CN115186391B - Load analysis method for large bypass ratio engine installation system - Google Patents
Load analysis method for large bypass ratio engine installation system Download PDFInfo
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- CN115186391B CN115186391B CN202210893171.6A CN202210893171A CN115186391B CN 115186391 B CN115186391 B CN 115186391B CN 202210893171 A CN202210893171 A CN 202210893171A CN 115186391 B CN115186391 B CN 115186391B
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- G—PHYSICS
- G06—COMPUTING; CALCULATING OR COUNTING
- G06F—ELECTRIC DIGITAL DATA PROCESSING
- G06F30/00—Computer-aided design [CAD]
- G06F30/10—Geometric CAD
- G06F30/15—Vehicle, aircraft or watercraft design
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- G—PHYSICS
- G06—COMPUTING; CALCULATING OR COUNTING
- G06F—ELECTRIC DIGITAL DATA PROCESSING
- G06F30/00—Computer-aided design [CAD]
- G06F30/10—Geometric CAD
- G06F30/17—Mechanical parametric or variational design
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- 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
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- 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
Abstract
The application belongs to the field of aeroengine design, and discloses a load analysis method of a large bypass ratio engine mounting system, wherein the load analysis method is characterized in that the load transmission path of the mounting system is determined, the force of each position of the mounting system can be calculated, the motorized load born by the mounting system can be calculated by determining the mass, the mass center and the moment of inertia of the whole engine and rotor parts of the engine, so that the corresponding pneumatic load is calculated, then the mechanical parameters of the stress points of the mounting system are calculated, the stress of each position of the mounting system is obtained, the mathematical model established in this way can accurately find out the load of each system affecting the mounting system and the load generated by each system, the load born by each system in the mounting system is balanced, and then the load of each system is distributed according to the space suction balance equation and the load matching relation of each system, and after each system can reach the required target value, the design is completed.
Description
Technical Field
The application belongs to the field of aeroengine design, and particularly relates to a load analysis method of a large bypass ratio engine mounting system.
Background
The large bypass is compared with the turbofan engine mounting system, a wing hanging mounting mode is adopted, and a redundant design is structurally carried out for ensuring safety, so that a load transmission path is changeable, meanwhile, as the engine is exposed outside a machine body, fan blades are large, load factors influencing the strength of the mounting structure are more, the mounting system can fix the engine (comprising all additional equipment, aircraft accessories, engine accessories and working fluid which are arranged on the engine) in all flight, take-off, landing and ground states, and can bear limited loads without harmful deformation and extreme loads without damage. When one of the connection points of the engine fails, the remaining mounting knots of the engine should be sufficient to support the engine.
Therefore, how to perform effective load analysis on a large bypass ratio engine mounting system is a problem to be solved.
Disclosure of Invention
The application aims to provide a load analysis method of a large bypass ratio engine mounting system, which aims to solve the problem that in the prior art, the large bypass ratio turbofan engine has more load factors influencing the strength of a mounting structure, so that effective load analysis is difficult to perform.
The technical scheme of the application is as follows: a method of analyzing load of a large bypass ratio engine mounting system, comprising: determining a mounting system load transfer path; determining the mass, mass center and rotational inertia of the whole engine and rotor components; determining mechanical parameters of stress points of the mounting system; establishing a load analysis mathematical model; analyzing load influence factors influencing the installation system and calculating each load one by one; matching the load relation, carrying out statistical analysis on each load influence factor and combining the load influence factors; and determining a final installation system load analysis result.
Preferably, the load influencing factors influencing the mounting system include: the side wind load generated by the air inlet channel; motorized conditions; the matching relation between the pneumatic working condition and the motor working condition is established according to the pneumatic working condition; the load of the thrust reverser on the mounting system; loads generated to the mounting system after a rotor blade fracture; the rotor card lags the load generated on the mounting system.
Preferably, the method for establishing the load analysis mathematical model comprises the following steps: and forming a space static force system according to each parameter of the installation system, listing a space force system balance equation according to the Darby principle, and establishing a load analysis mathematical model according to the space force system balance equation.
According to the load analysis method for the large bypass ratio engine mounting system, the force at each position of the mounting system can be calculated by determining the load transmission path of the mounting system, the motorized load which can be borne by the mounting system can be calculated by determining the mass, the mass center and the rotational inertia of the whole engine and rotor components, so that the corresponding pneumatic load is calculated, then the mechanical parameters of the stress points of the mounting system are calculated to obtain the stress of each position of the mounting system, the mathematical model established in this way can accurately find out each system affecting the mounting system and the load generated by each system, the balance of the forces of each load borne by the mounting system is kept, the load of each system is distributed according to the space suction balance equation and the load matching relation of each system, and after each system can reach the required target value, the design is completed.
Drawings
In order to more clearly illustrate the technical solution 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 merely some embodiments of the application.
FIG. 1 is a schematic diagram of the overall flow of the present application;
FIG. 2 is a graph of the lifting point force diagram of the thrust pull rod of the present application during normal operation;
FIG. 3 is a graph of the lifting point force after failure of the thrust rod of the present application.
Detailed Description
In order to make the objects, technical solutions and advantages of the present application become more apparent, 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 analyzing load of a large bypass ratio engine mounting system, as shown in fig. 1, comprising the steps of:
step S100, determining a load transmission path of an installation system;
the main installation section structure adopts a redundant design, and the thrust pull rod has two modes of normal operation and failure operation.
When the thrust pull rod works normally, the stress conditions of the lifting points are shown in the figures 2,1 and 3, the lifting points bear the force along the direction of the thrust pull rod, and the lifting points are equal in size; the hanging points 2 bear lateral and vertical forces, the hanging points 4, 5 and 6 bear forces along the direction of the auxiliary installation joint pull rod, and the stress calculation result of each point is positive as the direction specified in the figure 3, and is negative.
The main installation section thrust pull rod is not stressed after failure, the two points 1 and 3 are not stressed, the axial force of the engine is borne by the 2 lifting points, the 4, 5 and 6 lifting points bear the force along the direction of the auxiliary installation section pull rod, and the stress load is shown in figure 3, so that the structural stress is changed into two from one mode.
Step S200, determining mass diagrams, mass centers and rotational inertia of the whole engine and rotor components, wherein the parameters are used for analyzing the maneuvering load born by the installation system;
step S300, determining mechanical parameters of stress points of an installation system, wherein the structural size of the installation system comprises parameters such as inclination angles of pull rods;
step S400, establishing a load analysis mathematical model;
the method for establishing the load analysis mathematical model comprises the following steps: and forming a space static force system according to each parameter of the installation system, wherein the space static force system is established by loads in the three directions of X, Y, Z and bending moments corresponding to the three directions, a space force system balance equation is listed according to the Dallange principle, and a load analysis mathematical model is established according to the space force system balance equation.
The space force system balance equation consists of a crosswind load, a maneuvering load, a pneumatic load, a thrust load, a rotor blade fracture load, a rotor clamping stagnation generated load and the like, other factors for setting the space force system balance equation are known, are given by the existing test parameters, and the equation is the existing equation and is not described in detail.
S500, analyzing load influence factors influencing an installation system and calculating each load one by one;
load influencing factors that influence the mounting system include:
the side wind load generated by the air inlet channel;
load influence corresponding to the maneuvering condition;
analyzing the load influence corresponding to the pneumatic working condition, and matching the possible pneumatic working condition with the maneuvering working condition, if the load corresponding to the maneuvering working condition is larger, the pneumatic working condition with larger pneumatic load needs to be matched;
the thrust reverser is used for loading the mounting system, and when the load generated by the thrust reverser is large, the corresponding casing of the mounting system can bear the corresponding load during design;
loads generated to the mounting system after a rotor blade fracture;
the rotor card lags the load generated on the mounting system.
Step S600, matching the load relation, and carrying out statistical analysis and combination on each load influence factor; according to a space force system balance equation, unified arrangement analysis is carried out on a target value which can be achieved by each load, if a system corresponding to a certain load target value cannot complete the target, the system needs to be redesigned, for example, the target thrust generated by a thrust reverser is 150MPa on the premise of ensuring balance according to the space force system balance equation, and if the actually designed thrust reverser exceeds the target value, the newly designed thrust reverser needs to be subjected to secondary design; and if all the systems meet the target value requirement, completing statistical analysis and combination.
And step S700, determining a final load analysis result of the installation system, and then carrying out specific design according to the final load analysis result.
When load analysis of the installation system is carried out, the magnitude of force at each position of the installation system can be calculated by determining the load transmission path of the installation system, the motorized load born by the installation system can be calculated by determining the mass, the mass center and the rotational inertia of the whole engine and rotor components, so as to calculate the corresponding pneumatic load, then the mechanical parameters of the stress points of the installation system are calculated to obtain the stress at each position of the installation system, the mathematical model established in this way can accurately find out each system affecting the installation system and the magnitude of the load generated by each system on the installation system, the force of each load born by the installation system is kept balanced, and then the load magnitude of each system is distributed according to the space suction balance equation and the load matching relation of each system, and when each system can reach the required target value, the design is completed; if the system is not achieved, the corresponding system is redesigned.
The application has the following advantages:
1) The influence of the crosswind on the installation system is increased;
2) The matching relation between maneuver and air is increased;
3) The structural stress is changed into two from one mode, so that the structural reliability is improved;
4) The influence factors of abnormal loads such as blade flying and losing are considered in the structural load and strength analysis of the whole machine installation system for the first time.
The foregoing is merely illustrative of the present application, and the present application is not limited thereto, and any changes or substitutions easily contemplated by those skilled in the art within the scope of the present application should be included in the present application. Therefore, the protection scope of the present application shall be subject to the protection scope of the claims.
Claims (1)
1. A method of analyzing load of a large bypass ratio engine mounting system, comprising:
determining a mounting system load transfer path;
determining the mass, mass center and rotational inertia of the whole engine and rotor components;
determining mechanical parameters of stress points of the mounting system;
establishing a load analysis mathematical model;
analyzing load influence factors influencing the installation system and calculating each load one by one;
matching the load relation, carrying out statistical analysis on each load influence factor and combining the load influence factors;
determining a final installation system load analysis result;
load influencing factors that influence the mounting system include:
the side wind load generated by the air inlet channel;
motorized conditions;
the matching relation between the pneumatic working condition and the motor working condition is established according to the pneumatic working condition; according to a space force system balance equation, unified arrangement analysis is carried out on target values which can be achieved by each load, and if a system corresponding to a certain load target value cannot complete the target, the system needs to be redesigned;
the load of the thrust reverser on the mounting system;
loads generated to the mounting system after a rotor blade fracture;
the rotor card delays the load generated on the mounting system;
the method for establishing the load analysis mathematical model comprises the following steps: and forming a space static force system according to each parameter of the installation system, listing a space force system balance equation according to the Darby principle, and establishing a load analysis mathematical model according to the space force system balance equation.
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| CN202210893171.6A CN115186391B (en) | 2022-07-27 | 2022-07-27 | Load analysis method for large bypass ratio engine installation system |
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| CN202210893171.6A CN115186391B (en) | 2022-07-27 | 2022-07-27 | Load analysis method for large bypass ratio engine installation system |
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| CN115186391B true CN115186391B (en) | 2023-10-20 |
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| CN107563039A (en) * | 2017-08-28 | 2018-01-09 | 中国航空工业集团公司沈阳飞机设计研究所 | A kind of intensity layout design method of aircraft engine installation system |
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| CN113987861A (en) * | 2021-10-11 | 2022-01-28 | 南京航空航天大学 | Multi-parameter fatigue test spectrum compiling method based on local load state consistency |
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|---|---|---|---|---|
| US20150203215A1 (en) * | 2014-01-17 | 2015-07-23 | Eric T. Falangas | Early performance evaluation of conceptual flight and space vehicles |
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| CN106777499A (en) * | 2016-11-18 | 2017-05-31 | 云南电网有限责任公司电力科学研究院 | A kind of whole machine dynamic modelling method of dual-feed asynchronous wind power generator group |
| CN107563039A (en) * | 2017-08-28 | 2018-01-09 | 中国航空工业集团公司沈阳飞机设计研究所 | A kind of intensity layout design method of aircraft engine installation system |
| CN111173648A (en) * | 2020-01-03 | 2020-05-19 | 中国航发沈阳发动机研究所 | Ground test run method for aviation thrust vector engine |
| CN113987861A (en) * | 2021-10-11 | 2022-01-28 | 南京航空航天大学 | Multi-parameter fatigue test spectrum compiling method based on local load state consistency |
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