CN115358113B - Pulse life calculation method for polytetrafluoroethylene hose for aircraft engine - Google Patents

Pulse life calculation method for polytetrafluoroethylene hose for aircraft engine Download PDF

Info

Publication number
CN115358113B
CN115358113B CN202210902437.9A CN202210902437A CN115358113B CN 115358113 B CN115358113 B CN 115358113B CN 202210902437 A CN202210902437 A CN 202210902437A CN 115358113 B CN115358113 B CN 115358113B
Authority
CN
China
Prior art keywords
hose
polytetrafluoroethylene hose
polytetrafluoroethylene
pulse
calculating
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Active
Application number
CN202210902437.9A
Other languages
Chinese (zh)
Other versions
CN115358113A (en
Inventor
沈锡钢
史志勇
冯凯
齐晓雪
张强
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
AECC Shenyang Engine Research Institute
Original Assignee
AECC Shenyang Engine Research Institute
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by AECC Shenyang Engine Research Institute filed Critical AECC Shenyang Engine Research Institute
Priority to CN202210902437.9A priority Critical patent/CN115358113B/en
Publication of CN115358113A publication Critical patent/CN115358113A/en
Application granted granted Critical
Publication of CN115358113B publication Critical patent/CN115358113B/en
Active legal-status Critical Current
Anticipated expiration legal-status Critical

Links

Images

Classifications

    • G—PHYSICS
    • G06—COMPUTING; CALCULATING OR COUNTING
    • G06F—ELECTRIC DIGITAL DATA PROCESSING
    • G06F30/00—Computer-aided design [CAD]
    • G06F30/20—Design optimisation, verification or simulation
    • G06F30/23—Design optimisation, verification or simulation using finite element methods [FEM] or finite difference methods [FDM]
    • G—PHYSICS
    • G06—COMPUTING; CALCULATING OR COUNTING
    • G06F—ELECTRIC DIGITAL DATA PROCESSING
    • G06F30/00—Computer-aided design [CAD]
    • G06F30/20—Design optimisation, verification or simulation
    • G06F30/28—Design optimisation, verification or simulation using fluid dynamics, e.g. using Navier-Stokes equations or computational fluid dynamics [CFD]
    • G—PHYSICS
    • G06—COMPUTING; CALCULATING OR COUNTING
    • G06F—ELECTRIC DIGITAL DATA PROCESSING
    • G06F2113/00—Details relating to the application field
    • G06F2113/08—Fluids
    • G—PHYSICS
    • G06—COMPUTING; CALCULATING OR COUNTING
    • G06F—ELECTRIC DIGITAL DATA PROCESSING
    • G06F2113/00—Details relating to the application field
    • G06F2113/14—Pipes
    • G—PHYSICS
    • G06—COMPUTING; CALCULATING OR COUNTING
    • G06F—ELECTRIC DIGITAL DATA PROCESSING
    • G06F2119/00—Details relating to the type or aim of the analysis or the optimisation
    • G06F2119/14—Force analysis or force optimisation, e.g. static or dynamic forces
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T90/00—Enabling technologies or technologies with a potential or indirect contribution to GHG emissions mitigation

Landscapes

  • Engineering & Computer Science (AREA)
  • Physics & Mathematics (AREA)
  • Theoretical Computer Science (AREA)
  • General Physics & Mathematics (AREA)
  • Computer Hardware Design (AREA)
  • General Engineering & Computer Science (AREA)
  • Geometry (AREA)
  • Evolutionary Computation (AREA)
  • Fluid Mechanics (AREA)
  • Pure & Applied Mathematics (AREA)
  • Mathematical Physics (AREA)
  • Mathematical Optimization (AREA)
  • Mathematical Analysis (AREA)
  • Computing Systems (AREA)
  • Algebra (AREA)
  • Investigating Strength Of Materials By Application Of Mechanical Stress (AREA)

Abstract

The application belongs to the technical field of engine part tests, and particularly relates to a pulse life calculation method for a polytetrafluoroethylene hose for an aircraft engine. The method comprises determining an equivalent density of the polytetrafluoroethylene hose at a maximum operating pressure of the engine; measuring a first-order natural frequency of the polytetrafluoroethylene hose; constructing a finite element model of the polytetrafluoroethylene hose, calculating a corresponding first-order natural frequency in the finite element model through a given elastic modulus range, and determining the equivalent elastic modulus when the calculated first-order natural frequency is the same as the first-order natural frequency measured in the step three; calculating to obtain a stress cloud picture by using the finite element model; and calculating the fatigue life value of the polytetrafluoroethylene hose based on a preset fatigue load course. The method for calculating the pulse life is beneficial to determining whether the pulse life meets the requirement or not at the initial research and development stage of the hose, and then the improvement design is carried out, and the research and development period is shortened.

Description

Pulse life calculation method for polytetrafluoroethylene hose for aircraft engine
Technical Field
The application belongs to the technical field of engine part tests, and particularly relates to a pulse life calculation method for a polytetrafluoroethylene hose for an aircraft engine.
Background
The pipeline system of the aero-engine is used as an important component of the aero-engine and has the function of conveying media such as fuel oil, lubricating oil and air. Based on the displacement compensation requirement, the pipeline system assembly error compensation requirement, the damping requirement and the like of part of engine accessories, a polytetrafluoroethylene hose is adopted in a pipeline system. The polytetrafluoroethylene hose assembly for the aircraft engine comprises a polytetrafluoroethylene inner tube (a conductive layer is attached inside), a steel wire reinforcing layer, a metal connecting piece, a fireproof rubber layer and the like. The pipeline of the aircraft engine has a severe working environment and bears loads such as pressure pulsation, vibration, deformation, temperature and the like, and the safety of the aircraft engine and even the flight of an airplane is directly influenced if the pipeline structure can work reliably. The pulse life of the hose is an important design index for hose design, and has great significance for ensuring the working safety of an aircraft engine and establishing a maintenance strategy of the polytetrafluoroethylene hose. In the initial stage of polytetrafluoroethylene hose development, the working condition of an aircraft engine and the use condition of the polytetrafluoroethylene hose are combined, a pulse life is obtained by combining finite element simulation analysis through a small amount of tests, the design iteration of the polytetrafluoroethylene hose can be reduced, the development period is shortened, and the development cost is saved.
The calculation of the service life of the metal hard tube is based on the theoretical calculation and simulation analysis of metal fatigue development, and the problem of calculating the fatigue service life of part of metals can be well solved. In the Chinese invention patent with the application number of 201910401845.4, a method for judging the fatigue life of an air conditioner pipeline is provided, a method for obtaining a finished product grade S-N curve through vibration tests of a large number of products is provided, stress tests are carried out, a working cycle is obtained, and the service life is judged by establishing a model. The calculation method of the metal hard tube is not suitable for calculating the service life of the polytetrafluoroethylene hose due to different material characteristics. In the initial research and development stage of the polytetrafluoroethylene hose, no test condition and data accumulation condition of an air conditioner pipeline fatigue life judgment method exist, so that the method is technically difficult to realize. In the aspect of cost, a large number of tests are adopted for verification, so that greater cost waste is caused, and the repetition of development work is easy to occur. In the aspect of efficiency, the efficiency of the test method is low, and the requirement of the development cycle of the aircraft engine cannot be met. Therefore, the prior art does not meet the development requirement of the polytetrafluoroethylene hose for the aircraft engine.
Disclosure of Invention
In order to solve one of the problems, the application provides a pulse life calculation method for a polytetrafluoroethylene hose for an aircraft engine, which solves the problem of establishing a finite element model of the polytetrafluoroethylene hose in a working state, establishes an analysis model adaptive to the polytetrafluoroethylene hose in the working state, and analyzes the stress condition of the hose; providing a reference S-N curve of a common specification and a related correction method for calculating the subsequent service life; and establishing a life evaluation model, calculating the pulse life of the hose and providing guidance for hose design.
The utility model provides a polytetrafluoroethylene hose pulse life computational method for aeroengine mainly includes:
step one, determining the equivalent density of a polytetrafluoroethylene hose under the maximum working pressure of an engine;
secondly, one end of a polytetrafluoroethylene hose is plugged, and the other end of the polytetrafluoroethylene hose applies pressure which is a preset multiple of the maximum working pressure of the engine;
measuring the first-order natural frequency of the polytetrafluoroethylene hose;
step four, constructing a finite element model of the polytetrafluoroethylene hose, calculating a corresponding first-order natural frequency in the finite element model through a given elastic modulus range, and determining the equivalent elastic modulus when the calculated first-order natural frequency is the same as the first-order natural frequency measured in the step three;
fifthly, calculating to obtain a stress cloud picture by using the finite element model;
and step six, loading the stress cloud chart data into fatigue analysis software, inputting the equivalent density, the Poisson ratio, the equivalent elastic modulus and a reference S-N curve, and calculating the fatigue life value of the polytetrafluoroethylene hose based on a preset fatigue load course.
Preferably, in the first step, the equivalent density ρ is calculated by the following formula:
Figure BDA0003771349350000021
wherein L is polyLength of tetrafluoroethylene hose, d 1 Is the inner diameter of a polytetrafluoroethylene hose, d 2 Is the outer diameter of the polytetrafluoroethylene hose, and M is the mass of the polytetrafluoroethylene hose.
Preferably, in the second step, the predetermined multiple is 1.5 times.
Preferably, the polytetrafluoroethylene hose is fixed in the second step in the same manner as the polytetrafluoroethylene hose in the engine-mounted state in the first step.
Preferably, in step three, the first-order natural frequency of the teflon hose is measured by a force hammer impact method.
Preferably, in the fourth step, in the finite element model, the boundary condition is the same as the engine installation state, the internal pressure is a pressure which is a predetermined multiple of the maximum operating pressure of the engine, the equivalent elastic modulus is set to be changed from 10MPa to 1000MPa, and the equivalent elastic modulus is searched by the bisection method so that the first-order natural frequency calculated at the equivalent elastic modulus is the same as the measured first-order natural frequency.
Preferably, in the fourth step, when constructing the finite element model of the ptfe hose, the selected parameter includes a poisson's ratio, where the poisson's ratio is 3.4 when the inner tube of the ptfe hose is a straight tube, and the poisson's ratio is 4.2 when the inner tube of the ptfe hose is a corrugated tube.
Preferably, in the sixth step, the reference S-N curve is an S-N curve selected from the group of S-N curves, which is closest to the inner diameter of the polytetrafluoroethylene hose to be tested, and in the S-N curve, the ordinate is the logarithm of the service life N, and the abscissa is the stress value S.
Preferably, step six is preceded by further modifying the S-N curve, wherein the modifying comprises: and selecting a plurality of pipelines to carry out pulse test according to the maximum working pressure of the engine to obtain the pulse times, obtaining the maximum stress through a finite element model, and correcting the S-N curve according to the relationship between the pulse times and the maximum stress.
Preferably, in the sixth step, the predetermined fatigue load history comprises a plurality of continuous pulse load cycles, and the load in each pulse load cycle has a minimum value of 0.2 times and a maximum value of 1.5 times of the maximum working pressure of the engine.
The method for correcting the polytetrafluoroethylene hose to establish the finite element simulation model is definite, the equivalent elastic modulus is determined quickly, the necessary conditions for service life calculation are provided, the calculation method of the pulse life is beneficial to determining whether the pulse life meets the requirements or not at the initial stage of research and development of the hose, and then the improvement and design are carried out, the research and development period is shortened, and the technical support is provided for the design and maintenance strategy formulation of the hose of the aero-engine.
Drawings
FIG. 1 is a flow chart of a preferred embodiment of a pulse life calculation method for a Teflon hose used for an aircraft engine according to the present invention;
FIGS. 2a-2f are schematic S-N curves of polytetrafluoroethylene hoses with different inner diameter specifications;
FIG. 3 is a schematic diagram illustrating the correction of the S-N curve;
fig. 4 is a schematic diagram of fatigue load history.
Detailed Description
In order to make the implementation objects, technical solutions and advantages of the present application clearer, the technical solutions in the embodiments of the present application will be described in more detail below with reference to the drawings in the embodiments of the present application. In the drawings, the same or similar reference numerals denote the same or similar elements or elements having the same or similar functions throughout. The described embodiments are some, but not all embodiments of the present application. The embodiments described below with reference to the drawings are exemplary and intended to be used for explaining the present application, and should not be construed as limiting the present application. All other embodiments obtained by a person of ordinary skill in the art without any inventive work based on the embodiments in the present application are within the scope of protection of the present application. Embodiments of the present application will be described in detail below with reference to the drawings.
The application provides a polytetrafluoroethylene hose pulse life calculation method for an aircraft engine, which is characterized in that a finite element simulation model is built from the whole dimensionality based on equivalent elastic modulus, the stress condition of the polytetrafluoroethylene hose is analyzed, a design reference S-N curve is given based on engineering data, a load history loading curve is given at the same time, and a method for calculating the pulse life of the polytetrafluoroethylene hose is given on the basis. The method is used for calculating the service life of the polytetrafluoroethylene hose in the external pipeline of the aircraft engine under the pulse load, and whether the hose structure meets the design requirements or not is checked in the initial development stage of the polytetrafluoroethylene hose, so that design optimization and improvement are promoted, and the method has important significance for improving the design quality and shortening the development period.
As shown in fig. 1, the method for calculating the pulse life of the ptfe hose for an aircraft engine provided by the present application mainly includes:
step one, determining the maximum working pressure P of an engine Pressure of The equivalent density of the polytetrafluoroethylene hose below.
In some alternative embodiments, the equivalent density ρ is calculated by the following equation:
Figure BDA0003771349350000041
wherein L is the length of the polytetrafluoroethylene hose, d 1 Is the inner diameter of a polytetrafluoroethylene hose, d 2 Is the outer diameter of the polytetrafluoroethylene hose, and M is the mass of the polytetrafluoroethylene hose.
Step two, plugging one end of a polytetrafluoroethylene hose, and applying the maximum working pressure P of the engine to the other end Pressure of A predetermined multiple of.
In some alternative embodiments, one end of the hose is plugged with a plug and the other end applies 1.5 times the maximum engine operating pressure P Pressure of The fixing mode of the hose is the same as the engine installation state
And step three, measuring the first-order natural frequency of the polytetrafluoroethylene hose.
In some alternative embodiments, the first natural frequency of the ptfe hose is measured by a force hammer impact method, denoted as ω Testing of . The knockingThe method needs a force hammer and a high-precision laser displacement sensor to obtain the natural frequency through testing.
It should be noted that the force hammer impact method is the most commonly used method for testing the transfer function. The force hammer is used as an excitation source to give transient excitation to a test object and cause a vibration response of the test object in a certain frequency band range, and the response can be captured and analyzed by a signal analyzer. The range of this frequency band is related to the force hammer, including its size, material. Both the impulse signal and the response signal will be captured and recorded by the analyzer, which will then calculate the transfer function of the object from the two signals.
And step four, constructing a finite element model of the polytetrafluoroethylene hose, calculating a corresponding first-order natural frequency in the finite element model through a given elastic modulus range, and determining the equivalent elastic modulus when the calculated first-order natural frequency is the same as the first-order natural frequency measured in the step three.
In the step, L and d are obtained according to the step one 1 、d 2 Rho and Poisson ratio mu, and establishing a finite element model. In some alternative embodiments, the poisson's ratio is 3.4 when the inner tube of the ptfe hose is a straight tube and 4.2 when the inner tube of the ptfe hose is a corrugated tube.
In some optional embodiments, in step four, in the finite element model, the boundary condition is the same as the engine installation state, and the internal pressure is the maximum working pressure P of the engine Pressure of The equivalent elastic modulus is set to vary from 10MPa to 1000MPa, and the equivalent elastic modulus is searched by dichotomy so that the first-order natural frequency calculated at the equivalent elastic modulus is the same as the measured first-order natural frequency.
In this example, the natural frequency value of the modulus of elasticity (10 MPa to 1000 MPa) and the test frequency ω were calculated by finite element Testing Comparing, searching until the calculated natural frequency and the tested natural frequency are found to be equal, wherein the elastic modulus is equivalent elastic modulus E Equivalent weight 。
And fifthly, calculating to obtain a stress cloud picture by using the finite element model.
It can be understood that, by adding boundary conditions including working in consideration of the pressure P, the hose torsion angle θ, the compensation distance S, etc., to the established finite element model, the stress cloud chart can be calculated and the calculated data can be saved.
And step six, loading the stress cloud chart data into fatigue analysis software, inputting the equivalent density, the Poisson ratio, the equivalent elastic modulus and a reference S-N curve, and calculating the fatigue life value of the polytetrafluoroethylene hose based on a preset fatigue load course.
In this example, the fatigue analysis software was Fe-safe.
In some optional embodiments, in the sixth step, the reference S-N curve refers to selecting one S-N curve from the group of S-N curves, which is closest to the inner diameter of the polytetrafluoroethylene hose to be tested, in the S-N curve, the ordinate of the curve is logarithmic coordinate, and is logarithm of the pulse life N, and the abscissa is the stress value S.
FIGS. 2a-2f show the S-N curves of PTFE hoses with major diameters 6,8, 13, 15, 20, 25, respectively, and adjacent sizes may be referenced by similar curves.
In some optional embodiments, step six is preceded by further comprising modifying the S-N curve, the modifying comprising: selecting multiple pipelines according to the maximum working pressure P of the engine Pressure of And performing a pulse test to obtain the pulse times, obtaining the maximum stress through a finite element model, and correcting the S-N curve according to the relationship between the pulse times and the maximum stress.
In this embodiment, when pipelines with different specifications and the same structure are used, the S-N curves of the adjacent specifications are taken first. At least 1 point is selected for correction, and the method comprises the following steps: and 3 pipelines are selected to work according to the working pressure P to carry out a pulse test, and the pulse times N1 are obtained. The maximum stress sigma 1 is obtained through a finite element model, and the model is modified according to D1 (sigma 1, N1). The correction method is shown in fig. 3, and in fig. 3, a curve 6 is a curve obtained by single-point translation of the left curve according to N1, and the curve is a correction curve. In which the reference numeral 7 is a reference curve and the reference numeral 6 is a correction curve. In an alternative embodiment, where multipoint correction is used, the curve may be fitted using a least squares fit.
In some optional embodiments, in step six, the predetermined fatigue load history comprises a plurality of consecutive pulse load cycles, and the minimum value of the load in each pulse load cycle is the maximum working pressure P of the engine Pressure of 0.2 times of the maximum value of the maximum working pressure P of the engine Pressure of 1.5 times of the total weight of the composition. In one specific example, the fatigue load history is shown in FIG. 4, wherein the applied pressure value is the number on the vertical axis of the graph of FIG. 4 multiplied by the maximum engine operating pressure P Pressure of 。
The method for correcting the polytetrafluoroethylene hose to establish the finite element simulation model is definite, the equivalent elastic modulus is determined quickly, the necessary conditions for service life calculation are provided, the calculation method of the pulse life is beneficial to determining whether the pulse life meets the requirements or not at the initial stage of research and development of the hose, and then the improvement and design are carried out, the research and development period is shortened, and the technical support is provided for the design and maintenance strategy formulation of the hose of the aero-engine.
Although the present application has been described in detail with respect to the general description and specific embodiments, it will be apparent to those skilled in the art that certain modifications or improvements may be made based on the present application. Accordingly, such modifications and improvements are intended to be within the scope of this invention as claimed.

Claims (10)

1. A polytetrafluoroethylene hose pulse life calculation method for an aircraft engine is characterized by comprising the following steps:
step one, determining the equivalent density of a polytetrafluoroethylene hose under the maximum working pressure of an engine;
secondly, one end of a polytetrafluoroethylene hose is plugged, and the other end of the polytetrafluoroethylene hose applies pressure which is a preset multiple of the maximum working pressure of the engine;
measuring first-order natural frequency of the polytetrafluoroethylene hose;
step four, constructing a finite element model of the polytetrafluoroethylene hose, calculating a corresponding first-order natural frequency in the finite element model through a given elastic modulus range, and determining the equivalent elastic modulus when the calculated first-order natural frequency is the same as the first-order natural frequency measured in the step three;
fifthly, calculating to obtain a stress cloud picture by using the finite element model;
and step six, loading the stress cloud chart data into fatigue analysis software, inputting the equivalent density, the Poisson ratio, the equivalent elastic modulus and a reference S-N curve, and calculating the fatigue life value of the polytetrafluoroethylene hose based on a preset fatigue load course.
2. The method for calculating the pulse life of the polytetrafluoroethylene hose for the aircraft engine according to claim 1, wherein in the first step, the equivalent density p is calculated by the following formula:
Figure QLYQS_1
wherein L is the length of the polytetrafluoroethylene hose, d 1 Is the inner diameter of a polytetrafluoroethylene hose, d 2 Is the outer diameter of the polytetrafluoroethylene hose, and M is the mass of the polytetrafluoroethylene hose.
3. The method for calculating the pulse life of a polytetrafluoroethylene hose for an aircraft engine according to claim 1, wherein in the second step, the predetermined multiple is 1.5 times.
4. The method for calculating the pulse life of a polytetrafluoroethylene hose for an aircraft engine according to claim 1, wherein the polytetrafluoroethylene hose in the second step is fixed in the same manner as the polytetrafluoroethylene hose in the engine-mounted state in the first step.
5. The pulse life calculation method for teflon hoses for aircraft engines of claim 1, wherein in step three, the first order natural frequency of the teflon hose is measured by a force hammer impact method.
6. The method of calculating an impulse life of a teflon hose for an aircraft engine according to claim 1, wherein in step four, in the finite element model, the boundary conditions are the same as the engine installation state, the internal pressure is a predetermined multiple of the maximum operating pressure of the engine, the equivalent elastic modulus is set to vary from 10MPa to 1000MPa, and the equivalent elastic modulus is searched by the bisection method so that the first-order natural frequency calculated at the equivalent elastic modulus is the same as the measured first-order natural frequency.
7. The method for calculating the pulse life of the polytetrafluoroethylene hose for the aircraft engine according to claim 1, wherein in step four, the selected parameter includes a poisson's ratio when constructing the finite element model of the polytetrafluoroethylene hose, wherein the poisson's ratio is 3.4 when the inner tube of the polytetrafluoroethylene hose is a straight tube, and the poisson's ratio is 4.2 when the inner tube of the polytetrafluoroethylene hose is a corrugated tube.
8. The method for calculating the pulse life of the polytetrafluoroethylene hose for the aircraft engine according to claim 1, wherein in the sixth step, the reference S-N curve is an S-N curve selected from a group of S-N curves, the S-N curve being closest to the inner diameter of the polytetrafluoroethylene hose to be tested, and in the S-N curve, the ordinate is the logarithm of the life N and the abscissa is the stress value S.
9. The pulse life calculation method for the polytetrafluoroethylene hose for the aircraft engine according to claim 8, wherein step six is preceded by further modifying the S-N curve, the modifying comprising: and selecting a plurality of pipelines to carry out pulse test according to the maximum working pressure of the engine to obtain the pulse times, obtaining the maximum stress through a finite element model, and correcting the S-N curve according to the relationship between the pulse times and the maximum stress.
10. The pulse life calculation method for teflon hoses used for aircraft engines of claim 1 wherein in step six, the predetermined fatigue load history comprises a plurality of consecutive pulse load cycles, and the load in each pulse load cycle has a minimum value of 0.2 times the maximum working pressure of the engine and a maximum value of 1.5 times the maximum working pressure of the engine.
CN202210902437.9A 2022-07-29 2022-07-29 Pulse life calculation method for polytetrafluoroethylene hose for aircraft engine Active CN115358113B (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
CN202210902437.9A CN115358113B (en) 2022-07-29 2022-07-29 Pulse life calculation method for polytetrafluoroethylene hose for aircraft engine

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
CN202210902437.9A CN115358113B (en) 2022-07-29 2022-07-29 Pulse life calculation method for polytetrafluoroethylene hose for aircraft engine

Publications (2)

Publication Number Publication Date
CN115358113A CN115358113A (en) 2022-11-18
CN115358113B true CN115358113B (en) 2023-04-07

Family

ID=84031683

Family Applications (1)

Application Number Title Priority Date Filing Date
CN202210902437.9A Active CN115358113B (en) 2022-07-29 2022-07-29 Pulse life calculation method for polytetrafluoroethylene hose for aircraft engine

Country Status (1)

Country Link
CN (1) CN115358113B (en)

Citations (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN102567567A (en) * 2011-11-15 2012-07-11 北京宇航系统工程研究所 Finite element analysis based pipeline random-vibration fatigue life analyzing method
CN111079329A (en) * 2019-12-04 2020-04-28 中国直升机设计研究所 Fatigue life assessment method based on similar structure test

Family Cites Families (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN109885874B (en) * 2019-01-11 2022-12-23 华东理工大学 ABAQUS-based multi-axial creep fatigue prediction method

Patent Citations (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN102567567A (en) * 2011-11-15 2012-07-11 北京宇航系统工程研究所 Finite element analysis based pipeline random-vibration fatigue life analyzing method
CN111079329A (en) * 2019-12-04 2020-04-28 中国直升机设计研究所 Fatigue life assessment method based on similar structure test

Non-Patent Citations (3)

* Cited by examiner, † Cited by third party
Title
方红荣 等.基于有限元法的运载火箭管路随机振动疲劳寿命分析.导弹与航天运载技术.2017,(第04期),第107-110页. *
聂水湘 等.聚四氟乙烯软管组件耐久性初步研究.液压与气动.2014,(第8期),第88-94页. *
黄民锋 等.基于有限元法的汽车构件疲劳寿命分析.机械研究与应用.2008,(第02期),第57-60页. *

Also Published As

Publication number Publication date
CN115358113A (en) 2022-11-18

Similar Documents

Publication Publication Date Title
CN105651496B (en) A kind of hydraulic pipe fatigue life Index
CN106777457B (en) Reliability assessment software system for solid engine grain structure
CN114429060A (en) Method for assessing structure dislocation failure and service life prediction in fatigue vibration
CN111881564A (en) Method for predicting amplitude-variable fatigue life of mechanical structure
CN115358113B (en) Pulse life calculation method for polytetrafluoroethylene hose for aircraft engine
CN113919078A (en) Notch structure fatigue analysis method for coupling stress gradient under size effect
CN110287631B (en) L-shaped pipeline clamp system modeling method
CN115292925B (en) Method for evaluating working blade of single-crystal high-pressure turbine
CN111238804B (en) Test piece configuration method for over-rotation rupture test of aircraft engine rotor
CN115288849B (en) Reciprocating engine combustion chamber wear state evaluation method and device
CN115855654A (en) Multi-parameter graphical representation method for comprehensively evaluating mechanical property of structural material
CN103678775B (en) A kind of delivery pipe analysis for dynamic strength method
Brun et al. Valve performance and life of reciprocating compressors
Zhao et al. Vibration characteristics and power flow analysis of a constant cracked beam with general boundary conditions
CN103674521A (en) Compensator verification method based on working condition separating design
CN114112176B (en) Design method of external pipeline connected with surge pressure difference or pressure sensor
Rahman et al. Finite element based vibration fatigue analysis of a new twostroke linear generator engine component
Londhe et al. Finite element analysis of connecting rod and correlation with test
CN116429362B (en) Fatigue test method for engine pipeline structure
Vulić et al. Implementing SimulationX in the modelling of marine shafting steady state torsional vibrations
CN113962120A (en) Method for predicting ultimate pressure resistance of combustion chamber casing
Su et al. Cae virtual test of air intake manifolds using coupled vibration and pressure pulsation loads
CN118153183A (en) Dynamic stiffness design method of aeroengine pipeline based on response surface analysis
CN110119560B (en) Method for checking communication satellite soft waveguide strength based on curvature radius
CN115372182A (en) Accelerated life test method for polytetrafluoroethylene hose for aircraft engine

Legal Events

Date Code Title Description
PB01 Publication
PB01 Publication
SE01 Entry into force of request for substantive examination
SE01 Entry into force of request for substantive examination
GR01 Patent grant
GR01 Patent grant