A step-by-step verification method for a flock of birds swallowed by an aviation turbofan engine

Abstract

The present application belongs to the field of whole-machine bird swallowing test scheme design, and is a step-by-step verification method for an aviation turbofan engine swallowing a flock of birds. The bird swallowing test parameters are first determined, and based on these parameters, a component test scheme is quickly designed. Then, a component bird strike test is first conducted to find out the structural mismatch and optimize the component until the structural mismatch is eliminated; and the component structure optimization of the component bird strike test is retained in the whole engine through replacement, and the mismatch position in the aerodynamic design caused by the bird strike structural damage is verified by conducting a whole-machine test run, and the mismatch in the aerodynamic design is eliminated through optimized design. In this way, in the whole-machine bird swallowing test, the bird swallowing test parameters of the engine bird swallowing capability design and the whole-machine bird swallowing test verification requirements are fully matched, the test success rate is high, and the test cycle is short; it solves the problem of engine bird swallowing capability verification that the component test verification was incomplete and the whole-machine test risk was high in the past.

Description

Technical Field

[0001] The present application belongs to the field of whole-machine bird swallowing test scheme design, and particularly relates to a step-by-step verification method for an aviation turbofan engine swallowing a flock of birds. Background Art

[0002] The world's major aviation powers have systematic and complete regulations and mature verification experience in engine bird-swallowing capability verification, have formed their own bird-swallowing capability verification systems, and have the ability to carry out bird-swallowing verification in accordance with airworthiness regulations or military specifications.

[0003] The bird swallowing test for an aircraft engine is a comprehensive verification of the engine's structure and aerodynamics. Directly conducting bird swallowing capability verification for the entire aircraft carries a high risk factor, resulting in low test success rates, wasted resources, and wasted cycle costs. Component testing, on the other hand, cannot achieve the purpose of aerodynamic verification. Given the shortcomings of the two aforementioned verification methods and the increasingly stringent bird swallowing capability requirements in airworthiness regulations and military standards, there is an urgent need to develop a bird swallowing capability verification method that matches the current state of turbofan engine development and technological advancements and meets the requirements of these regulations and military standards. Summary of the Invention

[0004] The purpose of this application is to provide a step-by-step verification method for an aviation turbofan engine swallowing a flock of birds, so as to solve the problem in the prior art that the bird swallowing test does not match the engine development capability, resulting in a low success rate and a high risk.

[0005] The technical solution of the present application is: a step-by-step verification method for an aviation turbofan engine swallowing a flock of birds, comprising: selecting a test basis standard, selecting an engine to be used, and determining the bird swallowing test parameters according to the control test basis standard; conducting a component bird strike test according to the bird swallowing test parameters to verify whether the structural damage results of the component under the bird strike condition meet the requirements, if so, obtaining the component bird strike test data and executing the next step; if not, determining a specific improvement plan for the specific damaged structure, and re-performing the component bird strike test until the requirements are met; replacing the component structure of the component bird strike test to the engine as a whole; conducting a whole-machine test verification design in combination with the component bird strike test data, and conducting a whole-machine test after the design is completed to verify whether the whole-machine aerodynamic change results caused by the structural damage of the component bird strike test piece meet the requirements, if so, obtaining the whole-machine test data and executing the next step; if not, analyzing the specific aerodynamic damage design, determining a specific improvement plan, and re-performing the component bird strike test until the requirements are met; carrying out the whole-machine test design, and conducting the whole-machine bird swallowing test in combination with the whole-machine test data.

[0006] Preferably, the specific steps of the component bird strike test include: determining the technical status of the test component and determining the component status that meets the bird swallowing capability verification requirements; then debugging the test equipment, and after meeting the bird swallowing test parameter requirements, recording the fan blade status before the test, and then conducting the component bird strike test, recording the fan blade status after the test, and comparing the difference in fan blade status before and after the test to obtain structural damage results.

[0007] Preferably, the bird swallowing test parameters include the number and weight of swallowed birds, bird speed, launch position, test status, test procedure, and pass standard.

[0008] Preferably, the specific design of replacing the component structure to the engine as a whole includes: determining the required components to be replaced on the engine as a whole for the component bird strike test, determining the corresponding position of each required component on the engine as a whole to be replaced, measuring the residual unbalance of the fan blades, and analyzing the impact on the vibration of the low-pressure rotor to determine whether the rotor passes the critical speed during the start-up of the engine as a whole; if so, all required components are replaced on the corresponding positions of the engine as a whole to complete the replacement; if not, the required components are replaced on the corresponding positions of the engine as a whole and adjusted to complete the replacement after the residual unbalance of the fan blades is satisfied; the required components include all fan blades used in the component bird strike test.

[0009] Preferably, the method for verifying the design by whole machine test run includes:

[0010] Determine the test procedure and keep the test status points of the test procedure the same as the formal test;

[0011] Perform target capability verification to check whether the thrust loss in the test assessment state meets the requirements. If so, proceed to the next step.

[0012] Determine whether the technical status of the test engine meets the requirements. If so, proceed to the next step;

[0013] Keep the test equipment requirements the same as the formal test requirements;

[0014] Determine test parameter measurements and constraints;

[0015] Carry out pre-test preparations and record the status of the entire machine before testing;

[0016] Determine whether the test data recording content and the post-test whole machine inspection content meet the requirements. If so, conduct a whole machine test run.

[0017] Preferably, the structural damage verification of the component bird strike test is obtained by adopting a damage structure inspection and a data result analysis of the component bird strike test; when it is determined that the structural damage verified by the component bird strike test does not meet the requirements or the aerodynamic damage of the whole machine test does not meet the requirements due to structural damage, a specific improved design scheme is determined by comparative analysis with domestic and foreign equivalent engine structures, strength simulation calculations, and aerodynamic simulation calculations; after the improved design scheme is determined, a simulation analysis or test verification is carried out to verify whether it is effective. If effective, the improvement is qualified; if not, the improved design scheme is redesigned until the requirements are met.

[0018] Preferably, the aerodynamic damage verification of the whole machine test is obtained by analyzing the performance and parameter changes of the engine performance parameters, control system parameters, vibration parameters, pulsation parameters, and camera data during the whole machine test. When it is determined that the aerodynamic damage results caused by the aerodynamic design do not meet the requirements, a comparative analysis with the aerodynamic designs of equivalent engines at home and abroad and an aerodynamic simulation analysis are used to determine a specific improved design scheme; after determining the improved design scheme, a simulation analysis or test verification is carried out to verify whether it is effective. If effective, the improvement is qualified; if not, the improved design scheme is redesigned until it meets the requirements.

[0019] The present application discloses a step-by-step verification method for an aviation turbofan engine swallowing a flock of birds. The method first determines the bird swallowing test parameters, and uses these parameters as a basis for rapid design of component test schemes. Then, by first conducting a component bird strike test, the structural mismatch is found and the component is optimized until the structural mismatch is eliminated. The component structure optimization of the component bird strike test is retained in the engine as a whole through replacement, and the mismatch position in the aerodynamic design caused by the bird strike structural damage is verified through the whole-machine test run, and the aerodynamic mismatch is eliminated through optimized design. In this way, in the whole-machine bird swallowing test, the engine bird swallowing capability (structural damage and aerodynamic stability) design is fully matched with the whole-machine bird swallowing verification requirements, and the test success rate is high and the test cycle is short. At the same time, through the distributed verification method of component bird strike test-whole-machine test run-whole-machine bird swallowing test, the problem of engine bird swallowing capability verification, which was previously incomplete in component test verification and high in whole-machine test risk, is solved, and has strong engineering application value. BRIEF DESCRIPTION OF THE DRAWINGS

[0020] In order to more clearly illustrate the technical solutions provided by this application, the following is a brief introduction to the accompanying drawings. Obviously, the accompanying drawings described below are only some embodiments of this application.

[0021] Figure 1 This is a schematic diagram of the overall process of this application. DETAILED DESCRIPTION

[0022] In order to make the purpose, technical solutions and advantages of the implementation of this application clearer, the technical solutions in the embodiments of this application will be described in more detail below in conjunction with the drawings in the embodiments of this application.

[0023] A step-by-step verification method for an aviation turbofan engine swallowing a flock of birds, such as Figure 1 As shown, the following steps are included:

[0024] Step S100, select the test basis standard, select the engine to be used, combine the actual characteristics of the engine, and determine the bird swallowing test parameters according to the control test basis standard; the bird swallowing test parameters include the number and weight of swallowed birds, the speed of the birds, the launch position, the test status, the test procedure, and the passing standard.

[0025] By first determining the swallowing bird test parameters and then conducting specific test design in accordance with the requirements of meeting the corresponding test parameters, a test plan that meets the requirements can be quickly designed.

[0026] Step S200: Perform a component bird strike test based on the bird ingestion test parameters to verify whether the structural damage results under the component bird strike conditions meet the requirements. If so, obtain the component bird strike test data and proceed to the next step. If not, determine a specific improvement plan for the specific damaged structure and re-perform the component bird strike test until the requirements are met.

[0027] The specific steps of the component bird strike test include: determining the technical status of the test components, such as fan blades, etc., to ensure that each component meets the bird swallowing capability verification requirements, which are determined in step S100.

[0028] After determining the component status that meets the bird swallowing capacity requirement, the test equipment is debugged to ensure that the bird weight, bird speed, projection position, test speed, etc. meet the test parameter requirements determined in step S100.

[0029] After meeting the bird swallowing test parameter requirements, the fan blade status before the test is recorded, including the fan blade status and size, etc., and a component bird strike test is carried out. The fan blade status after the test is recorded, including damage inspection, size measurement and photo recording data of the fan blades. The difference in fan blade status before and after the test is compared to obtain the structural damage results.

[0030] By comparing before and after, accurate structural damage results can be obtained. If the current engine capability does not match the bird-swallowing test parameter requirements, the structural damage will not meet the requirements. In this case, since the first bird strike test is conducted on a component, rather than the entire engine, even if a mismatch occurs, it will not be dangerous. The next step is to find the specific location of the structural mismatch based on the specific damaged structure, so that improvements can be directly made and applied to the entire engine to eliminate the mismatch. By correcting various mismatches one by one and applying them to the entire engine, the structural mismatch between the engine capability and the bird-swallowing test parameter requirements can be eliminated.

[0031] Structural damage verification from component bird strike tests is achieved through structural damage inspection and analysis of component bird strike test data. If the structural damage verified by the component bird strike test does not meet the requirements, comparative analysis with equivalent domestic and international engine structures, strength simulation calculations, and aerodynamic simulation calculations are used to determine specific design improvements, such as fan blade profile optimization, connection structure optimization, and wear-resistant layer material optimization.

[0032] After determining the improved design plan, conduct simulation analysis or test verification to verify whether it is effective. If it is effective, the improvement is qualified; if not, redesign the improved design plan until it meets the requirements.

[0033] Step S300, replacing the component structure of the component bird strike test with the complete engine;

[0034] The specific design of component structure replacement to the complete engine includes: determining the components required for replacement to the complete engine for the component bird strike test, for example, whether to replace all fan components used in the component test or only the fan blades;

[0035] Determine the position of each required component and its corresponding position with the complete engine to ensure that the relative positions of all fan blades after installation on the complete engine are consistent with those during component testing;

[0036] The residual unbalance of the fan blades is measured and its impact on low-pressure rotor vibration is analyzed to determine whether the rotor has passed the critical speed during engine startup. If so, all required components are reinstalled in their corresponding positions on the engine, completing the reinstallation. If not, the required components are reinstalled in their corresponding positions on the engine, adjusted, and the reinstallation is completed after the residual unbalance of the fan blades is met. This prevents the rotor from vibrating excessively due to exceeding the critical speed and preventing testing.

[0037] The required components include at least all fan blades used in the component bird strike test.

[0038] Step S400: Perform a full-machine test run to verify the design based on the component bird strike test data. After the design is completed, perform a full-machine test to verify whether the aerodynamic damage results of the bird strike structure under the full-machine test meet the requirements. If they do meet the requirements, obtain the full-machine test data and proceed to the next step. If they do not meet the requirements, analyze the specific aerodynamic damage design, determine a specific improvement plan, and re-perform the component bird strike test until the requirements are met.

[0039] The methods for verifying the design through whole machine commissioning include:

[0040] Determine the test procedure and keep the test status points of the test procedure the same as the formal test;

[0041] Perform target capability verification to check whether the thrust loss in the test assessment state meets the requirements. If so, proceed to the next step.

[0042] Determine whether the technical status of the test engine meets the requirements. If so, proceed to the next step;

[0043] Keep the test equipment requirements the same as the formal test requirements;

[0044] Determine test parameter measurements and constraints;

[0045] Carry out pre-test preparations and record the status of the entire machine before testing;

[0046] Determine whether the test data recording content and the post-test whole machine inspection content meet the requirements. If so, conduct a whole machine test run.

[0047] The aerodynamic damage verification of the whole machine test is obtained by analyzing the performance and parameter changes of engine performance parameters, control system parameters, vibration parameters, pulsation parameters, camera data, etc. during the whole machine test. When it is determined that the aerodynamic damage results caused by the aerodynamic design do not meet the requirements, comparative analysis with the aerodynamic designs of equivalent engines at home and abroad, aerodynamic simulation analysis, etc. are used to determine the specific improvement design plan; such as control law optimization, flow path component optimization, etc.

[0048] After determining the improved design plan, conduct simulation analysis or test verification to verify whether it is effective. If it is effective, the improvement is qualified; if not, redesign the improved design plan until it meets the requirements.

[0049] By replacing the component structure with the entire engine, any structural mismatches are eliminated. A full engine test can then identify the specific location of the aerodynamic design mismatch, again without causing any danger. Once the specific location of the aerodynamic mismatch is identified, aerodynamic optimization and design improvements can be performed to eliminate the mismatch, eliminating all design mismatches. If the aerodynamic damage failure during the full engine test is due to structural damage, the structural improvement design solution in step S200 is used for optimization.

[0050] Step S500: Carry out the whole machine test design, and conduct the whole machine bird swallowing test based on the whole machine test data.

[0051] This application first determines the bird swallowing test parameters, and uses these parameters as a basis for rapid design of component test plans. Then, by first conducting a component bird strike test, the structural mismatch is found and the component is optimized until the structural mismatch is eliminated. The component structure optimization of the component bird strike test is retained in the engine as a whole through replacement, and the mismatch position in the aerodynamic design caused by the bird strike structural damage is verified by conducting a whole-machine test run, and the mismatch in the aerodynamic design is eliminated by optimizing the design. In this way, in the whole-machine bird swallowing test, the bird swallowing test parameters designed for the engine's bird swallowing capability (structural damage and aerodynamic stability) are fully matched with the whole-machine bird swallowing test verification requirements, with a high test success rate and a short test cycle. At the same time, through the distributed verification method of component bird strike test-whole-machine test run-whole-machine bird swallowing test, the problem of engine bird swallowing capability verification, which was previously incomplete in component test verification and high in whole-machine test risk, is solved, and has strong engineering application value.

[0052] The above description is merely a specific embodiment of the present application, but the scope of protection of the present application is not limited thereto. Any changes or substitutions that can be easily conceived by a person skilled in the art within the technical scope disclosed in this application should be included in the scope of protection of the present application. Therefore, the scope of protection of the present application should be based on the scope of protection of the claims.

Claims

1. A step-by-step verification method for an aviation turbofan engine swallowing a flock of birds, characterized in that: include: Select the test standard, select the engine to be used, and determine the bird swallowing test parameters based on the standard for the control test; Conduct component bird strike tests based on the bird swallowing test parameters to verify whether the structural damage results under the component bird strike conditions meet the requirements. If they do, obtain the component bird strike test data and proceed to the next step. If they do not meet the requirements, determine a specific improvement plan for the specific damaged structure and re-conduct the component bird strike test until the requirements are met. Replace the component structure of the bird strike test component with the complete engine; Combined with component bird strike test data, the whole-machine test is conducted to verify the design. After the design is completed, the whole-machine test is conducted to verify whether the aerodynamic changes of the whole-machine caused by the structural damage of the component bird strike test piece meet the requirements. If the requirements are met, the whole-machine test data is obtained and the next step is executed. If the requirements are not met, the specific aerodynamic damage design is analyzed, a specific improvement plan is determined, and the component bird strike test is repeated until the requirements are met. Carry out the whole machine test design, and conduct the whole machine bird swallowing test based on the whole machine test data; The specific steps of the component bird strike test include: determining the technical status of the test component and determining the component status that meets the bird swallowing capability verification requirements; then debugging the test equipment, after meeting the bird swallowing test parameter requirements, recording the fan blade status before the test, and then conducting the component bird strike test, recording the fan blade status after the test, and comparing the fan blade status difference before and after the test to obtain structural damage results; The bird swallowing test parameters include the number and weight of swallowed birds, bird speed, launch position, test status, test procedure, and pass standard; The specific design of replacing the component structure with the complete engine includes: determining the required components to be replaced on the complete engine for the component bird strike test, determining the corresponding position of each required component on the complete engine, measuring the residual unbalance of the fan blades, analyzing the impact on the vibration of the low-pressure rotor to determine whether the rotor passes the critical speed during the start-up of the complete engine; if so, replacing all required components with the corresponding positions of the complete engine to complete the replacement; if not, adjusting the required components with the corresponding positions of the complete engine to meet the residual unbalance of the fan blades, and completing the replacement; the required components include all fan blades used in the component bird strike test; The method for verifying the design by whole machine test run includes: Determine the test procedure and keep the test status points of the test procedure the same as the formal test; Perform target capability verification to check whether the thrust loss in the test assessment state meets the requirements. If so, proceed to the next step. Determine whether the technical status of the test engine meets the requirements. If so, proceed to the next step; Keep the test equipment requirements the same as the formal test requirements; Determine test parameter measurements and constraints; Carry out pre-test preparations and record the status of the entire machine before testing; Determine whether the test data recording content and the post-test whole machine inspection content meet the requirements. If so, conduct a whole machine test run.

2. The step-by-step verification method for an aviation turbofan engine swallowing a flock of birds as claimed in claim 1, characterized in that: The structural damage verification of the component bird strike test is obtained by means of damage structure inspection and analysis of the data results of the component bird strike test; when it is determined that the structural damage verified by the component bird strike test does not meet the requirements or the aerodynamic damage of the whole engine test does not meet the requirements due to structural damage, a specific improvement design solution is determined by means of comparative analysis with equivalent domestic and foreign engine structures, strength simulation calculations, and aerodynamic simulation calculations; After determining the improved design solution, conduct simulation analysis or test verification to verify whether it is effective. If it is effective, the improvement is qualified; If it is ineffective, redesign and improve the design until it meets the requirements.

3. The step-by-step verification method for an aviation turbofan engine swallowing a flock of birds as claimed in claim 1, characterized in that: The aerodynamic damage verification of the whole-machine test is obtained by analyzing the performance and parameter changes of engine performance parameters, control system parameters, vibration parameters, pulsation parameters, and camera data during the whole-machine test. When it is determined that the aerodynamic damage results caused by the aerodynamic design do not meet the requirements, a specific improvement design solution is determined by comparative analysis with equivalent domestic and foreign engine aerodynamic designs and aerodynamic simulation analysis; After determining the improved design solution, conduct simulation analysis or test verification to verify whether it is effective. If it is effective, the improvement is qualified; If it is ineffective, redesign and improve the design until it meets the requirements.

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