CN-115270467-B - Method for determining bird swallowing capacity of aero-engine

CN115270467BCN 115270467 BCN115270467 BCN 115270467BCN-115270467-B

Abstract

The application provides an aero-engine bird-swallowing capacity determining method, which belongs to the field of aero-engine tests and comprises the steps of carrying out blade bird strike resistance evaluation through an intensity simulation method, correcting a part test result to obtain a blade bird strike resistance rule, carrying out pneumatic modeling through damaged blades, carrying out pneumatic influence evaluation caused by damaged blades, correcting the damaged blades through hanging test run to obtain a pneumatic influence rule of the damaged blades on the engine, determining quantitative relation between bird-swallowing parameters and blade damage through test and simulation results, determining an intensity boundary and a pneumatic boundary of the aero-engine bird-swallowing capacity, determining the bird-swallowing capacity of the engine according to the engine bird-swallowing intensity and the pneumatic boundary in combination with bird-swallowing standards, and determining the bird-swallowing capacity of the engine.

Inventors

LI XIAOCHONG
HAN FANGJUN
WANG HUA
ZHANG HAIYANG
FENG DONGMIN
LIU DACHENG
ZHANG QING

Assignees

中国航发沈阳发动机研究所

Dates

Publication Date: 20260505
Application Date: 20220727

Claims (5)

1. A method for determining bird swallowing capacity of an aeroengine, comprising the steps of: Step S1, determining test parameters of a bird swallowing test of a test piece according to a given standard of the bird swallowing test examination; S2, performing blade bird strike strength simulation calculation on the test piece according to the test parameters to obtain a damage simulation model; Step S3, performing a component rotation test on the test piece, and checking the damage simulation model by using the result of the component rotation test to obtain a high-precision damage simulation model; s4, based on the high-precision damage simulation model, performing pneumatic simulation evaluation to obtain a bird impact damage pneumatic loss evaluation model; S5, carrying out a damaged blade hanging piece test on the test piece, and checking a bird strike damage pneumatic loss evaluation model according to the result of the damaged blade hanging piece test to obtain a high-precision bird strike damage pneumatic loss evaluation model; S6, adjusting the test parameters to obtain multiple high-precision damage simulation models of different positions of the blade of the test piece, which bear the impacts of birds with different weights, and determining the strength boundary of the bird swallowing capacity of the aero-engine; the parameters of thrust loss and aerodynamic loss caused by the impact of different bird weights on different positions of the blades of the test piece are obtained through adjusting the input parameters of the high-precision bird impact damage aerodynamic loss evaluation model, and the aerodynamic boundary of the bird swallowing capacity of the aeroengine is determined; and S7, determining the bird swallowing capacity of the engine according to the intensity boundary and the pneumatic boundary of the bird swallowing of the engine and combining the standard of the bird swallowing test examination.
2. The method for determining the bird swallowing capacity of an aeroengine according to claim 1, wherein the test parameters in the step S1 comprise an engine state parameter, a bird speed parameter and a fan rotation speed parameter.
3. The method for determining the bird swallowing capacity of an aeroengine according to claim 1, wherein step S1 further determines a criterion for passing the test, a program and time executed by the engine after swallowing, a continuous running time of the test state and a thrust loss.
4. The method of determining the bird swallowing capacity of an aeroengine of claim 1, wherein the result of the component rotation test is a damage pattern of a truly damaged blade of the test piece, the damage pattern including cracking, deformation, and chipping of the test piece.
5. The method for determining the bird swallowing capacity of an aeroengine according to claim 1, wherein the simulated bird bodies used in the component rotation test are identical to the simulated bird bodies used in the blade bird strike strength simulation calculation.

Description

Method for determining bird swallowing capacity of aero-engine Technical Field The application belongs to the field of aeroengine tests, and particularly relates to a method for determining bird swallowing capacity of an aeroengine. Background The aeroengine needs to be subjected to bird swallowing test examination, namely a certain amount of bird bodies with certain weight are swallowed according to a specific standard, so that the safety of the aeroengine when the bird is encountered in the air is examined. At present, the bird swallowing capacity of the aero-engine is verified to pass through a front-stage static blade bird strike test, a rotating part bird strike test and a final complete machine bird swallowing test; The main purpose of the current bird swallowing part and complete machine test is to verify whether the engine can pass through the bird swallowing examination, and the maximum and minimum bird swallowing capacity of the engine cannot be clarified because the test cost is high, the period is long, the test times are limited, the bird swallowing capacity of the engine cannot be comprehensively known. In addition, when the engine has test capability, the design stage of the engine is approaching tail sound, and if the bird swallowing capability does not meet the requirement, the cost for design improvement is high and the difficulty is high. Therefore, it is desirable to construct a verification method that can fully understand the bird swallowing ability of an engine, while guiding the bird strike resistant design of the engine. Disclosure of Invention In order to solve the problems, the application provides a method for determining bird swallowing capacity of an aeroengine, which comprises the following steps: Step S1, determining test parameters of a bird swallowing test of a test piece according to a given standard of the bird swallowing test examination; S2, performing blade bird strike strength simulation calculation on the test piece according to the test parameters to obtain a damage simulation model; Step S3, performing a component rotation test on the test piece, and checking the damage simulation model by using the result of the component rotation test to obtain a high-precision damage simulation model; s4, based on the high-precision damage simulation model, performing pneumatic simulation evaluation to obtain a bird impact damage pneumatic loss evaluation model; S5, carrying out a damaged blade hanging piece test on the test piece, and checking a bird strike damage pneumatic loss evaluation model according to the result of the damaged blade hanging piece test to obtain a high-precision bird strike damage pneumatic loss evaluation model; S6, adjusting the test parameters to obtain multiple high-precision damage simulation models of different positions of the blade of the test piece, which bear the impacts of birds with different weights, and determining the strength boundary of the bird swallowing capacity of the aero-engine; the parameters of thrust loss and aerodynamic loss caused by the impact of different bird weights on different positions of the blades of the test piece are obtained through adjusting the input parameters of the high-precision bird impact damage aerodynamic loss evaluation model, and the aerodynamic boundary of the bird swallowing capacity of the aeroengine is determined; and S7, determining the bird swallowing capacity of the engine according to the intensity boundary and the pneumatic boundary of the bird swallowing of the engine and combining the standard of the bird swallowing test examination. Preferably, the test parameters described in step S1 include an engine state parameter, a bird speed parameter, and a fan speed parameter. Preferably, step S1 further determines the criteria for passing the test, the program and time executed by the engine after bird swallowing, the test state duration and the thrust loss. Preferably, the result of the component rotation test is a damage pattern of the test piece actually damaging the blade, the damage pattern including cracking, deformation, and chipping of the test piece. Preferably, the simulated bird body used in the component rotation test is the same as the simulated bird body used in the blade bird strike strength simulation calculation. Preferably, the high-precision damage simulation model using method comprises the steps of adjusting the test parameters to obtain multiple damage simulation models of different positions of the test piece blade, which bear different weight bird impacts, and determining the strength boundary of the bird swallowing capacity of the aeroengine. The advantages of the application include: 1. determining bird swallowing capacity of the aeroengine; 2. the method for determining the bird swallowing capacity has the advantages of low cost, short period and small risk; 3. the bird swallowing capacity determining method is generalized and is not only used for a specific engine; 4. The