CN116296419A - Method for verifying bird-swallowing navigable compliance of aviation turbofan engine - Google Patents
Method for verifying bird-swallowing navigable compliance of aviation turbofan engine Download PDFInfo
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- 230000009747 swallowing Effects 0.000 claims abstract description 40
- 230000008450 motivation Effects 0.000 claims description 13
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Abstract
According to the aviation turbofan engine bird swallowing airiness compliance verification method, the types of tests to be carried out are judged according to different engines, then bird swallowing airiness compliance verification is carried out according to different modes according to bird bodies with different weight levels, when any single test is carried out, only a targeted test is needed to be unfolded, and the cooperative coordination of a plurality of engine resources, rack resources, debugging and test projection bird body resources, manpower resources and the like is not needed.
Description
Technical Field
The application belongs to the field of aeroengine bird swallowing tests, and particularly relates to a method for verifying avigation suitability of an aero turbofan engine.
Background
With the rapid development of the aviation field, the influence of birds on the flight safety is continuously highlighted, and the airworthiness compliance verification of bird swallowing capacity becomes an important working content in the development process of civil aviation turbofan engines. And aiming at the validation of the navigability compliance of the engine bird swallowing capacity, the regulation bird swallowing clause prescribes the safety influence and the working capacity requirement of the engine under the condition of bird swallowing in different weight grades. Although the verification method of the whole machine test is adopted, whether the bird swallowing capacity of the engine meets the airworthiness requirement can be judged directly and accurately based on the test result, the conditions of single bird, medium bird and medium bird additional integrity assessment, bird and multi-feather bird verification requirements are respectively proposed based on airworthiness regulations, all the verification is completed through the whole machine test, the required resources are excessive, the period is too long, and the method is difficult to popularize in the actual engineering application of the aeroengine. Therefore, it is particularly important to design a set of aviation turbofan engine bird swallowing capacity airworthiness compliance verification method, which not only accurately verifies the meeting condition of airworthiness regulation requirements, but also can meet the limiting conditions of resources, period and the like in the development and practice of the aviation engine.
Disclosure of Invention
The purpose of the application is to provide a method for verifying the avigation suitability of an aviation turbofan engine, so as to solve the problems of more resources and long required period in the bird swallowing test in the prior art.
The technical scheme of the application is as follows: a method for verifying avigation suitability of an aviation turbofan engine comprises the following steps:
acquiring engine data, and judging the type of a test to be performed, wherein the test type comprises an improved/derivative engine verification test and a new research and development motivation verification test, and the new research and development motivation verification test comprises a single bird verification test, a medium bird verification test, a small bird verification test and a multi-feather bird verification test;
judging whether a prototype engine corresponding to the improved/derived engine is an engine which passes through the bird swallowing airworthiness compliance verification or not before the improved/derived engine is judged; if yes, carrying out comparison analysis of the improved/derivative engine and the prototype engine; if not, carrying out the navigable compliance verification of the bird swallowing capacity according to a verification test of a new research and development motivation;
judging to perform a new research and development motivation verification test, and judging a specific test type;
if the single bird verification test is judged to be carried out, 1) determining the test parameter requirement according to the navigability rule, and carrying out complete machine test verification of the single bird; or 2) adopting a containment test equivalent method for verification;
if the middle bird verification test is judged to be carried out, 1) determining the test parameter requirement according to the navigability regulation, and carrying out the whole machine test verification of the middle bird; 2) Performing additional integrity assessment verification;
if the bird test verification is judged, whether the bird test verification passes through the endocytic bird capability verification is judged. If yes, equivalent verification of the bird capability is achieved through the medium bird verification result; if not, determining the test parameter requirements according to the navigable regulations, and performing overall test verification of the bird;
if the multi-feather bird verification test is judged to be carried out, 1) carrying out complete machine test verification on the multi-feather bird according to the test parameter requirement; or 2) verifying the whole machine for stringing the bird strike part.
Preferably, in the improved/derived engine verification test, after the comparative analysis of the improved/derived engine and the prototype engine is performed, whether the relevant design characteristics are the same or better than those of the prototype engine is judged again, and if not, the navigability compliance verification of the bird swallowing capacity is performed according to the engine verification test; if yes, consulting whether the user agrees to try-out, and if yes, trying-out.
Preferably, the content of the comparison analysis of the improved/derivative engine and the prototype engine comprises: a fan blade configuration change; the tangential speed of the blade tip of the fan changes; the deflection capability of the blade root of the fan blade in the mortise is changed; the axial distance between the fan blade and the booster stage inlet guide vane varies; the front edge inclination angle of the inlet guide vane of the supercharging stage changes; the conical surface form of the fan cap is changed; the shape of the neck flow path of the outlet of the pressurizing stage is changed; VBV bleed valve variation; the fan case contains the ring change; the design of the core machine is changed; fan related component materials vary.
Preferably, the containment test equivalent verification method comprises the following steps:
determining test parameters according to airworthiness regulations, performing a bird strike test on a fan component, and measuring axial load caused by bird strike in the component test;
aiming at the axial load influence, based on an axial load measurement result in the bird strike part test, analyzing and proving that the axial load influence does not exceed the bearing capacity, and if proving success, completing the axial load influence analysis;
aiming at the influence of blade containment and rotor unbalance, comparing the weight of the lost block/broken flying-lost blade in the bird strike part test, the blade containment and the rotor unbalance test, and judging the difference of influence of the blade on the containment of the casing; calculating and comparing centrifugal loads of fragments under 2 test conditions according to the weight, the gravity center and the test rotating speed of the falling/broken flying blade, and judging the influence difference of unbalanced loads of the falling/broken flying blade and the broken flying blade;
aiming at the load influence of the installation section, adopting dynamic simulation analysis based on a complete machine finite element model, an installation section safety strength test and the like, and comparing and analyzing the load difference of the installation section under the bird strike/blade flight loss condition;
aiming at the surge load influence, considering the damage of the fan blade, the blocking influence of the bird body on the airflow channel and the like, and comparing and analyzing the surge energy under the condition of bird strike/blade loss;
considering rotor clamping stagnation under bird strike/blade loss conditions aiming at torque load influence, and comparing and analyzing maximum torque under two conditions according to parameters such as rotor rotation speed, rotor moment of inertia, time and the like, or analyzing and proving whether the torque load under bird strike conditions is in an acceptable range of an engine;
in the aspect of fire prevention, the methods of fragment flying-off track, energy analysis and the like under bird strike/blade flying-off conditions can be adopted to compare and analyze the differences of damage of the lubricating oil tank and oil pipe breakage under two conditions;
carrying out comprehensive comparison analysis on the load influence under the two test conditions, and finishing the comprehensive comparison analysis if the impact load of the bird is proved to be lower than that of the blade containment and rotor unbalance test;
and indirectly verifying whether the single bird swallowing capacity of the engine meets the navigability requirement or not based on the result that the containing capacity passes the verification.
Preferably, the whole machine test verification method for the multi-feather bird comprises the following steps:
determining test parameter requirements according to multi-feather bird requirements specified by airworthiness, and verifying bird swallowing capacity in a complete machine test mode;
and the test is carried out in combination with a single bird test, the weight, the speed and the impact position of the bird are verified according to the airworthiness rule, and the test procedure after swallowing the bird is respectively verified according to the airworthiness rule through the standard.
Preferably, the bird strike part stringing complete machine verification method comprises the following steps:
determining test parameters according to airworthiness regulations, and performing a bird strike test of a fan component, wherein a test piece at least comprises parts which have key influence on swallowing ability of a multi-feather bird;
performing impact analysis of the dynamics and performance directions of the whole machine;
and (3) stringing the part of the fan part subjected to the bird strike test to the whole engine, and performing operation of the whole engine to verify whether the fan part meets the requirement of the navigable regulations.
According to the aviation turbofan engine bird swallowing airiness compliance verification method, according to the types of tests required to be carried out by different engine judgment, bird swallowing airiness compliance verification is carried out according to different modes aiming at bird bodies with different weight levels, when any single test is carried out, only a targeted test is needed to be unfolded, a plurality of engine resources, rack resources, debugging and test projection bird body resources, manpower resources and the like are not needed to be matched in a cooperative mode, the method is comprehensive and systematic, reasonable and effective verification is ensured, meanwhile, the working period is shortened, test resources are saved, the development cost is reduced, and the whole set of method is successfully applied to the turbofan engine bird swallowing airiness compliance verification.
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In order to more clearly illustrate the technical solutions provided by the present application, the following description will briefly refer to the accompanying drawings. It will be apparent that the figures described below are only some embodiments of the present application.
Fig. 1 is a schematic diagram of a rectification flow chart of the present application.
Detailed Description
In order to make the purposes, technical solutions and advantages of the implementation of the present application more clear, the technical solutions in the embodiments of the present application will be described in more detail below with reference to the accompanying drawings in the embodiments of the present application.
A method for verifying avigation suitability of an aviation turbofan engine, as shown in figure 1, comprises the following steps:
step S100, obtaining engine data, judging the type of an experiment to be performed, namely judging the type of the engine to be an improved/derivative engine or a new research and development motivation, and performing different experiments on different engines, wherein the test type comprises an improved/derivative engine verification experiment and a new research and development motivation verification experiment, and the new research and development motivation verification experiment comprises a single bird verification experiment, a medium bird verification experiment, a bird verification experiment and a multi-feather bird verification experiment;
step S200, judging whether an improved/derived engine verification test is carried out, and firstly judging whether a prototype engine corresponding to the improved/derived engine is an engine which passes through bird swallowing airworthiness compliance verification; if yes, carrying out comparison analysis of the improved/derivative engine and the prototype engine; if not, carrying out the navigable compliance verification of the bird swallowing capacity according to a verification test of a new research and development motivation;
in the modified/derived engine verification test, the content of the modified/derived engine to prototype engine comparison analysis is preferably:
1) Fan blade configuration changes, such as: whether the fan blade has a vibration damping shoulder, fan blade geometry, fan blade chord length, fan blade thickness, fan blade material, etc.;
2) The tangential speed of the blade tip of the fan changes;
3) The deflection capability of the blade root of the fan blade in the mortise is changed;
4) The axial distance between the fan blade and the booster stage inlet guide vane varies;
5) The front edge inclination angle of the inlet guide vane of the supercharging stage changes;
6) The conical surface form of the fan cap is changed;
7) The shape of the neck flow path of the outlet of the pressurizing stage is changed;
8) VBV bleed valve variation;
9) Fan case containment ring variations such as: containment ring structural form, containment ring material, containment ring thickness, etc.;
10 A core machine design change;
11 A change in material of related components such as a fan;
12 Other design changes related to bird swallowing ability are analyzed according to the specific practical situation of the improvement.
After the analysis is finished, judging whether the related design characteristics are the same, similar or better than those of the prototype engine again, and if not, carrying out the navigable compliance verification of the bird swallowing capacity according to an engine verification test; if yes, consulting whether the user agrees to try-out, and if yes, trying-out.
Step S300, judging to perform a new research and development motivation verification test, and judging a specific test type;
if judging that a single bird verification test is carried out, two verification methods are provided, specifically comprising the following steps:
1) Determining test parameter requirements according to navigability regulations, and verifying bird swallowing capacity of a single bird whole machine test;
2) Performing equivalent verification of a containment test;
according to different engine models, one of the proper verification methods is selected, when the equivalent verification of the containment test is carried out, the required resources of the test are greatly reduced, the development cost is obviously reduced, the verification period is obviously shortened, and the development efficiency is obviously improved.
The verification steps are as follows:
(1) determining test parameters according to airworthiness regulations, performing a bird strike test on a fan component, and measuring axial load caused by bird strike in the component test;
(2) aiming at the axial load influence, based on an axial load measurement result in the bird strike part test, analyzing and proving that the axial load influence does not exceed the bearing capacity, and if proving success, completing the axial load influence analysis;
(3) aiming at the influence of blade containment and rotor unbalance, comparing the weight of the lost block/broken flying-lost blade in the bird strike part test, the blade containment and the rotor unbalance test, and judging the difference of influence of the blade on the containment of the casing; calculating and comparing centrifugal loads of fragments under 2 test conditions according to the weight, the gravity center and the test rotating speed of the falling/broken flying blade, and judging the influence difference of unbalanced loads of the falling/broken flying blade and the broken flying blade;
(4) aiming at the load influence of the installation section, adopting dynamic simulation analysis based on a complete machine finite element model, an installation section safety strength test and the like, and comparing and analyzing the load difference of the installation section under the bird strike/blade flight loss condition;
(5) aiming at the surge load influence, considering the damage of the fan blade, the blocking influence of the bird body on the airflow channel and the like, and comparing and analyzing the surge energy under the condition of bird strike/blade loss;
(6) considering rotor clamping stagnation under bird strike/blade loss conditions aiming at torque load influence, and comparing and analyzing maximum torque under two conditions according to parameters such as rotor rotation speed, rotor moment of inertia, time and the like, or analyzing and proving whether the torque load under bird strike conditions is in an acceptable range of an engine;
(7) in the aspect of fire prevention, the methods of fragment flying-off track, energy analysis and the like under bird strike/blade flying-off conditions can be adopted to compare and analyze the differences of damage of the lubricating oil tank and oil pipe breakage under two conditions;
(8) carrying out comprehensive comparison analysis on the load influence under the two test conditions, and finishing the comprehensive comparison analysis if the impact load of the bird is proved to be lower than that of the blade containment and rotor unbalance test;
(9) and indirectly verifying whether the single bird swallowing capacity of the engine meets the navigability requirement or not based on the result that the containing capacity passes the verification.
If judging that the in-process bird verification test is performed, the method comprises two verification contents, and specifically comprises the following steps:
1) Determining test parameter requirements according to airworthiness regulations, and verifying bird swallowing capacity of a whole medium bird test;
2) Performing additional integrity assessment verification;
if the bird test verification is judged to be carried out, the whole bird test verification is carried out on the engine which is not carried out or is not verified to pass through, and the test parameter requirement is determined according to the navigable regulations, wherein the whole bird test verification method is the same as the bird swallowing capacity verification method of the whole bird test.
If the multi-feather bird verification test is judged to be carried out, two verification methods are provided, and specifically include:
1) Performing complete machine test verification of the multi-feather bird according to test parameter requirements, and specifically comprising the following steps:
(1) determining test parameter requirements according to the requirements of the air-fit regulation FAR33.76 (d) multi-feather birds, and verifying bird swallowing capacity in a complete machine test mode.
(2) Combined with a single bird test. That is, the weight, speed and impact position of the birds were carried out according to the (1) th in the single bird of the air-qualified prescription FAR33.76 (b), and the test procedure after swallowing the birds was carried out according to the (4) th and (5) th in the multi-feather birds of the air-qualified prescription FAR33.76 (d) by the standard.
2) Performing verification of the bird strike assembly complete machine, specifically comprising:
(1) determining test parameters according to the requirements of a specified air-Fit (FAR) 33.76 (d) multi-feather bird, and performing a fan component bird strike test, wherein the test piece at least comprises parts which have key influence on the swallowing capacity of the multi-feather bird, such as a fan blade and a connecting piece thereof, a fan inlet and outlet guide blade, a cap, a fan disc, a shaft, a fan casing, a bearing seat and the like;
(2) analyzing the effects of the dynamics, performance and the like of the whole machine, including but not limited to surge, flameout, overrun and the like, and proving that the effects on the requirements of the (4) th and (5) th strips in the air-fit regulation FAR33.76 (d) are negligible;
(3) and (3) the parts subjected to the test (1) are assembled to the whole engine in series, and the whole engine is operated, so that the requirements of the (4) th and the (5) th strips in the air-fit regulation FAR33.76 (d) are verified.
According to different engine models, one of the proper verification methods is selected, when the verification method is combined with a single bird test to be carried out, or the verification of the bird strike part serial assembly complete machine is carried out, the required resources of the test are greatly reduced, the development cost is obviously reduced, the verification period is obviously shortened, and the development efficiency is obviously improved.
By adopting the method, bird swallowing airworthiness compliance verification is respectively carried out according to different modes aiming at bird bodies with different weight levels, when any single test is carried out, only a targeted test is needed to be unfolded, the cooperative coordination of a plurality of engine resources, rack resources, debugging and test projection bird body resources, manpower resources and the like is not needed, the method is comprehensive and systematic, the reasonable and effective verification is ensured, meanwhile, the working period is shortened, the test resources are saved, the development cost is reduced, and the whole method is successfully applied to the turbofan engine bird swallowing airworthiness compliance verification.
The foregoing is merely specific embodiments of the present application, but the scope of the present application is not limited thereto, and any changes or substitutions easily conceivable by those skilled in the art within the technical scope of the present application should be covered in the scope of the present application. Therefore, the protection scope of the present application shall be subject to the protection scope of the claims.
Claims (6)
1. A method for verifying avigation suitability of an aviation turbofan engine is characterized by comprising the following steps:
acquiring engine data, and judging the type of a test to be performed, wherein the test type comprises an improved/derivative engine verification test and a new research and development motivation verification test, and the new research and development motivation verification test comprises a single bird verification test, a medium bird verification test, a small bird verification test and a multi-feather bird verification test;
judging whether a prototype engine corresponding to the improved/derived engine is an engine which passes through the bird swallowing airworthiness compliance verification or not before the improved/derived engine is judged; if yes, carrying out comparison analysis of the improved/derivative engine and the prototype engine; if not, carrying out the navigable compliance verification of the bird swallowing capacity according to a verification test of a new research and development motivation;
judging to perform a new research and development motivation verification test, and judging a specific test type;
if the single bird verification test is judged to be carried out, 1) determining the test parameter requirement according to the navigability rule, and carrying out complete machine test verification of the single bird; or 2) adopting a containment test equivalent method for verification;
if the middle bird verification test is judged to be carried out, 1) determining the test parameter requirement according to the navigability regulation, and carrying out the whole machine test verification of the middle bird; 2) Performing additional integrity assessment verification;
if the bird test verification is judged, whether the bird test verification passes through the endocytic bird capability verification is judged. If yes, equivalent verification of the bird capability is achieved through the medium bird verification result; if not, determining the test parameter requirements according to the navigable regulations, and performing overall test verification of the bird;
if the multi-feather bird verification test is judged to be carried out, 1) carrying out complete machine test verification on the multi-feather bird according to the test parameter requirement; or 2) verifying the whole machine for stringing the bird strike part.
2. The method for verifying avigation suitability of an aviation turbofan engine as defined in claim 1, wherein the method comprises the steps of: in the improved/derived engine verification test, after the comparison analysis of the improved/derived engine and the prototype engine is carried out, judging whether the related design characteristics are the same as or better than those of the prototype engine again, if not, carrying out the navigability compliance verification of the bird swallowing capacity according to the engine verification test; if yes, consulting whether the user agrees to try-out, and if yes, trying-out.
3. The method for verifying avigation suitability of an aircraft turbofan engine of claim 2, wherein the content of the comparison analysis of the modified/derivative engine with the prototype engine comprises:
a fan blade configuration change; the tangential speed of the blade tip of the fan changes; the deflection capability of the blade root of the fan blade in the mortise is changed; the axial distance between the fan blade and the booster stage inlet guide vane varies; the front edge inclination angle of the inlet guide vane of the supercharging stage changes; the conical surface form of the fan cap is changed; the shape of the neck flow path of the outlet of the pressurizing stage is changed; VBV bleed valve variation; the fan case contains the ring change; the design of the core machine is changed; fan related component materials vary.
4. The method for verifying avigation suitability of an aviation turbofan engine as defined in claim 1, wherein the containment test equivalent verification method comprises:
determining test parameters according to airworthiness regulations, performing a bird strike test on a fan component, and measuring axial load caused by bird strike in the component test;
aiming at the axial load influence, based on an axial load measurement result in the bird strike part test, analyzing and proving that the axial load influence does not exceed the bearing capacity, and if proving success, completing the axial load influence analysis;
aiming at the influence of blade containment and rotor unbalance, comparing the weight of the lost block/broken flying-lost blade in the bird strike part test, the blade containment and the rotor unbalance test, and judging the difference of influence of the blade on the containment of the casing; calculating and comparing centrifugal loads of fragments under 2 test conditions according to the weight, the gravity center and the test rotating speed of the falling/broken flying blade, and judging the influence difference of unbalanced loads of the falling/broken flying blade and the broken flying blade;
aiming at the load influence of the installation section, adopting dynamic simulation analysis based on a complete machine finite element model, an installation section safety strength test and the like, and comparing and analyzing the load difference of the installation section under the bird strike/blade flight loss condition;
aiming at the surge load influence, considering the damage of the fan blade, the blocking influence of the bird body on the airflow channel and the like, and comparing and analyzing the surge energy under the condition of bird strike/blade loss;
considering rotor clamping stagnation under bird strike/blade loss conditions aiming at torque load influence, and comparing and analyzing maximum torque under two conditions according to parameters such as rotor rotation speed, rotor moment of inertia, time and the like, or analyzing and proving whether the torque load under bird strike conditions is in an acceptable range of an engine;
in the aspect of fire prevention, the methods of fragment flying-off track, energy analysis and the like under bird strike/blade flying-off conditions can be adopted to compare and analyze the differences of damage of the lubricating oil tank and oil pipe breakage under two conditions;
carrying out comprehensive comparison analysis on the load influence under the two test conditions, and finishing the comprehensive comparison analysis if the impact load of the bird is proved to be lower than that of the blade containment and rotor unbalance test;
and indirectly verifying whether the single bird swallowing capacity of the engine meets the navigability requirement or not based on the result that the containing capacity passes the verification.
5. The method for verifying avigation suitability of an aviation turbofan engine as defined in claim 1, wherein the method for verifying complete machine test of the multi-feather bird comprises the following steps:
determining test parameter requirements according to multi-feather bird requirements specified by airworthiness, and verifying bird swallowing capacity in a complete machine test mode;
and the test is carried out in combination with a single bird test, the weight, the speed and the impact position of the bird are verified according to the airworthiness rule, and the test procedure after swallowing the bird is respectively verified according to the airworthiness rule through the standard.
6. The method for verifying avionics of an aircraft turbofan engine according to claim 1, wherein the method for verifying the bird-strike assembly machine comprises the following steps:
determining test parameters according to airworthiness regulations, and performing a bird strike test of a fan component, wherein a test piece at least comprises parts which have key influence on swallowing ability of a multi-feather bird;
performing impact analysis of the dynamics and performance directions of the whole machine;
and (3) stringing the part of the fan part subjected to the bird strike test to the whole engine, and performing operation of the whole engine to verify whether the fan part meets the requirement of the navigable regulations.
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| CN202211104528.4A CN116296419A (en) | 2022-09-09 | 2022-09-09 | Method for verifying bird-swallowing navigable compliance of aviation turbofan engine |
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| CN202211104528.4A CN116296419A (en) | 2022-09-09 | 2022-09-09 | Method for verifying bird-swallowing navigable compliance of aviation turbofan engine |
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