustion chamber and changes in the substrate microstructure of the combustion chamber before and after use;

[0019] According to the changes in the thermal barrier coating and the microstructure of the substrate, the deposit distribution characteristics are obtained.

[0020] As an improvement to the above solution, the life analysis of the floating tile component according to the flow field distribution characteristics includes:

[0021] According to the flow field distribution characteristics, the distribution characteristics of the temperature field on the combustion chamber wall are obtained;

[0022] The lifespan analysis of the floating tile component is performed using the distribution characteristics of the temperature field as a variable.

[0023] As an improvement to the above solution, the calculation of the temperature field distribution under typical engine operating conditions to obtain the first flow field distribution characteristics includes:

[0024] Obtain the gas pressure and temperature parameters at the inlet and outlet of the combustion chamber obtained from the test bench test;

[0025] The gas pressure and temperature parameters are used as boundary conditions to calculate the first temperature field distribution under typical operating conditions to obtain the first flow field distribution characteristics; the typical operating conditions include engine starting, engine acceleration and engine cruising.

[0026] As an improvement to the above solution, the calculation of the temperature field distribution when using different fuel nozzles to obtain the second flow field distribution characteristics includes:

[0027] calculating a second temperature field distribution in the combustion chamber using a plurality of fuel nozzles having different fault types, spray characteristics, and spray directions;

[0028] performing fuel injection tests using a plurality of fuel nozzles with different service cycles, and calculating a third temperature field distribution in the combustion chamber based on differences in injection cone angles, spray particle sizes, and injection velocities of the plurality of fuel nozzles;

[0029] A second flow field distribution characteristic is obtained according to the second temperature field distribution and the third temperature field distribution.

[0030] As an improvement to the above solution, the fault types include fuel injector blockage and nozzle deformation faults.

[0031] As an improvement to the above solution, after adjusting the aircraft engine according to the on-wing adjustment scheme, the method further includes:

[0032] monitoring the adjusted aircraft engine to track damage to its combustion chamber;

[0033] According to the damage condition, the time for the on-wing adjustment scheme to delay the damage to the combustion chamber is calculated.

[0034] An embodiment of the present invention further provides an on-wing adjustment device for an aircraft engine, comprising:

[0035] A flow field distribution characteristics generation module is used to perform flow field simulation on the combustion chamber of an aircraft engine to obtain flow field distribution characteristics in the combustion chamber; the flow field at least includes a temperature field;

[0036] A deposit distribution characteristic generating module is used to obtain a floating tile component with ablation damage of the aircraft engine to be adjusted, and obtain a deposit distribution characteristic by analyzing the microscopic changes of the floating tile component;

[0037] a damage process reproduction module, configured to apply a load to a floating tile sample component based on the flow field distribution characteristics and the deposit distribution characteristics, so as to make the load consistent with the floating tile component, thereby reproducing the damage process of the combustion chamber of the aircraft engine to be adjusted; the floating tile sample component is consistent with the floating tile component of the aircraft engine to be adjusted before use;

[0038] A life analysis module, configured to perform life analysis on the floating tile component according to the flow field distribution characteristics;

[0039] An on-wing adjustment plan generating module is configured to obtain the location and replacement timing of the fuel nozzle of the damaged combustion chamber liner according to the damage process and the results of the life analysis, and generate an on-wing adjustment plan;

[0040] The aircraft engine adjustment module is used to adjust the aircraft engine to be adjusted according to the on-wing adjustment plan.

[0041] As an improvement to the above solution, the flow field simulation of the combustion chamber of the aircraft engine is performed to obtain the flow field distribution characteristics in the combustion chamber, including:

[0042] Calculate the temperature field distribution under typical engine operating conditions and obtain the first flow field distribution characteristics;

[0043] Calculate the temperature field distribution when using different fuel nozzles and obtain the second flow field distribution characteristics;

[0044] The flow field distribution characteristics in the combustion chamber are obtained by combining the first flow field distribution characteristics and the second flow field distribution characteristics.

[0045] Compared with the prior art, the present invention discloses an on-wing adjustment method and device for an aircraft engine. The method obtains the flow field distribution characteristics in the combustion chamber of the aircraft engine by performing flow field simulation on the combustion chamber; the flow field includes at least a temperature field; a floating tile component with ablation damage of the aircraft engine to be adjusted is obtained, and a deposit distribution characteristic is obtained by analyzing the microscopic changes of the floating tile component; according to the flow field distribution characteristics and the deposit distribution characteristics, a load is applied to a floating tile sample component to make it consistent with the floating tile component, thereby reproducing the damage process of the combustion chamber of the aircraft engine to be adjusted; the floating tile sample component is consistent with the floating tile component of the aircraft engine to be adjusted before use; according to the flow field distribution characteristics, a life analysis is performed on the floating tile component; according to the results of the damage process and the life analysis, the position and replacement timing of the fuel nozzle that damages the combustion chamber liner are respectively obtained, and an on-wing adjustment plan is generated; according to the on-wing adjustment plan, the aircraft engine to be adjusted is adjusted. By adopting the embodiment of the present invention, the fuel nozzle that damages the combustion chamber liner can be accurately located and the replacement time can be determined, thereby realizing on-wing adjustment of the aircraft engine, extending the service life of the aircraft engine, and reducing the frequency and cost of disassembly maintenance. BRIEF DESCRIPTION OF THE DRAWINGS

[0046] Figure 1 This is a schematic flow chart of the steps of an on-wing adjustment method for an aircraft engine provided by an embodiment of the present invention;

[0047] Figure 2 is a schematic diagram of the life analysis results provided by an embodiment of the present invention;

[0048] Figure 3 is a schematic diagram of an on-wing adjustment solution provided by an embodiment of the present invention;

[0049] Figure 4 The diagram is a structural diagram of an on-wing adjustment device for an aero-engine provided by an embodiment of the present invention. DETAILED DESCRIPTION

[0050] The following will clearly and completely describe the technical solutions in the embodiments of the present invention in conjunction with the accompanying drawings. Obviously, the described embodiments are only part of the embodiments of the present invention, not all of the embodiments. All other embodiments obtained by ordinary technicians in this field based on the embodiments of the present invention without making any creative efforts shall fall within the scope of protection of the present invention.

[0051] In the description of the specification and claims, it should be understood that the terms "first," "second," etc., are used solely for descriptive purposes to distinguish between identical technical features and are not to be construed as indicating or implying relative importance or implicitly specifying the number of technical features being referred to, nor do they necessarily describe a sequential or chronological order. The terms are interchangeable where appropriate. Thus, a feature specified as "first" or "second" may explicitly or implicitly include at least one of those features.

[0052] See also Figure 1 , is a schematic flow chart of the steps of an on-wing adjustment method for an aircraft engine provided by an embodiment of the present invention. In this embodiment, the on-wing adjustment method for an aircraft engine is specifically performed through steps S1 to S6:

[0053] S1. Perform flow field simulation on a combustion chamber of an aircraft engine to obtain flow field distribution characteristics in the combustion chamber; the flow field includes at least a temperature field.

[0054] It should be noted that, in the embodiment of the present invention, the flow field distribution characteristics are mainly for analyzing the temperature field distribution. This is because during the use of the combustion chamber, temperature is an important factor affecting the damage of the combustion chamber liner; in actual applications, the flow field distribution characteristics may also include other flow field factors, such as pressure, etc., but the flow field at least includes the temperature field, and the analysis of other flow field factors does not affect the beneficial effects achieved by this application.

[0055] S2. Obtaining a floating tile component with ablation damage of the aircraft engine to be adjusted, and obtaining a sediment distribution characteristic by analyzing microscopic changes of the floating tile component.

[0056] S3. Apply a load to the floating tile sample component based on the flow field distribution characteristics and the deposit distribution characteristics to make it consistent with the floating tile component, thereby reproducing the damage process of the combustion chamber of the aircraft engine to be adjusted; the floating tile sample component is consistent with the floating tile component of the aircraft engine to be adjusted before use.

[0057] It can be understood that when the aircraft engine to be adjusted has not been used, the floating tile sample component is an unused floating tile sample component; and when the aircraft engine to be adjusted has a certain usage cycle, the floating tile sample component is consistent with the floating tile component of the aircraft engine to be adjusted before use, and is not necessarily a completely unused floating tile sample component.

[0058] It should be noted that the amount and characteristics of the load applied to the floating tile sample component are derived based on the flow field distribution characteristics and the deposit distribution characteristics. They are not randomly generated but rather directional. The load is used to describe the potential damage process of the aircraft engine's combustion chamber. When the floating tile sample component matches the ablation-damaged floating tile component of the aircraft engine to be adjusted, the applied load can replicate the damage process of the aircraft engine's combustion chamber. In an embodiment of the present invention, this process is performed on a combustion test bench.

[0059] S4. Performing life analysis on the floating tile component according to the flow field distribution characteristics.

[0060] S5. According to the damage process and the results of the life analysis, the location and replacement timing of the fuel nozzle of the damaged combustion chamber liner are obtained, and an on-wing adjustment plan is generated.

[0061] S6. Adjust the aircraft engine to be adjusted according to the on-wing adjustment plan.

[0062] In the above scheme, the floating tile components of the combustion chamber of the aircraft engine to be adjusted are analyzed by calculating the universal flow field distribution characteristics and sediment distribution characteristics in the combustion chamber, which can reproduce its damage process, further accurately locate the position of the fuel nozzle that damages the combustion chamber liner, and obtain the best time to replace the fuel nozzle; realize the on-wing adjustment of the aircraft engine to be adjusted, maximize the extension of the service life of the aircraft engine, and reduce the frequency and cost of disassembly and maintenance.

[0063] It should be noted that the aircraft engine described in the above-mentioned step S1 is a typical aircraft engine. The typical aircraft engine and the aircraft engine to be adjusted belong to the same series or have similar working principles. Therefore, the typical aircraft engine and the aircraft engine to be adjusted have the same flow field distribution characteristics. The floating tile sample component described in the above-mentioned step S2 is obtained during the actual overhaul of the aircraft engine. It is understandable that a large number of floating tile sample components can be obtained during the disassembly and overhaul of the aircraft engine. By conducting experimental analysis on the existing floating tile sample components, the deposit distribution characteristics can be obtained. In actual applications, the typical aircraft engine can also be modeled, and the flow field distribution characteristics and the deposit distribution characteristics can be analyzed in the combustion chamber model obtained by modeling. In subsequent calculations, relevant data can be directly extracted from the combustion chamber model. Whether or not the typical aircraft engine is modeled does not affect the beneficial effects obtained by the present invention.

[0064] The V2500 series engines are widely used in the aviation field. In the embodiment of the present invention, the aircraft engine and the aircraft engine to be adjusted are both V2500 series engines.

[0065] Preferably, the performing of flow field simulation on the combustion chamber of the aircraft engine to obtain flow field distribution characteristics in the combustion chamber includes:

[0066] Calculate the temperature field distribution of the typical engine operating conditions and obtain the first flow field distribution characteristics;

[0067] Calculate the temperature field distribution when using different fuel nozzles and obtain the second flow field distribution characteristics;

[0068] The flow field distribution characteristics in the combustion chamber are obtained by combining the first flow field distribution characteristics and the second flow field distribution characteristics.

[0069] In the above scheme, the effects of different engine operating conditions and different fuel nozzles on the temperature field distribution are comprehensively analyzed to obtain the flow field distribution characteristics in the combustion chamber, making the flow field distribution characteristics more comprehensive and accurate.

[0070] Furthermore, as a preferred embodiment, the calculating the temperature field distribution under the typical operating conditions of the engine to obtain the first flow field distribution characteristics includes:

[0071] Obtain the gas pressure and temperature parameters at the inlet and outlet of the combustion chamber obtained from the test bench test;

[0072] The gas pressure and temperature parameters are used as boundary conditions to calculate the first temperature field distribution under typical operating conditions to obtain the first flow field distribution characteristics; the typical operating conditions include engine starting, engine acceleration and engine cruising.

[0073] It is understandable that before an aircraft engine leaves the factory, it will undergo a test bench test. The parameters obtained from the test include the gas pressure and temperature parameters at the inlet and outlet of the combustion chamber. The parameters can characterize the performance standards of this series of aircraft engines. Using them as boundary conditions, the temperature field distribution under typical working conditions can be scientifically calculated.

[0074] Preferably, the calculating of the temperature field distribution when using different fuel nozzles to obtain the second flow field distribution characteristics includes:

[0075] calculating a second temperature field distribution in the combustion chamber using a plurality of fuel nozzles having different fault types, spray characteristics, and spray directions;

[0076] performing fuel injection tests using a plurality of fuel nozzles with different service cycles, and calculating a third temperature field distribution in the combustion chamber based on differences in injection cone angles, spray particle sizes, and injection velocities of the plurality of fuel nozzles;

[0077] A second flow field distribution characteristic is obtained according to the second temperature field distribution and the third temperature field distribution.

[0078] As an example, in an embodiment of the present invention, a high-speed camera is used to record and analyze the injection process of a fuel nozzle, digitally characterize the injection cone angle, spray particle size, and injection speed, and analyze the differences between fuel nozzles with different usage cycles.

[0079] Further, preferably, the fault types include fuel injector blockage and nozzle deformation faults.

[0080] In the above scheme, by using several fuel nozzles with different fault types, spray characteristics, and at least one of spray directions, the second temperature field distribution of the combustion chamber is calculated when one or more conditions change to obtain a comprehensive second flow field distribution characteristic.

[0081] As a preferred embodiment, obtaining the ablation-damaged floating tile component of the aircraft engine to be adjusted and analyzing the microscopic changes of the floating tile component to obtain the deposit distribution characteristics includes:

[0082] Obtaining a floating tile component with ablation damage of an aircraft engine to be adjusted;

[0083] The floating tile component is subjected to SEM testing, nanoindentation testing, and XRD testing to obtain changes in the thermal barrier coating on the surface of the combustion chamber and changes in the substrate microstructure of the combustion chamber before and after use;

[0084] According to the changes in the thermal barrier coating and the microstructure of the substrate, the deposit distribution characteristics are obtained.

[0085] Preferably, performing life analysis on the floating tile component according to the flow field distribution characteristics includes:

[0086] According to the flow field distribution characteristics, the distribution characteristics of the temperature field on the combustion chamber wall are obtained;

[0087] The lifespan analysis of the floating tile component is performed using the distribution characteristics of the temperature field as a variable.

[0088] See Figure 2 , Figure 2 Schematic diagram of the life analysis results provided by the embodiment of the present invention. Figure 3 It can be seen from the figure that by analyzing the damage rate of the combustion chamber liner, the result of life analysis can be obtained. In the embodiment of the present invention, according to Figure 3 It can be determined that the time between D3 and D4 is the optimal time to replace the fuel nozzle.

[0089] It should be noted that, based on the flow field distribution characteristics obtained by simulation, it is possible to determine what changes will occur in the distribution characteristics of the temperature field on the combustion chamber wall. When performing life analysis on the floating tile component, the distribution characteristics of the temperature field are used as the only variable without replacing the fuel nozzle, thereby analyzing the life of the floating tile component under the current usage conditions.

[0090] See Figure 3 , Figure 3 This is a schematic diagram of an on-wing adjustment solution provided by an embodiment of the present invention. As an example, the combustion chamber liner is damaged in row 3 of the outer barrel, and the fuel nozzles with damaged combustion chamber liner are located at row 6, row 7, and row 8, respectively.

[0091] As a preferred embodiment, after adjusting the aircraft engine according to the on-wing adjustment scheme, the method further includes:

[0092] monitoring the adjusted aircraft engine to track damage to its combustion chamber;

[0093] According to the damage condition, the time for the on-wing adjustment scheme to delay the damage to the combustion chamber is calculated.

[0094] It should be noted that after the aircraft engine is adjusted according to the on-wing adjustment plan, the damage to the combustion chamber is continuously tracked, and the time for the on-wing adjustment plan to delay the damage to the combustion chamber is calculated. By comparing and analyzing the calculated time with the actual delay time, test data can be provided for the on-wing adjustment plan, and the parameters in the process of generating the on-wing adjustment plan, such as flow field distribution characteristics, can be fine-tuned based on the test data to achieve optimization of the on-wing adjustment plan.

[0095] An on-wing adjustment method for an aircraft engine provided by an embodiment of the present invention is used. By calculating the universal flow field distribution characteristics and deposit distribution characteristics in the combustion chamber, the floating tile components of the combustion chamber of the aircraft engine to be adjusted are analyzed, and its damage process can be reproduced. The position of the fuel nozzle that damages the combustion chamber liner can be further accurately located, and the optimal time to replace the fuel nozzle can be obtained. This method can realize on-wing adjustment of the aircraft engine to be adjusted, maximize the extension of the service life of the aircraft engine, and reduce the frequency of disassembly and maintenance and the maintenance cost.

[0096] See Figure 4 , Figure 4 The diagram is a schematic structural diagram of an on-wing adjustment device for an aircraft engine provided by an embodiment of the present invention. The on-wing adjustment device for an aircraft engine includes a flow field distribution characteristic generation module 11, a deposit distribution characteristic generation module 12, a damage process reproduction module 13, a life analysis module 14, an on-wing adjustment solution generation module 15, and an aircraft engine adjustment module 16, wherein:

[0097] The flow field distribution characteristics generating module 11 is used to perform flow field simulation on the combustion chamber of the aircraft engine to obtain the flow field distribution characteristics in the combustion chamber; the flow field at least includes a temperature field;

[0098] The deposit distribution characteristic generating module 12 is used to obtain the ablation-damaged floating tile component of the aircraft engine to be adjusted, and obtain the deposit distribution characteristic by analyzing the microscopic changes of the floating tile component;

[0099] The damage process reproduction module 13 is configured to apply a load to a floating tile sample component based on the flow field distribution characteristics and the deposit distribution characteristics, so as to make the floating tile component consistent with the floating tile component, thereby reproducing the damage process of the combustion chamber of the aircraft engine to be adjusted; the floating tile sample component is consistent with the floating tile component of the aircraft engine to be adjusted before use;

[0100] A life analysis module 14 is used to perform life analysis on the floating tile component according to the flow field distribution characteristics;

[0101] An on-wing adjustment plan generating module 15 is configured to obtain the location and replacement timing of the fuel nozzle of the damaged combustion chamber liner according to the damage process and the results of the life analysis, and generate an on-wing adjustment plan;

[0102] The aircraft engine adjustment module 16 is configured to adjust the aircraft engine to be adjusted according to the on-wing adjustment plan.

[0103] As a preferred embodiment, the flow field simulation of the combustion chamber of the aircraft engine to obtain the flow field distribution characteristics in the combustion chamber includes:

[0104] Calculate the temperature field distribution under typical engine operating conditions and obtain the first flow field distribution characteristics;

[0105] Calculate the temperature field distribution when using different fuel nozzles and obtain the second flow field distribution characteristics;

[0106] The flow field distribution characteristics in the combustion chamber are obtained by combining the first flow field distribution characteristics and the second flow field distribution characteristics.

[0107] Furthermore, as a preferred embodiment, the calculating the temperature field distribution under the typical operating conditions of the engine to obtain the first flow field distribution characteristics includes:

[0108] Obtain the gas pressure and temperature parameters at the inlet and outlet of the combustion chamber obtained from the test bench test;

[0109] The gas pressure and temperature parameters are used as boundary conditions to calculate the first temperature field distribution under typical operating conditions to obtain the first flow field distribution characteristics; the typical operating conditions include engine starting, engine acceleration and engine cruising.

[0110] It is understandable that before an aircraft engine leaves the factory, it will undergo a test bench test. The parameters obtained from the test include the gas pressure and temperature parameters at the inlet and outlet of the combustion chamber. The parameters can characterize the performance standards of this series of aircraft engines. Using them as boundary conditions, the temperature field distribution under typical working conditions can be scientifically calculated.

[0111] Preferably, the calculating of the temperature field distribution when using different fuel nozzles to obtain the second flow field distribution characteristics includes:

[0112] calculating a second temperature field distribution in the combustion chamber using a plurality of fuel nozzles having different fault types, spray characteristics, and spray directions;

[0113] performing fuel injection tests using a plurality of fuel nozzles with different service cycles, and calculating a third temperature field distribution in the combustion chamber based on differences in injection cone angles, spray particle sizes, and injection velocities of the plurality of fuel nozzles;

[0114] A second flow field distribution characteristic is obtained according to the second temperature field distribution and the third temperature field distribution.

[0115] Further, preferably, the fault types include fuel injector blockage and nozzle deformation faults.

[0116] As a preferred embodiment, obtaining the ablation-damaged floating tile component of the aircraft engine to be adjusted and analyzing the microscopic changes of the floating tile component to obtain the deposit distribution characteristics includes:

[0117] Obtaining a floating tile component with ablation damage of an aircraft engine to be adjusted;

[0118] The floating tile component is subjected to SEM testing, nanoindentation testing, and XRD testing to obtain changes in the thermal barrier coating on the surface of the combustion chamber and changes in the substrate microstructure of the combustion chamber before and after use;

[0119] According to the changes in the thermal barrier coating and the microstructure of the substrate, the deposit distribution characteristics are obtained.

[0120] Preferably, performing life analysis on the floating tile component according to the flow field distribution characteristics includes:

[0121] According to the flow field distribution characteristics, the distribution characteristics of the temperature field on the combustion chamber wall are obtained;

[0122] The lifespan analysis of the floating tile component is performed using the distribution characteristics of the temperature field as a variable.

[0123] As a preferred embodiment, the device further includes:

[0124] a damage tracking module, configured to monitor the adjusted aircraft engine and track damage to its combustion chamber;

[0125] The delay time calculation module is used to calculate the time for the on-wing adjustment scheme to delay the damage to the combustion chamber according to the damage condition.

[0126] An on-wing adjustment method for an aircraft engine provided by an embodiment of the present invention is used. By calculating the universal flow field distribution characteristics and deposit distribution characteristics in the combustion chamber, the floating tile components of the combustion chamber of the aircraft engine to be adjusted are analyzed, and its damage process can be reproduced. The position of the fuel nozzle that damages the combustion chamber liner can be further accurately located, and the optimal time to replace the fuel nozzle can be obtained. This method can realize on-wing adjustment of the aircraft engine to be adjusted, maximize the extension of the service life of the aircraft engine, and reduce the frequency of disassembly and maintenance and the maintenance cost.

[0127] An embodiment of the present invention also provides an on-wing adjustment device for an aircraft engine, comprising a processor, a memory, and a computer program stored in the memory and configured to be executed by the processor. When the processor executes the computer program, an on-wing adjustment method for an aircraft engine as described above is implemented. The working principles and beneficial effects of the two correspond one to one, and therefore will not be repeated here.

[0128] Those skilled in the art will appreciate that all or part of the processes in the above-described method embodiments can be implemented by instructing related hardware through a computer program. The program can be stored in a computer-readable storage medium, and when executed, the program can include the processes in the above-described method embodiments. The storage medium can be a magnetic disk, an optical disk, a read-only memory (ROM), or a random access memory (RAM).

[0129] The above is a preferred embodiment of the present invention. It should be pointed out that for ordinary technicians in this technical field, several improvements and modifications can be made without departing from the principles of the present invention. These improvements and modifications are also considered to be within the scope of protection of the present invention.

Claims

1. A method for adjusting an aircraft engine on wing, characterized in that: include: Conduct flow field simulation on the combustion chamber of an aircraft engine to obtain the flow field distribution characteristics inside the combustion chamber; The flow field at least includes a temperature field; Obtaining a floating tile component with ablation damage of an aircraft engine to be adjusted, and obtaining a deposit distribution characteristic by analyzing microscopic changes in the floating tile component; applying a load to a floating tile sample component based on the flow field distribution characteristics and the deposit distribution characteristics so as to make the load consistent with the floating tile component, thereby reproducing the damage process of the combustion chamber of the aircraft engine to be adjusted; the floating tile sample component is consistent with the floating tile component of the aircraft engine to be adjusted before use; performing a life analysis on the floating tile component according to the flow field distribution characteristics; According to the damage process and the results of the life analysis, the location and replacement timing of the fuel nozzle of the damaged combustion chamber liner are obtained, and an on-wing adjustment plan is generated; The aircraft engine to be adjusted is adjusted according to the on-wing adjustment plan.

2. The on-wing adjustment method of an aircraft engine according to claim 1, characterized in that: The flow field simulation of the combustion chamber of the aircraft engine is performed to obtain the flow field distribution characteristics in the combustion chamber, including: Calculate the temperature field distribution under typical engine operating conditions and obtain the first flow field distribution characteristics; Calculate the temperature field distribution when using different fuel nozzles and obtain the second flow field distribution characteristics; The flow field distribution characteristics in the combustion chamber are obtained by combining the first flow field distribution characteristics and the second flow field distribution characteristics.

3. The on-wing adjustment method of an aircraft engine according to claim 1, characterized in that: The method of obtaining a floating tile component with ablation damage of the aircraft engine to be adjusted and obtaining a sediment distribution characteristic by analyzing microscopic changes of the floating tile component includes: Obtaining a floating tile component with ablation damage of an aircraft engine to be adjusted; The floating tile component is subjected to SEM testing, nanoindentation testing, and XRD testing to obtain changes in the thermal barrier coating on the surface of the combustion chamber and changes in the substrate microstructure of the combustion chamber before and after use; According to the changes in the thermal barrier coating and the microstructure of the substrate, the deposit distribution characteristics are obtained.

4. The on-wing adjustment method of an aircraft engine according to claim 1, characterized in that: The performing life analysis on the floating tile component according to the flow field distribution characteristics includes: According to the flow field distribution characteristics, the distribution characteristics of the temperature field on the combustion chamber wall are obtained; The lifespan analysis of the floating tile component is performed using the distribution characteristics of the temperature field as a variable.

5. The on-wing adjustment method of an aircraft engine according to claim 2, characterized in that: The calculating of the temperature field distribution under the typical operating condition of the engine to obtain the first flow field distribution characteristic includes: Obtain the gas pressure and temperature parameters at the inlet and outlet of the combustion chamber obtained from the test bench test; The gas pressure and temperature parameters are used as boundary conditions to calculate the first temperature field distribution under typical operating conditions to obtain the first flow field distribution characteristics; the typical operating conditions include engine starting, engine acceleration and engine cruising.

6. The on-wing adjustment method of an aircraft engine according to claim 2, characterized in that: The calculation of the temperature field distribution when using different fuel nozzles to obtain the second flow field distribution characteristics includes: calculating a second temperature field distribution in the combustion chamber using a plurality of fuel nozzles having different fault types, spray characteristics, and spray directions; performing fuel injection tests using a plurality of fuel nozzles with different service cycles, and calculating a third temperature field distribution in the combustion chamber based on differences in injection cone angles, spray particle sizes, and injection velocities of the plurality of fuel nozzles; A second flow field distribution characteristic is obtained according to the second temperature field distribution and the third temperature field distribution.

7. The on-wing adjustment method of an aircraft engine according to claim 6, characterized in that: The fault types include fuel injector blockage and nozzle deformation faults.

8. The on-wing adjustment method of an aircraft engine according to claim 1, characterized in that: After adjusting the aircraft engine according to the on-wing adjustment plan, the method further includes: monitoring the adjusted aircraft engine to track damage to its combustion chamber; According to the damage condition, the time for the on-wing adjustment scheme to delay the damage to the combustion chamber is calculated.

9. An on-wing adjustment device for an aircraft engine, characterized in that: include: The flow field distribution characteristics generation module is used to simulate the flow field of the combustion chamber of an aircraft engine and obtain the flow field distribution characteristics in the combustion chamber; The flow field at least includes a temperature field; A deposit distribution characteristic generating module is used to obtain a floating tile component with ablation damage of the aircraft engine to be adjusted, and obtain a deposit distribution characteristic by analyzing the microscopic changes of the floating tile component; a damage process reproduction module, configured to apply a load to a floating tile sample component based on the flow field distribution characteristics and the deposit distribution characteristics, so as to make the load consistent with the floating tile component, thereby reproducing the damage process of the combustion chamber of the aircraft engine to be adjusted; the floating tile sample component is consistent with the floating tile component of the aircraft engine to be adjusted before use; A life analysis module, configured to perform life analysis on the floating tile component according to the flow field distribution characteristics; An on-wing adjustment plan generating module is configured to obtain the location and replacement timing of the fuel nozzle of the damaged combustion chamber liner according to the damage process and the results of the life analysis, and generate an on-wing adjustment plan; The aircraft engine adjustment module is used to adjust the aircraft engine to be adjusted according to the on-wing adjustment plan.

10. The on-wing adjustment device of an aircraft engine according to claim 9, characterized in that: The flow field simulation of the combustion chamber of the aircraft engine is performed to obtain the flow field distribution characteristics in the combustion chamber, including: Calculate the temperature field distribution under typical engine operating conditions and obtain the first flow field distribution characteristics; Calculate the temperature field distribution when using different fuel nozzles and obtain the second flow field distribution characteristics; The flow field distribution characteristics in the combustion chamber are obtained by combining the first flow field distribution characteristics and the second flow field distribution characteristics.

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